WO2013141928A1

WO2013141928A1 - Gas turbine with extended turbine blade stream adhesion

Info

Publication number: WO2013141928A1
Application number: PCT/US2012/071879
Authority: WO
Inventors: Robert E. Breidenthal; Joseph Colannino; Christopher A. Wiklof
Original assignee: Clearsign Combustion Corporation
Priority date: 2011-12-30
Filing date: 2012-12-27
Publication date: 2013-09-26
Also published as: EP2798173A4; WO2013141928A4; US20140208758A1; EP2798173A1

Abstract

A gas turbine may include turbine blades configured to improve stream adhesion by selectively attracting or reducing repulsion of charged particles carried by a combustion gas stream. According to an embodiment, a gas turbine may include a combustor configured to output a combustion gas stream, the combustion gas stream being controlled or driven to at least intermittently or periodically include charged particles having a first sign. For example the first sign may be positive during at least an instant. The gas turbine also includes at least one turbine configured to receive the combustion gas stream (carrying the charged particles at least intermittently or periodically). The turbine includes at least one turbine stage having turbine blades. Each turbine blade includes a repelling surface configured to be at least intermittently or periodically held or driven to a repelling voltage having a polarity the same as the charged particles having the first sign.

Description

GAS TURBINE WITH EXTENDED TURBINE BLADE

STREAM ADHESION

CROSS REFERENCE TO RELATED APPLICATIONS

The present application claims priority benefit from U.S. Provisional Patent Application No. 61/582,243, entitled "GAS TURBINE WITH EXTENDED

TURBINE BLADE STREAM ADHESION", filed December 30, 201 1 , which, to the extent not inconsistent with the disclosure herein, is incorporated by reference.

The present application is related to U.S. Non-Provisional Patent

Application No. 13/172,652, entitled "GAS TURBINE WITH COULOMBIC

THERMAL PROTECTION", filed December 12, 2012, which, to the extent not inconsistent with the disclosure herein, is incorporated by reference.

BACKGROUND

Gas turbines, which (for example) are used in terrestrial power generation and jet aircraft propulsion, include turbine blades that are design-constrained according to a maximum "lift" or rotational force that may be applied by any one blade under a given set of conditions. One limiting factor is a tendency for streamwise pressure variation along a low pressure side of the turbine blade to cause a near-surface velocity reversal with concomitant loss of stream adhesion to the turbine blade. The phenomenon of loss of adhesion may typically be referred to as flow separation. Flow separation may be regarded as a form of aerodynamic stall. The tendency to undergo flow separation may be most pronounced near trailing edges of the turbine blades. According to a related application, gas turbine blades may be configured to operate at higher than previously attainable combustion gas (free stream) temperatures through the use of Coulombic repulsion of charged particles in the combustion gas, combined with film-cooling. This may result in higher thermodynamic efficiency of the gas turbine. However, a higher free stream temperature may result in higher lift per turbine blade at relatively lower free stream velocity. This greater lift at lower velocity may increase streamwise pressure variations along the low pressure side of the turbine blade, and hence (absent redesign of turbine blade aerodynamics) may be associated with an increased propensity for flow separation .

Moreover, the Coulombic repulsion itself may tend to urge the free stream away from surfaces of the turbine blade, and further add to flow separation, especially on the low pressure side of the turbine blade.

Additionally, the power output range (dynamic range) of a gas turbine may be related to an allowable range of combustion gas volume delivered to the turbine at a given rotational rate of the rotor, which (for a given cross-sectional area) can be related to a range of mass flows at which a given turbine

blade/stator aerodynamic design will work most efficiently. Just as an airplane wing will stall at low velocities, corresponding to a high angle of attack, and operate less efficiently at velocities that differ significantly from a designated cruise velocity, turbine blades may suffer similar flow separation at extremes of dynamic range.

Moreover, flow separation effects may force gas turbines to use a relatively large number of stages to extract all power. More stages negatively affect capital cost, weight, and size of the gas turbine (particularly the length of the rotor shaft).

What is needed is a gas turbine that can operate with a higher combustion gas temperature without requiring turbine blade redesign, can exhibit larger dynamic range, have a lower capital cost, have a lower weight, and/or have a reduced size compared to previous gas turbines. SUMMARY

According to an embodiment, a gas turbine may include a combustor configured to output a combustion gas stream, the combustion gas stream being controlled or driven to at least intermittently or periodically include charged particles having a first sign. For example the first sign may be positive during at least an instant. The gas turbine also includes at least one turbine configured to receive the combustion gas stream (carrying the charged particles at least intermittently or periodically). The turbine includes at least one turbine stage having turbine blades. Each turbine blade includes a repelling surface

configured to be at least intermittently or periodically held or driven to a repelling voltage having a polarity the same as the charged particles having the first sign. At least some turbine blades also include an adhesion surface configured to be at least intermittently or periodically held, driven, or in equilibrium to an adhesion voltage or charge having lower magnitude than or opposite polarity from the repelling voltage. This may cause a reduced net force of repulsion, the reduction of which may improve boundary layer and free stream adhesion. FIG. 3A shows an example.

An air channel may be configured to deliver film-cooling air adjacent to the repelling surface of the turbine blade.

According to another embodiment, a method of operating a gas turbine includes providing a combustion gas stream at least intermittently or periodically carrying charged particles having a first sign; converting thermodynamic energy to rotational energy with turbine blades; at least intermittently or periodically applying Coulombic repulsion to the charged particles from a repelling portion of each turbine blade by applying a repelling voltage to the repelling portion; and at least intermittently or periodically applying reduced Coulombic repulsion from or increased Coulombic attraction to an adhesion portion of each turbine blade by at least one of shielding the Coulombic repulsion caused by the repelling voltage or by applying an adhesion voltage to attract the charged particles to the adhesion portion of the turbine blade.

The method may include providing film-cooling air adjacent to at least the repelling portion of the turbine blade.

According to an embodiment, a turbine blade includes a repelling surface configured to be at least intermittently or periodically held or driven to a repelling voltage and an adhesion surface configured to be at least intermittently or periodically held, driven, or in equilibrium to an adhesion voltage or charge having lower magnitude than or opposite polarity from the repelling voltage. The turbine blade may include a gas channel configured to deliver film-cooling gas adjacent to at least the repelling surface. The adhesion surface may include an electrical insulator disposed adjacent to the repelling surface and an electrical conductor or semiconductor disposed adjacent to the electrical insulator.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a block diagram of a gas turbine, according to an embodiment. FIG. 2 is a diagram illustrating cascaded momentum transfer from

Coulombically repelled particles to neutral particles, according to an embodiment.

FIG. 3A is a streamwise sectional diagram of a turbine blade configured for extended free stream adhesion, according to an embodiment.

FIG. 3B is a diagram showing fluid velocities and free stream adhesion over the turbine blade of FIG. 3A, according to an embodiment.

FIG. 4 is a diagram from an A-A view illustrated on FIG. 3A including an adhesion surface having a spanwise varying adhesion surface coupling

efficiency, charge/voltage, or area, according to an embodiment.

FIG. 5 is a span-wise B-B view of portions of a repelling surface and an adhesion surface of the turbine blade of FIGS. 3A and 4, according to an embodiment. FIG. 6 is a span-wise B-B view diagram of portions of a repelling surface and an adhesion surface of the turbine blade of FIGS. 3A and 4, according to another embodiment.

DETAILED DESCRIPTION

In the following detailed description, reference is made to the

accompanying drawings, which form a part hereof. In the drawings, similar symbols typically identify similar components, unless context dictates otherwise. The illustrative embodiments described in the detailed description, drawings, and claims are not meant to be limiting. Other embodiments may be utilized, and other changes may be made, without departing from the spirit or scope of the subject matter presented here.

FIG. 1 is a block diagram of a gas turbine 101 , according to an

embodiment. The gas turbine 101 includes a compressor 1 12 configured to compress air, the compressed air then entering a combustor 1 14. Fuel is burned in the combustor 1 14 to raise the temperature of the air and produce combustion products. The hot combustion products exit the combustor 1 14 and travel through a turbine 1 16. The turbine 1 16 includes turbine blades attached to a shaft 1 18. The combustion gases impinging on the turbine blades cause rotation of the shaft 1 18, which provides power to the compressor 1 12. The shaft 1 18 may also be coupled to fan blades (such as in an aircraft jet engine, not shown) or an electrical power generator or alternator (such as in a terrestrial power generator or aircraft auxiliary power unit (APU), not shown).

Fuel is introduced to the combustor 1 14 through one or more nozzles 120. The combustor 1 14 includes a wall 122 that must be kept cool. Typically, the wall 122 may be cooled by introducing cool air through vents (not shown). The combustor wall 122 may also be cooled according to methods described herein. Turbine blade cooling air from the compressor may be admitted, such as through an air passage 124 formed by the shaft 1 18. The turbine blade cooling air provides cooling to the shaft 1 18 by forced convection, and travels into the turbine blades. Cooling of the turbine blades is described in greater detail in conjunction with FIGS. 2 and 3A. According to an embodiment, one or more electrode(s) 126 may be disposed near the fuel nozzle(s) 120. Optionally, the one or more electrode(s) 126 may be coextensive with at least a portion of the fuel nozzle(s) 120. The electrode(s) 126 may apply a continuous or modulated voltage potential near flame(s) anchored by the fuel nozzle(s) 120.

During combustion, a flame produces charged intermediate species or transition states. These charged species include free electrons, fuel and fuel fragments, oxygen radicals, etc. Conservation of charge dictates that positive and negative charges nominally balance such that the total charge is

approximately neutral. The electrode(s) 126 may attract charge of opposite sign. For example, the electrode(s) 126 may be held or modulated to a positive voltage, and may responsively attract electrons from the flame. Similarly, the electrode(s) 126 may be held or modulated to a negative voltage, which responsively removes positively charges species from the flame. The

electrode(s) 126 may be modulated across a positive and negative voltage range, may be modulated in voltage above and below a DC bias voltage, and/or may be held at a substantially constant DC bias voltage. According to

embodiments, the electrode(s) 126 may be modulated between relative ground and a positive voltage of a few hundred volts at a time-varying frequency of a few kilohertz up to a few hundred kilohertz. Higher or lower voltages may be used and/or higher or lower frequency may be used.

The effect of at least intermittently or periodically removing charged particles of one sign or polarity from the flame results in a charge imbalance that may be used to apply Coulombic forces on the combustion gas. The applied Coulombic forces may directly affect the movement of charged particles, and the charged particles, in turn, may transfer momentum to uncharged particles. As used herein, a "particle" may include an aerosol such as unburned fuel, a gas molecule, an ion, and/or an electron, for example. As will be described below, the applied Coulombic forces may be used to repel hot gas from temperature- sensitive surfaces, such as turbine blades, turbine inlet guide vanes, turbine stators, the turbine shaft, and/or the combustor wall.

The electrode(s) 126 may be voltage isolated from other portions of the gas turbine 101 by suitable clearances (e.g., "air gaps") or electrical insulators 128. A voltage source 134 may provide the voltage to the electrode(s) 126. The voltage source 134 may also apply a voltage to the combustor wall 122 and to the turbine 1 16 blades and optionally turbine shaft 1 18 via a voltage conduction circuit 130. The voltage conduction circuit 130 may include one or more electrical insulators 128. Optionally, the voltage source 134 may provide different voltages to the electrode(s) 126, combustor wall 122, and/or turbine 1 16 blades. The voltage source 134 may include a DC voltage source and/or a modulated voltage source.

Optionally, the number density of ions may be increased or the ions may be produced by a mechanism other than the electrode(s) 126 acting on the combustion reaction to produce a majority species. Increasing the number density of ions may be used to increase the Coulombic forces acting on the hot gas. Operating by a mechanism other than the electrode(s) 126 acting on the combustion reaction to produce a majority species may be used according to designer preferences.

According to an embodiment, an electrode (optionally, electrode(s) 126 or a different electrode, not shown) may be operated at sufficient voltage to generate a corona discharge upstream of the turbine blades. In another embodiment, an additive such as one or more alkali salt(s) may be included in the fuel. In another embodiment, an additive such as one or more alkali salt(s) may be injected into the combustor 1 14.

Approaches for producing or increasing an ion number density are described by Lawton and Weinberg in Electrical Aspects of Combustion, incorporated herein by reference. It is possible that alternative theories could be constructed to explain the conversion of Coulombic repulsion to electrostatic or electrodynamic

acceleration of the bulk region of the fluid. FIG. 2 is a diagram 201 illustrating cascaded momentum transfer from electrostatically-repelled particles to neutral particles, according to an embodiment. Throughout the description herein, it may be assumed that voltages are either too low to cause dielectric breakdown (arcing) or that passive or active voltage control will decrease voltages under conditions where dielectric breakdown or incipient dielectric breakdown occurs. While voltages and particle charges are shown as positive in FIG. 2, the same effect may be seen with negative voltages and negative particle charges (or, as will be described more fully below, sign-modulated similar charges). Accordingly, the principles illustrated by FIG. 2 may be applied to a system using one or more constant or modulated positive voltages, one or more constant or modulated negative voltages, or positive and negative voltages modulated in time. In most gas turbine systems, it may be assumed that each particle corresponds to a gaseous molecule, atom, or ion.

A body, such as a turbine blade 202, may be driven to or held at a voltage, VT, such as a positive voltage. A film-cooling layer 204 may include substantially only neutral particles 206. Neutral particles 206 may be regarded as not interacting with the positive voltage V_T of the body 202 (ignoring dipole

interactions). Accordingly, the film-cooling layer 204 may be substantially unaffected by Coulombic forces.

A bulk region 207, separated from the body 202 by the film-cooling layer 204, may include neutral particles 206 and charged particles 208. For purposes of description, charged particles 208 may be regarded as positively charged. The positively charged particles 208, 208a may be Coulombically

(electrostatically) repelled by the same sign voltage V_T of the body 202 and may be responsively accelerated along a path 209. The path 209 may be visualized as the positive particle 208 "falling" through a voltage gradient caused by the voltage V_T of the body 202. The path 209 (e.g., the mean free path 209) typically has a probable distance inversely proportional to density. The path 209 eventually intersects another particle 206, whereupon a collision 210 between the charged particle 208 and a second particle 206 causes momentum transfer from the charged particle 208 to the second particle 206. For an average elastic collision (or a particular elastic collision of favorable orientation), momentum of the charged particle 208 may be halved, and the momentum of the second particle 206 may be increased by the same amount.

For systems where charged particles 208 are present in low concentration (which corresponds to most or all embodiments described herein), most collisions 210 involving a charged particle 208 may be binary interactions between the charged particle 208 and a neutral particle 206. After the collision 210, momentum transferred to the neutral particle 206 causes it to travel a distance near a mean free path until it undergoes a collision 212 with another particle after a time approximating a mean time between collisions. For systems where charged particles 208 are present in low concentration, most collisions 212 involving momentum transfer from a neutral particle 206 may be binary interactions between the first neutral particle 206 and a second neutral particle 206'. For an average elastic collision, half the momentum of the first neutral particle 206 may be transferred to the second neutral particle 206'. The first neutral particle 206 and the second neutral particle 206' may then travel along respective paths until each collides with other respective neutral particles in collisions 212 and momentum is again transferred. The series of neutral particle collisions 212 thus distribute momentum originally received from the charged particle 208 across a large number of neutral particles 206 according to an exponential 2^N progression in a parallel process.

Meanwhile, the charged particle 208 is again accelerated responsive to

Coulombic interaction with the voltage V_T of the body 202, and accelerates along a path to another collision 210, whereupon the process is repeated as described above.

According to an illustrative embodiment, charged particles 208 may be present in the free stream (also referred to as a combustion gas stream) 207 at a concentration on the order of one to one-hundred parts per billion (ppb). According to the geometric momentum distribution described above, momentum may be transferred from one charged particle 208 to a majority of all particles 206, 208 in the free stream 207 in about 24 to 30 generations of collisions 210, 212 (2³⁰ > 1 X 10⁹, 2²³ > 8 X 10⁶). The amount of transferred momentum at each collision is a function of the voltage V_T of the body 202, the magnitude of charge carried by the charged particle 208, the density of the free stream 207 (and hence the mean free path length), and the distance from the surface of the body 202 to the charged particle 208 at the point of each collision 210.

Because Coulombic forces substantially do not act on particles in the film- cooling layer 204, the film-cooling layer 204 undergoes substantially no repulsion. Moreover, the Coulombic repulsion acting on the charge-carrying free stream 207 may be viewed as producing a partial vacuum in regions between the surface of the charged body 202 and the free stream 207. The film-cooling layer 204 may thus also be viewed as being held in contact with the surface of the body 202 by the partial vacuum produced by evacuation of charged particles 208.

Referring to FIG. 1 , an optional adhesion voltage lead 136 may provide an adhesion voltage to an adhesion surface of the turbine blades. The adhesion voltage will be explained more fully in conjunction with FIGS. 3A, 4, 5, and 6.

An optional counter-ion injection lead 138 may optionally provide charge of opposite sign to the charge imbalance in the gas stream, and thus allow the combustion reaction to proceed to completion. Optionally, the counter-ion injection lead 138 may be configured to inject the counter-ions after the first stage turbine blades, between later turbine stages, or at the outlet end of the turbine 1 16. The counter-ion injection lead may produce exhaust gas that is less reactive than a charged gas stream, thereby reducing environmental effects of the system described herein. The counter-ion injection lead may further be used to balance charges delivered by the voltage source 134, and thereby reduce power consumption and/or charge bleed to isolated system components.

FIG. 3A is a streamwise sectional diagram of a region 301 including a turbine blade 302 configured for Coulombic thermal protection from hot combustion gases, and extended free stream adhesion of the gases to the surface of the turbine blade 302, according to an embodiment. As described above, a combustion gas stream 207 may at least intermittently or periodically include charged particles 208. The turbine blade 302 may include a repelling surface 304 configured to be at least intermittently or periodically held or driven to a repelling voltage V_T. The repelling voltage V_T may typically be driven to a voltage having the same sign as a majority of charged particles 208 proximate to the turbine blade 302 such that repulsion of the hot combustion gas stream 207 occurs according to a mechanism similar to that described in conjunction with FIG. 2, or according to another mechanism.

A gas channel 306 may be configured to deliver film-cooling gas 204 adjacent to at least the repelling surface 304. For example, the gas channel 306 may be a first gas channel configured to deliver film-cooling gas through slots or holes 308 proximate a flow forward edge 310 of the repelling surface 304.

Nominally, the film-cooling gas 204 and the combustion gas stream 207 may travel along streamlines 312 parallel to the surface 304 of the turbine blade 302. Because streaming is parallel to the surface 304, the film-cooling gas 204 and the combustion gas 207 may tend to not mix. Moreover, the repulsion of the charged particles 208 by the repelling voltage V_T of the repelling surface 304 may tend to prevent mixing of the combustion gas 207 with the film-cooling gas 204.

A location 314 along the surface 304 may be characterized by a first pressure Pi, as shown in FIG. 3A. FIG. 3B is a diagram showing fluid velocities and possible flow separation over the turbine blade of FIG. 3A, according to an embodiment. Referring to FIG. 3B, fluid velocity near the surface 304 at the location 314 corresponding to the first pressure Pi may follow a function represented by the velocity curve 316. The velocity curve 316 conforms to a requirement that velocity v be zero at the surface 304. Velocity v represented by the velocity curve 316 is positive at all points not at the surface 304 and asymptotically approaches the free stream velocity v_F at locations removed from the surface 304. Referring to FIG. 3A, for a lifting body such as the turbine blade 302, the gas pressure over the low pressure surface (top surface) of the turbine blade 302 may increase with distance along the surface 304 such that a second pressure P₂ at a second point 318 on the low pressure surface is higher than the first pressure Pi at the first point 314 nearer the flow forward edge 310 of the turbine blade 302. In other words, Pi < P₂.

The system illustrated by FIGS 3A and 3B may be represented according to the Navier-Stokes partial differential residual: v dv/ds = (-1/p) dp/ds + u d²v/dy² where s is the streamwise axis,

y is the normal axis,

v is velocity along the streamwise axis,

p is density,

p is pressure, and

u is a second derivative constant.

For a case where non-streamwise velocity gradients and gradient curvatures are small compared to streamwise gradients, the equation reduces to: v dv/ds = (-1/p) dp/ds.

In other words, the change in streamwise velocity is nonlinear and negative with the increase in pressure along the stream path. For otherwise conventional turbine blade designs (e.g. absent "steps"), pressure may vary monotonically and increasing with distance along the turbine blade 302 beyond the minimum pressure point.

When dp/ds>0,

velocity v decreases as s increases. There may be conditions under which v is less than or equal to 0, a result of which is illustratively shown in FIGS. 3A and 3B. This corresponds to a flow separated velocity profile illustrated by a v<0 solution shown as the velocity curve 322 in FIG. 3B. For steady y-axis conditions, the velocity inversion in the velocity profile 322 may correspond to spanwise vortex shedding.

For cases where P₂ is sufficiently greater than Pi , the streamline 312 may lift off the surface 304 of the turbine blade 302 as indicated by a stall streamline 320. In fact, the streamline 320 may represent the outer edge of a region characterized by the spanwise vortex shedding. Such behavior may be referred to as an aerodynamic stall.

Referring again to FIG. 3B, aerodynamic stall may occur when a velocity profile 322 includes a portion near the surface 304 having a negative value. As shown, the velocity profile 322 represents a flow direction reversal at a small distance from the surface 304 up to a magnitude of -V_MAX- For comparison, a nominal velocity profile 316 at the location 314 is superimposed.

Referring again to FIG. 3A, according to embodiments, the turbine blade 302 includes an adhesion surface 324 configured to prevent the lift-off or stall behavior 320, and instead substantially keep the flow 312 in contact with the upper surface of the turbine blade 302, as illustrated by the streamline 326.

Referring to FIG. 3B, the adhesion surface 324 may act to create a velocity profile 328. The velocity profile 328 is "squished" such that velocity increases faster near the surface such that a measurable negative velocity is substantially avoided, and stall does not occur.

The adhesion surface 324 creates the velocity profile 328 and the streamline 326 by reducing or reversing the repulsion exerted by the repelling surface 304 across at least a portion of the turbine blade 302. The adhesion surface 324 is configured to be at least intermittently or periodically held, driven, or in equilibrium to produce an adhesion voltage V_A or charge having lower magnitude than or opposite polarity from the repelling voltage V_T.

As described above, the repelling surface 304 may be configured to repel the combustion gas stream 207 by Coulombic repulsion. The gas channel 308 may thus deliver the film-cooling gas 204 to a volume adjacent to the repelling surface 304 between the repelling surface 304 and the combustion gas stream 207. The Coulonnbic repulsion of the combustion gas stream 207 by the repelling surface 304 may help to maintain the relative positions of the repelling surface 304, the film-cooling gas 204, and the combustion gas 207, and thereby reduce turbine blade 302 heating and deterioration or failure.

According to embodiments, the adhesion surface 324 may act to shield the combustion gas 207 from the repelling action of the repelling surface 304 at locations prone to stall 318.

According to embodiments, the adhesion surface 324 may be configured as an electrical shield to shield the combustion gas stream 207 from the repelling voltage V_T applied to the repelling surface 304 of the turbine blade 302. The adhesion surface 324 may provide extended flow adhesion and reduce or substantially eliminate flow separation, as shown by the alternative, non- separated stream 326 and the "squished" velocity profile 328.

An electric field environment different than the electric field environment caused by V_T may be formed by the adhesion surface 324. For example, a conductor or semiconductor of the adhesion surface 324 (optionally as image charge balanced against charges deposited on an overlying insulator) may be driven or otherwise carry an equilibrium or pseudo-equilibrium voltage or charge deposited by the ionized combustion gas 207. For example, the charge or voltage V_A carried by the adhesion surface may be normally in equilibrium with the time-averaged charge(s) carried by the combustion gas. According to one view, this may be visualized as a Faraday cage shielding the electric field environment corresponding to adhesion flow 326. A charge 208b shielded from the repulsion voltage V_T and/or responsive to an adhesion voltage V_A may "feel" less Coulombic acceleration away from the surface 304 than the acceleration felt by charges 208a operatively coupled to the repulsion voltage V_T.

According to an embodiment, the adhesion surface 324 may be

configured to be in charge equilibrium or pseudo-equilibrium with the charged combustion gas stream 207 such that the adhesion surface 324 is charged to an adhesion voltage V_A having an average value lower in magnitude than an average of the turbine blade 302 repelling voltage V_T. For example, at least one of the sign of the charged particles 208 or the concentration of the charged particles 208 in the combustion gas 207 may be modulated responsive to modulation of voltage of the electrode(s) by the voltage source (FIG. 1 , 126, 134) according to a desired equilibrium or pseudo-equilibrium voltage.

According to other embodiments, the adhesion surface 324 may be driven to or held at an adhesion voltage V_A opposite in polarity from the repelling voltage V_T of the repelling surface 304. Referring to FIG. 1 , the voltage source 134 may apply such an attraction voltage to the adhesion surface 324. A charged particle 208b proximate the adhesion surface 324 may be intermittently or periodically attracted to or receive a reduced repulsion from an adhesion voltage V_A. For example, the adhesion voltage V_A may be at ground, may be opposite in sign (polarity) from the charged particle 208b, or as described above, at a reduced magnitude compared to the repelling voltage V_T.

According to an embodiment, the adhesion voltage V_A may be modulated in phase with a variation in passing charged particle 208 concentration and/or sign. The phase may optionally be selected responsive to mass flow rate, fuel burn rate, and/or flow velocity of the combustion gas 207. According to another embodiment, the adhesion voltage V_A may follow a phase-delayed varying equilibrium with a concentration and/or sign of passing charged particles 208.

FIG. 4 illustrates an embodiment 401 from an A-A view illustrated on

FIG. 3A including an adhesion surface 324 having a spanwise varying adhesion surface coupling efficiency, charge/voltage, or area. Areas 402 may be extended into or past regions of the adhesion surface 324. The areas 402 may be an extension of the repelling surface 304, for example. A reduced repelling force and/or increased attracting (adhesion) force felt by a charge 208a when proximate the adhesion surface 324 in combination with repelling force felt by a charge 208 may tend to cause a spanwise acceleration variation that is conducive to forming streamwise vortices 404. Streamwise vortices may tend to have desirable aerodynamic effects compared to spanwise vortices.

Various physical embodiments of the adhesion surface 324 are

contemplated. According to embodiments, the adhesion surface 324 may be configured to apply at least reduced Coulonnbic repulsion on the combustion gas stream 207 compared to the repelling surface 304. As illustrated in FIGS. 4-6, the adhesion surface 324 may include a spanwise variation in applied voltage, charge, or area configured to promote streamwise vortex 404 generation.

According to an embodiment, the adhesion surface 324 may be

configured to apply Coulombic attraction to the combustion gas stream 207. For example, a gas turbine 101 (FIG. 1 ) may include a voltage source 134

operatively coupled to the adhesion surface 324 and configured to provide an adhesion voltage to the adhesion surface 324. The turbine blade 302 may include an electrical lead (not shown) operatively coupled to the adhesion surface 324, the electrical lead being configured to conduct a voltage to at least a portion of the adhesion surface 324. The electrical lead may receive the adhesion voltage from the voltage source 134.

The adhesion surface 324 may be shaped to occupy a void 406 defined by the repelling surface 304. The adhesion surface 324 may include an electrical insulator 408 adjacent to one or more voids 406 defined by the repelling surface 304. An electrical conductor or semiconductor 410, operable as an adhesion electrode, may be disposed adjacent to the electrical insulator 408. For example, the electrical conductor or semiconductor (adhesion electrode) 410 may be disposed in a recess or void 412 defined by the electrically insulating material 408. A second electrical insulator or semiconductor portion 408 may be disposed over the electrical conductor or semiconductor 410 forming the adhesion electrode. In such an arrangement, the adhesion electrode 410 may be referred to as "buried". According to other embodiments, the adhesion electrode 410 may be exposed.

The adhesion surface 324 may comprise at least a flow rearward portion 330 of a low pressure side of the turbine blade 302. The repelling surface 304 may include substantially the remainder of the surface of the turbine blade 302. According to embodiments, the repelling surface 304 may include at least a flow forward portion of a low pressure side of the turbine blade 302 and at least a portion of a high pressure side of the turbine blade 302. Referring to FIGS. 1 and 2, the voltage source 134 may be configured to cause modulation of at least one of a sign or concentration of charged particles 208 in the combustion gas stream 207. The voltage source 134 may be configured to select the modulation to cause a selected equilibrium voltage carried by the adhesion surface 324. The voltage source may optionally be configured to apply a substantially constant or modulated adhesion voltage to the adhesion surface 324 of the turbine blade 302.

Referring again to FIG. 4, the adhesion surface 324 may include a

"buried" adhesion electrode 410, wherein the insulator 408 covers the conductor or semiconductor forming the adhesion electrode 410. According to other embodiments, the adhesion electrode 410 may include an exposed upper surface (as shown in FIG. 3A).

According to embodiments, tantalum (Ta) may form at least a portion or alloy of the adhesion electrode 410. Tantalum may be advantageous due to its relatively high electrical opacity.

As described above, the adhesion surface 324 may include a spanwise variation in area with regions having relatively high area and regions having relatively low area. According to other embodiments, the adhesion surface 324 may be configured to support a spanwise variation in applied voltage or charge, or a spanwise variation in coupling efficiency to the combustion gas 207.

Various arrangements are contemplated. FIG. 5 is a span-wise B-B view of portions of a repelling surface 304 and an adhesion surface 324 of the turbine blade of FIGS. 3A and 4, according to an embodiment wherein the adhesion surface 324 has a spanwise variation in area. FIG. 6 is a span-wise B-B view of a portion of the turbine blade of FIGS. 3A and 4 according to another

embodiment wherein the adhesion surface 324 has a spanwise variation in area. The spanwise variations in area depicted in FIGS. 5 and 6 may also help analogously describe the effect of a spanwise variation in voltage, charge, and/or coupling efficiency.

FIG. 5 illustrates an embodiment 501 wherein the area of the adhesion surface 324 is varied spanwise by a serpentine variation in the position of the adhesion surface 324 leading edge. A void may be machined in the surface 304 of the turbine blade 302, and an insulator 408 applied therein. A void may then be machined in the insulator 408 surface and an adhesion electrode 410 disposed in the insulator void.

Streamlines superimposed over the adhesion surface indicate relative combustion gas flow over the turbine blade surface. Streamwise vortices 404 may be set up by a difference between repulsion of the charged particles 208 from the repelling surface 304 and the adhesion electrode 410.

FIG. 6 illustrates an alternative embodiment wherein the leading edge of the adhesion electrode 410 is not varied, but wherein a plurality of discontinuous regions of repelling surface 304 are arranged to potentiate the formation of streamwise vortices 404. According to other embodiments (not shown), the adhesion surface and/or the adhesion electrode 410 may include a plurality of discontinuous regions.

While various aspects and embodiments have been disclosed herein, other aspects and embodiments are contemplated. The various aspects and embodiments disclosed herein are for purposes of illustration and are not intended to be limiting, with the true scope and spirit being indicated by the following claims.

Claims

CLAIMS What is claimed is:

1 . A gas turbine, comprising:

a combustor configured to output a combustion gas stream at least intermittently or periodically including charged particles having a first sign; and a turbine configured to receive the combustion gas stream and including at least one turbine stage having turbine blades, each turbine blade of the at least one stage including:

a repelling surface configured to be at least intermittently or periodically held or driven to a repelling voltage having a polarity the same as the charged particles having the first sign, and

an adhesion surface configured to be at least intermittently or periodically held, driven, or in equilibrium to an adhesion voltage or charge having lower magnitude than or opposite polarity from the repelling voltage.

2. The gas turbine of claim 1 , wherein each turbine blade further comprises: an air channel configured to deliver film-cooling air adjacent to the repelling surface.

3. The gas turbine of claim 2, wherein the repelling surface is configured to repel the combustion gas stream by Coulombic repulsion; and

wherein the film-cooling air occupies a volume adjacent to the repelling surface between the repelling surface and the combustion gas stream.

4. The gas turbine of claim 1 , wherein the adhesion surface is configured to apply at least reduced Coulombic repulsion on the combustion gas stream compared to the repelling surface.

5. The gas turbine of claim 1 , wherein the adhesion surface is configured to apply Coulombic attraction to the combustion gas stream.

6. The gas turbine of claim 1 , wherein the adhesion surface includes a spanwise variation in applied voltage, charge, or area configured to promote streamwise vortex generation.

7. The gas turbine of claim 1 , further comprising:

a voltage source operatively coupled to the adhesion surface and configured to provide the adhesion voltage to the adhesion surface.

8. The gas turbine of claim 1 , wherein the adhesion surface is configured as an electrical shield to shield the combustion gas stream from the repelling voltage.

9. The gas turbine of claim 1 , wherein the adhesion surface includes is shaped to occupy a void defined by the repelling surface.

10. The gas turbine of claim 1 , wherein the adhesion surface further comprises:

an electrical insulator adjacent to one or more voids defined by the repelling surface; and

an electrical conductor or semiconductor adjacent to the electrical insulator.

1 1 . The gas turbine of claim 1 , wherein the adhesion surface further comprises:

in a recess or void defined by the repelling surface, an electrically insulating material; and

in a recess or void defined by the electrically insulating material, an electrically conductive or semiconductive adhesion electrode.

12. The gas turbine of claim 1 1 , wherein the electrically conductive or semiconductive adhesion electrode is configured to be in charge equilibrium or pseudo-equilibrium with the charged combustion gas stream.

13. The gas turbine of claim 12, wherein the electrically conductive or semiconductive adhesion electrode is configured to be charged to an average voltage lower in magnitude than an average of the turbine blade repelling voltage.

14. The gas turbine of claim 12, wherein at least one of the sign of the charged particles or the concentration of the charged particles is modulated according to a desired equilibrium or pseudo-equilibrium voltage.

15. The gas turbine of claim 1 , wherein the adhesion surface comprises at least a flow rearward portion of a low pressure side of the turbine blade.

16. The gas turbine of claim 15, wherein the repelling surface includes substantially the remainder of the surface of the turbine blade.

17. The gas turbine of claim 1 , wherein the repelling surface includes at least a flow forward portion of a low pressure side of the turbine blade and at least a portion of a high pressure side of the turbine blade.

18. The gas turbine of claim 1 , further comprising:

a gas turbine controller, configured to cause modulation of at least one of a sign or concentration of charged particles in the combustion gas stream.

19. The gas turbine of claim 18, wherein the gas turbine controller is configured to select the modulation to cause a selected equilibrium voltage carried by the adhesion surface.

20. The gas turbine of claim 1 , further comprising:

a gas turbine controller configured to apply a substantially constant or modulated adhesion voltage to the adhesion surface of the turbine blade.

21 . The gas turbine of claim 1 , wherein each turbine blade further comprises: a first air channel configured to deliver film-cooling air through slots or holes proximate a flow forward edge of the repelling surface.

22. The gas turbine of claim 21 , wherein each turbine blade further comprises: a second air channel configured to deliver cooling air through slots or holes proximate the adhesion surface.

23. The gas turbine of claim 22, wherein the adhesion surface includes a spanwise variation in area with regions having relatively high area and regions having relatively low area; and

wherein the slots or holes proximate the adhesion surface are aligned with or preferentially distributed near the regions having relatively low area and are configured to impart upward momentum on the combustion gas stream and on film-cooling air flowing over the slots or holes;

whereby the slots or holes proximate the adhesion surface and the spanwise variation in area of the adhesion surface are configured to cooperate to promote streamwise vortex generation.

24. The gas turbine of claim 23, further comprising:

a charge source configured to insert charged particles having the first sign into the second air channel at least when the charged particles having the first sign in the combustion gas are proximate the turbine blade.

25. The gas turbine of claim 22, wherein the adhesion surface includes a spanwise variation in area include regions having relatively high area and regions having relatively low area; and

wherein the slots or holes proximate the adhesion surface are aligned with or preferentially distributed near the regions having relatively high area.

26. The gas turbine of claim 25, further comprising:

electrical insulation to electrically isolate the second air channel from portions of the turbine blade carrying the repelling voltage; and

a charge source configured to insert charged particles having a second sign opposite in polarity to the first sign into the second air channel at least when the charged particles having the first sign in the combustion gas are proximate the turbine blade;

whereby the charged particles having the second sign flowing through slots or holes proximate the adhesion surface and the spanwise variation in area of the adhesion surface are configured to cooperate to promote streamwise vortex generation.

27. The gas turbine of claim 1 , further comprising:

an electrode located upstream of the turbine configured to be driven to a voltage sufficient to undergo corona discharge and at least intermittently or periodically add charged particles having the first sign or a second sign different than the first sign to the combustion gas stream.

28. The gas turbine of claim 1 , wherein the combustor is configured to burn a fuel containing an additive to increase the production of the charged particles having the first sign.

29. A method of operating a gas turbine, comprising: providing a combustion gas stream at least intermittently or periodically carrying charged particles having a first sign;

converting thermodynamic energy to rotational energy with turbine blades; at least intermittently or periodically applying Coulombic repulsion to the charged particles from a repelling portion of each turbine blade by applying a repelling voltage to the repelling portion; and

at least intermittently or periodically applying reduced Coulombic repulsion from or increased Coulombic attraction to an adhesion portion of each turbine blade surface by at least one of shielding the Coulombic repulsion caused by the repelling voltage or by applying an adhesion voltage to the adhesion portion of the turbine blade surface.

30. The method of operating a gas turbine of claim 29, further comprising: delivering film-cooling gas adjacent to at least the repelling portion.

31 . The method of operating a gas turbine of claim 30, wherein the Coulombic repulsion does not apply a force directly to the film-cooling gas.

32. The method of operating a gas turbine of claim 30, wherein the film- cooling gas is caused to preferentially stream adjacent to the repelling portion of the turbine blade responsive to the Coulombic repulsion of the charged particles in the combustion gas stream.

33. The method of operating a gas turbine of claim 29, wherein at least intermittently or periodically applying reduced Coulombic repulsion from or Coulombic attraction to the adhesion portion of each turbine blade surface includes applying a spanwise variation in voltage of the adhesion portion.

34. The method of operating a gas turbine of claim 29, wherein at least intermittently or periodically applying reduced Coulombic repulsion from or Coulonnbic attraction to an adhesion portion of each turbine blade surface includes applying a spanwise variation in charge carried by the adhesion surface.

35. The method of operating a gas turbine of claim 29, wherein the adhesion portion includes a spanwise variation in area; and

wherein at least intermittently or periodically applying reduced Coulombic repulsion from or Coulombic attraction to an adhesion portion of each turbine blade surface includes applying a spanwise variation in repelling voltage responsive to the spanwise variation in adhesion area.

36. The method of operating a gas turbine of claim 29, wherein at least intermittently or periodically applying reduced Coulombic repulsion from or Coulombic attraction to an adhesion portion of each turbine blade surface includes at least intermittently or periodically applying a spanwise varying reduced Coulombic repulsion from or Coulombic attraction to an adhesion portion of each turbine blade surface.

37. The method of operating a gas turbine of claim 36, wherein the spanwise variation in reduced Coulombic repulsion from or Coulombic attraction to the adhesion portion further cooperates with an aerodynamic response of each turbine blade to cause streamwise vortices to form proximate a flow rearward portion of each turbine blade.

38. The method of operating a gas turbine of claim 37, wherein the

streamwise vortices correspond to a spatially periodic spanwise increase in adhesion of the combustion gas to each turbine blade.

39. The method of operating a gas turbine of claim 29, wherein providing a combustion gas stream at least intermittently or periodically carrying charged particles having a first sign includes modulating charged particle concentration or charged particle concentration and sign; and wherein applying a repelling voltage to the repelling portion of each turbine blade includes modulating the repelling voltage synchronously with the

modulated charged particle concentration or charged particle concentration and sign proximate each turbine blade.

40. The method of operating a gas turbine of claim 39, wherein at least intermittently or periodically applying reduced Coulombic repulsion from or a Coulombic attraction to the adhesion portion of the turbine blade surface includes maintaining a time-averaged equilibrium or pseudo-equilibrium with the modulated charged particle concentration or charged particle concentration and sign in the combustion gas.

41 . The method of operating a gas turbine of claim 39, wherein at least intermittently or periodically applying reduced Coulombic repulsion from or a Coulombic attraction to the adhesion portion of the turbine blade surface includes holding the adhesion portion of the turbine blade surface at ground or modulating the adhesion portion of the turbine blade surface to one or more voltages opposite in sign from the combustion gas charge proximate the turbine blade.

42. The method of operating a gas turbine of claim 39, wherein at least intermittently or periodically applying reduced Coulombic repulsion from or a Coulombic attraction to the adhesion portion of the turbine blade surface includes modulating a voltage carried by the adhesion portion of the turbine blade surface inversely with a combustion gas charge concentration proximate the turbine blade.

43. The method of operating a gas turbine of claim 29, wherein at least intermittently or periodically applying Coulombic repulsion to the charged particles from the repelling portion of the turbine blade surface includes modulating the repelling portion of the turbine blade surface to one or more voltages synchronously with a charge concentration or charge concentration and sign in the combustion gas proximate the turbine blade.

44. The method of operating a gas turbine of claim 43, wherein the charged particles in the combustion gas stream proximate the turbine blade and the repelling voltage are the same sign; and

wherein the repelling voltage is varied synchronously and inversely with the charged particle concentration.

45. The method of operating a gas turbine of claim 43, wherein the charged particles in the combustion gas stream proximate the turbine blade and the repelling voltage are opposite signs; and

wherein the repelling voltage is varied synchronously with the charged particle concentration.

46. The method of operating a gas turbine of claim 29, further comprising: delivering first film-cooling gas through slots or holes proximate a flow forward edge of the repelling portion.

47. The method of operating a gas turbine of claim 29, further comprising: delivering second gas through slots or holes proximate the adhesion portion.

48. The method of operating a gas turbine of claim 47, wherein the adhesion portion includes a spanwise variation in area with regions having relatively high area and regions having relatively low area;

wherein the slots or holes proximate the adhesion portion are aligned with or preferentially distributed near the regions having relatively low area; further comprising:

imparting upward momentum on the combustion gas stream flowing over the slots or holes proximate the adhesion surface to cooperate with the spanwise variation in area of the adhesion portion to promote streamwise vortex

generation.

49. The method of operating a gas turbine of claim 48, further comprising: inserting charged particles having the first sign into the second gas at least when the charged particles having the first sign in the combustion gas are proximate the turbine blade.

50. The method of operating a gas turbine of claim 47, wherein the adhesion surface includes a spanwise variation in area include regions having relatively high area and regions having relatively low area; and

wherein delivering the second gas includes delivering the second gas through the slots or holes proximate the adhesion portion that are aligned with or preferentially distributed near the regions having relatively high area.

51 . The method of operating a gas turbine of claim 50, further comprising: inserting charged particles having a second sign opposite in polarity from the first sign into the second gas at least when the charged particles having the first sign in the combustion gas are proximate the turbine blade, the insertion of charged particles cooperating with the spanwise variation in area of the adhesion surface to promote streamwise vortex generation.

52. The method for operating a gas turbine of claim 29, further comprising: driving an electrode upstream of the turbine blades to a sufficient voltage to achieve corona discharge.

53. The method for operating a gas turbine of claim 29, further comprising: combusting a fuel containing an additive to produce the combustion gas stream, the additive being selected to increase a number density of the charged particles.

54. A turbine blade, comprising:

a repelling surface configured to be at least intermittently or periodically held or driven to a repelling voltage; and

55. The turbine blade of claim 54, further comprising a gas channel configured to deliver film-cooling gas adjacent to at least the repelling surface.

56. The turbine blade of claim 55, wherein the repelling surface is configured to repel a combustion gas stream by Coulombic repulsion; and

wherein the gas channel is configured to deliver the film-cooling gas to a volume adjacent to the repelling surface between the repelling surface and the combustion gas stream.

57. The turbine blade of claim 54, wherein the adhesion surface further comprises:

an electrical insulator disposed adjacent to the repelling surface; and an electrical conductor or semiconductor disposed adjacent to the electrical insulator.

58. The turbine blade of claim 57, wherein the adhesion surface further comprises:

a second electrical insulator or semiconductor disposed over the electrical conductor or semiconductor.

59. The turbine blade of claim 57, wherein the electrical conductor or semiconductor is configured to electrically shield a combustion gas stream from the repelling surface.

60. The turbine blade of claim 57, wherein the electrical conductor or semiconductor is configured to apply at least reduced Coulombic repulsion to a combustion gas stream compared to the repelling surface.

61 . The turbine blade of claim 54 wherein the adhesion surface is configured to apply at least reduced Coulombic repulsion on a combustion gas stream compared to the repelling surface.

62. The turbine blade of claim 54, wherein the adhesion surface is configured to apply Coulombic attraction to a combustion gas stream.

63. The turbine blade of claim 54, wherein the adhesion surface is configured to support a spanwise variation in applied voltage or charge.

64. The turbine blade of claim 54, wherein the adhesion surface includes a spanwise variation in area.

65. The turbine blade of claim 54, further comprising:

an electrical lead operatively coupled to the adhesion surface, the electrical lead being configured to conduct a voltage to at least a portion of the adhesion surface.

66. The turbine blade of claim 54, wherein the adhesion surface is shaped to occupy a void defined by the repelling surface.

67. The turbine blade of claim 54, wherein the adhesion surface further comprises:

in a recess or void defined by the repelling surface, and electrically insulating material; and

68. The turbine blade of claim 67, wherein the electrically conductive or semiconductive adhesion electrode is configured to be in charge equilibrium or pseudo-equilibrium with a charged combustion gas stream.

69. The turbine blade of claim 68, wherein the electrically conductive or semiconductive adhesion electrode is configured to be charged to an average voltage lower in magnitude than an average of a turbine blade repelling voltage.

70. The turbine blade of claim 54, wherein the adhesion surface comprises at least a flow rearward portion of a low pressure side of the turbine blade.

71 . The turbine blade of claim 70, wherein the repelling surface includes substantially the remainder of the surface of the turbine blade.

72. The turbine blade of claim 54, wherein the repelling surface includes at least a flow forward portion of a low pressure side of the turbine blade and at least a portion of a high pressure side of the turbine blade.

73. The turbine blade of claim 54, further comprising:

a first gas channel configured to deliver film-cooling gas through slots or holes proximate a flow forward edge of the repelling surface.

74. The turbine blade of claim 73, further comprising:

a second gas channel configured to deliver cooling gas through slots or holes proximate the adhesion surface.

75. The turbine blade of claim 74, wherein the adhesion surface includes a spanwise variation in area with regions having relatively high area and regions having relatively low area; and wherein the slots or holes proximate the adhesion surface are aligned with or preferentially distributed near the regions having relatively low area and are configured to impart upward momentum on a combustion gas stream and on film-cooling air flowing over the slots or holes.

76. The turbine blade of claim 75, further comprising:

a charge source configured to at least intermittently or periodically insert charged particles having a first sign into the second gas channel.

77. The turbine blade of claim 74, wherein the adhesion surface includes a spanwise variation in area include regions having relatively high area and regions having relatively low area; and

78. The turbine blade of claim 77, further comprising:

electrical insulation to electrically isolate the second air channel from portions of the turbine blade carrying the repelling voltage.

79. The turbine blade of claim 78, further comprising:

a charge source configured to insert charged particles having a second sign opposite in polarity from the repelling voltage at least intermittently or periodically.

80. The turbine blade of claim 74, wherein the adhesion surface includes a plurality of discontinuous regions.