US20130129498A1 - Diffuser, in particular for an axial flow machine - Google Patents
Diffuser, in particular for an axial flow machine Download PDFInfo
- Publication number
- US20130129498A1 US20130129498A1 US13/678,676 US201213678676A US2013129498A1 US 20130129498 A1 US20130129498 A1 US 20130129498A1 US 201213678676 A US201213678676 A US 201213678676A US 2013129498 A1 US2013129498 A1 US 2013129498A1
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- United States
- Prior art keywords
- diffuser
- steps
- flow
- recited
- cross sectional
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/601—Fluid transfer using an ejector or a jet pump
Definitions
- the present invention relates to the field of axial flow machines and more particularly to a diffuser.
- Diffusers which are arranged at the outlet of stationary gas turbines and which are to reduce the speed of flow of the gases coming out of the turbine and to bring about a build-up of pressure in order to improve the efficiency of the gas turbine, have been known for a long time in the prior art (see, for example, document EP 0 491 966 A1 or document US 2011/058939 A1 along with the attached FIG. 1 ).
- document EP 0 265 633 B1 proposes dividing the diffuser into several part diffusers in the radial direction by means of flow-conducting baffle plates.
- the inner tapering part of the diffuser is provided with a controllable Coanda flow by way of which the flow in the diffuser can be influenced in a favorable manner.
- the inner part of the diffuser, the hub, tapers downstream without forming a step. From an external source, a gas is guided toward a ring chamber in the hub and from there is injected by means of a number of slotted nozzles in the direction of flow of the hot exhaust gases parallel to the surface of the hub.
- said additional gas flow sucks in hot exhaust gas and deflects it in the direction of the hub.
- EP 0 265 633 B1 provides a sudden transition in the cross sectional area at the outlet of the diffuser which is designated as a Carnot diffuser.
- the present invention provides a diffuser for an axial flow machine.
- the diffuser has a transition from a ring channel having a first cross sectional area into an outlet space with a second, larger cross sectional area along a machine axis of the axial flow machine.
- the transition includes a plurality of steps.
- FIG. 1 shows the schematic design of a gas turbine with an exhaust gas diffuser, as is known
- FIG. 2 shows the inside design of a conventional Carnot diffuser
- FIG. 3 shows, in comparison to FIG. 2 , the inside design of a multi-step diffuser according to one exemplary embodiment of the invention
- FIG. 4 shows a perspective side view of a 2-step diffuser according to another exemplary embodiment of the invention.
- the invention provides a diffuser, in particular for an industrial gas turbine, which results, in a simple manner, in a further improvement in the overall efficiency of the gas turbine.
- An embodiment of the invention proceeds from a diffuser, in particular for an axial flow machine, preferably a stationary gas turbine, which diffuser transforms from a ring channel with a first cross sectional area into an outlet space with a second, larger cross sectional area along a machine axis. It is distinguished in that the transition is effected in several steps.
- a first development of an embodiment of the invention provides that the cross sectional area inside the diffuser is increased in two steps. Said diffuser is designed in a particularly simple manner.
- the diffuser is realized as a Carnot diffuser.
- a further development of an embodiment of the invention is distinguished in that the diffuser includes an outer casing and an inner casing, between which the medium flows through the diffuser, and that the steps are generated in the cross sectional area by diameter steps on the inner casing.
- an embodiment of the invention is characterized in that a ring-shaped, convexly curved guiding surface which tapers in diameter is arranged between two adjacent steps, and that on the upstream step of the two steps there is provided an annular passage, through which a gas flow is able to escape and to flow along the guiding surface in the form of a Coanda flow.
- the flow in the diffuser is able to be influenced in a favorable manner.
- the guiding surface is preferably arranged between the penultimate and the last step of the diffuser.
- Yet another development of an embodiment of the invention is characterized in that the diffuser is arranged at the outlet of an industrial gas turbine.
- FIG. 1 shows the schematic design of a gas turbine with an exhaust gas diffuser, as is known in the prior art.
- the gas turbine 10 shown in FIG. 1 includes a compressor 12 , which sucks in air by means of an air inlet 11 and compresses it. The compressed air is supplied to a combustion chamber 13 and there is used for the combustion of a fuel 14 .
- the resultant hot gas is expanded in a turbine 15 downstream under operating conditions and then flows through a diffuser 16 in order to slow down the speed of flow and to bring about a build-up of pressure.
- FIG. 2 shows a highly simplified representation of the inside design of a conventional Carnot diffuser.
- the diffuser 16 which is realized in a concentric manner with respect to a machine axis 31 , on the inlet side includes a ring channel 17 , by means of which the exhaust gas 19 of the turbine flows into the diffuser 16 .
- Connecting to the ring channel 17 with its comparatively small cross sectional area is an outlet space 21 , the cross sectional area of which is substantially larger for the flow.
- the transition between the ring channel 17 and the outlet space 21 is effected, in this example, by means of a sudden step 22 , which characterizes the diffuser 16 as a Carnot diffuser.
- Radial struts 18 which connect the inside part and the outside part of the diffuser 16 and at the same time serve for steering the flow, can be arranged in the ring channel 17 .
- the invention now proposes, according to the exemplary embodiment shown in FIG. 3 , to realize the transition between the ring channel 17 and the outlet space 21 in multiple steps in the case of a diffuser 20 .
- two steps 22 a and 22 b are provided for this purpose.
- a further step 22 c (shown by the broken line in FIG. 3 ) is optional.
- the number of steps, however, is not limited upward.
- the diameter jumps connected to the steps 22 a - c are limited in the exemplary embodiment in FIG. 3 to the inside part of the diffuser 20 . However, it is also just as conceivable to provide diameter jumps on the outside part of the diffuser.
- Such a multiply stepped inside contour produces a gain in the build-up of pressure which can be 0.1% of the turbine efficiency and in the case of a GT26 model gas turbine of the Applicant signifies a gain in capacity of almost half a megawatt.
- a corresponding diffuser looks, for example, as shown in FIG. 4 .
- the diffuser 20 a of FIG. 4 includes a ring-shaped outer casing 23 which surrounds an inner casing 24 in a concentric manner and together with the inner casing 24 defines a flow channel.
- the inner casing 24 and the outer casing 23 are connected by means of radial struts 25 .
- Two rings 26 and 27 which are stepped in diameter and by means of which the multiply stepped expansion of the diffuser 20 a is brought about, are arranged one behind the other in the axial direction at the outlet of the diffuser 20 a.
- the flow conditions in the diffuser can be influenced by means of a Coanda flow, as has been proposed, in principle, in document US 2011/058939 A1 mentioned in the introduction.
- a ring-shaped, convexly curved guiding surface 28 which tapers in diameter is arranged between two steps 22 a and 22 b in the case of a diffuser 20 b.
- an annular passage 29 On the upstream step of the two steps 22 a and 22 b is provided an annular passage 29 , through which a gas flow is able to escape and to flow along the guiding surface 28 in the form of a Coanda flow 30 .
- the gas feed for the Coanda flow 30 can be effected in different ways. Contrary to what the aforementioned document teaches, however, as claimed in the invention an external reference source for an actively injected additional gas is to be omitted.
- an external reference source for an actively injected additional gas is to be omitted.
- the Coanda flow is preferably inserted between the penultimate and the last step.
Abstract
Description
- Priority is claimed to German Patent Application No. DE 10 2011 118 735.2, filed on Nov. 17, 2011, the entire disclosure of which is hereby incorporated by reference herein.
- The present invention relates to the field of axial flow machines and more particularly to a diffuser.
- Diffusers which are arranged at the outlet of stationary gas turbines and which are to reduce the speed of flow of the gases coming out of the turbine and to bring about a build-up of pressure in order to improve the efficiency of the gas turbine, have been known for a long time in the prior art (see, for example,
document EP 0 491 966 A1 or document US 2011/058939 A1 along with the attachedFIG. 1 ). - In the past, various proposals have been made in order to improve the action of the diffuser at the outlet of a gas turbine and consequently the overall efficiency of the machine. Thus, among other things,
document EP 0 265 633 B1 proposes dividing the diffuser into several part diffusers in the radial direction by means of flow-conducting baffle plates. - In US 2011/058939 A1, already mentioned, to improve the flow conditions in the diffuser the inner tapering part of the diffuser is provided with a controllable Coanda flow by way of which the flow in the diffuser can be influenced in a favorable manner. The inner part of the diffuser, the hub, tapers downstream without forming a step. From an external source, a gas is guided toward a ring chamber in the hub and from there is injected by means of a number of slotted nozzles in the direction of flow of the hot exhaust gases parallel to the surface of the hub. As a result of the known Coanda effect, said additional gas flow sucks in hot exhaust gas and deflects it in the direction of the hub. The exhaust gas flow is accelerated there and adapts to the surface of the hub which tapers downstream. In order to achieve a desired influencing of the exhaust gas flow in the diffuser, up to 4% of the exhaust gas mass flow in additional gas has to be injected, which is equal to not insignificant expenditure.
- Contrary to this,
EP 0 265 633 B1 provides a sudden transition in the cross sectional area at the outlet of the diffuser which is designated as a Carnot diffuser. - Although said measures provide certain improvements in efficiency, the possibilities for exerting influence in the region of the diffuser have not been exhausted by a long way.
- In an embodiment, the present invention provides a diffuser for an axial flow machine. The diffuser has a transition from a ring channel having a first cross sectional area into an outlet space with a second, larger cross sectional area along a machine axis of the axial flow machine. The transition includes a plurality of steps.
- The present invention will be described in even greater detail below based on the exemplary figures. The invention is not limited to the exemplary embodiments. All features described and/or illustrated herein can be used alone or combined in different combinations in embodiments of the invention. The features and advantages of various embodiments of the present invention will become apparent by reading the following detailed description with reference to the attached drawings which illustrate the following:
-
FIG. 1 shows the schematic design of a gas turbine with an exhaust gas diffuser, as is known; -
FIG. 2 shows the inside design of a conventional Carnot diffuser; -
FIG. 3 shows, in comparison toFIG. 2 , the inside design of a multi-step diffuser according to one exemplary embodiment of the invention; -
FIG. 4 shows a perspective side view of a 2-step diffuser according to another exemplary embodiment of the invention; and -
FIG. 5 shows the inside design of a 2-step diffuser with Coanda control according to a further exemplary embodiment of the invention. - In an embodiment, the invention provides a diffuser, in particular for an industrial gas turbine, which results, in a simple manner, in a further improvement in the overall efficiency of the gas turbine.
- An embodiment of the invention proceeds from a diffuser, in particular for an axial flow machine, preferably a stationary gas turbine, which diffuser transforms from a ring channel with a first cross sectional area into an outlet space with a second, larger cross sectional area along a machine axis. It is distinguished in that the transition is effected in several steps.
- A first development of an embodiment of the invention provides that the cross sectional area inside the diffuser is increased in two steps. Said diffuser is designed in a particularly simple manner.
- As provided in another development of an embodiment of the invention, the diffuser is realized as a Carnot diffuser.
- A further development of an embodiment of the invention is distinguished in that the diffuser includes an outer casing and an inner casing, between which the medium flows through the diffuser, and that the steps are generated in the cross sectional area by diameter steps on the inner casing.
- Another development of an embodiment of the invention is characterized in that a ring-shaped, convexly curved guiding surface which tapers in diameter is arranged between two adjacent steps, and that on the upstream step of the two steps there is provided an annular passage, through which a gas flow is able to escape and to flow along the guiding surface in the form of a Coanda flow. As a result, the flow in the diffuser is able to be influenced in a favorable manner.
- The guiding surface is preferably arranged between the penultimate and the last step of the diffuser.
- Yet another development of an embodiment of the invention is characterized in that the diffuser is arranged at the outlet of an industrial gas turbine.
-
FIG. 1 shows the schematic design of a gas turbine with an exhaust gas diffuser, as is known in the prior art. Thegas turbine 10 shown inFIG. 1 includes acompressor 12, which sucks in air by means of an air inlet 11 and compresses it. The compressed air is supplied to acombustion chamber 13 and there is used for the combustion of afuel 14. The resultant hot gas is expanded in aturbine 15 downstream under operating conditions and then flows through adiffuser 16 in order to slow down the speed of flow and to bring about a build-up of pressure. -
FIG. 2 shows a highly simplified representation of the inside design of a conventional Carnot diffuser. In this case, thediffuser 16, which is realized in a concentric manner with respect to amachine axis 31, on the inlet side includes aring channel 17, by means of which the exhaust gas 19 of the turbine flows into thediffuser 16. Connecting to thering channel 17 with its comparatively small cross sectional area is anoutlet space 21, the cross sectional area of which is substantially larger for the flow. The transition between thering channel 17 and theoutlet space 21 is effected, in this example, by means of asudden step 22, which characterizes thediffuser 16 as a Carnot diffuser.Radial struts 18, which connect the inside part and the outside part of thediffuser 16 and at the same time serve for steering the flow, can be arranged in thering channel 17. - In contrast, the invention now proposes, according to the exemplary embodiment shown in
FIG. 3 , to realize the transition between thering channel 17 and theoutlet space 21 in multiple steps in the case of adiffuser 20. In the example shown, twosteps further step 22 c (shown by the broken line inFIG. 3 ) is optional. The number of steps, however, is not limited upward. The diameter jumps connected to thesteps 22 a-c are limited in the exemplary embodiment inFIG. 3 to the inside part of thediffuser 20. However, it is also just as conceivable to provide diameter jumps on the outside part of the diffuser. - Such a multiply stepped inside contour produces a gain in the build-up of pressure which can be 0.1% of the turbine efficiency and in the case of a GT26 model gas turbine of the Applicant signifies a gain in capacity of almost half a megawatt.
- In practice, a corresponding diffuser looks, for example, as shown in
FIG. 4 . The diffuser 20 a ofFIG. 4 includes a ring-shaped outer casing 23 which surrounds aninner casing 24 in a concentric manner and together with theinner casing 24 defines a flow channel. Theinner casing 24 and the outer casing 23 are connected by means ofradial struts 25. Tworings - In addition to the multi-stepped expansion of the cross sectional flow, the flow conditions in the diffuser can be influenced by means of a Coanda flow, as has been proposed, in principle, in document US 2011/058939 A1 mentioned in the introduction. To this end, according to
FIG. 5 , a ring-shaped, convexly curved guidingsurface 28 which tapers in diameter is arranged between twosteps steps surface 28 in the form of a Coanda flow 30. In this case, the gas feed for the Coanda flow 30 can be effected in different ways. Contrary to what the aforementioned document teaches, however, as claimed in the invention an external reference source for an actively injected additional gas is to be omitted. By arranging the components in a proper manner, the pressure conditions prevailing in the region of the erratic cross sectional expansion of the diffuser are to be utilized in such a manner that, during operation, a wall flow 30 is automatically built up along thecurved guiding surface 28 and said wall flow deflects the parallel exhaust gas flow 19. The static pressure p2 behind thering body 27 is higher than the inlet pressure p1 at the annular passage on account of the deceleration of the flow through the cross sectional expansion. Accordingly, aflow 32 is formed from the higher pressure region into the lower one. - If more than two steps are present in the diffuser, the Coanda flow is preferably inserted between the penultimate and the last step.
- While the invention has been illustrated and described in detail in the drawings and foregoing description, such illustration and description are to be considered illustrative or exemplary and not restrictive. It will be understood that changes and modifications may be made by those of ordinary skill within the scope of the following claims. In particular, the present invention covers further embodiments with any combination of features from different embodiments described above and below.
-
- 10 Gas turbine
- 11 Air inlet
- 12 Compressor
- 13 Combustion chamber
- 14 Fuel
- 15 Turbine
- 16,20 Diffuser
- 17 Ring channel
- 18,25 Strut
- 19 Exhaust gas
- 20 a,b Diffuser
- 21 Outlet space
- 22 a-c Step (cross sectional area)
- 23 Outer casing
- 24 Inner casing
- 26,27 Ring
- 28 Guiding surface (curved convexly)
- 29 Annular passage
- 30 Coanda flow
- 31 Machine axis
- 32 Return flow
Claims (8)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102011118735A DE102011118735A1 (en) | 2011-11-17 | 2011-11-17 | DIFFUSER, ESPECIALLY FOR AN AXIAL FLOW MACHINE |
DE102011118735.2 | 2011-11-17 |
Publications (1)
Publication Number | Publication Date |
---|---|
US20130129498A1 true US20130129498A1 (en) | 2013-05-23 |
Family
ID=47215404
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/678,676 Abandoned US20130129498A1 (en) | 2011-11-17 | 2012-11-16 | Diffuser, in particular for an axial flow machine |
Country Status (6)
Country | Link |
---|---|
US (1) | US20130129498A1 (en) |
EP (1) | EP2594741A3 (en) |
JP (2) | JP2013108498A (en) |
CN (1) | CN103122776B (en) |
DE (1) | DE102011118735A1 (en) |
RU (1) | RU2569015C2 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
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EP2947283A1 (en) | 2014-05-23 | 2015-11-25 | GE Energy Products France SNC | Thermal-acoustic insulation structure for the exhaust of a rotating machine |
US20170342862A1 (en) * | 2016-05-31 | 2017-11-30 | General Electric Company | Exhaust Diffuser |
US11291938B2 (en) | 2016-12-16 | 2022-04-05 | General Electric Technology Gmbh | Coanda effect moisture separator system |
US11506145B2 (en) * | 2020-03-20 | 2022-11-22 | Doosan Enerbility Co., Ltd | Exhaust diffuser hub structure for reducing flow separation |
EP4197621A1 (en) * | 2021-12-17 | 2023-06-21 | Pratt & Whitney Canada Corp. | Diffuser nozzle for a gas turbine engine |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2896793A1 (en) | 2014-01-21 | 2015-07-22 | Alstom Technology Ltd | Method of operating a gas turbine assembly and the gas turbine assembly |
EP3023695A1 (en) * | 2014-11-20 | 2016-05-25 | Siemens Aktiengesellschaft | Thermal energy machine |
FR3029568B1 (en) * | 2014-12-05 | 2016-11-18 | Turbomeca | PLENUM OF AIR SUPPLY |
RU2632354C1 (en) * | 2016-12-01 | 2017-10-04 | Открытое акционерное общество "Научно-производственное объединение по исследованию и проектированию энергетического оборудования им. И.И. Ползунова" (ОАО "НПО ЦКТИ") | Steam turbine double-flow low-pressure cylinder |
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2012
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- 2012-11-16 US US13/678,676 patent/US20130129498A1/en not_active Abandoned
- 2012-11-16 RU RU2012148919/06A patent/RU2569015C2/en not_active IP Right Cessation
- 2012-11-16 CN CN201210465817.7A patent/CN103122776B/en not_active Expired - Fee Related
- 2012-11-16 JP JP2012252515A patent/JP2013108498A/en active Pending
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US11291938B2 (en) | 2016-12-16 | 2022-04-05 | General Electric Technology Gmbh | Coanda effect moisture separator system |
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Also Published As
Publication number | Publication date |
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RU2012148919A (en) | 2014-05-27 |
JP2013108498A (en) | 2013-06-06 |
CN103122776A (en) | 2013-05-29 |
DE102011118735A1 (en) | 2013-05-23 |
EP2594741A2 (en) | 2013-05-22 |
JP2016180412A (en) | 2016-10-13 |
RU2569015C2 (en) | 2015-11-20 |
EP2594741A3 (en) | 2017-08-23 |
CN103122776B (en) | 2016-02-10 |
JP6188885B2 (en) | 2017-08-30 |
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