CN102770623B - Turbine or compressor blade and rotor component - Google Patents
Turbine or compressor blade and rotor component Download PDFInfo
- Publication number
- CN102770623B CN102770623B CN201080052132.9A CN201080052132A CN102770623B CN 102770623 B CN102770623 B CN 102770623B CN 201080052132 A CN201080052132 A CN 201080052132A CN 102770623 B CN102770623 B CN 102770623B
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- Prior art keywords
- blade
- holder
- bearing member
- load
- groove
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Classifications
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- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
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- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
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- 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
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
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- 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
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
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- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
Abstract
The invention relates to a blade for a turbine or a compressor, at least partially made of fiber-reinforced plastic, in particular carbon fiber reinforced plastic, being particularly durable under operating conditions. According to the invention, the blade (4) comprises a blade body (5) and a blade root (6). The blade body (5) is substantially made of a folded fabric web (7) made of fiber reinforced plastic, wherein a retaining loop (9) is formed in the area of the fold (8), and wherein a blade surface (11) is formed from the overlapping web ends (10). The blade root comprises a longitudinal beam (20) and at least two holders (25) for anchoring the blade (4) in a corresponding groove (3) of a rotor (2), said holders being preferably each fixedly connected to said beam at both ends. The blade body (5) is suspended on the beam (20) by means of the retaining loop (9).
Description
Technical field
The present invention relates to a kind of turbine or compressor blade.
Background technique
The blade of turbo machine usually comprises the bending blade of aerodynamics on the one hand and comprises blade root on the other hand, and this blade root is used for blade to be anchored in the corresponding groove of rotor.Equip vaned rotor and be called rotor assembly below.
Also consider that carbon fiber-reinforced plastics (CFK) are as the relatively new-type material for the manufacture of blade now.By CFK Production Example as advantageously caused the lower weight of blade.Unfortunately, CFK is relatively unstable for pressure load.This pressure stress is such as passed through by the effect rotating the centrifugal force caused in groove inside and produces on blade in the region of blade root.
To this, such as, by US 4,037,990 known a kind of turbo machines, the moving vane be made up of fibrous composite.This moving vane is made up of multiple fibrous layer, and these layers form common ring on the end of its root side.At this, two in these rings are arranged for formation blade root.In order to be fixed in rotor disk by moving vane, be provided with the bolt of slotting for a long time, the bolt element of this bolt extends through corresponding ring.Blade is clamped in the axial groove of rotor by bolt head and the nut that can be tightened on this bolt end regularly.When turbo machine runs, due to centrifugal action, fibrous layer is forced on the carrying side of retention groove.But the pressure stress owing to occurring in these layers at this, only limitedly can keep moving vane.In addition, by US 2,929,755 known a kind of moving vanes for gas turbine, this moving vane has columniform, hard core in root side, is provided with multiple by thread woven layer around this core annularly.Also blade is formed by these layers.In order to be fixed in retention groove by moving vane, core is provided with sheet metal, these sheet metals abut on the side of retention groove.The packing material be made of plastics is provided with, to be filled in the free space between outmost layer and retention groove profile between two sheet metals.
Summary of the invention
The object of the invention is to, propose one at least in part by fiber strengthened plastics, especially the blade for turbine or compressor made of CFK, this blade is especially durable, that is long service life.In addition, the object of the invention is to, a kind of rotor assembly that is especially durable, that have the blade be substantially made up of fiber strengthened plastics is in operating conditions provided.
About blade, this object following feature according to the present invention realizes: the blade for turbine or compressor comprises blade and blade root, wherein, described blade is made up of the laminated fabric breadth folding, described laminated fabric breadth is made up of fiber strengthened plastics, wherein, retaining ring is configured with in the region of kink, and wherein, by the end formed blade face of mutually stacked breadth, wherein, described blade root comprises microscler load-bearing member, and at least two are permanently connected with described load-bearing member position respectively, for described blade being anchored at the holder in the corresponding groove of turbine rotor component, and wherein, described blade is suspended on described load-bearing member by described retaining ring, wherein each is interconnected by least one lateral wall piece for stable described holder, and wherein, it is directed that described lateral wall piece is parallel to described load-bearing member, the longitudinal extension of each described holder relative to blade in the region of load-bearing member extends over blade at a right angle on both sides, described lateral wall piece is arranged on extending on the side margin in two regions of described blade of described holder.To this, blade also comprises the blade root with microscler or pin-shaped load-bearing member except the blade that aerodynamics bends, and this load-bearing member is made of metal in a preferred embodiment.In addition, blade root comprises at least two holders, and wherein, these holder (at least in the radial direction thereof) positions being preferably plate shape are fixedly attached on load-bearing member.In groove that is that each holder is configured for corresponding capitate blade being anchored at rotor or fir shape, and can abut on the sidewall of groove.
Blade is made up of the stacked laminated fabric breadth be made up of fiber strengthened plastics, especially CFK substantially, and this laminated fabric breadth (substantially between these holders) is directed round load-bearing member.At this, two are interconnected away from the breadth level land that load-bearing member is outstanding respectively, for formation blade face.The part around load-bearing member guiding of blade is configured to the retaining ring for being suspended by blade on the load bearing member.At this, preferably propose in manufacturing technology, first manufacture the laminated fabric for the blade that is shaped (i.e. blade face and retaining ring), and subsequently the blade so made is set with on the load bearing member.To this as an alternative, obvious laminated fabric also can be installed round load-bearing member, for forming and the blade connected thereon that is shaped.
In the assembling situation of the routine of blade, blade, by its blade root, be that is placed in the groove of rotor by the retaining ring together with the load-bearing member be arranged on wherein of blade, and the blade of blade stretches out from groove relative to rotor radial substantially.
Because blade by retaining ring suspension on the load bearing member, so act on absorbing basically by load-bearing member by rotating the centrifugal force caused on blade.Not occur or only in the relatively little direct power transmission circumferentially occurred between blade and rotor.Therefore, blade is under its laminated fabric overwhelming majority is in tensile stress in other words.
Because compare opposing pressure load or shear load, fiber strengthened plastics can more times of ground opposing pulling loads, so blade and especially blade be the fixed area of blade root form is especially durable and long service life relative to operating conditions thus.
Advantageously, use fiber strengthened plastics, especially CFK to manufacture the possibility that blade achieves the aerodynamically especially favourable blade of structure.Thus, this contributes to reducing energy input, and the energy input of this reduction advantageously causes again the CO of reduction
2generate.Due to the lower weight of fiber strengthened plastics, when the blade root of formed objects, the blade of this blade also can be greater than the blade of metal blade.This also achieves the lifting of mass flow.
Each holder of blade root is interconnected by least one lateral wall piece in order to stable blade root, and wherein, lateral wall piece is arranged essentially parallel to load-bearing member orientation.
At this preferably, be provided with two lateral wall pieces, these lateral wall pieces are arranged on two each side margin in holder respectively, and corresponding holder extends over blade with these side margin.Corresponding to this place, two lateral wall pieces are preferred relative to load-bearing member completely opposite.At this, especially and for example this place realizes the installation of lateral wall piece, makes these lateral wall pieces at least to extend in the region of blade not contact laminating fabric web at holder.Reliably avoid the unexpected pressure stress in laminated fabric breadth thus.In trapezoidal holder, lateral wall piece is preferably fixed on two trapezoidal waists, and the line of force is realized completely on lateral wall piece.This greatly reduces the load of the side of retention groove, and therefore make the load in rotor disk based on significantly being become large surface of contact by lateral wall piece and homogenization.Therefore, the claw be arranged between two adjacent retention grooves diminishes, and the space-saving layout that retention groove is compact in the rotor is thus possible.
In the especially preferred mode of execution of the present invention, each longitudinal extension at least substantially relative to blade in the region of load-bearing member in holder extends over blade at a right angle on both sides.In other words, in such an embodiment, holder extends over laminated fabric breadth towards both sides in the region of suspension blade, makes not contact with the respective side (groove side) of groove in laminated fabric region at least there.Therefore, mainly not abutted on groove side by laminated fabric by means of only holder at the situation lower blade of centrifugal force, make only holder through compression chord.The pressure stress occurred due to centrifugal action when which avoid in the laminated fabric region of root side, in root side laminated fabric contact groove side.
Desirably, each in holder also extends over blade on the side of the usual radial direction of blade inner (deviating from blade face), and laminated fabric breadth is also contactlessly suspended in the bottom land of rotor.
In another embodiment of the present invention, blade root comprises the holder that two are especially arranged on load-bearing member side, and at least one the 3rd holder, wherein, the 3rd holder is located at interval on the load bearing member with to be arranged in two holders of side each in the longitudinal direction of load-bearing member.Preferably, these additional holders arranged distribute equably in the length of load-bearing member.In this embodiment, blade is made up of multiple laminated fabric breadth aptly, and these laminated fabric breadths suspend on the load bearing member respectively between two holders, and the holder of central authorities is positioned in the longitudinal direction of load-bearing member thus.In principle, two fixed positions of holder on microscler load-bearing member are selected with depending on blade center of gravity, make the non-side of holder but the fixed position be arranged in load-bearing member end regions also can be significant.
Preferably, each in holder is provided with the penetrating part matched with the cross section of load-bearing member, load-bearing member correspondingly substantially precise match ground insert through this penetrating part.Optionally, load-bearing member welds with holder.
Desirably, shape joint or material are connected with holder lateral wall piece with engaging the preferred grafting in ground or welding respectively.
Preferably, the cross section of load-bearing member is shaped to round or substantially leg-of-mutton.When triangular shaped, preferred isosceles triangle, especially has the isosceles triangle of rounded edge, wherein, by the especially about blade face towards blade of seamed edge that two purses enclose.
Preferably, load-bearing member is provided with sliding layer in its surface, is especially provided with the layer be made up of teflon.Thus, as necessary, inner most laminated fabric breadth can slide relative to load-bearing member.
In favourable mode of execution of the present invention, laminated fabric is uniaxially structure substantially, and wherein, laminated fabric has primary fibre direction, and this primary fibre direction is substantially along directed by running the centrifugal force direction caused.Thus, blade is especially stable for produced pulling force.Additionally or as an alternative, laminated fabric is interweaved by the three-dimensional of fiber and strengthens in the region of blade root or in the region of load-bearing member.
Desirably, blade is at least provided with corrosion protection layer in its surface in the region of its blade face, especially by particle composites or the corrosion protection layer be made up of the metallic thin film being coated with hard material.This layer also advantageously improves the repellence that blade immerses for water.
About rotor assembly, above-mentioned object is realized by following feature according to the present invention: rotor assembly has rotor and at least one is according to blade of the present invention, introduce at least one groove in the rotor, wherein, the blade root of described blade is inserted in described groove, and wherein, described blade root and described rotor are positioned in described groove with being connected.So, rotor assembly comprises rotor, introduces at least one groove and at least one according to blade of the present invention aforementioned in this rotor.Blade is placed in groove regularly by its blade root position.
Due to the relatively low weight of blade be substantially made up of fiber strengthened plastics, to arrange in groove in the rotor each is advantageously formed relatively littlely.In addition, whole rotor assembly is advantageously light especially.If it is apparent that should substitute the blade be made up of metal or stainless steel completely in the turbo machine of running load according to blade of the present invention, so blade root also too greatly can be formed relative to blade.
Preferably, groove is coordinated into mutually with holder, and holder is supported on the side of groove respectively.Holder substantially fills up groove cross section in suitable mode of execution.
Preferably, not only the cross section of holder but also groove is construct (" swallow tail shaped slot ") substantially trapezoidally.Other shape of cross sections, such as " fir shape " or semicircle are also possible for holder and groove cross-sectional profiles.
In appropriate configuration of the present invention, the holder of blade constructs identical from one anotherly, and wherein, groove has unified width and shape over its length.
In the preferred implementation of rotor assembly, this rotor assembly comprise multiple difference substantially vertically directed, at circumferentially equally distributed groove, wherein, blade especially correspondingly to be inserted in each groove and is located there.To this as an alternative, turbine rotor component or compressor drum assembly rotor in introduce circumferential groove, wherein, multiple blade mutual arrangement ground holds in the cell, and is fixed on there.
Accompanying drawing explanation
Explain two embodiments of the present invention below with reference to the accompanying drawings in detail.Accompanying drawing illustrates:
Fig. 1 illustrates the first mode of execution of the turbine rotor component with turbine blade with cross section, this turbine blade comprises blade and blade root;
Fig. 2 illustrates the blade root according to the first mode of execution with the exploded view of signal; And
Fig. 3 is to illustrate the blade root according to the second mode of execution according to the diagram of Fig. 2.
The parts of mutual correspondence and parameter are provided with identical reference character in all of the figs all the time.
Embodiment
Fig. 1 illustrates turbine rotor component 1 with the sectional view slightly illustrated.Turbine rotor component 1 comprises the rotor 2 be made up of stainless steel, and multiple axial groove 3 is incorporated in this rotor in the mode be evenly distributed on circumferentially.The sectional view of rotor 2 in the region of single axial groove 3 is only shown in FIG.In the first mode of execution shown here, each axial groove 3 is configured to so-called swallow tail shaped slot substantially.
Turbine blade 4 is accommodated in axial groove 3.This turbine blade 4 comprises blade 5 (only partly illustrating) here, and blade root 6, and this blade root is used for turbine blade to be anchored in axial groove 3.
Blade 5 is made up of multiple stacked breadth 7 made primarily of unidirectional CFK laminated fabric.At this, breadth 7 preferably approximately builds up in central folding, makes to form retaining ring 9 in the region of the kink 8 produced when folding.On the one side (in the drawings top) away from this retaining ring 9, these level lands, breadth end 10 are mutually stacked, and wherein, they are " joints " when being shaped to blade face 11 of blade 5.Blade face 11 approximately stretches out diametrically from the axial groove 3 of rotor 2.
The majority fibers direction of CFK laminated fabric is approximately directed along breadth 7, makes each carbon fiber 12 of CFK laminated fabric be arranged essentially parallel to longitudinal section (substantially also respectively when the forming ring) orientation of blade 5.
Blade 5 covers with corrosion protection layer on the surface 13 in its (under manufacture state shown here) outside.To this alternatively, corrosion protection layer 14 is only arranged in the region of blade face 11.
Blade root 6 one aspect comprises microscler metal-cored 20 as load-bearing member, and this is metal-cored is inserted in the retaining ring 9 of blade to suspend blade 5.The structure of blade root 6 is explained in detail according to three-dimensional, exploded view in fig. 2.Can see thus, metal-cored 20 poles be made up of stainless steel are formed.The surface 21 of metal-cored 20 can be provided with the sliding layer 22 be such as made up of PTFE (teflon).Metal-cored 20 are connected with holder 25 respectively on two end 23,24.Two holders 25 are made up of steel plate that is identical, isosceles trapezoid substantially, and axial groove 3 ground that these steel plates can be matched with swallow-tail form is inserted in described axial groove.
Each holder 25 has circular penetrating part 26 at its center, face about, and metal-cored 20 are inserted in this penetrating part substantially precise match, and wherein, these holders 25 approximately extend over metal-cored at a right angle relative to metal-cored 20.
On two waists 27 of each holder 25, the recess 28 of each edge side is introduced in described waist.These recesses 28 are connected with these lateral wall pieces in the assembled condition respectively for fixing two lateral wall pieces, 30, two holders 25 on these waists 27.
Each lateral wall piece 30 is made up of rectangle, microscler steel plate substantially.Each lateral wall piece 30 has ridge 32 on side 31, and this ridge extends respectively in the whole length of corresponding lateral wall piece 30.At this, ridge 32 is complementally shaping with recess 28 respectively, makes lateral wall piece 30 can by ridge 32 fixed position in recess 28.
In addition, each lateral wall piece 30 has the edge 33 of the longitudinal side bent a little.At this, the size of each lateral wall piece 30 is defined as, and makes the straight part of side 31 have width b, and this width is approximately corresponding to the long L of waist of holder 25.In the assembled condition, lateral wall piece 30 is installed in both sides respectively, is preferably welded on two waists 27 of two holders 25.Lateral wall piece 30 is arranged with trapezoidal long limit 35 by the side margin 34 opposed with edge 33 respectively with approximately flushing, and wherein, the edge 33 of bending extends over waist 27 respectively on trapezoidal minor face 36.
Can be seen by Fig. 1, the edge 33 exceeded is substantially for keeping blade 5 in the tangential direction in the assembled condition.
In addition, can be seen by Fig. 1, the size of each mean breadth B (Fig. 2) in holder 25 even as big as make holder metal-cored 20 or retaining ring 9 region in be substantially perpendicular to blade face 14 ground and extend over blade 5 in both sides, namely especially also exceed laminated fabric breadth 7 respectively.
Thus, especially radially metal-cored 20 or retaining ring 9 height on, there is not the contact between lateral wall piece 30 and CFK laminated fabric breadth 7.Thus, even if also do not produce the disadvantageous pressure load of CFK laminated fabric under (radial in rotor effect) the centrifugal force F effect produced when turbine rotor component 1 is run in this region.
Therefore operationally, blade 5 is directed along centrifugal force F, and under blade 5 is similar to and is only in pulling load thus, CFK laminated fabric is especially also because described pulling load is resisted in favourable majority fibers direction especially.
In mode of execution shown here, two lateral wall pieces 30 weld with rotor 2 in axial groove 3.
The blade root 6 of the second mode of execution according to turbine rotor component 1 or turbine blade 4 shown in Figure 3.This second mode of execution is substantially corresponding to the first mode of execution.Unlike this, blade root 6 has the 3rd holder 25 here in order to more advantageously eliminate load, and the 3rd holder is approximately arranged on central authorities in the longitudinal direction of metal-cored 20.The holder 25 of these central authorities is similar to the holder 5 ground structure of side, and wherein, metal-cored 20 insert through penetrating part 26.
Blade 5 is formed by being divided into two-part breadth 7 at this.In the region of retaining ring 9, breadth 7 is arranged between these holders 25 respectively in the longitudinal direction of metal-cored 20, and wherein, described breadth is except the holder 25 for suspending also for axial restraint central authorities except blade 5.
Also the mode of execution with four or more holders 25 can be considered.
Claims (14)
1., for the blade (4) of turbine or compressor, comprise blade (5) and blade root (6),
-wherein, described blade (5) is made up of the laminated fabric breadth (7) folding, described laminated fabric breadth is made up of fiber strengthened plastics, wherein, retaining ring (9) is configured with in the region of kink (8), and wherein, by mutually stacked breadth end (10) shaping blade face (11)
-wherein, described blade root (6) comprises microscler load-bearing member (20), and at least two that be permanently connected with described load-bearing member position respectively, for described blade (4) being anchored at the holder (25) in the corresponding groove (3) of turbine rotor component (1), and
-wherein, described blade (5) is suspended on described load-bearing member (20) by described retaining ring (9),
It is characterized in that, each is interconnected by least one lateral wall piece (30) for stable described holder (25), and wherein, it is directed that described lateral wall piece is parallel to described load-bearing member (20),
Wherein, each described holder (25) extends over blade at a right angle relative to the longitudinal extension of blade (5) in the region of load-bearing member (20) on both sides, and
Described lateral wall piece (30) is arranged on extending on the side margin (27) in two regions of described blade (5) of described holder (25).
2. blade according to claim 1 (4), have at least one for being anchored at the other holder (25) in corresponding groove (3), described other holder is positioned at interval on described load-bearing member (20) with to be especially arranged in two holders (25) of side each in the longitudinal direction of described load-bearing member (20).
3. blade according to claim 1 and 2 (4), wherein, described lateral wall piece (30) form fit or material fit ground are connected with described holder (25).
4. blade according to claim 1 and 2 (4), described blade has two lateral wall pieces (30), and described two lateral wall pieces are arranged on extending on the side margin (27) in two regions of described blade (5) of described holder (25) respectively.
5. blade according to claim 1 and 2 (4), wherein, the cross section of described load-bearing member (20) is configured as circle or triangle.
6. blade according to claim 1 and 2 (4), wherein, described load-bearing member (20) is made of metal.
7. blade according to claim 1 and 2 (4), wherein, described load-bearing member (20) is provided with sliding layer (22) on its surface (21).
8. blade according to claim 1 and 2 (4), wherein, described laminated fabric breadth (7) uniaxially structure, and wherein, the primary fibre direction of described laminated fabric breadth is farthest along directed by running the centrifugal force direction caused.
9. blade according to claim 1 and 2 (4), wherein, described blade (5) is provided with corrosion protection layer (14) at least in part on its surface (13).
10. blade according to claim 1 and 2 (4), wherein, described fiber strengthened constructed in plastic material is carbon fiber-reinforced plastics (CFK).
11. rotor assembly (1), there is rotor (2) and at least one is according to the blade (4) one of claim 1 to 10 Suo Shu, introduce at least one groove (3) in the rotor, wherein, the blade root (6) of described blade (4) is inserted in described groove (3), and wherein, described blade root is positioned in described groove (3) with described rotor (2) with being connected.
12. rotor assembly according to claim 11 (1), wherein, described holder (25) and/or described lateral wall piece (30) are supported on the side of described groove (3).
13. rotor assembly (1) according to claim 11 or 12, wherein, described holder (25) fills up groove cross section.
14. rotor assembly (1) according to claim 11 or 12, wherein, not only the cross-sectional configuration of described groove (3) but also described holder (25) in echelon.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP09014381A EP2322763A1 (en) | 2009-11-17 | 2009-11-17 | Turbine or compressor blade |
| EP09014381.9 | 2009-11-17 | ||
| PCT/EP2010/067581 WO2011061192A1 (en) | 2009-11-17 | 2010-11-16 | Turbine or compressor blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102770623A CN102770623A (en) | 2012-11-07 |
| CN102770623B true CN102770623B (en) | 2015-01-07 |
Family
ID=42062015
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201080052132.9A Active CN102770623B (en) | 2009-11-17 | 2010-11-16 | Turbine or compressor blade and rotor component |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US20120230829A1 (en) |
| EP (2) | EP2322763A1 (en) |
| JP (1) | JP2013510994A (en) |
| CN (1) | CN102770623B (en) |
| ES (1) | ES2530053T3 (en) |
| PL (1) | PL2501901T3 (en) |
| RU (1) | RU2517005C2 (en) |
| WO (1) | WO2011061192A1 (en) |
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| US10024177B2 (en) | 2012-05-15 | 2018-07-17 | United Technologies Corporation | Detachable fan blade platform and method of repairing same |
| JP6121740B2 (en) * | 2013-02-13 | 2017-04-26 | 株式会社Ihi | Fan blade manufacturing method and manufacturing apparatus |
| RU2609800C1 (en) * | 2013-02-13 | 2017-02-06 | АйЭйчАй КОРПОРЕЙШН | Method of fan blade making and fan blade production device |
| DE202013010937U1 (en) | 2013-11-30 | 2015-03-02 | Oerlikon Leybold Vacuum Gmbh | Rotor disc and rotor for a vacuum pump |
| US9938930B2 (en) * | 2015-05-11 | 2018-04-10 | United Technologies Corporation | Composite wear pad for exhaust nozzle |
| US10227880B2 (en) | 2015-11-10 | 2019-03-12 | General Electric Company | Turbine blade attachment mechanism |
| US10443409B2 (en) * | 2016-10-28 | 2019-10-15 | Rolls-Royce North American Technologies Inc. | Turbine blade with ceramic matrix composite material construction |
| US10577939B2 (en) * | 2016-11-01 | 2020-03-03 | Rolls-Royce Corporation | Turbine blade with three-dimensional CMC construction elements |
| JP6778147B2 (en) * | 2017-05-31 | 2020-10-28 | 三菱重工業株式会社 | Method for manufacturing composite blades and composite blades |
| GB201803802D0 (en) | 2018-03-09 | 2018-04-25 | Rolls Royce Plc | Composite fan blade and manufacturing method thereof |
| GB201808939D0 (en) * | 2018-05-31 | 2018-07-18 | Rolls Royce Plc | Composite fan blade root |
| JP7236337B2 (en) | 2019-06-19 | 2023-03-09 | 三菱重工業株式会社 | Composite material wing and molding method for composite material wing |
| CN110454233A (en) * | 2019-08-08 | 2019-11-15 | 中国长江动力集团有限公司 | A kind of steam turbine is cultivated one's moral character the movable vane piece group of blade and its composition |
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| US2929755A (en) * | 1958-07-24 | 1960-03-22 | Orenda Engines Ltd | Plastic blades for gas turbine engines |
| US3737250A (en) * | 1971-06-16 | 1973-06-05 | Us Navy | Fiber blade attachment |
| US4047840A (en) * | 1975-05-29 | 1977-09-13 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Impact absorbing blade mounts for variable pitch blades |
| SU922324A1 (en) * | 1980-09-09 | 1982-04-23 | Производственное Объединение "Ворошиловградский Тепловозостроительный Завод Им.Октябрьской Революции" | Axial fan impeller |
| DE3826378A1 (en) * | 1988-08-03 | 1990-02-08 | Mtu Muenchen Gmbh | FIBER TECHNICAL PROPELLER BLADES |
| US6857856B2 (en) * | 2002-09-27 | 2005-02-22 | Florida Turbine Technologies, Inc. | Tailored attachment mechanism for composite airfoils |
| DE10326719A1 (en) * | 2003-06-06 | 2004-12-23 | Rolls-Royce Deutschland Ltd & Co Kg | Compressor blade base for engine blades of aircraft engines |
| GB0815475D0 (en) * | 2008-08-27 | 2008-10-01 | Rolls Royce Plc | A blade |
-
2009
- 2009-11-17 EP EP09014381A patent/EP2322763A1/en not_active Withdrawn
-
2010
- 2010-11-16 JP JP2012539305A patent/JP2013510994A/en active Pending
- 2010-11-16 ES ES10782578.8T patent/ES2530053T3/en active Active
- 2010-11-16 WO PCT/EP2010/067581 patent/WO2011061192A1/en active Application Filing
- 2010-11-16 RU RU2012124907/06A patent/RU2517005C2/en not_active IP Right Cessation
- 2010-11-16 EP EP10782578.8A patent/EP2501901B1/en active Active
- 2010-11-16 CN CN201080052132.9A patent/CN102770623B/en active Active
- 2010-11-16 US US13/510,295 patent/US20120230829A1/en not_active Abandoned
- 2010-11-16 PL PL10782578T patent/PL2501901T3/en unknown
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4037990A (en) * | 1976-06-01 | 1977-07-26 | General Electric Company | Composite turbomachinery rotor |
| US5292231A (en) * | 1991-12-31 | 1994-03-08 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Turbomachine blade made of composite material |
| US5240377A (en) * | 1992-02-25 | 1993-08-31 | Williams International Corporation | Composite fan blade |
| US5409353A (en) * | 1993-01-14 | 1995-04-25 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbomachine rotor with blades secured by pins |
| CN101313129A (en) * | 2005-11-21 | 2008-11-26 | 西门子公司 | Turbine blade for a steam turbine |
| EP2077376A2 (en) * | 2008-01-04 | 2009-07-08 | United Technologies Corporation | Composite rotor blade attachment in a gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| US20120230829A1 (en) | 2012-09-13 |
| RU2012124907A (en) | 2013-12-27 |
| EP2501901B1 (en) | 2014-12-31 |
| WO2011061192A1 (en) | 2011-05-26 |
| PL2501901T3 (en) | 2015-05-29 |
| CN102770623A (en) | 2012-11-07 |
| JP2013510994A (en) | 2013-03-28 |
| EP2322763A1 (en) | 2011-05-18 |
| RU2517005C2 (en) | 2014-05-27 |
| ES2530053T3 (en) | 2015-02-26 |
| EP2501901A1 (en) | 2012-09-26 |
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