CN117449918A - Turbine guide vane, turbine comprising same and aeroengine - Google Patents
Turbine guide vane, turbine comprising same and aeroengine Download PDFInfo
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- CN117449918A CN117449918A CN202210842468.XA CN202210842468A CN117449918A CN 117449918 A CN117449918 A CN 117449918A CN 202210842468 A CN202210842468 A CN 202210842468A CN 117449918 A CN117449918 A CN 117449918A
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- vane
- turbine
- plate
- guide vane
- guide
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- 239000000463 material Substances 0.000 claims abstract description 25
- 238000001816 cooling Methods 0.000 claims description 40
- 230000000670 limiting effect Effects 0.000 claims description 14
- 230000002093 peripheral effect Effects 0.000 claims description 5
- 230000013011 mating Effects 0.000 claims 1
- 239000002184 metal Substances 0.000 abstract description 18
- 238000000034 method Methods 0.000 abstract description 16
- 230000008569 process Effects 0.000 abstract description 16
- 230000005540 biological transmission Effects 0.000 description 11
- 230000002829 reductive effect Effects 0.000 description 11
- 238000009434 installation Methods 0.000 description 9
- 238000004519 manufacturing process Methods 0.000 description 7
- 230000006835 compression Effects 0.000 description 6
- 238000007906 compression Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 6
- 239000000956 alloy Substances 0.000 description 4
- 239000011153 ceramic matrix composite Substances 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 230000036961 partial effect Effects 0.000 description 3
- 229910000601 superalloy Inorganic materials 0.000 description 3
- 239000000919 ceramic Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 210000001503 joint Anatomy 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 229910052814 silicon oxide Inorganic materials 0.000 description 1
- 239000012720 thermal barrier coating Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- 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
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- 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
- 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
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a turbine guide vane, a turbine and an aeroengine comprising the turbine guide vane, and the turbine guide vane comprises a guide vane body made of CMC materials, and further comprises a cover plate, an elastic supporting plate and a bearing component, wherein the elastic supporting plate comprises an upper supporting plate and a lower supporting plate, an elastic piece is arranged between the upper supporting plate and the lower supporting plate, and two ends of the guide vane body in the length direction are respectively connected with the cover plate and the upper supporting plate; the bearing component is arranged in the inner cavity of the guide vane body, at least part of the outer surface of the bearing component is abutted against the inner cavity wall of the guide vane body, the upper end connecting part of the bearing component is connected with the cover plate, and the lower end connecting part of the bearing component is connected with the lower supporting plate and enables the elastic piece to be in a compressed state. The turbine guide vane can avoid the problems that larger stress is generated at the rounding weak part of the guide vane body made of CMC material and thermal mismatch exists in the process of matching the guide vane body with the metal component, and larger gaps are possibly generated between the CMC guide vane component and the metal component at high temperature.
Description
Technical Field
The invention relates to the field of aeroengines, in particular to a turbine guide vane, a turbine comprising the turbine guide vane and an aeroengine.
Background
The high Wen Qifei turbine front gas temperature of the current commercial aero-engine reaches 1978K, and along with the higher and higher requirements on the performance of the aero-engine, the turbine front gas temperature is higher and higher, and the service life of the aero-engine is longer and longer. The design life of the hot end part of the commercial aeroengine which is developed in modern times is not less than 10000 flight cycles (20000 hours). At present, aiming at a high-temperature turbine stator component, under the condition of adopting a traditional cooling technology and a thermal barrier coating technology, the service temperature and the service performance of a traditional high-temperature alloy material are close to the limit, and the design requirement of a next-generation advanced aeroengine is difficult to meet. The adoption of ceramic matrix composite materials (Ceramic Matrix Composites, CMC) to replace the traditional high-temperature alloy materials is the best way for improving the temperature resistance and the efficiency of the hot end parts of the aero-engine.
Compared with the traditional superalloy, the ceramic matrix composite has the following advantages: (1) high temperature resistance, reducing the amount of cold air: the high temperature resistant material can reduce the cold air quantity of the turbine component, thereby improving the efficiency of the turbine component; (2) corrosion resistance: under the high-temperature environment, siC, si3N4 and other ceramics can form a silicon oxide protective layer on the surface, and can meet the high-temperature oxidation resistance requirement below 1600 ℃; (3) low density: the density of CMC is only 1/3-1/4 of that of high-temperature alloy, thus the weight of the engine can be reduced, and the efficiency of the engine can be further improved; (4) The combustion temperature and the thermal efficiency are improved, and the pollutant emission can be reduced by 75 percent. Based on these advantages, the need for weight reduction and subsequent elevation of turbine front inlet temperatures for civilian aircraft engines, the use of CMC materials on turbine stator components such as turbine guide vanes, is a necessary choice for future aircraft engines.
In the assembly structure of the traditional metal two-stage turbine guide vane and part of CMC guide vane, aerodynamic load is transmitted to a front casing and a rear casing or other metal parts through the upper edge plate and the lower edge plate of the guide vane, at the moment, the stress of the CMC guide vane is concentrated at the rounding positions of the upper edge plate, the lower edge plate and the vane blade body, and due to the limitation of process conditions, the possibility of strength reduction exists in the vicinity of the rounding of the existing CMC guide vane relative to a matrix. Meanwhile, the existing CMC guide vane cannot be processed into a too complex configuration, and compared with the traditional superalloy, the CMC material has a small thermal expansion coefficient, so that the problem of thermal mismatch exists in the process of being matched with a metal component, and a large gap can be generated between the CMC guide vane component and the metal component at high temperature to influence the aerodynamic performance of the turbine.
Disclosure of Invention
The invention aims to solve the technical problems that in the prior art, due to small thermal expansion coefficient of materials, thermal mismatch is easy to occur in the process of matching with a metal part, so that a larger gap is generated between the CMC guide vane part and the metal part at a high temperature to influence the aerodynamic performance of a turbine, the strength of a relative matrix near a rounding between the vane body of the CMC guide vane and an upper edge plate and a lower edge plate is lower, and the CMC guide vane cannot bear larger aerodynamic load, and provides a turbine guide vane, a turbine comprising the CMC guide vane, and an aeroengine.
The invention solves the technical problems by the following technical scheme:
the invention provides a turbine guide vane, which comprises a guide vane body made of CMC materials, a cover plate, an elastic supporting plate and a bearing component, wherein the elastic supporting plate comprises an upper supporting plate and a lower supporting plate, an elastic piece is arranged between the upper supporting plate and the lower supporting plate, and two ends of the guide vane body in the length direction are respectively connected with the cover plate and the upper supporting plate;
the bearing component is arranged in the inner cavity of the guide vane body, at least part of the outer surface of the bearing component is abutted to the inner cavity wall of the guide vane body, the upper end connecting part of the bearing component is connected with the cover plate, and the lower end connecting part of the bearing component is connected with the lower supporting plate and enables the elastic component to be in a compressed state.
In the scheme, a guide vane body made of CMC materials is clamped and fixed between a cover plate and an elastic supporting plate through the elastic pre-tightening force of the elastic supporting plate at normal temperature, the cover plate and the elastic supporting plate are assembled with other metal parts in a turbine, other assembling structures are not arranged on the guide vane body made of CMC materials except the matching surfaces of the cover plate and the elastic supporting plate, and the simplification of the manufacturing process of the blade is realized; the cover plate is connected with the elastic supporting plate through a bearing component, and the bearing component plays a bearing role; in a high-temperature working state, under the pushing of aerodynamic force, the bearing component is abutted with the inner cavity wall of the guide vane body to realize force transmission, the aerodynamic force borne by the guide vane body is directly transmitted to the bearing component, the cover plate and the elastic supporting plate, so that larger stress is prevented from being generated at the rounding weak part of the guide vane body made of CMC material, and the turbine guide vane is ensured to bear larger aerodynamic load; through the use of the elastic supporting plate, the cover plate and the elastic supporting plate in the working state are always kept in contact with the guide vane body, the problem of thermal mismatch in the process of matching the guide vane body with the metal part is avoided, and the problem that a large gap is possibly generated between the CMC guide vane part and the metal part at high temperature is eliminated, so that the influence on the pneumatic performance of the turbine is avoided.
Preferably, the upper end connecting part of the bearing component comprises a first threaded connecting piece, and the first threaded connecting piece is fixed with the cover plate through a nut or a bolt; and/or the number of the groups of groups,
the upper end connecting portion of the bearing component comprises a boss, a groove is formed in one side, facing the bearing component, of the cover plate, and the boss is matched with the groove.
In this scheme, set up the upper end connecting portion of bearing part into threaded connection spare, be convenient for install and dismantle, the installation angle of being convenient for simultaneously adjusting bearing part in the stator body makes bearing part better bear the aerodynamic force of stator body transmission. The boss is arranged on the bearing component and matched with the groove arranged on the cover plate to form a mortise and tenon structure, so that the positioning of the bearing component and the rigidity reinforcement of the joint of the bearing component and the cover plate are realized.
Preferably, the first threaded connecting piece is arranged on the boss, and a first through hole for the first threaded connecting piece to pass through is correspondingly formed in the bottom of the groove.
In this scheme, locate first threaded connection spare on the boss for bearing part and apron junction structure are compacter, reduce the radial force that first threaded connection spare bore simultaneously, avoid first threaded connection spare to take place the fracture.
Preferably, the bearing component is provided with a cooling cavity, and the side wall of the bearing component is penetrated with a cooling hole communicated with the cooling cavity.
In this scheme, through setting up the cooling chamber in the load-carrying member, the lateral wall of load-carrying member sets up the cooling hole, makes cooling intracavity air form the impingement cooling in order to reduce the temperature of stator body to the inner wall of stator body.
Preferably, a first air guiding hole is formed in the boss, a second air guiding hole corresponding to the first air guiding hole is formed in the cover plate, located in the groove, and the second air guiding hole is communicated with the cooling cavity through the first air guiding hole.
In the scheme, the first air vent and the second air vent are correspondingly arranged on the boss and the cover plate, so that cooling air flow outside the casing is conveniently led into the cooling cavity to cool the CMC guide vane body.
Preferably, a third air bleed hole is formed in the bottom of the bearing component, and the third air bleed hole is communicated with the cooling cavity and the inner cavity of the guide vane body.
In this scheme, be equipped with the third air vent in the bottom of bearing part, make cooling air current mainstream flow from between leading-leaf lower edge board and the elastic support board after the cooling chamber, reduce the operating temperature of elastic component in the elastic support board, improve the reliability of elastic component, can also reduce the temperature of leading-leaf lower edge board and elastic support board simultaneously to reduce the thermal deformation range of leading-leaf lower edge board and elastic support board, reduce the influence that the thermal mismatch brought.
Preferably, the outer surface of the bearing component is provided with a convex hull, and the convex hull is abutted to the inner cavity wall of the guide vane body.
In the scheme, the convex hulls are arranged on the outer surfaces of the bearing parts, so that the bearing parts are guaranteed to be abutted with the guide vane bodies so that the bearing parts can transmit aerodynamic force generated when the engine works, and the convex hulls can allow manufacturing deviations to exist on the inner wall surfaces of the guide vane bodies, so that the structure of the CMC guide vane bodies is simplified, the inner and outer wall surfaces of the guide vane bodies are allowed to be manufactured into complex three-dimensional curved surfaces, and the aerodynamic efficiency is improved and the manufacturing process is simplified. And the convex hulls are arranged, so that the bearing component and the guide vane body can keep a certain gap, and higher impact cooling efficiency is obtained.
Preferably, the guide vane body has a windward side and a leeward side, and the convex hull is arranged on the inner cavity wall of the guide vane body, corresponding to the windward side and the leeward side, of the bearing component, or the convex hull is arranged on the inner cavity wall of the guide vane body, corresponding to the windward side, of the bearing component; and/or the number of the groups of groups,
the convex hull is a spherical bulge; and/or the number of the groups of groups,
the convex hull and the bearing component are integrally formed.
In the scheme, under the condition of strength permission, the convex hulls are only reserved on one side of the bearing component, and the other side is not arranged, so that the feasibility of assembling the bearing component and the guide vane body is improved. Under the condition that the convex hulls are arranged on two sides, in the room temperature assembly state, proper gaps are reserved between the convex hulls on the side with smaller bearing force and the inner wall surface of the CMC guide vane body, so that the bearing member can be installed into a designated position along the profile curve of the inner cavity of the guide vane body, and the reserved gaps are enough to ensure that the expansion amount generated by heating the bearing member in the working state can not generate large extrusion stress with the inner wall surface of the guide vane body. The convex hulls and the bearing parts are integrally formed, and the same material is used, so that the convex hulls and the bearing parts cannot be cracked due to heating.
Preferably, the lower end connecting part of the bearing component comprises a second threaded connecting piece, and the second threaded connecting piece and the lower supporting plate are fixed through nuts or bolts.
In this scheme, set up the lower extreme connecting portion of bearing part into threaded connection spare, be convenient for install and dismantle to and be convenient for adjust bearing part's installation angle in the stator body and make bearing part better bear the aerodynamic force of stator body transmission. And the compression amount of the elastic piece in the elastic supporting plate at normal temperature assembly can be adjusted according to actual demands, so that the elastic piece still keeps a small amount of compression amount under the most severe working condition, a pressing force is provided between the upper supporting plate and the guide vane body, the cover plate and the elastic supporting plate still keep a certain clamping effect on the guide vane body, and partial force transmission support is provided.
Preferably, the middle part of the lower supporting plate is provided with a mounting platform protruding towards the direction of the upper supporting plate, the upper supporting plate is correspondingly provided with a second through hole for the mounting platform to extend out, and the mounting platform is provided with a third through hole matched with the second threaded connecting piece;
the second threaded connecting piece is provided with external threads, penetrates through the third through hole and is connected to the mounting platform through a nut; or, the second threaded connector is provided with an internal threaded hole, and is in threaded connection with the internal threaded hole through the third through hole by a bolt.
In this scheme, set up bellied mounting platform and pass the backup pad in the middle part of lower backup pad, can reduce the length of second threaded connection spare, strengthen the intensity of second threaded connection spare, avoid the too big and fracture of second threaded connection spare atress.
Preferably, the guide vane body comprises a vane body, a guide vane upper edge plate and a guide vane lower edge plate, the guide vane upper edge plate and the guide vane lower edge plate are respectively positioned at two ends of the vane body in the length direction, the guide vane upper edge plate is in butt joint with the cover plate, and the guide vane lower edge plate is in butt joint with the upper support plate.
In this scheme, the guide vane upper edge plate and apron butt, guide vane lower edge plate and last backup pad butt can reduce the aerodynamic force that the guide vane body bore, avoids the guide vane body to produce great stress in the rounding weak point.
Preferably, the guide vane upper edge plate and/or the guide vane lower edge plate are/is detachably and fixedly connected with the blade body; and/or the number of the groups of groups,
the blade body, the guide vane upper edge plate and the guide vane lower edge plate are integrally formed.
Preferably, along the chord direction of the guide vane body, two ends of the cover plate are provided with limiting parts extending towards the direction of the guide vane upper edge plate, and two opposite ends of the guide vane upper edge plate are abutted against two opposite side walls of the limiting parts.
In the scheme, the limiting part is arranged on the cover plate and used for positioning the CMC guide vane body in the assembly process and helping the guide vane assembly to return to the initial assembly state in the cooling process.
Preferably, the extension length of the limiting part is smaller than the thickness of the guide vane upper edge plate; and/or the number of the groups of groups,
the lower end part of the side end surface of the guide vane upper edge plate is provided with a shielding part, and the limiting part is positioned above the shielding part.
In this scheme, adopt above-mentioned structure, can avoid spacing portion entering runner direct contact high temperature gas to lead to the apron to take place thermal deformation and influence the cooperation of apron and other parts.
Preferably, along the chord direction of the guide vane body, the two ends of the cover plate are provided with a front mounting structure and a rear mounting structure which are matched and mounted with the turbine casing.
In this scheme, adopt above-mentioned structure, be convenient for install turbine stator through the apron.
Preferably, a guide member is further arranged between the upper support plate and the lower support plate, one end of the guide member is connected with the upper support plate or the lower support plate, and the other end of the guide member is correspondingly and slidably connected in the first guide hole of the lower support plate or the upper support plate.
In this scheme, the guide is provided to restrict the in-plane relative movement between the upper support plate and the lower support plate of the elastic pallet, so that the upper support plate and the lower support plate can move relatively in the up-down direction as much as possible.
Preferably, the guide piece is a pin shaft, one end of the pin shaft is in interference fit connection with the upper support plate or the lower support plate, and the other end of the pin shaft is in clearance fit connection with the lower support plate or the upper support plate; and/or the number of the groups of groups,
the elastic piece is a spring, and the spring is sleeved on the outer peripheral side of the guide piece.
In the scheme, the guide piece adopts the installation structure, so that the installation is convenient; the elastic piece adopts the spring and is sleeved on the outer peripheral side of the guide piece, so that the influence of deflection of the spring in the telescoping process on the pre-tightening effect of the elastic supporting plate on the guide vane body is avoided.
Preferably, one end of the guide vane body, which is abutted against the upper supporting plate, is provided with a second guiding hole corresponding to the guiding piece, and the upper end of the guiding piece extends out of the upper supporting plate and slides in a matched manner with the second guiding hole.
In the scheme, the guide vane body can be positioned or acted by the transmission force by adopting the structure.
Preferably, the upper support plate is of a split structure, each split structure is abutted to the guide vane body, and each split structure is provided with the second guide hole.
In the scheme, the upper supporting plate adopts a split structure, so that friction stress generated by thermal mismatch can be reduced.
The invention also provides a turbine comprising turbine vanes as described above.
Preferably, the turbine further comprises a first-stage turbine casing and a second-stage turbine casing, two ends of the cover plate are respectively connected with the first-stage turbine casing and the second-stage turbine casing along the chord direction of the guide vane body, and the lower support plate is fixedly connected with the guide vane inner side installation part at the inner side of the turbine casing.
The invention also provides an aeroengine comprising a turbine as described above.
The invention has the positive progress effects that: according to the turbine guide vane, the guide vane body made of CMC materials is clamped and fixed between the cover plate and the elastic supporting plate through the elastic pre-tightening force of the elastic supporting plate at normal temperature, the cover plate and the elastic supporting plate are assembled with other metal parts in the turbine, other assembling structures are not arranged on the guide vane body made of CMC materials except the matching surfaces of the cover plate and the elastic supporting plate, and the simplification of the manufacturing process of the blade is realized; the cover plate is connected with the elastic supporting plate through a bearing component, and the bearing component plays a bearing role; in a high-temperature working state, under the pushing of aerodynamic force, the bearing component is abutted with the inner cavity wall of the guide vane body to realize force transmission, the aerodynamic force borne by the guide vane body is directly transmitted to the bearing component, the cover plate and the elastic supporting plate, so that larger stress is prevented from being generated at the rounding weak part of the guide vane body made of CMC material, and the turbine guide vane is ensured to bear larger aerodynamic load; through the use of the elastic supporting plate, the cover plate and the elastic supporting plate in the working state are always kept in contact with the guide vane body, the problem of thermal mismatch in the process of matching the guide vane body with the metal part is avoided, and the problem that a large gap is possibly generated between the CMC guide vane part and the metal part at high temperature is eliminated, so that the influence on the pneumatic performance of the turbine is avoided.
Drawings
FIG. 1 is a schematic view of a turbine vane according to a preferred embodiment of the present invention.
FIG. 2 is a structural exploded view of the turbine vane of FIG. 1.
FIG. 3 is a schematic vertical cross-section of the turbine vane of FIG. 1.
FIG. 4 is a schematic cross-sectional view of the turbine vane of FIG. 1.
FIG. 5 is a schematic structural view of a cover plate in the turbine vane of FIG. 1.
FIG. 6 is a schematic structural view of another view of a cover plate in the turbine vane of FIG. 1.
FIG. 7 is a schematic structural view of a force bearing component of the turbine vane of FIG. 1.
FIG. 8 is a schematic view of the structure of the resilient blade in the turbine vane of FIG. 1.
FIG. 9 is a partial cross-sectional view of the connection of the bearing member and the resilient blade of the turbine vane of FIG. 1.
FIG. 10 is a schematic view of the mounting location of turbine vanes in a turbine in a preferred embodiment of the present invention.
Reference numerals illustrate:
turbine vane 100
Guide vane body 11
Blade body 111
Guide vane upper edge plate 112
Guide vane lower edge plate 113
Cover plate 12
Front mounting structure 121
Rear mounting structure 122
Groove 123
Second air hole 124
Limit part 125
First through hole 126
Force bearing member 13
Upper end connecting portion 131
Convex hull 132
Lower end connection portion 133
Cooling holes 134
Cooling cavity 135
Boss 136
Third air hole 137
First air vent 138
Elastic pallet 14
Lower support plate 141
Mounting platform 1411
Upper support plate 142
Pin shaft mounting hole 1421
Second through hole 1422
Pin 143
Spring 144
Bolt 15
Nut 16
Primary turbine casing 200
Two-stage turbine casing 300
Guide vane inner side mounting portion 400
Detailed Description
The invention will now be more fully described by way of example only and with reference to the accompanying drawings, but the invention is not thereby limited to the scope of this example.
As shown in fig. 1-9, a turbine vane 100 according to an embodiment of the present invention includes a vane body 11 made of CMC material, the turbine vane 100 further includes a cover plate 12, an elastic supporting plate 14, and a bearing component 13, the elastic supporting plate 14 includes an upper supporting plate 142 and a lower supporting plate 141, an elastic member is disposed between the upper supporting plate 142 and the lower supporting plate 141, and two ends of the vane body 11 in a length direction are respectively connected to the cover plate 12 and the upper supporting plate 142. The bearing component 13 is arranged in the inner cavity of the guide vane body 11, at least part of the outer surface of the bearing component 13 is abutted against the inner cavity wall of the guide vane body 11, the upper end connecting part 131 of the bearing component 13 is connected with the cover plate 12, and the lower end connecting part 133 of the bearing component 13 is connected with the lower supporting plate 141 and enables the elastic piece to be in a compressed state. The bearing component 13 can be made of a traditional high-temperature alloy material, or can be made of a high-temperature resistant ceramic matrix composite material partially or completely.
In the embodiment, the guide vane body 11 made of CMC materials is clamped and fixed between the cover plate 12 and the elastic supporting plate 14 by the elastic pre-tightening force of the elastic supporting plate 14 at normal temperature, and is assembled with other metal components in the turbine by the cover plate 12 and the elastic supporting plate 14, and other assembling structures are not arranged on the guide vane body 11 made of CMC materials except the matching surfaces of the guide vane body 11 and the cover plate 12 and the elastic supporting plate 14, so that the manufacturing process of the blade is simplified; the cover plate 12 is connected with the elastic supporting plate 14 through the bearing component 13, and the bearing component 13 plays a bearing role; in a high-temperature working state, under the pushing of aerodynamic force, the bearing part 13 is abutted with the inner cavity wall of the guide vane body 11 to realize force transmission, the aerodynamic force borne by the guide vane body 11 is directly transmitted to the bearing part 13, the cover plate 12 and the elastic supporting plate 14, so that larger stress is avoided at the rounding weak part of the guide vane body 11 made of CMC material, and the turbine guide vane 100 is ensured to bear larger aerodynamic load; through the normal-temperature compression and high Wen Chi relaxation processes of the elastic pieces in the elastic supporting plates 14, the cover plate 12 and the elastic supporting plates 14 in the working state are always kept in a contact state with the guide vane body 11, the problem of thermal mismatch in the process of matching the guide vane body 11 with the metal parts is avoided, the initial installation pretightening force is reduced, and the large gap possibly generated between the CMC guide vane parts and the metal parts at high temperature is eliminated, so that the influence on the aerodynamic performance of the turbine is avoided.
The upper end connection portion 131 of the force bearing member 13 includes a first screw connection member fixed to the cap plate 12 by nuts or bolts. As shown in fig. 2, 3 and 7, in the present embodiment, the first threaded connection is a stud with external threads, and the stud passes through the cover plate 12 and is fastened by a nut to fix the upper end of the bearing member 13 to the cover plate 12. In other embodiments, the first threaded connection may be a connection structure with an internally threaded hole, and the upper end of the bearing member 13 is fixed to the cover plate 12 by inserting a bolt from outside the cover plate 12 and screwing the bolt thereto. The upper end connecting part 131 of the bearing part 13 is arranged to be a threaded connecting piece, so that the bearing part 13 is convenient to install and detach, and meanwhile, the installation angle of the bearing part 13 in the guide vane body 11 is convenient to adjust, so that the bearing part 13 can bear aerodynamic force transmitted by the guide vane body 11 better.
As shown in fig. 2 and fig. 5-7, in this embodiment, the upper end connection portion 131 of the bearing member 13 further includes a boss 136, and a side of the cover plate 12 facing the bearing member 13 has a groove 123, where the boss 136 matches with the groove 123. The boss 136 is arranged on the bearing part 13 and is matched with the groove 123 arranged on the cover plate 12 to form a mortise and tenon structure, so that the positioning of the bearing part 13 and the rigidity reinforcement of the joint of the bearing part and the cover plate are realized. The recess 123 and the boss 136 may be of any shape, and are not limited herein.
As shown in fig. 7, in the present embodiment, the first threaded connection is disposed on the boss 136, and the bottom of the groove 123 is correspondingly provided with a first through hole 126 through which the first threaded connection passes. The first threaded connecting piece is arranged on the boss 136, so that the structure of the joint of the bearing part 13 and the cover plate 12 is more compact, and meanwhile, the radial force born by the first threaded connecting piece is reduced, and the first threaded connecting piece is prevented from breaking.
In other embodiments, the first threaded connection and the boss 136 may also be separately provided, and the specific structure will not be repeated.
As shown in fig. 3, in the present embodiment, the force-bearing member 13 has a cooling cavity 135, and the side wall of the force-bearing member 13 is penetrated with a cooling hole 134 communicating with the cooling cavity 135. By arranging the cooling cavity 135 in the bearing component 13, the side wall of the bearing component 13 is provided with the cooling hole 134, so that cold air in the cooling cavity 135 forms impact cooling on the inner wall of the guide vane body 11 to reduce the temperature of the guide vane body 11. Further optimization of the force transmission path can be achieved by adding stiffening ribs in the cooling chamber 135 of the force-bearing part 13.
As shown in fig. 3, 5 and 7, a first air vent 138 is formed in the boss 136, and a second air vent 124 corresponding to the first air vent 138 is formed in the groove 123 of the cover plate 12, and the second air vent 124 communicates with the cooling cavity 135 through the first air vent 138. By correspondingly arranging the first air vent 138 and the second air vent 124 on the boss 136 and the cover plate 12, cooling air flow outside the casing is conveniently led into the cooling cavity 135 to cool the CMC guide vane body 11.
As shown in fig. 4, a third air vent 137 is arranged at the bottom of the bearing component 13, and the third air vent 137 is communicated with the cooling cavity 135 and the inner cavity of the guide vane body 11. The third air-inducing hole 137 is arranged at the bottom of the bearing component 13, so that the cooling air flow flows out from between the lower edge plate 113 of the guide vane and the elastic supporting plate 14 after passing through the cooling cavity 135, the working temperature of the elastic piece in the elastic supporting plate 14 is reduced, the reliability of the elastic piece is improved, and meanwhile, the temperature of the lower edge plate 113 of the guide vane and the temperature of the elastic supporting plate 14 can be reduced, thereby reducing the thermal deformation amplitude of the lower edge plate 113 of the guide vane and the thermal deformation amplitude of the elastic supporting plate 14, and reducing the influence caused by thermal mismatch.
As shown in fig. 3, 4 and 7, in the present embodiment, the outer surface of the bearing component 13 is provided with a convex hull 132, and the convex hull 132 abuts against the inner cavity wall of the guide vane body 11. The convex hulls 132 are arranged on the outer surfaces of the bearing parts 13, so that the bearing parts 13 are ensured to be abutted with the guide vane bodies 11, aerodynamic force generated when the bearing parts 13 transmit an engine to work is ensured, manufacturing deviation can be allowed to exist on the inner wall surfaces of the guide vane bodies 11 by arranging the convex hulls 132, no additional matching surfaces are needed, the structure of the CMC guide vane bodies 11 is simplified, the inner and outer wall surfaces of the guide vane bodies 11 are allowed to be manufactured into complex three-dimensional curved surfaces, and the aerodynamic efficiency is improved and the manufacturing process is simplified. In addition, the convex hulls 132 can keep a certain gap between the bearing part 13 and the guide vane body 11, so that higher impact cooling efficiency is obtained.
Specifically, in this embodiment, the guide vane body 11 has a windward side and a leeward side, and the convex hull 132 is disposed on the inner cavity wall of the guide vane body 11 corresponding to the windward side and the leeward side of the bearing component 13. Under the condition that the convex hulls 132 are arranged on two sides, in the room temperature assembly state, proper gaps are reserved between the convex hulls 132 on the side with smaller bearing force and the inner wall surface of the CMC guide vane body 11, so that the bearing member 13 can be installed into a designated position along the profile curve of the inner cavity of the guide vane body 11, and the reserved gaps are enough to ensure that the expansion amount generated by heating the bearing member 13 in the working state can not generate large extrusion stress with the inner wall surface of the guide vane body 11.
In other embodiments, in order to increase the feasibility of assembling the bearing component 13 and the guide vane body 11 under the condition of allowable strength, the convex hull 132 may be only retained on one side of the bearing component 13, and the other side is not provided, i.e. the convex hull 132 is provided on the inner cavity wall of the guide vane body 11 corresponding to the windward side of the bearing component 13.
The convex hull 132 can be integrally formed with the bearing component 13, and the same material is used, and can also be added by means of later welding and the like, and different materials are adopted with the bearing component 13, so that the heat resistance and modulus at the convex hull 132 can meet the requirements, and the force transmission efficiency can be improved. In this embodiment, the convex hull 132 has a spherical bulge; the convex hull 132 and the bearing component 13 are integrally formed, and are made of the same material, so that cracking caused by heating is avoided.
Additional cooling holes 134 can be arranged on the periphery of the convex hull 132, so that the temperature of a contact position is further reduced, and the heat resistance requirement of the material is reduced; the position, height and number of the convex hulls 132 can be adjusted according to the actual stress conditions, so that the stress directions and the stress amounts of the components in all working states can reach the standards. During the assembly process, the bearing part 13 and the cover plate 12 allow a small amount of relative movement before being completely fastened, so that the target convex hull 132 contacts with the inner wall surface of the guide vane body 11 during the assembly process, and the force transmission path in the working state is determined. The target convex hull 132 should be a convex hull 132 that is better for the force transfer effect selected by calculation in advance.
The lower end connection portion 133 of the force bearing member 13 includes a second screw connection member fixed to the lower support plate 141 by nuts or bolts.
As shown in fig. 9, in the present embodiment, the second screw-threaded connector is a connection structure having an internally threaded hole, and the lower end of the load-bearing member 13 is fixed to the elastic pallet 14 by inserting a bolt from outside the lower load-bearing plate and screwing it. In other embodiments, the second threaded connection is a stud with external threads, and the stud passes through the elastic supporting plate 14 and is fastened by a nut to fix the lower end of the bearing component 13 with the elastic supporting plate 14.
The lower end connecting part 133 of the bearing part 13 is arranged as a threaded connecting piece, so that the bearing part 13 is convenient to install and detach, and the installation angle of the bearing part 13 in the guide vane body 11 is convenient to adjust, so that the bearing part 13 can bear aerodynamic force transmitted by the guide vane body 11 better. And the compression amount of the elastic piece in the elastic supporting plate 14 at normal temperature assembly can be adjusted according to actual demands, so that the elastic piece still keeps a small compression amount under the most severe working condition, and a pressing force is provided between the upper supporting plate 142 and the guide vane body 11, so that the cover plate 12 and the elastic supporting plate 14 still keep a certain clamping effect on the guide vane body 11, and partial force transmission support is provided.
As shown in fig. 8 to 9, in this embodiment, the middle part of the lower support plate 141 has a mounting platform 1411 protruding toward the upper support plate 142, the upper support plate 142 is correspondingly provided with a second through hole 1422 for the mounting platform 1411 to protrude, the mounting platform 1411 has a third through hole matched with the second threaded connecting member, and the mounting platform 1411 is threaded with the second threaded connecting member by penetrating the third through hole through a bolt. The raised mounting platform 1411 is arranged in the middle of the lower support plate 141 and penetrates through the upper support plate 142, so that the length of the second threaded connecting piece can be reduced, the strength of the second threaded connecting piece is enhanced, and the second threaded connecting piece is prevented from being broken due to overlarge stress.
Similarly, when the second threaded connection is a threaded stud with external threads, the second threaded connection passes through the third through hole and is connected to the mounting platform 1411 by a nut.
As shown in fig. 1 to 3, the vane body 11 includes a vane body 111, a vane upper edge plate 112 and a vane lower edge plate 113, the vane upper edge plate 112 and the vane lower edge plate 113 are respectively located at two ends of the vane body 111 in the length direction, the vane upper edge plate 112 is abutted with the cover plate 12, and the vane lower edge plate 113 is abutted with the upper support plate 142. The guide vane upper edge plate 112 is abutted with the cover plate 12, and the guide vane lower edge plate 113 is abutted with the upper supporting plate 142, so that aerodynamic force born by the guide vane body 11 can be reduced, and the guide vane body 11 is prevented from generating larger stress at the rounding weak position.
Of course, in some embodiments, the vane upper edge plate 112 and the cover plate 12 may be fixedly connected, and the vane lower edge plate 113 and the upper support plate 142 may also be fixedly connected.
The blade body 111, the guide vane upper edge plate 112 and the guide vane lower edge plate 113 are integrally formed. The fibers are continuous.
In other embodiments, the vane upper edge plate 112 and/or the vane lower edge plate 113 are detachably and fixedly connected to the vane body 111, i.e. assembled together by mortise and tenon structures or bolting, and the fibers are discontinuous.
As shown in fig. 3, 5 and 6, along the chord direction of the guide vane body 11, two ends of the cover plate 12 are provided with limiting portions 125 extending toward the guide vane upper edge plate 112, and two opposite ends of the guide vane upper edge plate 112 are abutted against opposite side walls of the two limiting portions 125. The cover plate 12 is provided with a limiting part 125 for positioning the CMC guide vane body 11 in the assembly process and helping the guide vane assembly to return to the initial assembly state in the cooling process.
In the present embodiment, the extending length of the limiting portion 125 is smaller than the thickness of the guide vane upper edge plate 112. The limit part 125 can be prevented from entering the runner to directly contact with high-temperature fuel gas, so that the cover plate 12 is prevented from thermal deformation to influence the matching of the cover plate 12 and other components.
Alternatively, in other embodiments, the lower end of the side end surface of the guide vane upper edge plate 112 has a shielding portion, and the limiting portion 125 is located above the shielding portion. Contact with high temperature gas is blocked by way of external structural shielding or local extension of the vane upper edge plate 112.
The limiting portion 125 and the cover plate 12 may be integrated or separate components.
As shown in fig. 5 and 6, in the chord direction of the vane body 11, both ends of the cover plate 12 have a front mounting structure 121 and a rear mounting structure 122 mounted in cooperation with the turbine casing, with which the turbine vane 100 is easily mounted through the cover plate 12.
A guide member is further provided between the upper support plate 142 and the lower support plate 141, one end of the guide member is connected to the upper support plate 142 or the lower support plate 141, and the other end of the guide member is correspondingly slidably connected to the lower support plate 141 or the first guide hole of the upper support plate 142. The guide is provided to restrict the in-plane relative movement between the upper support plate 142 and the lower support plate 141 of the elastic pallet 14, so that the upper support plate 142 and the lower support plate 141 are moved relatively in the up-down direction as much as possible.
As shown in fig. 8 and 9, the guide is a pin 143, one end of the pin 143 is in interference fit connection with a pin mounting hole 1421 on the upper support plate 142 or the lower support plate 141, and the other end of the pin 143 is in clearance fit connection with a first guide hole of the lower support plate 141 or the upper support plate 142. The guide piece adopts the installation structure, and is convenient to install. The elastic member is a spring 144, and the spring 144 is sleeved on the outer peripheral side of the guide member. The elastic piece adopts the spring 144 and is sleeved on the outer peripheral side of the guide piece, so that the influence of deflection of the spring 144 in the telescoping process on the pre-tightening effect of the elastic supporting plate 14 on the guide vane body 11 is avoided.
The spring 144 may be a superalloy coil spring, belleville spring or ceramic spring allowing radial relative movement between the upper support plate 142 and the lower support plate 141; the spring parameters and the pre-compression force of each spring 144 may be different.
In other embodiments, the guide may be mounted and guided in other ways, and the spring 144 may be provided separately from the guide.
The end of the guide vane body 11 abutting against the upper support plate 142 has a second guide hole corresponding to a guide member, and the upper end of the guide member extends out of the upper support plate 142 and slides in cooperation with the second guide hole (not shown). With the above structure, the guide vane body 11 can be positioned or transmitted.
The upper support plate 142 is a split structure, each split structure is abutted against the guide vane body 11, and each split structure is provided with a second guide hole. The upper support plate 142 is constructed in a split structure to reduce friction stress generated by thermal mismatch.
The present embodiment also provides an aeroengine comprising a turbine comprising the turbine vane 100 described above. As shown in fig. 10, the turbine further includes a first-stage turbine casing 200 and a second-stage turbine casing 300, two ends of the cover plate 12 of the turbine vane 100 are respectively connected to the first-stage turbine casing 200 and the second-stage turbine casing 300 along the chord direction of the vane body 11, the lower support plate 141 is fixedly connected to the inner side mounting part 400 of the vane inside the turbine casing, and the inner side mounting part 400 of the vane inside the turbine casing may be a honeycomb seal structure or other metal components.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (22)
1. The turbine guide vane comprises a guide vane body made of CMC materials, and is characterized by further comprising a cover plate, an elastic supporting plate and a bearing component, wherein the elastic supporting plate comprises an upper supporting plate and a lower supporting plate, an elastic piece is arranged between the upper supporting plate and the lower supporting plate, and two ends of the guide vane body in the length direction are respectively connected with the cover plate and the upper supporting plate;
the bearing component is arranged in the inner cavity of the guide vane body, at least part of the outer surface of the bearing component is abutted to the inner cavity wall of the guide vane body, the upper end connecting part of the bearing component is connected with the cover plate, and the lower end connecting part of the bearing component is connected with the lower supporting plate and enables the elastic component to be in a compressed state.
2. The turbine vane of claim 1, wherein the upper end connection of the load bearing member includes a first threaded connection secured to the cover plate by a nut or bolt; and/or the number of the groups of groups,
the upper end connecting portion of the bearing component comprises a boss, a groove is formed in one side, facing the bearing component, of the cover plate, and the boss is matched with the groove.
3. The turbine vane of claim 2, wherein the first threaded connection is disposed on the boss, and a bottom of the groove is correspondingly provided with a first through hole through which the first threaded connection passes.
4. The turbine vane of claim 2 wherein said force bearing member has a cooling cavity, a sidewall of said force bearing member extending through a cooling hole in communication with said cooling cavity.
5. The turbine vane of claim 4 wherein a first bleed hole is provided in the boss and a second bleed hole corresponding to the first bleed hole is provided in the cover plate in the recess, the second bleed hole communicating with the cooling cavity through the first bleed hole.
6. The turbine vane of claim 4 wherein a third bleed hole is provided in a bottom of the force bearing member, the third bleed hole being in communication with the cooling cavity and an inner cavity of the vane body.
7. The turbine vane of claim 1 wherein the outer surface of the bearing member is provided with a convex hull that abuts against the inner cavity wall of the vane body.
8. The turbine vane of claim 7, wherein the vane body has a windward side and a leeward side, the convex hull is provided on an inner cavity wall of the vane body where the bearing component faces the windward side and the leeward side, or the convex hull is provided on an inner cavity wall of the vane body where the bearing component faces the windward side; and/or the number of the groups of groups,
the convex hull is a spherical bulge; and/or the number of the groups of groups,
the convex hull and the bearing component are integrally formed.
9. The turbine vane of claim 1, wherein the lower end connection of the load bearing member includes a second threaded connection secured to the lower support plate by a nut or bolt.
10. The turbine vane of claim 9, wherein a middle portion of the lower support plate has a mounting platform protruding toward the upper support plate, a second through hole for the mounting platform to protrude is correspondingly provided in the upper support plate, and the mounting platform has a third through hole matched with the second threaded connector;
the second threaded connecting piece is provided with external threads, penetrates through the third through hole and is connected to the mounting platform through a nut; or, the second threaded connector is provided with an internal threaded hole, and is in threaded connection with the internal threaded hole through the third through hole by a bolt.
11. The turbine vane of claim 1 wherein the vane body includes a vane body, a vane upper edge plate and a vane lower edge plate, the vane upper edge plate and the vane lower edge plate being located at respective ends of the vane body in a length direction, the vane upper edge plate being in abutment with the cover plate, the vane lower edge plate being in abutment with the upper support plate.
12. The turbine vane as claimed in claim 11 wherein the vane upper edge plate and/or the vane lower edge plate is detachably fixedly connected to the blade body; and/or the number of the groups of groups,
the blade body, the guide vane upper edge plate and the guide vane lower edge plate are integrally formed.
13. The turbine vane of claim 11 wherein said cover plate has limiting portions at opposite ends extending in a direction of said vane upper edge plate along a chord direction of said vane body, opposite ends of said vane upper edge plate abutting opposite sidewalls of two of said limiting portions.
14. The turbine vane of claim 13 wherein the limit portion has an extension length less than a thickness of the vane upper edge plate; and/or the number of the groups of groups,
the lower end part of the side end surface of the guide vane upper edge plate is provided with a shielding part, and the limiting part is positioned above the shielding part.
15. The turbine vane of claim 1 wherein the cover plate has forward and aft mounting structures at both ends thereof for mating mounting with a turbine case along a chordwise direction of the vane body.
16. The turbine vane of claim 1 further having a guide member between the upper support plate and the lower support plate, one end of the guide member being connected to the upper support plate or the lower support plate, and the other end of the guide member being correspondingly slidably connected within the first guide hole of the lower support plate or the upper support plate.
17. The turbine vane of claim 16, wherein the guide is a pin having one end in interference fit connection with the upper support plate or the lower support plate and the other end in clearance fit connection with the lower support plate or the upper support plate; and/or the number of the groups of groups,
the elastic piece is a spring, and the spring is sleeved on the outer peripheral side of the guide piece.
18. The turbine vane of claim 16, wherein an end of the vane body abutting the upper support plate has a second guide hole corresponding to the guide member, and an upper end of the guide member extends out of the upper support plate and slides in cooperation with the second guide hole.
19. The turbine vane of claim 18 wherein said upper support plate is a split structure, each said split structure abutting said vane body, each said split structure being provided with said second guide hole.
20. A turbine comprising the turbine vane of any one of claims 1-19.
21. The turbine vane of claim 20, wherein the turbine further comprises a primary turbine casing and a secondary turbine casing, the two ends of the cover plate are respectively connected to the primary turbine casing and the secondary turbine casing along the chord direction of the vane body, and the lower support plate is fixedly connected to a vane inner side mounting part inside the turbine casing.
22. An aeroengine comprising a turbine as claimed in any of claims 20 to 21.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210842468.XA CN117449918A (en) | 2022-07-18 | 2022-07-18 | Turbine guide vane, turbine comprising same and aeroengine |
| PCT/CN2023/107969 WO2024017261A1 (en) | 2022-07-18 | 2023-07-18 | Turbine guide vane and turbine containing same, and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210842468.XA CN117449918A (en) | 2022-07-18 | 2022-07-18 | Turbine guide vane, turbine comprising same and aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117449918A true CN117449918A (en) | 2024-01-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210842468.XA Pending CN117449918A (en) | 2022-07-18 | 2022-07-18 | Turbine guide vane, turbine comprising same and aeroengine |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN117449918A (en) |
| WO (1) | WO2024017261A1 (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7824152B2 (en) * | 2007-05-09 | 2010-11-02 | Siemens Energy, Inc. | Multivane segment mounting arrangement for a gas turbine |
| US8292580B2 (en) * | 2008-09-18 | 2012-10-23 | Siemens Energy, Inc. | CMC vane assembly apparatus and method |
| US10329931B2 (en) * | 2014-10-01 | 2019-06-25 | United Technologies Corporation | Stator assembly for a gas turbine engine |
| CN110030037B (en) * | 2018-01-11 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Turbine guide vane, turbine guide vane assembly and core machine |
| US10767497B2 (en) * | 2018-09-07 | 2020-09-08 | Rolls-Royce Corporation | Turbine vane assembly with ceramic matrix composite components |
-
2022
- 2022-07-18 CN CN202210842468.XA patent/CN117449918A/en active Pending
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2023
- 2023-07-18 WO PCT/CN2023/107969 patent/WO2024017261A1/en unknown
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| WO2024017261A1 (en) | 2024-01-25 |
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