CN116335771A - Combined turbine stator blade assembly made of dissimilar materials - Google Patents
Combined turbine stator blade assembly made of dissimilar materials Download PDFInfo
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- CN116335771A CN116335771A CN202310179048.2A CN202310179048A CN116335771A CN 116335771 A CN116335771 A CN 116335771A CN 202310179048 A CN202310179048 A CN 202310179048A CN 116335771 A CN116335771 A CN 116335771A
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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
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/005—Selecting particular materials
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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
- 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
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the technical field of aeroengines, and particularly relates to a combined type turbine stator blade component made of different materials. The invention has the advantages of excellent temperature resistance of the ceramic matrix composite blade, reliable mechanical property and excellent aerodynamic property of the high-temperature alloy blade, improves the temperature bearing capacity of the front edge of the high-pressure turbine guide blade, solves the problem of overtemperature of the front edge of the turbine guide blade of the new generation advanced engine, realizes the lightweight of the turbine blade, prolongs the working life of the blade, and generally improves the overall performance of the aeroengine.
Description
Technical Field
The invention belongs to the technical field of aeroengines, and particularly relates to a combined type turbine stator blade assembly made of different materials.
Background
The turbine guide vane converts the heat energy of the high-temperature gas part flowing through the turbine guide vane into kinetic energy and changes the direction of the gas flow so as to meet the inlet requirement of the working vane, is a key component for determining the turbine efficiency, and is an important part of the turbine part of the aeroengine. With the development of aero-engines, the thrust-weight ratio index of the engine and the inlet temperature of the turbine are continuously improved. The harsher high temperature and high thrust-weight ratio requirement of the engine bring about the problems of reduced service life of turbine parts, overweight of the engine and the like, the front edge of the high-pressure turbine guide vane is directly flushed by high-temperature fuel gas, and the overtemperature problem of the front edge position of the vane is serious. The ceramic matrix composite material has the characteristics of low density, outstanding temperature resistance and the like, and can better solve the problems of over-temperature and over-heavy weight of the front edge of the turbine guide vane of the engine when being used as the material of the turbine guide vane. But is limited by the forming and preparing process capability of the ceramic matrix composite material, and the manufacturing of the ceramic matrix high-pressure turbine guide vane with the structures of large folding of the upper and lower edge plates, complex inner cavities and the like is difficult to realize; meanwhile, the middle and rear parts of the blade are high flow velocity areas, the surface quality of the blade profile has a great influence on aerodynamic efficiency, the larger the thickness of the tail edge of the blade body is, the larger the wake loss of the blade is, the decisive influence on turbine efficiency is achieved, the maximum thickness requirement of the tail edge of the blade body is generally no more than 1.2mm, and the ceramic matrix composite material is limited by the characteristics of materials and the technological level, so that the requirements of the surface quality and the thickness of the tail edge of the middle and rear parts of the blade are difficult to meet.
Disclosure of Invention
In view of this, the present invention provides a combined turbine stator vane assembly made of heterogeneous materials, in which a ceramic-based vane is used to bear one end of the high-temperature gas washout, and a metal vane is used in a high-flow-velocity-resistant flow guiding area with complex structure and great processing difficulty. The invention has the advantages of excellent temperature resistance of the ceramic matrix composite blade, reliable mechanical property and excellent aerodynamic property of the high-temperature alloy blade, improves the temperature bearing capacity of the front edge of the high-pressure turbine guide blade, solves the problem of overtemperature of the front edge of the turbine guide blade of the new generation advanced engine, realizes the lightweight of the turbine blade, prolongs the working life of the blade, and generally improves the overall performance of the aeroengine.
In order to achieve the technical purpose, the invention adopts the following specific technical scheme:
a combined dissimilar material turbine stator blade assembly comprising:
a ceramic-based blade comprising a ceramic-based blade body; the ceramic-based She Shenwei ceramic-based hollow air-cooled structure is arranged at one end of the turbine stator blade, which is subjected to high-temperature gas flushing, and the windward side faces the incoming direction of the high-temperature gas;
a metal blade comprising a metal-based metal blade body; the metal blade body is of a hollow double-layer wall air-cooled structure, and the two layers of blade body walls form a hollow blade body structure with gradually changed thickness; the large-thickness front end of the metal blade body is spliced with the lee surface of the ceramic base blade body, and the small-thickness convergence tail end of the metal blade body is a high-flow-velocity-resistant flow guiding area of the turbine stator blade;
a metal upper edge plate; a plurality of metal upper edge plates are spliced in sequence to form an outer ring structure;
a metal lower edge plate; a plurality of metal lower edge plates are spliced in sequence to form an inner ring structure;
wherein: the ceramic-based blade and the metal blade are combined into one turbine stator blade; the outer ring structure and the inner ring structure are coaxially arranged; the cavity between the outer ring structure and the inner ring structure forms a part of a diversion cavity; the plurality of turbine stator blades are symmetrically and uniformly distributed in the flow guiding cavity by the center axis of the flow guiding cavity.
Further, the combined type dissimilar material turbine stator blade assembly further comprises an upper edge plate and an upper hanging nail; the upper edge plate is spliced at one end of the metal upper edge plate in the gas incoming direction of the high-temperature gas; a plurality of upper edge plates are spliced in sequence to form a front end ring; the front end ring and the flow guide cavity are coaxially arranged; another part of the diversion cavity is formed between the inner ring surface of the front end ring and the metal lower edge plate;
the ceramic-based blade is provided with an upper mounting edge which is mutually fixed with the ceramic-based blade body on the top surface which is not contacted with the high-temperature fuel gas and the metal blade body; the ceramic-based blade is spliced between two adjacent upper edge plates based on the upper mounting edge;
the upper hanging top is used for fixing two adjacent upper edge plates at the outer ring surface of the front end ring.
Furthermore, the ceramic-based blade is provided with a lower end positioning boss which is mutually fixed with the ceramic-based blade body on the bottom surface which is not contacted with the high-temperature fuel gas and the metal blade body;
the metal lower edge plate is provided with a groove at one end of the high-temperature fuel gas in the gas incoming direction
The ceramic-based blade is spliced in the groove based on the positioning boss.
Further, a cold air cavity is arranged in the ceramic base blade body; the ceramic-based shell of the ceramic-based blade body is uniform in wall thickness and is formed by weaving ceramic-based composite materials, the main body is provided with a plurality of ceramic-based blade body air film holes for conducting air in the cold air cavity and the diversion cavity, and the upper mounting edge is provided with an air inlet channel.
Further, the wall thickness of the ceramic-based shell is 2-3 mm; the aperture of the ceramic base blade body air film hole is smaller than 0.6mm.
Further, the metal blade is formed by integral casting of high-temperature single crystal alloy; an air collecting cavity is arranged in the metal blade body, and a plurality of impact cavities are arranged at the interlayer between the double-layer walls;
the impact cavity is communicated with the gas collecting cavity based on the blade impact hole;
a plurality of metal blade body air film holes are formed at the positions of the blade basin and the blade back where the metal blade body is contacted with the high-temperature fuel gas; the metal blade body air film hole is used for conducting the impact cavity and the diversion cavity;
a tail split joint is arranged at the convergence tail end of the metal blade body; and the tail split joint gas conducts the impact cavity and the diversion cavity.
Further, the aperture of the blade body impact hole is 1-1.5 mm; the aperture of the metal blade body air film hole is smaller than 0.5mm.
Further, a plurality of front-end impact holes are formed in the joint of the metal blade body and the ceramic-based blade; the front end air film hole is in air conduction with the air collecting cavity.
Further, a plurality of front-end air film holes are formed in the joint of the metal blade body and the ceramic-based blade; and one end of the front end air film hole is in air conduction with the splicing part between the metal blade body and the ceramic base blade, and the other end of the front end air film hole is in conduction with the flow guide cavity.
Further, the metal blade is spliced between the metal upper edge plate and the metal lower edge plate based on the top surface and the bottom surface which are not contacted with the high-temperature fuel gas and the metal blade body.
By adopting the technical scheme, the invention has the following beneficial effects:
a) Compared with a single high-temperature alloy material blade, the invention can effectively improve the temperature resistance level by more than 200 ℃;
b) Compared with single crystal superalloy cast blades, the invention can reduce the weight by more than 20 percent;
c) Compared with the metal blades, the invention can reduce the cold air consumption of the turbine guide blades and improve the engine efficiency;
d) The ceramic matrix composite part has simple structure and good manufacturing manufacturability.
e) The assembly mode blade has reliable structure and good assembly performance, and can effectively solve the problem of thermal matching between the ceramic base and the metal piece.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present disclosure, and other drawings may be obtained according to these drawings without inventive effort to a person of ordinary skill in the art.
FIG. 1 is an exploded view of a combined dissimilar material turbine stator blade assembly in accordance with an embodiment of the present invention;
FIG. 2 is an assembled view of a combined dissimilar material turbine stator blade assembly in accordance with an embodiment of the present invention;
FIG. 3 is an axial cross-sectional view of a combined dissimilar material turbine stator blade assembly in accordance with an embodiment of the present invention;
FIG. 4 is a radial cross-sectional view of a combined dissimilar material turbine stator blade assembly in accordance with an embodiment of the invention;
wherein: 1. a ceramic-based blade; 101. a ceramic base blade body; 102. positioning the boss; 103. an upper mounting edge; 104. a mounting hole; 105. ceramic base blade body air film holes; 106. an air intake passage; 107. a cold air chamber; 108. ceramic-based fibers; 2. a metal blade; 201. a metal blade body; 202. a metal upper edge plate; 203. a metal lower edge plate; 204. a groove; 205. a front end impingement hole; 205a, blade body impingement holes; 206. metal blade body air film hole; 206a, front end air film holes; 207. tail split joint; 208. an air collection cavity; 209. an impingement cavity; 3. an upper edge plate; 301. a mounting boss; 302. a mounting edge; 303. upper edge plate bolt holes; 304. an inner annulus; 4. a hanging ring is arranged; 401. an upper hanging ring bolt hole; 5. and (5) a screw.
Detailed Description
Embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present disclosure will become readily apparent to those skilled in the art from the following disclosure, which describes embodiments of the present disclosure by way of specific examples. It will be apparent that the described embodiments are merely some, but not all embodiments of the present disclosure. The disclosure may be embodied or practiced in other different specific embodiments, and details within the subject specification may be modified or changed from various points of view and applications without departing from the spirit of the disclosure. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art without inventive effort, based on the embodiments in this disclosure are intended to be within the scope of this disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concepts of the disclosure by way of illustration, and only the components related to the disclosure are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
In one embodiment of the present invention, a combined dissimilar material turbine stator blade assembly is provided, as shown in FIGS. 1-4, comprising:
a ceramic base blade 1 including a ceramic base blade body 101; the ceramic base blade body 101 is a ceramic base hollow air-cooled structure and is arranged at one end of the turbine stator blade, which is subjected to high-temperature gas flushing, and the windward side faces the incoming direction of the high-temperature gas;
a metal blade 2 including a metal-based metal blade body 201; the metal blade body 201 is a hollow double-layer wall air-cooled structure, and the two layers of blade body walls form a hollow blade body structure with gradually changed thickness; the large-thickness front end of the metal blade body 201 is spliced with the lee surface of the ceramic base blade body 101, and the small-thickness convergence tail end of the metal blade body 201 is a high-flow-velocity-resistant flow guiding area of the turbine stator blade;
a metal upper rim plate 202; a plurality of metal upper edge plates 202 are spliced in sequence to form an outer ring structure;
a metal lower rim plate 203; a plurality of metal lower edge plates 203 are spliced in sequence to form an inner ring structure;
wherein: the ceramic-based blade 1 and the metal blade 2 are combined into a turbine stator blade; the outer ring structure and the inner ring structure are coaxially arranged; the cavity between the outer ring structure and the inner ring structure forms a part of the diversion cavity; the plurality of turbine stator blades are symmetrically and uniformly distributed in the flow guide cavity by the center axis of the flow guide cavity.
In this embodiment, as shown in fig. 1 and 2, the combined type dissimilar material turbine stator blade assembly further includes an upper rim plate 3 and an upper hanging nail; the upper edge plate 3 is spliced at one end of the metal upper edge plate 202 in the gas incoming direction of the high-temperature gas; a plurality of upper edge plates 3 are spliced in sequence to form a front end ring; the front end ring and the flow guiding cavity are coaxially arranged; another part of the diversion cavity is formed between the inner annular surface 304 of the front end ring and the metal lower edge plate 203;
the ceramic base blade 1 is provided with an upper mounting edge 103 which is mutually fixed with the ceramic base blade body 101 on the top surface which is not contacted with the high-temperature fuel gas and the metal blade body 201; the ceramic-based blade 1 is spliced between two adjacent upper edge plates 3 based on an upper mounting edge 103;
the upper hanging top is used for fixing two adjacent upper edge plates 3 at the outer ring surface of the front end ring.
In the present embodiment, as shown in fig. 1, the ceramic base blade 1 is provided with a lower end positioning boss 102 fixed to the ceramic base blade body 101 on the bottom surface which is not in contact with the high-temperature gas and the metal blade body 201;
the metal lower edge plate 203 is provided with a groove 204 at one end of the high temperature gas in the gas direction
The ceramic base blade 1 is spliced in the groove 204 based on the positioning boss 102.
In this embodiment, as shown in fig. 3, a cold air cavity 107 is provided in the ceramic base blade body 101; the ceramic base shell of the ceramic base blade body 101 has uniform wall thickness and is formed by weaving a ceramic base composite material, a plurality of ceramic base blade body air film holes 105 communicated with a cold air cavity 107 are arranged on the main body, and an air inlet channel 106 is arranged at the upper mounting edge 103.
In this embodiment, the wall thickness of the ceramic-based shell is 2-3 mm; the aperture of the ceramic base blade body air film hole 105 is smaller than 0.6mm.
In the present embodiment, the metal blade 2 is formed by bulk casting of a high-temperature single crystal alloy; as shown in fig. 3, the metal blade 201 is internally provided with an air collecting cavity 208, and a plurality of impact cavities 209 are arranged at the interlayer between the double-layer walls;
the impact cavity 209 is in air communication with the gas collection cavity 208 based on the blade impact hole 205 a;
a plurality of metal blade body air film holes 206 are arranged at the positions of the blade basin and the blade back where the metal blade body 201 is contacted with the high-temperature fuel gas; the metal blade body air film hole 206 is in air conduction with the impact cavity 209;
a tail split 207 is arranged at the convergence tail end of the metal blade body 201; the tail split 207 is in air communication with the impingement cavity 209.
In this embodiment, the blade body impingement holes 205a have a diameter of 1 to 1.5mm; the aperture of the metal blade body air film hole 206 is less than 0.5mm.
In the present embodiment, a plurality of front-end impact holes 205 are provided at the joint of the metal blade body 201 and the ceramic base blade 1; the front end air film hole 206a is in air conduction with the air collection cavity 208.
In this embodiment, a plurality of front end air film holes 206a are provided at the joint of the metal blade body 201 and the ceramic base blade 1; the front end air film hole 206a is connected with the splicing part between the metal blade body 201 and the ceramic base blade 1 at one end and connected with the flow guiding cavity at the other end.
In the present embodiment, the metal blade 2 is spliced between the metal upper edge plate 202 and the metal lower edge plate 203 based on the top and bottom surfaces that are not in contact with the high-temperature gas and the metal blade body 201.
The front half part of the combined type dissimilar material turbine stator blade component of the embodiment is a hollow air-cooled ceramic-based blade 1, is formed by integrally weaving ceramic-based fibers 108 and adding a ceramic matrix, and is mainly used for bearing the scouring of high-temperature fuel gas at the front edge; as shown in fig. 2 and 4, the ceramic-based blades 2 are matched with the upper edge plate 3 to form the front end part of the upper flow path surface, and are connected with the upper hanging ring 4 through bolts so as to enable the ceramic-based blades 2 to be combined into a ring;
the rear half part of the combined type heterogeneous material turbine stator blade component is provided with a double-layer wall efficient cooling structure air-cooled metal blade 2 with an upper edge plate and a lower edge plate, is formed by single-crystal superalloy block casting, is mainly used for drainage of high-temperature gas main flow gas, ensures excellent pneumatic efficiency of the blade, and ensures reliable transmission of axial force of the blade to an inner casing and an outer casing; the ceramic base blade body 101 and the metal blade body 201 are combined to form a complete aerodynamic profile of the turbine guide blade; and the inner annular surface 304 of the upper edge plate 3, the metal upper edge plate 202 and the metal lower edge plate 203 are combined into a ring to form a complete diversion cavity flow passage.
The ceramic base blade 1 mainly comprises a ceramic base blade body 101, a lower end positioning boss 102 and an upper mounting edge 103. A simple cold air cavity 107 is arranged in the ceramic base blade body 101, the section is provided with uniform wall thickness as required, and the wall thickness is generally 2-3 mm; an air inlet channel 106 is arranged at the top end of the ceramic base blade body 101, a compact ceramic base blade body air film hole 105 is arranged on the main body, and the diameter of the ceramic base blade body air film hole 105 is generally not more than 0.6mm; cool air enters the cool air cavity 107 through the air inlet channel 106 and is discharged through the ceramic base blade body air film holes 105, so that convection and air film cooling of the ceramic base blade body 101 are realized.
The metal blade 2 mainly comprises a metal blade body 201, a metal upper edge plate 202 and a metal lower edge plate 203. The metal She Shenshe body 201 is internally provided with a double-layer wall efficient cooling structure, a large gas collecting cavity 208 is arranged in the middle, a plurality of impact cavities 209 are arranged between the inner wall and the outer wall in an interlayer manner, the gas collecting cavity 208 is communicated with the impact cavities 209 through a plurality of blade impact holes 205a, and the diameter of each blade impact hole is generally 1-1.5 mm; the two sides of the blade basin and the blade back of the metal blade 201 are provided with a plurality of rows of compact metal blade body air film holes 206, the diameter of the metal blade body air film holes 206 is generally not more than 0.5mm, the front end of the metal blade 201 is provided with a plurality of front end impact holes 205, and the tail edge is provided with a tail split joint 207. Most of the cold air enters the impact cavity 209 from the middle air collecting cavity 208 through the blade body impact holes 205a on the inner layer wall, and is discharged through the compact metal blade body air film holes 206 and the tail split slits 207 at corresponding positions while the outer layer wall surface of the metal blade body 201 is subjected to impact cooling, so that the full cooling of the basin, the back side and the tail edge of the metal blade body 201 is realized through cold air impact and air film coverage; the air collecting cavity 208 is further provided with a cold air flow discharged through the front end impact hole 205, cools and seals the clamping cavity formed by the ceramic base blade body 101 and the metal blade body 201, and is discharged through the front end air film holes 206a on both sides.
The lower extreme of ceramic base blade 1 is provided with location boss 102, and the location boss can be set up to the form such as keyway, dogtooth, bulb as required, is provided with on the metal lower edge plate 203 with the recess 204 of location boss 102 looks adaptation, and ceramic base blade 1 lower extreme nestification is installed in recess 204, and the cooperation department leaves 0.1 ~ 0.3mm clearance to guarantee that ceramic base blade 1 lower extreme has certain activity space, in order to solve the thermal match problem between ceramic base blade 1 and the metalwork.
The upper end of the ceramic base blade 1 is provided with a mounting edge 103 along the axial direction, the mounting edge 103 is provided with a mounting through hole 104, and the mounting hole can be arranged in a round, runway-shaped, dovetail-shaped and other structural forms as required; an adaptive installation boss 301 is arranged on one side surface of the upper edge plate 3, and the ceramic-based blade 1 and the upper edge plate 3 are fixedly connected through an installation structure; the four corners of the upper edge plate 3 are respectively provided with 4 mounting edges 302, the mounting edges are respectively provided with upper edge plate bolt holes 303, 4 upper hanging ring bolt holes 401 are correspondingly arranged on the upper hanging ring 4, the mounting edges 302 between the adjacent upper edge plates 3 are paired in pairs, and the upper hanging ring 4 is connected with one group of upper edge plates 3 in a mounting way through screws 5; after sequential assembly, the blades are assembled into a ring to form the complete turbine guide.
The foregoing is merely specific embodiments of the disclosure, but the protection scope of the disclosure is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the disclosure are intended to be covered by the protection scope of the disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.
Claims (10)
1. A combined dissimilar material turbine stator blade assembly comprising:
a ceramic-based blade comprising a ceramic-based blade body; the ceramic-based She Shenwei ceramic-based hollow air-cooled structure is arranged at one end of the turbine stator blade, which is subjected to high-temperature gas flushing, and the windward side faces the incoming direction of the high-temperature gas;
a metal blade comprising a metal-based metal blade body; the metal blade body is of a hollow double-layer wall air-cooled structure, and the two layers of blade body walls form a hollow blade body structure with gradually changed thickness; the large-thickness front end of the metal blade body is spliced with the lee surface of the ceramic base blade body, and the small-thickness convergence tail end of the metal blade body is a high-flow-velocity-resistant flow guiding area of the turbine stator blade;
a metal upper edge plate; a plurality of metal upper edge plates are spliced in sequence to form an outer ring structure;
a metal lower edge plate; a plurality of metal lower edge plates are spliced in sequence to form an inner ring structure;
wherein: the ceramic-based blade and the metal blade are combined into one turbine stator blade; the outer ring structure and the inner ring structure are coaxially arranged; the cavity between the outer ring structure and the inner ring structure forms a part of a diversion cavity; the plurality of turbine stator blades are symmetrically and uniformly distributed in the flow guiding cavity by the center axis of the flow guiding cavity.
2. The combined dissimilar material turbine stator blade assembly of claim 1 further comprising an upper rim plate and an upper peg; the upper edge plate is spliced at one end of the metal upper edge plate in the gas incoming direction of the high-temperature gas; a plurality of upper edge plates are spliced in sequence to form a front end ring; the front end ring and the flow guide cavity are coaxially arranged; another part of the diversion cavity is formed between the inner ring surface of the front end ring and the metal lower edge plate;
the ceramic-based blade is provided with an upper mounting edge which is mutually fixed with the ceramic-based blade body on the top surface which is not contacted with the high-temperature fuel gas and the metal blade body; the ceramic-based blade is spliced between two adjacent upper edge plates based on the upper mounting edge;
the upper hanging top is used for fixing two adjacent upper edge plates at the outer ring surface of the front end ring.
3. The combined type dissimilar material turbine stator vane assembly according to claim 2, wherein the ceramic base vane is provided with a lower end positioning boss fixed to the ceramic base vane body on a bottom surface which is not in contact with the high-temperature fuel gas and the metal vane body;
the metal lower edge plate is provided with a groove at one end of the high-temperature fuel gas in the gas incoming direction
The ceramic-based blade is spliced in the groove based on the positioning boss.
4. The combined dissimilar material turbine stator blade assembly of claim 3 wherein a cold air cavity is provided within the ceramic base blade body; the ceramic-based shell of the ceramic-based blade body is uniform in wall thickness and is formed by weaving ceramic-based composite materials, the main body is provided with a plurality of ceramic-based blade body air film holes for conducting air in the cold air cavity and the diversion cavity, and the upper mounting edge is provided with an air inlet channel.
5. The combined dissimilar material turbine stator blade assembly of claim 4 wherein the ceramic based housing has a wall thickness of 2 to 3mm; the aperture of the ceramic base blade body air film hole is smaller than 0.6mm.
6. The combined dissimilar material turbine stator blade assembly of claim 5 wherein said metal blades are integrally cast from a high temperature single crystal alloy; an air collecting cavity is arranged in the metal blade body, and a plurality of impact cavities are arranged at the interlayer between the double-layer walls;
the impact cavity is communicated with the gas collecting cavity based on the blade impact hole;
a plurality of metal blade body air film holes are formed at the positions of the blade basin and the blade back where the metal blade body is contacted with the high-temperature fuel gas; the metal blade body air film hole is used for conducting the impact cavity and the diversion cavity;
a tail split joint is arranged at the convergence tail end of the metal blade body; and the tail split joint gas conducts the impact cavity and the diversion cavity.
7. The combined dissimilar material turbine stator blade assembly of claim 6 wherein the blade impingement holes have a bore diameter of 1-1.5 mm; the aperture of the metal blade body air film hole is smaller than 0.5mm.
8. The combined type dissimilar material turbine stator blade assembly according to claim 7, wherein a plurality of front-end impact holes are formed at the joint of the metal blade body and the ceramic-based blade; the front end air film hole is in air conduction with the air collecting cavity.
9. The combined type dissimilar material turbine stator blade assembly according to claim 8, wherein a plurality of front end air film holes are formed at the joint of the metal blade body and the ceramic base blade; and one end of the front end air film hole is in air conduction with the splicing part between the metal blade body and the ceramic base blade, and the other end of the front end air film hole is in conduction with the flow guide cavity.
10. The combined dissimilar material turbine stator vane assembly of claim 9 wherein said metal vanes are spliced between said metal upper rim plate and said metal lower rim plate based on top and bottom surfaces that are not in contact with said high temperature gas and said metal vanes.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310179048.2A CN116335771A (en) | 2023-02-27 | 2023-02-27 | Combined turbine stator blade assembly made of dissimilar materials |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310179048.2A CN116335771A (en) | 2023-02-27 | 2023-02-27 | Combined turbine stator blade assembly made of dissimilar materials |
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| CN202310179048.2A Pending CN116335771A (en) | 2023-02-27 | 2023-02-27 | Combined turbine stator blade assembly made of dissimilar materials |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116857021A (en) * | 2023-09-04 | 2023-10-10 | 成都中科翼能科技有限公司 | Disconnect-type turbine guide vane |
| CN116906126A (en) * | 2023-09-14 | 2023-10-20 | 中国航发北京航空材料研究院 | Multi-body guide vane of ceramic matrix composite and single crystal superalloy and preparation method thereof |
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2023
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116857021A (en) * | 2023-09-04 | 2023-10-10 | 成都中科翼能科技有限公司 | Disconnect-type turbine guide vane |
| CN116857021B (en) * | 2023-09-04 | 2023-11-14 | 成都中科翼能科技有限公司 | Disconnect-type turbine guide vane |
| CN116906126A (en) * | 2023-09-14 | 2023-10-20 | 中国航发北京航空材料研究院 | Multi-body guide vane of ceramic matrix composite and single crystal superalloy and preparation method thereof |
| CN116906126B (en) * | 2023-09-14 | 2023-12-08 | 中国航发北京航空材料研究院 | Multi-body guide vane of ceramic matrix composite and single crystal superalloy and preparation method thereof |
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