WO2023231218A1

WO2023231218A1 - Turbine guide vane mounting structure and turbine

Info

Publication number: WO2023231218A1
Application number: PCT/CN2022/117703
Authority: WO
Inventors: 郭洪宝; 洪智亮; 蒋婷; 王子媛
Original assignee: 中国航发商用航空发动机有限责任公司
Priority date: 2022-05-30
Filing date: 2022-09-08
Publication date: 2023-12-07
Also published as: CN117189266A

Abstract

A turbine guide vane mounting structure, comprising a metal cover plate and CMC turbine guide vanes. The metal cover plate comprises at least one protrusion and at least one inclined surface, and exhaust slots are further formed in the inclined surface and the protrusion; each CMC turbine guide vane comprises an edge plate for matching the metal cover plate, and a blade body; the blade body comprises a hollow cavity; the position where the edge plate matches the inclined surface is a secondary inclined surface, and the position where the edge plate matches the protrusion is a plane or a cambered surface; relative dislocation can occur between the inclined surface and the secondary inclined surface, and between the protrusion and the plane or the cambered surface; a gap cavity is formed between the edge plate and the metal cover plate by means of the protrusion, and the gap cavity is communicated with the hollow cavity and the exhaust slots to serve as a circulation area of cooling gas. According to the turbine guide vane mounting structure, the thermal mismatch problem can be effectively relieved. Provided is a turbine, comprising the turbine guide vane mounting structure.

Description

Turbine guide vane installation structure and turbine

Technical field

The present invention relates to the field of aeroengines, and specifically to the field of CMC turbine guide vanes.

Background technique

As an important high-temperature turbine component of a gas turbine engine, turbine guide vanes are subject to high ambient temperatures and aerodynamic pressure loads during service. At present, turbine guide vanes are mainly made of high-temperature alloy materials, which significantly affects the upper service temperature limit of turbine guide vanes and the improvement of overall engine efficiency. Using ceramic matrix composites (CMC) instead of high-temperature alloy materials to prepare turbine guide vanes can give full play to the excellent high-temperature mechanical properties of CMC, significantly improve the upper temperature limit of the turbine guide vanes and the overall efficiency of the engine, and reduce pollution emissions. .

However, during temperature changes, significant thermal deformation mismatch problems will occur between the CMC turbine guide vanes and metal components, which will affect the maintenance of the installation preload force within the assembly structure. In addition, the high temperature of the CMC turbine guide vanes itself can easily cause Overtemperature issues with metal components.

Contents of the invention

An object of the present invention is to provide a turbine guide vane installation structure that alleviates the thermal deformation mismatch problem inside the assembly structure and enables effective cooling.

The turbine guide vane installation structure to achieve the above purpose includes a metal cover plate and a CMC turbine guide vane. The metal cover plate includes at least one protrusion and at least one inclined surface, and exhaust grooves are also provided on the inclined surface and the protrusion; the CMC turbine guide vane includes an edge plate and a vane for mating with the metal cover plate. The blade body includes a hollow cavity, the matching point between the edge plate and the inclined surface is a sub-inclined surface, and the matching point with the protrusion is a flat or arc surface; the inclined surface and the sub-inclined surface, the protrusion and the flat surface Or relative displacement can occur between arc surfaces; the protrusion causes a gap cavity to be formed between the edge plate and the metal cover plate, and the gap cavity is connected to the hollow cavity and connected to the exhaust recess. The grooves are connected to serve as a circulation area for cooling gas.

In one or more embodiments, the metal cover plate includes an upper cover plate and a lower cover plate, the edge plate includes an upper edge plate and a lower edge plate, and the upper edge plate is used to cooperate with the upper cover plate. , the lower edge plate is used to cooperate with the lower cover plate, and at least one protrusion and at least one slope are provided on the upper cover plate and/or the lower cover plate.

In one or more embodiments, the inclined surface on the upper cover plate and the sub-inclined surface on the upper edge plate are set to approximate the inclination direction of the inclined surface on the lower cover plate and the sub-inclined surface on the lower edge plate. parallel.

In one or more embodiments, the normal direction of the sub-slope on the lower edge plate is set to an angle greater than 0° and less than 90° with the gas flow direction.

In one or more embodiments, the lower cover plate further includes at least one metal pillar, the upper cover plate includes a through hole, and each of the metal pillars passes through the hollow cavity and through the through hole, The turbine guide vane installation structure also includes a metal elastic element and a nut. The metal elastic element is used to be sleeved on the end periphery of the metal column. The nut is used to press the metal elastic element against the upper part. On the cover plate, an installation preload force is applied to the upper cover plate, the CMC turbine guide vane and the lower cover plate by virtue of the resilience of the metal elastic element.

In one or more embodiments, the metal uprights include a plurality of uprights that are respectively provided with the protruding positions of the leading edge, the trailing edge and the suction surface of the blade, and each of the uprights is independently connected to the metal elastic element and a plurality of nuts. Cooperate.

In one or more embodiments, the metal column includes an axial cavity and a plurality of cold air outflow holes, and the cold air outflow holes are used to communicate the axial cavity with the outside of the metal column.

In one or more embodiments, the metal post includes a mounting end that includes threads for threadingly mating with the nut.

In one or more embodiments, the turbine guide vane mounting structure further includes a thin-walled bushing, which is built into the hollow cavity and sleeved on the outside of the metal column, and includes a plurality of impingement cooling holes.

In one or more embodiments, the upper cover plate includes an upper limit groove, the lower cover plate includes a lower limit groove, and the upper limit groove and the lower limit groove are respectively used to embed the Thin-walled bushing, and the thin-walled bushing is stuck between the upper limiting groove and the lower limiting groove by virtue of the resilience of the metal elastic element, so that the thin-walled bushing, The metal column, the upper cover plate and the lower cover plate define an annular cavity, and the annular cavity is connected with the through hole.

In one or more embodiments, the radially outer side of the upper cover plate includes an annular protrusion, the annular protrusion forms an annular groove, the annular groove is a part of the through hole, and is used for the metal column. Passing through, the annular groove is used to place the metal elastic element, and the bottom surface of the nut abuts against the flange surface of the annular protrusion.

In one or more embodiments, the annular protrusion further includes a plurality of notches, which form an air inlet channel when the bottom surface abuts the flange surface, and the metal elastic element, the The inner wall of the annular protrusion and the outer wall of the metal column form a cold air channel, and the cold air channel is connected with the air inlet channel and the through hole.

In one or more embodiments, the metal elastic element is a coil spring, and the metal elastic element has a rectangular cross-section.

In one or more embodiments, the upper cover plate further includes a mounting hook for mounting the turbine guide vane to the casing.

Another object of the present invention is to provide a turbine including the above-mentioned turbine guide vanes.

The above turbine guide vane installation structure effectively installs the metal cover plate with an inclined plane and a protrusion with an exhaust groove, and sets the CMC edge plate into a sub-inclined plane and a planar structure that matches the inclined plane and the protrusion. A gap cavity connected to the hollow cavity is constructed between the cover plate and the CMC edge plate, thereby increasing the circulation path of the cooling gas and effectively cooling the metal cover plate and CMC edge plate. In addition, the thermal deformation difference between the CMC turbine guide vane and the metal column along the height direction of the blade is compensated by the increase or release of the elastic deformation of the metal elastic element itself, thus avoiding the problem of excessive or loose pre-tightening force in the internal installation of the component. ;The thermal deformation difference between the metal upper cover plate and the metal lower cover plate and the CMC upper edge plate and CMC lower edge plate is determined by the mutual misalignment between the inclined plane, the bulge, the sub-inclined plane, and the flat/arc surface. It can be released automatically to prevent the problem of excessive thermal mismatch stress, effectively avoiding problems such as excessive thermal mismatch stress and loose installation pre-tightening force.

Description of the drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description in conjunction with the accompanying drawings and embodiments, in which:

Figure 1 is a front view of an embodiment of a turbine guide vane mounting structure.

Figure 2 is a radial cross-sectional view of an embodiment of a turbine guide vane mounting structure.

Figure 3A is a top view of an embodiment of an airfoil.

Figure 3B is a bottom view of one embodiment of the airfoil.

Figure 4 is a schematic diagram of an embodiment of the lower cover.

Figure 5 is a front view of one embodiment of the lower cover.

Figure 6 is a cross-sectional view of an embodiment of the lower cover.

Figure 7 is a top view of an embodiment of the upper cover.

Figure 8 is a bottom view of an embodiment of the upper cover.

Figure 9 is a front view of an embodiment of the upper cover.

Figure 10 is a cross-sectional view of an embodiment of the upper cover plate.

Figure 11A is a schematic diagram of one embodiment of a nut.

Figure 11B is a perspective view of one embodiment of the nut.

Figure 12 is a schematic diagram of one embodiment of a thin wall bushing.

Figure 13A is a cross-sectional view of one embodiment of a metal elastic element.

Figure 13B is a perspective view of an embodiment of a metal elastic element.

FIG. 14A is an enlarged view of position A in FIG. 2 .

FIG. 14B is an enlarged view of position B in FIG. 2 .

Figure 15 is a transverse cross-sectional view of an embodiment of a turbine guide vane mounting structure.

Figure 16A is an exploded view of one embodiment of a turbine guide vane mounting structure.

FIG. 16B is an exploded perspective view of one embodiment of the turbine guide vane mounting structure.

Figure 17 is a top view of one embodiment of the turbine guide vane mounting structure.

Figure 18A is a cross-sectional view of the upper edge plate and the upper cover plate mating.

Figure 18B is a cross-sectional view of the lower edge plate and the lower cover plate.

FIG. 19A is an enlarged view of position E in FIG. 18A.

FIG. 19B is an enlarged view of position F in FIG. 18A.

Symbol marking description

1. CMC turbine guide vane

2. Lower cover

3. Upper cover

4. Nuts

5. Thin-walled bushing

6. Metal elastic components

8. Edge plate

9. Metal cover

11. Leaf body

12. Lower edge plate

13. Upper edge plate

51. Impact cooling holes

21. Lower cover body

22. Metal columns

31. Main body of upper cover

32. Annular bulge

33. Install hooks

41. Wire binding hole

42. Bottom surface

71. Interstitial cavity

111. Hollow cavity

121. Second slope

131. The first bevel

211. Second slope

212. Third exhaust groove

213. The second bump

214. Fourth exhaust groove

215. Lower limit groove

221. Installation end

222. Axial cavity

223. Cold air outflow hole

311. The first inclined plane

312. First exhaust groove

313. The first bump

314. Second exhaust groove

315. Upper limit groove

316.Through hole

321. Gap

322. Annular groove

328. Flange surface

Detailed ways

Turbine vane is the main stationary part of the gas turbine engine turbine. It is placed between the two adjacent turbine rotating blades. It withstands ultra-high temperature and aerodynamic pressure service environment and is used to change the direction of gas flow so that the high-speed gas flow can Impact the rotating blades of the next stage turbine at a suitable angle to perform work efficiently.

Turbine guide vanes made of CMC materials have excellent high-temperature mechanical properties, but the fit with metal components will cause significant thermal deformation and thermal mismatch problems. Thermal mismatch refers to the phenomenon that adjacent materials or components with different thermal expansion coefficients in the same system exhibit inconsistent thermal expansion and deformation during temperature changes. The thermal deformation mismatch that cannot be released will cause thermal deformation in the system. Significant thermal mismatch stress affects the maintenance of the internal installation pre-tightening force of the assembly structure. In addition, the high temperature of the CMC turbine guide vane itself can easily lead to overtemperature problems of adjacent metal components.

The turbine guide vane installation structure described in the present disclosure can effectively alleviate the thermal deformation mismatch problem inside the assembly structure, avoid excessive thermal mismatch stress and loose installation pre-tightening force, and effectively improve the safety and reliability of the assembly structure.

Referring to FIGS. 1 and 2 , the turbine guide vane mounting structure of the present disclosure includes a metal cover plate 9 and a CMC turbine guide vane 1 . The CMC turbine guide vane 1 includes an edge plate 8 for mating with the metal cover plate 9 . More specifically, the edge plate 8 includes an upper edge plate 13, a lower edge plate 12 and a blade body 11. The metal cover plate 9 includes an upper cover plate 3 and a lower cover plate 2. The upper edge plate 13 is used to cooperate with the upper cover plate 3. The lower edge plate 12 is used to cooperate with the lower cover plate 2 .

The CMC turbine guide vane 1 can be understood in conjunction with Figure 3A and Figure 3B and includes an upper edge plate 13, a lower edge plate 12 and a blade body 11 connecting the upper edge plate 13 and the lower edge plate 12. In one embodiment, the upper edge plate 13, The lower edge plate 12 and the blade body 11 are prepared by CMC integrated molding technology. The blade body 11 includes a hollow cavity 111 that penetrates the upper edge plate 13 and the lower edge plate 12 . The metal lower cover plate 2 is arranged on the lower side of the CMC lower edge plate 12 and cooperates with it, and the metal upper cover plate 3 is arranged on the upper side of the CMC upper edge plate 13 and cooperates with it.

In one embodiment, the metal cover plate and the CMC turbine guide vane are fixedly connected by arranging metal columns and elastic members. As shown in FIG. 4 , the lower cover 2 includes at least one metal column 22 , and the upper cover 3 includes a through hole 316 . Each metal column 22 passes through the hollow cavity 111 and passes through the through hole 316 . The turbine guide vane installation structure also includes a metal elastic element 6 and a nut 4. The metal elastic element 6 is used to be sleeved on the end periphery of the metal column 22, and the nut 4 is used to press the metal elastic element 6 on the upper cover plate 3. , to exert installation pre-tightening force on the upper cover plate 3, CMC turbine guide vane 1 and lower cover plate 2 by virtue of the resilience of the metal elastic element 6.

Specifically, as shown in FIGS. 4 to 6 , the lower cover body 21 faces the lower edge plate 12 , and the metal pillars 22 are provided on the lower cover body 21 , and can be manufactured together with the lower cover body 21 by, for example, integrated molding. . The side of the metal column 22 away from the lower cover body 21 includes a mounting end 221 , and the mounting end 221 includes threads for threading with the nut 4 at the upper cover 3 . The diameter of the preferred mounting end 221 is larger than the diameter of the metal column 22 in order to achieve a fixed connection with the nut 4 . The metal column 22 also includes an axial cavity 222 and a plurality of cold air outflow holes 223 . The cold air outflow holes 223 are used to connect the axial cavity 222 with the outside of the metal column 22 . The axial cavity 222 is an axial cavity inside the metal column 22 and serves as a cold air flow path. Preferably, the cold air outflow hole 223 is provided at the lower part of the axial cavity 222 on one side close to the lower cover plate 2. The above design allows the cooling air to flow through a larger area of the axial cavity 222 from top to bottom, thereby cooling the entire metal. The column 22 is cooled to prevent its temperature from being too high.

In one embodiment, the metal pillars 22 include multiple pillars that are respectively provided with the protruding positions of the leading edge, trailing edge and suction surface of the blade. Each pillar independently cooperates with a plurality of metal elastic elements 6 and a plurality of nuts 4. The above-mentioned distribution The position design is conducive to improving the ability of metal assembly components to resist bending and torsional deformation, is conducive to restraining the CMC turbine guide vane 1 and resisting the bending moment and torque load caused by aerodynamic pressure, and reducing the deformation and stress level of the CMC turbine guide vane 1 itself. Improve strength performance. In addition, the number of metal elastic elements 6 is the same as the number of metal columns 22. The increase of metal columns 22 will increase the number of metal elastic elements 6, which is conducive to increasing the total resilience force provided by the metal elastic elements 6 inside the installation structure, and thus Better eliminate the problem of installation preload relaxation caused by thermal deformation difference. Preferably, the number of metal columns 22 is three, and they are respectively arranged near the leading edge, trailing edge and suction surface convex position of the CMC blade.

The upper cover plate 3 can be understood with reference to Figures 7 to 10. The upper cover plate 3 includes an upper cover plate main body 31 and mounting hooks 33 on both sides. The mounting hooks 33 are used to install the CMC turbine guide vane 1 to the casing. In one embodiment, the radially outer side of the main body area of the upper cover plate 3 includes an annular protrusion 32 . The annular protrusion 32 forms an annular groove 322 . The annular groove 322 is part of the through hole 316 and allows the metal column 22 to pass through. The annular groove 322 is used to place the metal elastic element 6 , and the bottom surface 42 of the nut 4 abuts against the flange surface 328 of the annular protrusion 32 . The annular protrusion 32 also includes a plurality of notches 321. When the bottom surface 42 of the notches 321 abuts the flange surface 328, the annular groove 322 is in an unsealed state due to the presence of the notches 321, and the notches 321 form an air inlet channel. At this time, the metal elastic element 6, the inner wall of the annular protrusion 32 and the outer wall of the metal column 22 form a cold air channel. If the cold air channel is a spiral cold air channel, the cold air channel is connected with the air inlet channel formed by the notch 321 and the through hole 316. , this channel can significantly improve the cooling effect of the cold air on the metal elastic element 6 .

In one embodiment, the turbine guide vane mounting structure further includes a thin-walled bushing 5, which is built into the hollow cavity 111 and sleeved outside the metal column 22, and includes a plurality of impingement cooling holes 51 thereon. That is, as shown in Figure 15, the thin-walled liner 5 is located between the blade body 11 and the metal column 22. The thin-walled liner 5 is used to organize the cooling air path and improve the cooling efficiency of the CMC blade body. The impact cooling holes 51 on the thin-walled liner 5 can impact and release the cold air in the cavity surrounded by the thin-walled liner 5 to the blade body 11 to achieve effective cooling of the inner surface of the blade body 11 .

On the basis of the above embodiment, the thin-walled bushing 5 is defined by the upper cover plate 3 and the lower cover plate 2 . The upper cover 3 includes an upper limit groove 315 , and the lower cover 2 includes a lower limit groove 215 . The upper limit groove 315 and the lower limit groove 215 are respectively used to embed the thin-walled bushing 5 , that is, the thin-walled bushing 5 The upper and lower ends are inserted into the limit grooves on the metal upper cover 3 and the lower cover 2, and the thin-walled bushing 5 is stuck in the upper limit groove 315 and the lower limit groove by virtue of the resilience of the metal elastic element 6 215 to achieve its own limit fixation. At this time, the thin-walled bushing 5, the metal column 22, the upper cover plate 3 and the lower cover plate 2 define an annular cavity G, and the annular cavity G is connected to the through hole 316. As shown in FIG. 14A , it can be understood that the annular cavity G is also connected to the cold air channel formed by the metal elastic element 6 , the inner wall of the annular protrusion 32 and the outer wall of the metal column 22 through the through hole 316 , and further communicates with the inlet formed by the gap 321 . The air channels are connected so that the cooling gas from near the upper cover 3 can enter the spiral cold air channel through the gap 321 .

The structure of the metal elastic element 6 can be understood in conjunction with Figure 13A and Figure 13B. The preferred metal elastic element 6 is a coil spring. The cross section of the metal elastic element 6 is rectangular. The rectangular cross section is conducive to the formation of a regular spiral cold air channel, which can increase the cooling air Cooling effect on the metal elastic element 6.

The structure of the nut 4 can be understood with reference to FIGS. 11A and 11B . The nut 4 includes a threaded portion that threadably matches the mounting end 221 of the metal pole 22 , and also includes a bottom surface 42 close to the side of the upper cover 3 . The nut 4 also includes a wire binding hole 41, which is used to cooperate with the anti-loosening binding wire to prevent loosening.

Continuing to refer to FIG. 14A , it will be understood that when the nut 4 is threaded with the metal pole 22 , the bottom surface 42 is pressed against the flange surface 328 of the annular protrusion 32 , and the metal elastic element 6 is pressed against the annular protrusion 32 . In the groove 322, at this time, the metal column 22 passes through the hollow cavity 111, the through hole 316 and the metal elastic element 6 placed in the annular groove 322 in sequence. The nut 4 is assembled on the installation end 221 through threaded fit and compresses the metal downward through the tightening torque. The elastic element 6 generates a rebound force, thereby exerting an installation pre-tightening force between the metal lower cover plate 2, the CMC turbine guide vane 1 and the metal upper cover plate 3, and causes the thin-walled bushing 5 to be clamped in the lower limit recess. In the groove 215 and the upper limit groove 315, the assembly of the CMC turbine guide vane assembly and the application of installation pre-tightening force are completed.

During the temperature change process, the thermal deformation difference between the CMC turbine guide vane 1 and the metal column 22 along the height direction of the blade is compensated by the increase or release of the elastic deformation of the metal elastic element 6 itself, thereby avoiding pre-tightening of the internal installation of the component. Problems with excessive force or slack.

In addition, the metal cover plate 9 includes at least one protrusion and at least one inclined plane, and the inclined plane and the protrusion are also provided with exhaust grooves; an edge plate 8 cooperates with the metal cover plate 9, and the matching point between the edge plate 8 and the inclined plane is the second The inclined surface, which matches the protrusion, is a curved surface or a flat surface; a gap cavity 71 is formed between the edge plate 8 and the metal cover plate 9. The gap cavity 71 is connected to the hollow cavity 111 and the exhaust groove, and serves as a circulation area for cooling gas. , and the protrusion and arc surface or flat surface, bevel surface and sub-bevel surface can be displaced from each other.

Specifically, as shown in FIG. 8 , taking the upper cover 3 as an example, the upper cover 3 includes a first inclined surface 311 and a first protrusion 313 . The first inclined surface 311 has a plurality of first exhaust grooves 312 . The protrusion 313 has a plurality of second exhaust grooves 314. Correspondingly, as shown in Figure 3A, the upper edge plate 13 that matches the upper cover plate 3 has a first inclined surface 131. The first inclined surface 131 and the first inclined surface 311 cooperate with each other for assembly contact limiting. . At this time, the existence of the first exhaust groove 312 causes the first slope 311 and the first slope 131 not to be in close contact with each other, but to have an exhaust channel formed by the first exhaust groove 312 . The first protrusion 313 is higher than the plane of the main body of the upper cover 3, and because the position of the upper edge plate 13 that cooperates with the first protrusion 313 on the upper cover 3 is a flat or arc surface, the upper cover 3 3 and the upper edge plate 13 are pushed up by the protrusion to form a gap cavity 71. As shown in Figures 18A and 19A, the gap cavity 71 is connected with the second exhaust groove 314 and the first exhaust groove 312. They are connected to form a cooling gas circulation area, so that there is a gas circulation path between the upper cover plate 3 and the upper edge plate 13 instead of a close contact state.

As shown in FIG. 4 , taking the lower cover 2 as an example, the lower cover 2 includes a second inclined surface 211 and a second protrusion 213 . The second inclined surface 211 includes a plurality of third exhaust grooves 212 . The base 213 includes a plurality of fourth exhaust grooves 214. The surface of the lower edge plate 12 opposite to the second inclined surface 211 is the second inclined surface 121, as shown in FIG. 3B, which is used to achieve contact limiting. The surface opposite to the second protrusion 213 is a plane, and normal contact limitation is achieved between the second protrusion 213 and the plane of the lower edge plate 12 . Therefore, a gap cavity 71 is formed between the lower edge plate 12 and the lower cover plate 2 by virtue of the protrusion, as shown in FIG. 18B , and the gap cavity 71 is connected with the third exhaust groove 212 and the fourth exhaust groove 214 and the hollow cavity 111 are connected to form a cold air passage.

In the assembled state, the metal lower cover plate 2 is pressed against the lower surface of the lower edge plate 12, and only limited contact occurs between the second slope 211 and the second slope 121, the second protrusion 213 and the lower surface of the lower edge plate 12. , the gap cavity 71 or the channel formed by the exhaust groove exists in the remaining areas, so the assembly surface area between the metal cover plate and the CMC edge plate is effectively reduced, and there is no need for tightness between the metal cover plate and the CMC edge plate. Therefore, it also reduces the difficulty of preparation, molding and processing of CMC turbine guide blades.

The gap cavity 71 serves as a circulation area for cooling gas, which can reduce the temperature between the metal cover plate and the CMC edge plate, reduce the risk of over-temperature, and at the same time reduce the size of the assembly joint surface between the two, which is beneficial to reducing the risk of CMC edge plate or The surface accuracy requirements and preparation and processing difficulty of the metal cover plate.

The lower cover plate 2 and the upper cover plate 3 can also enhance the effect of compacting and clamping the CMC turbine guide vane 1 through the inclined surface. Refer to Figure 1 to understand that the slope between the lower cover plate 2 and the lower edge plate 12 and the slope between the upper cover plate 3 and the upper edge plate 13 can provide upward and downward force components to clamp the CMC turbine guide vanes. 1. Preferably, the inclination direction of the inclined surface on the upper cover plate 3 and the secondary inclined surface on the upper edge plate 13 and the inclined surface on the lower cover plate 2 and the secondary inclined surface on the lower edge plate 12 are set to be approximately parallel, so that the upper and lower directions of the guide vanes are direction provides approximately symmetrical forces.

In addition, in order to further improve the compaction and clamping effect and transmit the installation restraining force more efficiently, in one embodiment, the angle between the normal direction of the second slope 121 of the lower edge plate 12 and the gas flow direction is set to be greater than 0 ° and less than 90°, which makes it easier for the contact reaction force transmitted between the contact slopes to balance the bending moment caused by the aerodynamic pressure on the CMC turbine guide vane. The direction of gas flow is shown as arrow S in Figure 1. The normal direction of the second slope 121 of the lower edge plate 12 is set so that the angle between the direction S of the gas flow and the direction S of the gas flow is greater than 0° and less than 90°, then the A force component opposite to the gas flow direction S, thereby balancing the bending moment caused by the gas flow direction on the turbine guide vanes.

During the temperature change process, the thermal deformation difference between the turbine guide vane 1 and the metal column 22 is compensated by the increase or release of the elastic deformation of the metal elastic element 6 itself to avoid the problem of excessive or loose pre-tightening force in the internal installation of the component. In addition, the thermal deformation difference between the upper cover plate 3 and the lower cover plate 2 and the upper edge plate 13 and the lower edge plate 12 along the plane in all directions is determined by the mutual misalignment between the above-mentioned inclined plane and sub-inclined plane, protrusion and plane. It is released by movement, and the cold air can flow in the gap cavity to prevent the problem of excessive thermal mismatch stress. However, other uncontacted areas in the metal cover plate and CMC edge plate, that is, non-convex and bevel contact areas, are not There is a thermal deformation mismatch problem.

The overall cooling scheme will be described below in conjunction with the above turbine guide vane installation structure. The first stream of cooling gas is shown with reference to Figures 14A and 14B. First, the engine cooling gas is introduced into the cavity C enclosed by the upper surface of the upper cover plate 3, and then the first stream of cooling gas, as shown by the solid arrows in Figures 14A and 14B, passes through the inlet gap 321. The air channel flows into the spiral cold air channel surrounded by the inner surface of the annular groove 322, the outer annular surface of the mounting end 221 of the metal column 22, and the outer surface of the metal elastic element 6, thereby fully cooling the metal elastic element 6. The metal elastic element 6 is at a lower temperature level, thereby reducing the risk of high-temperature creep, insufficient resilience, and other problems. Then the first stream of cold air flows into the annular cavity G surrounded by the thin-walled bushing 5 and the upper cover plate 3 and the lower cover plate 2 through the matching gap between the metal column 22 and the through hole 316 .

At the same time, the second stream of cold air, as shown by the dotted arrows in Figures 14A and 14B, flows through the axial cavity 222 of the metal column 22, fully cooling the metal column 22, reducing its own temperature, and preventing Its high-temperature elastic modulus drops significantly or high-temperature creep occurs, ensuring that it has sufficient deformation stiffness and strength to transmit the installation restraint load between the metal upper cover 3 and the metal lower cover 2 . Then the second stream of cold air flows into the annular cavity G surrounded by the thin-walled bushing 5, the metal upper cover 3 and the metal lower cover 2 through the cold air outflow hole 223 on the metal column 22.

Then, the cold air in the annular cavity G surrounded by the thin-walled liner 5, that is, the sum of the first and second cold air, carries out impact cooling on the inner surface of the blade body 11 through the impact cooling holes 51. The distribution design of 51 achieves effective cooling of the high temperature area of the blade 11, thus significantly reducing the temperature gradient and thermal stress level.

Then, the cooling air flows into the gap between the thin-walled liner 5 and the inner surface of the blade body 11, that is, the cooling gas in the hollow cavity 111 flows into the gap cavity 71 between the metal cover plate 9 and the edge plate 8, and finally passes through The first exhaust groove 312, the second exhaust groove 314, the third exhaust groove 212 and the fourth exhaust groove 214 flow out into the gas flow channel, and at the same time, the metal upper cover 3 and the metal lower cover 2. The lower edge plate 12 and the upper edge plate 13 are cooled to prevent over-temperature, and the cooling air path ends.

Therefore, for the high-temperature area of the blade, a large number of impact cooling holes 51 are opened on the thin-walled bushing 5, and the introduced cooling gas effectively cools the inner cavity surface of the blade 11 through impact cooling; for installation restraint loads, the main load-bearing metal The assembly metal column 22 has an axial cavity 222 designed inside it. The cooling gas flows in from the upper inlet of the axial cavity 222 and flows out from the cold air outflow hole 223 at the lower end, and then flows into the thin-walled bushing 5 and the inner surface of the metal cover 9 In the enclosed annular cavity G, a large-area gap cavity 71 and an exhaust groove are designed between the edge plate 8 and the metal cover plate 9 to allow the cold air in the annular cavity G to flow out, effectively realizing the Cooling of the edge plate 8 and the metal cover plate 9; for the metal elastic element 6, with the help of its spiral structure and the spiral cold air channel formed by the inner wall of the annular groove 322 on the metal upper cover plate 3 and the outer surface of the metal column 22, the cold air is cooled It flows into the upper end notch 321 and flows out at the lower end through the spiral cold air channel, and finally flows into the annular cavity G surrounded by the thin-walled bushing 5 and the inner surface of the metal cover 9 to achieve cooling of the metal elastic element 6. Finally, all the cooling gas flows into the gas flow channel through the above-mentioned cold air channel. The above-mentioned cooling structure effectively enhances the cooling effect of each component, significantly reduces the risk of over-temperature of the CMC turbine guide vane assembly, and effectively slows down the thermal deformation mismatch problem inside the assembly structure, which can avoid excessive thermal mismatch stress and installation Problems such as preload relaxation occur.

The assembly process of the turbine guide vane installation assembly will be described below with reference to Figures 16A and 16B. First, place the thin-walled bushing 5 in the lower limiting groove 215, and then insert the metal lower cover 2 together with the thin-walled bushing 5 into the blade body cavity 111, so that the second inclined surface 211 and the second inclined surface 121 fit together. , the second protrusion 213 is in contact with the plane of the lower surface of the lower edge plate 12 . Then place the metal upper cover 3 on the upper edge plate 13, so that the metal pillar 22 passes through the through hole 316, so that the first bevel 311 and the first bevel 131 fit, and the upper surface of the first protrusion 313 is in contact with the upper edge plate. 13. Fit the plane where the lower surface is located. Then, the metal elastic element 6 is placed around the outer periphery of the mounting end 221 and placed in the annular groove 322 . Finally, tighten the nut 4 on the upper end of the installation end 221 and apply a tightening torque. At this time, the metal elastic element 6 is compressed and applies an installation pre-tightening force to the upper cover plate 3, CMC turbine guide vane 1 and lower cover plate 2, and makes the thin-walled lining The sleeve 5 is clamped in the limiting groove, and the assembly of the CMC turbine guide vane assembly is completed.

The above-mentioned turbine guide vane installation structure realizes the assembly between the CMC turbine guide vane and the metal cover plate through nuts, metal elastic elements and metal columns, and alleviates the thermal deformation mismatch problem inside the assembly structure by virtue of the increase or release of elastic force. ; Also by designing cooling structures such as exhaust grooves, gap cavity 71, annular cavity G, cold air channels, etc., effective cooling of various components such as the high-temperature area of the guide vane, main load-bearing metal components, and elastic metal components is achieved. It significantly reduces the risk of over-temperature of the CMC turbine guide vane assembly, avoids problems such as excessive thermal mismatch stress and loose installation pre-tightening force, and improves the safety and reliability of the assembly structure. In addition, the above-mentioned turbine guide vane installation structure has a simple overall structure and a small assembly surface area, which significantly reduces the difficulty of preparation, molding and processing of CMC turbine guide vanes; using CMC instead of high-temperature alloy materials to prepare gas turbine engine turbine guide vanes overcomes the problems of high-temperature alloys The material's shortcomings of low upper temperature limit, high material density and poor chemical stability are of great value in promoting the engineering application of CMC turbine guide vanes and improving the performance indicators of gas turbine engines.

Based on the above introduction to the installation structure of turbine guide vanes, it can also be understood that a turbine using the above installation structure of turbine guide vanes has better performance.

It should be noted that the use of words such as "first" and "second" in the above introduction to define parts is only to facilitate the distinction between corresponding parts. Unless otherwise stated, the above words have no special meaning and do not represent Therefore, it cannot be understood as limiting the scope of protection of this application.

At the same time, this application uses specific words to describe the embodiments of the application. For example, "one embodiment", "an embodiment", and/or "some embodiments" means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that “one embodiment” or “an embodiment” or “an alternative embodiment” mentioned twice or more at different places in this specification does not necessarily refer to the same embodiment. . In addition, certain features, structures or characteristics in one or more embodiments of the present application may be appropriately combined.

Claims

A turbine guide vane installation structure, which is characterized by including:

Metal cover plate (9), the metal cover plate (9) includes at least one protrusion and at least one bevel, and exhaust grooves are also provided on the bevel and the protrusion;

CMC turbine guide vane (1) includes an edge plate (8) used to cooperate with the metal cover plate (9) and a blade body (11). The blade body (11) includes a hollow cavity (111). The place where the edge plate (8) fits with the inclined surface is a sub-inclined surface, and the place where it fits with the protrusion is a flat or arc surface. Relative displacement can occur between the inclined surface and the sub-inclined surface, and between the protrusion and the flat or arc surface. ;

The protrusion forms a gap cavity (71) between the edge plate (8) and the metal cover plate (9), and the gap cavity (71) is connected to the hollow cavity (111) and is connected with the hollow cavity (111). The exhaust grooves are connected to serve as a circulation area for cooling gas.
The turbine guide vane installation structure according to claim 1, characterized in that the metal cover plate (9) includes an upper cover plate (3) and a lower cover plate (2), and the edge plate (8) includes an upper edge plate (13) and a lower edge plate (12). The upper edge plate (13) is used to cooperate with the upper cover plate (3), and the lower edge plate (12) is used to cooperate with the lower cover plate (3). 2) In cooperation, at least one protrusion and at least one slope are provided on the upper cover plate (2) and/or the lower cover plate (3).
The turbine guide vane installation structure according to claim 2, characterized in that the inclined surface on the upper cover plate (3) and the secondary inclined surface on the upper edge plate (13) are consistent with the inclined surfaces on the lower cover plate (2). The inclined direction of the inclined surface and the secondary inclined surface on the lower edge plate (12) are set to be approximately parallel.
The turbine guide vane installation structure according to claim 2, characterized in that the normal direction of the sub-inclined surface on the lower edge plate (12) is set to an angle greater than 0° and less than 90° with the gas flow direction.
The turbine guide vane installation structure according to claim 2, characterized in that the lower cover plate (2) further includes at least one metal column (22), and the upper cover plate (3) includes a through hole (316) , each of the metal columns (22) passes through the hollow cavity (111) and passes through the through hole (316),

The turbine guide vane installation structure also includes a metal elastic element (6) and a nut (4). The metal elastic element (6) is used to be sleeved on the end periphery of the metal column (22). The nut (4) ) is used to press the metal elastic element (6) on the upper cover plate (3), so as to rely on the resilience of the metal elastic element (6) to push the metal elastic element (6) toward the upper cover plate (3) and the upper cover plate (3). The CMC turbine guide vane (1) and the lower cover plate (2) apply installation pre-tightening force.
The turbine guide vane installation structure according to claim 5, characterized in that the metal uprights (22) include a plurality of uprights that are respectively provided with the leading edge, trailing edge and suction surface protruding positions of the blade, and each of the uprights is independent. It cooperates with the metal elastic element (6) and the plurality of nuts (4).
The turbine guide vane installation structure according to claim 5, characterized in that the metal column (22) includes an axial cavity (222) and a plurality of cold air outflow holes (223), and the cold air outflow holes (223) Used to communicate the axial cavity (222) and the outside of the metal column (22).
The turbine guide vane mounting structure according to claim 5, characterized in that the metal column (22) includes a mounting end (221), and the mounting end (221) includes threads for connecting with the nut (4). Thread fit.
The turbine guide vane installation structure according to claim 5, characterized in that the turbine guide vane installation structure further includes a thin-walled bushing (5), built in the hollow cavity (111) and sleeved on the metal The outside of the column (22) includes a plurality of impact cooling holes (51).
The turbine guide vane installation structure according to claim 9, characterized in that the upper cover plate (3) includes an upper limit groove (315), and the lower cover plate (2) includes a lower limit groove (215). , the upper limit groove (315) and the lower limit groove (215) are respectively used to embed the thin-walled bushing (5), and rely on the resilience of the metal elastic element (6) to make the The thin-walled bushing (5) is stuck between the upper limiting groove (315) and the lower limiting groove (215), so that the thin-walled bushing (5) and the metal column (22 ), the upper cover plate (3) and the lower cover plate (2) define an annular cavity, and the annular cavity is connected with the through hole (316).
The turbine guide vane installation structure according to claim 5, characterized in that the radial outer side of the upper cover plate (3) includes an annular protrusion (32), and the annular protrusion (32) forms an annular groove (322). ), the annular groove (322) is a part of the through hole (316) and is for the metal column (22) to pass through. The annular groove (322) is used to place the metal elastic element (6 ), the bottom surface (42) of the nut (4) abuts the flange surface (328) of the annular protrusion (32).
The turbine guide vane installation structure according to claim 11, characterized in that the annular protrusion (32) further includes a plurality of notches (321), the notches (321) are against the bottom surface (42) of the An air inlet channel is formed when the flange surface (328) is on the upper surface.

The metal elastic element (6), the inner wall of the annular protrusion (32) and the outer wall of the metal column (22) form a cold air channel, and the cold air channel is connected with the air inlet channel and the through hole (316) .
The turbine guide vane installation structure according to claim 5, characterized in that the metal elastic element (6) is a coil spring, and the cross section of the metal elastic element (6) is rectangular.
The turbine guide vane installation structure according to claim 2, characterized in that the upper cover plate (3) further includes a mounting hook (33) for installing the turbine guide vane (1) to the casing.
A turbine, characterized in that it includes a turbine guide vane according to any one of claims 1-14.