A ceramic-based composite adjustable turbine guide vane

Abstract

The present invention belongs to a blade. In order to solve the technical problem that the current ceramic-based composite material adjustable turbine guide blade is not suitable for bearing torsional loads and cannot meet the use requirements, a ceramic-based composite material adjustable turbine guide blade is provided. The blade body is composed of a blade back and a blade basin of a rotating surface to form a rotating body structure, which effectively improves the effect of the blade body transmitting torque, and the rotating body has high strength. In addition, the upper and lower end surfaces of the blade body are designed with flanges, which can increase the combined area of ​​the blade body and the upper edge plate and the lower edge plate, and is also conducive to the bearing and transmission of torque in a high-temperature working environment.

Description

Technical Field

[0001] The invention belongs to a blade, and in particular relates to an adjustable turbine guide vane made of ceramic-based composite material. Background Art

[0002] In order to reduce the fuel consumption rate of aircraft and enhance the high maneuverability of aircraft, the world's aviation powers are competing to develop variable cycle aircraft engines. Variable cycle aircraft engines are gas turbine aircraft engines with different thermodynamic cycles obtained by changing the geometric shape, size or position of some components in the engine. Among them, the adjustable turbine guide vane is one of the most important components of the variable cycle aircraft engine. By changing the turbine throat area, the air flow of the engine can be controlled, thereby changing the engine cycle working mode, so that the engine can work in the best state under various flight conditions. According to the use conditions in the turbine of the new high-performance variable cycle aircraft engine and the load characteristics of the adjustable guide vane, designing a new adjustable turbine guide vane is the main task of developing a new generation of aircraft engines.

[0003] At present, most of the new advanced high-performance aircraft engines are variable cycle aircraft engines, and the temperature before the turbine is as high as 2100K or more. Even if cooling technology is used and the adjustable turbine guide vane is made of high-temperature alloy materials, it is difficult to meet the working requirements under this condition. It is urgent to develop new materials to adapt to the development of new high-performance variable cycle aircraft engine adjustable turbine guide vanes. SiC / SiC ceramic matrix composite material is a new type of thermal structure / functional integrated material with the advantages of high temperature resistance, high specific strength, high specific modulus, oxidation resistance, long life, low density and insensitivity to cracks. It is very suitable for use in the turbine of new high-performance variable cycle aircraft engines.

[0004] There are very few reports on ceramic-based composite adjustable turbine guide vanes, and this type of blade is basically still in the research and exploration stage. The existing ceramic-based composite turbine guide vanes are all fixed guide vanes, the blade body is a vertical rotating body structure, the upper and lower edge plates are arc-shaped plate structures and are perpendicular to the blade body, and the blade body and the upper and lower edge plates are connected into a whole through online riveting technology. In this structural form, due to the small contact area between the blade body and the edge plate, it is not suitable for bearing torsional loads. However, the adjustable turbine guide vanes of variable cycle aircraft engines are mostly complex rotating small-sized structures, which need to overcome the aerodynamic load under high temperature and high pressure airflow conditions and rotate around the rotating shaft within a certain angle range. This functional feature requires the adjustable turbine guide vanes to have a good ability to withstand torsional loads. Therefore, the existing blade structure cannot meet the use requirements of adjustable turbine guide vanes. Summary of the invention

[0005] The present invention provides a ceramic-based composite material adjustable turbine guide vane to solve the technical problem that the current ceramic-based composite material adjustable turbine guide vane is not suitable for bearing torsional loads and cannot meet the use requirements.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A ceramic-based composite material adjustable turbine guide vane, comprising a blade body, an upper edge plate and a lower edge plate; the blade body, the upper edge plate and the lower edge plate are all made of ceramic-based composite materials;

[0008] The blade back and blade basin of the blade body are both revolution surfaces, one side of the blade back and one side of the blade basin are smoothly connected through an arc surface, and the other side of the blade back is connected to the other side of the blade basin, and the inner surfaces of the blade back and the blade basin form surface contact at the connection, so that a cavity with openings at the upper and lower ends is formed inside the blade body;

[0009] The upper end surface and the lower end surface of the blade back and the upper end surface and the lower end surface of the blade basin are all provided with flanges extending to the outside; wherein the flange located at the upper end surface of the blade back is the first flange, the flange located at the lower end surface of the blade back is the second flange, the flange located at the upper end surface of the blade basin is the third flange, and the flange located at the lower end surface of the blade basin is the fourth flange;

[0010] The upper edge plate and the lower edge plate are respectively installed at the openings of the upper end surface and the lower end surface of the blade body by riveting.

[0011] Furthermore, the blade back and blade basin are both twisted surfaces of revolution.

[0012] Further, the upper edge plate includes an upper mounting seat and a first interface section;

[0013] The upper mounting seat is mounted on the first flange and the third flange by riveting, and the first interface section is mounted on the upper mounting seat by riveting;

[0014] The first interface section and the upper mounting seat are both hollow structures and are connected to the cavity. The hollow structure of the first interface section is connected to the outside, and the upper mounting seat closes the upper end opening of the cavity.

[0015] Furthermore, the upper mounting seat comprises a first seat body and two side ears riveted to each other; the first interface section comprises an upper opening section and two first clamping parts;

[0016] The first seat body is a hollow column, and two mounting grooves are provided on the lower end surface of the first seat body, and the two mounting grooves are respectively adapted to the first flange and the third flange, and the two mounting grooves of the first seat body are riveted to the first flange and the third flange respectively; the two side ears are both located between the lower end surface of the first seat body and the upper end surface of the blade body, and the two side ears are respectively located between the two mounting grooves, and are used to close the upper end opening of the cavity;

[0017] The upper section is in the shape of a hollow column. The two first clamping parts are spliced ​​into a circular ring and are both riveted to the lower end of the upper section. The first clamping parts are riveted to the first seat body.

[0018] Furthermore, a limiting protrusion is provided on the inner wall of the first clamping member, and a limiting groove matched with the limiting protrusion is provided at the lower end of the upper opening section.

[0019] Furthermore, the lower edge plate includes a second seat body and two second clamping members;

[0020] The second seat body is in a hollow column shape, and the second flange and the fourth flange are located in the second seat body;

[0021] The two second clamping parts are sleeved on the outside of the second base body, and the two second clamping parts, the second base body and the blade body are riveted into a whole.

[0022] Furthermore, the second seat body and the two second clamping members are connected via radial pins.

[0023] Furthermore, the wall thickness of the blade body is equal at all locations.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. The present invention proposes a ceramic-based composite material adjustable turbine guide vane, wherein the blade body is composed of a blade back and a blade basin of a rotating surface, forming a rotating body structure, which effectively improves the effect of the blade body transmitting torque, and the rotating body has high strength. In addition, the upper and lower end surfaces of the blade body are designed with flanges, which can increase the combined area of ​​the blade body and the upper and lower edge plates, and is also conducive to the bearing and transmission of torque in a high-temperature working environment.

[0026] 2. The upper edge plate structure of the present invention is that the upper edge plate components and the flanged end surface of the blade body are riveted as a whole, so that the rotational torque of the blade body can be transmitted to the upper edge plate, which effectively solves the torque transmission problem from the blade body to the upper edge plate. At the same time, it also improves the connection reliability between the various components of the upper edge plate.

[0027] 3. The components of the lower edge plate structure in the present invention are riveted together with the flanges of the lower end surface of the blade body as a whole, and then connected with radial pins, so that the rotational torque of the blade body can be transmitted to the lower edge plate through the radial pins, which effectively solves the torque transmission problem from the blade body to the lower edge plate. At the same time, it also improves the connection reliability between the various components of the lower edge plate.

[0028] 4. In the present invention, the wall thickness of the blade body is equal at all places, which is convenient for processing and characterization, and also convenient for the cold zone gas to flow through the internal cavity of the blade body. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 A schematic diagram of an embodiment of a ceramic-based composite adjustable turbine guide vane of the present invention;

[0030] Figure 2 A schematic diagram of a blade body and a blade back in an embodiment of a ceramic-based composite adjustable turbine guide vane of the present invention;

[0031] Figure 3 A schematic diagram of a blade body in an embodiment of a ceramic-based composite adjustable turbine guide vane of the present invention;

[0032] Figure 4 An exploded view of an upper edge plate of an embodiment of an adjustable turbine guide vane of a ceramic-based composite material according to the present invention;

[0033] Figure 5 It is a schematic diagram of an upper edge plate of an adjustable turbine guide vane of a ceramic-based composite material according to the present invention being installed on a blade body;

[0034] Figure 6 An exploded view of a lower edge plate of an adjustable turbine guide vane made of ceramic matrix composite material according to the present invention.

[0035] Among them: 1-blade body, 101-blade back, 102-blade basin, 103-arc surface, 104-flange, 105-cavity, 2-upper edge plate, 201-upper mounting seat, 2011-first seat body, 2012-side ear, 2013-mounting groove, 202-first interface section, 2021-upper mouth section, 2022-first clamping piece, 2023-limiting protrusion, 2024-limiting groove, 3-lower edge plate, 301-second seat body, 302-second clamping piece. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0037] The structural design of ceramic matrix composite adjustable turbine guide vane faces four major challenges: (1) It is difficult to realize the process in a narrow design space. The adjustable turbine guide vane is small in size, and it must ensure that its function is realized and that the cooling air enters from the bottom of the blade and flows out smoothly from the top. Therefore, the available design space is very small. (2) It is difficult to improve the ability of the blade to bear torsional loads. When the adjustable turbine guide vane is working, it needs to overcome a large high-temperature and high-speed aerodynamic load to rotate, and it must be ensured that it has the ability to withstand extremely large torque; (3) It is difficult to enhance the torque transmission ability of the blade to the upper and lower edge plates. The upper and lower ends of the blade must drive the upper and lower edge plates to rotate, and the combined area of ​​the blade and the upper and lower edge plates must be increased to enable them to have the ability to transmit torque. (4) It is difficult to ensure the reliability of the fixation and connection between the blade and the upper and lower edge plates. For this reason, it is necessary to further optimize the design of the adjustable turbine guide vane structure.

[0038] In view of the design requirements of the adjustable turbine guide vane and the above technical difficulties, combined with the process characteristics and performance laws of ceramic-based composite materials, the present invention optimizes the design of the adjustable turbine guide vane structure.

[0039] like Figure 1 As shown, under the premise of ensuring structural integrity, in order to realize the process of ceramic matrix composite materials, a ceramic matrix composite material adjustable turbine guide vane of the present invention includes an upper edge plate 2, a blade body 1 and a lower edge plate 3. Under the condition of ensuring the aerodynamic shape of the blade, in order to ensure that the blade body 1 has excellent structural strength and the ability to withstand and transmit torque, the overall structure of the blade body 1 is designed to be an I-shaped rotating body structure. Figures 1 to 3As shown. The blade back 101 and blade pot 102 of the blade body 1 are both rotating surfaces with a certain twist. One side of the blade back 101 and one side of the blade pot 102 are smoothly connected through an arc surface 103. The arc surface 103 is not a standard arc surface, but is inclined to the outside of the blade body 1. The other side of the blade back 101 is connected to the other side of the blade pot 102. At the connection, the inner surfaces of the blade back 101 and the blade pot 102 form a surface contact, that is, the other side of the blade back 101 and the other side of the blade pot 102 intersect at one point, so that a cavity 105 with openings at both the upper and lower ends is formed inside the blade body 1. The upper and lower end surfaces of the blade back 101 and the upper and lower end surfaces of the blade pot 102 are all provided with flanges 104 extending to the outside. For the convenience of description, the flange located at the upper end surface of the blade back 101 is recorded as the first flange, the flange located at the lower end surface of the blade back 101 is recorded as the second flange, the flange located at the upper end surface of the blade basin 102 is recorded as the third flange, and the flange located at the lower end surface of the blade basin 102 is recorded as the fourth flange. When preparing the blade body 1, the corresponding blade body preform can be formed by winding and laying a two-dimensional SiC fiber cloth or C fiber cloth with the help of a cavity 105 inner mold, and the root of the blade body 1 is respectively turned outward at 90°. The flange 104 can also form a part of the upper edge plate 2 and the lower edge plate 3. After the interface layer preparation and the matrix preparation, an I-shaped blade body 1 structure is formed.

[0040] The present invention designs an I-shaped rotor blade 1 structure capable of bearing and transmitting torque. The blade 1 has a uniform wall thickness at all locations, and can generally be designed to have a wall thickness of 2 mm. The uniform wall thickness rotor blade 1 structure is convenient for shaping the two-dimensional SiC fiber cloth or C fiber cloth preform during processing, and provides an effective channel for cold zone air to flow through the internal cavity 105 of the blade 1. The advantages of the I-shaped blade 1 structure, such as good torque transmission effect, high rotor structure strength, and flanged edges that can increase the combined area between the blade 1 and the upper edge plate 2 and the lower edge plate 3, are fully utilized to solve the problem of bearing and transmitting torque of adjustable turbine guide blades under high temperature and high pressure airflow.

[0041] like Figure 4 and Figure 5As shown, in order to facilitate the preform molding and the densification of the material, ensure that the blade body 1 is reliably connected to the upper edge plate 2, and be able to transmit the torque to the upper edge plate 2, the upper edge plate 2 includes an upper mounting seat 201 and a first interface section 202, the upper mounting seat 201 includes a first seat body 2011 and two side ears 2012 riveted to each other, and the first interface section 202 includes an upper opening section 2021 and two first clamping parts 2022. The first seat body 2011 is a hollow column, and two mounting grooves 2013 are provided on the lower end surface of the first seat body 2011. The two mounting grooves 2013 are respectively matched with the first flange and the third flange, and the two mounting grooves 2013 of the first seat body 2011 are respectively riveted to the first flange and the third flange; the two side ears 2012 are both located between the lower end surface of the first seat body 2011 and the upper end surface of the blade body 1, and the two side ears 2012 are respectively located between the two mounting grooves 2013, and are used to close the upper end opening of the cavity 105. The upper section 2021 is a hollow column, and the two first clamping pieces 2022 are spliced ​​into a ring shape, and are both riveted to the lower end of the upper section 2021, and the first clamping piece 2022 is riveted to the first seat body 2011. In addition, a limiting protrusion 2023 is provided on the inner wall of the first clamping member 2022, and a limiting groove 2024 matching the limiting protrusion 2023 is provided at the lower end of the upper opening section 2021. The components of the upper edge plate 2 are connected to the blade body 1 as a whole through the CVI online riveting technology. The upper edge plate 2 structure in the present invention can output cooling gas through the upper mounting seat 201 and the first interface section 202, and has the function of transmitting torsional load. The first seat body 2011 and the upper section 2021 of the rotary upper edge plate 2 are both hollow columns, and the inner cavity of the column ensures the outflow channel of the cold zone gas. The various components of the upper edge plate 2 are connected into a whole through the CVI online riveting technology, and then riveted into a whole with the upper end face flange 104 of the blade body 1 through the CVI online riveting technology, so that the rotational torque of the blade body 1 is transmitted to the upper edge plate 2 through the flange 104 of the upper end face of the blade body 1, effectively solving the torque transmission from the blade body 1 to the upper edge plate 2 and the connection reliability problems between the various parts of the upper edge plate 2.

[0042] like Figure 6As shown, in order to facilitate the preform molding and material densification, ensure that the blade 1 is reliably connected to the lower edge plate 3, and be able to transmit torque to the lower edge plate 3, the lower edge plate 3 includes a second seat body 301 and two second clamping parts 302. The second seat body 301 is a hollow column, and the second flange and the fourth flange are located in the second seat body 301. The two second clamping parts 302 are sleeved on the outside of the second seat body 301, and the two second clamping parts 302, the second seat body 301 and the blade 1 are riveted as a whole. The second seat body 301 and the two second clamping parts 302 are also connected by radial pins. The various components of the lower edge plate 3 are connected to the blade 1 as a whole through CVI online riveting technology. The radial pins also contribute to torque transmission. The lower edge plate 3 of the present invention can input cooling gas through the second seat body 301, and has the function of transmitting torsional loads. The lower edge plate 3 and the flange 104 on the lower end surface of the blade body 1 form a cavity, which can ensure that the cooling air flows smoothly from the bottom to the top of the adjustable turbine guide blade. The components of the lower edge plate 3 and the flange 104 on the lower end surface of the blade body 1 are connected into an organic whole through CVI online riveting technology, so that the rotational torque of the blade body 1 is transmitted to the lower edge plate 3 through the radial pins, effectively solving the torque transmission from the blade body 1 to the lower edge plate 3 and the connection reliability problems between the various parts of the lower edge plate 3.

[0043] The present invention aims at the many problems of low high temperature resistance, heavy weight, narrow design space, difficult preform shaping, and difficult torque transmission of the adjustable turbine guide vane of high-performance variable cycle aircraft engine. According to the transmission route and load conditions of the adjustable turbine guide vane force, combined with the molding characteristics of SiC fiber toughened silicon carbide ceramic matrix composite materials, a ceramic matrix composite material adjustable turbine guide vane composed of an upper edge plate 2, an I-shaped rotating body blade 1, and a lower edge plate 3 is proposed. The blade 1 effectively solves the problems of blade preform shaping and torque transmission of the adjustable blade. The present invention can significantly improve the temperature resistance of the adjustable turbine guide vane of the variable cycle aircraft engine, reduce the weight, and enhance the torque transmission capacity of the adjustable turbine guide vane, thereby improving the working efficiency of the aircraft engine and the air flow matching capacity when the variable cycle engine is switched.

[0044] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A ceramic matrix composite adjustable turbine guide vane, comprising a blade body (1), an upper edge plate (2) and a lower edge plate (3); characterized in that: The blade body (1), the upper edge plate (2) and the lower edge plate (3) are all made of ceramic-based composite materials; The blade back (101) and the blade pot (102) of the blade body (1) are both revolving surfaces, one side of the blade back (101) and one side of the blade pot (102) are smoothly connected via a curved surface (103), and the other side of the blade back (101) and the other side of the blade pot (102) are connected, and the inner surfaces of the blade back (101) and the blade pot (102) form surface contact at the connection point, so that a cavity (105) with openings at both the upper and lower ends is formed inside the blade body (1); The upper end surface and the lower end surface of the blade back (101) and the upper end surface and the lower end surface of the blade basin (102) are both provided with flanges (104) extending to the outside; wherein the flange located at the upper end surface of the blade back (101) is a first flange, the flange located at the lower end surface of the blade back (101) is a second flange, the flange located at the upper end surface of the blade basin (102) is a third flange, and the flange located at the lower end surface of the blade basin (102) is a fourth flange; The upper edge plate (2) and the lower edge plate (3) are respectively mounted on the upper end surface and the lower end surface openings of the blade body (1) by riveting.

2. According to claim 1, a ceramic matrix composite adjustable turbine guide vane, characterized in that: The blade back (101) and the blade basin (102) are both twisted surfaces of revolution.

3. A ceramic matrix composite adjustable turbine guide vane according to claim 1 or 2, characterized in that: The upper edge plate (2) comprises an upper mounting seat (201) and a first interface section (202); The upper mounting seat (201) is mounted on the first flange and the third flange by riveting, and the first interface section (202) is mounted on the upper mounting seat (201) by riveting; The first interface section (202) and the upper mounting seat (201) are both hollow structures and are in communication with the cavity (105); the hollow structure of the first interface section (202) is in communication with the outside, and the upper mounting seat (201) closes the upper opening of the cavity (105).

4. The ceramic matrix composite adjustable turbine guide vane according to claim 3, characterized in that: The upper mounting seat (201) comprises a first seat body (2011) and two side ears (2012) riveted to each other; the first interface section (202) comprises an upper opening section (2021) and two first clamping parts (2022); The first seat body (2011) is in the shape of a hollow column, and two mounting grooves (2013) are provided on the lower end surface of the first seat body (2011), and the two mounting grooves (2013) are respectively adapted to the first flange and the third flange, and the two mounting grooves (2013) of the first seat body (2011) are respectively riveted to the first flange and the third flange; the two side ears (2012) are both located between the lower end surface of the first seat body (2011) and the upper end surface of the blade body (1), and the two side ears (2012) are respectively located between the two mounting grooves (2013), and are used to close the upper end opening of the cavity (105); The upper section (2021) is in the shape of a hollow column, and the two first clamping parts (2022) are spliced ​​into a circular ring shape and are both riveted to the lower end of the upper section (2021), and the first clamping parts (2022) are riveted to the first seat body (211).

5. The ceramic matrix composite adjustable turbine guide vane according to claim 4, characterized in that: A limiting protrusion (2023) is provided on the inner wall of the first clamping member (2022), and a limiting groove (2024) adapted to the limiting protrusion (2023) is provided at the lower end of the upper opening section (2021).

6. The ceramic matrix composite adjustable turbine guide vane according to claim 5, characterized in that: The lower edge plate (3) comprises a second base body (301) and two second clamping parts (302); The second base body (301) is in the shape of a hollow column, and the second flange and the fourth flange are located inside the second base body (301); The two second clamping parts (302) are sleeved on the outside of the second base body (301), and the two second clamping parts (302), the second base body (301) and the blade body (1) are riveted together as a whole.

7. The ceramic matrix composite adjustable turbine guide vane according to claim 6, characterized in that: The second seat body (301) and the two second clamping parts (302) are connected via radial pins.

8. The ceramic matrix composite adjustable turbine guide vane according to claim 7, characterized in that: The wall thickness of the blade body (1) is equal at all locations.

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