A turbine guide vane based on a ceramic matrix composite blade

Abstract

The present invention discloses a turbine guide vane based on a ceramic matrix composite airfoil, comprising: an inner rim plate, an airfoil, and an outer fixing sleeve. Both the inner rim plate and the outer fixing sleeve are made of metal materials, the airfoil is made of a ceramic matrix composite material. Both the inner rim plate and the outer fixing sleeve are of annular structures. The inner rim plate is arranged inside the outer fixing sleeve, and a plurality of the airfoils are circumferentially and equidistantly distributed between the inner rim plate and the outer fixing sleeve. In the present invention, the airfoil material is made of a ceramic matrix composite material, while the inner rim plate, the outer rim plate, and the outer cover for fixing the airfoil are all made of metal materials. By utilizing the high-temperature resistance and low-density characteristics of the ceramic matrix composite material, the turbine guide vane assembly has high strength and long service life under high-temperature working conditions, reduces the demand for cooling air, and can improve the overall performance of aeroengines and gas turbines, so as to achieve the purposes of engine weight reduction, increase of turbine inlet temperature, and simplification of the cooling system, etc.

Description

Technical Field

[0001] The present invention belongs to the technical field of turbines, and particularly relates to a turbine guide vane based on a ceramic matrix composite airfoil. Background Art

[0002] In the guide vane designed by the prior art, the guide vanes are divided into several fan-shaped segments along the circumferential direction. Each fan-shaped segment is a single-row or multi-row guide vane. The latter usually integrates the airfoil with the upper and lower edge plates and is integrally cast with a superalloy material. As Figure 4 shown.

[0003] In order to improve the efficiency, modern aero-engines and gas turbines pursue higher compressor pressure ratios and turbine inlet gas temperatures. Under such working conditions, for the metal turbine guide vane designed by the prior art, since the gas temperature is higher than the melting point of the material, it is necessary to draw cooling air from the compressor to cool the metal guide vanes. The higher the gas temperature, the more cooling air needs to be drawn, which mainly causes two aspects of influence: on the one hand, the metal vanes are between the high-temperature gas and the low-temperature cooling air, and the metal vanes need to bear higher thermal stresses, which has an adverse impact on the strength and life of the metal vanes. On the other hand, a large amount of cooling air drawn from the compressor has an adverse impact on the performance of aero-engines and gas turbines. Summary of the Invention

[0004] In order to overcome the defects existing in the above-mentioned prior art, the purpose of the present invention is to solve the problem of insufficient strength and life of the guide vanes caused by the relatively high turbine inlet temperature in large and medium-sized aero-engines and gas turbines. To achieve the above purpose, the present invention provides the following technical solutions:

[0005] A turbine guide vane based on a ceramic matrix composite airfoil, comprising: an inner edge plate, an airfoil, and an outer fixing sleeve. Both the inner edge plate and the outer fixing sleeve are made of metal materials, the airfoil is a ceramic matrix composite material, both the inner edge plate and the outer fixing sleeve are of annular structures, the inner edge plate is arranged inside the outer fixing sleeve, and a plurality of the airfoils are circumferentially and equidistantly distributed between the inner edge plate and the outer fixing sleeve.

[0006] Further, the outer fixing sleeve includes an outer edge plate and an outer cover, and the outer cover is sleeved on the outer edge plate.

[0007] Further, a plurality of outer edge plate limiting airfoil holes are provided on the outer edge plate, and the outer edge plate limiting airfoil holes are in one-to-one correspondence and cooperation with the airfoils.

[0008] Further, a plurality of inner edge plate limiting airfoil grooves are provided on the inner edge plate, and the inner edge plate limiting airfoil grooves are in one-to-one correspondence and cooperation with the airfoils.

[0009] Further, a reserved gap exists between the outer edge plate limiting airfoil holes and the airfoils.

[0010] Further, there is a reserved gap between the inner edge plate limiting blade profile groove and the blade body.

[0011] Further, the outer cover is formed by connecting a plurality of identical outer cover pieces end to end.

[0012] Further, a sealing ring groove is provided at one end of the outer edge plate, the sealing ring groove is located outside the outer cover, and a sealing ring is provided between the sealing ring groove and the outer cover.

[0013] Further, a slot is provided inside the outer cover, and a boss extending outward is provided at one end of the outer edge plate, and the boss is inserted into the slot.

[0014] Further, one end face of the blade body is attached to the inner edge plate, and there is a gap between the other end face of the blade body and the outer fixing sleeve.

[0015] Technical effects and advantages of the present invention:

[0016] In the present invention, the blade body material is made of a ceramic matrix composite material, while the inner edge plate, outer edge plate, and outer cover used for fixing the blade body are all made of metal materials. Utilizing the high-temperature resistance and low-density characteristics of the ceramic matrix composite material, the turbine guide vane assembly has high strength and long life under high-temperature working conditions, and reduces the demand for cooling air, which can improve the overall performance of aeroengines and gas turbines, so as to achieve the purposes of reducing the weight of the engine, increasing the turbine inlet temperature, and simplifying the cooling system; on this basis, using metal to make the inner edge plate, outer edge plate, and outer cover utilizes the easy-to-shape characteristics of metal materials to reduce the manufacturing cost of the overall turbine guide.

[0017] Other features and advantages of the present invention will be described in the subsequent specification, and, in part, will be obvious from the specification, or will be understood by implementing the present invention. The objectives and other advantages of the present invention can be achieved and obtained through the structures pointed out in the specification and the drawings. Brief Description of the Drawings

[0018] Figure 1 It is a schematic structural view of a turbine guide based on a blade body of a ceramic matrix composite material according to the present invention;

[0019] Figure 2 It is a cross-sectional view of a turbine guide based on a blade body of a ceramic matrix composite material according to the present invention;

[0020] Figure 3 It is a schematic structural view of the inner edge plate lower limiting blade profile groove and the outer edge plate limiting blade profile hole in a turbine guide based on a blade body of a ceramic matrix composite material according to the present invention;

[0021] Figure 4It is a schematic structural diagram of a turbine guide vane in the prior art.

[0022] In the figure: 1 - outer cover, 2 - inner edge plate, 3 - blade body, 4 - outer edge plate, 5 - sealing ring, 6 - sealing ring groove, 7 - inner edge plate limiting blade profile groove, 8 - outer edge plate limiting blade profile hole, 9 - slot. Specific embodiments

[0023] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts shall fall within the protection scope of the present invention.

[0024] In addition, in the invention, terms such as "first", "second" and other similar terms do not imply any order, quantity or importance, but are only used to distinguish different elements. Terms such as "upper", "lower", "left", "right" and other similar terms are only the positional relationships in the drawings.

[0025] As Figure 4 shown, Figure 4 It is a schematic structural diagram of a turbine guide vane in the prior art. In the guide vane designed in the prior art, the guide vanes are divided into several fan-shaped segments along the circumferential direction. Each fan-shaped segment is a single-row or multi-row guide vane. The latter usually integrates the blade body with the upper and lower edge plates and is integrally cast with a superalloy material.

[0026] In modern aero-engines and gas turbines, the metal blades are between high-temperature combustion gas and low-temperature cooling gas, and the metal blades need to bear high thermal stress, which has an adverse impact on the strength and life of the metal blades. And in the cooling system, a large amount of cooling gas is led out from the compressor, which has an adverse impact on the performance of aero-engines and gas turbines.

[0027] In the present invention, the blade body material is made of a ceramic matrix composite material. Utilizing the high-temperature resistance and low density characteristics of the ceramic matrix composite material, the turbine guide vane assembly has high strength and long life under high-temperature working conditions, and reduces the demand for cooling gas, which can improve the overall performance of aero-engines and gas turbines, so as to achieve the purposes of reducing the weight of the engine, increasing the turbine inlet temperature, and simplifying the cooling system.

[0028] The following will be described by specific embodiments.

[0029] As attached Figure 1As shown in the figure, this embodiment provides a turbine guide vane based on a ceramic matrix composite blade body, including: an inner rim plate 2, a blade body 3, and an outer fixing sleeve. Both the inner rim plate 2 and the outer fixing sleeve are made of metal materials. The blade body 3 is a ceramic matrix composite material. Both the inner rim plate 2 and the outer fixing sleeve are of annular structures. The inner rim plate 2 is arranged inside the outer fixing sleeve, and a plurality of the blade bodies 3 are circumferentially and equidistantly distributed between the inner rim plate 2 and the outer fixing sleeve.

[0030] Compared with superalloy materials, ceramic matrix composite materials have excellent properties such as low density and high temperature resistance. Using them on turbine guide vanes can bring many benefits such as reducing the weight of the engine, increasing the turbine inlet temperature, and simplifying the cooling system. However, the process freedom of ceramic matrix composite materials is far less than that of metal materials. Therefore, both the outer fixing sleeve and the inner rim plate 2 are made of metal materials. On the other hand, the main component in the guide vane component that bears the impact of high-temperature gas is the blade body 3, and the temperatures of the inner rim plate 2 and the outer fixing sleeve do not exceed the temperature-bearing capacity of the metal, and metal materials are more suitable for machining into complex curved surface structures of the inner rim plate 2 and the outer fixing sleeve.

[0031] As Figure 2 and Figure 3 shown in the figure, in an embodiment of the present invention, the outer fixing sleeve includes an outer rim plate 4 and an outer cover 1, and the outer cover 1 is sleeved on the outer rim plate 4. Among them, a plurality of outer rim plate limiting blade-shaped holes 8 are provided on the outer rim plate 4, and the outer rim plate limiting blade-shaped holes 8 are in one-to-one correspondence and cooperation with the blade body 3. The outer cover 1 is formed by connecting the heads and tails of a plurality of identical outer cover pieces. When installing the turbine guide vane, the blade body 3 is inserted through the outer rim plate limiting blade-shaped holes 8 for installation. After installing the blade body 3, then the plurality of outer cover pieces are sequentially connected and installed around the outer rim plate 4.

[0032] As Figure 2 and Figure 3 shown in the figure, in an embodiment of the present invention, a plurality of inner rim plate limiting blade-shaped grooves 7 are provided on the inner rim plate 2, and the inner rim plate limiting blade-shaped grooves 7 are in one-to-one correspondence and cooperation with the blade body 3. Different from the outer rim plate limiting blade-shaped holes 8, the inner rim plate limiting blade-shaped grooves 7 are not only used for limiting the blade body 3, but also for supporting and fixing the blade body 3. For this reason, one end face of the blade body 3 is attached to the inner rim plate 2, and there is a gap between the other end face of the blade body 3 and the outer fixing sleeve.

[0033] Since metal materials and ceramic matrix composite materials have different thermal expansion coefficients, the expansion deformation amount of metal materials is greater than that of ceramic matrix composite materials at high temperatures. Therefore, in an embodiment of the present invention, there is a reserved gap between the outer rim plate limiting blade-shaped holes 8 and the blade body 3, and there is also a reserved gap between the inner rim plate limiting blade-shaped grooves 7 and the blade body 3.

[0034] Through reasonable clearance design, it can be ensured that the blade profile holes of the upper metal edge plate and the limiting blade profile grooves of the lower edge plate shrink and extrude the ceramic matrix composite blade body during the working state. Since the compressive strength of the ceramic matrix composite is much higher than the tensile strength, the limited compressive stress will not cause damage to the ceramic matrix composite. The shrinkage of the blade profile holes of the upper edge plate and the limiting grooves of the lower edge plate can not only achieve axial and circumferential limitation of the guide vane during the working state, but also seal the flow passage, thus preventing gas leakage.

[0035] As Figure 2 shown, in an embodiment of the present invention, a sealing ring groove 6 is provided at one end of the outer edge plate 4. The sealing ring groove 6 is located outside the outer cover 1. A sealing ring 5 is provided between the sealing ring groove 6 and the outer cover 1 for sealing the gap between the outer cover 1 and the outer edge plate 4.

[0036] As Figure 2 shown, in an embodiment of the present invention, a slot 9 is provided inside the outer cover 1. One end of the outer edge plate 4 is provided with a convex platform extending outward. The convex platform is inserted into the slot 9 to strengthen the connection between the outer cover 1 and the outer edge plate 4.

[0037] Finally, it should be noted that the above are only preferred embodiments of the present invention and are not used to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, 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 turbine guide vane based on a ceramic matrix composite blade, characterized in that, it includes: an inner rim plate (2), a blade (3), and an outer fixing sleeve. Both the inner rim plate (2) and the outer fixing sleeve are made of metal materials. The blade (3) is a ceramic matrix composite material. Both the inner rim plate (2) and the outer fixing sleeve are of annular structures. The inner rim plate (2) is arranged inside the outer fixing sleeve. A plurality of the blades (3) are circumferentially and equidistantly distributed between the inner rim plate (2) and the outer fixing sleeve; the outer fixing sleeve includes an outer rim plate (4) and an outer cover (1), and the outer cover (1) is sleeved on the outer rim plate (4); a plurality of outer rim plate limiting blade-shaped holes (8) are provided on the outer rim plate (4), and the outer rim plate limiting blade-shaped holes (8) are in one-to-one correspondence and cooperation with the blades (3); a plurality of inner rim plate limiting blade-shaped grooves (7) are provided on the inner rim plate (2), and the inner rim plate limiting blade-shaped grooves (7) are in one-to-one correspondence and cooperation with the blades (3); a reserved gap exists between the outer rim plate limiting blade-shaped hole (8) and the blade (3); a reserved gap exists between the inner rim plate limiting blade-shaped groove (7) and the blade (3); one end face of the blade (3) is in contact with the inner rim plate (2), and a gap exists between the other end face of the blade (3) and the outer fixing sleeve.

2. The turbine guide vane based on a ceramic matrix composite blade according to claim 1, characterized in that, the outer cover (1) is formed by connecting a plurality of identical outer cover pieces end to end.

3. The turbine guide vane based on a ceramic matrix composite blade according to claim 1, characterized in that, a seal ring groove (6) is provided at one end of the outer rim plate (4), the seal ring groove (6) is located outside the outer cover (1), and a seal ring (5) is provided between the seal ring groove (6) and the outer cover (1).

4. The turbine guide vane based on a ceramic matrix composite blade according to claim 1, characterized in that, a slot (9) is provided inside the outer cover (1), and a boss extending outward is provided at one end of the outer rim plate (4), and the boss is inserted into the slot (9).

Images