Fan hollow guide vane, manufacturing method and aeroengine

Abstract

The application discloses a fan hollow guide vane, a preparation method and an aero-engine, and relates to the technical field of aviation, and aims to solve the problems of excessive weight and insufficient rigidity of the existing guide vane. The framework of the fan hollow guide vane is a composite material framework, the composite material framework comprises a silicon carbide fiber reinforced titanium-based composite material, the guide vane has a vane leading edge and a vane trailing edge, and the guide vane is provided with a plurality of hollow cavities which are distributed along the distribution direction from the vane leading edge to the vane trailing edge. The aero-engine comprises an inner casing, an outer casing and the fan hollow guide vane. The fan hollow guide vane provided by the application is used for reducing the weight of the guide vane, improving the rigidity of the guide vane, and thus improving the performance of the aero-engine.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aviation technology, and in particular to a fan hollow guide vane, a manufacturing method and an aero-engine. BACKGROUND

[0002] The stator guide vane is one of the core parts of the aero-engine, and its proportion in the aero-engine manufacturing is about 30%. The stator guide vane completes the compression and expansion of the gas in the aero-engine and produces powerful thrust with the highest efficiency.

[0003] However, when the aero-engine is working, the fan inlet guide vane bears very complex load, so when the weight of the fan inlet guide vane is too large and the rigidity is insufficient, the reliability of the aero-engine will be affected. SUMMARY

[0004] The purpose of the present application is to provide a fan hollow guide vane, a manufacturing method and an aero-engine to reduce the weight of the guide vane, improve the rigidity of the guide vane and thus improve the performance of the aero-engine.

[0005] In a first aspect, the present application provides a fan hollow guide vane, the skeleton of the guide vane is a composite material skeleton, the material of the composite material skeleton includes a silicon carbide fiber reinforced titanium-based composite material, the guide vane has a vane leading edge and a vane trailing edge, and the guide vane has a plurality of hollow cavities distributed along the distribution direction from the vane leading edge to the vane trailing edge.

[0006] Compared with the prior art, the skeleton of the guide vane provided by the embodiment of the present application is a composite material skeleton, the material of the composite material skeleton includes a silicon carbide fiber reinforced titanium-based composite material, the silicon carbide fiber reinforced titanium-based composite material is a composite material with silicon carbide fiber as the reinforcing phase and titanium (or titanium alloy) as the matrix, which has high specific strength, high specific stiffness, high creep and fatigue performance. Using it as the skeleton of the guide vane can make the guide vane have lower density, higher strength, higher elastic modulus and better fatigue and creep performance, greatly improving the structural bearing capacity and rigidity of the guide vane, and thus improving the performance of the engine. At the same time, the guide vane has a vane leading edge and a vane trailing edge, and the guide vane has a plurality of hollow cavities distributed along the distribution direction from the vane leading edge to the vane trailing edge. The design of the hollow cavities can greatly reduce the weight of the guide vane, and the hollow cavities can also provide a channel for bearing cooling oil, thereby eliminating the cooling oil pipeline, further reducing the weight of the engine.

[0007] As can be seen from the above, the fan hollow guide vane provided by the embodiment of the present application can greatly reduce the weight of the guide vane while increasing the structural rigidity of the guide vane and improving the reliability, thereby improving the performance of the aero-engine.

[0008] In a second aspect, the present application provides a manufacturing method of the fan hollow guide vane, comprising: using titanium or titanium alloy and continuous monofilament silicon carbide fiber as raw materials, and manufacturing the guide vane of the first aspect by using an additive manufacturing process.

[0009] Compared with the prior art, the manufacturing method of the guide vane provided by the present application has the same beneficial effects as the fan hollow guide vane of the first aspect of the present application, which will not be repeated here.

[0010] In a third aspect, the present application provides an aero-engine, comprising an inner casing, an outer casing and the fan hollow guide vane of the first aspect.

[0011] Compared with the prior art, the aero-engine provided by the present application has the same beneficial effects as the fan hollow guide vane of the first aspect of the present application, which will not be repeated here. BRIEF DESCRIPTION OF DRAWINGS

[0012] The drawings described herein are intended to provide further understanding of the present application, and form a part of the present application. The illustrative embodiments of the present application and their description serve to explain the present application. They do not constitute an inappropriate limitation on the present application. In the drawings:

[0013] Figure 1 A structural schematic view of the fan hollow guide vane framework of the exemplary embodiment of the present application is shown;

[0014] Figure 2 A sectional view of the fan hollow guide vane framework of the exemplary embodiment of the present application is shown;

[0015] Figure 3 A top view of the fan hollow guide vane framework of the exemplary embodiment of the present application is shown;

[0016] Figure 4 A structural schematic view of the fan hollow guide vane with an assembly structure of the exemplary embodiment of the present application is shown;

[0017] Figure 5 A top view of the fan hollow guide vane with an assembly structure of the exemplary embodiment of the present application is shown.

[0018] Reference signs:

[0019] 1 - guide vane framework, 11 - first hollow vane framework, 12 - second hollow vane framework, 13 - third hollow vane framework, 2 - reinforcing rib, 21 - first reinforcing rib, 22 - second reinforcing rib, 100 - vane leading edge, 200 - hollow cavity, 300 - vane trailing edge, 400 - vane basin, 500 - vane back, 600 - assembly structure, 601 - first assembly part, 602 - second assembly part. DETAILED DESCRIPTION

[0020] In order to make the technical problems to be solved by the present application, technical solutions and beneficial effects clearer, the present application will be further described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and not intended to limit the present application.

[0021] It should be noted that when an element is referred to as being "fixed" or "set" on another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or indirectly connected to the other element.

[0022] In addition, the terms "first", "second" are only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise explicitly specified and limited. The meaning of "several" is one or more, unless otherwise explicitly specified and limited.

[0023] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements indicated must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0024] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0025] The guide vane is one of the core components of the aero-engine. However, when the aero-engine is working, the fan inlet guide vane bears very complex load. Therefore, when the weight of the engine guide vane is too large and the rigidity is insufficient, the performance of the aero-engine will be affected.

[0026] Based on the above problems, the exemplary embodiments of the present application provide a fan hollow guide vane and an aero-engine to reduce the weight of the guide vane, improve the stiffness of the guide vane, and thus improve the performance of the aero-engine.

[0027] The framework of the fan hollow guide vane provided by the exemplary embodiments of the present application is a composite material framework, and the composite material framework comprises a silicon carbide fiber reinforced titanium-based composite material, Figure 1 A structural schematic diagram of the framework of the guide vane is shown. As shown in the diagram, Figure 1 The framework of the guide vane has a vane leading edge 100 and a vane trailing edge 300, and the guide vane has a plurality of hollow cavities 200 distributed along a distribution direction from the vane leading edge 100 to the vane trailing edge 300, as well as a vane platform 400 and a vane back 500. It should be understood that the number of the hollow cavities can be three, four, five, six, seven or ten, which is not described herein. The silicon carbide fiber reinforced titanium-based composite material can be manufactured by using an additive manufacturing process.

[0028] The framework of the fan hollow guide vane provided by the exemplary embodiments of the present application is a composite material framework, and the composite material framework comprises a silicon carbide fiber reinforced titanium-based composite material,

[0029] As can be seen from the above, the fan hollow guide vane provided by the exemplary embodiments of the present application can greatly reduce the weight of the guide vane while increasing the structural stiffness of the guide vane and improving the reliability, thereby improving the performance of the aero-engine.

[0030] In an implementable manner, the silicon carbide fiber reinforced titanium-based composite material of the exemplary embodiments of the present application is made of continuous monofilament silicon carbide fibers and titanium (or titanium alloy) in a volume ratio of (20-30):(70-80). That is, the vane leading edge, the vane trailing edge, the vane back and the vane platform are all made of continuous monofilament silicon carbide fibers and titanium (or titanium alloy) in a volume ratio of (20-30):(70-80).

[0031] The titanium alloy can include heat-resistant alloy, high-strength alloy, corrosion-resistant alloy (e.g., titanium-molybdenum alloy, titanium-palladium alloy, etc.), or other alloys, which are not limited herein. In addition, the volume ratio of the single-silicon-carbide fiber to the titanium (or titanium alloy) is controlled within the range of (20-30):(70-80) in the embodiment of the present application, the titanium (or titanium alloy) can be uniformly formed on the continuous single-silicon-carbide fiber, and the single-silicon-carbide fiber can be uniformly distributed in the titanium (or titanium alloy) in a filament form, thereby improving the stiffness of the guide vane and the performance of the engine by using a small amount of single-silicon-carbide fiber.

[0032] In an alternative way, Figure 2 A cross-sectional view of a fan hollow guide vane skeleton of an exemplary embodiment of the present application is shown. As Figure 2 shown, the fiber length direction of the continuous single-silicon-carbide fiber of the embodiment of the present application extends along the span direction of the guide vane. It should be understood that the span direction of the guide vane herein specifically refers to the direction indicated by the arrow in Figure 2 . The fiber length direction of the continuous single-silicon-carbide fiber of the embodiment of the present application extends along the direction indicated by the arrow in Figure 2 . That is, the continuous single-silicon-carbide fiber is a filament fiber, and the continuous single-silicon-carbide fiber extending along the direction indicated by the arrow is present on the composite skeleton regardless of the leading edge, trailing edge, suction surface, or pressure surface of the guide vane. By extending the continuous single-silicon-carbide fiber along the span direction, the mechanical strength of the guide vane can be increased, and the stiffness can be better.

[0033] Exemplarily, the composite skeleton of the embodiment of the present application has a gas passage, and the extending direction of the gas passage is the same as the fiber length direction of the continuous single-silicon-carbide fiber. For convenience of use, the gas passage can be a long slot type hole provided on the wall surface of the hollow cavity 100. At least one hollow cavity can be used to introduce high-temperature gas of a high-pressure compressor, and then the high-temperature gas is discharged from the long slot type hole designed on the wall surface of the hollow cavity 100, which is used to prevent the leading edge of the guide vane from icing during operation. It should be noted that when the long slot type hole is provided on the wall surface of the hollow cavity 100, the long slot type hole should not interfere with the continuous single-silicon-carbide fiber.

[0034] Considering the weight and stiffness of the composite skeleton, Figure 3 A top view of a fan hollow guide vane skeleton of an exemplary embodiment of the present application is shown. As Figure 3 shown, the skeleton of the guide vane includes a hollow vane skeleton 1 and a plurality of reinforcing ribs 2 formed in the hollow vane skeleton 1, the plurality of reinforcing ribs 2 are distributed along the distribution direction from the leading edge to the trailing edge, and the plurality of reinforcing ribs 2 separate the hollow vane skeleton 1 into a plurality of hollow vane skeletons.

[0035] In an example, when the reinforcing ribs are two, the two reinforcing ribs divide the hollow blade skeleton into a first hollow blade skeleton, a second hollow blade skeleton and a third hollow blade skeleton, and the first hollow blade skeleton, the second hollow blade skeleton and the third hollow blade skeleton are distributed along the distribution direction from the blade leading edge to the blade trailing edge.

[0036] That is, as shown in Figure 3 when the reinforcing ribs are two, the two reinforcing ribs can be defined as a first reinforcing rib 21 and a second reinforcing rib 22, and the first reinforcing rib 21 and the second reinforcing rib 22 divide the hollow blade skeleton 1 into a first hollow blade skeleton 11, a second hollow blade skeleton 12 and a third hollow blade skeleton 13. At this time, the blade leading edge is located on the first hollow blade skeleton 11, the blade basin and the blade back are located on the second hollow blade skeleton 12, and the blade trailing edge is located on the third hollow blade skeleton 13. The embodiment of the application can strengthen the structure of the hollow blade skeleton 1 by arranging a plurality of reinforcing ribs 2 in the hollow blade skeleton 1, so that the structure of the hollow blade skeleton 1 is more stable, the mechanical properties are better, the probability of deformation of the guide vane due to a large impact is reduced, and the performance of the engine is better.

[0037] The reinforcing ribs simultaneously divide the hollow cavity of the guide vane into a plurality of hollow cavities. At least one of the hollow cavities can be used to provide a fulcrum lubrication cooling oil passage, and the fulcrum lubrication cooling oil can supply oil to the bearing in the engine, thereby eliminating the cooling oil delivery pipeline, so that the engine is further lightened. That is, the hollow cavity of the guide vane of the embodiment of the application not only makes the engine further lightened, but also provides anti-icing air for the engine, avoiding the situation that the surface of the guide vane is iced during operation.

[0038] For example, the length ratio of the first hollow blade skeleton 11, the second hollow blade skeleton 12 and the third hollow blade skeleton 13 along the direction from the blade leading edge to the blade trailing edge is (2-3):(6-9):(2-3). It should be understood that, as shown in Figure 3 the length ratio here specifically refers to L1:L2:L3. That is, L1:L2:L3=(2-3):(6-9):(2-3). By setting the length ratio of the first hollow blade skeleton 11, the second hollow blade skeleton 12 and the third hollow blade skeleton 13 along the direction from the blade leading edge to the blade trailing edge as (2-3):(6-9):(2-3), the embodiment of the application can make the first hollow blade skeleton 11, the second hollow blade skeleton 12 and the third hollow blade skeleton 13 have a suitable structural stability ratio, so that the impact force borne by the blade trailing edge and the blade leading edge is smaller when impacted, and the structure of the guide vane is more stable.

[0039] In another example, the fan hollow guide vane of the embodiment of the present application further comprises an assembling structure, Figure 4 A structural schematic diagram of the fan hollow guide vane with the assembling structure of the embodiment of the present application is shown, Figure 5 A top view of the fan hollow guide vane with the assembling structure of the embodiment of the present application is shown. As Figure 4 shown and Figure 5 shown, the guide vane of the embodiment of the present application further comprises an assembling structure, which comprises a first assembling part 601 and a second assembling part 602, and the first assembling part 601 and the second assembling part 602 are used for assembling the guide vane.

[0040] In order to facilitate installation, the first assembling part 601 is arranged on the top of the framework of the guide vane, and the second assembling part 602 is arranged under the framework of the guide vane, and the first assembling part 601 and the second assembling part 602 are equivalent to the upper edge plate and the lower edge plate of the framework of the guide vane. The first assembling part 601 can have a matching structure for assembling with the outer casing, and the second assembling part 602 can have a matching structure for assembling with the inner casing, such as a through hole, a bolt or other connecting structure. The first assembling part 601 and the second assembling part 602 can be welded with the framework of the guide vane, or can be an integrated mechanical forming structure, which is not limited here. By arranging the first assembling part 601 and the second assembling part 602 on the top of the framework of the guide vane, the guide vane can be more conveniently connected with the inner and outer casings.

[0041] In an optional manner, the embodiment of the present application further provides a manufacturing method of the fan hollow guide vane, which comprises: taking titanium or titanium alloy and continuous monofilament silicon carbide fiber as raw materials, and using an additive manufacturing process to manufacture the guide vane.

[0042] It should be understood that the additive manufacturing process can adopt a selective laser melting technology. The selective laser melting technology is to melt metal powder to form a molten pool according to a given path with a high-energy beam laser as a heat source, and the molten pool is quickly cooled and solidified to form a deposition track after the heat source moves away. The above process is repeated point by point and layer by layer to complete the accumulation, directly manufacturing a dense and high-performance metal structure from a digital model, reducing the manufacturing steps and material waste, and providing great design freedom.

[0043] In an example, the laser scanning mode of the additive manufacturing process described above is a layer-by-layer laser scanning mode. The embodiment of the present application imports the guide vane model into the SLM forming control software, and performs layering, path planning, support adding and the like under the special three-dimensional layering software. For example, the three-dimensional model is discretized into a plurality of slices according to a certain layering thickness and is sequenced according to the positional relationship, and then reasonable processing paths, overlapping distances, laser scanning speeds and the like are set according to the shape features of each slice layer, and the above information is converted into an additive manufacturing processing program. The forming data is saved in a format (such as STL) recognizable by the SLM device and is imported into the SLM device to prepare for manufacturing the guide vane.

[0044] For example, before the hollow guide vane is manufactured by using the additive manufacturing, the silicon carbide fibers are pre-arranged in the powder bed of the laser selective melting device according to the required arrangement mode, and then powder is laid to prepare.

[0045] For example, the temperature of the molten pool of the embodiment of the present application is less than the melting point of the silicon carbide fibers and greater than the melting point of the titanium matrix, at this time, the morphology of the silicon carbide fibers can not be changed, so that the titanium matrix can be uniformly fused on the silicon carbide fibers, and solidified connection of the titanium matrix and the silicon carbide fibers can be realized.

[0046] As can be seen from the above, the fan hollow guide vane of the embodiment of the present application is produced by using the additive manufacturing technology, and when facing the demand of high customization and small batch, the processing cost can be reduced and the production cycle can be shortened. The laser selective melting forming technology based on powder laying has high forming precision, is suitable for manufacturing very complex parts, and the cooling speed of the molten pool in the forming process is extremely high, so that the grain size of the formed metal parts is small and the mechanical properties are excellent.

[0047] The exemplary embodiment of the present application provides an aero-engine, which comprises the fan hollow guide vane of the exemplary embodiment of the present application, the first assembly part of the guide vane is assembled with the outer casing, and the second assembly part of the guide vane is assembled with the inner casing.

[0048] Although the present application has been described in connection with specific features and embodiments thereof, it is evident that various modifications and combinations can be made thereto without departing from the spirit and scope of the application. Accordingly, the present specification and drawings are to be regarded simply as illustrative of the present application and are to be construed in accordance with the appended claims, rather than in a limiting sense. Obviously, various modifications and changes can be made to the present application by those skilled in the art without departing from the spirit and scope of the present application. Thus, it is intended that the present application cover modifications and variations of this application provided they come within the scope of the appended claims and their equivalents.

[0049] The above merely illustrates the specific embodiments of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A fan hollow guide vane, characterized by, The skeleton of the guide vane is a composite material skeleton, the composite material skeleton comprises a silicon carbide fiber reinforced titanium-based composite material, the guide vane has a vane leading edge and a vane trailing edge, the guide vane has a plurality of hollow cavities distributed along a distribution direction from the vane leading edge to the vane trailing edge, the silicon carbide fiber reinforced titanium-based composite material is made of continuous monofilament silicon carbide fibers and titanium or titanium alloy in a volume ratio of (20-30):(70-80), a fiber length direction of the continuous monofilament silicon carbide fibers extends along a span direction of the guide vane, and the composite material skeleton has a gas passage, a stretching direction of the gas passage is the same as the fiber length direction of the continuous monofilament silicon carbide fibers.

2. The fan hollow guide vane of claim 1, wherein, The skeleton of the guide vane comprises a hollow vane skeleton and a plurality of reinforcing ribs formed in the hollow vane skeleton, the plurality of reinforcing ribs are distributed along a distribution direction from the vane leading edge to the vane trailing edge, and the plurality of reinforcing ribs separate the hollow vane skeleton into a plurality of hollow vane skeletons.

3. The fan hollow guide vane of claim 2, wherein, When the reinforcing ribs are two reinforcing ribs, the two reinforcing ribs separate the hollow vane skeleton into a first hollow vane skeleton, a second hollow vane skeleton and a third hollow vane skeleton, and the first hollow vane skeleton, the second hollow vane skeleton and the third hollow vane skeleton are distributed along the distribution direction from the vane leading edge to the vane trailing edge.

4. The fan hollow guide vane of claim 3, wherein, The length ratio of the first hollow vane skeleton, the second hollow vane skeleton and the third hollow vane skeleton along the direction from the vane leading edge to the vane trailing edge is (2-3):(6-9):(2-3).

5. A method of manufacturing a fan hollow guide vane, characterized by, Comprising: A fan hollow guide vane according to any one of claims 1-4 is manufactured by using an additive manufacturing process with titanium or titanium alloy and continuous monofilament silicon carbide fibers as raw materials.

6. An aeroengine characterised in that, A fan comprising an inner casing, an outer casing and a fan hollow guide vane according to any one of claims 1-4.

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