Support structure, support method, gas turbine engine, and cradle

Abstract

The invention relates to a supporting structure, a supporting method, a gas turbine engine and a bracket. The supporting structure comprises a casing, the casing comprises a casing connecting surface, and a first mounting hole is formed in the casing connecting surface; the support comprises a base part, a first arm part and a second arm part, the first arm part and the second arm part are located on the two sides of the base part respectively, and the first arm part, the second arm part and the base part are arranged in a non-coplanar mode; the base part is provided with a second mounting hole, the first arm part and the second arm part are provided with third mounting holes for connecting accessories, and the bracket is made of a thermosetting composite material; and the connecting piece is connected with the first mounting hole and the second mounting hole, so that the bracket and the casing are directly connected in an abutting manner through the base part and the casing connecting surface.

Description

Technical Field

[0001] The invention relates to a supporting structure, a supporting method, a gas turbine engine and a bracket. Background Art

[0002] There are a large number of mounting brackets in aircraft engines, which are used for the installation and fixation of engine pipelines, accessories and other structures to ensure the normal function. At present, most of the accessory mounting brackets in traditional aircraft engines are made of common metal materials such as steel, high-temperature alloys and titanium alloys, and are formed by multi-pass machining or sheet metal forming + welding. However, on the one hand, the high density of metal materials will lead to a large weight of the final accessory mounting bracket; on the other hand, if the multi-pass machining method is adopted, it will not only lead to a long production cycle, but also cause great waste of raw materials. If the sheet metal forming method is adopted, it is only suitable for some thinner accessory mounting brackets, and the applicability is poor. In addition, some sheet metal brackets need welding treatment, resulting in many processes, cracks are easy to occur at the weld, and the reliability is not high. In addition, metal accessory mounting brackets are usually used in conjunction with other metal structural parts (such as sleeves, etc.), which greatly increases the number of engine components, is not conducive to the improvement of subsequent assembly efficiency and reduces structural reliability. With the requirements of lightweight and integrated design of aircraft engines, new requirements are put forward for the material selection and structural design of accessory mounting brackets in aircraft engines. As an emerging material with high specific strength and low density, high-performance thermosetting composites have attracted widespread attention in the aerospace field and have become an important development direction and trend for the development of composite materials for commercial aircraft engines. In the design process of aircraft engine accessory mounting brackets, high-performance thermosetting composites have shown a series of advantages such as high weight reduction efficiency, integrated design and high reliability, and have become the preferred alternative material for metal accessory mounting brackets. Summary of the invention

[0003] It is an object of the present invention to provide a support structure.

[0004] An object of the present invention is to provide a supporting method.

[0005] An object of the present invention is to provide a gas turbine engine.

[0006] An object of the present invention is to provide a stent.

[0007] A supporting structure according to a first aspect of the present invention comprises a receiver, comprising a receiver connecting surface, wherein a first mounting hole is arranged on the receiver connecting surface; a bracket comprising a base, a first arm and a second arm, wherein the first arm and the second arm are respectively located on both sides of the base, and the first arm and the second arm are arranged non-coplanarly with the base; the base has a second mounting hole, and the first arm and the second arm have a third mounting hole for connecting accessories, and the material of the bracket is a thermosetting composite material; wherein a connecting member connects the first mounting hole and the second mounting hole, so that the bracket and the receiver are directly connected by abutting against each other through the base and the receiver connecting surface.

[0008] In one or more embodiments of the support structure, the matrix of the thermosetting composite material of the bracket includes epoxy resin, bismaleimide resin, and the reinforcement includes glass fiber and carbon fiber.

[0009] In one or more embodiments of the support structure, the matrix of the thermosetting composite material is epoxy resin, and the reinforcement is T300 grade carbon fiber reinforced high-performance prepreg fabric.

[0010] In one or more embodiments of the support structure, the thickness of the base, the first arm and the second arm are consistent, and are 2.5 mm-3.5 mm.

[0011] In one or more embodiments of the supporting structure, the first arm has a first region and a second region extending in a direction from away from to close to the base, the first region and the second region are arranged non-coplanarly, and the first region is provided with a third mounting hole.

[0012] A supporting method according to a second aspect of the present invention adopts the supporting structure as described in the first aspect.

[0013] A gas turbine engine according to a third aspect of the present invention comprises the support structure according to the first aspect.

[0014] A bracket according to a fourth aspect of the present invention is used for the supporting structure as described in the first aspect, the bracket comprises: a base, a first arm and a second arm, the first arm and the second arm are respectively located on both sides of the base, and the first arm and the second arm are arranged non-coplanarly with the base; the base has a second mounting hole, and the first arm and the second arm have a third mounting hole for connecting accessories, the material of the bracket is a thermosetting composite material, and the bracket and the receiver are directly connected by the base and the receiver connecting surface.

[0015] The beneficial effects of using the support structure, support method, gas turbine engine and bracket described above include one or a combination of the following beneficial effects:

[0016] 1. Compared with the original metal accessory mounting bracket, the structural weight is reduced by more than 70%, which is conducive to achieving the goal of lightweighting aircraft engines;

[0017] 2. The optimized integrated design structure greatly reduces the number of components, simplifies the assembly process, and improves structural reliability compared to the original metal mounting bracket + metal sleeve structure;

[0018] 3. The manufacturing process of paving and autoclave molding can effectively avoid the waste of raw materials and shorten the manufacturing cycle. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments. It should be noted that the drawings are only examples and are not drawn to scale, and should not be used as a limitation on the actual scope of protection required by the present invention, wherein:

[0020] Figure 1 It is a schematic diagram of the structure of a bracket of a comparative scheme.

[0021] Figure 2A , Figure 2B It is a structural schematic diagram of a supporting structure and a bracket thereof according to an embodiment.

[0022] Figure 3 It is a schematic diagram of a finite element model of a bracket according to an embodiment.

[0023] Figure 4 1 is a modal analysis vibration shape diagram of a bracket according to an embodiment.

[0024] Figure 5 It is a strain cloud diagram of the frequency response analysis of the bracket of one embodiment.

[0025] Reference numerals:

[0026] 10-Supporting structure

[0027] 2-Stand

[0028] 20-base

[0029] 21-First arm

[0030] 211-First Area

[0031] 212-Second Area

[0032] 22- Second arm

[0033] 221-First Area

[0034] 222-Second Area

[0035] 223-Third Area

[0036] 201-Second mounting hole

[0037] 23-Third mounting hole. DETAILED DESCRIPTION

[0038] The following discloses various different implementation methods or embodiments of the subject technical solution. To simplify the disclosure, specific examples of various elements and arrangements are described below. Of course, these are only examples and are not intended to limit the scope of protection of the present invention.

[0039] In addition, it should be understood that, for example, "one embodiment", "an embodiment", and / or "some embodiments", "one or more embodiments" refer to 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 "some embodiments" or "one or more embodiments" mentioned twice or more in different places in this specification do 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.

[0040] like Figure 1 As shown, the bracket of the existing gas turbine engine is generally formed by a stainless steel alloy accessory mounting bracket formed by sheet metal technology and a sleeve structure prepared by machining for use. When in use, the metal bracket 1000 and two metal sleeves 2000 and 3000 together form the mounting structure of the accessory. The bracket is mainly responsible for the fixing and support of the accessory, and the sleeve is mainly responsible for the fixing of the bracket on the casing. The bracket and the sleeve are both made of AISI321 stainless steel. The bracket includes 7 bolt holes 4-10, of which bolt holes 4-8 are used for the fixing and support of accessories and related structures, and bolt holes 9-10 are used for long bolts to pass through sleeves 2000 and 3000 and connect with the casing connection surface of the casing to fix the metal bracket 1000 to the corresponding position of the casing. The materials of the current commercial aircraft engine system bracket are generally traditional metal materials such as aluminum alloy, steel and titanium alloy. Its disadvantage is that due to the heavy weight of the alloy, the post-processing process such as heat treatment is complicated, and the manufacturing cost is relatively high. The arm of the bracket is used to connect the accessories introduced above.

[0041] The supporting structure of this case is used in the scenario of commercial aircraft engines as an example, but it is not limited to this and can also be used in other types of gas turbine engines, such as marine gas turbines, ground gas turbines, etc.

[0042] like Figure 2A as well as Figure 2BAs shown, the supporting structure 10 includes a receiver and a bracket 2, including a receiver connection surface, and a first mounting hole is arranged on the receiver connection surface. The bracket 2 includes a base 20, a first arm 21 and a second arm 22, the first arm 21 and the second arm 22 are respectively located on both sides of the base 20, and the first arm 21 and the second arm 22 are arranged non-coplanar with the base 20; the base 20 has a second mounting hole 201, and the first arm 21 and the second arm 22 have a third mounting hole 23 for connecting accessories, and the material of the bracket 2 is a thermosetting composite material. Among them, the connecting piece connects the first mounting hole and the second mounting hole 201, so that the bracket 2 and the receiver are directly connected to the receiver connection surface through the base 20. The receiver, accessories and connecting pieces here can all adopt the structure of the prior art, so they are not specifically shown in the figure, and the technicians in the field should be able to understand the corresponding connection relationship and structure.

[0043] Preferably, continue to refer to Figure 2A as well as Figure 2B As shown, in some embodiments, the thickness of the base 20, the first arm 21 and the second arm 22 remain consistent, which is 2.5 mm-3.5 mm.

[0044] Preferably, the first arm portion 21 has a first region 211 and a second region 212 extending from away from the base portion 20, the first region 211 and the second region 212 are arranged non-coplanarly, and the first region 211 is provided with a third mounting hole 23. Similarly, the second arm portion 22 is provided with a first region 221, a second region 222, and a third region 223 extending from away from the base portion 20, the first region 221, the second region 222, and the third region 223 are arranged non-coplanarly, and the first region 221 is provided with a third mounting hole 23.

[0045] The beneficial effect of this is that the parts are tightened at the bend, which does not significantly increase the space occupied compared to the original bracket with sleeve. The thickness of the entire bracket remains consistent, and the bending radius is large, the transition is smooth, and compared to the original metal bracket, the change in the width direction at both ends of the bracket is reduced, the prepreg cutting and laying processes are simplified, and the production efficiency is improved.

[0046] The implementation steps of the embodiment are specifically described below.

[0047] 1. Working condition input: Considering the service environment, service temperature and load conditions of the accessory mounting bracket, the worst load state is selected as the main working condition input.

[0048] 2. Material selection: The selection of thermosetting resin as the matrix is ​​mainly based on the working environment temperature. The available types mainly include epoxy resin, bismaleimide resin, polyimide resin, etc.; the available types of fibers as reinforcements mainly include glass fiber and carbon fiber. Mechanical properties and cost should be taken into account when selecting materials. Referring to the main working condition input, preferably, epoxy resin-based T300 grade carbon fiber reinforced high-performance prepreg fabric is selected. Compared with metal materials commonly used in aircraft engines, such as steel, high-temperature alloys and titanium alloys, the main properties are shown in Table 1.

[0049] Table 1: Common material properties

[0050]

[0051] 3. Structural optimization: Based on the characteristics and requirements of the thermosetting composite material molding process, and in order to meet the needs of integrated design, the number of components is minimized, and the structural design of alternative parts is compared to perform structural design and optimization.

[0052] 4. Strength verification: After design, carry out corresponding finite element calculations on the replaced parts, perform modal analysis and frequency response analysis, and for the composite accessory mounting bracket, the maximum strain should be less than the material allowable value (safety margin greater than 0).

[0053] 5. Molding process: The manufacturing process adopts paving and hot press molding.

[0054] The supporting structure in the embodiment has a service temperature of 274K-400K, and the contact medium is air, which bears the vibration load of the engine and the load transmitted by the accessories. The design optimization principles are as follows: (1) maintain the current installation method and installation interface; (2) reduce the number of components; (3) maintain the current bolt connection hole diameter and position; (4) meet the strength requirements of the parts; (5) reduce weight; (6) reduce the width change of the whole piece to reduce the number of prepreg cutting passes.

[0055] like Figure 2A as well as Figure 2B As shown, in some embodiments, the original accessory mounting bolt holes 4-8 are kept in the same position and size, and the original interface form is maintained; the sleeve structure is eliminated (two parts are reduced) and an integrated bracket structure is adopted, and the original bolt holes 9-10 are moved to the original metal sleeve mounting hole position to ensure that the bracket is installed in the same position of the receiver. The integrated design of the mounting bracket and the two sleeves is realized, which significantly reduces the number of parts and improves assembly.

[0056] Strength calculation

[0057] The finite element model of bracket 2 is as follows: Figure 3 As shown, the first six vibration modes of bracket 2 are as follows Figure 4As shown, the frequency response analysis is performed in three directions, XYZ, respectively. Figure 5 As shown, the maximum tensile, compressive and shear strains at the first six resonant frequencies are all less than their allowable values, meeting the strength requirements. In summary, the composite accessory mounting bracket fully meets the strength requirements.

[0058] Weight comparison: The raw material of the metal accessory mounting bracket and the matching sleeve is AISI321 (AMS5510), and the weight is 0.353kg;

[0059] After changing the material and optimizing the configuration, the material was changed to CYCOM 970 / PWC T300 3K, the weight was 0.079kg, and the actual weight reduction was 77.6%.

[0060] Molding process

[0061] Since the optimized bracket 2 has a relatively simple configuration and uniform thickness, the overall manufacturing process is mold laying and autoclave molding.

[0062] The specific process is: after the prepreg is laid on the mold, the parts are packaged and then put into the autoclave for curing. After curing, demoulding is carried out.

[0063] Finally, the mounting bolt holes are prepared by machining, and the net size of the parts is processed to meet the requirements of the drawings.

[0064] As described above, the beneficial effects of using the support structure, support method, gas turbine engine and bracket described above include one or a combination of the following beneficial effects:

[0065] 1. Compared with the original metal accessory mounting bracket, the structural weight is reduced by more than 70%, which is conducive to achieving the goal of lightweighting aircraft engines;

[0066] 2. The optimized integrated design structure greatly reduces the number of components, simplifies the assembly process, and improves structural reliability compared to the original metal mounting bracket + metal sleeve structure;

[0067] 3. The manufacturing process of paving and autoclave molding can effectively avoid the waste of raw materials and shorten the manufacturing cycle.

[0068] Although the present invention is disclosed as above with the above embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A support structure (10), characterized in that: include: A casing, comprising a casing connecting surface, wherein a first mounting hole is provided on the casing connecting surface; A bracket (2) comprises a base (20), a first arm (21) and a second arm (22), wherein the first arm (21) and the second arm (22) are respectively located on both sides of the base (20), and the first arm (21) and the second arm (22) are arranged non-coplanarly with the base (20); the base (20) has a second mounting hole (201), and the first arm (21) and the second arm (22) have a third mounting hole (23) for connecting accessories, and the bracket (2) is made of a thermosetting composite material; Wherein, the connecting member connects the first mounting hole and the second mounting hole (201), so that the bracket (2) and the casing are directly connected by abutting against each other through the base (20) and the casing connection surface.

2. The support structure (10) according to claim 1, characterized in that The matrix of the thermosetting composite material of the support (2) includes epoxy resin, bismaleimide resin, and polyimide resin, and the reinforcement includes glass fiber and carbon fiber.

3. The support structure (10) according to claim 2, characterized in that The matrix of the thermosetting composite material is epoxy resin, and the reinforcement is T300 grade carbon fiber reinforced high-performance prepreg fabric.

4. The support structure (10) according to claim 1, characterized in that The thickness of the base (20), the first arm (21) and the second arm (22) are consistent, and are 2.5 mm to 3.5 mm.

5. The support structure (10) according to claim 1, characterized in that The first arm portion (21) comprises a first region (211) and a second region (212) extending in a direction from away from the base portion (20) to close to the base portion (20); the first region (211) and the second region (212) are arranged non-coplanarly; and the first region (211) is provided with a third mounting hole (23).

6. A gas turbine engine, characterized in that: It comprises a supporting structure (10) as claimed in any one of claims 1 to 5.

7. A supporting method, characterized in that: A supporting structure (10) as claimed in any one of claims 1 to 5 is used.

8. A bracket (2), characterized in that: A support structure (10) according to any one of claims 1 to 5, wherein the bracket (2) comprises: a base (20), a first arm (21) and a second arm (22), wherein the first arm (21) and the second arm (22) are respectively located on both sides of the base (20), and the first arm (21) and the second arm (22) are arranged non-coplanarly with the base (20); the base (20) has a second mounting hole (201), and the first arm (21) and the second arm (22) have a third mounting hole (23) for connecting accessories, the material of the bracket (2) is a thermosetting composite material, and the bracket (2) and the receiver are directly connected to each other through the base (20) and the receiver connection surface.

9. The support (2) according to claim 8, characterized in that: The thickness of the base (20), the first arm (21) and the second arm (22) are consistent, and are 2.5 mm to 3.5 mm.

10. The support (2) according to claim 8, characterized in that: The first arm portion (21) comprises a first region (211) and a second region (212) extending in a direction from away from the base portion (20) to close to the base portion (20); the first region (211) and the second region (212) are arranged non-coplanarly; and the first region (211) is provided with a third mounting hole (23).

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