A gearbox for an aeroengine

Abstract

The utility model provides a kind of transmission case of aero-engine, the transmission case of aero-engine includes first shell, second shell and transmission assembly, first shell is detachably connected with second shell, they are enclosed and are equipped with multiple bearing seats, transmission assembly is located in inner chamber and includes multiple transmission components, each transmission component includes transmission wheel group and a pair of bearings, second shell is provided with oil inlet and multiple second oil outlet, first shell is equipped with multiple first oil outlet, oil inlet is communicated with second oil outlet and first oil outlet by internal oil channel, to provide lubricating oil to bearing and transmission wheel group, wherein, internal oil channel is located in first shell and second shell.The transmission case of aero-engine of the utility model embodiment has the advantages such as low cost and compact structure.

Description

Technical Field

[0001] This utility model relates to the field of aircraft engine transmission technology, and in particular to an aircraft engine transmission box. Background Technology

[0002] The existing transmission housings of aero engines have many shortcomings in terms of structural design and lubrication system integration. On the one hand, traditional housings mostly adopt an integral structure with complex internal cavities and multiple curved surfaces, resulting in high processing difficulty and manufacturing costs, and are not conducive to the assembly and subsequent maintenance of internal transmission components and bearing housings. On the other hand, in terms of lubrication systems, existing technologies often use external oil pipes for oil supply, which has problems such as messy oil circuit layout and large space occupation. It is difficult to achieve precise and efficient lubrication of the meshing areas of multi-stage transmission gear trains and multiple high-speed bearings, affecting the life and operational reliability of the transmission system. Utility Model Content

[0003] This utility model provides a transmission box for an aero-engine, which solves the defects of the existing transmission box for aero-engines, such as complex shell structure and large space occupied by the lubrication system. It simplifies the shell manufacturing process, reduces manufacturing costs, and achieves a high degree of integration of the lubrication system.

[0004] This utility model provides a transmission box for an aircraft engine, comprising: The first and second housings are detachably connected, forming an inner cavity, and are provided with multiple bearing seats; A transmission assembly is disposed in the inner cavity and includes multiple transmission components, each of which includes a transmission wheel set and a pair of bearings; The second housing is provided with an oil inlet and a plurality of second oil outlets, and the first housing is provided with a plurality of first oil outlets. The oil inlet is connected to the second oil outlets and the first oil outlets through an internal oil passage, so as to provide lubricating oil to the bearing and the transmission wheel assembly. The internal oil passage is provided in the first housing and the second housing.

[0005] In some embodiments, the transmission assembly includes: The first transmission component includes a first transmission wheel set, bearing A and bearing B, wherein bearing A and bearing B are arranged opposite to each other and support the first transmission wheel set; The second transmission component includes a second transmission wheel set, a bearing C and a bearing D, wherein the bearing C and the bearing D are arranged opposite to each other and support the second transmission wheel set; The third transmission component includes a third transmission wheel set, bearing E and bearing F, wherein bearing E and bearing F are arranged opposite to each other and support the third transmission wheel set; The first and second transmission wheel sets mesh to form a primary transmission wheel system, and the second and third transmission wheel sets mesh to form a secondary transmission wheel system.

[0006] In some embodiments, bearing A, bearing C, and bearing E are disposed in the second housing, and bearing B, bearing D, and bearing F are disposed in the first housing; The bearing housing includes bearing housing A, bearing housing B, bearing housing C, bearing housing D, bearing housing E, and bearing housing F, so as to be set up one-to-one with multiple bearings.

[0007] In some embodiments, the plurality of second oil outlets include: The second oil outlet A is used for jet lubrication of the first-stage transmission gear train; The second oil outlet B is located in the bearing housing A to spray lubricate the bearing A; The second oil outlet C is located in the bearing housing C to spray lubricate the bearing C; The second oil outlet D is located in the bearing housing E to spray lubricate the bearing E.

[0008] In some embodiments, the plurality of first oil outlets include: The first oil outlet E is used for spraying lubrication to the meshing inlet of the secondary transmission gear train; The first oil outlet F is used for spraying lubrication to the meshing outlet of the secondary transmission gear train; The first oil outlet G is located in the bearing housing B to spray lubricate the bearing B; The first oil outlet H is located in the bearing housing D to spray lubricate the bearing D; The first oil outlet I is located in the bearing housing F to spray lubricate the bearing F.

[0009] In some embodiments, the internal oil passage includes: Seven second oil passages, four of which are respectively connected to the second oil outlets A to D in a one-to-one correspondence; Five first oil passages are respectively connected to the first oil outlet E to the first oil outlet I; Among them, the other three second oil passages are connected to the five first oil passages.

[0010] In some embodiments, each of the first oil outlets and each of the second oil outlets is provided with a damping orifice at the outlet.

[0011] In some embodiments, the second housing is bolted to the first housing.

[0012] In some embodiments, a sealing layer is provided on the connection surface between the second housing and the first housing.

[0013] In some embodiments, the first housing and / or the second housing are provided with reinforcing ribs.

[0014] The transmission box of the aero-engine of this utility model embodiment firstly ensures the overall structural strength of the housing by means of a detachable connection design between the first housing and the second housing. It also solves the problems of high processing difficulty and high cost caused by complex cavities and curved surfaces in traditional integral housings. Moreover, the first housing and the second housing do not need to be cast, thereby simplifying the manufacturing process and reducing production difficulty and cost.

[0015] Secondly, the separate structure of the first and second shells avoids the design compromises of an integrated shell, which would otherwise have to increase wall thickness and size due to casting or processing limitations (such as difficulty in demolding or inability of cutting tools to enter), making the transmission box of the aero-engine more compact.

[0016] Furthermore, by placing the internal oil passages on the first or second housing, the lubrication system is highly integrated, avoiding the space occupation, leakage risks, and assembly complexity caused by external oil pipes. This makes the overall structure more compact and is conducive to the engine's lightweight design and optimized space layout.

[0017] Therefore, the transmission box of the aero-engine in this embodiment of the present invention has the advantages of low cost and compact structure. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the transmission box of the aero-engine provided by this utility model.

[0020] Figure 2 yes Figure 1 A schematic diagram of the cross-sectional structure at point AA.

[0021] Figure 3 This is a schematic diagram of the structure of the second housing of the transmission box of the aero-engine provided by this utility model.

[0022] Figure 4 This is a schematic diagram of the structure of the first housing of the transmission box of the aero-engine provided by this utility model.

[0023] Figure label: 100. Transmission box of aircraft engine; 1. First housing; 2. Second housing; 3. Inner cavity; 4. Bearing housing; 41. Bearing housing A; 42. Bearing housing B; 43. Bearing housing C; 44. Bearing housing D; 45. Bearing housing E; 46. Bearing housing F; 5. Internal oil passages; 6. Oil inlet; 7. Second oil outlet; 71. Second oil outlet A; 72. Second oil outlet B; 73. Second oil outlet C; 74. Second oil outlet D; 8. First oil outlet; 81. First oil outlet E; 82. First oil outlet F; 83. First oil outlet G; 84. First oil outlet H; 85. First oil outlet I; 9. Sealing layer; 10. Bolts. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0025] like Figures 1 to 4 As shown, the transmission housing 100 of the aircraft engine in this embodiment of the present invention includes a first housing 1 and a second housing 2 that are detachably connected, and a transmission assembly. The first housing 1 and the second housing 2 form an inner cavity 3, and a plurality of bearing seats 4 are provided on the first housing 1 and the second housing 2.

[0026] The transmission assembly is located in the inner cavity 3 and includes multiple transmission components, each of which includes a transmission wheel set and a pair of bearings.

[0027] The second housing 2 is provided with an oil inlet 6 and multiple second oil outlets 7. The first housing 1 is provided with multiple first oil outlets 8. The oil inlet 6 is connected to the second oil outlets 7 and the first oil outlets 8 through an internal oil passage 5, so as to provide lubricating oil to the bearings and transmission wheel assembly. The internal oil passage 5 is located in the first housing 1 and the second housing 2.

[0028] The transmission housing 100 of the aircraft engine of this embodiment of the present invention is formed by a first housing 1 and a second housing 2 that are detachably connected, forming an inner cavity 3 and providing multiple bearing seats 4, thereby integrating the transmission assembly into the inner cavity 3. The transmission assembly includes multiple transmission components, each component including a transmission wheel set and a pair of bearings.

[0029] An oil inlet 6 and multiple second oil outlets 7 are provided on the second housing 2, and multiple first oil outlets 8 are provided on the first housing 1. A portion of the second oil outlets 7 and a portion of the first oil outlets 8 are located at each of the bearing seats 4 to provide lubricating oil to the corresponding bearings; another portion of the second oil outlets 7 and another portion of the first oil outlets 8 correspond to multiple of the transmission wheel sets to provide lubricating oil to the corresponding transmission wheel sets. This ensures that the key friction pairs of the bearings and transmission wheel sets (such as the bearing rolling contact surface and gear meshing area) can receive sufficient and direct lubrication under high-speed operation, significantly reducing wear and heat generation risks and improving transmission efficiency.

[0030] Existing aero-engine casings have several shortcomings in terms of structural design and lubrication system integration. On the one hand, traditional casings often adopt an integral structure with complex internal cavities and numerous curved surfaces, resulting in high machining difficulty and manufacturing costs, and hindering the assembly and subsequent maintenance of internal transmission components and bearing housings. On the other hand, in terms of lubrication systems, existing technologies often use external oil pipes for oil supply, which leads to problems such as chaotic oil circuit layout and large space occupation. This makes it difficult to achieve precise and efficient lubrication of the meshing areas of multi-stage transmission gear trains and multiple high-speed bearings, affecting the lifespan and operational reliability of the transmission system.

[0031] The transmission box 100 of the aircraft engine in this embodiment of the utility model firstly ensures the overall structural strength of the housing by means of a detachable connection design between the first housing 1 and the second housing 2. It also solves the problems of high processing difficulty and high cost caused by complex cavities and curved surfaces in traditional integral housings. Moreover, the first housing 1 and the second housing 2 do not need to be cast, thereby simplifying the manufacturing process and reducing production difficulty and cost.

[0032] Secondly, the separate structure of the first housing 1 and the second housing 2 avoids the design compromises of increasing wall thickness and enlarging size that must be made by the integrated housing due to casting or processing limitations (such as difficulty in demolding and inability of cutting tools to enter), making the structure of the transmission box 100 of the aero-engine more compact.

[0033] Furthermore, by placing the internal oil passage 5 on the first housing 1 or the second housing 2, the lubrication system is highly integrated, avoiding the space occupation, leakage risk and assembly complexity caused by external oil pipes, making the overall structure more compact, which is conducive to the lightweighting of the engine and the optimization of space layout.

[0034] Therefore, the transmission box 100 of the aircraft engine in this embodiment of the present invention has the advantages of low cost and compact structure.

[0035] In some embodiments, the transmission assembly includes a first transmission component, a second transmission component, and a third transmission component.

[0036] The first transmission component includes a first transmission wheel set, bearing A and bearing B, with bearing A and bearing B arranged opposite to each other and supporting the first transmission wheel set.

[0037] The second transmission component includes a second transmission wheel set, bearing C and bearing D, with bearing C and bearing D arranged opposite to each other and supporting the second transmission wheel set.

[0038] The third transmission component includes a third transmission wheel set, bearing E and bearing F, with bearing E and bearing F arranged opposite to each other and supporting the third transmission wheel set.

[0039] The first and second transmission wheel sets mesh to form a primary transmission wheel system, and the second and third transmission wheel sets mesh to form a secondary transmission wheel system.

[0040] Bearings A and B are respectively mounted on corresponding bearing seats 4 in the second housing 2 and the first housing 1, jointly supporting the rotation of the first transmission wheel assembly. Bearing C is located in the second housing 2 and bearing D is located in the first housing 1, used to support the second transmission wheel assembly. Bearing E is located in the second housing 2 and bearing F is located in the first housing 1, used to support the third transmission wheel assembly.

[0041] The first and second transmission wheel sets mesh with each other to form a primary transmission gear system, realizing the initial transmission of speed and torque. The second and third transmission wheel sets mesh with each other to form a secondary transmission gear system, completing further transmission ratio adjustment. The inner second housing 2 supports each transmission component in a coordinated manner, ensuring the stability of meshing of each level of the gear system and meeting the transmission accuracy and reliability requirements of the transmission box 100 of the aero-engine.

[0042] In some embodiments, bearings A, C, and E are disposed in the second housing 2, and bearings B, D, and F are disposed in the first housing 1.

[0043] The bearing housing 4 includes bearing housing A41, bearing housing B42, bearing housing C43, bearing housing D44, bearing housing E45, and bearing housing F46, so that they can be set up one-to-one with multiple bearings.

[0044] Bearings A, C, and E are mounted on the second housing 2 and are supported and positioned by bearing seats A41, C43, and E45 located inside the second housing 2. Bearings B, D, and F are mounted on the first housing 1 and are supported by bearing seats B42, D44, and F46 located inside the first housing 1. Each bearing seat 4 is used to install and fix the corresponding bearing.

[0045] Optionally, the coaxiality of bearing housing A41 and bearing housing B42, the coaxiality of bearing housing C43 and bearing housing D44, and the coaxiality of bearing housing E45 and bearing housing F46 are required to meet the requirements of high-speed transmission systems for transmission accuracy and lifespan.

[0046] In some embodiments, the plurality of second oil outlets 7 include a second oil outlet A71, a second oil outlet B72, a second oil outlet C73, and a second oil outlet D74.

[0047] The second oil outlet, A71, is used for jet lubrication of the primary drive train.

[0048] The second oil outlet B72 is located in bearing housing A41 to spray lubricate bearing A.

[0049] The second oil outlet C73 is located in the bearing housing C43 to spray lubricate the bearing C.

[0050] The second oil outlet D74 is located in bearing housing E45 to spray lubricate bearing E.

[0051] The second oil outlet A71 is used to spray lubricating oil into the meshing joint of the primary transmission gear train, achieving effective lubrication and cooling of the gear meshing area. The second oil outlet B72 is located at bearing housing A41 and is used to spray lubricating oil onto bearing A for lubrication. The second oil outlet C73 is located at bearing housing C43 and is used to lubricate bearing C. The second oil outlet D74 is located at bearing housing E45 and is used to lubricate bearing E.

[0052] All the second oil outlets 7 are connected to the oil inlet 6 through the integrated oil passage inside the second housing 2. After the lubricating oil enters from the oil inlet 6, it is distributed to each of the second oil outlets 7 inside the second housing 2, ensuring that the primary transmission gear train and the bearings A, C and E on the second housing 2 are accurately and continuously lubricated.

[0053] In some embodiments, the plurality of first oil outlets 8 include first oil outlet E81, first oil outlet F82, first oil outlet G83, first oil outlet H84 and first oil outlet I85.

[0054] The first oil outlet, E81, is used for the engagement port of the secondary transmission gear train via jet lubrication.

[0055] The first oil outlet F82 is used for the meshing outlet of the secondary transmission gear train for jet lubrication.

[0056] The first oil outlet G83 is located in bearing housing B42 to spray lubricate bearing B.

[0057] The first oil outlet H84 is located in bearing housing D44 to spray lubricate bearing D.

[0058] The first oil outlet I85 is located in bearing housing F46 to spray lubricate bearing F.

[0059] The first oil outlet E81 is used to spray lubricating oil into the meshing inlet of the secondary transmission gear train. The first oil outlet F82 is used to spray lubricating oil into the meshing outlet of the secondary transmission gear train, so as to achieve sufficient lubrication and cooling throughout the gear meshing process. The first oil outlet G83 is located at bearing housing B42 and is used to spray lubricating oil into bearing B for lubrication. The first oil outlet H84 is located at bearing housing D44 and is used to lubricate bearing D. The first oil outlet I85 is located at bearing housing F46 and is used to lubricate bearing F.

[0060] The transmission box 100 of the aircraft engine in this embodiment of the present invention achieves comprehensive and precise lubrication of the secondary transmission gear train and bearings B, D and F by setting multiple first oil outlets 8.

[0061] In some embodiments, the internal oil passage 5 includes: There are seven second oil passages, four of which are connected to the second oil outlets A71 to D74 respectively.

[0062] The first oil passage has five sections, which are connected to the first oil outlet E81 to the first oil outlet I85 respectively.

[0063] Among them, the other three second oil passages are connected to the five first oil passages.

[0064] The internal oil passage 5 includes seven second oil passages located in the second housing 2 and five first oil passages located in the first housing 1. Four of the second oil passages are respectively connected to the second oil outlet A71, the second oil outlet B72, the second oil outlet C73, and the second oil outlet D74, and are used to directly deliver lubricating oil to the meshing inlet of the first-stage transmission gear train and to bearings A, C, and E for spray lubrication.

[0065] The other three second oil passages serve as oil supply channels to the first housing 1, and are connected to the five first oil passages inside the first housing 1. After the lubricating oil is introduced into the first housing 1, it is delivered to the first oil outlet E81, the first oil outlet F82, the first oil outlet G83, the first oil outlet H84 and the first oil outlet I85 through these five first oil passages, so as to achieve lubrication of the meshing inlet and meshing outlet of the secondary transmission gear train as well as bearings B, bearing D and bearing F.

[0066] The internal oil passage 5 of the transmission box 100 of the aircraft engine in this embodiment is arranged so that the lubricating oil can be diverted after entering from the oil inlet 6 and distributed to each transmission component and each bearing, ensuring the effectiveness and stability of the lubrication system at high speed. At the same time, the internal oil passage 5 is integrated on the first housing 1 and the second housing 2, eliminating the need for external pipeline connections, making the structure compact and improving space utilization.

[0067] In some embodiments, each first oil outlet 8 and each second oil outlet 7 is provided with a damping orifice at the outlet.

[0068] The damping orifice, as a throttling structure, can effectively increase the pressure and flow rate of the lubricating oil during injection, making the lubricating oil form a concentrated and stable fluid, so that the lubricating oil can be sprayed to the meshing area of ​​the primary and secondary transmission gear trains and each bearing, thereby enhancing the cooling and lubrication effect on high-speed rotating components.

[0069] In some embodiments, the second housing 2 is connected to the first housing 1 by bolts 10.

[0070] The second housing 2 is connected to the first housing 1 by bolts 10. This connection method facilitates the assembly and disassembly of the housing, and is beneficial for the installation, debugging and subsequent maintenance of the internal transmission components. At the same time, it ensures the structural strength and connection reliability of the mating surface of the inner second housing 2.

[0071] In some embodiments, a sealing layer 9 is provided on the connection surface between the second housing 2 and the first housing 1.

[0072] The sealing layer 9 is formed by applying sealant to the connecting surface. It can effectively fill the tiny gaps at the connection of the inner second housing 2, prevent lubricating oil from leaking out of the housing, ensure the sealing reliability of the integrated oil passage system, and prevent external contaminants from entering the housing and affecting the normal operation of the transmission components.

[0073] In some embodiments, the first housing 1 and / or the second housing 2 are provided with reinforcing ribs.

[0074] The first housing 1 or the second housing 2 is provided with reinforcing ribs, or both the first housing 1 and the second housing 2 are provided with reinforcing ribs. The reinforcing ribs are located at stress concentration points of the first housing 1 or the second housing 2, which can effectively improve the overall structural strength and rigidity of the first housing 1 or the second housing 2, enhance its resistance to deformation and load-bearing capacity, thereby ensuring the stability of the housing structure under high engine speed operation conditions and avoiding fatigue damage caused by vibration or excessive load.

[0075] It should be noted that the second oil outlet B72, the second oil outlet C73, the second oil outlet D74, the first oil outlet G83, the first oil outlet H84, and the first oil outlet I85 are all located on the corresponding bearing housing 4. Their positions on the bearing housing 4 are not limited to those shown in the attached figure. They can be arbitrarily set along the circumference of the bearing housing 4, except for the lowest point of the bearing housing 4.

[0076] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A transmission case for an aircraft engine, characterized in that, include: The first housing (1) and the second housing (2) are detachably connected, forming an inner cavity (3), and are provided with multiple bearing seats (4). The transmission assembly is located in the inner cavity (3) and includes multiple transmission components, each of which includes a transmission wheel set and a pair of bearings; The second housing (2) is provided with an oil inlet (6) and a plurality of second oil outlets (7), and the first housing (1) is provided with a plurality of first oil outlets (8). The oil inlet (6) is connected to the second oil outlets (7) and the first oil outlets (8) through an internal oil passage (5) so as to provide lubricating oil to the bearing and the transmission wheel assembly. The internal oil passage (5) is located between the first housing (1) and the second housing (2).

2. The transmission case of the aero-engine according to claim 1, characterized in that, The transmission assembly includes: The first transmission component includes a first transmission wheel set, bearing A and bearing B, wherein bearing A and bearing B are arranged opposite to each other and support the first transmission wheel set; The second transmission component includes a second transmission wheel set, a bearing C and a bearing D, wherein the bearing C and the bearing D are arranged opposite to each other and support the second transmission wheel set; The third transmission component includes a third transmission wheel set, bearing E and bearing F, wherein bearing E and bearing F are arranged opposite to each other and support the third transmission wheel set; The first and second transmission wheel sets mesh to form a primary transmission wheel system, and the second and third transmission wheel sets mesh to form a secondary transmission wheel system.

3. The transmission case of the aero-engine according to claim 2, characterized in that, The bearings A, C, and E are disposed in the second housing (2), and the bearings B, D, and F are disposed in the first housing (1). The bearing housing (4) includes bearing housing A (41), bearing housing B (42), bearing housing C (43), bearing housing D (44), bearing housing E (45), and bearing housing F (46), so as to be set in a one-to-one correspondence with multiple bearings.

4. The transmission case of the aero-engine according to claim 3, characterized in that, The plurality of second oil outlets (7) include: The second oil outlet A (71) is used for jet lubrication of the first-stage transmission gear train; The second oil outlet B (72) is provided in the bearing housing A (41) to spray lubricate the bearing A; The second oil outlet C (73) is provided in the bearing housing C (43) to spray lubricate the bearing C; The second oil outlet D (74) is located in the bearing housing E (45) to spray lubricate the bearing E.

5. The transmission case of the aero-engine according to claim 4, characterized in that, The plurality of first oil outlets (8) include: The first oil outlet E (81) is used for spraying lubrication of the meshing inlet of the secondary transmission gear train; The first oil outlet F (82) is used for spraying lubrication of the meshing outlet of the secondary transmission gear train; The first oil outlet G (83) is provided in the bearing housing B (42) to spray lubricate the bearing B; The first oil outlet H (84) is provided in the bearing housing D (44) to spray lubricate the bearing D; The first oil outlet I (85) is located in the bearing housing F (46) to spray lubricate the bearing F.

6. The transmission case of an aero-engine according to claim 5, characterized in that, The internal oil passage (5) includes: Seven second oil passages, four of which are connected one-to-one with the second oil outlet A (71) to the second oil outlet D (74); Five first oil passages are respectively connected to the first oil outlet E (81) to the first oil outlet I (85); Among them, the other three second oil passages are connected to the five first oil passages.

7. The transmission case of the aero-engine according to claim 1, characterized in that, Each of the first oil outlet (8) and each of the second oil outlets (7) is provided with a damping orifice at the outlet.

8. The transmission case of the aero-engine according to claim 1, characterized in that, The second housing (2) is connected to the first housing (1) by bolts (10).

9. The transmission case of the aero-engine according to claim 1, characterized in that, A sealing layer (9) is provided on the connection surface between the second housing (2) and the first housing (1).

10. The transmission case of the aero-engine according to claim 1, characterized in that, The first housing (1) and / or the second housing (2) are provided with reinforcing ribs.

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