Mechanical transmission device for rocking-turn of high-pressure rotor of aviation turbine engine

Abstract

The utility model provides a mechanical transmission device for rocking-turn of a high-pressure rotor of an aviation turbine engine, which is characterized in that a first shaft section of an input shaft is connected with the inner end face of an input shaft shell through a first bearing, and a second shaft section of the input shaft is connected with the inner end face of the input shaft shell through a second bearing; the third shaft section is connected with a first transmission gear; a fourth shaft section of the output shaft is connected with the inner end face of the output shaft shell through a third bearing, a fifth shaft section of the output shaft is connected with the inner end face of the output shaft shell through a fourth bearing, and a sixth shaft section of the output shaft is connected with a second transmission gear. The first transmission gear and the second transmission gear are meshed to realize vertical constant-speed transmission between the input shaft and the output shaft; the first butt joint part of the input shaft shell is connected with an external driving device; and the second butt joint part of the output shaft shell is connected with a rocking-turn port of an external aero-engine. The auxiliary driving device solves the problem that the auxiliary driving device is difficult to install when the aero-turbine engine borescope is explored, and is simple in structure.

Description

TECHNICAL FIELD

[0001] The utility model relates to aviation turbine engine detection technical field, concretely relates to a kind of mechanical transmission device for aviation turbine engine high-pressure rotor swing. BACKGROUND

[0002] When aviation turbine engine (for example CFM56-7B model) swings high-pressure rotor through special swing port, the sensor nearby and the starter gas source pipe in front will form obstruction, resulting in that auxiliary driving equipment cannot be directly installed when hole-probing work is carried out on engine, and then high-pressure rotor cannot be driven by auxiliary driving equipment, to improve the efficiency and precision of rotating rotor. And since the uniformity and precision requirement of high-pressure rotor rotation is extremely high when aviation engine is hole-probed, manpower swing cannot meet these requirements.

[0003] One of the existing ways is to set universal joint for transmission, but this way is generally applied in low-pressure rotor swing, occupies larger volume, and the structure is also more complex. UTILITY MODEL CONTENT

[0004] The utility model aims at providing a kind of mechanical transmission device for aviation turbine engine high-pressure rotor swing, which is simple in structure and small in occupied volume.

[0005] In order to realize the above-mentioned purpose, the utility model provides a kind of mechanical transmission device for aviation turbine engine high-pressure rotor swing, wherein, it includes: input shaft, input shaft shell, connecting shell, output shaft, output shaft shell, first transmission gear, second transmission gear, first bearing, second bearing, third bearing, fourth bearing;Input shaft shell, connecting shell, output shaft shell form accommodating space between them;Input shaft is sequentially provided with first shaft section, second shaft section, third shaft section along vertical direction, first shaft section is connected between the inner end surface of input shaft shell through first bearing, second shaft section is connected between the inner end surface of input shaft shell through second bearing, and third shaft section is arranged in accommodating space and is connected with first transmission gear;Output shaft is sequentially provided with fourth shaft section, fifth shaft section, sixth shaft section along horizontal direction, fourth shaft section is connected between the inner end surface of output shaft shell through third bearing, fifth shaft section is connected between the inner end surface of output shaft shell through fourth bearing, and sixth shaft section is arranged in accommodating space and is connected with second transmission gear;First transmission gear and second transmission gear are engaged to realize vertical constant-speed transmission between input shaft and output shaft;Input shaft shell includes first butt joint, and first butt joint is arranged around first shaft section, and first butt joint is used to connect with external driving device;Output shaft shell includes second butt joint, and second butt joint is arranged around fourth shaft section, and second butt joint is used to connect with swing port of external aviation engine.

[0006] From the above scheme can be seen, the utility model discloses a first transmission gear is arranged on the input shaft, a second transmission gear is arranged on the output shaft, and the perpendicular constant velocity transmission between the input shaft and the output shaft is realized through the meshing of the first transmission gear and the second transmission gear, through the utility model, the external auxiliary driving device can be conveniently connected at the first butt joint portion of the input shaft shell, and the aviation turbine engine needing to be subjected to hole exploration work is connected at the second butt joint portion of the output shaft shell, so that the auxiliary driving device drives the input shaft, the high-pressure rotor of the aviation turbine engine is driven by the output shaft after the angle conversion of the first transmission gear and the second transmission gear, the utility model solves the problem that the sensor near the aviation turbine engine and the starter gas source pipe in front form an obstruction and the auxiliary driving device cannot be installed when the aviation turbine engine is rocked through the special rocking opening, and the utility model has small occupied volume and simple structure.

[0007] Further, the mechanical transmission device further comprises a first baffle, a first fixing screw, a second baffle and a second fixing screw.

[0008] Therefore, the first transmission gear is limited by the first baffle, and the first baffle is fixed by the first fixing screw to prevent the first transmission gear from sliding off the input shaft.

[0009] Further, the first transmission gear and the second transmission gear are a pair of arc-tooth constant-diameter bevel gears.

[0010] Therefore, stable meshing and constant velocity transmission can be realized.

[0011] Further, the first bearing and the third bearing are needle bearings, and the second bearing and the fourth bearing are deep groove ball bearings.

[0012] Therefore, the needle bearings are arranged close to the external auxiliary driving device to provide high radial rigidity and ensure transmission accuracy, and the deep groove ball bearings are arranged close to the transmission gears to allow axial fine adjustment and improve stability.

[0013] Further, a first gasket is arranged between the second bearing and the first transmission gear, and a second gasket is arranged between the fourth bearing and the second transmission gear.

[0014] Therefore, the positions of the first transmission gear and the second transmission gear can be adjusted by adjusting the thickness of the gaskets.

[0015] Further, the third shaft segment is connected with the first transmission gear by a flat key, and the sixth shaft segment is connected with the second transmission gear by a flat key.

[0016] Therefore, the flat key prevents the gear from sliding relative to the input shaft, and has the advantages of simple structure, reliable transmission, and low cost.

[0017] Further, a first bearing mounting portion is formed in the input shaft housing relative to the inner end face of the second shaft segment, and the second bearing is arranged in the first bearing mounting portion; and a second bearing mounting portion is formed in the output shaft housing relative to the inner end face of the fifth shaft segment, and the fourth bearing is arranged in the second bearing mounting portion.

[0018] Therefore, the outer ring of the bearing is fixed to the bearing mounting seat of the input shaft housing by a tight fit.

[0019] Further, the first connecting portion is provided with a plurality of first mounting screw holes; and the first shaft segment is provided with a shaft hole.

[0020] Therefore, the first mounting screw hole facilitates the mounting of an external auxiliary driving device, and the shaft hole facilitates the connection of the external auxiliary driving device to the input shaft to drive the input shaft to rotate.

[0021] Further, the output shaft is sequentially provided with the output shaft segment, the fourth shaft segment, the fifth shaft segment, and the sixth shaft segment along the horizontal direction.

[0022] Therefore, the output shaft segment matched with the rotating port of the external turbine engine is arranged, so as to facilitate the connection with the external turbine engine.

[0023] Further, the second connecting portion is matched with the plug cover of the CFM56-7B type turbine engine, and the second connecting portion is provided with a plurality of second mounting screw holes, and the positions of the second mounting screw holes are matched with the positions of the mounting screw holes of the plug cover of the CFM56-7B type turbine engine.

[0024] Therefore, the auxiliary driving device can be applied to the CFM56-7B type turbine engine, and the problem that the sensors near the turbine engine and the air source pipe of the starter in front of the turbine engine form an obstruction to prevent the auxiliary driving device from being installed can be solved. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 is a structural schematic view of an embodiment of the present application.

[0026] Figure 2 is a sectional view of an embodiment of the present application.

[0027] Figure 3 is a structural schematic view when the connecting housing is taken out in an embodiment of the present application.

[0028] Figure 4 is Figure 3 The schematic view after being enlarged at A in the figure.

[0029] The utility model will be further described below in combination with the drawings and embodiments. DETAILED DESCRIPTION

[0030] The utility model discloses a mechanical transmission device for aero turbine engine high pressure rotor swing, input shaft is driven by external driving device, and the angle is converted after a pair of transmission gear, and is exported by output shaft, and then can drive the rotation of the external aero engine high pressure rotor.

[0031] The technical solutions in the embodiments of the utility model will be clearly and completely described below in combination with the drawings in the embodiments of the utility model.

[0032] Referring to Figures 1 to 4 The utility model discloses a mechanical transmission device for aero turbine engine high pressure rotor swing, input shaft housing 11, input shaft 12, first bearing 13, second bearing 14, first transmission gear 15, first baffle 16, first fixed screw 17, first gasket 18, connecting housing 21, output shaft housing 31, output shaft 32, third bearing 33, fourth bearing 34, second transmission gear 35, second baffle 36, second fixed screw 37, second gasket 38 are included.

[0033] The accommodating space 901 is formed between input shaft housing 11, connecting housing 21, output shaft housing 31.

[0034] The input shaft 12 is sequentially provided with first shaft section 121, second shaft section 122, third shaft section 123 along the vertical direction.Output shaft 32 is sequentially provided with output shaft section 342, fourth shaft section 321, fifth shaft section 322, sixth shaft section 323 along the horizontal direction.The shaft hole 1211 is arranged in the first shaft section 121.In the embodiment, referring to Figure 2 Along the vertical direction, that is, along the direction of y-axis arrow, along the horizontal direction, that is, along the direction of x-axis arrow in the figure.

[0035] The first shaft section 121 is connected with the inner end surface 111 of the input shaft housing through the first bearing 13, the second shaft section 122 is connected with the inner end surface 111 of the input shaft housing through the second bearing 14, and the third shaft section 123 is arranged in the accommodating space 901 and is connected with the first transmission gear 15.

[0036] The first bearing mounting portion 1211 is formed in the input shaft housing 11 relative to the inner end surface of the second shaft section 122, and the second bearing 14 is arranged in the first bearing mounting portion 1211, specifically, the second bearing 14 is fixed with the first bearing mounting portion 1211 through the tight fit.

[0037] The fourth shaft segment 321 is connected to the inner end surface 311 of the output shaft housing through the third bearing 33, the fifth shaft segment 322 is connected to the inner end surface 311 of the output shaft housing through the fourth bearing 34, and the sixth shaft segment 323 is arranged in the accommodating space 901 and connected to the second transmission gear 35.

[0038] The second bearing mounting portion 3111 is formed in the output shaft housing 31 opposite to the inner end surface of the fifth shaft segment 322, and the fourth bearing 34 is arranged in the second bearing mounting portion 3111, specifically, the fourth bearing 34 is fixed in the second bearing mounting portion 3211 through a tight fit.

[0039] In the embodiment, the first bearing 13 and the third bearing 33 are preferably needle bearings, and the second bearing 14 and the fourth bearing 34 are deep groove ball bearings. In other embodiments, a person skilled in the art can select other types of bearings according to actual needs.

[0040] The first transmission gear 15 and the second transmission gear 35 are engaged in the accommodating space 901, and the vertical constant speed transmission between the input shaft 12 and the output shaft 32 is realized through the cooperation of the first transmission gear 15 and the second transmission gear 35.

[0041] In the embodiment, the first transmission gear 15 and the second transmission gear 13 are preferably a pair of arc-tooth constant-diameter bevel gears. In other embodiments, a person skilled in the art can select other types of gears according to actual needs, for example, a pair of straight-tooth constant-diameter bevel gears.

[0042] The third shaft segment 123 is connected to the first transmission gear 15 through a flat key, and the sixth shaft segment 323 is connected to the second transmission gear 35 through a flat key. For example, a flat key (not shown in the figure) can be arranged on the sixth shaft segment, and a working groove 351 matched with the flat key is formed on the second transmission gear, so that when the first transmission gear drives the second transmission gear to rotate, the flat key on the sixth shaft segment is acted on by the working groove 35, and then the flat key drives the output shaft to rotate.

[0043] The first baffle 16 is close to one end of the first transmission gear 155 away from the input shaft 12, and the first fixing screw 17 passes through the first baffle 16 into the input shaft 12 to fix the first transmission gear 155 on the input shaft.

[0044] The second baffle 36 is close to one end of the second transmission gear 35 away from the output shaft 32, and the second fixing screw 37 passes through the second baffle 36 into the output shaft 32 to fix the second transmission gear 35 on the output shaft 32.

[0045] The first gasket 18 is arranged between the second bearing 14 and the first transmission gear 15, and the installation position of the first transmission gear 15 is adjusted by the thickness of the first gasket 18. The second gasket 38 is arranged between the fourth bearing 34 and the second transmission gear 35, and the installation position of the second transmission gear 35 is adjusted by the thickness of the second gasket 38.

[0046] The input shaft housing 11 further comprises a first connecting part 112, which is arranged around the first shaft segment 121, and is used to connect with an external driving device. A second connecting part 312 is arranged around the fourth shaft segment 321, and is used to connect with a swing port of an external aero turbine engine.

[0047] The first connecting part 112 is provided with two first mounting screw holes 1121, which are used to fix the external driving device to the first connecting part 112 by two screws.

[0048] In this embodiment, the shape of the second connecting part 312 matches the plug cover of the CFM56-7B type aero turbine engine, and the second connecting part 312 is provided with four second mounting screw holes 3121. The second connecting part 312 is fixed to the external turbine engine by four screws which match the mounting screw holes of the plug cover of the CFM56-7B type aero turbine engine. The output shaft segment 324 of the output shaft is square, and matches the swing port of the CFM56-7B type aero turbine engine. In different embodiments, the shape of the second connecting part 312 can be adjusted according to different aero turbine engines.

[0049] In operation, the first connecting part 112 is connected to an external driving device, and the second connecting part 312 is connected to an external turbine engine. The external driving device drives the input shaft 12 to rotate by inserting into the shaft hole 1211, and the input shaft 12 drives the first transmission gear 15 to rotate, and the second transmission gear 16 rotates at the same speed as the first transmission gear 15, and the output shaft 32 rotates at the same speed as the second transmission gear 16, and the output shaft segment 324 of the input shaft which enters the swing port of the high pressure rotor of the external turbine engine drives the high pressure rotor to rotate, and then subsequent hole exploration work is performed.

[0050] The utility model discloses can conveniently connect the outside auxiliary drive device at the first docking portion of input shaft shell, connect the aviation turbine engine that the outside needs to carry out the hole to explore work at the second docking portion of output shaft shell to drive input shaft by auxiliary drive device, and the high pressure rotor work of output shaft drives the aviation turbine engine after the angle conversion of first transmission gear and second transmission gear, the utility model discloses solve the problem that the sensor of aviation turbine engine and the starter air supply pipe of preceding when passing through the special swing -turning mouth swing -turning high pressure rotor, cannot form the obstruction and install auxiliary drive device, and the volume is small, and simple structure is occupied.

[0051] Finally, it needs to emphasize that the above-mentioned is only the preferred embodiment of the utility model, and is not used to limit the utility model, for the person skilled in the art, the utility model can have various changes and changes, any modification, equivalent replacement, improvement etc. that is done within the spirit and principles of the utility model, should be included in the protection scope of the utility model.

Claims

1. A mechanical drive for high pressure rotor spin-up of an aero turbine engine, characterized by, Comprise: input shaft, input shaft housing, connecting housing, output shaft, output shaft housing, first transmission gear, second transmission gear, first bearing, second bearing, third bearing, fourth bearing; The input shaft housing, the connecting housing, the output shaft housing form a containing space between them; The input shaft is sequentially provided with a first shaft section, a second shaft section and a third shaft section in the vertical direction, the first shaft section is connected with the inner end face of the input shaft housing through the first bearing, the second shaft section is connected with the inner end face of the input shaft housing through the second bearing, and the third shaft section is arranged in the containing space and connected with the first transmission gear; The output shaft is sequentially provided with a fourth shaft section, a fifth shaft section and a sixth shaft section in the horizontal direction, the fourth shaft section is connected with the inner end face of the output shaft housing through the third bearing, the fifth shaft section is connected with the inner end face of the output shaft housing through the fourth bearing, and the sixth shaft section is arranged in the containing space and connected with the second transmission gear; The first transmission gear and the second transmission gear are engaged to realize vertical constant speed transmission between the input shaft and the output shaft; The input shaft housing comprises a first docking part, the first docking part is arranged around the first shaft section, and the first docking part is used for connecting with an external driving device; the output shaft housing comprises a second docking part, the second docking part is arranged around the fourth shaft section, and the second docking part is used for connecting with a swing port of an external aero-engine.

2. The mechanical transmission for high pressure turbine rotor spin-up of an aeronautical turbine engine according to claim 1, characterized in that, Further comprise: A first baffle, a first fixed screw, a second baffle and a second fixed screw; The first baffle is close to one end of the first transmission gear away from the input shaft, the first fixed screw passes through the first baffle into the input shaft to fix the first transmission gear on the input shaft; The second baffle is close to one end of the second transmission gear away from the output shaft, and the second fixed screw passes through the second baffle into the output shaft to fix the second transmission gear on the output shaft.

3. The mechanical transmission device for high-pressure rotor swing of an aero turbine engine according to claim 1, characterized in that: The first transmission gear and the second transmission gear are a pair of arc-tooth constant-diameter bevel gears.

4. The mechanical transmission device for high-pressure rotor swing of an aero turbine engine according to claim 1, characterized in that: The first bearing and the third bearing are needle bearings, and the second bearing and the fourth bearing are deep groove ball bearings.

5. The mechanical transmission device for high-pressure rotor swing of an aero turbine engine according to claim 1, characterized in that: A first gasket is arranged between the second bearing and the first transmission gear, and a second gasket is arranged between the fourth bearing and the second transmission gear.

6. The mechanical transmission device for high-pressure rotor swing of an aero turbine engine according to claim 1, characterized in that: The third shaft section is connected with the first transmission gear through a flat key, and the sixth shaft section is connected with the second transmission gear through a flat key.

7. The mechanical transmission device for high pressure rotor of aero turbine engine as claimed in claim 1, wherein: a first bearing mounting portion is formed in the input shaft housing opposite to the inner end face of the second shaft section, and the second bearing is arranged in the first bearing mounting portion; and a second bearing mounting portion is formed in the output shaft housing opposite to the inner end face of the fifth shaft section, and the fourth bearing is arranged in the second bearing mounting portion.

8. The mechanical transmission device for high pressure rotor of aero turbine engine as claimed in claim 1, wherein: the first connecting portion is provided with a plurality of first mounting screw holes; and a shaft hole is arranged in the first shaft section.

9. The mechanical transmission device for high pressure rotor of aero turbine engine as claimed in claim 1, wherein: the output shaft is sequentially provided with the output shaft section, the fourth shaft section, the fifth shaft section and the sixth shaft section in the horizontal direction.

10. The mechanical transmission device for high pressure rotor of aero turbine engine as claimed in any one of claims 1 to 9, wherein: the second connecting portion is shaped to match the plug cover of the CFM56-7B type turbine engine, and the second connecting portion is provided with a plurality of second mounting screw holes, and the positions of the second mounting screw holes match the positions of the mounting screw holes of the plug cover of the CFM56-7B type turbine engine. ​ ​ ​ ​ ​ ​

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