CN113719584A - Hydraulic pump interface reducer of aircraft engine fly-attached casing - Google Patents

Hydraulic pump interface reducer of aircraft engine fly-attached casing Download PDF

Info

Publication number
CN113719584A
CN113719584A CN202110950528.5A CN202110950528A CN113719584A CN 113719584 A CN113719584 A CN 113719584A CN 202110950528 A CN202110950528 A CN 202110950528A CN 113719584 A CN113719584 A CN 113719584A
Authority
CN
China
Prior art keywords
output shaft
hydraulic pump
input shaft
shaft
pump interface
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202110950528.5A
Other languages
Chinese (zh)
Inventor
许柯
朱海雄
胡长寿
杨光荣
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Guiyang Engine Design Research Institute
Original Assignee
AECC Guiyang Engine Design Research Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AECC Guiyang Engine Design Research Institute filed Critical AECC Guiyang Engine Design Research Institute
Priority to CN202110950528.5A priority Critical patent/CN113719584A/en
Publication of CN113719584A publication Critical patent/CN113719584A/en
Pending legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H1/00—Toothed gearings for conveying rotary motion
    • F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
    • F16H1/32—Toothed gearings for conveying rotary motion with gears having orbital motion in which the central axis of the gearing lies inside the periphery of an orbital gear
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B53/00—Component parts, details or accessories not provided for in, or of interest apart from, groups F04B1/00 - F04B23/00 or F04B39/00 - F04B47/00
    • F04B53/16—Casings; Cylinders; Cylinder liners or heads; Fluid connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H57/021—Shaft support structures, e.g. partition walls, bearing eyes, casing walls or covers with bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/0412—Cooling or heating; Control of temperature
    • F16H57/0415—Air cooling or ventilation; Heat exchangers; Thermal insulations
    • F16H57/0417—Heat exchangers adapted or integrated in the gearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/042—Guidance of lubricant
    • F16H57/0421—Guidance of lubricant on or within the casing, e.g. shields or baffles for collecting lubricant, tubes, pipes, grooves, channels or the like
    • F16H57/0424—Lubricant guiding means in the wall of or integrated with the casing, e.g. grooves, channels, holes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/042—Guidance of lubricant
    • F16H57/043—Guidance of lubricant within rotary parts, e.g. axial channels or radial openings in shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/0467—Elements of gearings to be lubricated, cooled or heated
    • F16H57/0469—Bearings or seals
    • F16H57/0471—Bearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/048—Type of gearings to be lubricated, cooled or heated
    • F16H57/0482—Gearings with gears having orbital motion
    • F16H57/0486—Gearings with gears having orbital motion with fixed gear ratio

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Details Of Gearings (AREA)

Abstract

The invention discloses a hydraulic pump interface reducer of an aircraft engine fly-attached casing, which comprises: a reduction box body; the planetary gear is arranged on the transmission assembly and transmits the rotary motion to the output shaft through the transmission assembly; the front end of the input shaft is provided with a spline A connected with a hydraulic pump interface of the fly-attached casing, and the rear end of the output shaft is provided with a spline B connected with a hydraulic pump. The input shaft passes through spline A and flies to attach quick-witted casket hydraulic pump interface connection, and the output shaft passes through spline B and hydraulic pump connection, because the sun gear overlaps on the input shaft and meshes with the planet wheel, has reduced output structure's complexity, simultaneously, because input shaft and output shaft are relative coaxial rotatable installs on reduction box for the swift installation of whole reduction gear installation ability realization.

Description

Hydraulic pump interface reducer of aircraft engine fly-attached casing
Technical Field
The invention relates to a hydraulic pump interface reducer of an aircraft engine flying attachment casing, and belongs to the technical field of reducers.
Background
The output rated speed of a hydraulic pump interface of an aircraft accessory casing of the aircraft engine is 4200r/min during work. According to the development requirement, a hydraulic pump needs to be installed on a hydraulic pump interface of the flying attachment casing, the input rotating speed is 1800r/min during working, and a speed reducer is additionally arranged between the hydraulic pump interface of the flying attachment casing and the hydraulic pump, so that the purpose of simulating loading and extracting power is achieved. The flight attachment casing is hung and hoisted, the installation space is limited, the hydraulic pump is required to be installed in a cantilever mode, so that the installation mode of the speed reducer is cantilever installation, the installation space is narrow, high-rotation-speed transmission is achieved, and the length of the installation cantilever is limited.
Current reduction gear mostly sets up alone the sun gear, and output structure is complicated, and the installation form is flange mounting, shaft coupling installation, and most of reduction gear installations are mostly ground support mode, and the input shaft is not coaxial with the output shaft, and it is comparatively troublesome to install.
Disclosure of Invention
In order to solve the technical problem, the invention provides a hydraulic pump interface reducer of an aircraft engine fly-attached casing.
The invention is realized by the following technical scheme.
The invention provides a hydraulic pump interface reducer of an aircraft engine fly-attached casing, which comprises: a reduction box body;
the planetary gear is arranged on the transmission assembly and transmits the rotary motion to the output shaft through the transmission assembly;
the front end of the input shaft is provided with a spline A connected with a hydraulic pump interface of the fly-attached casing, and the rear end of the output shaft is provided with a spline B connected with a hydraulic pump.
The spline B is concentric with the spline A.
The transmission assembly comprises a support shaft, one end of the support shaft is inserted into a hole of the reduction box body, and the other end of the support shaft is pressed and fixed by the end cover;
the step sleeve is rotatably sleeved on the supporting shaft through a bearing A;
the step sleeve is close to the end part of the output shaft to realize the transmission of rotary motion through gear engagement, and the planet wheel sleeve is sleeved on the step sleeve and is engaged with the sun wheel on the input shaft; the meshing of sun gear and planet wheel drives the step cover and rotates around the back shaft on bearing A, and the gear meshing through step cover and output shaft transmits the rotary motion to the output shaft and exports.
The number of the bearings A is four, the bearings A are distributed at two ends of the meshing part of the step sleeve at intervals, a lubricating oil inlet path is arranged above the reduction box body and penetrates through the inside of the supporting shaft to be discharged from the middle to the two pairs of bearings A at intervals for lubricating, and cooling oil passing through the lubricating oil inlet path is cooled and lubricated from the inner space where the bearings A are located.
The input shaft is rotatably supported and installed on the reduction box body through a bearing B, and the input shaft is tightly pressed and fixed on the reduction box body through an input shaft end cover, so that the input shaft can only rotate under the support of the bearing B.
The output shaft is rotatably supported and installed on the reduction box body through a bearing C, and the output shaft is tightly pressed and fixed on the reduction box body through an output end cover.
The output shaft is rotatably supported with the input shaft through a bearing D.
The hollow output shaft is internally provided with a hollow body with two communicated ends, the end part of the input shaft close to the output shaft is provided with the hollow body, the hollow space of the input shaft and the hollow space of the output shaft can be communicated, and the hollow output shaft is internally provided with a sealing element for sealing oil.
The spline B is positioned in the hollow interior of the output shaft, the sealing element separates the spline B from the space where the sealing element is positioned, and the space communicated with the output shaft, the sun gear, the bearing D and the bearing B is arranged below the reduction gearbox body to form a lubricating oil outlet path;
the lubricating oil inlet path is connected with the upper part of the reduction box body in a detachable mode through an installation adapter joint in a lap joint mode, and the lubricating oil outlet path is connected with the lower part of the reduction box body in a detachable mode through an installation adapter joint in a lap joint mode.
The oil entering from the lubricating oil inlet path can lubricate and cool the bearing A, the bearing B, the gear meshing part of the step sleeve and the output shaft, the meshing part of the sun wheel and the planet wheel and the bearing D when rotating, and finally the oil is discharged from the lubricating oil outlet path.
The invention has the beneficial effects that: the input shaft passes through spline A and flies to attach quick-witted casket hydraulic pump interface connection, and the output shaft passes through spline B and hydraulic pump connection, because the sun gear overlaps on the input shaft and meshes with the planet wheel, has reduced output structure's complexity, simultaneously, because input shaft and output shaft are relative coaxial rotatable installs on reduction box for the swift installation of whole reduction gear installation ability realization.
Drawings
FIG. 1 is a schematic cross-sectional view of the present invention;
in the figure: 1-a reduction box body; 2-lubricating oil inlet path; 3-a planet wheel; 4-a sun gear; 5-an input shaft; 6-spline A; 7-an output shaft; 8-spline B; 9-a lubricating oil outlet path; 31-a support shaft; 32-bearing a; 33-step sleeve; 51-bearing B; 52-input shaft end cap; 71-bearing C; 72-an output end cap; 73-bearing D; 74-seal.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
As shown in fig. 1.
The invention relates to a hydraulic pump interface reducer of an aircraft engine flying-attached casing, which comprises: a rigid and hard reduction box body 1 providing a containing space;
the planetary gear mechanism comprises a planetary gear 3, an input shaft 5 and an output shaft 7 which are rotatably arranged on a reduction box body 1, wherein the input shaft 5 and the output shaft 7 are relatively coaxially and rotatably arranged on the reduction box body 1, a sun gear 4 is sleeved on the input shaft 5 and meshed with the planetary gear 3, and the planetary gear 3 is arranged on a transmission assembly and transmits the rotating motion to the output shaft 7 through the transmission assembly;
the front end of the input shaft 5 is provided with a spline A6 connected with a hydraulic pump interface of the fly-attachment casing, the rear end of the output shaft 7 is provided with a spline B8 connected with a hydraulic pump, and the spline B8 is concentric with the spline A6.
The working principle is as follows: the input shaft 5 is connected with a hydraulic pump interface of the flying attachment casing through a spline A6, the output shaft 7 is connected with a hydraulic pump through a spline B8, the sun gear 4 is sleeved on the input shaft 5 and meshed with the planet gear 3, the complexity of an output structure is reduced, and meanwhile, the input shaft 5 and the output shaft 7 are relatively coaxially and rotatably mounted on the reduction box body 1, so that the whole speed reducer can be rapidly mounted.
The transmission assembly comprises a support shaft 31, one end of the support shaft 31 is inserted into a hole of the reduction box body 1, and the other end of the support shaft 31 is pressed and fixed by an end cover 34 by using a screw;
the step sleeve 33 rotatably sleeved on the support shaft 31 through a bearing A32;
the end part of the step sleeve 33 close to the output shaft 7 realizes the transmission of the rotary motion through gear engagement, and the planet wheel 3 is sleeved on the step sleeve 33 and is engaged with the sun wheel 4 on the input shaft 5;
when the input shaft 5 rotates, the engagement of the sun gear 4 and the planet gears 3 drives the step sleeve 33 to rotate on the bearing A32 around the support shaft 31, and the rotation motion is transmitted to the output shaft 7 through the gear engagement of the step sleeve 33 and the output shaft 7 to be output.
The four bearings A32 are arranged at two ends of the meshing part of the step sleeve 33 in two pairs at intervals, a lubricating oil inlet path 2 is arranged above the reduction gearbox body 1, the lubricating oil inlet path 2 is lapped above the reduction gearbox body 1 through the installation of a detachable adapter joint, and the lubricating oil inlet path 2 penetrates through the inside of the supporting shaft 31 and is lubricated by two pairs of bearings A32 which are arranged at intervals from the middle, so that cooling oil passing through the lubricating oil inlet path 2 is cooled and lubricated from the inner space where the bearings A32 are located.
The input shaft 5 is rotatably supported and mounted on the reduction box body 1 through a bearing B51, and the input shaft 5 is tightly pressed and fixed on the reduction box body 1 through an input shaft end cover 52 by using screws, so that the input shaft 5 can only perform rotary motion under the support of a bearing B51.
The output shaft 7 is rotatably supported and installed on the reduction box body 1 through a bearing C71, the output shaft 7 is tightly pressed and fixed on the reduction box body 1 through an output end cover 72 by using a screw, and the output shaft 7 is rotatably supported with the input shaft 5 through a bearing D73.
The hollow part with two communicated ends is arranged in the output shaft 7, the hollow space of the input shaft 5 and the hollow space of the output shaft 7 can be communicated, the sealing element 74 for sealing oil is arranged in the hollow part of the output shaft 7, when the sealing element 74 does not exist, the coaxiality of the input shaft 5 and the output shaft 7 during installation is measured and debugged, the daily detection is carried out, and meanwhile, the sealing element 74 leaks oil at intervals; the spline B8 is positioned in the hollow interior of the output shaft 7, the sealing element 74 separates the space where the spline B8 and the sealing element 74 are positioned, the space communicated with the output shaft 7, the sun gear 4, the bearing D73, the bearing D73 and the bearing B51 is arranged below the reduction gearbox body 1 to form a lubricating oil outlet path 9, and the lubricating oil outlet path 9 is lapped below the reduction gearbox body 1 through a detachable adapter joint;
when rotating, the oil entering from the lubricating oil inlet passage 2 lubricates and cools the bearing a32, the bearing B51, the gear meshing part between the step sleeve 33 and the output shaft 7, the meshing part between the sun gear 4 and the planetary gear 3, and the bearing D73, and is finally discharged from the lubricating oil outlet passage 9.
The speed reducer is additionally arranged between a hydraulic pump interface of a flying attachment casing and a hydraulic pump, the input rated rotating speed of an input shaft 5 of the speed reducer is 4200r/min and the output rotating speed of an output shaft 7 of the speed reducer is 1800r/min during working, and the speed reducer runs normally and meets the requirement of high-speed to low-speed transmission; the input shaft 5 is convenient for being connected with the hydraulic pump interface of the flying attachment casing through a spline A6, in the rotation process of the reduction gearbox, lubricating oil flows into the interior of the reduction gearbox body 1 from the joint of the lubricating oil inlet path 2 to lubricate the sun gear 4 and the planet gear 3 rotating at a high speed, the lubricating oil flows out from an oil outlet 9 below the gearbox body, and the effect of cooling the gearbox body is achieved while the sun gear 4 and the planet gear 3 rotating at a high speed are lubricated.

Claims (10)

1. The utility model provides an aeroengine flies to attach quick-witted casket hydraulic pump interface reduction gear which characterized in that includes: a reduction box body (1);
the planetary gear type speed reducer comprises a planetary gear (3), an input shaft (5) and an output shaft (7) which are rotatably arranged on a speed reducer box body (1), wherein the input shaft (5) and the output shaft (7) are coaxially and rotatably arranged on the speed reducer box body (1) relatively, a sun gear (4) is sleeved on the input shaft (5) and is meshed with the planetary gear (3), and the planetary gear (3) is arranged on a transmission assembly and transmits rotary motion to the output shaft (7) through the transmission assembly;
the front end of the input shaft (5) is provided with a spline A (6) connected with a hydraulic pump interface of the fly-attached casing, and the rear end of the output shaft (7) is provided with a spline B (8) connected with a hydraulic pump.
2. The aircraft engine flying case hydraulic pump interface retarder of claim 1, wherein: the spline B (8) is concentric with the spline A (6).
3. The aircraft engine flying case hydraulic pump interface retarder of claim 1, wherein: the transmission assembly comprises a support shaft (31), one end of the support shaft (31) is inserted into a hole of the reduction box body (1), and the other end of the support shaft (31) is pressed and fixed by an end cover (34);
a step sleeve (33) which is rotatably sleeved on the supporting shaft (31) through a bearing A (32);
the end part of the step sleeve (33) close to the output shaft (7) realizes the transmission of rotary motion through gear engagement, and the planet wheel (3) is sleeved on the step sleeve (33) and is engaged with the sun wheel (4) on the input shaft (5); the meshing of the sun wheel (4) and the planet wheel (3) drives the step sleeve (33) to rotate around the supporting shaft (31) on the bearing A (32), and the rotating motion is transmitted to the output shaft (7) to be output through the gear meshing of the step sleeve (33) and the output shaft (7).
4. The aircraft engine flying case hydraulic pump interface retarder of claim 3, wherein: the four bearings A (32) are distributed at two ends of the meshing part of the step sleeve (33) at intervals, a lubricating oil inlet path (2) is arranged above the reduction box body (1), and the lubricating oil inlet path (2) penetrates through the inside of the supporting shaft (31) and is discharged from the middle to the two pairs of bearings A (32) at intervals for lubricating.
5. The aircraft engine flying case hydraulic pump interface retarder of claim 1 or 4, wherein: the input shaft (5) is rotatably supported and installed on the reduction box body (1) through a bearing B (51), and the input shaft (5) is tightly pressed and fixed on the reduction box body (1) through an input shaft end cover (52), so that the input shaft (5) can only rotate under the support of the bearing B (51).
6. The aircraft engine flying case hydraulic pump interface retarder of claim 5, wherein: the output shaft (7) is rotatably supported and installed on the reduction box body (1) through a bearing C (71), and the output shaft (7) is tightly pressed and fixed on the reduction box body (1) through an output end cover (72).
7. The aircraft engine flying case hydraulic pump interface retarder of claim 6, wherein: the output shaft (7) is rotatably supported with the input shaft (5) through a bearing D (73).
8. The aircraft engine flying case hydraulic pump interface retarder of claim 7, wherein: the hollow oil-sealed power transmission device is characterized in that a hollow body with two communicated ends is arranged in the output shaft (7), the end part of the input shaft (5) close to the output shaft (7) is the hollow body, hollow spaces of the input shaft and the output shaft can be communicated, and a sealing element (74) for sealing oil is arranged in the hollow part of the output shaft (7).
9. The aircraft engine flying case hydraulic pump interface retarder of claim 8, wherein: the spline B (8) is positioned in the hollow interior of the output shaft (7), the space where the spline B (8) and the sealing element (74) are located is separated by the sealing element (74), and the space communicated with the output shaft (7), the sun gear (4), the bearing D (73) and the bearing B (51) is arranged below the reduction gearbox body (1) to form a lubricating oil outlet channel (9).
10. The aircraft engine flying case hydraulic pump interface retarder of claim 9, wherein: the lubricating oil inlet path (2) is detachably connected with the adapter joint in an overlapping mode above the reduction box body (1) through installation, and the lubricating oil outlet path (9) is detachably connected with the adapter joint in an overlapping mode below the reduction box body (1) through installation.
CN202110950528.5A 2021-08-18 2021-08-18 Hydraulic pump interface reducer of aircraft engine fly-attached casing Pending CN113719584A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110950528.5A CN113719584A (en) 2021-08-18 2021-08-18 Hydraulic pump interface reducer of aircraft engine fly-attached casing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110950528.5A CN113719584A (en) 2021-08-18 2021-08-18 Hydraulic pump interface reducer of aircraft engine fly-attached casing

Publications (1)

Publication Number Publication Date
CN113719584A true CN113719584A (en) 2021-11-30

Family

ID=78676749

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202110950528.5A Pending CN113719584A (en) 2021-08-18 2021-08-18 Hydraulic pump interface reducer of aircraft engine fly-attached casing

Country Status (1)

Country Link
CN (1) CN113719584A (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN2739419Y (en) * 2004-11-06 2005-11-09 孙宝龙 WW planetary differential gear drive reducing gear
US20090318255A1 (en) * 2008-06-20 2009-12-24 Toyota Jidosha Kabushiki Kaisha Vehicle power transmitting device
CN203500386U (en) * 2013-10-23 2014-03-26 中国船舶重工集团公司第七�三研究所 Head joint type ordinary gear train transmission mechanism used for power branches
US20170197502A1 (en) * 2014-06-04 2017-07-13 Ryou Yukishima In-wheel motor drive device
US20180363758A1 (en) * 2016-02-25 2018-12-20 Daihen Corporation Driving apparatus
CN112879534A (en) * 2019-11-29 2021-06-01 中车时代电动汽车股份有限公司 Be applied to planetary reducer assembly of new forms of energy commercial car

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN2739419Y (en) * 2004-11-06 2005-11-09 孙宝龙 WW planetary differential gear drive reducing gear
US20090318255A1 (en) * 2008-06-20 2009-12-24 Toyota Jidosha Kabushiki Kaisha Vehicle power transmitting device
CN203500386U (en) * 2013-10-23 2014-03-26 中国船舶重工集团公司第七�三研究所 Head joint type ordinary gear train transmission mechanism used for power branches
US20170197502A1 (en) * 2014-06-04 2017-07-13 Ryou Yukishima In-wheel motor drive device
US20180363758A1 (en) * 2016-02-25 2018-12-20 Daihen Corporation Driving apparatus
CN112879534A (en) * 2019-11-29 2021-06-01 中车时代电动汽车股份有限公司 Be applied to planetary reducer assembly of new forms of energy commercial car

Similar Documents

Publication Publication Date Title
CN105378336B (en) Wheel chain is incorporated in the pinion gear wall of turbine gear-box
CN105431657B (en) Epicyclic reduction gear with fluid transmission pipe and the properller turbine with the reduction gearing
US9863325B2 (en) Assembly for aircraft turbine engine and method for mounting same
CN205479154U (en) Planet gear of electricelectric motor car
CN113719584A (en) Hydraulic pump interface reducer of aircraft engine fly-attached casing
CN202158172U (en) Forced lubricating system for meshing of planetary system
CN202182170U (en) Planetary system outer meshing forcemeat lubricating device
CN209430737U (en) A kind of new energy pure electric vehicle reduction gearbox lubricating system
CN109578562B (en) Lubricating oil circuit structure of wind power gear box
CN116241641A (en) Planetary reducer convenient for adding lubricating oil
CN2379643Y (en) Pneumatic friction plate type clutch
CN215440892U (en) Spinning thread lubricating arrangement for textile production
CN216078157U (en) Aeroengine flies to attach quick-witted casket generator interface speed increaser
CN102829167A (en) Planetary external gearing forced lubrication device
CN216478715U (en) Speed reducer
CN201170290Y (en) Speeding-up gear box of wind power generator
CN206111964U (en) Planetary gear reducer
CN215763075U (en) Gear box of grease gun
CN217002986U (en) Planetary gear transmission mechanism for speed reducer
CN220711260U (en) Planetary reduction electric driving device
CN219798698U (en) Planetary gear box test device
CN221257555U (en) Planetary transmission structure of motor
CN202756595U (en) Lubricating system of vertical type planetary reducer
CN219655173U (en) Built-in motor integrated planetary reducer
CN110345200A (en) A kind of tubular motor reducer

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination