CN107893832B - High-speed heavy-load power split-flow type speed reducer system of micro turboprop engine - Google Patents

High-speed heavy-load power split-flow type speed reducer system of micro turboprop engine Download PDF

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Publication number
CN107893832B
CN107893832B CN201711105946.4A CN201711105946A CN107893832B CN 107893832 B CN107893832 B CN 107893832B CN 201711105946 A CN201711105946 A CN 201711105946A CN 107893832 B CN107893832 B CN 107893832B
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speed
gear
low
bearing
lubricating oil
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CN107893832A (en
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李纪永
张征
陈溯
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Sichuan Aerospace Zhongtian Power Equipment Co ltd
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Sichuan Aerospace Zhongtian Power Equipment Co ltd
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    • 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
    • F16H1/02—Toothed gearings for conveying rotary motion without gears having orbital motion
    • F16H1/20—Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members
    • F16H1/22—Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with a plurality of driving or driven shafts; with arrangements for dividing torque between two or more intermediate shafts
    • F16H1/222—Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with a plurality of driving or driven shafts; with arrangements for dividing torque between two or more intermediate shafts with non-parallel axes
    • 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
    • F16H57/022—Adjustment of gear shafts or 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
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H57/023—Mounting or installation of gears or shafts in the gearboxes, e.g. methods or means for assembly
    • 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
    • F16H57/027—Gearboxes; Mounting gearing therein characterised by means for venting gearboxes, e.g. air breathers
    • 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
    • F16H57/029—Gearboxes; Mounting gearing therein characterised by means for sealing the gearboxes, e.g. to improve airtightness
    • 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
    • F16H57/031—Gearboxes; Mounting gearing therein characterised by covers or lids for gearboxes
    • 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
    • F16H57/0402—Cleaning of lubricants, e.g. filters or magnets
    • F16H57/0404—Lubricant filters
    • 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
    • F16H57/0413—Controlled cooling or heating of lubricant; Temperature control therefor
    • 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
    • F16H57/0434—Features relating to lubrication or cooling or heating relating to lubrication supply, e.g. pumps ; Pressure control
    • 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
    • F16H2057/02039—Gearboxes for particular applications

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

Abstract

The invention discloses a high-speed heavy-load power split type speed reducer system of a miniature turboprop engine, which comprises a speed reducer shell, a high-speed gear set, a low-speed gear set and a turning bevel gear set, wherein the high-speed gear set comprises a high-speed pinion, a high-speed bull gear A and a high-speed bull gear B, the high-speed bull gear A and the high-speed bull gear B are respectively meshed with symmetrical gears of the high-speed pinion, and a high-speed shaft is arranged in the center of the high-speed pinion; the direction-changing bevel gear set comprises a bevel gear A and a bevel gear B, the end part of a power input shaft of the generator is fixed at the center of the bevel gear B, and the bevel gear A is in power connection with the high-speed large gear B through an intermediate shaft B; the low-speed gear set comprises a low-speed pinion and a low-speed bull gear, the low-speed pinion is in power connection with the high-speed bull gear A through an intermediate shaft A, and a low-speed shaft penetrating through the low-speed side of the reducer shell is installed in the center of the low-speed bull gear. The invention improves the service performance and the service life of the speed reducer.

Description

High-speed heavy-load power split-flow type speed reducer system of micro turboprop engine
Technical Field
The invention relates to the technical field of miniature turboprop engines, in particular to a high-speed heavy-load power split-flow speed reducer system of a miniature turboprop engine.
Background
The power of the high-speed heavy-load power split type speed reducer of the micro turboprop engine is more than 50 kW, and the linear speed of a gear of the speed reducer is more than 150 m/s. Particularly, under the conditions of high input rotating speed, compact structure and large load of the speed reducer, the design of core functional components and auxiliary system structures of the speed reducer ensures the safe operation of the speed reducer, improves the operation performance of the speed reducer, and simultaneously shunts the output power of the speed reducer for power generation so as to ensure the normal work of the aircraft during long-term flight at medium and high altitude.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a high-speed heavy-load power split-flow type speed reducer system of a miniature turboprop engine, which realizes the output power split of the high-speed heavy-load speed reducer in a simple gear meshing structure mode, eliminates the axial force caused by the transmission of a high-speed bevel gear pair of the speed reducer by using a bevel gear transmission of a low-speed gear pair, adopts spline connection between a high-speed shaft and a gear, adopts shaft shoulder positioning at one side, adopts a nut fastening at the other side in a direction opposite to the rotation direction of the gear, ensures the accurate installation position of the gear, ensures that the gear meets the design requirement of high-speed heavy load, simultaneously carries out independent lubricating oil loop design on the speed reducer in order to meet the requirements of the use performance and service life of the speed reducer and utilizes the advanced micro-system heat dissipation technology in the field of MEMS to cool lubricating oil, the power split power generation is carried out while the speed reducer works stably.
The purpose of the invention is realized by the following technical scheme:
a high-speed heavy-load power split type speed reducer system of a micro turboprop engine comprises a speed reducer shell, a high-speed gear set, a low-speed gear set and a direction-changing bevel gear set, wherein the high-speed gear set, the low-speed gear set and the direction-changing bevel gear set are positioned inside the speed reducer shell, the high-speed gear set and the low-speed gear set are parallel to each other, the speed reducer shell is provided with a power input end of a generator, a high-speed side and a low-speed side corresponding to the high-speed side, the high-speed gear set is correspondingly installed on the high-speed side of the speed reducer shell, the low-speed gear set is correspondingly installed on the low-speed side of the speed reducer shell, and the direction-changing bevel; the high-speed gear set comprises a high-speed pinion, a high-speed bull gear A and a high-speed bull gear B, the high-speed bull gear A and the high-speed bull gear B are respectively meshed with symmetrical gears of the high-speed pinion, a high-speed shaft is mounted in the center of the high-speed pinion, and the high-speed shaft is mounted in the center of the high-speed side of the reducer shell in a penetrating and matching mode; the generator power input end of the speed reducer shell is provided with a generator power input shaft in a penetrating and matching mode, the direction-changing bevel gear set comprises a bevel gear A and a bevel gear B in gear engagement with the bevel gear A, the end part of the generator power input shaft is fixed at the center of the bevel gear B, the bevel gear A is parallel to the high-speed large gear B, and the bevel gear A is in power connection with the high-speed large gear B through an intermediate shaft B; the low-speed gear set comprises a low-speed pinion and a low-speed gear wheel meshed with the low-speed pinion, the low-speed pinion is in power connection with the high-speed gear wheel A through an intermediate shaft A, and a low-speed shaft penetrating through the low-speed side of the speed reducer shell is installed at the center of the low-speed gear wheel.
In order to better realize the invention, the invention also comprises a lubricating oil tank, a lubricating oil pump and an oil filter, wherein a speed reducer shell of the speed reducer is provided with a lubricating oil hole A and a lubricating oil hole B which are communicated with the inside of the speed reducer shell, the inside of the speed reducer shell is provided with a lubricating oil flowing clearance channel communicated with the lubricating oil hole A and the lubricating oil hole B, a lubricating oil outlet of the lubricating oil pump is hermetically communicated with the lubricating oil hole A, the lubricating oil hole B is hermetically communicated with a lubricating oil recovery inlet of the oil filter through a pipeline, a lubricating oil inlet of the lubricating oil pump is communicated with a lubricating oil outlet of the lubricating oil tank, and a lubricating oil outlet of the oil filter is communicated with a lubricating oil inlet of the lubricating oil tank through a pipeline; the oil filter is internally provided with a filter element for filtering and treating recovered lubricating oil.
The further technical proposal is that the invention also comprises a compressor, heat exchange fins and a coolant liquid storage tank, a micro-channel heat exchange component is arranged in the lubricating oil tank, the micro-channel heat exchange component is provided with a coolant inlet pipe and a coolant outlet pipe, the coolant outlet of the coolant storage tank is hermetically communicated with the coolant inlet pipe of the micro-channel heat exchange component through a pipeline, the heat exchange fins are internally provided with heat exchange coils, the heat exchange coils of the heat exchange fins are provided with a coolant inlet end and a coolant outlet end, the coolant outlet end of the heat exchange fin is hermetically communicated with the coolant inlet of the coolant liquid storage tank through a pipeline, the coolant outlet pipe of the micro-channel heat exchange component is hermetically communicated with the coolant inlet of the compressor through a pipeline, the coolant outlet of the compressor is hermetically communicated with the coolant inlet end of the heat exchange fin through a pipeline; and a throttling valve is arranged on a pipeline between the coolant outlet end of the heat exchange fin and the coolant inlet of the coolant liquid storage tank.
Preferably, the invention further comprises a high-pressure gas path, wherein a reducer shell of the reducer is provided with a reducer gas hole communicated with the inside of the reducer shell, the reducer gas hole is hermetically communicated with the high-pressure gas path through a gas pressure balance pipeline, and the inside or/and the outside of the gas pressure balance pipeline is/are coated with a GORE-TEX film.
Preferably, the high-speed pinion and the high-speed shaft are in threaded connection and fixed through screws C with opposite rotation directions, and the center of the high-speed pinion and the end part of the high-speed shaft are locked and positioned through bolts; the low-speed shaft and the low-speed large gear are in threaded connection and fixed through screws B in opposite rotating directions, and spring gaskets B are mounted on the screws B; the low-speed pinion gear adopts a gear shaft structure, and the low-speed bull gear and the bevel gear B adopt a radial plate type structure.
Preferably, the high-speed side of the reducer shell is provided with a bearing C corresponding to the intermediate shaft B, the low-speed side of the reducer shell is provided with a bearing E corresponding to the intermediate shaft B, one end of the intermediate shaft B is correspondingly and rotatably mounted in the bearing C, the other end of the intermediate shaft B is correspondingly and rotatably mounted in the bearing E, an adjusting shim C for positioning the bevel gear a is mounted between the bevel gear a and the bearing E, and an adjusting shim B for positioning the high-speed bull gear B is mounted between the high-speed bull gear B and the bearing C; the high-speed side of the speed reducer shell is provided with a bearing A corresponding to the intermediate shaft A, the low-speed side of the speed reducer shell is provided with a bearing J corresponding to the intermediate shaft A, one end of the intermediate shaft A is correspondingly and rotatably installed in the bearing A, the other end of the intermediate shaft A is correspondingly and rotatably installed in the bearing J, and an adjusting gasket A used for positioning the high-speed gearwheel A is installed between the high-speed gearwheel A and the bearing A.
Preferably, the high-speed bull gear B, the high-speed pinion gear, the high-speed bull gear A, the low-speed pinion gear and the low-speed bull gear are all bevel gears; the bevel gear A is connected with the middle shaft B through splines, the high-speed gear B is connected with the middle shaft B through splines, the high-speed pinion is connected with the high-speed shaft through splines, the high-speed gear A is connected with the middle shaft A through splines, and the low-speed pinion is connected with the middle shaft A through splines.
Preferably, the bevel gear a is positioned and mounted on the intermediate shaft B through a shoulder on the bevel gear a, the high-speed bull gear B is positioned and mounted on the intermediate shaft B through a shoulder on the high-speed bull gear B, the high-speed pinion gear is positioned and mounted on the high-speed shaft through a shoulder on the high-speed pinion gear, the high-speed bull gear a is positioned and mounted on the intermediate shaft a through a shoulder on the high-speed bull gear a, and the low-speed pinion gear is positioned and mounted on the intermediate shaft a through a shoulder on the low-speed pinion gear.
Preferably, a bearing B which is in mutual rotating fit with the high-speed shaft is installed on the high-speed side of the speed reducer shell, a sealing rubber ring A is arranged between the bearing B and the high-speed side of the speed reducer shell, and the high-speed shaft and the bearing B are positioned and locked through a shaft shoulder and a locking nut; a bearing D which is in mutual rotating fit with a power input shaft of the generator is arranged at the power input end of the speed reducer shell, an oil seal A is arranged between the bearing D and a bevel gear B, a rubber ring A is arranged between the bearing D and the power input end of the generator of the speed reducer shell in a sealing way, an elastic retainer ring A is further arranged on the outer side of the bearing D, and the power input shaft of the generator and the bevel gear B are further fixedly connected through a screw A with a spring gasket A; bearing I with the mutual rotation complex of low-speed axle is installed to reduction gear housing low-speed side, install bearing F between low-speed level gear wheel and the bearing I, install oil blanket B between bearing I and the bearing F, sealing installation has rubber ring B between bearing I and the reduction gear housing low-speed side, the bearing I outside is equipped with circlip B, be equipped with adjusting shim D between bearing F and the low-speed level gear wheel.
Preferably, the reducer casing comprises a front end cover and a rear end cover, the front end cover of the reducer casing is provided with a screw hole B, the rear end cover of the reducer casing is provided with a screw hole A corresponding to the screw hole B, the front end cover and the rear end cover of the reducer casing are connected through screws, and the front end cover and the rear end cover of the reducer casing are further connected with a plurality of sealing rubber rings B in a sealing mode.
The invention realizes the output power split of the high-speed heavy-load speed reducer by a simple gear meshing structure mode, eliminates the axial force caused by the transmission of the high-speed stage bevel gear pair of the speed reducer by using the bevel gear transmission of the low-speed stage gear pair, ensures the accurate installation position of the gear and can also ensure that the gear meets the design requirement of high-speed heavy load by adopting spline connection on one side and fastening by adopting a nut with the opposite rotating direction of the gear on the other side, simultaneously designs an independent lubricating oil loop on the speed reducer for meeting the requirements of the service performance and the service life of the speed reducer on the basis of pursuing the requirement of compact structure, and cools the lubricating oil by utilizing the advanced micro-system heat dissipation technology in the field of MEMS (micro-electromechanical systems) so as to realize the stable work of the speed reducer and simultaneously carry out power split power generation.
One of the technical solutions of the present invention is: the high-speed-stage small gears are respectively meshed with the high-speed-stage large gears on two sides, and the high-speed-stage large gear on one side transmits most of power to the low-speed-stage small gear and finally transmits the power to the propeller through the low-speed-stage large gear to drive the aircraft to fly. And the high-speed large gear on the other side drives a bevel gear pair to rotate by a small part of power through a transmission shaft and transmits the power to a generator to generate power. And the adopted cylindrical gears are all helical gears. The solution principle of the invention is as follows: aiming at the high-speed heavy-load reducer gear, the gear is preliminarily designed by utilizing a contact fatigue strength criterion, the gear is designed in detail by utilizing romax software, and power flow calculation, gear and shaft strength calculation and the like are carried out. The two high-speed large gears are meshed with the high-speed small gear at the same time, so that the high-speed small gear simultaneously drives the gears on two sides to rotate, and the purpose of power splitting is achieved. In addition, because the bevel gear has the function of changing the transmission direction, the bevel gear is used for carrying out two-stage speed reduction, and simultaneously, the direction of the power input shaft of the generator is changed, so that the position interference between the installation position of the generator and the propeller behind the engine is avoided. The low-speed cylindrical gear is also the same as the high-speed cylindrical gear, and the helical gears are used for meshing transmission, so that the axial force caused by the high-speed helical gear in the torque transmission process of the speed reducer is eliminated as much as possible, the transmission stability of the speed reducer is improved, and the working noise of the speed reducer is reduced.
The second technical solution of the invention is as follows: the transmission gear and the transmission shaft are connected and fixed in position, the high-speed gear and the low-speed bevel pinion are connected with the transmission shaft through splines, one end of the gear, which is positioned, is located through a shaft shoulder, the other end of the high-speed pinion is locked through a nut in a rotating direction opposite to the rotating direction of the shaft, and the other ends of the high-speed gear and the low-speed bevel pinion are located through a bearing with an adjusting gasket. The low-speed pinion adopts a gear shaft form, and the low-speed bull gear and the low-speed bull bevel gear both adopt a radial plate type structural form. The solution principle of the invention is as follows: because the splined connection atress is comparatively even, and because of the groove is less, the concentration of stress of tooth root department is less, and the intensity weakening of axle and hub reduces, and the number of teeth is more, and total area of contact is great, therefore can bear great load, consequently each gear all adopts splined connection with the cooperation structure of axle, can cut close the high-speed heavily loaded design requirement of this patent. High-speed level pinion one side is fixed a position through the shaft shoulder, and the opposite side is through epaxial design and the opposite screw thread that revolves to of axle direction of rotation to join in marriage the nut and lock the gear fixedly, so can make the reduction gear in normal work, can not make nut pretightning force reduce, nut landing etc. because of the gear long-term rotation. The gear shaft can achieve the purpose of simplifying the structure, and the radial plate type gear structure can reduce the overall weight of the speed reducer.
The third technical solution of the invention is: the lubricating oil loop of the speed reducer is designed, and the lubricating oil hole is designed on the shell of the speed reducer, so that the lubricating oil in the lubricating oil tank is pumped into the lubricating oil hole of the speed reducer by the lubricating oil pump, a transmission gear and a bearing in the speed reducer are lubricated, and when the lubricating oil flows out from a lubricating oil outlet on the shell of the speed reducer, the lubricating oil is filtered by oil and then returns to the lubricating oil tank. The solution principle of the invention is as follows: the lubricating oil can lubricate each rotating part, can effectively relieve tooth surface abrasion and pitting corrosion caused by gear meshing, and meanwhile, the design of the circulating reciprocating lubricating oil loop can timely take away working heat generated by rotation of a bearing, a gear and the like, so that the lubricating oil is prevented from losing efficacy due to temperature rise of the lubricating oil in the speed reducer, the friction of the bearing is increased, the tooth surface abrasion is aggravated, the tooth surface gluing and other phenomena occur, and the service life of the speed reducer is further shortened.
The fourth technical solution of the invention is as follows: the design of the vent hole is that the vent hole is designed on the shell of the speed reducer, the air hole of the speed reducer is connected with the high-pressure air path by utilizing an air pressure balance pipeline so as to balance the pressure inside the speed reducer, a GORE-TEX film is covered between the vent hole and the high-pressure air path, and an oil filter screen is designed at the front end of the film to filter oil mixed in the air. The solution principle of the invention is as follows: because the high-speed rotation of the internal gear pair, the bearing and other parts of the speed reducer can generate a large amount of working heat, the temperature of lubricating oil is increased, lubricating oil steam is generated, and further the thermal expansion of air in the speed reducer is caused, and the pressure is increased. And the design of the vent hole can keep proper pressure in the oil pool, and also can keep the performance of the oil pump, simultaneously keep the pressure of the safe working inlet of the oil pump, and simultaneously ensure the normal oil return of the lubricating oil of the speed reducer. The GORE-TEX film can effectively prevent lubricating oil from leaking and has strong air permeability.
The fifth technical solution of the invention is as follows: the lubricating oil radiator is designed, a micro-channel heat exchange component is arranged in the lubricating oil device, coolant flows into a micro-channel from a coolant storage tank under the pumping action of a compressor to exchange heat with lubricating oil, then enters heat exchange fins after being compressed by the compressor and releases heat into air, and finally returns to the coolant storage tank after being throttled by a throttle valve. And a temperature sensor is arranged in the lubricating oil tank. The solution principle of the invention is as follows: because the micro flow channel has larger area-volume ratio, the heat exchange efficiency is higher than that of the conventional flow channel heat exchanger. Therefore, the micro-channel heat exchange component is designed and installed in the lubricating oil tank by utilizing the countercurrent principle, the coolant is pumped into the channel under the action of the coolant compressor so as to achieve the purpose of taking away the heat in the lubricating oil tank in real time, then the heat is released into the air through the external heat exchange fins, and finally the coolant returns to the coolant liquid storage tank after being throttled and depressurized by the throttle valve. The temperature sensor can play a role in monitoring the temperature change condition in the lubricating oil tank in real time so as to avoid the phenomena of tooth surface friction, pitting corrosion, gluing and the like caused by the failure of lubricating oil in the speed reducer due to heat transfer deterioration.
Compared with the prior art, the invention has the following advantages and beneficial effects:
the invention can realize power shunt power generation while not influencing the flight of the aircraft pushed by the propeller, and ensure the power supply of related electric equipment; and the high-speed gear and the shaft are connected by adopting splines, so that the use requirement of high speed and heavy load can be met. The bevel gear pair is adopted for meshing transmission, the transmission direction of the input shaft of the generator is changed, and the interference of the installation position between the generator and the propeller can be effectively avoided; meanwhile, an independent lubricating oil loop system is adopted, so that the lubrication of rotating parts such as a speed reducer, a bearing and the like is more effective. And cover novel material GORE-TEX membrane in atmospheric pressure balance pipeline, not only can effectively prevent that the reduction gear thermal energy from leading to the internal pressure increase, still can effectively prevent that the lubricating oil from revealing. And a lubricating oil heat dissipation system is designed in a matching way, so that the temperature of the lubricating oil can be maintained in a proper range, and the phenomena of lubricating oil failure, tooth surface pitting, abrasion, gluing and the like caused by the temperature rise of the lubricating oil are avoided. Therefore, the speed reducer not only meets the use requirements of high-speed heavy load and shunt power generation of the miniature turboprop engine, but also effectively enhances the use performance of the speed reducer of the engine and prolongs the service life of the speed reducer.
Drawings
FIG. 1 is a schematic illustration of the construction of the reducer of the present invention;
FIG. 2 is a schematic diagram of the structure of an oil circuit system formed by a reducer according to the present invention;
FIG. 3 is a schematic diagram of a heat dissipation circuit of the micro-system of the present invention;
FIG. 4 is a schematic view showing an internal structure of the decelerator according to the present invention;
fig. 5 is a partial structural sectional view of a decelerator according to the present invention.
Wherein, the names corresponding to the reference numbers in the drawings are:
1-reducer housing, 2-high-speed shaft, 3-high-speed pinion, 4-high-speed bull gear A, 5-intermediate shaft A, 6-low-speed pinion, 7-low-speed bull gear, 8-low-speed shaft, 9-bevel gear A, 10-bevel gear B, 11-generator power input shaft, 12-bearing A, 13-adjusting washer A, 14-sealing rubber ring A, 15-lock nut, 16-bearing B, 17-adjusting washer B, 18-bearing C, 19-rubber ring A, 20-oil seal A, 21-circlip A, 22-bearing D, 23-screw A, 24-spring washer A, 25-sealing rubber ring B, 26-bearing E, 27-screw hole A, 28-adjusting washer C, 29-rubber ring B, 30-oil seal B, 31-circlip B, 32-spring washer B, 33-screw B, 34-nut, 35-bearing F, 36-bearing I, 37-adjusting gaskets D, 38-bearings J, 39-screw hole B, 40-lubricating oil hole A, 41-reducer air hole, 42-lubricating oil hole B, 43-lubricating oil tank, 44-lubricating oil pump, 45-oil filter, 46-micro-channel heat exchange part, 47-compressor, 48-heat exchange fin, 49-throttle valve, 50-coolant liquid storage tank, 60-high-speed large gear B, 61-intermediate shaft B and 62-reducer.
Detailed Description
The present invention will be described in further detail with reference to the following examples:
examples
As shown in fig. 1 to 5, a speed reducer 62 of a high-speed heavy-load power split-type speed reducer system of a micro turboprop engine includes a speed reducer housing 1, a high-speed gear set, a low-speed gear set, and a direction-changing bevel gear set, wherein the high-speed gear set, the low-speed gear set, and the direction-changing bevel gear set are located inside the speed reducer housing 1, the high-speed gear set and the low-speed gear set are parallel to each other, the speed reducer housing 1 has a power input end of a generator, a high-speed side, and a low-speed side corresponding to the high-speed side, the high-speed gear set is correspondingly installed on the high-speed side of the speed reducer housing 1, the low-speed gear set is correspondingly installed on the low-speed side of the speed; the high-speed gear set comprises a high-speed pinion 3, a high-speed bull gear A4 and a high-speed bull gear B60, the high-speed bull gear A4 and the high-speed bull gear B60 are respectively engaged with the high-speed pinion 3 through symmetrical gears, a high-speed shaft 2 is mounted in the center of the high-speed pinion 3, and the high-speed shaft 2 is mounted in the center of the high-speed side of the reducer shell 1 in a penetrating and matching mode; the generator power input end of the speed reducer shell 1 is provided with a generator power input shaft 11 in a penetrating and matching mode, the direction change bevel gear set comprises a bevel gear A9 and a bevel gear B10 in gear engagement with the bevel gear A9, the end part of the generator power input shaft 11 is fixed at the center of the bevel gear B10, the bevel gear A9 is parallel to the high-speed large gear B60, and the bevel gear A9 is in power connection with the high-speed large gear B60 through an intermediate shaft B61; the low-speed gear set comprises a low-speed pinion 6 and a low-speed bull gear 7 which is in gear engagement with the low-speed pinion 6, the low-speed pinion 6 and the high-speed bull gear A4 are in power connection through an intermediate shaft A5, and a low-speed shaft 8 penetrating through the low-speed side of the reducer shell 1 is mounted in the center of the low-speed bull gear 7.
As shown in fig. 2, the reducer system of the present invention further includes a lubricating oil tank 43, a lubricating oil pump 44 and an oil strainer 45, as shown in fig. 5, a reducer housing 1 of the reducer 62 is provided with a lubricating oil hole a40 and a lubricating oil hole B42 communicated with the interior of the reducer housing 1, the interior of the reducer housing 1 is provided with a lubricating oil flow clearance passage communicated with the lubricating oil hole a40 and the lubricating oil hole B42, a lubricating oil outlet of the lubricating oil pump 44 is hermetically communicated with the lubricating oil hole a40, the lubricating oil hole B42 is hermetically communicated with a lubricating oil recovery inlet of the oil strainer 45 through a pipeline, a lubricating oil inlet of the lubricating oil pump 44 is communicated with a lubricating oil outlet of the lubricating oil tank 43, and a lubricating oil outlet of the oil strainer 45 is communicated with a lubricating oil inlet of the lubricating oil; the oil filter 45 has a filter element for filtering the recovered lubricating oil therein.
As shown in fig. 3, the retarder system of the present invention further comprises a compressor 47 and heat exchanging fins 48, the cooling agent storage tank 50 and the high-pressure gas circuit, the inside of the lubricating oil tank 43 is provided with a micro-channel heat exchange part 46, the micro-channel heat exchange part 46 is provided with a cooling agent inlet pipe and a cooling agent outlet pipe, a cooling agent outlet of the cooling agent storage tank 50 is hermetically communicated with the cooling agent inlet pipe of the micro-channel heat exchange part 46 through a pipeline, the inside of the heat exchange fin 48 is provided with a heat exchange coil, the heat exchange coil of the heat exchange fin 48 is provided with a cooling agent inlet end and a cooling agent outlet end, the cooling agent outlet end of the heat exchange fin 48 is hermetically communicated with the cooling agent inlet of the cooling agent storage tank 50 through a pipeline, the cooling agent outlet pipe of the micro-channel heat exchange part 46 is hermetically communicated with the cooling agent inlet of the compressor 47 through a pipeline; a throttle valve 49 is installed on a pipe between the coolant outlet end of the heat exchanging fin 48 and the coolant inlet of the coolant reservoir 50. As shown in fig. 5, a reducer air hole 41 communicated with the inside of the reducer housing 1 is formed in the reducer housing 1 of the reducer 62, the reducer air hole 41 is hermetically communicated with a high-pressure air path through an air pressure balance pipeline, and a GORE-TEX film is coated inside or/and outside the air pressure balance pipeline. According to the invention, the GORE-TEX film is covered in the air pressure balance pipeline, and the oil filter screen is designed at the front end of the film to filter oil contained in the air, so that a large amount of lubricating oil is prevented from being attached to the GORE-TEX film, and the air permeability of the GORE-TEX film is further influenced. The novel GORE-TEX film can effectively prevent the lubricating oil from leaking and has the characteristic of strong air permeability, so that the invention not only can effectively prevent the internal pressure from increasing caused by the thermal expansion of the speed reducer, but also can effectively prevent the lubricating oil from leaking.
According to the invention, a micro-channel heat exchange component 46 is designed and installed in a lubricating oil tank 43 by utilizing a counter-flow principle, a coolant flows into the micro-channel heat exchange component 46 from a coolant liquid storage tank 50 under the pumping action of a compressor 47 so as to achieve the purpose of taking away heat in the lubricating oil tank 43 in real time, then the coolant is compressed by the compressor 47 and enters an external heat exchange fin 48 to release the heat into air, and finally the coolant returns to the coolant liquid storage tank 50 after being throttled and depressurized by a throttle valve 49 so as to realize the strict control of the temperature of lubricating oil, thereby avoiding the phenomena of tooth surface abrasion, pitting corrosion, gluing and the like caused by the failure of the lubricating oil due to the temperature rise of the lubricating.
As shown in fig. 4, the high-speed pinion 3 and the high-speed shaft 2 are fixed by a screw C with opposite rotation directions, and the center of the high-speed pinion 3 and the end of the high-speed shaft 2 are locked and positioned by a bolt 34; the low-speed shaft 8 and the low-speed large gear 7 are in threaded connection and fixed through screws B33 with opposite screwing directions, and a spring gasket B32 is installed on the screw B33; the low-speed stage pinion 6 adopts a gear shaft structure, and the low-speed stage bull gear 7 and the bevel gear B10 adopt a web type structure. As shown in fig. 4, a bearing C18 is provided on the high-speed side of the reducer case 1 corresponding to the intermediate shaft B61, a bearing E26 is provided on the low-speed side of the reducer case 1 corresponding to the intermediate shaft B61, one end of the intermediate shaft B61 is correspondingly rotatably mounted in the bearing C18, the other end of the intermediate shaft B61 is correspondingly rotatably mounted in the bearing E26, an adjusting shim C28 for positioning the bevel gear a9 is mounted between the bevel gear a9 and the bearing E26, and an adjusting shim B17 for positioning the high-speed bull gear B60 is mounted between the high-speed bull gear B60 and the bearing C18; the high-speed side of the reducer shell 1 is provided with a bearing A12 corresponding to the intermediate shaft A5, the low-speed side of the reducer shell 1 is provided with a bearing J38 corresponding to the intermediate shaft A5, one end of the intermediate shaft A5 is correspondingly and rotatably mounted in the bearing A12, the other end of the intermediate shaft A5 is correspondingly and rotatably mounted in the bearing J38, and an adjusting gasket A13 for positioning the high-speed large gear A4 is mounted between the high-speed large gear A4 and the bearing A12.
As shown in fig. 4, the high-speed gear wheel B60, the high-speed pinion 3, the high-speed gear wheel a4, the low-speed pinion 6 and the low-speed gear wheel 7 are all bevel gears; the bevel gear A9 and the intermediate shaft B61 are in splined connection, the high-speed large gear B60 and the intermediate shaft B61 are in splined connection, the high-speed small gear 3 and the high-speed shaft 2 are in splined connection, the high-speed large gear A4 and the intermediate shaft A5 are in splined connection, and the low-speed small gear 6 and the intermediate shaft A5 are in splined connection. As shown in fig. 4, the bevel gear a9 is positioned and mounted on the intermediate shaft B61 by a shoulder on the bevel gear a9, the high-speed gear B60 is positioned and mounted on the intermediate shaft B61 by a shoulder on the high-speed gear B60, the high-speed pinion 3 is positioned and mounted on the high-speed shaft 2 by a shoulder on the high-speed gear 3, the high-speed gear a4 is positioned and mounted on the intermediate shaft a5 by a shoulder on the high-speed gear a4, and the low-speed pinion 6 is positioned and mounted on the intermediate shaft a5 by a shoulder on the low-speed pinion 6.
As shown in fig. 4, a bearing B16 which is rotationally matched with the high-speed shaft 2 is installed on the high-speed side of the reducer housing 1, a sealing rubber ring a14 is arranged between the bearing B16 and the high-speed side of the reducer housing 1, and the high-speed shaft 2 and the bearing B16 are positioned and locked through a shaft shoulder and a locking nut 15; a bearing D22 which is in mutual rotating fit with the power input shaft 11 is arranged at the power input end of the generator of the speed reducer housing 1, an oil seal A20 is arranged between the bearing D22 and a bevel gear B10, a rubber ring A19 is arranged between the bearing D22 and the power input end of the generator of the speed reducer housing 1 in a sealing way, an elastic retainer ring A21 is further arranged at the outer side of the bearing D22, and the power input shaft 11 of the generator and the bevel gear B10 are fixedly connected through a screw A23 with a spring gasket A24; bearing I36 rotationally matched with low-speed shaft 8 is installed on the low-speed side of reducer housing 1, bearing F35 is installed between low-speed gear wheel 7 and bearing I36, oil seal B30 is installed between bearing I36 and bearing F35, rubber ring B29 is installed between bearing I36 and the low-speed side of reducer housing 1 in a sealing mode, elastic retainer B31 is arranged on the outer side of bearing I36, and adjusting gasket D37 is arranged between bearing F35 and low-speed gear wheel 7. As shown in fig. 4, the reducer case 1 includes a front end cover and a rear end cover, the front end cover of the reducer case 1 is provided with a screw hole B39, the rear end cover of the reducer case 1 is provided with a screw hole a27 corresponding to the screw hole B39, the front end cover and the rear end cover of the reducer case 1 are connected by screws, and a plurality of sealing rubber rings B25 are hermetically connected between the front end cover and the rear end cover of the reducer case 1.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.

Claims (7)

1. The utility model provides a high-speed heavy load power shunting reduction gear system of miniature turboprop engine which characterized in that: the speed reducer (62) comprises a speed reducer shell (1), a high-speed gear set, a low-speed gear set and a turning bevel gear set, wherein the high-speed gear set, the low-speed gear set and the turning bevel gear set are positioned inside the speed reducer shell (1), the high-speed gear set and the low-speed gear set are parallel to each other, the speed reducer shell (1) is provided with a power input end of a generator, a high-speed side and a low-speed side corresponding to the high-speed side, the high-speed gear set is correspondingly installed on the high-speed side of the speed reducer shell (1), the low-speed gear set is correspondingly installed on the low-speed side of the speed reducer shell (1), and the turning bevel gear set is correspondingly installed at a position, close to the power; the high-speed gear set comprises a high-speed pinion (3), a high-speed gearwheel A (4) and a high-speed gearwheel B (60), the high-speed gearwheel A (4) and the high-speed gearwheel B (60) are respectively meshed with symmetrical gears of the high-speed pinion (3), a high-speed shaft (2) is mounted in the center of the high-speed pinion (3), and the high-speed shaft (2) is mounted in the center of the high-speed side of the reducer shell (1) in a penetrating and matching manner; the power input end of a generator of the speed reducer shell (1) is provided with a generator power input shaft (11) in a penetrating and matching mode, the direction-changing bevel gear set comprises a bevel gear A (9) and a bevel gear B (10) in gear engagement with the bevel gear A (9), the end part of the generator power input shaft (11) is fixed at the center of the bevel gear B (10), and the bevel gear A (9) is in power connection with the high-speed large gear B (60) through an intermediate shaft B (61); the low-speed gear set comprises a low-speed pinion (6) and a low-speed bull gear (7) in gear engagement with the low-speed pinion (6), the low-speed pinion (6) is in power connection with the high-speed bull gear A (4) through an intermediate shaft A (5), and a low-speed shaft (8) penetrating through the low-speed side of the reducer shell (1) is mounted in the center of the low-speed bull gear (7);
the lubricating oil filter is characterized by further comprising a lubricating oil tank (43), a lubricating oil pump (44) and an oil filter (45), wherein a lubricating oil hole A (40) and a lubricating oil hole B (42) which are communicated with the inside of the speed reducer shell (1) are formed in the speed reducer shell (1) of the speed reducer (62), a lubricating oil flowing clearance channel communicated with the lubricating oil hole A (40) and the lubricating oil hole B (42) is formed in the speed reducer shell (1), a lubricating oil outlet of the lubricating oil pump (44) is hermetically communicated with the lubricating oil hole A (40), the lubricating oil hole B (42) is hermetically communicated with a lubricating oil recovery inlet of the oil filter (45) through a pipeline, a lubricating oil inlet of the lubricating oil pump (44) is communicated with a lubricating oil outlet of the lubricating oil tank (43), and a lubricating oil outlet of the oil filter (45) is communicated with a lubricating oil inlet of the lubricating oil tank (43) through a; the inside of the oil filter (45) is provided with a filter element for filtering and treating recovered lubricating oil;
still include compressor (47), heat transfer fin (48), coolant liquid storage pot (50), smooth oil tank (43) inside is equipped with microchannel heat transfer part (46), microchannel heat transfer part (46) have coolant import pipe and coolant outlet pipe, the coolant outlet of coolant liquid storage pot (50) passes through the airtight intercommunication of pipeline with the coolant import pipe of microchannel heat transfer part (46), heat transfer fin (48) inside has heat transfer coil, the heat transfer coil of heat transfer fin (48) has coolant entry end and coolant outlet end, the coolant outlet end of heat transfer fin (48) passes through the airtight intercommunication of pipeline with the coolant entry of coolant liquid storage pot (50), the coolant outlet pipe of microchannel heat transfer part (46) passes through the airtight intercommunication of pipeline with the coolant inlet of compressor (47), the coolant outlet of compressor (47) and the coolant inlet end of heat transfer fin (48) pass through the airtight even of pipeline Opening; a throttling valve (49) is arranged on a pipeline between the coolant outlet end of the heat exchange fin (48) and the coolant inlet of the coolant liquid storage tank (50);
the gas-liquid separator is characterized by further comprising a high-pressure gas circuit, wherein a speed reducer gas hole (41) communicated with the inside of the speed reducer shell (1) is formed in the speed reducer shell (1) of the speed reducer (62), the speed reducer gas hole (41) is communicated with the high-pressure gas circuit in a sealed mode through a gas pressure balance pipeline, and a GORE-TEX film is covered inside or/and outside the gas pressure balance pipeline.
2. The high-speed heavy-load power-split speed reducer system for a micro turboprop according to claim 1, wherein: the high-speed pinion (3) and the high-speed shaft (2) are in threaded connection and fixation through screws C with opposite rotation directions, and the center of the high-speed pinion (3) and the end part of the high-speed shaft (2) are locked and positioned through bolts (34); the low-speed shaft (8) and the low-speed large gear (7) are in threaded connection and fixed through a screw B (33) with opposite screwing directions, and a spring gasket B (32) is installed on the screw B (33); the low-speed pinion (6) adopts a gear shaft structure, and the low-speed bull gear (7) and the bevel gear B (10) adopt a radial plate type structure.
3. The high-speed heavy-load power-split speed reducer system for a micro turboprop according to claim 1, wherein: the high-speed side of the speed reducer shell (1) is provided with a bearing C (18) corresponding to the intermediate shaft B (61), the low-speed side of the speed reducer shell (1) is provided with a bearing E (26) corresponding to the intermediate shaft B (61), one end of the intermediate shaft B (61) is correspondingly and rotatably mounted in the bearing C (18), the other end of the intermediate shaft B (61) is correspondingly and rotatably mounted in the bearing E (26), an adjusting gasket C (28) for positioning the bevel gear A (9) is mounted between the bevel gear A (9) and the bearing E (26), and an adjusting gasket B (17) for positioning the high-speed gearwheel B (60) is mounted between the high-speed gearwheel B (60) and the bearing C (18); the utility model discloses a speed reducer casing, including reduction gear casing (1), bearing J (38), jackshaft A (5) and adjusting shim A (13) are installed to the corresponding rotation of jackshaft A (5) in the high-speed side of reduction gear casing (1) low-speed side, reduction gear casing (1) low-speed side is equipped with bearing J (38) corresponding jackshaft A (5), jackshaft A (5) one end tip is corresponding to rotate and is installed in bearing J (38), install between high-speed level gear wheel A (4) and bearing A (12) and be used for fixing a position high-speed level gear wheel A (4).
4. The high-speed heavy-load power-split speed reducer system for a micro turboprop according to claim 1, wherein: the high-speed bull gear B (60), the high-speed pinion gear (3), the high-speed bull gear A (4), the low-speed pinion gear (6) and the low-speed bull gear (7) are all bevel gears; bevel gear A (9) and jackshaft B (61) adopt splined connection, high-speed level gear wheel B (60) and jackshaft B (61) adopt splined connection, high-speed level pinion (3) and high-speed shaft (2) adopt splined connection, high-speed level gear wheel A (4) and jackshaft A (5) adopt splined connection, low-speed level pinion (6) and jackshaft A (5) adopt splined connection.
5. The high-speed heavy-load power-split speed reducer system for a micro turboprop according to claim 1, wherein: bevel gear A (9) are installed on jackshaft B (61) through the shoulder location on bevel gear A (9), high-speed level gear wheel B (60) are installed on jackshaft B (61) through the shoulder location on high-speed level gear wheel B (60), high-speed level pinion (3) are installed on high-speed axle (2) through the shoulder location on high-speed level pinion (3), high-speed level gear wheel A (4) are installed on jackshaft A (5) through the shoulder location on high-speed level gear wheel A (4), low-speed level pinion (6) are installed on jackshaft A (5) through the shoulder location on low-speed level pinion (6).
6. The high-speed heavy-load power-split speed reducer system for a micro turboprop according to claim 1, wherein: a bearing B (16) which is in mutual rotating fit with the high-speed shaft (2) is arranged on the high-speed side of the speed reducer shell (1), and a sealing rubber ring A (14) is arranged between the bearing B (16) and the high-speed side of the speed reducer shell (1); a bearing D (22) which is in mutual rotating fit with the generator power input shaft (11) is installed at the generator power input end of the speed reducer shell (1), an oil seal A (20) is installed between the bearing D (22) and the bevel gear B (10), a rubber ring A (19) is installed between the bearing D (22) and the generator power input end of the speed reducer shell (1) in a sealing mode, an elastic retainer ring A (21) is further arranged on the outer side of the bearing D (22), and the generator power input shaft (11) and the bevel gear B (10) are further fixedly connected through a screw A (23) with a spring gasket A (24); reduction gear housing (1) low-speed side install with low-speed axle (8) rotation fit's bearing I (36) each other, install bearing F (35) between low-speed level gear wheel (7) and bearing I (36), install oil blanket B (30) between bearing I (36) and bearing F (35), sealing installation has rubber ring B (29) between bearing I (36) and reduction gear housing (1) low-speed side, the bearing I (36) outside is equipped with circlip B (31), be equipped with adjusting shim D (37) between bearing F (35) and low-speed level gear wheel (7).
7. The high-speed heavy-load power-split speed reducer system for a micro turboprop according to claim 1, wherein: the speed reducer casing (1) comprises a front end cover and a rear end cover, a screw hole B (39) is formed in the front end cover of the speed reducer casing (1), a screw hole A (27) corresponding to the screw hole B (39) is formed in the rear end cover of the speed reducer casing (1), the front end cover and the rear end cover of the speed reducer casing (1) are connected through screws, and a plurality of sealing rubber rings B (25) are connected between the front end cover and the rear end cover of the speed reducer casing (1) in a sealing mode.
CN201711105946.4A 2017-11-10 2017-11-10 High-speed heavy-load power split-flow type speed reducer system of micro turboprop engine Active CN107893832B (en)

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CN109058388B (en) * 2018-09-30 2024-06-11 韦天一 Main reducer of drive axle
FR3090786B1 (en) * 2018-12-21 2020-12-04 Safran Trans Systems LUBRICATING OIL DISPENSER FOR AN AIRCRAFT TURBOMACHINE MECHANICAL REDUCER
US11143234B2 (en) * 2019-03-02 2021-10-12 Superturbo Technologies, Inc. Fluid damping system for traction drive

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201843978U (en) * 2010-02-07 2011-05-25 吴为国 Reduction gearbox and impeller type oxygen enricher with same
CN202274072U (en) * 2011-09-12 2012-06-13 宿迁市强峰机械制造公司 Oil cooling circulation system of speed reducer
CN103939529A (en) * 2014-03-14 2014-07-23 广州明珞汽车装备有限公司 Gear transmission mechanism of electrode coping and cap replacing all-in-one machine
CN106028884A (en) * 2014-02-28 2016-10-12 雀巢产品技术援助有限公司 Beverage system for providing cold beverage
CN106358467A (en) * 2016-11-30 2017-02-01 广西大学 Power output steering device for lawn fertilizer applicator
WO2017029125A1 (en) * 2015-08-18 2017-02-23 Mahle International Gmbh Actuator for adjusting an actuating element

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201843978U (en) * 2010-02-07 2011-05-25 吴为国 Reduction gearbox and impeller type oxygen enricher with same
CN202274072U (en) * 2011-09-12 2012-06-13 宿迁市强峰机械制造公司 Oil cooling circulation system of speed reducer
CN106028884A (en) * 2014-02-28 2016-10-12 雀巢产品技术援助有限公司 Beverage system for providing cold beverage
CN103939529A (en) * 2014-03-14 2014-07-23 广州明珞汽车装备有限公司 Gear transmission mechanism of electrode coping and cap replacing all-in-one machine
WO2017029125A1 (en) * 2015-08-18 2017-02-23 Mahle International Gmbh Actuator for adjusting an actuating element
CN106358467A (en) * 2016-11-30 2017-02-01 广西大学 Power output steering device for lawn fertilizer applicator

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