CN103043217A - Power output assembly of aviation piston engine - Google Patents
Power output assembly of aviation piston engine Download PDFInfo
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- CN103043217A CN103043217A CN2012105930012A CN201210593001A CN103043217A CN 103043217 A CN103043217 A CN 103043217A CN 2012105930012 A CN2012105930012 A CN 2012105930012A CN 201210593001 A CN201210593001 A CN 201210593001A CN 103043217 A CN103043217 A CN 103043217A
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- piston engine
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Abstract
The invention discloses a power output assembly of an aviation piston engine and belongs to the field of helicopter transmission systems using reciprocating type piston engines as power device. The power output assembly comprises a shell, a bearing cap, an output shaft, a working cylinder of a diaphragm type clutch hydraulic release mechanism and a belt pulley, the integral type shell is directly connected with an engine body, the shell and the bearing cap support the output shaft through a front end bearing and a rear end bearing, a lubricating oil storage tank is formed by the shell, the bearing cap and an oil seal, the front end of the output shaft is connected with a driven disc of a diaphragm type clutch through a spline, and the rear end of the output shaft is connected with the belt pulley used for belt driving. By the aid of modular design, the whole power output assembly of the aviation piston engine can be applied to multiple types of aviation piston engines with same mounting flanges, is free of additional support points and lifting points, and is easily arranged in the layout of a whole helicopter transmission system. The bearings of the output shaft are lubricated by oil bath, so that high power can be transmitted. The hydraulic release mechanism is adopted for the diaphragm type clutch, and hydraulic oil and bearing oil are of the same kind, so that the power output assembly is convenient to use and maintain.
Description
Technical field
The present invention relates to a kind of aviation piston engine power output assembly, specifically, is about the helicopter take reciprocating piston engine as engine installation, is in a kind of power take-off implement between the driving engine and main reduction gear in its driving system.
Background technology
Mini Tele-Copter driving system take aviation piston engine as engine installation generally is comprised of driving engine, main reduction gear, main rotor shaft, tail transmission shaft, tail reducer, tail-rotor axle etc.Wherein, driving engine passes to main reduction gear by gear transmission or with the mode of transmission with power.
US Patent No. 2007/0262197 A1 discloses a kind of light-duty co-axial helicopter, and this helicopter is take aviation piston engine as power, engine output by centrifugal clutch and overriding clutch unit after, via a transmission shaft driving pulley.But its transmission shaft is longer, supports complicated, lubricated difficult.
German patent DE 3706379 A1 disclose a kind of supporting way of helicopter power output assembly, pass through band type of drive transmitted power between the driving engine of this helicopter and the main reduction gear.But be designed with supporting mechanism between driving pulley and the driven pulley in this scheme band transmission, structure is heavy, the unrealized modular design of power take-off implement that engine output shaft and driving pulley consist of, and commonality is relatively poor.
Traditional Mini Tele-Copter take aviation piston engine as engine installation, the transmission shaft backup bearing of its engine power output assembly adopts grease lubrication or oil bath lubrication more, its power-transfer clutch adopts centrifugal clutch and overriding clutch series connection to use more, has no the use of diaphragm clutch.
Summary of the invention
The present invention has overcome deficiency of the prior art, and the aviation piston engine power output assembly of a kind of compact conformation, highly versatile, applying flexible, modular design is provided.
The invention is characterized in, be a kind of power take-off implement between the reciprocating piston engine and main reduction gear in the Helicopter Transmission System that is in, and contains clutch release slave cylinder and the belt wheel of housing, bearing cap shim, output shaft, diaphragm clutch hydraulic pressure separating mechanism, wherein:
Housing, all-in-one-piece, front end links to each other with described reciprocating piston engine through flange, the rear end links to each other with described bearing cap shim, described housing and bearing cap shim consist of a lubricating oil storage tank, top at described housing, have the mounting hole of filling bearing oil and installation respirator, the bottom has one for the oil drain hole of the hydraulic main cylinder make-up oil of the hydraulic pressure separating mechanism of the described diaphragm clutch of changing the bearing oil in the described petrol storage tank and namely exsomatizing outside aviation piston engine power output assembly, also have the hole of passing through of a high pressure fuel pipe, so that described hydraulic main cylinder is enclosed within the clutch release slave cylinder conveying high-pressure oil of the diaphragm clutch hydraulic pressure separating mechanism on the described output shaft to pine by this high pressure fuel pipe;
Output shaft, front axle journal via the front end bearings of front end oil sealing sealing in the bearing hole of described housing, rear axle journal is supported in the bearing hole of described bearing cap shim via the rear end bearing of rear end oil sealing sealing, the front end of described output shaft links to each other with the clutch plate of described diaphragm clutch by spline, and the rear end of this output shaft is connected with described belt wheel.
The described front side bearing of the employed hydraulic oil of diaphragm clutch hydraulic pressure separating mechanism and output shaft and the employed lubricating oil of rear end bearing are the oil plants of same breed.
Compared with prior art, the present invention adopts modular design, whole engine power output assembly can be used in the many moneys aviation piston engine with identical mounting flange, and this assembly need not extra support point and suspension centre, easier layout in the layout of the whole driving system of helicopter.Output shaft bearing of the present invention is oil bath lubrication, can transmit larger power.Diaphragm clutch of the present invention adopts hydraulic pressure separating mechanism, and hydraulic oil and bearing oil are selected the same oil plant, and operation and maintenance is convenient.Clutch end adopts the mode with transmission, and flexible arrangement can be selected the belt wheel transmission of the forms such as V band, Timing Belt, flat rubber belting.
Description of drawings
Fig. 1 is the overall schematic of aviation piston engine power output assembly of the present invention;
Fig. 2 is the front view of aviation piston engine power output assembly;
Fig. 3 is the right elevation of aviation piston engine power output assembly;
Fig. 4 is the cut-away view of aviation piston engine power output assembly;
Fig. 5 is a kind of embodiment scheme drawing with electric pushrod controlling diaphragm lamella clutch hydraulic main cylinder.
The specific embodiment
Technical scheme of the present invention is: a kind of aviation piston engine power output assembly, comprise housing 1, bearing cap shim 3, output shaft 7, the clutch release slave cylinder 6 of diaphragm clutch hydraulic pressure separating mechanism, belt wheel 4, unitized housing directly links to each other with engine body, housing and bearing cap shim support output shaft by front side bearing 10 and rear end bearing 11, consist of lubricating oil storage tank by housing 1 and bearing cap shim 3 and oil sealing, the output shaft front end links to each other with the diaphragm clutch clutch plate by spline, and the output shaft rear end connects the belt wheel 4 that is used for transmission.
Housing 1 links to each other with engine body by flange 8, and housing 1 need not other strong point and suspension centre.Output shaft 7 is supported on housing 1 and the bearing cap shim 3 by front side bearing 10, rear end bearing 11.The front side bearing 10 of output shaft 7 and rear end bearing 11 adopt oil bath lubrication, housing 1, bearing cap shim 3, front end oil sealing 13, rear end oil sealing 12 consist of petrol storage tank, respirator 2 is installed on the housing 1, be positioned at petrol storage tank vertical directly over, be used for guaranteeing the petrol storage tank inside and outside air pressure balance, simultaneously can be by the mounting hole filling bearing oil of respirator 2, oil drain hole 5 is opened on housing 1, be positioned at petrol storage tank vertical under, be used for changing bearing oil and in the course of the work to hydraulic main cylinder 14 make-up oils of diaphragm clutch hydraulic pressure separating mechanism.The front side bearing 10 of the employed hydraulic oil of diaphragm clutch hydraulic pressure separating mechanism and output shaft 7 and rear end bearing 11 employed lubricating oils are the same oil plant, all use bearing oil.The hydraulic main cylinder 14 of diaphragm clutch hydraulic pressure separating mechanism is by the clutch release slave cylinder 6 conveying high-pressures oil of high pressure fuel pipe 9 to diaphragm clutch hydraulic pressure separating mechanism, and oil drain hole 5 is transmitted back to the petrol storage tank that is made of housing 1, bearing cap shim 3, front end oil sealing 13, rear end oil sealing 12 again by oil pipe to hydraulic main cylinder 14 make-up oils of diaphragm clutch hydraulic pressure separating mechanism or with unnecessary lubricating oil.Output shaft 7 front ends link to each other with the diaphragm clutch clutch plate by spline, and output shaft 7 rear ends are connected with belt wheel 4.
Below in conjunction with accompanying drawing and the specific embodiment, the present invention is described in further detail:
Such as Fig. 1 ~ shown in Figure 4, a kind of aviation piston engine power output assembly, it mainly comprises the clutch release slave cylinder 6 of housing 1, bearing cap shim 3, output shaft 7, diaphragm clutch hydraulic pressure separating mechanism and belt wheel 4 etc.Described housing 1 links to each other with the aviation piston engine body by flange 8, the horsepower output of aviation piston engine is by bent axle, flywheel, diaphragm clutch clutch plate and be passed to output shaft 7, output shaft 7 direct driving pulleys 4, belt wheel 4 directly drives main rotor shaft after with the mode of transmission transmission of power being slowed down to the Helicopter Main Reducer input shaft or by the band transmission.The form of belt wheel 4 can according to concrete needs, be selected the belt wheel transmission of the forms such as V band, Timing Belt, flat rubber belting.
As shown in Figure 5, it is a kind of embodiment of a kind of hydraulic main cylinder 14 with electric pushrod 15 controlling diaphragm lamella clutch hydraulic pressure separating mechanisms of the present invention, electric pushrod 15 receives the control command of diaphragm clutch separation or combination, and the hydraulic main cylinder 14 of controlling diaphragm lamella clutch hydraulic pressure separating mechanism is made corresponding actions, high pressure oil is made corresponding actions by the clutch release slave cylinder 6 of high pressure fuel pipe 9 controlling diaphragm lamella clutch hydraulic pressure separating mechanisms, and the controlling diaphragm lamella clutch separates or combination.The bearing oil petrol storage tank that is made of housing 1, bearing cap shim 3, front end oil sealing 13, rear end oil sealing 12 is communicated with the hydraulic main cylinder 14 of diaphragm clutch hydraulic pressure separating mechanism by oil drain hole 5.
Above content be in conjunction with concrete preferred embodiment to further specifying that the present invention does, can not assert that implementation of the present invention is confined to these explanations.For the those of ordinary skill of technical field of the present invention, without departing from the inventive concept of the premise, can also make some simple deduction or replace, all should be considered as belonging to protection scope of the present invention.
Claims (2)
1. aviation piston engine power is exported assembly, it is characterized in that, it is a kind of power take-off implement between the reciprocating piston engine and main reduction gear in the Helicopter Transmission System that is in, the clutch release slave cylinder and the belt wheel that contain housing, bearing cap shim, output shaft, diaphragm clutch hydraulic pressure separating mechanism, wherein:
Housing, all-in-one-piece, front end links to each other with described reciprocating piston engine through flange, the rear end links to each other with described bearing cap shim, described housing and bearing cap shim consist of a lubricating oil storage tank, top at described housing, have the mounting hole of filling bearing oil and installation respirator, the bottom has one for the oil drain hole of the hydraulic main cylinder make-up oil of the hydraulic pressure separating mechanism of the described diaphragm clutch of changing the bearing oil in the described petrol storage tank and namely exsomatizing outside aviation piston engine power output assembly, also have the hole of passing through of a high pressure fuel pipe, so that described hydraulic main cylinder is enclosed within the clutch release slave cylinder conveying high-pressure oil of the diaphragm clutch hydraulic pressure separating mechanism on the described output shaft to pine by this high pressure fuel pipe
Output shaft, front axle journal via the front end bearings of front end oil sealing sealing in the bearing hole of described housing, rear axle journal is supported in the bearing hole of described bearing cap shim via the rear end bearing of rear end oil sealing sealing, the front end of described output shaft links to each other with the clutch plate of described diaphragm clutch by spline, and the rear end of this output shaft is connected with described belt wheel.
2. aviation piston engine power according to claim 1 is exported assembly, it is characterized in that the described front side bearing of the employed hydraulic oil of diaphragm clutch hydraulic pressure separating mechanism and output shaft and the employed lubricating oil of rear end bearing are the oil plants of same breed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210593001.2A CN103043217B (en) | 2012-12-31 | 2012-12-31 | Power output assembly of aviation piston engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210593001.2A CN103043217B (en) | 2012-12-31 | 2012-12-31 | Power output assembly of aviation piston engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103043217A true CN103043217A (en) | 2013-04-17 |
| CN103043217B CN103043217B (en) | 2015-02-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210593001.2A Active CN103043217B (en) | 2012-12-31 | 2012-12-31 | Power output assembly of aviation piston engine |
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| CN (1) | CN103043217B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103573864A (en) * | 2013-10-17 | 2014-02-12 | 清华大学 | Electronic-control hydraulic control system for diaphragm-type clutch of aviation piston engine |
| CN106763658A (en) * | 2016-12-27 | 2017-05-31 | 中国南方航空工业(集团)有限公司 | Reduction case |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4840330A (en) * | 1987-02-27 | 1989-06-20 | Dr. Ing. H.C.F. Porsche Aktiengesellschaft | Suspension system for a drive assembly of a helicopter |
| CN2864222Y (en) * | 2005-11-16 | 2007-01-31 | 张耿 | Clutch operation device with bond buffer function |
| CN201025116Y (en) * | 2006-11-23 | 2008-02-20 | 河南正工机械制造有限公司 | Direct output dynamic structure of an engine |
| EP1914404A1 (en) * | 2006-10-20 | 2008-04-23 | Kwang Yang Motor Co., Ltd. | Vehicle transmission |
| CN102062163A (en) * | 2009-11-11 | 2011-05-18 | 通用汽车环球科技运作公司 | Device for mechanically disengaging an automatically engaged clutch device |
| CN202578903U (en) * | 2012-05-02 | 2012-12-05 | 安徽华菱汽车有限公司 | Power takeoff at rear end of engine |
-
2012
- 2012-12-31 CN CN201210593001.2A patent/CN103043217B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4840330A (en) * | 1987-02-27 | 1989-06-20 | Dr. Ing. H.C.F. Porsche Aktiengesellschaft | Suspension system for a drive assembly of a helicopter |
| CN2864222Y (en) * | 2005-11-16 | 2007-01-31 | 张耿 | Clutch operation device with bond buffer function |
| EP1914404A1 (en) * | 2006-10-20 | 2008-04-23 | Kwang Yang Motor Co., Ltd. | Vehicle transmission |
| CN201025116Y (en) * | 2006-11-23 | 2008-02-20 | 河南正工机械制造有限公司 | Direct output dynamic structure of an engine |
| CN102062163A (en) * | 2009-11-11 | 2011-05-18 | 通用汽车环球科技运作公司 | Device for mechanically disengaging an automatically engaged clutch device |
| CN202578903U (en) * | 2012-05-02 | 2012-12-05 | 安徽华菱汽车有限公司 | Power takeoff at rear end of engine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103573864A (en) * | 2013-10-17 | 2014-02-12 | 清华大学 | Electronic-control hydraulic control system for diaphragm-type clutch of aviation piston engine |
| CN106763658A (en) * | 2016-12-27 | 2017-05-31 | 中国南方航空工业(集团)有限公司 | Reduction case |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103043217B (en) | 2015-02-18 |
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