CN102733890B - Oil-gas separation device of aero star-shaped piston engine - Google Patents
Oil-gas separation device of aero star-shaped piston engine Download PDFInfo
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- CN102733890B CN102733890B CN201210227891.5A CN201210227891A CN102733890B CN 102733890 B CN102733890 B CN 102733890B CN 201210227891 A CN201210227891 A CN 201210227891A CN 102733890 B CN102733890 B CN 102733890B
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- breathing pipe
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- separating plant
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Abstract
The invention discloses an oil-gas separation device of an aero star-shaped piston engine. The oil-gas separation device comprises a front oil-gas separator and a back oil-gas separator. The front oil-gas separator is arranged on the retarder casing of the engine, and comprises a first aeration pipe outside the retarder casing, a second aeration pipe which extends into the inner cavity of the retarder casing and is provided with a first filter screen, and a plurality of oil-blocking wing panels which form an oil-blocking maze and are probvided on the inner cavity wall of the first aeration pipe. Each oil-blocking wing panel extends obliquely downwards, so that separated lubricating oil drops back to the inner cavity of the retarder casing. The back oil-gas separator is arranged on the center casing of the engine, and comprises a third aeration pipe which is provided with a second filter screen. A plurality of oil-blocking wing panels which form an oil-blocking maze are provided on the inner cavity wall of the third aeration pipe. Each oil-blocking wing panel extends obliquely downwards, so that the separated lubricating oil drops back to the center casing. Time for balancing a pressure difference between the engine inner cavity and an external environment is shortened, and oil impregnate in each part junction of the engine casing and engine power lose risks are reduced.
Description
Technical field
The present invention relates to a kind of aviation radial engine gas and oil separating plant.
Background technique
During piston engine work, because the gas in casing is heated and lubricant oil splashes in motor, form mist of oil, there is parts of lubricating oil because high temperature evaporates, to become steam simultaneously, in addition, due to piston ring sealed combustion chamber completely, there is part combustion gas to scurry into casing and also can make the pressure in casing increase.
Because the increased pressure in casing makes lubricant oil, from casing each several part junction, extrude, simultaneously intake stroke and working stroke piston during to lower dead centre displacement reaction force increase, cause engine power to decline.
For the pressure difference between balanced engine inner chamber and external environment, motor inner chamber should communicate with atmosphere.
Radial engine casing generally includes and holds the reduction case of retarder, the middle casing that holds connecting rod, supercharging casing and accessory drive gearbox (bonnet), each several part casing couples together with bolt, for avoiding joint leakage of oil, conventionally use cushion rubber, rubber strip to obturage.
Existing piston engine employing designs an oily labyrinth of gear and carries out Oil-gas Separation on middle casing or Rocker arm chamber cap, when mist of oil passes through the oily labyrinth of gear, lubricant oil in mist of oil can be attached on the oily labyrinth of gear, and lubricant oil returns motor inner chamber under the effect of self gravitation.
Owing to will cast or process the oily labyrinth of gear on middle casing or Rocker arm chamber cap, make the structure of casing or Rocker arm chamber cap become more complicated, be unfavorable for the casting processing of casing, simultaneously owing to being subject to the structural limitations of engine interior, the path that keeps off oily labyrinth can not be oversize, and this may cause especially not exclusively separated.
Summary of the invention
The object of the invention is to provide a kind of aviation star-like piston-engined gas and oil separating plant, so that motor inner chamber communicates with atmosphere.
For this reason, the invention provides the star-like piston-engined gas and oil separating plant of a kind of aviation, comprise: front deaerator, be arranged on the reduction case of motor, be included in the first breathing pipe of reduction case outside and stretch into the second breathing pipe with the first filter screen in reduction case inner chamber, wherein, form the oily fin of some gears in the oily labyrinth of gear on the internal chamber wall of the first breathing pipe, each keeps off, and oily fin is tilted to downward-extension so that separated lubricant oil falls after rise to the inner chamber of reduction case; Rear deaerator, be arranged on the middle casing of motor, comprise the 3rd breathing pipe with the second filter screen, wherein, the internal chamber wall of the 3rd breathing pipe is provided with the oily fin of some gears that forms the oily labyrinth of gear, and each keeps off, and oily fin is tilted to downward-extension so that separated lubricant oil drops in middle casing.
Further, above-mentioned the first filter screen is tapered, is welded in the second breathing pipe.
Further, the top that the bottom of above-mentioned the first breathing pipe has flange and the second breathing pipe is welded with flange, and is respectively equipped with pad between the flange of the first breathing pipe and the flange of the second breathing pipe and between the flange of the second breathing pipe and reduction case.
Further, the sidewall of above-mentioned the 3rd breathing pipe is provided with lubricant oil and injects arm, and lubricant oil injects arm and is provided with plug screw.
Further, above-mentioned the first breathing pipe is aluminum alloy cast forging piece, and it is aluminum alloy integrally casting part that the 3rd breathing pipe and lubricant oil inject arm.
Further, the lower end of above-mentioned the 3rd breathing pipe has flange, and flange has ring-shaped step inner chamber, and the second filter screen is arranged in ring-shaped step inner chamber.
Further, above-mentioned the first breathing pipe is bent upwards extension.
Further, above-mentioned the first breathing pipe integral body is S-shaped, comprises the first paragraph that tilts to extend from the ventilating hole of reduction case, in a side of first paragraph, extend straight up the 3rd section and the second segment to the 3rd section of curved extension by first end.
Further, the oily fin of some gears of above-mentioned the first breathing pipe is arranged in the internal chamber wall of second segment and from the curved outside of internal chamber wall and extends or extend to tube section central authorities from the curved interior of internal chamber wall to the central authorities of tube section.
Further, above-mentioned the 3rd breathing pipe comprises the 4th section of tilting to extend from the ventilating hole of middle casing and from the 4th section of the 5th section of extending straight up, and wherein, the oily fin of some gears of the 3rd breathing pipe is arranged in the internal chamber wall of the 5th section.
On the star-like piston-engined casing of aviation of the present invention, adopt former and later two external deaerators, the time of the pressure difference between balanced engine inner chamber and external environment shortens, and can reduce the risk of engine crankcase each several part junction oil impregnate and loss engine power.
Except object described above, feature and advantage, other object, feature and advantage that the present invention has, be described in further detail in connection with accompanying drawing.
Accompanying drawing explanation
Form this specification a part, for further understanding accompanying drawing of the present invention, show the preferred embodiments of the present invention, and be used for illustrating principle of the present invention together with specification.In figure:
Fig. 1 is for the star-like piston-engined schematic diagram of aviation of gas and oil separating plant of the present invention is installed;
Fig. 2 is according to the structural representation of the front deaerator of gas and oil separating plant of the present invention; And
Fig. 3 is according to the structural representation of the rear gas and oil separating plant of gas and oil separating plant of the present invention.
Description of reference numerals
The front deaerator of 10 motor 20
30 rear deaerator 21 first breathing pipes
22 first filter screen 23 second breathing pipes
Oily fin 31 second filter screens of 24 gear
The oily fin of 32 the 3rd breathing pipe 33 gear
21a/23a/32a flange 25 pads
34 lubricant oil inject arm 35 plug screws
36 pressure ring 211 first paragraphs
The 3rd section of 212 second segment 213
321 the 4th sections 322 the 5th sections
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
Fig. 2 and Fig. 3 show the star-like piston-engined gas and oil separating plant of aviation according to the present invention.In conjunction with referring to figs. 1 through Fig. 3, the star-like piston engine gas and oil separating plant of aviation of the present invention comprises: front deaerator 20, be arranged on the reduction case of motor 10, be included in the first breathing pipe 21 of reduction case outside and stretch into the second breathing pipe 23 with the first filter screen 22 in reduction case inner chamber, wherein, the first breathing pipe 21 is bent upwards extension, on the internal chamber wall of the first breathing pipe 21, form the oily fin 24 of some gears in the oily labyrinth of gear, each keeps off, and oily fin is tilted to downward-extension so that separated lubricant oil falls after rise to the inner chamber of reduction case; Rear deaerator 30, be arranged on the middle casing of motor 10, comprise the 3rd breathing pipe 32 with the second filter screen 31, wherein, the internal chamber wall of the 3rd breathing pipe 32 is provided with the oily fin 33 of some gears that forms the oily labyrinth of gear, and each keeps off, and oily fin is tilted to downward-extension so that separated lubricant oil drops in middle casing.
On the star-like piston-engined casing of aviation of the present invention, adopt former and later two external deaerators, the time of the pressure difference between balanced engine inner chamber and external environment shortens, and can reduce the risk of engine crankcase each several part junction oil impregnate and loss engine power.
Each keeps off oily fin 24 and is tilted to downward-extension, is convenient in inner chamber that separated lubricant oil inwardly drops to each casing.
Front and back of the present invention deaerator 20,30 is not subject to the structural limitations of engine interior, can to keeping off the path length in oily labyrinth, increase and decrease as required according to the feature of motor, can make oil gas completely separated.
The first breathing pipe 21 is bent upwards extension, compares with straight extension, has obviously improved oil gas separation, thereby can adopt the gear oil fin of lesser amt to obtain good separating effect.
Keep off the area of contour of oily fin 24 on the cross section of breathing pipe and can occupy the over half of cross section, for example, occupy 2/3～3/4 of cross-section area.
The first filter screen 22 is preferably tapered, is welded in the second breathing pipe 23.Adopt the filter screen of taper, compare with flat screen, area increases, and can increase Oil-gas Separation amount.
The mesh of the first filter screen 22 is intensive compared with the second filter screen 31, mainly plays the effect of Oil-gas Separation, stops in addition in addition the effect of extraneous foreign matter.And the second filter screen 31 mainly plays the effect that stops extraneous foreign matter, also there is in addition the effect of Oil-gas Separation.
The top that the bottom of the first breathing pipe 21 has flange 21a and the second breathing pipe 23 is welded with flange 23a, and between the flange 23a of the flange 21a of the first breathing pipe 21 and the second breathing pipe 23 and between the flange 23a of the second breathing pipe 23 and reduction case, be respectively equipped with pad 25, by two or more threaded fasteners, flange 21a, 23a be connected with reduction case.
In the present invention, preferably, the 3rd breathing pipe 32 is provided with lubricant oil and injects arm 34, and lubricant oil injects arm and is provided with plug screw 35, this lubricant oil inject arm 34 for motor after unpacking and start forward direction casing inner chamber and inject lubricant oil.It is aluminum alloy integrally casting part that the 3rd breathing pipe 32 and lubricant oil inject arm 34, makes the combination of rear deaerator 30 reasonable, compact.On certain h type engine h, this deaerator 30 is roughly positioned at the top of the mixed gas trap (not shown) of motor.
In the present invention, preferably, the lower end of the 3rd breathing pipe 32 has flange 32a, and flange 32a has ring-shaped step inner chamber 32b, and the second filter screen 31 is arranged in ring-shaped step inner chamber 32b, has so simplified the mounting structure of the second filter screen.This second filter screen can be pressed in ring-shaped step inner chamber by pressure ring 36.
In the present invention, preferably, the first breathing pipe 21 is whole S-shaped, comprises first paragraph 211 that the ventilating hole from reduction case tilts to extend, in a side of first paragraph 211, extend straight up the 3rd section 213 and the second segment 212 to the 3rd section of 213 curved extensions by first end 211.Each keeps off in the internal chamber wall that oily fin 24 is arranged on second segment and is interlaced, preferably, the oily fin 24a of a part of gear extends or another part keeps off oily fin 24b and extends to tube section central authorities from the curved interior of internal chamber wall to the central authorities of tube section from the curved outside of internal chamber wall.Compare with the oily labyrinth of other forms of gear, this position that keeps off oily labyrinth is selected and to keep off the configuration of oily fin reasonable, and oil-gas separation efficiency improves.
In the present invention, preferably, the 3rd breathing pipe 32 comprises the 4th section 321 of tilting to extend from the ventilating hole of middle casing and from the 4th section of the 5th section 322 of extending straight up, and wherein, the oily fin 33 of some gears is arranged in the internal chamber wall of the 5th section.
Forward and backward deaerator 20,30 adopts two-stage separation structure, and the gear being formed by the oily fin of some gears oil labyrinth outside, can prevent that external impurities from entering motor inner chamber, coordinates with position at interior filter screen simultaneously, realizes Oil-gas Separation.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (10)
1. the star-like piston engine gas and oil separating plant of aviation, is characterized in that, comprising:
Front deaerator, be arranged on the reduction case of motor, be included in the first breathing pipe of described reduction case outside and stretch into the second breathing pipe with the first filter screen in described reduction case inner chamber, wherein, on the internal chamber wall of described the first breathing pipe, form the oily fin of some gears in the oily labyrinth of gear, described in each, keep off that oily fin is tilted to downward-extension so that separated lubricant oil falls after rise to the inner chamber of described reduction case;
Rear deaerator, be arranged on the middle casing of motor, comprise the 3rd breathing pipe with the second filter screen, wherein, the internal chamber wall of described the 3rd breathing pipe is provided with the oily fin of some gears that forms the oily labyrinth of gear, keeps off that oily fin is tilted to downward-extension so that separated lubricant oil drops in middle casing described in each.
2. the star-like piston engine gas and oil separating plant of aviation according to claim 1, is characterized in that, described the first filter screen is tapered, is welded in described the second breathing pipe.
3. the star-like piston engine gas and oil separating plant of aviation according to claim 1, it is characterized in that, the top that the bottom of described the first breathing pipe has flange and described the second breathing pipe is welded with flange, and is respectively equipped with pad between the flange of described the first breathing pipe and the flange of the second breathing pipe and between the flange of the second breathing pipe and reduction case.
4. the star-like piston engine gas and oil separating plant of aviation according to claim 1, is characterized in that, the sidewall of described the 3rd breathing pipe is provided with lubricant oil and injects arm, and described lubricant oil injects arm and is provided with plug screw.
5. the star-like piston engine gas and oil separating plant of aviation according to claim 4, is characterized in that, it is aluminum alloy integrally casting part that described the 3rd breathing pipe and lubricant oil inject arm.
6. the star-like piston-engined gas and oil separating plant of aviation according to claim 1, is characterized in that, the lower end of described the 3rd breathing pipe has flange, and described flange has ring-shaped step inner chamber, and described the second filter screen is arranged in described ring-shaped step inner chamber.
7. the star-like piston-engined gas and oil separating plant of aviation according to claim 1, is characterized in that, described the first breathing pipe is bent upwards extension.
8. the star-like piston-engined gas and oil separating plant of aviation according to claim 7, it is characterized in that, described the first breathing pipe integral body is S-shaped, comprises the first paragraph that tilts to extend from the ventilating hole of described reduction case, in a side of described first paragraph, extend straight up the 3rd section and the second segment to described the 3rd section of curved extension by described first end.
9. the star-like piston-engined gas and oil separating plant of aviation according to claim 7, it is characterized in that, the oily fin of described some gears of described the first breathing pipe is arranged in the internal chamber wall of described second segment and from the curved outside of internal chamber wall and extends or extend to tube section central authorities from the curved interior of internal chamber wall to the central authorities of tube section.
10. the star-like piston-engined gas and oil separating plant of aviation according to claim 1, it is characterized in that, described the 3rd breathing pipe comprises the 4th section of tilting to extend from the ventilating hole of described middle casing and from described the 4th section of the 5th section of extending straight up, wherein, the oily fin of described some gears of described the 3rd breathing pipe is arranged in the internal chamber wall of described the 5th section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210227891.5A CN102733890B (en) | 2012-07-03 | 2012-07-03 | Oil-gas separation device of aero star-shaped piston engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210227891.5A CN102733890B (en) | 2012-07-03 | 2012-07-03 | Oil-gas separation device of aero star-shaped piston engine |
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| Publication Number | Publication Date |
|---|---|
| CN102733890A CN102733890A (en) | 2012-10-17 |
| CN102733890B true CN102733890B (en) | 2014-09-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210227891.5A Active CN102733890B (en) | 2012-07-03 | 2012-07-03 | Oil-gas separation device of aero star-shaped piston engine |
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| CN (1) | CN102733890B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106194334A (en) * | 2016-08-31 | 2016-12-07 | 潍柴动力股份有限公司 | A kind of gs-oil separator assembly |
| CN115324728A (en) * | 2022-08-08 | 2022-11-11 | 浙江吉利控股集团有限公司 | Two-stroke engine |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101463743A (en) * | 2008-12-16 | 2009-06-24 | 奇瑞汽车股份有限公司 | Crankcase ventilation system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4010032B2 (en) * | 1997-10-13 | 2007-11-21 | 株式会社Ｉｈｉ | Apparatus for separating oil droplets from cooled pressurized air in a gas turbine engine |
| JP3853582B2 (en) * | 2000-08-25 | 2006-12-06 | ダイハツ工業株式会社 | Structure of cylinder head cover in internal combustion engine |
| KR100410687B1 (en) * | 2001-10-12 | 2003-12-18 | 현대자동차주식회사 | Oil separating apparatus for blow by gas |
| JP4018944B2 (en) * | 2002-07-08 | 2007-12-05 | 富士重工業株式会社 | Blowby gas recirculation system and blowby gas recirculation method |
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101463743A (en) * | 2008-12-16 | 2009-06-24 | 奇瑞汽车股份有限公司 | Crankcase ventilation system |
Non-Patent Citations (2)
| Title |
|---|
| JP特开2002-70521A 2002.03.08 |
| JP特开平11-117709A 1999.04.27 |
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| CN102733890A (en) | 2012-10-17 |
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Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
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