CN111946586A - Compact aviation heavy oil piston engine air pump - Google Patents

Compact aviation heavy oil piston engine air pump Download PDF

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Publication number
CN111946586A
CN111946586A CN202010825593.0A CN202010825593A CN111946586A CN 111946586 A CN111946586 A CN 111946586A CN 202010825593 A CN202010825593 A CN 202010825593A CN 111946586 A CN111946586 A CN 111946586A
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CN
China
Prior art keywords
cylinder
air pump
piston
hole
air
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Pending
Application number
CN202010825593.0A
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Chinese (zh)
Inventor
黄云龙
杨广文
吴凯
夏杨
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No 60 Institute of Headquarters of General Staff of PLA
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No 60 Institute of Headquarters of General Staff of PLA
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Publication date
Application filed by No 60 Institute of Headquarters of General Staff of PLA filed Critical No 60 Institute of Headquarters of General Staff of PLA
Priority to CN202010825593.0A priority Critical patent/CN111946586A/en
Publication of CN111946586A publication Critical patent/CN111946586A/en
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B35/00—Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for
    • F04B35/01—Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for the means being mechanical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B69/00—Internal-combustion engines convertible into other combustion-engine type, not provided for in F02B11/00; Internal-combustion engines of different types characterised by constructions facilitating use of same main engine-parts in different types
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B39/00—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B39/00—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00
    • F04B39/0005—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00 adaptations of pistons
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B39/00—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00
    • F04B39/0094—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00 crankshaft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B39/00—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00
    • F04B39/10—Adaptations or arrangements of distribution members
    • F04B39/1013—Adaptations or arrangements of distribution members the members being of the poppet valve type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B39/00—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00
    • F04B39/10—Adaptations or arrangements of distribution members
    • F04B39/102—Adaptations or arrangements of distribution members the members being disc valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B39/00—Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups F04B25/00 - F04B37/00
    • F04B39/12—Casings; Cylinders; Cylinder heads; Fluid connections
    • F04B39/122—Cylinder block
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
    • F04B49/00—Control, e.g. of pump delivery, or pump pressure of, or safety measures for, machines, pumps, or pumping installations, not otherwise provided for, or of interest apart from, groups F04B1/00 - F04B47/00

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Compressors, Vaccum Pumps And Other Relevant Systems (AREA)

Abstract

The invention discloses a compact aviation heavy oil piston engine air pump which comprises an air cylinder, a cylinder cover, a spring, a valve plate, a piston, a shell, a connecting rod and a crankshaft, wherein the air cylinder is arranged on the cylinder cover; the cylinder is arranged in the inner cavity of the shell; the cylinder cover is arranged at the upper end of the cylinder; the upper part and the lower part of the cylinder are respectively provided with an air storage hole and a piston hole; the piston hole is provided with an air inlet communicated with the shell, and the side wall of the air storage hole is provided with an air exhaust hole; the valve plate is arranged in the air storage hole; a spring is arranged between the cylinder cover and the valve plate; the piston is arranged in the piston hole; the small end of the connecting rod is sleeved on the piston pin, and the large end is provided with a connecting rod shaft hole; the crankshaft comprises an eccentric wheel and a crankshaft counterweight; the eccentric wheel rotating shaft penetrates through the connecting rod shaft hole and the shell; the eccentric wheel and the crankshaft balance weight are integrated, the center of the eccentric wheel is positioned in the region of the crankshaft balance weight block, and the eccentric angle is matched with the installation angle of the air pump, so that the phase difference between the upper dead point of the air pump and the upper dead point of the engine is between-45 degrees and 45 degrees; the exhaust hole is connected with a pressure stabilizing end of the pressure stabilizing valve and the low-pressure direct injection nozzle; the pressure relief end of the pressure stabilizing valve is connected with a backflow hole; the pumping phase can be precisely controlled.

Description

Compact aviation heavy oil piston engine air pump
Technical Field
The invention belongs to the field of aero-engines, and particularly relates to a compact aero heavy oil piston engine air pump.
Background
The aviation piston engine is used as a power device, gasoline is widely used as a fuel at present, compared with gasoline, heavy oil has the characteristics of large viscosity and high flash point, transportation and storage are safe and reliable, and the heavy oil is universal in oil in military fields such as aviation, carrier-borne and the like, so that the guarantee can be simplified. However, heavy oil has high viscosity, poor flow property and poor atomization and evaporation effects at low temperature, and the air-assisted atomization device is adopted to realize good atomization of the heavy oil under the low-pressure injection condition in consideration of the lightweight requirement of the aircraft engine. The atomized auxiliary gas is provided by the air compression pump on the engine, and on large-scale engine usually, the air compression pump passes through the bent axle and drives the pulley drive, has the problem that the structure is complicated, weight is big, does not satisfy aeroengine lightweight requirement, and air pump drive non-integrated design, and pump gas phase control is inaccurate, can't be accurate stable the providing auxiliary air for air auxiliary formula atomizing device, influences heavy oil atomizing characteristic.
Chinese patent CN110778393A discloses an auxiliary air pump for a spark-ignition low-cylinder direct injection engine, which provides an improved air pump solution, in which the air pump is provided on the engine body, but has the following disadvantages: the eccentric wheel and the crankshaft are designed in a split mode, the assembly is complex, and the structural reliability is not strong; the cylinder body and the piston of the air pump are of a conventional structure, the overall structure of the air pump is large in size and heavy in weight, and the requirements of light weight and small envelope size of an aviation piston engine are not met; in addition, the patent does not provide a method for accurately controlling the air pump phase of the air pump and a scheme for prolonging the service life of the air pump.
Disclosure of Invention
The invention aims to provide a compact aviation heavy oil piston engine air pump which is simple and compact in structure, small in envelope size and light in weight, and realizes accurate control of the air pump phase of an air pump by adjusting the eccentric angle and the installation angle of the air pump.
The technical solution for realizing the purpose of the invention is as follows:
a compact aviation heavy oil piston engine air pump comprises an air cylinder, a cylinder cover, a spring, a valve plate, a piston, a shell, a connecting rod and a crankshaft;
the cylinder is arranged in an inner cavity at the upper end of the shell; the cylinder cover is arranged at the upper end of the cylinder and sealed with the cylinder; the upper end of the cylinder is provided with an air storage hole, and the lower end of the cylinder is provided with a piston hole; the side wall of the piston hole is provided with a plurality of air inlets communicated with the inner cavity of the shell, and the side wall of the air storage hole is provided with an air exhaust hole;
the valve plate is arranged in the air storage hole of the air cylinder; the lower end of the valve plate is sealed with the cylinder; a spring is arranged between the cylinder cover and the valve plate;
the piston is arranged in the piston hole; a piston pin and a piston ring are arranged on the piston;
the small end of the connecting rod is sleeved on the piston pin, and the large end of the connecting rod is provided with a connecting rod shaft hole;
the crankshaft is arranged in the shell and comprises an eccentric wheel and a crankshaft counterweight; the eccentric wheel rotating shaft is supported by a bearing and penetrates through the connecting rod shaft hole and the shell; the eccentric wheel and the crankshaft balance weight are integrated, the center of the eccentric wheel is positioned in the region of the crankshaft counterweight block, and the eccentric angle of the eccentric wheel is matched with the mounting angle of the air pump, so that the phase difference between the upper dead point position of the air pump and the upper dead point position of the engine is between minus 45 degrees and 45 degrees;
the exhaust hole of the cylinder is connected with a pressure stabilizing end of a pressure stabilizing valve and a low-pressure direct injection nozzle; the pressure relief end of the pressure stabilizing valve is communicated with a backflow hole in the shell.
Compared with the prior art, the invention has the following remarkable advantages:
(1) the eccentric wheel and the crankshaft balance weight are integrally designed, the center of the eccentric wheel is positioned in the crankshaft balance weight area, the crankshaft balance weight is compensated, the structure is simplified, the compactness is improved, and the whole weight of the engine is reduced; the air pump phase position of the air pump can be controlled by adjusting the installation angle and the eccentric angle of the air pump, the requirement of the periodic accurate air supply of the low-pressure direct injection nozzle by the air rail is met, and the air pump phase angle can be dynamically adjusted between minus 45 degrees and 45 degrees.
(2) A pressure stabilizing valve is designed in the air rail, so that the pressure of the air rail is stable in the working process of the air pump, the pressure difference between the pressure stabilizing valve and the atmosphere is adjustable, different pressure settings of the air rail are realized, the adjustable range of the pressure of the air rail is 3-6 bar, and various pressure requirements of a low-pressure direct injection nozzle can be met; redundant gas in the gas rail flows through the shell backflow hole through the pressure relief end of the pressure stabilizing valve and returns to the engine crankcase, so that energy recovery is realized, scavenging efficiency of the engine and the air pump is improved, and stability of air pressure of the air pump at different flight altitudes is ensured.
(3) The design of the stepped cylinder body and the piston is adopted, the volume of the air storage cavity is reduced, the air displacement is ensured, the outer envelope size of the head part of the air pump is effectively reduced, the structural weight is reduced, and the requirement of the small envelope size of the aero-engine is met.
(4) The cylinder adopts aluminum alloy material, and the hole plates pottery, reduces whole weight simultaneously, improves the hole wearability, extension air pump life satisfies aeroengine long-life design requirement.
Drawings
FIG. 1 is a cross-sectional view of the compact aviation heavy oil piston engine air pump of the present invention.
Fig. 2 is a partial cross-sectional view of an intake port in the cylinder block of the present invention.
Fig. 3 is an explanatory diagram of a method of calculating the pump phase angle of the air pump.
Fig. 4 is a schematic diagram of the air pump air rail piping arrangement.
Detailed Description
The invention is further described with reference to the following figures and embodiments.
With reference to fig. 1, the compact aviation heavy oil piston engine air pump of the invention comprises a housing 8, an air cylinder 1, a cylinder cover 3, a piston 6, a crankshaft 10, a connecting rod 9, a spring 4, a valve plate 5 and a cylinder sleeve 7;
the outer diameter of the cylinder 1 is smaller than the inner diameter of the shell 8, and the cylinder 1 is arranged in an inner cavity at the upper end of the shell;
the cylinder cover 3 is arranged at the upper end of the cylinder 1, and an O-shaped sealing ring 2 is arranged between the cylinder cover and the cylinder 1 for sealing;
the middle of the cylinder 1 is provided with an annular step to form a stepped hole 103, and the inner cavity of the cylinder 1 is divided into an air storage hole 106 and a piston hole 101 which are communicated up and down; the side wall of the piston hole 101 is provided with a plurality of air inlets 102 communicated with the inner cavity of the shell 8, and the side wall of the air storage hole 106 is provided with an air outlet 105. The cylinder adopts aluminum alloy material, and the hole plates pottery, reduces whole weight simultaneously, improves the hole wearability, extension air pump life satisfies aeroengine long-life design requirement.
The valve plate 5 is arranged in the gas storage hole 106 of the cylinder 1, the outer diameter of the valve plate 5 is smaller than the diameter of the piston hole 101, the lower end of the valve plate 5 is provided with a stepped first sealing ring groove 501, the middle annular step of the cylinder 1 is provided with a second sealing ring groove 104, and the first sealing ring groove 501 is tightly matched with the second sealing ring groove 104; the upper end surface of the valve plate 5 is provided with a spring positioning groove 502 for positioning the lower end of the spring 4; a spring 4 is arranged between the valve plate 5 and the cylinder cover 3; the valve block 5 is pressed on the upper end of the annular step of the cylinder under the action of the spring 4, before the gas pressure in the cylinder 1 does not reach the set pressure, the first sealing ring groove 501 of the valve block 5 is closely matched with the second sealing ring groove 104 designed on the cylinder 1, and the sealing performance in the cylinder 1 in the compression process is ensured. After the gas pressure in the cylinder 1 reaches the designated pressure, the valve plate 5 moves upwards along the inner wall of the gas storage hole 106 under the action of the gas pressure difference and the spring force on the two sides, and when the position of the valve plate 5 is higher than the position of the exhaust hole 105, high-pressure gas is exhausted into the gas rail through the exhaust hole 105. An O-shaped sealing ring 2 is arranged between the air storage hole 106 and the cylinder cover 3 for sealing, and the lower end of the cylinder cover 3 is provided with a positioning shaft for positioning the upper end of the spring 4.
The cylinder sleeve 7 is arranged on the outer wall of the cylinder 1 and is connected with the upper end face of the shell 8; in order to ensure that gas smoothly enters a cylinder body for compression, the cylinder sleeve 7 and the shell 8 are respectively provided with an axially distributed gas inlet channel which comprises a cylinder sleeve gas inlet channel 701 and a shell gas inlet channel 801 which are sequentially communicated from top to bottom, a gas inlet 102 is axially arranged on the cylinder 1, and the gas inlet 102 is communicated with the cylinder sleeve gas inlet channel 701; with reference to fig. 2, the air inlet 102 adopts a tapered hole design, so that air inlet resistance is reduced, and air inlet efficiency is improved. The position, the number and the shape of the air inlets can be changed, and the air displacement of the air pump can be adjusted.
The piston 6 is disposed in the piston bore 101; the top end of the piston 6 is provided with a stepped shaft 601 structure matched with the stepped hole 103 of the cylinder 1, and the piston 6 is provided with a piston pin and piston ring 602 and a piston pin retainer ring 603. The piston pin is arranged at the lower end of the piston 6, and piston rings 602 are arranged at two ends of the piston pin and are sleeved on the piston 6 through piston pin retaining rings 603.
The small end of the connecting rod 9 is matched with the needle bearing and then assembled on the piston pin, and the large end of the connecting rod is provided with a connecting rod shaft hole.
The crankshaft 10 is arranged in the shell 8 and comprises an eccentric wheel 1001 and a crankshaft counterweight 1002; the eccentric wheel 1001 rotating shaft is supported by a bearing and penetrates through a connecting rod shaft hole and the shell 8; the eccentric wheel 1001 and a crankshaft counterweight 1002 on the engine crankshaft 10 are integrated, the center of the eccentric wheel 1001 is located in the region of the crankshaft counterweight 1002, and the eccentric angle of the eccentric wheel 1002 is matched with the mounting angle of the air pump, so that the phase difference between the upper dead point position of the air pump and the upper dead point position of the engine is-45 degrees. The circle center of the eccentric wheel 1001 is located in the area of the crankshaft balancing weight 1002, and the mass of the eccentric wheel 1001 is counted into the mass of the crankshaft balancing weight 1002, so that the rotating inertia force and the reciprocating inertia force on the crankshaft 10 in the working process of the engine are balanced together.
And a pressure stabilizing valve 11, the pressure stabilizing end 1101 of which is communicated with the exhaust hole 105 and the low-pressure direct injection nozzle, the pressure relief end 1102 of which is communicated with a return hole 802 on the shell 8, and the pressure of which is adjustable. The exhaust hole 105 of the cylinder 1 is connected with a pressure stabilizing valve 11 and a low-pressure direct injection nozzle, the pressure stabilizing valve 11 is provided with an air port 1103 which is the same as the atmosphere, the pressure of the pressure stabilizing valve is adjustable, the difference value between the pressure in an air rail and the pressure of the surrounding environment is adjustable at 3-6 bar, and the injection pressure requirements of different low-pressure direct injection nozzles are met. The return end 1102 of the pressure stabilizing valve is connected with the return hole 802 on the shell 8, and when redundant gas exists in the gas rail, the gas can return to the gas pump through the return hole 802, so that the purpose of energy recovery is achieved.
The air pump phase angle of the air pump is adjusted through the design of the eccentric angle of the eccentric wheel 1001 and the air pump installation angle, the air pump installation angle is an included angle between an air pump installation surface and two surfaces of a cylinder body installation surface, and the eccentric angle is an included angle between a connecting line of the center of the eccentric wheel and the center of the crankshaft and the cylinder body installation surface when an engine piston is positioned at a top dead center. The air pump phase angle of the air pump is equal to the air pump installation angle-eccentric angle, and the designed air pump phase angle of the air pump is between minus 45 degrees and 45 degrees, namely the phase difference between the top dead center position of the air pump and the top dead center position of the engine is ensured to be between minus 45 degrees and 45 degrees.
After the gas enters the cylinder 1 through the gas inlet hole 102, the piston 6 is driven by the eccentric 1001 on the crankshaft 10 to compress the gas in the cylinder 1, and the compression stroke starts from the upward movement of the piston 6 and the complete shielding of the gas inlet hole 102. In order to improve the sealing effect and ensure the compression performance, the piston ring 602 is designed on the piston 6, the single-piston design is adopted, the pump air friction is reduced, and the clearance between the piston 6 and the cylinder 1 is 0.5-1 mm when the piston reaches the top dead center.

Claims (10)

1. A compact aviation heavy oil piston engine air pump comprises an air cylinder (1), a cylinder cover (3), a spring (4), a valve plate (5), a piston (6), a shell (8), a connecting rod (9) and a crankshaft (10); it is characterized in that the preparation method is characterized in that,
the cylinder (1) is arranged in an inner cavity at the upper end of the shell (8); the cylinder cover (3) is arranged at the upper end of the cylinder (1) and is sealed with the cylinder (1); the upper end of the cylinder (1) is provided with an air storage hole (106), and the lower end of the cylinder is provided with a piston hole (101); the side wall of the piston hole (101) is provided with a plurality of air inlets (102) communicated with the inner cavity of the shell (8), and the side wall of the air storage hole (106) is provided with an exhaust hole (105);
the valve plate (5) is arranged in the air storage hole (106) of the air cylinder (1); the lower end of the valve plate (5) is sealed with the cylinder (1); a spring (4) is arranged between the cylinder cover (3) and the valve plate (5);
the piston (6) is arranged in the piston hole (101); a piston pin and a piston ring (602) are arranged on the piston (6);
the small end of the connecting rod (9) is sleeved on the piston pin, and the large end is provided with a connecting rod shaft hole;
the crankshaft (10) is arranged in the shell (8) and comprises an eccentric wheel (1001) and a crankshaft counterweight (1002); the rotating shaft of the eccentric wheel (1001) is supported by a bearing and penetrates through the connecting rod shaft hole and the shell (8); the eccentric wheel (1001) and the crankshaft counterweight (1002) are integrated, the center of the eccentric wheel (1001) is located in the region of the crankshaft counterweight block (1002), and the eccentric angle of the eccentric wheel (1002) is matched with the mounting angle of the air pump, so that the phase difference between the upper dead point position of the air pump and the upper dead point position of the engine is-45 degrees;
an exhaust hole (105) of the cylinder (1) is connected with a pressure stabilizing end (1101) of a pressure stabilizing valve (11) and a low-pressure direct injection nozzle; the pressure relief end (1102) of the pressure stabilizing valve (11) is communicated with a backflow hole (802) on the shell (8).
2. The compact aviation heavy oil piston engine air pump according to claim 1, characterized in that an annular step is arranged in the middle of the cylinder (1), a second sealing ring groove (104) is arranged on the annular step, and a first sealing ring groove (501) is arranged at the lower end of the valve plate (5); the first sealing ring groove (501) is matched with the second sealing ring groove (104).
3. The compact aviation heavy oil piston engine air pump according to claim 1, characterized in that the cylinder (1) is provided with an annular step in the middle to form a stepped hole (103), and the top end of the piston (6) is provided with a stepped shaft (601) structure matched with the stepped hole (103).
4. The compact aviation heavy oil piston engine air pump according to claim 1, wherein a cylinder sleeve (7) is arranged on the outer wall of the air cylinder (1) and is connected with the upper end face of the shell (8); the cylinder sleeve (7) and the shell (8) are respectively provided with an air inlet channel which is axially distributed and comprises a cylinder sleeve air inlet channel (701) and a shell air inlet channel (801) which are sequentially communicated from top to bottom; the air inlet (102) is communicated with a cylinder sleeve air inlet channel (701).
5. The compact aviation heavy oil piston engine air pump of claim 1, wherein said air intake (102) is a tapered bore.
6. The compact aviation heavy oil piston engine air pump according to claim 1, wherein the upper end surface of the valve plate (5) is provided with a spring positioning groove (502), and the lower end of the cylinder cover (3) is provided with a positioning shaft.
7. The compact aviation heavy oil piston engine air pump according to claim 1, characterized in that a sealing ring (2) is arranged between the cylinder cover (3) and the cylinder (1) for sealing.
8. The compact aviation heavy oil piston engine air pump according to claim 1, wherein the cylinder (1) is aluminum alloy coated with ceramic inner bore.
9. A pump gas phase control method of a compact aviation heavy oil piston engine air pump is characterized in that adjustment is carried out through the design of the eccentric angle of an eccentric wheel and the installation angle of the air pump; the air pump phase angle of the air pump is equal to an air pump installation angle-an eccentric angle;
the air pump mounting angle is an included angle between the air pump mounting surface and two surfaces of the cylinder body mounting surface; the eccentric angle is an included angle between a connecting line of the circle center of the eccentric wheel and the center of the crankshaft and the cylinder body mounting surface when the piston of the engine is positioned at the top dead center.
10. The gas phase control method of claim 9, wherein the phase difference between the top dead center position of the air pump and the top dead center position of the engine is between-45 ° and 45 °.
CN202010825593.0A 2020-08-17 2020-08-17 Compact aviation heavy oil piston engine air pump Pending CN111946586A (en)

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CN110259661A (en) * 2019-07-24 2019-09-20 浙江北上新能源科技股份有限公司 A kind of new type compressor
CN110778393A (en) * 2019-09-30 2020-02-11 广西擎芯动力科技有限公司 Auxiliary air pump of direct injection engine in ignition type low-pressure cylinder
CN210195964U (en) * 2019-05-28 2020-03-27 一汽解放汽车有限公司 Lightweight air compressor assembly
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Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070065311A1 (en) * 2005-08-16 2007-03-22 Wen San Chou Air compressor having changeable structure
US20080240943A1 (en) * 2007-03-28 2008-10-02 Wei-Chi Wang Air pump
CN202273823U (en) * 2011-10-29 2012-06-13 温岭市富康汽车零部件有限公司 Minitype automobile air pump
CN203867802U (en) * 2014-05-27 2014-10-08 浙江振圣机电科技有限公司 Four-cylinder piston compressor
CN204299815U (en) * 2014-12-09 2015-04-29 淄博泰展机电有限公司 A kind of automobile chassis suspend control dehumidification type air pump
CN205977632U (en) * 2016-08-12 2017-02-22 宁波泰格尔机械有限公司 Piston air pump
CN108035863A (en) * 2018-01-08 2018-05-15 浙江北上新能源科技股份有限公司 A kind of compressor and the mechanized equipment with the compressor
CN210195964U (en) * 2019-05-28 2020-03-27 一汽解放汽车有限公司 Lightweight air compressor assembly
CN110259661A (en) * 2019-07-24 2019-09-20 浙江北上新能源科技股份有限公司 A kind of new type compressor
CN110778393A (en) * 2019-09-30 2020-02-11 广西擎芯动力科技有限公司 Auxiliary air pump of direct injection engine in ignition type low-pressure cylinder
CN213088174U (en) * 2020-08-17 2021-04-30 中国人民解放军总参谋部第六十研究所 Compact aviation heavy oil piston engine air pump

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