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an aviation piston engine

A technology of piston engine and engine casing, applied in the direction of internal combustion piston engine, engine components, combustion engine, etc., can solve the problems of complex structure, unsuitable for aviation kerosene piston engine, unsuitable two-stroke structure, etc., and achieve low operating cost. , The effect of compact structure and high power-to-weight ratio

Active Publication Date: 2021-08-06
SUNWARD INTELLIGENT EQUIP CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional two-stroke engine uses crankcase air intake, and uses lubricating oil mixed into the fuel to lubricate the engine. The structure of scavenging, lubrication, cooling, etc. is complicated, and the power is relatively high, but it is limited to low-power gasoline aeroengines. , the two-stroke structure is not suitable for high-power aviation heavy fuel oil engines that require higher intake pressure and lubrication methods and require supercharging
Therefore, current four-stroke engines and two-stroke engines are not suitable for use as aviation kerosene piston engines.

Method used

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Embodiment 1

[0054] Such as Figure 1-Figure 4 As shown, the aviation piston engine of the present embodiment comprises an engine housing 1, a crank linkage mechanism 2, a supercharger 3, a turbocharger 4, a belt transmission mechanism 5, a fuel pump 6, a generator 7, and a starter motor 8. Cooling water pump 9 and accessory box 10.

[0055] Such as Figure 10 As shown, the crank linkage mechanism 2 includes a horizontally arranged crankshaft 21, on which two cranks are fixed, the crank includes a crank journal 22 parallel to the crankshaft 21, and two cranks connected between the crankshaft 21 and the crank journal 22 Arm 23, two crank arms 23 are respectively arranged at the two ends of the crank journal 22; the counterweight 26 corresponding to the crank arm 23 is fixedly connected on the crankshaft 21, and the crank arm 23 and the corresponding counterweight 26 are respectively arranged on the crankshaft 21 both ends in the radial direction. The axial centerlines of the two cranksha...

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Abstract

The invention discloses an aviation piston engine, which comprises an engine casing, a crank connecting rod mechanism, a supercharger, a turbocharger, a belt transmission mechanism, a fuel pump, a generator and a starter motor. The crank-link mechanism includes a horizontally arranged crankshaft, on which two cranks are fixed, and two opposite connecting rods are installed on each crank, and a piston is installed on the end of each connecting rod away from the crankshaft. The engine casing includes a casing mounted on the crankshaft, and four cylinders installed on the casing and communicated with the casing, and four pistons are slidably arranged in the corresponding cylinders. The engine has a compact structure, reduces the installation size of the engine, and has a high power-to-weight ratio. The supercharger and turbocharger are connected in series, which can scavenge at high and low speeds, and have redundant backup at the same time.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to an aviation heavy oil piston engine. Background technique [0002] At present, aviation piston engines mainly use aviation gasoline. The compression ignition type aviation heavy oil piston engines currently used are basically four-stroke, and the valve phase mechanism is adopted. The overall weight of the engine is increased, and the components are complex. The power weight is relatively low; in addition, the cooling of the four-stroke engine is mostly air-cooled to reduce the complicated design of the internal cavity of the engine. The traditional two-stroke engine uses crankcase air intake, and uses lubricating oil mixed into the fuel to lubricate the engine. The structure of scavenging, lubrication, cooling, etc. is complicated, and the power is relatively high, but it is limited to low-power gasoline aeroengines. , the two-stroke structure is not suitable for high-power avia...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02B75/24F02F1/22F02B67/06F02B37/04F02B39/04F02M37/06F01P5/12F01P3/02F01M1/02F01M1/06F01P3/08
CPCF01M1/02F01M1/06F01M2001/062F01M2001/066F01P3/02F01P3/08F01P5/12F01P2003/021F02B37/04F02B39/04F02B67/06F02B75/005F02B75/246F02B2075/1816F02F1/22F02M37/06Y02T10/12
Inventor 何清华潘钟键邹湘伏杨斌刘厚根
Owner SUNWARD INTELLIGENT EQUIP CO LTD
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