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A kind of heavy oil aviation rotary engine and its detonation control method

A technology of rotary engine and engine block, applied in engine control, combustion engine, machine/engine, etc., can solve the problems of limiting engine speed, power and power-to-weight ratio, slow combustion speed of heavy oil, prone to knocking, etc. The effect of improving combustion performance, increasing flame propagation speed, and promoting thorough mixing

Active Publication Date: 2022-04-19
TIANJIN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Heavy oil burns slowly and is prone to knocking, which limits the engine's speed, power, and power-to-weight ratio. Therefore, it is necessary to solve the problems of atomization and knocking of heavy oil to achieve efficient combustion

Method used

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  • A kind of heavy oil aviation rotary engine and its detonation control method
  • A kind of heavy oil aviation rotary engine and its detonation control method
  • A kind of heavy oil aviation rotary engine and its detonation control method

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Embodiment Construction

[0026] The present invention will be further described below in conjunction with the accompanying drawings.

[0027] Such as figure 1 As shown, the heavy fuel aviation rotary engine of the present invention includes an engine block 1, an intake port 2, an exhaust port 3, a triangular rotor 4, a pre-combustion chamber 5, a first air-assisted fuel injector 6, a heating plug 7, and a spark plug 8 , Second air-assisted fuel injector 9, solenoid valve 10, bypass hole 11, bypass pipe 12, knock sensor 13, ECU14. The first air-assisted injector 6 , the second air-assisted injector 9 , the solenoid valve 10 and the knock sensor 13 are all electrically connected to the ECU 14 .

[0028] Such as figure 2 and image 3 As shown, the triangular rotor 4 is arranged inside the engine block 1 , and the outer surface of the triangular rotor 4 is provided with rotor pits 401 . On the surface of the triangular rotor 4 , along the direction opposite to the rotation direction of the triangular...

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Abstract

The invention discloses a heavy oil aviation rotary engine and a knock control method thereof: it comprises an engine block, the engine block is provided with an intake port, an exhaust port, a pre-combustion chamber, a second air-assisted fuel injector, a solenoid valve, The shock sensor, the pre-combustion chamber is equipped with the first air-assisted fuel injector, heating plug, spark plug, and the solenoid valve is connected to the intake port through the bypass pipe; the first air-assisted fuel injector, the second air-assisted fuel injector, the electromagnetic Valves and knock sensors are electrically connected to the ECU; the engine block has a built-in triangular rotor, and rotor pits are arranged on the outer surface of the triangular rotor. The cross-sectional profile of the central symmetrical plane is a smooth curve, and three mutually parallel cylinders are arranged in each rotor pit. The pre-combustion chamber of the present invention can improve the combustion atomization, diffusion and combustion process in the combustion chamber.

Description

technical field [0001] The invention belongs to the technical field of internal combustion engine combustion, and more specifically relates to a heavy oil aviation rotary engine and a knock control method thereof. Background technique [0002] UAVs have a very wide range of applications in the military. At present, the light-duty and short-range UAVs with power requirements below 250 horsepower all use internal combustion engines that burn aviation gasoline. The cruising range (and load capacity) of an aircraft is determined by the weight of the engine itself + the weight of the fuel loaded and the fuel consumption rate; the lighter the engine itself (the greater the power-to-weight ratio), the more fuel it can load; the higher the thermal efficiency of the engine (fuel consumption The lower the rate), the longer the running time of fuel per unit weight, so the weight of the engine and the fuel consumption rate are the key parameters to determine the cruising range of the a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02B53/00F02B55/02F02B55/16F02B53/08F02B53/06F02B53/12F02B53/10F02B19/10F02B19/16F02D41/40F02D41/30F02D35/02
CPCF02B53/00F02B55/02F02B55/16F02B53/08F02B53/06F02B53/12F02B53/10F02B19/108F02B19/1085F02B19/1014F02B19/16F02D41/403F02D41/3094F02D35/027F02B2053/005F02D2041/389Y02T10/12
Inventor 刘海峰孔祥恩尧命发郑尊清王浒
Owner TIANJIN UNIV