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Fuel thermal management method for aviation piston self-pressurized direct injection heavy fuel oil engine

A self-pressurization and engine technology, which is applied in engine control, machine/engine, mechanical equipment, etc., can solve problems such as the difficulty of applying small aviation piston engines, and achieve the effects of improving thermal management efficiency, reducing energy consumption, and ensuring safety

Active Publication Date: 2022-04-08
NANJING TECH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In-cylinder direct injection technology for vehicles has matured, but due to price and structure constraints, it is difficult to apply it to small aviation piston engines

Method used

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  • Fuel thermal management method for aviation piston self-pressurized direct injection heavy fuel oil engine
  • Fuel thermal management method for aviation piston self-pressurized direct injection heavy fuel oil engine
  • Fuel thermal management method for aviation piston self-pressurized direct injection heavy fuel oil engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0045] like figure 1As shown, the fuel thermal management method of the aviation piston self-supercharging direct injection heavy fuel oil engine implemented in this implementation uses the fuel temperature sensor 10 and the fuel pressure sensor 11 to collect the corresponding oil circuit temperature and pressure data in real time, and feeds back to the electronic control unit ECU. The control unit ECU controls the self-increasing fuel injector, the one-way normally closed solenoid valve 13, the small cycle fuel pump and the large cycle fuel pump according to the received temperature and pressure data to perform self-test mode, small cycle mode, transition Mode, large cycle mode and failure mode switch to realize heat dissipation of self-pressurized injector and fuel temperature control.

[0046] After the electronic control unit ECU is powered on, it executes a self-test command to obtain feedback signals from the fuel temperature sensor 10 and the fuel pressure sensor 11 . ...

Embodiment 2

[0051] After the engine is started, the electronic control unit ECU will switch the fuel supply system among the small circulation mode, the transition mode and the large circulation mode according to the workload of the engine.

[0052] like image 3 As shown, the small cycle mode of this embodiment refers to the working mode switched when the electronic control unit ECU detects that the engine is cold started and the idle speed is working with a small load. The specific working method is as follows:

[0053] The electronic control unit ECU controls to open the one-way normally closed solenoid valve 13, at this time the fuel flows along the small circulation oil circuit; the electronic control unit ECU drives the small circulation fuel pump, and the small circulation fuel pump adjusts the small circulation according to the signal feedback from the fuel temperature sensor 10 The fuel flow in the oil circuit controls the fuel temperature in the small circulation oil circuit to ...

Embodiment 3

[0062] like Image 6 As shown, the fuel thermal management method of the aviation piston self-pressurized direct-injection heavy fuel oil engine of this embodiment also includes a fuel tank, a self-pressurized fuel injector and an electronic control unit ECU, and the two ends of the fuel tank are respectively connected to the fuel pressure regulating valve through pipelines 14 and the fuel filter, the other end of the fuel pressure regulating valve 14 is connected with a large cycle fuel pump and a small cycle fuel pump through the one-way normally closed solenoid valve 13; Large cycle fuel pump and small cycle fuel pump and engine; fuel temperature sensor 10 and fuel pressure sensor 11 are arranged on the pipeline between the self-boosting fuel injector and fuel pressure regulating valve 14; the electronic control unit ECU according to the fuel temperature sensor 10 Based on the data fed back by the fuel pressure sensor 11, the self-boosting fuel injector, the one-way normall...

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Abstract

The invention discloses a fuel oil heat management method of an aviation piston self-pressurized direct injection heavy fuel oil engine. The temperature and pressure data of the corresponding oil circuit are collected in real time through a fuel temperature sensor and a fuel pressure sensor, and are fed back to an electronic control unit ECU. The ECU controls the self-boosting fuel injector, one-way normally closed solenoid valve, small cycle fuel pump and large cycle fuel pump according to the received temperature and pressure data, and completes the self-test mode, small cycle mode, transition mode, and large cycle Mode and failure mode switching, to achieve self-boost injector heat dissipation and fuel temperature control. The invention controls the corresponding fuel pump according to the signal feedback of the fuel temperature sensor, ensures the safety of the self-pressurized fuel injector and reduces the energy consumption of the corresponding fuel pump.

Description

technical field [0001] The invention belongs to the technical field of aero-engines, and in particular relates to a fuel heat management method for an aero-piston self-pressurized direct-injection heavy oil engine. Background technique [0002] The aviation piston heavy oil engine is a two-stroke or four-stroke, ignition or compression ignition piston engine burning heavy oil fuel. Heavy oil fuel represented by RP-3 aviation kerosene has the characteristics of high flash point and low saturated vapor pressure, which guarantees the safety in transportation, storage and use. Piston engines have both cost and fuel economy advantages. Low-speed drones equipped with piston engines with a power of less than 100 kW have become the development trend of future drone power systems. [0003] The physical and chemical properties of heavy oil fuel lead to poor fuel evaporation at low temperature, it is difficult to form an equivalent mixture, and it is difficult to start the engine. Th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02D41/06F02D41/30
CPCF02D41/064F02D41/068F02D41/3082F02D41/3005F02D2200/0606F02D2200/0602
Inventor 季昊成刘锐翟步云钟翎丰李松鸿
Owner NANJING TECH UNIV
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