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A double-margin aero-engine fuel regulation control system

A technology for aero-engine and fuel regulation, which is applied in general control systems, control/regulation systems, instruments, etc., and can solve problems such as insufficient safety and the inability of single-margin fuel regulation control systems to adjust with high precision and adaptability.

Active Publication Date: 2021-10-22
上海尚实航空发动机股份有限公司
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The present invention proposes a dual margin aero-engine fuel adjustment control system to solve the technical problem that the existing single margin fuel adjustment control system cannot perform high-precision adaptive adjustment according to different flight states of the aircraft and has insufficient safety

Method used

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  • A double-margin aero-engine fuel regulation control system
  • A double-margin aero-engine fuel regulation control system
  • A double-margin aero-engine fuel regulation control system

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Embodiment Construction

[0033] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0034] A specific embodiment of a dual-margin aero-engine fuel regulation control system of the present invention, as Figure 1-8 As shown, it includes the main fuel supply system S1, the auxiliary fuel supply system S2, the solenoid valve 3 and the fuel nozzle 4.

[0035] The main fuel supply system S1 includes a mechanical fuel pump 11, a main overflow valve 12, an electronic fuel regulator 13, and a fuel cut-off valve 14. The mechanical fuel pump 11 is driv...

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Abstract

The invention proposes a dual margin aero-engine fuel adjustment control system. It includes main and auxiliary fuel supply systems and solenoid valves. The main fuel supply system includes sequentially connected mechanical fuel pumps, main overflow valves, electronic fuel regulators and fuel cut-off valves. The auxiliary fuel supply system includes sequentially connected electric fuel pumps, auxiliary The overflow valve, the shuttle valve, and the fuel cut-off valve are connected with the other inlet of the shuttle valve, the shuttle valve is connected with the solenoid valve, and the solenoid valve is connected with the fuel nozzle. The double margin control of the main and auxiliary fuel supply systems is adopted, and when one path fails, the other path can still supply fuel relying on the structure of the shuttle valve to ensure the flight safety of the aircraft, and use the different characteristics of the mechanical fuel pump and the electric fuel pump to ensure It can be controlled with high precision under different flight conditions, and the fuel control is more accurate and reasonable.

Description

technical field [0001] The invention relates to a dual margin aero-engine fuel regulation control system. Background technique [0002] The aero-engine fuel adjustment system is mainly used to supply fuel to the main combustion chamber, afterburner and fuel hydraulic control system, and adjust the fuel supply according to the changes of the engine state and external conditions, so as to ensure that the engine can be stable in all states. Work. [0003] The existing fuel control system in the aviation field is a single-margin control system. Generally, a mechanical fuel pump is used to cooperate with a mechanical fuel adjustment system. Finally, through the mechanical fuel regulator, the fuel oil quantity required by the engine in different flight states is provided. In order to meet the fuel demand in different flight states, the mechanical fuel pump capacity is required to be larger than the design point demand, so as to make up for the starting fuel demand between engines...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B9/03
CPCG05B9/03
Inventor 黄啸顾程王石柱
Owner 上海尚实航空发动机股份有限公司
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