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A design method of fuel supply filling rate for aero-engine start-up

An aero-engine and design method technology, applied in complex mathematical operations, geometric CAD, special data processing applications, etc., can solve problems such as compressor stall, ignition failure, etc., to reduce stall, improve the success rate of starting ignition, and ensure consistency Effect

Active Publication Date: 2022-04-01
AECC SHENYANG ENGINE RES INST
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Problems solved by technology

[0005] The purpose of this application is to provide a method for designing the fuel supply filling rate at the start of an aero-engine to solve the problem of compressor stall or ignition failure in the prior art when the turbine engine starts fuel supply

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  • A design method of fuel supply filling rate for aero-engine start-up

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Embodiment Construction

[0019] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application.

[0020] A method for designing the filling rate of starting fuel supply for an aero-engine. This application adopts the method of ensuring the consistency of ignition performance in the starting process to solve the problem of compressor stall or ignition failure during starting fuel supply.

[0021] Such as figure 1 shown, including the following steps:

[0022] Step S100, using the fuel filling amount m fill and the increase in the conversion speed of the high-pressure rotor during the filling process Δn hr Get High Pressure Rotor Acceleration n hr,dot fill rate with start-up phase W fb The corresponding relationship, calculate the filling rate W fb ;

[0023] In order to be able to run at a giv...

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Abstract

This application belongs to the field of aero-engine design, and is a method for designing the fuel supply filling rate at the start of an aero-engine. Through calculation, the expression of the acceleration rate of the high-pressure rotor and the filling rate at the start-up stage is obtained, and the corresponding relationship between the acceleration rate of the high-pressure rotor and the filling rate at the start-up stage is found. , that is to use the acceleration rate of the high-pressure rotor to calculate the filling rate. The filling rate obtained in this way is only affected by the acceleration rate of the high-pressure rotor and is not affected by the high-voltage conversion speed. It can accurately control the speed at the end of filling and improve the supply of the starting filling section. Oil consistency, improve the success rate of starting ignition, and reduce the possibility of compressor stall caused by ignition. At the same time, considering the limitation of the filling rate, the coefficients in the calculation formula of the filling rate are updated in real time to ensure the consistency of filling and improve the adaptability of the method.

Description

technical field [0001] The application belongs to the field of aero-engine design, and in particular relates to a method for designing an aero-engine start-up fuel supply filling rate. Background technique [0002] The fuel supply during the start-up process of a turbine engine based on an open nozzle is generally divided into three sections: filling section, ignition section, and acceleration section. The requirement for the fill section is to fill up the fuel rail when the engine reaches ignition speed. The ignition speed of the engine needs to be controlled within a relatively small range to ensure good ignition performance. In this context, the speed at the end of filling is also required to be precisely controlled. [0003] The conventional oil supply rule for the filling section is to set the filling rate W fb Described as high-pressure conversion speed n hr The function. The problem with this oil supply rule is that the speed of the engine is not consistent when t...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F17/11
CPCG06F30/15G06F17/11
Inventor 贾琳渊程荣辉陈泽华袁继来姜繁生邴连喜
Owner AECC SHENYANG ENGINE RES INST
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