A Coupling Control Method of Afterburner and Free Nozzle of Small Turbojet Engine

A turbojet engine, coupled control technology, applied in engine control, engine function, machine/engine, etc., can solve problems such as causing danger, difficult to achieve optimal working conditions, and inability to guarantee control accuracy, to improve coupling, improve The effect of controlling precision

Active Publication Date: 2020-10-09
SICHUAN AEROSPACE ZHONGTIAN POWER EQUIP CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, small turbojet engines adopt the method of preset free nozzle area gears to carry out the matching control of afterburner and free nozzle, that is, when the afterburner combustion reaches a certain state, the free nozzle area is adjusted to a specific value and afterburner Combustion chamber coordination, control accuracy cannot be guaranteed, the best working condition is difficult to achieve, and it is very likely to cause danger

Method used

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  • A Coupling Control Method of Afterburner and Free Nozzle of Small Turbojet Engine
  • A Coupling Control Method of Afterburner and Free Nozzle of Small Turbojet Engine
  • A Coupling Control Method of Afterburner and Free Nozzle of Small Turbojet Engine

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Embodiment 1

[0024] see Figure 1~5 , the coupling control method of afterburner and free nozzle of small turbojet engine,

[0025] Step 1: Calculate the thrust output of the engine through the GASTURB simulation software. The actual thrust is measured by the thrust scale, and the difference between the thrust output and the actual thrust is calculated, which is used as the input for the coupling control of the afterburner and the free nozzle.

[0026] Step 2: Obtain the actual temperature parameters of the afterburner, the actual pressure parameters of the afterburner and the actual area parameters of the free nozzle by collecting the working state of the afterburner and the adjustment parameters of the free nozzle area, and compare them with those obtained by GASTURB simulation Afterburner simulation temperature parameters, afterburner simulation pressure parameters, and free nozzle simulation area parameters are calculated by difference, and the deviations of afterburner temperature, af...

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Abstract

The invention relates to the field of afterburner and free nozzle coupling control of small turbojet engines, and discloses an afterburner and free nozzle coupling control method for a small turbojetengine. The purpose is to adjust and determine the control law of afterburner and free nozzle regulation according to the actual working state of the engine in the testing stage, determine the optimummatching parameters of an afterburner and a free nozzle in a self-compensation way and realize the coordinative and cooperative work of the afterburner and the free nozzle of the small turbojet engine in an afterburner and free nozzle coupling control way. The afterburner and the free nozzle of the small turbojet engine can be under automatic coupling control, so that an afterburner fuel regulation system and an actuation system are automatically matched for regulation, and accordingly the actual optimal performance operating point of the small turbojet engine is quickly determined.

Description

technical field [0001] The invention relates to the field of coupling control of afterburner and free nozzle of a small turbojet engine, and more specifically relates to a coupling control method of afterburner and free nozzle of a small turbojet engine. Background technique [0002] The control system of a small turbojet engine with an afterburner is the core unit to realize the engine afterburner. Before determining the mass production control scheme, it is necessary to determine the control parameters and the best operating point in the control scheme through a large number of experiments. In the test, the afterburner and the free nozzle are matched with each other through a reasonable control method, and the determination of the actual optimal operating point of the small turbojet engine is an important way to provide the basis for the design of the control scheme for subsequent mass production. At present, small turbojet engines adopt the method of preset free nozzle ar...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/17
CPCF02K1/17F05D2260/81F05D2270/301F05D2270/303F05D2270/706
Inventor 李宗蔚宋勇刘驰何国忠陈溯袁清慧
Owner SICHUAN AEROSPACE ZHONGTIAN POWER EQUIP CO LTD
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