Time sequence control method for increasing ignition success rate of ramjet

A ramjet and timing control technology, applied in the field of ramjet, can solve the problems of not being able to judge whether the ignition is successful, unable to realize the ignition, not having the combustion chamber monitoring function, etc., to improve the ignition success rate, reliable ignition, and prevent flameout failures. Effect

Active Publication Date: 2016-09-28
NORTHWESTERN POLYTECHNICAL UNIV
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AI Technical Summary

Problems solved by technology

However, due to the fixed use of fuel nozzles, effective ignition can only be achieved for a specific Mach number, and ignition of a wide range of Mach numbers cannot be achieved
Moreover, it does not have the combustion chamber monitoring function, so it cannot judge whether the ignition is successful or whether the combustion chamber is turned off.

Method used

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  • Time sequence control method for increasing ignition success rate of ramjet

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[0042] There are two pressure sensors P installed in the combustion chamber of the engine 1 , P 2 , two temperature sensors T 1 , T 2 , a speed sensor S is installed on the aircraft fuselage 1 . In the engine controller, for Mach numbers of 4.5M and above, 3 to 4.5M, 3M and below, respectively set ignition sequence 1 to match ignition sequence 1; ignition sequence 2 to match ignition sequence 2; ignition sequence 3 to match ignition sequence 3. The specific content of each time sequence is as follows:

[0043]Ignition sequence 1: Turn on fuel nozzle 1 and nozzle 2 in the 1s, start injecting fuel at a speed of 100g / s from nozzle 1 and turn on the igniter in the 1.5s, and inject fuel at a speed of 80g / s in nozzle 2 in the 3s;

[0044] Ignition sequence 2: Turn on fuel nozzle 2 and nozzle 3 at 0.5s, and start injecting fuel at nozzle 3 at a speed of 70g / s and turn on the igniter at 1.2s, and inject fuel at a speed of 50g / s at nozzle 2 at 2.7s;

[0045] Ignition sequence 3:...

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Abstract

The invention relates to a time sequence control method for increasing the ignition success rate of a ramjet. Before ignition, according to different aircraft mach numbers, different working time sequences are set for fuel nozzles. During ignition of a combustion chamber, according to the speed of an aircraft, the fuel nozzles execute corresponding actions according to the time sequences, ignition and stable combustion of fuel are guaranteed, and ignition within the wide mach number range is achieved. After ignition, the state of the combustion chamber is monitored in real time, and whether ignition succeeds or not and whether a flameout fault occurs or not are judged. If ignition fails or flameout occurs, reignition operation is executed, and the ignition success rate of the ramjet is increased. The proper temperature and pressure are key factors for stable combustion of the fuel in the combustion chamber. According to the method, after ignition, the temperature and the pressure of the combustion chamber are detected in real time, when the pressure and the temperature are matched with corresponding conditions, the corresponding matching ignition time sequences are executed, that is, matching control is achieved, stable combustion of the fuel is guaranteed, and the flameout fault is avoided.

Description

technical field [0001] The invention belongs to the field of ramjets, and in particular relates to a time sequence control method for improving the ignition success rate of ramjets. Background technique [0002] The ramjet is an air jet engine that relies on the deceleration and boosting effect of the high-speed oncoming air flow. Its structure is simple, and there are no complicated rotating parts like the compressor and turbine of the turbojet engine. The air entering the engine is compressed by high speed. The stagnation of airflow (ramboost) is obtained. Therefore, the air velocity entering the ramjet combustion chamber is very fast, usually greater than the speed of sound, and the engine works at high altitude, with low ambient temperature and low air density. These factors make it difficult for the combustion chamber to ignite and stabilize combustion. [0003] In order to solve the problem of ignition and flame stabilization in supersonic gas flow, the local subsonic...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/266
CPCF02C7/266
Inventor 马瑞卿李锐韩伟健
Owner NORTHWESTERN POLYTECHNICAL UNIV
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