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A high-altitude ignition-starting missile engine

A technology of engines and starter motors, which is applied in the direction of machines/engines, mechanical equipment, gas turbine devices, etc., can solve the problems of high-altitude ignition and starting of bomb aviation turbojet and turbofan engines, and solve the problem of high-altitude ignition and starting, significantly The effect of engineering application value

Active Publication Date: 2018-05-04
JIANGXI HONGDU AVIATION IND GRP
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] Purpose of the present invention: In order to solve the problem of difficult high-altitude ignition and starting of the current bomb aviation turbojet and turbofan engines equipped with embedded air inlets, the present invention proposes a high-altitude ignition and starting bomb engine

Method used

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  • A high-altitude ignition-starting missile engine
  • A high-altitude ignition-starting missile engine
  • A high-altitude ignition-starting missile engine

Examples

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Embodiment Construction

[0013] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0014] Such as Figure 1-3 Shown, a kind of high-altitude ignition start bomb engine, described high-altitude ignition start bomb engine is installed in the aircraft 1, including:

[0015] The engine 6 and the embedded air intake 3, the engine 6 is connected with the embedded air intake 3 through the flange 4, the rubber sealing ring 5 in the groove of the flange 4, the Embedded air inlet 3 inlets are provided with front blocking cover 2, and engine 6 spout places are provided with rear blocking cover 8; Described engine 6 inside is equipped with starter motor 7, after aircraft 1 assembly is finished, to engine 6 and buried Vacuumize the interior of the in-type air inlet 3;

[0016] When the engine 6 is ready to ignite and start, under vacuum conditions, use the starter motor 7 to directly bring the engine 6 speed to more than 90% speed; then open the front...

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Abstract

The invention relates to a high-altitude ignition starting engine for bombs. The problems that gas injecting of a current aviation turbine used for the bombs and provided with an embedded type gas inlet channel and high-altitude ignition starting of a turbofan engine are difficult are solved. The high-altitude ignition starting engine for the bombs is installed in an aircraft (1) and comprises an engine (6) and an embedded type gas inlet channel (3); the engine (6) is connected with the embedded type gas inlet channel (3) through a flange plate (4); a rubber sealing ring (5) is arranged in a groove of the flange plate (4); a front plugging cover (2) is arranged at the position of an inlet of the embedded type gas inlet channel (3); a rear plugging cover (8) is arranged at the position of a spraying port of the engine (6); a starting motor (7) is installed in the engine (6); and after final assembly of the aircraft (1) is completed, the interior of the engine (6) and the interior of the embedded type gas inlet channel (3) are vacuumized.

Description

technical field [0001] The invention relates to an ammunition engine, in particular to an ammunition engine capable of being ignited and started at high altitude. Background technique [0002] In order to deal with the air ignition of the engine, the traditional method is to use a combination of pyrotechnic starter, pyrotechnic igniter and electric igniter to start, and the buried air inlet is often selected as the air intake device of the engine. [0003] However, the engine must solve the key technology of ignition and starting at high altitude (for example, 7000m). The low total pressure recovery coefficient of the buried intake port in the low flow state of the engine ignition and starting stage makes the problem of high-altitude ignition a higher challenge. . The main difficulty is that the pyrotechnic starter is difficult to turn the engine to a speed above 65.0% idle when the engine is full of air. When the pyrotechnic starter finishes working, the turbine cannot pro...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/266
CPCF02C7/266
Inventor 王春利卢杰赵胜海任志文万志明万俊丹戴佳赵政衡陈尊敬肖毅周俊伟杨佳壁王天绥
Owner JIANGXI HONGDU AVIATION IND GRP
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