Fuel gas generator and testing device suitable for test of swallowing gunpowder gas by engine

A gas generator and engine technology, applied in rocket engine devices, jet propulsion devices, machines/engines, etc., can solve problems such as danger and inability to control high-temperature exhaust gas flow, and achieve the effect of work safety and strong controllability

Active Publication Date: 2017-07-28
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the current test device cannot control the flow rate of the sim

Method used

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  • Fuel gas generator and testing device suitable for test of swallowing gunpowder gas by engine
  • Fuel gas generator and testing device suitable for test of swallowing gunpowder gas by engine
  • Fuel gas generator and testing device suitable for test of swallowing gunpowder gas by engine

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Example Embodiment

[0048] The technical solution of the present invention will be further described below according to specific embodiments. The protection scope of the present invention is not limited to the following embodiments, and these examples are only for exemplary purposes and do not limit the present invention in any way.

[0049] The test device of the present invention is a special test device that is finally designed to meet the test requirements based on the technical requirements of the engine swallowing gunpowder gas test, and through the efforts of multiple directions such as consulting data, program demonstration, numerical calculation, and test verification.

[0050] figure 1 It is a schematic diagram of the structure of the test device of an embodiment of the present invention, such as figure 1 As shown, the test device suitable for the test of engine swallowing gunpowder gas includes a gas generator 2, an exhaust pipe, a V-shaped ball valve 1, a V-shaped ball valve 3, and a contro...

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Abstract

The invention provides a fuel gas generator and a testing device suitable for a test of swallowing gunpowder gas by an engine. The fuel gas generator comprises an ignition device, a combustor, a gas collection chamber and an exhaust nozzle, wherein the ignition device is arranged at one end of the fuel gas generator, a plurality of grains are installed in the combustor and are in contact with the ignition, the gas collection chamber is arranged outside the combustor, the combustor is covered with the gas collection chamber, and the exhaust nozzle is arranged at the other end of the fuel gas generator and communicates with the gas collection chamber. The fuel gas generator and the testing device are high in controllability, safe and stable in operation, capable of precisely simulating the environment of high-temperature gas ejected from rocket projectiles, guided missiles and other weapon exhaust nozzles, capable of meeting the demand of conducting the test of swallowing gunpowder gas by the engine or a test of sucking weapon exhaust gas when an aircraft and the engine are shaped, and fills up the vacancy in the special test field at home.

Description

technical field [0001] The invention relates to the field of engine testing devices, in particular to a gas generator suitable for the test of engines swallowing gunpowder gas. Background technique [0002] In combat, the high-temperature exhaust gas produced by the aircraft itself launching missiles, rockets and other weapons is easily inhaled by the aircraft engine, causing the engine intake temperature to rise sharply, resulting in engine intake distortion, performance deterioration, and power loss. Reducing the stable working envelope of the engine may even cause the engine to stall, surge, stall, and stop in the air, which will not only delay the fighter plane, but may also cause the plane to crash. Therefore, when the engine or aircraft is finalized, it is necessary to carry out the engine swallowing gunpowder gas test. [0003] The engine swallows gunpowder gas test, also known as the inhalation aircraft weapon exhaust test. The aircraft inhales the high-temperature...

Claims

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Application Information

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IPC IPC(8): F02K9/96
CPCF02K9/96
Inventor 陈玮张永飞刘知理吴志勇韦海龙
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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