Turbo-rocket combined ramjet engine and operating method thereof

A technology of ramjet engine and working method, which is applied in the direction of combined engine, ramjet engine, mechanical equipment, etc., and can solve the problems of slow acceleration, large flow rate of high-thrust rocket, low specific impulse, etc.

Inactive Publication Date: 2016-10-26
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0005] The purpose of the present invention is to provide a turbo-rocket combined ramjet engine and its working method, to solve the shortcomings of the high-thrust rocket flow rate and low specific impulse when taking

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  • Turbo-rocket combined ramjet engine and operating method thereof

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[0020] The technical solutions of the present invention will be further described in detail below through the accompanying drawings and embodiments.

[0021] The invention provides a turbo-rocket combined ramjet, such as figure 1 As shown, including the air turbo ramjet and rocket-based cycle combined engine that share the intake port 1 and share the tail nozzle 5, the common intake port 1 and the tail nozzle 5 can reduce the air resistance.

[0022] The duct of the intake port 1 is provided with an intake port guide 2, which is used to turn and close the inlet of the rocket-based cycle combined engine when the air turbine ramjet starts at low speed to make the intake port 1 is connected to the inside of the air turbine ramjet; it is also used to turn and close the inlet of the air turbine ramjet when the speed of the air turbine ramjet is greater than or equal to Mach 2 to connect the intake port 1 with the rocket-based cycle combined engine. Increase the speed to Mach 6. Among ...

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Abstract

The present invention discloses a turbo-rocket combined ramjet engine, which comprises an air turbine ramjet and a rocket based combined cycle engine that share an air intake passage and an exhaust nozzle. An air intake passage guiding device is disposed on a duct of the air intake passage. The air intake passage guiding device is used for turning to seal an inlet of the rocket based combined cycle engine at low-speed start of the air turbine ramjet to achieve internal communication of the air intake passage and the air turbine ramjet, and further used for turning to seal an inlet of the air turbine ramjet when a speed of the air turbine ramjet is greater than or equal to Mach, thereby achieving internal communication of the air intake passage and the rocket based combined cycle engine to start the ramjet. A solution is provided for the problem that two existing power systems cannot independently and completely meet the power requirements of modern warfare on weapon systems in such aspects as ultrahigh acoustic velocity, superaltitude, high maneuverability and high airspace.

Description

【Technical field】 [0001] The invention belongs to the field of rocket carrier power systems, and in particular relates to a turbo-rocket combined ramjet engine and a working method thereof. 【Background technique】 [0002] The Air Turbine Ramjet (ATR) realizes the organic combination of the two basic propulsion methods of the gas turbine and the ramjet engine. It integrates a gas generator similar to a rocket combustor, and is a propulsion system with a compressor and a turbine. Its performance is between the turbojet engine and the rocket engine. The structure of the scheme is simple, compact and reasonable, and the working range is wide. It works like a turbojet engine at subsonic speed, and is similar to a ramjet with fan supercharging at supersonic speed. Different from the conventional turbojet engine, the temperature at the front end of the turbine is determined by the gas generator, which makes the ATR engine have higher speed characteristics without being limited by t...

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Application Information

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IPC IPC(8): F02K7/18
CPCF02K7/18
Inventor 刘洋祝珊李江刘凯
Owner NORTHWESTERN POLYTECHNICAL UNIV
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