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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 off from zero speed under the existing RBCC rocket ejection mode, and the problem that the engine is ejected from the ejection mode. The problem of slow acceleration from injection mode to sub-combustion stamping mode

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  • Turbo-rocket combined ramjet engine and operating method thereof

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Embodiment Construction

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

[0021] The invention provides a turbo-rocket combined ramjet engine, such as figure 1 As shown, the air turbine ramjet engine and the rocket basic cycle combination engine including the common inlet 1 and the common exhaust nozzle 5 can reduce air resistance by sharing the inlet 1 and the exhaust nozzle 5 .

[0022] The duct of the air intake 1 is provided with an air intake guide 2, and the air intake guide 2 is used to turn and close the inlet of the rocket basic cycle combined engine when the air turbo ramjet starts at a low speed, so that the air intake 1 communicates with the interior of the air turbo ramjet; it is also used to divert and seal the inlet of the air turbo ramjet when the speed of the air turbo ramjet is greater than or equal to Mach 2, so as to communicate the inlet 1 with the interior of the rocket...

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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...

Claims

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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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