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Turboramjet combined engine based on knocking combustion

A technology of turbo ramming combination and detonation engine, which is applied in the direction of combined engine, ramjet engine, mechanical equipment, etc., can solve the problems of long machine size, complex structure and many parts, etc. The effect of improving propulsion performance

Inactive Publication Date: 2011-08-17
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to overcome the deficiencies of the existing turbo-ramjet combined engine, such as long size, heavy weight, complex structure, and many parts, and improve its propulsion performance based on detonation combustion, the present invention proposes a turbine engine based on detonation combustion. The ramjet combination engine, in the subsonic and low supersonic state, the engine is in the working mode of the front turbine combined pulse detonation engine, and in the hypersonic state, the engine switches to the ramjet pulse detonation engine working mode, the two The two modes share the detonation combustion chamber, and all propulsion is based on detonation combustion.

Method used

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  • Turboramjet combined engine based on knocking combustion
  • Turboramjet combined engine based on knocking combustion
  • Turboramjet combined engine based on knocking combustion

Examples

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Embodiment 1

[0020] like image 3 As shown, it includes a front turbine combined pulse detonation engine a, an adjustable center cone 1, a complete machine housing 2, an adjustable air inlet 3, an adjustable inlet guide vane 4, an air duct 5 and an adjustable plate 6a , along the airflow direction of the combined engine, the adjustable central cone 1 is located at the front end of the engine, and the ring cavity surrounded by the whole machine casing 2 forms an adjustable air inlet 3, and the downstream of the adjustable central cone 1 is connected to the front turbine Combined pulse detonation engine a, upstream along the compressor casing a2 of the long front turbine combined pulse detonation engine, at least one stage of compressor length, combined pulse detonation in the long compressor casing a2 and the front turbine The upstream of the compressor a1 of the engine is installed with adjustable inlet guide vanes 4, the compressor case a2 of the combined pulse detonation engine with the ...

Embodiment 2

[0022] like Figure 4 As shown, it includes a front turbine combined pulse detonation engine a, an adjustable center cone 1, a complete machine casing 2, an adjustable air inlet 3, an adjustable inlet guide vane 4, an air duct 5 and an adjustable plate 6b , along the airflow direction of the engine, the adjustable central cone 1 is located at the front end of the engine, and the ring cavity surrounded by the whole machine casing 2 forms an adjustable air inlet 3, and the downstream of the adjustable central cone 1 is connected to the pre-turbine combination Pulse detonation engine a, upstream along the compressor casing a2 of the long front turbine combined pulse detonation engine with at least one stage of compressor length, in the long compressor casing a2 and the front turbine combined pulse detonation engine The upstream of the compressor a1 is equipped with adjustable inlet guide vanes 4, and the compressor case a2 of the front turbine combined pulse detonation engine and...

Embodiment 3

[0024] like Figure 5 As shown, it includes a front turbine combined pulse detonation engine a, an adjustable center cone 1, a complete machine casing 2, an adjustable air inlet 3, an adjustable inlet guide vane 4, an air duct 5 and an adjustable plate 6b , Cooling air duct 7, mixer 8 and nozzle 9. Along the airflow direction of the engine, the adjustable central cone 1 is located at the front end of the engine, and the ring cavity surrounded by the whole machine casing 2 forms an adjustable air inlet 3, and the downstream of the adjustable central cone 1 is connected to the front turbine combination pulse The detonation engine a, upstream along the compressor case a2 of the long pre-turbine combination pulse detonation engine, at least one stage of compressor length, in the long compressor case a2 and the pre-turbine combination pulse detonation engine The adjustable inlet guide vane 4 is installed upstream of the compressor a1, and the compressor casing a2 of the front turb...

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Abstract

The invention discloses a turboramjet combined engine based on knocking combustion. Along the air flow direction, an adjustable central conical body is positioned at the forefront end of the combined engine, and surrounds into an adjustable air intake channel with a shell; the downstream of the adjustable central conical body is connected with an air intake device of a preposed turbine combined pulsation knocking engine; the upstream of an air pressing machine of the preposed turbine combined pulsation knocking engine is provided with an adjustable inlet guiding blade; an engine shell of the preposed turbine combined pulsation knocking engine surrounds into an annular air duct with the shell; and an adjustable plate is positioned at an expanding pressure buffer chamber between the air duct and the preposed turbine combined pulsation knocking engine. By the turboramjet combined engine based on knocking combustion provided by the invention, the problems of long size, great weight, complex structure, many components, and the like of a complete machine are solved, and simultaneously the propulsive performance of the turboramjet combined engine based on the knocking combustion is improved.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a pulse detonation engine. Background technique [0002] The discovery of detonation waves can be traced back to the end of the 18th century. Compared with deflagration waves, the propagation speed of detonation waves can reach several kilometers per second, and at the same time, extremely high gas pressure (greater than 15 to 55 atmospheres) and gas temperature (greater than 2800K), according to the traditional CJ ​​theory, the CJ knock point is the minimum point of entropy increase, which means that the propulsion system based on detonation combustion will have an advantage in thermal cycle efficiency, so since the 1940s, Various institutions are competing to study detonation engines, and various types of pulse detonation engines based on detonation combustion have appeared in the exploration and research stage for more than 60 years. According to what Boeing and Pratt & Whitn...

Claims

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Application Information

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IPC IPC(8): F02K7/20
Inventor 邱华熊姹严传俊范玮郑龙席
Owner NORTHWESTERN POLYTECHNICAL UNIV
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