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Design method for common exhaust nozzle of unilateral expansion four-channel combined engine

A unilateral expansion and design method technology, applied in the direction of machines/engines, rocket engine devices, mechanical equipment, etc., can solve the problems of large space and large exhaust system occupation, and achieve the goal of reducing difficulty, compact structure, and reducing resistance Effect

Active Publication Date: 2019-07-16
XIAMEN UNIV
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  • Summary
  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For the parallel TBCC combined engine, if each channel is exhausted separately, there will be a problem that the exhaust system occupies a large space, which brings great challenges to the integrated design of the high-speed aircraft

Method used

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  • Design method for common exhaust nozzle of unilateral expansion four-channel combined engine
  • Design method for common exhaust nozzle of unilateral expansion four-channel combined engine
  • Design method for common exhaust nozzle of unilateral expansion four-channel combined engine

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Embodiment Construction

[0024] The following embodiments will further illustrate the present invention in conjunction with the accompanying drawings.

[0025] Embodiments of the present invention include the following steps:

[0026] Step 1: Design the ramjet exhaust nozzle profile based on the unilateral expansion theory

[0027] Design the upper and lower wall profiles of the unilateral expansion nozzle, using the asymmetric sub-combustion ramjet exhaust nozzle design method based on the short nozzle theory (M.Goeing, Nozzle Design Optimization by Method-of-Characteristics.AIAA- 90-2024): Compress all the expansion sections to a sharp corner of the throat, and then calculate the flow field to obtain the nozzle shape of the nozzle. Shortened length nozzle theory For any internal point in the flow field, firstly determine the airflow turning angle and airflow direction angle at this point, and then calculate the Mach number at this point according to the Prandtl-Meier relationship to obtain the Mach...

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Abstract

The invention discloses a design method of a common exhaust nozzle of a unilateral expansion four-channel combined engine, and relates to hypersonic aircrafts. The method includes: designing a three-dimensional model of the exhaust nozzle of the unilateral expansion asymmetric subcombustion ramjet; designing an exhaust nozzle of a turbine engine channel and a rocket engine channel; designing a parallel type TBCC engine common exhaust nozzle combination structure; design adjusting mechanism. Spraying pipes of a plurality of engines are integrated, centralized exhaust is achieved, the problem that thrust of multi-channel tail spraying pipes of the engines is asymmetric is solved, the resistance of the parallel TBCC engine is reduced, and the throat area can be adjusted through an adjusting plate so that the thrust requirement of the parallel TBCC engine within the wide speed range can be met. The four channels are integrated on the sub-combustion ramjet pipe of the ramjet, so that the structure is more compact, the difficulty of integrated design of the aircraft and the engine is reduced, and great advantages are achieved in moment balancing of integrated design of the aircraft and the engine.

Description

technical field [0001] The invention relates to a hypersonic aircraft, in particular to a design method for a common exhaust nozzle of a unilateral expansion four-channel combined engine exhaust nozzle of a parallel turbine-based combined cycle power (TurbineBased Combined Cycle, TBCC) engine. Background technique [0002] Hypersonic aircraft is a high-tech project focused on development in the 21st century. The supersonic ramjet is considered to be the "third power revolution" after the propeller and jet propulsion. Due to its simple structure and no need to carry oxidant, it is regarded as the best power choice for hypersonic aircraft. However, the ramjet engine can only start and work normally at a high Mach number. In order to enable the hypersonic vehicle to have the ability of autonomous horizontal take-off and landing and high Mach number cruise, scholars have proposed the Turbine Based Combined Cycle (TBCC) (Li Chao, Aerodynamic Design, Performance Research and Prel...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50F02K1/00F02K9/97
CPCF02K1/00F02K9/97G06F30/15G06F30/20Y02T90/00
Inventor 陈荣钱柳家齐黄阳灿吴林宽龙华强尤延铖
Owner XIAMEN UNIV