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Design method of three-power combination engine with common sub-combustion chamber

A sub-combustion combustion chamber and engine technology, applied in the field of three-power combined engine design, can solve the problems of long engineering application and low maturity, and achieve the effect of simple and reliable structure

Active Publication Date: 2020-03-27
XIAMEN UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the maturity of this technology is low at present, and it is far away from the realization of engineering application.

Method used

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  • Design method of three-power combination engine with common sub-combustion chamber
  • Design method of three-power combination engine with common sub-combustion chamber
  • Design method of three-power combination engine with common sub-combustion chamber

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Embodiment Construction

[0022] The following embodiments will further illustrate the present invention in conjunction with the accompanying drawings.

[0023] In the three-power combination engine sharing the sub-combustion chamber, the three-dimensional inward rotation inlet has three outlets: one connected to the turbine channel, one connected to the rocket channel and one connected to the ram channel. When the flight Mach number is 0-2, the turbine engine is ignited, the turbine channel splitter plate is opened, the rocket channel splitter plate is closed, and the ram channel is not ignited and is in a state of leakage. When the flight Mach number is 2-3, the turbine channel splitter plate is closed, the rocket channel splitter plate is opened, the rocket engine and the sub-combustion combustion chamber are ignited, and the ram channel acts as a discharge. When the flight Mach number is 3 to 4.5, the sub-combustion chamber stops working, the rocket engine continues to work, and the ram channel act...

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Abstract

The invention discloses a design method for a three-power combined engine sharing a sub-combustion combustion chamber, and relates to a combined engine. The design method is characterized in that a design technology for the three-power combined engine is introduced, wherein a rocket which is in parallel connection to a turbine engine is used to perform turbine-stamping thrust bridging, and the three-power combined engine shares the sub-combustion combustion chamber and is in series-parallel connection. The combined engine forms power hybrid application, and a rocket and turbine parallel-connection runner mode effectively crosses a thrust wide gap, and reduces complexity of the three-power combined system. The combined engine integrates advantages of high specific impulse of the turbine engine, high Mach structure of a ramjet engine and all-speed domain of a rocket engine, and has the advantages of being moderate in technical difficulty, capable of being repeatedly used, and the like. Avalve is selected by only needing one runner, so that the turbine engine and the rocket engine share one set of sub-combustion combustion chamber and a spray tube, and therefore, compared with a conventional three-channel three-power combined engine, the combined engine can reduce one set of sub-combustion combustion chamber and the spray tube, and therefore, the combined engine has the advantages of being simple and reliable in structure.

Description

technical field [0001] The invention relates to a combination engine, in particular to a design method for a three-power combination engine with a turbine and a rocket connected in parallel and sharing a subcombustion combustion chamber. Background technique [0002] Hypersonic flight is considered to be the third revolution after propellers and jet propulsion. All major military powers in the world, led by the United States, attach great importance to the research of hypersonic aircraft technology. At present, the frontier hotspots of academic research on aerospace vehicles are shifting from the development of scramjet engines to the research of combined power systems capable of horizontal take-off and acceleration to hypersonic speeds, among which the development of turbine-based combined cycle engines is the focus . Turbine-based combined cycle engine (TBCC) refers to a power plant composed of a turbine engine and other types of engines. It is one of the key power system...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K7/16F02K7/18F02K7/14
CPCF02K7/14F02K7/16F02K7/18
Inventor 尤延铖李伟朱剑锋
Owner XIAMEN UNIV
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