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Interstage rotation detonation variable cycle turboshaft engine

A turboshaft engine and variable cycle technology, which is applied to engine components, engine cooling, machines/engines, etc., can solve the problems of low kerosene activity and difficulty in direct detonation, and achieve the effect of reducing the difficulty of design

Active Publication Date: 2021-06-04
XIAMEN UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the activity of kerosene is low, and it is difficult to detonate directly in the rotating detonation combustion chamber.

Method used

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  • Interstage rotation detonation variable cycle turboshaft engine
  • Interstage rotation detonation variable cycle turboshaft engine
  • Interstage rotation detonation variable cycle turboshaft engine

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Embodiment Construction

[0028] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer and clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0029] Such as figure 1 As shown, this embodiment includes an inner casing 1 , an outer casing 2 , a power shaft 8 , a core machine 3 , a central chamber 16 , a power turbine 6 , a splitter plate, an oil circuit assembly 13 , and an igniter 14 .

[0030] The inside of the inner casing 1 is provided with a core machine 3, a central chamber 16 and a power turbine 6 in sequence from front to back; Output Power.

[0031] The core engine 3 includes a compressor 31 , an isobaric combustion chamber 32 and a gas turbine 33 , wherein the compressor 31 and the gas turbine 33 are connected by a high-pressure rotor shaft 11 and rotate synchronously.

[0032] A cooling flow path 12 is formed between the inner casi...

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Abstract

The invention discloses an interstage rotation detonation variable cycle turboshaft engine. A core machine, a center cavity and a power turbine are sequentially arranged in an inner casing; the center cavity and the power turbine are both connected with a power shaft; a cooling flow path is formed between the inner casing and an outer casing, an interstage rotation detonation combustion chamber is formed between the inner casing and the outer wall face of the center cavity, and a mixing cooling chamber is formed between the center cavity and the power turbine; a splitter plate is connected with the inner casing to control cooling air entraining; an oil way assembly is controlled to communicate with the interstage rotation detonation combustion chamber; an igniter is arranged in the interstage rotation detonation combustion chamber and ignites kerosene-air mixed gas entering the interstage rotation detonation combustion chamber so as to form rotation detonation combustion. Derivative problems caused by the scheme that the rotation detonation combustion chamber replaces a turboshaft engine isobaric combustion chamber are avoided, the high-power requirement of a helicopter in a take-off stage and the economical efficiency target of the helicopter in a cruise stage are considered, and the problem that when an existing rotary detonation turboshaft engine adopts kerosene as fuel, direct detonation combustion is difficult to achieve is solved.

Description

technical field [0001] The invention relates to the field of aeroengines, in particular to an interstage rotary detonation variable cycle turboshaft engine. Background technique [0002] Aviation gas turbine shaft engine (referred to as turboshaft engine) is the main power device of the helicopter, and its development level has a decisive influence on the comprehensive performance of the helicopter. In recent years, rotating detonation combustors have attracted extensive attention due to their advantages such as fast heat release rate, small entropy increase, and simultaneous heating and pressurization. Using the rotary detonation combustor to replace the isobaric combustor of the turboshaft engine can reduce the number of compressor stages and reduce the power consumption of the compression system, thereby improving the overall performance of the engine. However, using a rotating detonation combustor to replace the isobaric combustion chamber of a turboshaft engine will in...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C5/00F02C7/264F02C7/12F02C7/22F01D11/00F23R7/00
CPCF02C5/00F02C7/264F02C7/12F02C7/22F01D11/003F23R7/00
Inventor 尤延铖赵廷朱剑锋
Owner XIAMEN UNIV
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