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Afterburner and turbine engines

A technology of afterburner and combustion chamber, applied in the direction of combustion chamber, deflagration combustion chamber, gas turbine device, etc., can solve the problems of unstable combustion, limitation of working time and performance of afterburner, and decrease of working ability. , to solve the combustion instability, improve the working ability, and improve the thermal efficiency.

Active Publication Date: 2018-07-27
清航空天(浙江)科技有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional conventional gas turbine engine afterburner seriously affects the air time of fighter jets due to its extremely high fuel consumption
In addition, the conventional afterburner has the problem of unstable combustion, which may lead to engine flameout and damage to the system structure, further limiting the working time and performance of the afterburner
In addition, before the gas enters the afterburner, it has been expanded by the turbine, the pressure of the working medium is low, and the work ability is reduced

Method used

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  • Afterburner and turbine engines
  • Afterburner and turbine engines
  • Afterburner and turbine engines

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Embodiment Construction

[0035] The afterburner and turbine engine according to the present invention will be described in detail below with reference to the accompanying drawings.

[0036] First, the afterburner according to the first aspect of the present invention will be described.

[0037] refer to Figure 1 to Figure 4 , The afterburner 1 according to the present invention includes: an outer cylinder assembly 11 ; a central body assembly 12 , an oil circuit assembly 13 , an annular combustion chamber 14 and an igniter 16 .

[0038] The central body assembly 12 is accommodated in the outer cylinder assembly 11 and forms an annular combustion chamber 14 with the outer cylinder assembly 11 . The oil circuit assembly 13 is controlled to communicate with the annular combustion chamber 14 to provide fuel (ie fuel oil) to the annular combustion chamber 14 . Among them, the center body assembly 12 includes: a front body 12f, which is located at the axial front end of the afterburner 1 and forms an ann...

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Abstract

The invention provides an afterburner and a turbine engine. The afterburner comprises an outer cylinder assembly, a center body assembly, an oil way assembly, an annular combustion chamber and an igniter; the center body assembly comprises a front body, a middle body and a rear body, wherein the front body is located at the axial front end of the afterburner and forms a gas inlet, accepting entry of oxygen-containing gas, of the annular combustion chamber with the outer cylinder assembly, the middle body is located behind the front body along the axis and is connected to the front body and integrated with the front body, and the rear body is located behind the middle body in the axial direction, is arranged in the middle body in a slid and sleeved mode and forms a gas outlet of the annular combustion chamber with the outer cylinder assembly; the igniter is arranged at the corresponding part, forming the annular combustion chamber with the outer cylinder assembly, of the center body assembly and is used for igniting fuel gas formed by fuel and the oxygen-containing gas entering the annular combustion chamber, then rotation and knocking combustion of the fuel gas are realized, and therefore the problem that combustion of the afterburner is instable is solved, the heat efficiency of combustion is improved, and the power capability of working media is improved.

Description

technical field [0001] The invention relates to the technical field of aerospace power, in particular to an afterburner and a turbine engine. Background technique [0002] The afterburner is one of the important components of the military small-duct aviation gas turbine engine. Its mass accounts for a very small proportion in the total mass of the engine, but it can greatly increase the thrust of the engine in a short time, thereby improving the maneuverability of the aircraft. , Expand the flight envelope, and seize air supremacy. The traditional conventional gas turbine engine afterburner seriously affects the air time of fighter jets due to its extremely high fuel consumption rate. In addition, the conventional afterburner has the problem of unstable combustion, which may cause engine flameout and damage to the system structure, further limiting the working time and performance of the afterburner. In addition, before the gas enters the afterburner, it has been expanded ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R7/00F02C3/14
CPCF02C3/14F23R7/00
Inventor 王兵计自飞谢峤峰张会强
Owner 清航空天(浙江)科技有限公司
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