Integrated afterburner for preheating double-oil-way annular flame stabilizer

A flame stabilizer and afterburner technology, applied in the field of aero-engines, can solve problems such as large flow resistance loss, achieve weight reduction, broaden fuel supply range, and increase thrust-to-weight ratio

Active Publication Date: 2021-02-02
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Since the flame stabilizer, oil supply and ignition device do not work when the afterburner is not turned on, this will cause a large loss of flow resistance and produce ineffective resistance

Method used

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  • Integrated afterburner for preheating double-oil-way annular flame stabilizer
  • Integrated afterburner for preheating double-oil-way annular flame stabilizer
  • Integrated afterburner for preheating double-oil-way annular flame stabilizer

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Embodiment Construction

[0045] Embodiments of the present invention are described in detail below, and the embodiments are exemplary and intended to explain the present invention, but should not be construed as limiting the present invention.

[0046] An integrated afterburner for a preheating double oil passage annular flame stabilizer in this embodiment includes an afterburner inner cone, a central annular flame stabilizer, an outer annular flame stabilizer, an inner annular flame stabilizer and a radial flame stabilizer.

[0047] The central axis of the afterburner inner cone is arranged at the central axis of the afterburner casing; the front part of the afterburner inner cone is evenly arranged with 4 oil inlets, and the side of the afterburner inner cone has 4 oil outlets. The rear end of the inner cone has a fuel injection hole; after the fuel inlet of the afterburner inner cone, there is an independent fuel channel. There are 4 oil outlets on the side of the inner cone and a fuel injection h...

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Abstract

The invention provides an integrated afterburner for preheating a double-oil-way annular flame stabilizer. The integrated afterburner comprises an inner afterburner cone, a central annular flame stabilizer, an outer side annular flame stabilizer, an inner side annular flame stabilizer and radial flame stabilizers. A double-oil-way injection mode is adopted, fuel oil and air are mixed, atomizationmixing is enhanced, and the oil supply range of an engine is widened. An air inlet groove is formed in the inner afterburner cone, the fuel oil in a fuel oil channel, close to the air inlet groove, inthe inner afterburner cone is evaporated and atomized, the fuel oil atomization effect is effectively improved, then the combustion efficiency is improved, the weight of the afterburner is reduced, and the thrust-weight ratio is increased. The radial flame stabilizer is arranged behind the air inlet groove, so that the speed of incoming flows entering the air inlet groove is reduced, and the flame stabilizing effect is achieved. The working condition process from small stress application to maximum stress application is achieved by controlling oil injection of radial and annular flame stabilizer tail spray holes. The radial flame stabilizers are distributed in a staggered mode, and the effect of forming a low-speed backflow area to stabilize flames is achieved.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to an integrated afterburner for a preheating double oil passage annular flame stabilizer. Background technique [0002] With the rapid development of turbofan engines in the late 1960s and the emergence of variable cycle engines in the 1970s, the afterburner was used as an important technology to enhance the maneuverability of the engine. Its function is mainly to increase the thrust of the engine and enhance the maneuverability of the aircraft on military engines. For most engines, after the afterburner is turned on, the thrust is increased by about 50% compared with the thrust in the maximum state. Because the fuel consumption rate is high after the afterburner is turned on, it is only used for military aircraft to accelerate sharply during takeoff, climb and battle. work in the state. [0003] The afterburner is located between the turbine and the tail nozzle. The high-te...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28
CPCF23R3/28
Inventor 王治武张隆飞秦为峰刘志伟力斯王亚非
Owner NORTHWESTERN POLYTECHNICAL UNIV
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