Guide vane-type DBD plasma combustion-supporting exciter for aero-engine combustor

A technology of aero-engines and guide vanes, which is applied in the direction of plasma, machines/engines, mechanical equipment, etc., can solve the problems of low combustion efficiency and difficult combustion stability, and achieve simple manufacturing and installation processes, enhanced combustion-supporting effects, and structural simple effect

Inactive Publication Date: 2018-08-17
AIR FORCE UNIV PLA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to solve the problem that the combustion efficiency of the annular combustion chamber of the aero-engine is not high and the combustion is not easy to be stable, the present invention proposes a DBD plasma combustion-supporting actuator of the aero-engine combustion chamber guide vane

Method used

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  • Guide vane-type DBD plasma combustion-supporting exciter for aero-engine combustor
  • Guide vane-type DBD plasma combustion-supporting exciter for aero-engine combustor
  • Guide vane-type DBD plasma combustion-supporting exciter for aero-engine combustor

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Embodiment Construction

[0037] This embodiment is a guide vane type DBD plasma combustion-supporting actuator in the combustion chamber of an aero-engine. For the convenience of description, the direction of air entry is defined as the front, and the side in contact with the dielectric barrier discharge area is the inner surface of the component. The symmetrical axis of the middle part of the blade is the middle axis of the guide vane.

[0038] This embodiment includes an electrode mounting seat 1 , four flat electrodes 2 , four insulating dielectric plates 3 and a fixed base 4 . in:

[0039] Two groups of four guide vanes 12 are arranged on the lower surface of the electrode mounting seat; the geometric center of the adjacent surface of each group of guide vanes has a mounting groove 8 for a flat electrode and an insulating medium plate. A flat plate electrode 2 and an insulating dielectric plate 3 are sequentially embedded in each of the installation grooves; the inner surface of each of the flat ...

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Abstract

The invention discloses a guide-vane-type DBD plasma combustion-supporting exciter for an aero-engine combustor. Two groups of (four) guide vanes are arrayed on the lower surface of an electrode assembly base; a panel electrode is arranged in an assembly groove at a geometrical center between the adjacent surfaces of the guide vanes of each group through an isolated medium plate; the panel electrodes in the guide vanes of each group are correspondingly parallel to one another; and an air inlet passage is formed between adjacent surfaces of each pair of guide vanes. According to the guide-vane-type DBD plasma combustion-supporting exciter, through the annular cavity air inlet passages arranged before a diffuser of the aero-engine combustor, uniformity of a temperature field at an outlet ofthe aero-engine combustor is improved, and combustion efficiency is improved; the combustion stability range of the combustor is widened; and the guide-vane-type DBD plasma combustion-supporting exciter has the characteristics of being capable of generating large-size plasma activated particles, simple in structure, convenient to manufacture and mount, high in universality and the like; combustionefficiency of the annular combustor of an aero-engine is effectively improved; a flameout limit is widened; and uniformity of the temperature field at the outlet of the combustor is improved.

Description

technical field [0001] The invention relates to plasma combustion enhancement technology in the field of aero-engines, in particular to a guide vane type dielectric barrier discharge plasma combustion-supporting exciter for an aero-engine combustion chamber. The dielectric barrier discharge is called DBD for short. Background technique [0002] With the development of technology in the field of aerodynamics, human beings have put forward higher requirements for the economy and reliability of aerodynamic systems, especially there is an urgent need to improve the performance of aeroengines. How to ensure the stable operation of the engine combustion chamber and effectively improve the combustion reaction rate and combustion efficiency has become a current research hotspot. In 1987, the United States launched the "Comprehensive High Performance Turbine Engine Technology Program", with the goal of doubling the thrust-to-weight ratio of aero-engines. Increasing the outlet tempe...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/00H05H1/24
CPCF02C7/00H05H1/2406
Inventor 何立明邓俊陈一雷健平张华磊陈高成刘鹏飞费力
Owner AIR FORCE UNIV PLA
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