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Plasma synthetic jet combustion chamber

A technology of synthetic jet and combustion chamber, which is applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of cost and time increase, and achieve the effects of saving economic cost, shortening the processing cycle and ensuring continuity

Active Publication Date: 2022-03-01
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004]However, the structure of the usual combustion chamber is basically fixed, and corresponding test pieces need to be processed for different mixing hole designs, resulting in a double increase in cost and time , and at the same time, in order to improve the combustion efficiency and maintain the stability of the combustion chamber, more solutions need to be proposed

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  • Plasma synthetic jet combustion chamber
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Embodiment Construction

[0024] In order to clearly illustrate the technical characteristics of this patent, the following describes this patent in detail through specific implementation methods and in conjunction with the accompanying drawings.

[0025] The present invention as Figure 1-5 As shown, first tap the external thread 11 on the exciter bushing 8, hollow out the inside, and have small air inlet and outlet holes 13 on the bottom, and at the same time, the side wall is also provided with an air inlet slit 12. The exciter is often due to the extension of working time and discharge The increase in temperature causes insufficient air inhalation in the recovery stage of inhalation, which reduces the jet velocity and weakens the flow control ability. Therefore, two spring diaphragms are welded on the air inlet slit wall 12, and the spring diaphragm presents a convergent "V" shape, forming The configuration of the one-way gas supply actuator is opposite to the incoming flow of the combustion chambe...

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Abstract

The invention discloses a plasma synthetic jet combustion chamber, and relates to the field of aero-engine combustion chamber structures. Various characteristic parameters such as mixing jet flow depth and the like are researched, so that the processing of a test piece is reduced, and the purpose of effectively improving the outlet temperature distribution is finally achieved. A threaded hole located on the outer side of the mixing hole is formed in the cartridge receiver; a plasma synthetic jet exciter is mounted in the threaded hole; the plasma synthetic jet exciter comprises an exciter lining and an electrode mounted in the exciter lining, and an external thread matched with the threaded hole is formed in the outer wall of the exciter lining; the lower portion of the side wall of the plasma synthetic jet exciter is provided with an air inlet seam facing the air inlet flow incoming direction of the combustion chamber, and the bottom of the plasma synthetic jet exciter is provided with small air outlet holes facing the mixing holes. Integrated machining of multiple sets of combustion chamber model test pieces is avoided, the machining period can be greatly shortened, and the economic cost can be greatly saved.

Description

technical field [0001] The invention relates to the field of aero-engine combustor structures, in particular to a design and method for a plasma synthetic jet combustor. Background technique [0002] With the rapid development of aero-engine technology and the continuous improvement of the thrust-to-weight ratio, the combustion chamber will undoubtedly develop in the direction of high oil-gas ratio, high temperature rise and high heat capacity in the future, so the outlet temperature of the combustion chamber will also continue to increase, which is used for outlet temperature distribution adjustment The amount of mixed air is also decreasing, and the turbine works normally in extremely high-temperature harsh environments, and higher requirements are put forward for the outlet temperature distribution coefficient and radial temperature distribution curve. How to ensure that the temperature rise continues to increase Reasonable control of the outlet temperature field is one o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/58F02C5/02
CPCF23R3/58F02C5/02
Inventor 姚倩汤朝伟李建中金武李培星
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS