Aeroengine combustor and method of operation thereof

An aero-engine and combustion chamber technology, which is applied in the field of aero-engines, can solve problems such as the superior performance of unfavorable pulse detonation engines, and achieve the effects of reliable guarantee, avoidance of ignition failure, and optimal mixing rate.

Active Publication Date: 2021-04-06
成都裕鸢航空智能制造股份有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In actual use, the length of the engine is limited. In order to meet the detonation conditions of the pulse deflagration engine, only a composite fuel with strong detonation can be used, or a strengthening device is installed in the combustion chamber structure.
However, the above measures are not conducive to the full play of the superior performance of the pulse detonation engine.

Method used

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  • Aeroengine combustor and method of operation thereof
  • Aeroengine combustor and method of operation thereof
  • Aeroengine combustor and method of operation thereof

Examples

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Embodiment Construction

[0048] In the following, only some exemplary embodiments are briefly described. As those skilled in the art would realize, the described embodiments may be modified in various different ways, all without departing from the spirit or scope of the embodiments of the application. Accordingly, the drawings and descriptions are to be regarded as illustrative in nature and not restrictive.

[0049] In the description of the embodiments of the present application, it should be understood that the orientations or positional relationships indicated by the terms "front", "rear", "inner", "outer", and "axial" are based on those shown in the accompanying drawings. Orientation or positional relationship is only for the convenience of describing the embodiment of the application and simplifying the description, and does not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, so it cannot be understood...

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Abstract

The invention provides an aero-engine combustion chamber, which is arranged between an oil-gas mixing chamber and a nozzle, and includes a combustion chamber formed by the pipe wall of the combustion chamber. The front end of the combustion chamber has a flaring part, which communicates with the oil-gas mixing chamber; the rear end of the combustion chamber has a constriction part, which communicates with the nozzle; wherein, the flaring part is movably sealed by a disc-shaped air-mixing input valve assembly; the constriction part is equipped with A little lighter. The present invention adopts the way of post-ignition, cooperates with the disc-shaped air-mixing input valve assembly arranged at the front end of the combustion chamber of the combustion chamber to actively seal the combustion chamber, and shortens the DDT distance. The present invention also provides a working method for the combustion chamber of an aero-engine, which prolongs the mixing time of oil and gas raw materials to increase their mixing rate through the post-ignition mode, thereby ensuring the success rate of ignition; The active sealing of the components to the combustion chamber effectively shortens the DDT distance and broadens the use range of raw oil and gas.

Description

technical field [0001] The present application relates to the technical field of aero-engines, in particular to an aero-engine combustion chamber and a working method of the aero-engine combustion chamber. Background technique [0002] After more than a hundred years of development, aero engines have produced a variety of mature products with high reliability. They are not only used as power for military and civilian aircraft, drones and cruise missiles for various purposes, but their derivative products are also used in electric power, Oil and gas exploration and other fields. At present, the development of aero-engines is accelerating, and a variety of non-traditional new aero-engines have been developed with the goals of "faster", "higher", "further", and "more economical". Among them, the pulse detonation engine, as a non-traditional new type of aero-engine, has become a hot spot in many countries because of its advantages of high cycle thermal efficiency, high specific...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K7/067F02C7/057F02C7/04F02C7/22F02C7/264F23R7/00
CPCF02C7/04F02C7/057F02C7/222F02C7/264F02K7/067F23R7/00
Inventor 周继德刘勇涛
Owner 成都裕鸢航空智能制造股份有限公司
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