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Combustion chamber casing

A combustion chamber and outer casing technology, applied in the combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of short axial length, large pressure loss, large radial profile, etc.

Active Publication Date: 2021-01-05
AECC SICHUAN GAS TURBINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the pressure loss of these two combustion chambers increases with the increase of speed, and at the same time, the axial length is short and the radial profile is large in size.

Method used

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Embodiment Construction

[0028] Embodiments of the present disclosure will be described in detail below in conjunction with the accompanying drawings.

[0029] Embodiments of the present disclosure are described below through specific examples, and those skilled in the art can easily understand other advantages and effects of the present disclosure from the contents disclosed in this specification. Apparently, the described embodiments are only some of the embodiments of the present disclosure, not all of them. The present disclosure can also be implemented or applied through different specific implementation modes, and various modifications or changes can be made to the details in this specification based on different viewpoints and applications without departing from the spirit of the present disclosure. It should be noted that, in the case of no conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in the present disclosure, a...

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Abstract

The invention belongs to the field of aero-engines, particularly relates to the field of aero-engines for small bombs, and particularly relates to a combustion chamber casing. The combustion chamber casing comprises an outer casing assembly, an inner casing assembly and a gas compressor final-stage stator blade set. The outer casing assembly is connected with the inner casing assembly through thegas compressor final-stage stator blade set. The inner casing assembly comprises a gas compressor bearing seat, a turbine bearing seat and at least two sets of inner casing cylinders. The inner casingcylinders are sleeved between the gas compressor bearing seat and the turbine bearing seat in a layered manner, a gas inlet is formed in the gas compressor bearing seat, and a gas outlet is formed inthe turbine bearing seat. An air channel between the gas inlet and the gas outlet is formed between the inner casing cylinders. The combustion chamber casing is high in function integration degree ofthe layout structure, effectively utilizes the engine space, greatly shortens the axial length of an engine, reduces the weight of the engine, and achieves low cost and high performance of the engine.

Description

technical field [0001] The invention belongs to the field of aero-engines, in particular to the field of small-sized bomb aero-engines, in particular to a combustor casing. Background technique [0002] Since the 1970s, the rapid development of cruise missile technology has had a profound impact on modern warfare. Especially since the Gulf War in the 1990s, various local wars and regional conflicts in the world, such as the Kosovo War, the US-Iran War, the Libyan War, and the Syrian conflict, have fully proved the important role of precision-guided missiles in modern warfare. [0003] One of the key technologies of cruise missiles is the development of small, high-performance and low-cost aero-engines. At present, in terms of engine research at this level, the most representative ones are the F107 series of the United States and the TRI60 series of France. The former is mainly used for "Tomahawk" cruise missiles, and the latter is used for various drones and missiles. [0...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/00F23R3/02
CPCF23R3/00F23R3/02Y02T50/60
Inventor 时远赵弦宋宇佳郭凯曾宇晖何鹏邓远灏李九龙张伟卢加平徐兵姜山
Owner AECC SICHUAN GAS TURBINE RES INST
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