A Lateral Sealing Device for the Middle Adjusting Plate of Combined Nozzle

A technology of sealing device and regulating plate, which is applied in the direction of jet propulsion device, machine/engine, etc., can solve the problem that there is no relatively mature structural design for the side sealing device of the parallel combined nozzle of turboramjet combined engine, and achieve reliable function, The effect of safe and reliable work and reduction of thrust loss

Active Publication Date: 2021-08-03
AECC SICHUAN GAS TURBINE RES INST
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  • Application Information

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Problems solved by technology

[0003] At present, domestic and foreign studies on turbo-ramjet combined engines are competing, but they are basically in the stage of key technology research and complete machine integration verification stage. Therefore, there is no relatively mature structural design for the parallel-connected combined nozzle lateral sealing device of turbo-ramjet combined engines

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  • A Lateral Sealing Device for the Middle Adjusting Plate of Combined Nozzle
  • A Lateral Sealing Device for the Middle Adjusting Plate of Combined Nozzle

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Embodiment Construction

[0020] Embodiments of the present disclosure will be described in detail below in conjunction with the accompanying drawings.

[0021] 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 provides a lateral sealing device for an intermediate regulating plate of a combined nozzle, and relates to the technical field of sealing structure of an aeroengine nozzle. It includes a jaw-type seal housing. The jaws of the jaw-type seal housing are connected to the air outlet of the casing engine nozzle. The two sides of the jaw are respectively rail-type stamping side cooling channels and turbine side cooling channels; jaw type One side of the seal housing is close to the side wall of the middle adjustment plate of the nozzle, and the other side is fixedly installed with the load-bearing frame of the nozzle; the inner wall of the cooling channel on the stamping side is sealed by a Z-shaped stamping sealing plate and an arc-shaped stamping side cold air The stamping side cooling passage surrounded by the sheet; the inner wall of the turbine side cooling passage includes a turbine side cooling passage surrounded by a Z-shaped turbine sealing plate and an arc-shaped turbine side cold air sealing sheet. The invention has metal elastic sealing and self-cooling functions at the same time, meets the functional requirements of the nozzle pipe of the turboram combined engine, and finally ensures the safe and reliable operation of the nozzle pipe.

Description

technical field [0001] The present disclosure relates to the technical field of aero-engine nozzle sealing structure, in particular to a lateral sealing device for a combined nozzle middle adjusting plate. Background technique [0002] The combined turbo-ramjet engine is an ideal power source for reusable near-space high-speed combat aircraft in the future. The combined nozzle used is a parallel binary vector nozzle, and the cooling design and sealing design are important and difficult technologies. and safety have important implications. The lateral seal of the middle adjustment plate of the combined nozzle needs to ensure that the gas in the ram side channel and the gas in the turbine side channel do not leak at the same time. In addition, it needs to have a self-cooling function to ensure that the component materials have sufficient temperature tolerance. The design is very difficult. [0003] At present, domestic and foreign researches on turbo-ramjet combined engine ar...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/82
CPCF02K1/82F02K1/822
Inventor 许光伟杨亚雄余祖潮谢龙王恒卿太木朱川蒲永彬
Owner AECC SICHUAN GAS TURBINE RES INST
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