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A Thermal Compensation Device for Heat Shield of Special-shaped Nozzle

A special-shaped nozzle and heat shield technology, which is applied in jet propulsion devices, machines/engines, etc., can solve the problem of lack of penetration, and achieve the effect of enhancing strength, ensuring the size of the profile, and ensuring the safety of use.

Active Publication Date: 2021-08-03
AECC SICHUAN GAS TURBINE RES INST
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0005] At present, the design of special-shaped nozzles is in its infancy, and the research on the effective thermal compensation connection structure of heat shields for special-shaped nozzles is not yet in-depth. There is an urgent need for a combined thermal compensation connection structure that can adapt to high temperature and high pressure working environments to meet the functional requirements of special-shaped nozzles.

Method used

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  • A Thermal Compensation Device for Heat Shield of Special-shaped Nozzle
  • A Thermal Compensation Device for Heat Shield of Special-shaped Nozzle
  • A Thermal Compensation Device for Heat Shield of Special-shaped Nozzle

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Embodiment Construction

[0024] Embodiments of the present disclosure will be described in detail below in conjunction with the accompanying drawings.

[0025] 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 heat compensation device for a special-shaped nozzle heat shield, and relates to the technical field of aeroengine nozzles. The thermal compensation device includes a special-shaped heat shield, and a plurality of L-shaped brackets are evenly spaced and fixed on the outside of the special-shaped heat shield. There is an assembly gap at the assembly place between the longitudinal sections, so that the lifting lug is movably connected with the L-shaped bracket; the assembly hole for assembling the lifting lug on the longitudinal section of the L-shaped bracket is a round hole or a waist-shaped hole. The invention utilizes the combined structure of L-shaped brackets, lifting lugs, and bow-shaped frames assembled on the outer surface of the special-shaped heat shield to realize the effective transformation of the radial thermal deformation of the special-shaped heat shield after being heated to the axial direction and the circumferential direction, ensuring the inner and outer connotations The size of the runner profile ensures the aerodynamic and stealth performance of the nozzle.

Description

technical field [0001] The disclosure relates to the technical field of aeroengine nozzles, in particular to a heat compensation device for a special-shaped nozzle heat shield. Background technique [0002] High stealth performance is the trend of future aircraft research and development. The design technology of the low-detectable and large-curvature special-shaped nozzle is a new stealth technology based on this. The low-detectable large-curvature special-shaped nozzle not only has good stealth performance, but also facilitates integration with the rear body. The advantage of design is a research hotspot in recent years. [0003] Compared with the traditional axisymmetric nozzle, the low-detectable large-curvature special-shaped nozzle has a non-axisymmetric cross-section and a curved centerline, which requires the ability to completely block the rearward visible high-temperature components. precedent. At the same time, when the engine air flow is applied to the non-axi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/82
CPCF02K1/822
Inventor 郭建伟廖华琳谢龙罗红飞刘立立朱川母鸿瑞商盼盼
Owner AECC SICHUAN GAS TURBINE RES INST
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