A design method of cooling structure of an ultrahigh-temperature wind tunnel nozzle

By designing a cooling structure for the ultra-high temperature wind tunnel nozzle, the problem of existing materials being easily damaged under high temperature and high pressure airflow was solved, enabling the normal operation of the nozzle and improving its thermal protection performance.

CN117494341BActive Publication Date: 2026-07-24AVIC SHENYANG AERODYNAMICS RES INST
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Patent Information

Application Number
CN202311497855.5
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2023-11-13
Publication Date
2026-07-24
Estimated Expiration
2043-11-13

AI Technical Summary

Technical Problem

The operating temperature limit of existing materials is lower than that of ultra-high temperature wind tunnels, making it difficult to simultaneously ensure both structural support and thermal protection performance, which makes the structure susceptible to damage under high temperature and high pressure airflow.

Method used

The design of the ultra-high temperature wind tunnel nozzle cooling structure includes nozzle inner shell thickness design, determination of cooling structure location and size, 3D model establishment, CFD simulation calculation, multi-objective optimization and material selection. The optimal cooling structure and water flow rate are determined by simulation and optimization using computational fluid dynamics software.

Benefits of technology

Under the existing material system, the normal operation of the ultra-high temperature wind tunnel nozzle was achieved, the problem of the material's operating temperature limit was solved, and the thermal protection performance of the structure was improved.

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Abstract

The application discloses a kind of hypersonic wind tunnel nozzle cooling structure design method, belongs to aerodynamics wind tunnel design technical field.The application solves the problem that the temperature limit of currently commonly used material is lower than the temperature of wind tunnel operation during the operation of hypersonic equipment, and it is difficult to simultaneously consider support-thermal protection performance.The application determines the inner wall surface pressure according to the design Mach number of nozzle by designing the thickness of nozzle inner shell, calculates the thickness of nozzle inner shell according to the national standard of pressure vessel, determines the position and size range of nozzle cooling structure, carries out CFD simulation calculation on nozzle cooling structure, carries out multi-objective optimization on nozzle cooling structure, selects materials and processing technology.The application solves the problem that hypersonic wind tunnel can normally operate under existing material system by reasonable cooling structure design when the operating temperature of hypersonic wind tunnel exceeds the temperature limit of existing materials.
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