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Cooler

A cooler and cooling water technology, applied in the direction of heat exchanger types, indirect heat exchangers, fixed tubular conduit components, etc., to achieve the effect of improving heat transfer coefficient, reducing tube bundle flow resistance, and improving high temperature resistance performance

Inactive Publication Date: 2018-04-27
BEIJING INST OF AEROSPACE TESTING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0013] The technical problem to be solved by the present invention is to overcome the deficiencies of the existing high-temperature and high-speed airflow cooling technology, and provide a new cooler, especially suitable for the incoming flow of rocket engines, ramjet engines, aeroengine test systems and ablation test systems. It is a high-temperature, high-velocity gas that requires low flow resistance of the cooler

Method used

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Embodiment Construction

[0023] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0024] attached by figure 1 Given, the present invention is a partition cooler, which uses cooling water to cool the high-temperature incoming flow, and the incoming flow inlet 1, the shell 2, the expansion section 3, the diversion cone 4, the light pipe cooling section 5, the cooling light pipe 6, and the cooling light pipe Cooling water inlet 7, cooling light pipe cooling water outlet 8, finned tube cooling section 9, cooling finned tube 10, cooling finned tube cooling water inlet 11, cooling finned tube cooling water outlet 12, diversion cone cooling water outlet 13. Shell cooling water outlet 14, incoming and outgoing outlet 15, diversion cone cooling water inlet 16, and shell cooling water inlet 17. The high-temperature air enters the cooler from the inflow port 1, passes through the expansion section 3, the bare tube cooling se...

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Abstract

The invention discloses a cooler. The cooler is composed of an incoming flow inlet (1), a shell (2), an expansion segment (3), a flow guide cone (4), a light pipe cooling segment (5), a cooling lightpipe (6), a cooling light pipe cooling water inlet (7), a cooling light pipe cooling water outlet (8), a fin pipe cooling segment (9), a cooling fin pipe (10), a cooling fin pipe cooling water inlet (11), a cooling fin pipe cooling water outlet (12), a flow guide cone cooling water outlet (13), a shell cooling water outlet (14), an incoming flow outlet (15), a flow guide cone cooling water inlet (16), and a shell cooling water inlet (17). The cooler is used for cooling high-temperature incoming flow gas.

Description

technical field [0001] The invention relates to a cooler, in particular to a cooler with low flow resistance of high-speed airflow, which is suitable for occasions where the incoming flow is high-temperature, high-speed airflow and low flow resistance of cooling equipment is required, such as rocket engines, ramjet engines, and aeroengines. Test system and ablation test system, etc. Background technique [0002] Some rocket engines, ramjet engines, aeroengine test systems and ablation test systems need to be equipped with coolers, whose function is to cool the high-temperature, high-speed airflow for subsequent processing. For example, on the high-altitude simulation test bench for active ejection rocket engines, the temperature of the engine gas can reach above 2800K. Generally, a cooler is installed between the diffuser and the ejector to reduce the temperature of the engine gas to below 373K to protect downstream equipment. The gas specific volume of the engine can be re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F28D7/08
CPCF28D7/08
Inventor 胡旭坤张奎好李斌曲胜孙树江赵宏张海栋毕明卉张伟郭敬李欣金诚徐鑫刘屹孔凡超郑鑫
Owner BEIJING INST OF AEROSPACE TESTING TECH
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