Design method and device for cooling high-temperature gas with equal Mach number

Abstract

The invention provides an equal-mach-number high-temperature gas cooling design method and device, and the method comprises the steps: building a cooling device model which comprises a housing model and a heat exchange structure model; a given design condition is imported into a data analysis unit, and a data analysis criterion is set in the data analysis unit: the proportions of the solid areas of heat exchange structure models of front and back adjacent sections perpendicular to the high-temperature gas flowing direction in the cooling device model to the area of the sections are the same; performing analysis according to the data analysis criterion in combination with the design conditions to obtain the sectional areas of the air inlet and the air outlet of the heat exchange structure model and the sectional areas of the air inlet and the air outlet of the cooling device model; and determining the size of the cooling device model and the size of the heat exchange structure model. The problems that when the flight height is high and the Mach number is high, a gas compressor of an aerospace engine cannot effectively compress high-temperature incoming flow, so that the engine is difficult to work at a higher Mach number, and high-temperature waste gas is difficult to recycle are solved.

Description

[0001] Field of study [0002] The invention belongs to the technical field of air-breathing aerospace engine equipment, and in particular relates to a design method and device for cooling high-temperature gas with equal Mach number. Background technique [0003] Air-breathing aerospace engines are ideal power components for near-earth aircraft. Common air-breathing aerospace engines include turbines, ramjets and their combined engines. Their common working process includes the necessary compression of the incoming air, and by further heating the pressurized air flow (such as chemical combustion heating method), the gas obtains sufficient energy and expands to do work to generate thrust. When this type of engine needs to work at a higher altitude and a faster flight Mach number (especially at an altitude of 20km and a speed of Mach 3 or higher), the total temperature of the incoming flow captured by the intake port is already quite high (see Table 1 - Aerospace Engines Typica...

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Problems solved by technology

[0011] The invention provides a high-temperature gas cooling design method and device of equal Mach number, which solves the problem that the air compressor of an aerospace engine cannot be used when the flight altitude is high and the Mach number is fast (especially at a height of 20 km and a speed of Mach 3 or more). The high temperature incoming flow is effectively compressed, thus making it difficult for the engine to work at a higher Mach number and the recovery and utilization of high temperature exhaust gas

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