The Hypersonic Precooled Combined Cycle Engine(HPCCE), which introduces precooler into traditional hypersonic engine, is regarded as the most promising propulsion system for realizing a single-stage-to-orbit vehicle. ...The Hypersonic Precooled Combined Cycle Engine(HPCCE), which introduces precooler into traditional hypersonic engine, is regarded as the most promising propulsion system for realizing a single-stage-to-orbit vehicle. The unique demands lead to the application of the compact heat exchangers, which can realize high thrust-to-weight ratio, sufficient specific impulse and high compression ratio. However, it is challenging to accurately manufacture the compact heat exchanger due to its extremely high heat dissipation capacity, remarkable compactness, superior adaptability and harsh operating condition. This review summarizes the precooling schemes of combined cycle propulsions and describes the demands and key issues in the fabrication of a compact heat exchanger for HPCCE. The investigation focuses on the application of various micromanufacturing methods of heat exchangers constructed from tubes of less than 1 mm in diameter and microchannels of less than 200 micrometers. Various micromanufacturing processes, which include microforming, micromachining, stereolithography, chemical etching, 3 D printing, joining and other advanced microfabricating processes, were reviewed. In addition, the technologies are compared in terms of dimensional tolerance, material compatibility, and process applicability. Furthermore, the boundaries of the micromanufacturing constraints are specified as references for the design of compact heat exchangers. Ultimately, the technological difficulties and development trends are discussed for the fabrication of compact heat exchangers for HPCCE.展开更多
In this paper results of previous researches of two-mode full engine model for Mach number range from 3 to 6 are presented. The main aims of researches are to obtain characteristics of full engine model and its compon...In this paper results of previous researches of two-mode full engine model for Mach number range from 3 to 6 are presented. The main aims of researches are to obtain characteristics of full engine model and its components (the inlet, the combustion chamber and the nozzle) in ramjet and scramjet regimes and to compare these characteristics with the calculation results according to CFD and to approximate (engineering) methods. Tests were carried out without ha supply (cold tests) and with fuel supply (study of ignition and combustion).Hydrocarbon and hydrogen fuel (gaseous or liquid) were used during the tests.展开更多
基金the funding support to this research from the National Natural Science Foundation of China (Nos. 51635005, 51975031 and 51605018)Defense Industrial Technology Development Program of China (No.JCKY2018601C207)。
文摘The Hypersonic Precooled Combined Cycle Engine(HPCCE), which introduces precooler into traditional hypersonic engine, is regarded as the most promising propulsion system for realizing a single-stage-to-orbit vehicle. The unique demands lead to the application of the compact heat exchangers, which can realize high thrust-to-weight ratio, sufficient specific impulse and high compression ratio. However, it is challenging to accurately manufacture the compact heat exchanger due to its extremely high heat dissipation capacity, remarkable compactness, superior adaptability and harsh operating condition. This review summarizes the precooling schemes of combined cycle propulsions and describes the demands and key issues in the fabrication of a compact heat exchanger for HPCCE. The investigation focuses on the application of various micromanufacturing methods of heat exchangers constructed from tubes of less than 1 mm in diameter and microchannels of less than 200 micrometers. Various micromanufacturing processes, which include microforming, micromachining, stereolithography, chemical etching, 3 D printing, joining and other advanced microfabricating processes, were reviewed. In addition, the technologies are compared in terms of dimensional tolerance, material compatibility, and process applicability. Furthermore, the boundaries of the micromanufacturing constraints are specified as references for the design of compact heat exchangers. Ultimately, the technological difficulties and development trends are discussed for the fabrication of compact heat exchangers for HPCCE.
文摘In this paper results of previous researches of two-mode full engine model for Mach number range from 3 to 6 are presented. The main aims of researches are to obtain characteristics of full engine model and its components (the inlet, the combustion chamber and the nozzle) in ramjet and scramjet regimes and to compare these characteristics with the calculation results according to CFD and to approximate (engineering) methods. Tests were carried out without ha supply (cold tests) and with fuel supply (study of ignition and combustion).Hydrocarbon and hydrogen fuel (gaseous or liquid) were used during the tests.
