一种多热力循环组合发动机进气道设计方案

doi:10.7527/S1000-6893.2020.23745

Abstract

Abstract: To satisfy the requirement of wide range operations for the pre-cooling turbojet + ramjet combined multiple thermodynamic cycle engine with Mach numbers from 0 to 6, a variable geometry adjustment scheme of an axisymmetric inlet with full flow capture ability within Mach number from 2 to 6 is proposed. The mass flow distribution and compression requirement between the turbojet and ramjet passages can be met simultaneously by moving the center cone and the splitter plate. In this paper, the scheme design and comparative study of two variable geometry inlets with initial half cone angles of 13° and 20° respectively are conducted. The results show that the initial half cone angle affects the design of the final scheme most. The inlet scheme with an initial half cone angle of 13° is advantageous over the one with an initial half cone angle of 20° in that the critical total pressure recovery in ramjet and turbojet channels increase by 16% and 14% respectively when the free stream Mach number is 6, and the maximum windward area decreases by 12.4%. However, the moving distances of the center cone and the splitter are increased by 84% and 91% respectively.

Key words: pre-cooling combined engines, high flow capture, variable geometry inlets, axisymmetric inlets, hypersonic

CLC Number:

V231.3

CAI Yiwen, JIN Zhiguang, ZHOU Jianxing, ZHOU Hang. Design scheme of combined multiple thermodynamic cycle engine inlet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(11): 123745-123745.

References 20

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Design scheme of combined multiple thermodynamic cycle engine inlet

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