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Publishing Language: Chinese

Inward-turning TBCC intake design

State Key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace Engineering, Xi'an Jiaotong University, Xi'an 710049, China
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Abstract

The increasing demand for air-breathing propulsion systems in hypersonic aircraft that can operate over a wide Mach number range has led to development of the turbine based combined cycle (TBCC). The high-performance compressed air intake system is a key component of these systems. This study analyzed the requirements for air intake systems of hypersonic aircraft operating over a wide Mach number range. This paper reviews research on the TBCC intake design, especially the internal rotating TBCC air intake system presented by TriJet. This review then summarizes the main challenges facing the development of the TBCC intake and the unique conical shock wave/boundary layer interactions in this intake to provide references for subsequent research work.

Keywords

hypersonicscramjetturbine based combined cycleinward-turning intake
CLC number: TP242.2 Document code: A Article ID: 1000-0054(2022)03-0555-07

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Journal of Tsinghua University (Science and Technology)
Volume 62 Issue 3,
March 2022
Pages 555-561
DOI: 10.16511/j.cnki.qhdxxb.2021.26.029
Cite this article:
ZUO F. Inward-turning TBCC intake design. Journal of Tsinghua University (Science and Technology), 2022, 62(3): 555-561. https://doi.org/10.16511/j.cnki.qhdxxb.2021.26.029

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Received: 13 March 2021
Published: 15 March 2022
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