TY - GEN
T1 - Study on Matching Characteristics of Pre-cooling Air Turbo Rocket Engine
AU - Wang, Yunlong
AU - Miao, Huihui
AU - Yong, Xuejun
AU - Wang, Yi
AU - Liu, Yi
AU - Ma, Yuan
AU - Zhao, Xiaotian
AU - Liu, Jinxin
AU - Nan, Xiangyi
N1 - Publisher Copyright:
© The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2024.
PY - 2024
Y1 - 2024
N2 - The pre-cooling air turbo rocket (PATR) engine, designed to operate with high propulsion efficiency and within a wide operating range, is one of the most promising and effective reusable single-stage in-orbit power solutions. The matching characteristics of the supersonic inlet and the engine directly affect the feasibility and overall performance of the engine scheme. The wide operating envelope of a PATR engine requires excellent operating performance in the full range of flight envelope, as well as needing the inlet and the engine to maintain good matching performance. Therefore, matching the inlet and the engine is recognized as a critical and challenging problem. In this paper, a three-dimensional system-level simulation model is established for a PATR engine with a bilateral mixed-compression supersonic inlet. The 3D numerical calculation of the internal flow field of a PATR engine was carried out to simulate its free jet test. The flow field characteristics of the inner channel and the matching characteristics between the inlet and the turbine during the starting process of the engine are obtained. The work studied in this paper can provide data reference for the development and flight test of a PATR engine.
AB - The pre-cooling air turbo rocket (PATR) engine, designed to operate with high propulsion efficiency and within a wide operating range, is one of the most promising and effective reusable single-stage in-orbit power solutions. The matching characteristics of the supersonic inlet and the engine directly affect the feasibility and overall performance of the engine scheme. The wide operating envelope of a PATR engine requires excellent operating performance in the full range of flight envelope, as well as needing the inlet and the engine to maintain good matching performance. Therefore, matching the inlet and the engine is recognized as a critical and challenging problem. In this paper, a three-dimensional system-level simulation model is established for a PATR engine with a bilateral mixed-compression supersonic inlet. The 3D numerical calculation of the internal flow field of a PATR engine was carried out to simulate its free jet test. The flow field characteristics of the inner channel and the matching characteristics between the inlet and the turbine during the starting process of the engine are obtained. The work studied in this paper can provide data reference for the development and flight test of a PATR engine.
KW - 3D System-level simulation
KW - Bilateral Supersonic Inlet
KW - Matching Characteristics
KW - PATR Engine
UR - https://www.scopus.com/pages/publications/85200516112
U2 - 10.1007/978-981-97-4010-9_85
DO - 10.1007/978-981-97-4010-9_85
M3 - 会议稿件
AN - SCOPUS:85200516112
SN - 9789819740093
T3 - Lecture Notes in Electrical Engineering
SP - 1097
EP - 1106
BT - 2023 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2023, Proceedings - Volume II
A2 - Fu, Song
PB - Springer Science and Business Media Deutschland GmbH
T2 - Asia-Pacific International Symposium on Aerospace Technology, APISAT 2023
Y2 - 16 October 2023 through 18 October 2023
ER -