Precooler development and performance analysis of a precooling air turbo rocket engine
- Paper number
IAC-15,C4,9,7,x28469
- Author
Dr. Yuan Ma, Xi'an Aerospace Propulsion Institute, China
- Coauthor
Mr. Yan Zhu, China
- Coauthor
Dr. Xiangyi NAN, Academy of Aerospace Propulsion Technology (CASC), China
- Coauthor
Mr. LI Wenlong, Xi'an Aerospace Propulsion Institute, China
- Coauthor
Mr. Mengzheng Zhang, ShaanXi Engineering and Mechanics Design institute, China
- Year
2015
- Abstract
For near space aircraft, pre-cooling the incoming high temperature air is considered as an effective approach to enhance the engine performance, which potentially improves the flying speed up to Mach 6. This paper introduces a pre-cooling air turbo rocket engine (PATR) based on the conventional ATR engine. A mathematical model was built and the simulation tool was developed to evaluate the PATR engine performance. In order to investigate the pre-cooler, a specific mathematical model was built to simulate the heat transfer process and evaluate the pre-cooler’s performance. Depending on the engine analysis and pre-cooler investigation, the operating parameters of pre-cooler were determined for the previous ATR engine and the pre-cooler was developed as the tube bundle structure. The existing ATR engine applied an external fuel-rich rocket as the gas-generator driving the turbo. The engine performance was analyzed with and without the pre-cooler respectively. In addition, the pre-cooler is particularly studied with CFD method to understand the flow field distribution. Next, experimental evaluations about the pre-cooler and the PATR engine will be carried out.
- Abstract document
- Manuscript document
(absent)