|Table of Contents|

Analysis on thermodynamic cycle characteristics of synergistic air-breathing rocket engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2013年03期
Page:
15-20
Research Field:
研究与设计
Publishing date:

Info

Title:
Analysis on thermodynamic cycle characteristics of synergistic air-breathing rocket engine
Author(s):
GUO Hai-bo1;  XIAO Hong2;  NAN Xiang-yi1;  LU Wan-ruo1
1. Xi'an Aerospace Propulsion Institute, Xi'an 710100, China
Keywords:
synergistic air-breathing rocket engine;  thermodynamic cycle;  ideal cycle work;  thermal efficiency
PACS:
V434+.1
DOI:
-
Abstract:
The basic thermodynamic process of synergistic air-breathing rocket engine (SABRE) is analyzed with the first law of thermodynamics method. The ideal cycle work and thermal efficiency expressions in both air-breathing mode and rocket mode were obtained. Furthermore, several characteristic parameters which affect the performance of the ideal thermodynamic cycles were determined. Results reveal that the pressune ratio of the compressor and cycle temperature ratio are the key parameters affecting the ideal thermodynamic cycle performance when SABRE core engine in air-breathing mode works in Brayton cycle, and the decompression ratio in the nozzle and exhaust velocity at nozzle outlet are the important parameters affecting the ideal thermodynamic cycle performance when the rocket engine cycle is adopted for SABRE . The helium energy transmission between all the cycle sub-systems is realized only by heat exchangers in the engine, but has no effects on ideal cycle work and thermal efficiency of SABRE.

References:

[1]RICHARD V, ALAN B. The Skylon spaceplane, IAA 95-V3.07 [R]. [S.l.]: IAA, 1995.
[2]RICHARD V, ALAN B. The SKYLON spaceplane: pro- gress to realization[J]. JBIS, 2008, 61: 412-418.
[3]RICHARD V, ALAN B. The SKYLON spaceplane[J]. JBIS,2004, 57: 22-32 .
[4]HEMPSELL M,BOND A,VARVILL R. Progress on the SKYLON and SABRE development programme [C]// 62nd International Astronautical Congress. [S.l.]: IAC, 2011: 111-121.
[5]ROGER L, ALAN B. The SKYLON project, AIAA 2011-2244[R]. USA: AIAA, 2011.
[6]WEBBER H, FEAST S, BOND A. Heat exchanger design in combined cycle engines[J]. Journal of the British Interplanetary Society, 2009, 62: 122-130.
[7]WEBBER H,, ALAN B, MARK H, et al. The sensitivity of precooled air-breathing engine performance to heat exchanger design parameters[J]. JBIS, 2007, 60: 188-196.
[8]JAMES J M, CHRISTOPHER M H, ALAN B. An experi- mental precooler for airbreathing rocket engines[J]. JBIS, 2001, 54: 199-209 .
[9]TAYLOR N V,TETSUYA S. Experimental and computa- tional an[J]. 火箭推进, 2008, 34(6): 31-35.
[10]沈维道, 蒋智敏, 童钧耕. 工程热力学[M]. 北京: 高等教育出版社, 2001.
[11]冯青, 李世武, 张丽. 工程热力学[M]. 西安: 西北工业大学出版社, 2006.
[12]柳长安, 李平, 张蒙正. 吸气式发动机流道调节的影响[J].火箭推进, 2011, 37(4): 24-27.

Memo

Memo:
-
Last Update: 1900-01-01