|Table of Contents|

Influence of flow state on initiation process of oblique detonation wave induced by hydrodynamic wedge in supersonic combustible flow (PDF)

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

Issue:
2015年01期
Page:
29-35
Research Field:
研究与设计
Publishing date:

Info

Title:
Influence of flow state on initiation process of oblique detonation wave induced by hydrodynamic wedge in supersonic combustible flow
Author(s):
LI Zi-ran;  LIN Zhi-yong
National University of Defense Technology, Changsha 410073, China
Keywords:
supersonic combustionoblique detonationlow-speed thermojetinitiation processinfluence fact
PACS:
V434-34
DOI:
-
Abstract:
The initiation characteristics of supersonic-speed oblique detonation thermojet are influenced by the airflow status parameters. The high speed laser schlieren technology and pressure sensor technology are adopted to study the influence of state parameters such as the thermojet premixed combustible gas equivalence ratio, inlet flow temperature and velocity on the low-speed continuous thermojet. It is found in the experiment that the influence of equivalence ratio on the initiation process has a certain randomness, but under general condition, increase of the fuel equivalence ratio will benefit DDT (deflagration to detonation), increase of the inlet flow temperature will reduce the DDT time and benefit the initiation, and increase of the inlet flow velocity will result in poor mixing effect and will not benefit the initiation.

References:

[1]LU F K. Prospects for detonations in propulsion[C]//Proceedings of the 9th International Symposium on Experimental and Computational Aerothermodynamics of Internal Flows. Gyeongju, Korea: [s.n.], 2009: 11-14.
[2]HARRIS P G. Structure of conical oblique detonation waves[C]//44th AIAA/ASME/ SAE/ASEE Joint Propulsion Conference & Exhibit. Harvard, CT: AIAA, 2008: 111-115.
[3]OSTRANDER M J, HYDE J C, YOUNG M F, et al. Standing oblique detonation wave engine performance, AIAA 1987-2002[R]. USA: AIAA, 1987.
[4]SISLIAN J P. Propulsive performance of hypersonic oblique detonation wave and shock-induced combustion ramjets[J]. Journal of Propulsion and Power, 2001, 17(3): 599-604.

[5]FUSINA G. Formation and stability of near chapman- jouguet standing oblique detonation waves[J]. American Institute of Aeronautics and Astronautics, 2005, 43(7): 1591-1604.

[6]HARRIS P G. Structure of conical oblique detonation waves[C]//44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Harvard, CT: AIAA, 2008: 222-228.
[7]FUSINA G, PARENT B. Numerical study of structure and stability of oblique detonation waves[C]//42nd AIAA Aerospace Sciences Meeting and Exhibit, AIAA 2004-1125. Reno, Nevada: AIAA, 2004: 123-128.
[8]CARRIER G F, FENDELL F E. Nonintrusive stabilization of a conical detonation wave for supersonic combustion [J]. Combustion and Flame, 1995, 103(4): 281-295.
[9]LEE J H S. Initiation of gaseous detonation[J]. Annual Review of Physical Chemistry, 1977, 28: 75-104.
[10]CHOI J Y. Capturing unstable wrinkled oblique detonation wave front by Hi-Fi numerical simulation, AIAA 2006-5100[R]. USA: AIAA, 2006.

Memo

Memo:
-
Last Update: 1900-01-01