Experimental investigation on flame stabilization of a kerosene-fueled scramjet combustor with pilot hydrogen
- PDF / 2,144,469 Bytes
- 10 Pages / 595.22 x 842 pts (A4) Page_size
- 54 Downloads / 189 Views
663
Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering) ISSN 1673-565X (Print); ISSN 1862-1775 (Online) www.jzus.zju.edu.cn; www.springerlink.com E-mail: [email protected]
Experimental investigation on flame stabilization of a kerosene-fueled scramjet combustor with pilot hydrogen* Wen SHI, Ye TIAN†‡, Wan-zhou ZHANG, Wei-xin DENG, Fu-yu ZHONG, Jia-ling LE China Aerodynamic Research and Development Center, Mianyang 621000, China †
E-mail: [email protected]
Received Nov. 18, 2019; Revision accepted Apr. 1, 2020; Crosschecked July 15, 2020
Abstract: Flame stabilization in a kerosene-fueled scramjet combustor was investigated experimentally through Schlieren, flame luminosity, and wall pressure measurement, aiming to obtain better insight into combustion characteristics. Experiments were conducted in a direct-connected supersonic combustion facility with inflow conditions of Mach number 2.0, stagnation pressure 0.82 MPa, and temperature 950 K, simulating the flight condition of Mach number 4.0. Results revealed that kerosene was able to be ignited when the equivalence ratio of pilot hydrogen reached 0.080, but was unsuccessful when the equivalence ratio was 0.040. Once ignited, the intense combustion induced high back pressure forcing the flame to spread into the isolator. The pilot flame invariably appeared in the cavity shear layer and attached to the cavity ramp under different equivalence ratios of pilot hydrogen. With the mass flux of pilot hydrogen increased, the kerosene flame located near the cavity ramp was asymmetrical and unstable since it propagated upstream repeatedly. Therefore, the kerosene could be ignited by a suitable equivalence ratio of continuous pilot hydrogen, potentially accompanied with unstable combustion. Key words: Scramjet; Flame stabilization; Pilot hydrogen; Kerosene; Supersonic combustion https://doi.org/10.1631/jzus.A1900565 CLC number: V43
1 Introduction Combustion characteristics, which contain mixing (Huang and Yan, 2013; Huang et al., 2016), ignition, flame stabilization (Liao et al., 2018), and oscillation in scramjet combustors, are still not fully comprehended despite nearly seven decades of research. It is the inability of measuring crucial flow properties experimentally that leads to this situation. Along with the improvement of measurement, large numbers of experiments have been carried out to better understand the combustion characteristics and contributory factors. ‡
Corresponding author Project supported by the National Natural Science Foundation of China (No. 51706237), the China Aerodynamic Research and Development Center Fundamental and Frontier Technology Research Fund, and the Postdoctoral Research Foundation of China (No. 2019M653953) ORCID: Ye TIAN, https://orcid.org/0000-0001-9955-3438 © Zhejiang University and Springer-Verlag GmbH Germany, part of Springer Nature 2020
*
Chang JT et al. (2018) and Zhang et al. (2018) investigated combustion stabilization in a kerosenefueled combustor, equipped with a strut, experimentally and numerically. A
Data Loading...
