Sensitivity Analysis of Combustor Incoming Parameters on Dual-Mode Scramjet Performance Potential at Ma6

被引：0

作者：

Chen J. ^{[1
]}

Liu S. ^{[1
]}

Liu W.-D. ^{[2
]}

Bai H.-C. ^{[1
]}

机构：

[1] Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center Hypersonic Institute, Mianyang

[2] Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2017年 / 38卷 / 11期

关键词：

Combustor incoming parameters; Dual-mode scramjet; One-dimensional method; Performance potential; Sensitivity analysis;

D O I：

10.13675/j.cnki.tjjs.2017.11.003

中图分类号：

学科分类号：

摘要：

To obtain a systematic understanding about the effects of supersonic combustor incoming parameters on a Dual-mode scramjet performance potential (fuel specific impulse Isp, f), one dimensional analysis method is applied to study the relationship between performance and incoming parameters, including Mach number (Main) and total pressure recovery coefficient (σin), while the flight Mach number is 6, the incoming massflow rate is fixed, and the characteristic Mach number (Mac) in heating sections is varied. Results indicate that the performance potential is influenced synthetically by these incoming parameters. In a common range of the combustor inflow parameters (Main∈[2.4 3.5], σin∈[0.3 0.7]), Isp, f increases by 1.1%~1.8% while Main decrease by 0.1. The higher σin is, the greater influence of Main has. Isp, f increases by 2.4%~4.0% while σin increase by 0.1. The higher Main is, the more influence of σin has. There are cases with the same specific impulse but different incoming parameters. Loss analysis for combustor subsections shows that increasing of Main leads to great loss in its pre-combustion shock train process with supersonic incoming flow and subsonic heating process. This is the main reason to make Isp, f decreased. More loss will be deduced in combustion process when Mac increases in heating section. The formulized sensitivity relationship between the potential performance and combustor incoming parameters is deduced. The difference from the original data is less than 3%. The relationship can be used to match the processes between engine components. © 2017, Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：2422 / 2430

页数：8

共 11 条

[1]

Niu Z.-G., Fei L.-Q., Feng S.-Y., Et al., Experiment on Combustion Performance of a Ramjet Prototype Combustor in Low Pressure Condition, Journal of Propulsion Technology, 32, 4, (2011)

[2]

Luo W.-L., Pan Y., Tan J.-G., Et al., Experimental Investigation on Combustion Efficiency of the Ramjet Model at Low Pressure, Journal of Propulsion Technology, 31, 3, (2010)

[3]

Heiser W.H., Pratt D.T., Hypersonic Airbreathing Propulsion, (1994)

[4]

Chen J., Bai H., Study of the Combustion Organization Method's Effects on Performance of Ramjet, Sino-Russia Hypersonic Flow Conference, (2011)

[5]

Chen J., Bai H.-C., Liu S., Effects of Chemical Equilibrium on Relation Between Performance and Process for Scramjet Combustor, Journal of Propulsion Technology, 34, 10, (2013)

[6]

Ikui T., Matsuo K., Nagai M., The Mechanism of Pseudo-Shock Waves, Bulletin of JSME, 17, 108, pp. 731-739, (1974)

[7]

O'Brien T.F., Starkey R.P., Lewis M.J., Et al., Quasi-One-Dimensional High-Speed Engine Model with Finite-Rate Chemistry, Journal of Propulsion and Power, 17, 6, (2001)

[8]

Smith T.B., Development and Ground Testing of Direct Measuring Skin Friction Gages for High Enthalpy Supersonic Flight Tests, (2001)

[9]

Babinsky H., Harvery J.K., Shock Wave Boundary-Layer Interaction, pp. 15-18, (2015)

[10]

Sun B., Zhang K.-Y., Jin Z.-G., Et al., Selection of Design Parameters for Stream Traced Hypersonic Busemann Inlets, Journal of Propulsion Technology, 28, 1, (2007)

← 1 2 →