Measurement and imaging of supersonic combustion in a model scramjet engine

Shock Waves ◽  
1999 ◽  
Vol 9 (4) ◽  
pp. 221-226 ◽  
Author(s):  
S. O'Byrne ◽  
M. Doolan ◽  
S.R. Olsen ◽  
A.F.P. Houwing
Keyword(s):  
Supersonic Combustion ◽  
Scramjet Engine

Supersonic Combustion Processes in a Premixed Three-Dimensional Nonuniform-Compression Scramjet Engine

AIAA Journal ◽  
2014 ◽  
Vol 52 (8) ◽  
pp. 1670-1685 ◽  
Author(s):  
Mathew G. Bricalli ◽  
Laurie M. Brown ◽  
Russell R. Boyce
Keyword(s):  
Three Dimensional ◽  
Supersonic Combustion ◽  
Scramjet Engine ◽  
Combustion Processes

Intermittent back-flash phenomenon of supersonic combustion in the staged-strut scramjet engine

2018 ◽  
Vol 79 ◽  
pp. 70-74 ◽  
Author(s):  
Shaohua Zhu ◽  
Xu Xu ◽  
Qingchun Yang ◽  
Yushu Jin
Keyword(s):  
Supersonic Combustion ◽  
Scramjet Engine

718 Flow and Supersonic Combustion Phenomena in Scramjet Engine by Using Shock Tunnel

2001 ◽  
Vol 2001.41 (0) ◽  
pp. 264-265
Author(s):  
Koji MUKAI ◽  
Takakage ARAI ◽  
Jiro KASAHARA ◽  
Takashi KOKUBO
Keyword(s):  
Shock Tunnel ◽  
Supersonic Combustion ◽  
Scramjet Engine

scholarly journals Some Topics of Research on Hypersonic Airbreathing Engines at National Aerospace Laboratory

1992 ◽  
Author(s):  
Kimio Sakata ◽  
Hiroyuki Nouse ◽  
Mitsuhiro Minoda
Keyword(s):  
High Temperature ◽  
System Optimization ◽  
Supersonic Combustion ◽  
Gradient Material ◽  
Matrix Composites ◽  
Regenerative Heat ◽  
Ramjet Engine ◽  
Functionally Gradient ◽  
Air Intake ◽  
Scramjet Engine

Some research tupics on hypersonic airbreathing engines conducted at National Aerospace Laboratory in Japan (NAL) are introduced. Variable Cycle engine (VCE) for the next generation supersonic transports (SST), Combined turbo-ramjet engine for hypersonic transports (HST) and turbo-engines, such as Airturbo-ramjet engine (ATR), and Scramjet engine for Space Plane propulsion systems are being studied. Engine system design to make evaluate capability for Space Plane and system optimization are described. Component studies; supersonic air-intake with mixed and internal compression configuration, hydrogen fueled ram-combustor, supersonic combustion chamber, high temperature and highly loaded turbo-component, regenerative heat exchanger and noise reduction nozzle are being conducted and some results are presented. In the material study, carbon/carbon composites, metal compound metal matrix composites and functionally gradient material (FGM) are also investigated and evaluated for application to high temperature and/or light weight structures.

Investigation of Performance of Scramjet Combustion Used Kerosene with Clean Air

2012 ◽  
Vol 601 ◽  
pp. 294-298
Author(s):  
Wei Qiang Li ◽  
Fei Teng Luo
Keyword(s):  
Supersonic Combustion ◽  
Experimental Result ◽  
Scramjet Combustor ◽  
Clean Air ◽  
Cavity Design ◽  
Total Temperature ◽  
Scramjet Engine ◽  
Ignition Characteristics ◽  
Flight Regimes ◽  
Inflow Conditions

The aaviation kerosene is a practical candidate fuel for scramjet engine in the flight regimes of Mach number less than 8, in considerations of safety, economy and portable. In the present paper, the ignition characteristics of a scramjet combustor model fueled by aviation kerosene was experimentally investigated, using the resistance heating direct-connected supersonic combustion facility of Northwestern Polytechnical University. The inflow conditions at the direct-connected combustor entrance were specified as: the nominal Mach of 2.0, the total temperature of 870～930K and the total pressure of about 770kPa. Three combustor performance of difference ER were compared applied CFD simulated. The experimental result suggested that: the cavity design is a key problem for kerosene successful ignition is the combustor; That chooses appropriate gas-oil ratio could increased performance of combustor and kept isolator interfered by gas.

Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector

2017 ◽  
Vol 34 (1) ◽  
Author(s):  
Gautam Choubey ◽  
K. M. Pandey
Keyword(s):  
Numerical Analysis ◽  
Flow Structure ◽  
Fuel Injection ◽  
Angle Of Attack ◽  
Supersonic Combustion ◽  
Scramjet Combustor ◽  
Numerical Studies ◽  
Scramjet Engine

AbstractNumerical analysis of the supersonic combustion and flow structure through a scramjet engine at Mach 7 with alternating wedge fuel injection and with three angle of attack (

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