scholarly journals Total temperature estimation of a hydrogen/air burned-gas torch igniter for a scramjet combustor

2018 ◽  
Vol 13 (2) ◽  
pp. JTST0030-JTST0030 ◽  
Author(s):  
Tatsuya YAMAGUCHI ◽  
Tomohiro HIZAWA ◽  
Taro ICHIKAWA ◽  
Taku KUDO ◽  
Akihiro HAYAKAWA ◽  
...  
Keyword(s):  
Temperature Estimation ◽  
Scramjet Combustor ◽  
Total Temperature ◽  
Torch Igniter

scholarly journals Study on the Effect of Air Throttling on Flame Stabilization of an Ethylene Fueled Scramjet Combustor

2015 ◽  
Vol 2015 ◽  
pp. 1-10 ◽  
Author(s):  
Ye Tian ◽  
Shunhua Yang ◽  
Jialing Le
Keyword(s):  
Numerical Simulation ◽  
Total Pressure ◽  
Time Sequence ◽  
Flame Stabilization ◽  
Shock Train ◽  
Lower Velocity ◽  
Scramjet Combustor ◽  
Inflow Condition ◽  
Total Temperature ◽  
Simulation Results

The effect of air throttling on flame stabilization of an ethylene fueled scramjet combustor was investigated by numerical simulation and experiments in this paper. The results were obtained under the inflow condition with Mach number of 2.0, total temperature of 900 K, total pressure of 0.8 MPa, and total equivalence ratio of 0.5. The shock train generated by air throttling had a big effect on the flow structure of the scramjet combustor. Compared with the combustor without air throttling, the flow field with air throttling had a lower velocity and higher pressure, temperature, and vortices intensity. Air throttling was an effective way to achieve flame stabilization; the combustion in the combustor without air throttling was nearly blowout. In the experiment, the combustion was nearly blowout with air throttling location of 745 mm, and the fuel/air mixture in the combustor with air throttling location of 875 mm was burned intensively. It was important to choose the location and time sequence of air throttling for fuel ignition and flame stabilization. The numerical simulation results agreed well with experimental measurements.

Some governing parameters of plasma torch igniter/flameholder in a scramjet combustor

1993 ◽  
Vol 9 (2) ◽  
pp. 176-181 ◽  
Author(s):  
G. Masuya ◽  
K. Kudou ◽  
A. Murakami ◽  
T. Komuro ◽  
K. Tani ◽  
...  
Keyword(s):  
Plasma Torch ◽  
Scramjet Combustor ◽  
Torch Igniter

Some governing parameters of plasma torch igniter/flameholder in a scramjet combustor

1990 ◽  
Author(s):  
G. MASUYA ◽  
K. KUDOU ◽  
A. MURAKAMI ◽  
T. KOMURO ◽  
K. TANI
Keyword(s):  
Plasma Torch ◽  
Scramjet Combustor ◽  
Torch Igniter

A Study on Performance Comparison of Integrated Aerodynamic-Ramp-Injector/ Gas-Portfire Flame Holder with Cavity

2013 ◽  
Vol 390 ◽  
pp. 8-11
Author(s):  
Bao Xi Wei ◽  
Qiang Gang ◽  
Yan Zhang ◽  
Rong Jian Liu ◽  
Liang Tian ◽  
...  
Keyword(s):  
Experimental Study ◽  
Mach Number ◽  
Supersonic Flow ◽  
Specific Impulse ◽  
Combustion Efficiency ◽  
Performance Comparison ◽  
Test Facility ◽  
Flame Holder ◽  
Scramjet Combustor ◽  
Total Temperature

Experimental study of an integrated aerodynamic-ramp-injector /gas-portfire (aero-ramp/G-P) has been conducted in a hydrogen-fueled scramjet combustor. The aero-ramp injectors consisted of four flush-walled holes, arranged to induce vorticular motion and enhance mixing. For comparison, a recessed cavity with four low downstream-angled circular injector holes was also examined. The combustor models were investigated experimentally using the scramjet direct connected test facility at the Beihang University. The facility can deliver a continuous supersonic flow of Mach number 2 with a total temperature of 1200K. The hot experimental results showed that the combustion efficiency and air specific impulse of aero-ramp/G-P are 85% and 35s while the corresponding values of cavity are 92% and 34s. These results justify the feasibility of aero-ramp/G-P flame holder.

A novel design of a plasma jet torch igniter in a scramjet combustor

2005 ◽  
Vol 30 (2) ◽  
pp. 2843-2849 ◽  
Author(s):  
Kenichi Takita ◽  
Koichi Murakami ◽  
Hideaki Nakane ◽  
Goro Masuya
Keyword(s):  
Plasma Jet ◽  
Scramjet Combustor ◽  
Torch Igniter ◽  
Novel Design

scholarly journals Investigations on the Influence of the In-Stream Pylon and Strut on the Performance of a Scramjet Combustor

2014 ◽  
Vol 2014 ◽  
pp. 1-10 ◽  
Author(s):  
Hao Ouyang ◽  
Weidong Liu ◽  
Mingbo Sun
Keyword(s):  
Mach Number ◽  
Pressure Loss ◽  
Total Pressure ◽  
Wall Pressure ◽  
Total Pressure Loss ◽  
Research Results ◽  
Scramjet Combustor ◽  
Total Temperature

The influence of the in-stream pylon and strut on the performance of scramjet combustor was experimentally and numerically investigated. The experiments were conducted with a direct-connect supersonic model combustor equipped with multiple cavities. The entrance parameter of combustor corresponds to scramjet flight Mach number 4.0 with a total temperature of 947 K. The research results show that, compared with the scramjet combustor without pylon and strut, the wall pressure and the thrust of the scramjet increase due to the improvement of mixing and combustion effect due to the pylon and strut. The total pressure loss caused by the strut is considerable whereas pylon influence is slight.

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.

Effects of Cavity Configurations on Flameholding and Performances of Kerosene Fueled Scramjet Combustor

2017 ◽  
Vol 34 (3) ◽  
Author(s):  
Deyong Shi ◽  
Wenyan Song ◽  
Yuhang Wang ◽  
Yanhua Wang
Keyword(s):  
Total Pressure ◽  
Cavity Length ◽  
Flow Characteristics ◽  
Reacting Flows ◽  
Experimental Results ◽  
Reacting Flow ◽  
High Enthalpy ◽  
Scramjet Combustor ◽  
Total Temperature ◽  
Single Cavity

AbstractIn this work, the effects of cavity flameholder configurations on flameholding and performances of kerosene fueled scramjet combustor were studied experimentally and numerically. For experiments, a directly connected ground facility was used and clean high enthalpy air, with a total temperature of 800 K and a total pressure of 800 Kpa, was provided by an electricity resistance heater. To investigate the effects of cavity configurations on flameholding capacity and reacting-flow characteristics, three different flameholders, one single cavity flameholder and two tandem cavity flameholders, were used in experiments. For the two combustors with tandem cavity flameholders, the location and configurations of its up-stream cavity were same with the single cavity flameholder, and the length-to-depth ratios for down-stream cavities were 9 and 11 respectively. The experimental results showed that stabilize kerosene combustion were achieved for combustor with tandem cavity flameholders mounted, and none for that with single cavity flameholder. The none-reacting and reacting flows of combustor models with tandem cavity flameholders were compared and studied with numerical and experimental results. The results showed that higher combustion efficiencies and pressure recovery ratios were achieved for the combustor with down-stream cavity length-to-depth ratio of 9.

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