Effect of Fuel Injection Locations with a Hyper Mixer in Supersonic Combustion

2011 ◽  
Author(s):  
Chae-Hyoung Kim ◽  
In-Seuck Jeung ◽  
Byungil Choi ◽  
Toshinori Kouchi ◽  
Goro Masuya
Keyword(s):  
Fuel Injection ◽  
Supersonic Combustion

Computational investigation of multi-cavity fuel injection on hydrogen mixing at supersonic combustion chamber

2020 ◽  
Vol 45 (15) ◽  
pp. 9077-9087 ◽  
Author(s):  
Zhixiong Li ◽  
Tran Dinh Manh ◽  
M. Barzegar Gerdroodbary ◽  
Nguyen Dang Nam ◽  
R. Moradi ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Fuel Injection ◽  
Supersonic Combustion ◽  
Computational Investigation

3D numerical simulation of the supersonic combustion of H2

2006 ◽  
Vol 110 (1114) ◽  
pp. 773-782 ◽  
Author(s):  
Prashant Dinde ◽  
A. Rajasekaran ◽  
V. Babu
Keyword(s):  
Static Pressure ◽  
Fuel Injection ◽  
Numerical Solutions ◽  
Pressure Rise ◽  
Reacting Flows ◽  
Single Step ◽  
Supersonic Combustion ◽  
Finite Rate ◽  
Average Value ◽  
The Mean

Results from numerical simulations of supersonic combustion of H2 are presented. The combustor has a single stage fuel injection parallel to the main flow from the base of a wedge. The simulations have been performed using FLUENT. Realisable k-ε model has been used for modelling turbulence and single step finite rate chemistry has been used for modelling the H2-Air kinetics. All the numerical solutions have been obtained on grids with average value for wall y+ less than 40. Numerically predicted profiles of static pressure, axial velocity, turbulent kinetic energy and static temperature for both non-reacting as well as reacting flows are compared with the experimental data. The RANS calculations are able to predict the mean and fluctuating quantities reasonably well in most regions of the flow field. However, the single step kinetics predicts heat release much more rapid than what was seen in the experiments. Nonetheless, the overall pressure rise in the combustor due to combustion is predicted well. Also, the k-ε model is not able to predict the fluctuating quantities in the base region of the wedge where there is strong anisotropy in the presence of combustion.

scholarly journals Development of rotating supersonic combustion engine with swirling air-fuel injection

2019 ◽  
Author(s):  
Ahmad Dairobi Ghazali ◽  
Mazlan Abdul Wahid ◽  
Muhammad Amri Mazlan ◽  
Aminuddin Saat ◽  
Mohd Fairus Mohd Yasin ◽  
...  
Keyword(s):  
Fuel Injection ◽  
Combustion Engine ◽  
Supersonic Combustion

Numerical Study of Staged Fuel Injection for Supersonic Combustion

AIAA Journal ◽  
1982 ◽  
Vol 20 (10) ◽  
pp. 1426-1431 ◽  
Author(s):  
Elizabeth H. Weidner ◽  
J. Philip Drummond
Keyword(s):  
Fuel Injection ◽  
Numerical Study ◽  
Supersonic Combustion

scholarly journals The Effect of Fuel Injection Location on Supersonic Hydrogen Combustion in a Cavity-Based Model Scramjet Combustor

Energies ◽  
2020 ◽  
Vol 13 (1) ◽  
pp. 193 ◽  
Author(s):  
Eunju Jeong ◽  
Sean O’Byrne ◽  
In-Seuck Jeung ◽  
A. F. P. Houwing
Keyword(s):  
Equivalence Ratio ◽  
Fuel Injection ◽  
Flow Direction ◽  
Flame Structure ◽  
Flow Characteristics ◽  
Supersonic Combustion ◽  
Reacting Flow ◽  
Total Enthalpy ◽  
Scramjet Combustor ◽  
Injection Location

Supersonic combustion experiments were performed using three different hydrogen fuel-injection configurations in a cavity-based model scramjet combustor with various global fuel–air equivalence ratios. The configurations tested were angled injection at 15° to the flow direction upstream of the cavity, parallel injection from the front step, and upstream injection from the rear ramp. Planar laser-induced fluorescence of the hydroxyl radical and time-resolved pressure measurements were used to investigate the flow characteristics. Angled injection generated a weak bow shock in front of the injector and recirculation zone to maintain the combustion as the equivalence ratio increased. Parallel and upstream injections both showed similar flame structure over the cavity at low equivalence ratio. Upstream injection enhanced the fuel diffusion and enabled ignition with a shorter delay length than with parallel injection. The presence of a flame near the cavity was determined while varying the fuel injection location, the equivalence ratio, and total enthalpy of the air flow. The flame characteristics agreed with the correlation plot for the stable flame limit of non-premixed conditions. The pressure increase in the cavity for reacting flow compared to non-reacting flow was almost identical for all three configurations. More than 300 mm downstream of the duct entrance, averaged pressure ratios at low global equivalence ratio were similar for all three injection configurations.

scholarly journals Direct Measurements of Skin Friction in Supersonic Combustion Flow Fields

1992 ◽  
Author(s):  
K. M. Chadwick ◽  
D. J. Deturris ◽  
J. A. Schetz
Keyword(s):  
Skin Friction ◽  
Fuel Injection ◽  
Force Measurement ◽  
Tangential Force ◽  
Transverse Component ◽  
Supersonic Combustion ◽  
Quartz Tube ◽  
Hydrogen Fuel ◽  
Sensor Head ◽  
Scramjet Combustor

An experimental investigation was conducted to measure skin friction along the chamber walls of supersonic combustors. A direct force measurement device was used to simultaneously measure an axial and transverse component of the small tangential shear force passing over a non-intrusive floating element. This measurement was made possible with a sensitive piezoresistive deflection sensing unit. The floating head is mounted to a stiff cantilever beam arrangement with deflection due to the flow on the order of 0.00254 mm (0.0001 in). This allowed the instrument to be a non-nulling type. A second gauge was designed with active cooling of the floating sensor head to eliminate non-uniform temperature effects between the sensor head and the surrounding wall. The key to this device is the use of a quartz tube cantilever with piezoresistive strain gages bonded directly to its surface. A symmetric fluid flow was developed inside the quartz tube to provide cooling to the backside of the floating head. Tests showed that this flow did not influence the tangential force measurement. Measurements were made in three separate combustor test facilities. Tests at NASA Langley Research Center consisted of a Mach 3.0 vitiated air flow with hydrogen fuel injection at Pt = 500 psia (3446 kPa) and Tt = 3000 R (1667 K). Two separate sets of tests were conducted at the General Applied Science Laboratory (GASL) in a scramjet combustor model with hydrogen fuel injection in vitiated air at Mach = 3.3, Pt = 800 psia (5510 kPa), and Tt = 4000 R (2222 K). Skin friction coefficients between 0.001–0.005 were measured dependent on the facility and measurement location. Analysis of the measurement uncertainties indicate an accuracy to within ±10–15% of the streamwise component.

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