Supersonic Combustion of Hydrogen Fuel Injection Locations in a Cavity-Based Combustor

2008 ◽  
Author(s):  
Eunju Jeong ◽  
Sean O'Byrne ◽  
In-Seuck Jeung ◽  
A.F.P Houwing
Keyword(s):  
Fuel Injection ◽  
Supersonic Combustion ◽  
Hydrogen Fuel ◽  
Combustion Of Hydrogen

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.

Direct Measurements of Skin Friction in Supersonic Combustion Flow Fields

1993 ◽  
Vol 115 (3) ◽  
pp. 507-514 ◽  
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 measure simultaneously an axial and a transverse component of the small tangential shear force passing over a nonintrusive 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 nonnulling type. A second gage was designed with active cooling of the floating sensor head to eliminate nonuniform 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 (3466 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 percent of the streamwise component.

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

Numerical Simulation on Hypersonic Combustion of Hydrogen-Fueled Scramjet Combustor with Parallel Strut Fuel Injection at a Flight Mach Number of 7

2015 ◽  
Vol 766-767 ◽  
pp. 1044-1049
Keyword(s):  
Numerical Simulation ◽  
Mach Number ◽  
Numerical Investigation ◽  
Fuel Injection ◽  
International Space ◽  
Scramjet Combustor ◽  
Combustion Of Hydrogen

Removed due to plagiarism. The original was published as: Numerical Investigation of Inlet-Combustor Interactions for a Scramjet Hydrogen-Fueled Engine at a Flight Mach number of 8. Authors: Edder Rabadan and Bernhard Weigand 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, Tours, France, 2012. Paper ID AIAA-2012-5926, DOI: 10.2514/6.2012-5926

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