Numerical Simulation of Hydrogen Supersonic Combustion and Validation of Computational Approach

Numerical simulation of the supersonic combustion of kerosene in a model combustor

Progress in Computational Fluid Dynamics An International Journal ◽

10.1504/pcfd.2009.022306 ◽

2009 ◽

Vol 9 (1) ◽

pp. 30 ◽

Cited By ~ 6

Author(s):

A. Rajasekaran ◽

G. Satishkumar ◽

V. Babu

Keyword(s):

Numerical Simulation ◽

Supersonic Combustion

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A Numerical Simulation Capability for Analysis of Aircraft Inlet-Engine Compatibility

Journal of Engineering for Gas Turbines and Power ◽

10.1115/1.1925649 ◽

2004 ◽

Vol 128 (3) ◽

pp. 473-481 ◽

Cited By ~ 4

Author(s):

Alan Hale ◽

Milt Davis ◽

Jim Sirbaugh

Keyword(s):

Numerical Simulation ◽

Computational Approach ◽

The Other ◽

Computational Tool ◽

Additional Insight ◽

Turbine Engine ◽

Inlet Distortion ◽

Full Knowledge ◽

Engine System ◽

Isolated Systems

Two primary aircraft propulsion subsystems are the inlet and the engine. Traditionally these subsystems have been designed, analyzed, and tested as isolated systems. The interaction between the subsystems is modeled primarily through evaluating inlet distortion in an inlet test and then simulating this distortion in engine tests via screens or similar devices. Recently, it has been recognized that significant improvements in both performance and operability can be realized when both the inlet and the engine are designed with full knowledge of the other. In this paper, a computational tool called Turbine Engine Analysis Compressor Code is used to evaluate the effect of inlet distortion on a three-stage military fan. This three-stage military fan is further connected to an F-16 inlet and forebody operating at an angle of attack and sideslip to demonstrate the effect of inlet distortion generated by flight maneuvers. The computational approach of simulating an integrated inlet-engine system is expected to provide additional insight over evaluating the components separately.

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A Numerical Simulation Capability for Analysis of Aircraft Inlet – Engine Compatibility

Volume 2: Turbo Expo 2004 ◽

10.1115/gt2004-53473 ◽

2004 ◽

Cited By ~ 5

Author(s):

Alan Hale ◽

Milt Davis ◽

Jim Sirbaugh

Keyword(s):

Numerical Simulation ◽

Computational Approach ◽

The Other ◽

Computational Tool ◽

Additional Insight ◽

Turbine Engine ◽

Inlet Distortion ◽

Full Knowledge ◽

Engine System ◽

Isolated Systems

Two primary aircraft propulsion subsystems are the inlet and the engine. Traditionally these subsystems have been designed, analyzed, and tested as isolated systems. The interaction between the subsystems is modeled primarily through evaluating inlet distortion in an inlet test and then simulating this distortion in engine tests via screens or similar devices. Recently, it has been recognized that significant improvements in both performance and operability can be realized when both the inlet and the engine are designed with full knowledge of the other. In this paper, a computational tool called Turbine Engine Analysis Compressor Code (TEACC) is used to evaluate the effect of inlet distortion on a three-stage military fan. This three-stage military fan is further connected to an F-16 inlet and forebody operating at an angle of attack and sideslip to demonstrate the effect of inlet distortion generated by flight maneuvers. The computational approach of simulating an integrated inlet-engine system is expected to provide additional insight over evaluating the components separately.

Download Full-text