Navier-Stokes flow simulation of the Space Shuttle Main Engine hot gas manifold

1992 ◽  
Vol 29 (2) ◽  
pp. 253-259 ◽  
Author(s):  
R.-J. Yang ◽  
J. L. C. Chang ◽  
D. Kwak
Keyword(s):  
Stokes Flow ◽  
Space Shuttle ◽  
Flow Simulation ◽  
Navier Stokes ◽  
Hot Gas ◽  
Main Engine

scholarly journals Experimental evaluation of an advanced Space Shuttle Main Engine hot-gas manifold design concept

1984 ◽  
Author(s):  
D. PELACCIO ◽  
F. LEPORE ◽  
G. OCONNOR ◽  
G. RAO ◽  
G. RATEKIN ◽  
...  
Keyword(s):  
Experimental Evaluation ◽  
Space Shuttle ◽  
Design Concept ◽  
Hot Gas ◽  
Main Engine

Time-Averaged Heat Transfer and Pressure Measurements and Comparison With Prediction for a Two-Stage Turbine

1994 ◽  
Vol 116 (1) ◽  
pp. 14-22 ◽  
Author(s):  
M. G. Dunn ◽  
J. Kim ◽  
K. C. Civinskas ◽  
R. J. Boyle
Keyword(s):  
Surface Pressure ◽  
Space Shuttle ◽  
Three Dimensional ◽  
Stanton Number ◽  
Navier Stokes ◽  
Pressure Measurements ◽  
Two Stage ◽  
Pressure Transducers ◽  
Pressure Distributions ◽  
Main Engine

Time-averaged Stanton number and surface-pressure distributions are reported for the first-stage vane row and the first-stage blade row of the Rocketdyne Space Shuttle Main Engine two-stage fuel-side turbine. These measurements were made at 10, 50, and 90 percent span on both the pressure and suction surfaces of the component. Stanton-number distributions are also reported for the second-stage vane at 50 percent span. A shock tube is used as a short-duration source of heated and pressurized air to which the turbine is subjected. Platinum thin-film gages are used to obtain the heat-flux measurements and miniature silicone-diaphragm pressure transducers are used to obtain the surface pressure measurements. The first-stage vane Stanton number distributions are compared with predictions obtained using a quasi-three dimensional Navier–Stokes solution and a version of STAN5. This same N–S technique was also used to obtain predictions for the first blade and the second vane.

Aerodynamic evaluation of the redesigned Space Shuttle Main Engine hot-gas manifold

1985 ◽  
Author(s):  
S. VOGT ◽  
W. CUAN ◽  
F. HOEHN ◽  
B. KIM ◽  
G. OCONNOR ◽  
...  
Keyword(s):  
Space Shuttle ◽  
Hot Gas ◽  
Main Engine

A Three Dimensional Spiral Casing Navier-Stokes Flow Simulation

1996 ◽  
pp. 81-90
Author(s):  
Ch. Bruttin ◽  
J.-L. Kueny ◽  
B. Boyer ◽  
K. Héon ◽  
T. C. Vu ◽  
...  
Keyword(s):  
Stokes Flow ◽  
Three Dimensional ◽  
Flow Simulation ◽  
Navier Stokes ◽  
Spiral Casing

Validation of the INS3D-UP Code in the Prediction of Turbulent Flow of Liquid Propellants in a Sharp Bend

1995 ◽  
Author(s):  
M. A. R. Sharif ◽  
J. T. Haskew
Keyword(s):  
Turbulent Flow ◽  
Space Shuttle ◽  
Circular Cross Section ◽  
Navier Stokes ◽  
Navier Stokes Equation ◽  
Sharp Bend ◽  
Flow Problems ◽  
Fortran Code ◽  
Main Engine ◽  
Liquid Propellants

Abstract The capability of the INS3D-UP code in the prediction of turbulent flow in a sharp bend of circular cross-section has been investigated. The code, developed by the NASA Ames Research Center, is being used by the NASA Marshal Space Flight Center to analyze turbulent flow of liquid propellant in vaned pipe bends designed for use in the Space Shuttle Main Engine. The FORTRAN code is based on finite difference method and uses the concept of pseudocompressibility to solve incompressible Navier-Stokes equation. The Baldwin-Barth turbulence model is embedded in the code for turbulence computation. The flow field, at a Reynolds number of 43,000, in a sharp 90° bend has been predicted and compared with measurement. It is found that the agreement between the predicted and measured velocities is very well. The predicted pressures at the bend wall also compares reasonably well with the measurement. It is concluded that the INS3D-UP code is a good computational tool to analyze similar flow problems.

Time-Averaged Heat Transfer and Pressure Measurements and Comparison With Prediction for a Two-Stage Turbine

1992 ◽  
Author(s):  
M. G. Dunn ◽  
J. Kim ◽  
K. C. Civinskas ◽  
R. J. Boyle
Keyword(s):  
Surface Pressure ◽  
Space Shuttle ◽  
Stanton Number ◽  
Navier Stokes ◽  
Pressure Measurements ◽  
Two Stage ◽  
Pressure Transducers ◽  
Pressure Distributions ◽  
Flux Measurements ◽  
Main Engine

Time-averaged Stanton number and surface-pressure distributions are reported for the first-stage vane row and the first-stage blade row of the Rocketdyne Space Shuttle Main Engine two-stage fuel-side turbine. These measurements were made at 10%, 50%, and 90% span on both the pressure and suction surfaces of the component. Stanton-number distributions are also reported for the second-stage vane at 50% span. A shock tube is used as a short-duration source of heated and pressurized air to which the turbine is subjected. Platinum thin-film pages are used to obtain the heat-flux measurements and miniature silicone-diaphragm pressure transducers are used to obtain the surface pressure measurements. The first-stage vane Stanton number distributions are compared with predictions obtained using a quasi-3D Navier-Stokes solution and a version of STAN5. This same N-S technique was also used to obtain predictions for the first blade and the second vane.

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