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

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.

The Reynolds Stress in Channel Flows From a Lagrangian Treatment of the Turbulence Momentum

2019 ◽  
Author(s):  
T.-W. Lee
Keyword(s):  
Turbulent Flow ◽  
Reynolds Stress ◽  
Current Approach ◽  
Navier Stokes ◽  
Current Transport ◽  
Lagrangian Analysis ◽  
Navier Stokes Equation ◽  
Mechanistic Approach ◽  
Turbulent Momentum

Abstract We have developed a mechanistic approach for determination of the Reynolds stress, using a Lagrangian analysis of turbulent momentum. Analysis and comparison with DNS and experimental data point toward the soundness of this approach (Lee, 2018). von Karman constant, the inner layer thickness and the Reynolds stress itself are all recovered through this approach, in agreement with DNS data. In addition, the turbulent flow profiles can be calculated iteratively using the basic Reynolds-averaged Navier-Stokes equation, in conjunction with the current transport equation for the Reynolds stress. In this work, we explore these and further uses of the current approach in solving turbulent flow dynamics.

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

Preliminary Imaging of Red Blood Cells in Turbulent Flow

2012 ◽  
Author(s):  
Mostafa Shakeri ◽  
Iman Khodarahmi ◽  
M. Keith Sharp
Keyword(s):  
Turbulent Flow ◽  
Red Blood Cells ◽  
Blood Cells ◽  
Imaging System ◽  
Navier Stokes ◽  
Viscous Stress ◽  
Damage Potential ◽  
Navier Stokes Equation ◽  
Considerable Uncertainty ◽  
Mathematical Construct

Considerable uncertainty exists about how momentum and energy are transferred to cells in turbulent flow, which has been shown to cause six times more damage to red blood cells (RBC’s) than laminar flow with the same mean wall shear stress [Kameneva, et al. 2004]. Though it is a purely mathematical construct to yield closure of the time-averaged Navier-Stokes equation for a continuum fluid, which is not valid at the scale of the cell, Reynolds stress has been used as an empirical indicator for damage potential [Sallam & Hwang 1984]. Other scales, including local viscous stress [Jones 1995], flow of plasma around inertia cells [Quinlan & Dooley 2007], shear within eddies [Quinlan & Dooley 2007] and shear between rigid cells within an eddy [Antiga & Steinman 2009], have been forwarded. To provide data to validate these models, an imaging system was assembled to directly observe RBC’s in turbulent flow under a microscope.

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.

Simulations and Measurements of Dredge Pump

2005 ◽  
Author(s):  
Guangjie Peng ◽  
Zhengwei Wang ◽  
Wen Yang
Keyword(s):  
Centrifugal Pump ◽  
Flow Characteristics ◽  
Navier Stokes ◽  
Navier Stokes Equation ◽  
Flow Problems ◽  
Computational Performance ◽  
Discharge Curve ◽  
Lower Capacity ◽  
Reynolds Average ◽  
Measuring Curve

Flow field of centrifugal pump (Pump flow passage includes suction pipe, impeller and volute casing.) obtained by solving the Reynolds average Navier-Stokes equation. Computational performance curve is compared with measuring curve. The result demonstrates that the computational head versus discharge curve is coincident with the measuring curve; the computational efficiency curve is coincident with the measuring curve in large-capacity area, in lower-capacity area not so well. Though the simulation result is not accurate highly in part operating domains, the pressure and velocity distribution and other flow characteristics in whole flow path in all operating domain produced by the simulation are also useful to analyze flow problems in dredge centrifugal pump.

Experimental study of the velocity of the flow of highly viscous Newtonian liquid in a curved rectangular duct

1986 ◽  
Vol 51 (1) ◽  
pp. 66-74
Author(s):  
Pavel Seichter
Keyword(s):  
Experimental Study ◽  
Stokes Equation ◽  
Cross Section ◽  
Circular Cross Section ◽  
Newtonian Liquid ◽  
Creeping Flow ◽  
Navier Stokes ◽  
Rectangular Duct ◽  
Navier Stokes Equation ◽  
Experimental Values

Thermistor anemometer measurements in a curved rectangular duct and a straight circular cross section tube permitted verification of the theoretical values of tangential velocities computed on the basis of the solution of the Navier-Stokes equation for the drag isothermal and creeping flow of a Newtonian liquid. From comparison of the theoretical and experimental values there follows that the achieved agreement is acceptable.

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