Turbine rotor/stator flowfield analysis
A numerical study of the unsteady aerodynamic and thermal environment associated with axial turbine stages is presented. Computations are performed using a modification of the ROTOR1 rotor/stator interaction code. Two different turbine states are analyzed: the first state of the United Technologies Research Center large scale rotating rig and the first state of the Space Shuttle main engine (SSME) high pressure fuel turbopump. Time-averaged blade midspan pressure and heat transfer profiles are calculated using the following different surface boundary conditions: adiabatic wall, prescribed wall temperature, and prescribed heat flux. Numerical solutions for the large scale rotating rig are compared with experimental data. Unsteady pressure envelopes are also presented for each geometry. In addition, instantaneous contours are plotted for the SSME configuration.
- Research Organization:
- Lockheed Missiles and Space Co., Huntsville, AL (USA)
- OSTI ID:
- 5521870
- Report Number(s):
- N-89-24433; NASA-CR-183639; NAS-1.26:183639; LMSC-HEC-TR-F-268519
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
GAS TURBINES
AERODYNAMICS
PRESSURE GRADIENTS
TEMPERATURE DISTRIBUTION
TURBINE BLADES
HEAT FLUX
HEAT TRANSFER
NUMERICAL ANALYSIS
STATORS
UNSTEADY FLOW
ENERGY TRANSFER
FLUID FLOW
FLUID MECHANICS
MACHINERY
MATHEMATICS
MECHANICS
TURBINES
TURBOMACHINERY
421000* - Engineering- Combustion Systems