NDLI: Turbine rotor/stator flowfield analysis

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Turbine rotor/stator flowfield analysis

Content Provider	NASA Technical Reports Server (NTRS)
Author	Griffin, Lisa
Copyright Year	1989
Description	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.
File Size	1013428
Page Count	37
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19890015062
Archival Resource Key	ark:/13960/t5q866t2x
Language	English
Publisher Date	1989-03-01
Access Restriction	Open
Subject Keyword	Spacecraft Propulsion And Power Wall Temperature Axial Flow Turbines Thermal Environments Rotor Blades Turbomachinery Space Shuttle Main Engine Rotor Stator Interactions Pressure Distribution Stator Blades Adiabatic Conditions Unsteady Flow Heat Flux Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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