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  • 1
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    Average-passage flow model development (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A 3-D model was developed for simulating multistage turbomachinery flows using supercomputers. This average passage flow model described the time averaged flow field within a typical passage of a bladed wheel within a multistage configuration. To date, a number of inviscid simulations were executed to assess the resolution capabilities of the model. Recently, the viscous terms associated with the average passage model were incorporated into the inviscid computer code along with an algebraic turbulence model. A simulation of a stage-and-one-half, low speed turbine was executed. The results of this simulation, including a comparison with experimental data, is discussed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 247-251
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Simulation of three-dimensional viscous flow within a multistage turbine (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This work outlines a procedure for simulating the flow field within multistage turbomachinery which includes the effects of unsteadiness, compressibility, and viscosity. The associated modeling equations are the average passage equation system which governs the time-averaged flow field within a typical passage of a blade row embedded within a multistage configuration. The results from a simulation of a low aspect ratio stage and a one-half turbine will be presented and compared with experimental measurements. It will be shown that the secondary flow field generated by the rotor causes the aerodynamic performance of the downstream vane to be significantly different from that of an isolated blade row.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 89-GT-152
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Simulation of 3-D viscous flow within a multi-stage turbine (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This work outlines a procedure for simulating the flow field within multistage turbomachinery which includes the effects of unsteadiness, compressibility, and viscosity. The associated modeling equations are the average passage equation system which governs the time-averaged flow field within a typical passage of a blade row embedded within a multistage configuration. The results from a simulation of a low aspect ratio stage and a one-half turbine will be presented and compared with experimental measurements. It will be shown that the secondary flow field generated by the rotor causes the aerodynamic performance of the downstream vane to be significantly different from that of an isolated blade row.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-101376 , E-4430 , NAS 1.15:101376 , International Gas Turbine and Aeroengine Congress and Exposition; Jun 04, 1989 - Jun 08, 1989; Toronto, Ontario; Canada
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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