Accession Number : ADA312466
Title : Low Reynolds Number Turbine Blade Cascade Calculations.
Descriptive Note : Final rept. 1 Nov 95-9 Jul 96,
Corporate Author : WRIGHT LAB WRIGHT-PATTERSON AFB OH
Personal Author(s) : Rivir, Richard ; Sondergaard, Rolf ; Dahlstrom, Michael ; Ervin, Elizabeth
PDF Url : ADA312466
Report Date : 1996
Pagination or Media Count : 15
Abstract : Computations of the velocity fields for Langston turbine blade cascades with solidities of 1.075 and 0.84 have been carried out at Reynolds numbers of 50K, 100K, 200K, 441K, 1000K, and 2000K. A second cascade investigated at Reynolds numbers of 50K and 100K uses the Langston airfoil which has been modified by extending the trailing edge, resulting in a solidity of 0.786. The computations were performed with Allison's Blade Vanc Interaction code. Computational results are presented for transition, separation, and reattachment.
Descriptors : *BOUNDARY LAYER TRANSITION, *GAS TURBINE BLADES, *CASCADES(FLUID DYNAMICS), MATHEMATICAL MODELS, TURBULENCE, LOW PRESSURE, COMPUTATIONAL FLUID DYNAMICS, GAS TURBINES, FLOW FIELDS, UNSTEADY FLOW, NAVIER STOKES EQUATIONS, FLOW SEPARATION, REYNOLDS NUMBER, SKIN FRICTION, TRAILING EDGES.
Subject Categories : Fluid Mechanics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE