Accession Number:

AD1041446

Title:

A Comparison of Hybrid Reynolds Averaged Navier Stokes/Large Eddy Simulation (RANS/LES) and Unsteady RANS Predictions of Separated Flow for a Variable Speed Power Turbine Blade Operating with Low Inlet Turbulence Levels

Descriptive Note:

Technical Report,01 Oct 2016,30 Sep 2017

Corporate Author:

US Army Research Laboratory Aberdeen Proving Ground United States

Personal Author(s):

• Booth,David T

Report Date:

2017-10-01

Pagination or Media Count:

39.0

Abstract:

A comparison of hybrid Reynolds-averaged Navier-StokesLarge-Eddy Simulation RANSLES and unsteady RANS computations for unsteady separated flow prediction of a linear turbine blade cascade operating with large incidence angle variation is described. The computations comprise a periodic single blade that represents the midspan section of a variable-speed power-turbine blade that was tested in NASA Glenn Research Centers Transonic Turbine Blade Cascade Facility. A commercial, off-the-shelf software package, Pointwise and CFD , was used for the grid generation and computations. Simulations were assessed at low inlet turbulence levels for positive and negative incidence angles that represent turbine cruise and takeoff conditions. Comparisons of results for blade loading and loss were made to test data from the transonic tunnel. Comparisons of results for separation predictions were made between the hybrid RANSLES and RANS computations. Comparisons of separation prediction revealed significant differences in location and extent of separation between the models and grid types.

Descriptors:

• computational fluid dynamics
• reynolds number
• boundary layer
• tilt rotor aircraft
• turbulent mixing
• pressure distribution
• flow fields
• fluid flow
• mach number
• pressure measurement
• turbine blades
• leading edges
• mechanical properties
• trailing edges
• NAVIER STOKES EQUATIONS
• turbines

Subject Categories:

• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE