NDLI: Mach number effects on turbine blade transition length prediction

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Mach number effects on turbine blade transition length prediction

Content Provider	NASA Technical Reports Server (NTRS)
Author	Simon, F. F. Boyle, R. J.
Copyright Year	1998
Description	The effect of a Mach number correction on a model for predicting the length of transition was investigated. The transition length decreases as the turbulent spot production rate increases. Much of the data for predicting the spot production rate comes from low speed flow experiments. Recent data and analysis showed that the spot production rate is affected by Mach number. The degree of agreement between analysis and data for turbine blade heat transfer without film cooling is strongly dependent of accurately predicting the length of transition. Consequently, turbine blade heat transfer data sets were used to validate a transition length turbulence model. A method for modifying models for the length of transition to account for Mach number effects is presented. The modification was made to two transition length models. The modified models were incorporated into the two-dimensional Navier-Stokes code, RVCQ3D. Comparisons were made between predicted and measured midspan surface heat transfer for stator and rotor turbine blades. The results showed that accounting for Mach number effects significantly improved the agreement with the experimental data.
File Size	1205427
Page Count	15
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19980211447
Archival Resource Key	ark:/13960/t56f0sg3r
Language	English
Publisher Date	1998-06-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics And Heat Transfer Turbulent Heat Transfer Turbine Blades Low Speed Turbomachinery Computerized Simulation Navier-stokes Equation Turbulence Models Predictions Stator Blades Boundary Layer Transition Mathematical Models Film Cooling Mach Number 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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