An Experimental and Computational Investigation of Oscillating Airfoil Unsteady Aerodynamics at Large Mean Incidence
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Authors
Capece, Vincent R.
Platzer, Max F.
Subjects
UNSTEADY AERODYNAMICS
TURBOMACHINERY
AIRFOILS
AEROELASTICITY
GAS TURBINE ENGINES
INCIDENCE
FORCED VIBRATION
STEADY FLOW
SKIN FRICTION
TURBULENCE
SEPARATED FLOW
SUBSONIC SPEED
TWO DIMENSIONAL MODELS
FLUTTER
COMPRESSOR BLADES
TURBOMACHINERY
AIRFOILS
AEROELASTICITY
GAS TURBINE ENGINES
INCIDENCE
FORCED VIBRATION
STEADY FLOW
SKIN FRICTION
TURBULENCE
SEPARATED FLOW
SUBSONIC SPEED
TWO DIMENSIONAL MODELS
FLUTTER
COMPRESSOR BLADES
Advisors
Date of Issue
2003-03
Date
Mar 01, 2003
Publisher
Language
Abstract
A major challenge in the design and development of turbomachine airfoils for gas turbine engines is high cycle fatigue failures due to flutter and aerodynamically induced forced vibrations. In order to predict the aeroelastic response of gas turbine airfoils early in the design phase, accurate unsteady aerodynamic models are required. However, accurate predictions of flutter and forced vibration stress at all operating conditions have remained elusive. The overall objectives of this research program are to develop a transition model suitable for unsteady separated flow and quantify the effects of transition on airfoil steady and unsteady aerodynamics for attached and separated flow using this model. Furthermore, the capability of current state-of-the-art unsteady aerodynamic models to predict the oscillating airfoil response of compressor airfoils over a range of realistic reduced frequencies, Mach numbers, and loading levels will be evaluated through correlation with benchmark data. This comprehensive evaluation will assess the assumptions used in unsteady aerodynamic models. The results of this evaluation can be used to direct improvement of current models and the development of future models. The transition modeling effort will also make strides in improving predictions of steady flow performance of fan and compressor blades at off-design conditions. This report summarizes the progress and results obtained in the first year of this program. These include: installation and verification of the operation of the parallel version of TURBO; the grid generation and initiation of steady flow simulations of the NASA/Pratt&Whitney airfoil at a Mach number of 0.5 and chordal incidence angles of 0 and 10 deg.; and the investigation of the prediction of laminar separation bubbles on a NACA 0012 airfoil.
Type
Technical Report
Description
Series/Report No
Department
Organization
Glenn Research Center
Identifiers
NPS Report Number
Sponsors
Funding
NAG3-2613; WU?708?87?23?00
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.