Performance-Based Inspection Techniques for Turbine Engine Blades and Rotors

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-05-M-2584
Agency Tracking Number: F051-193-3168
Amount: $99,169.00
Phase: Phase I
Program: SBIR
Awards Year: 2005
Solicitation Year: 2005
Solicitation Topic Code: AF05-193
Solicitation Number: 2005.1
Small Business Information
140 Intracoastal Pointe; Suite 301, Jupiter, FL, 33477
DUNS: 048159342
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Susan Cunnigham
 Program Manager
 (561) 746-3317
Business Contact
 Lloyd Mazer
Title: Contracts Officer
Phone: (561) 746-3317
Research Institution
HCF is one of the leading causes of engine failure in aircraft. Preventing HCF failures requires accurate determination and avoidance of resonant frequencies in design. Designers use a combination of finite element structural analysis and modal frequency testing to identify the natural frequencies at which components resonate. However, these analyses are typically performed on nominal geometries. While each of the blades in a blade row is designed to the same nominal dimensions with close tolerances, the actual dimensions (and therefore resonant frequencies) of manufactured parts will vary a small amount from blade to blade. Methods for acquiring digital 3D dimensional data of manufactured parts are now available but the process to characterize stress from 3D scans is complex and time-consuming. Each blade requires it own mesh for computational fluid dynamics (CFD) analysis to predict aerodynamic loading, and finite element analysis (FEA) to calculate the blade frequency and stress. The goal herein is to develop methods for streamlining the process for calculating blade vibratory stress for measured airfoils. We propose to develop the techniques to efficiently manipulate the geometry and finite element meshes in order to permit multiple blade stress calculations in much less time than it takes today.

* Information listed above is at the time of submission. *

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