Performance-Based Inspection Techniques for Turbine Engine Blades and Rotors

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-05-M-2623
Agency Tracking Number: F051-193-3391
Amount: $99,158.00
Phase: Phase I
Program: SBIR
Awards Year: 2005
Solicitation Year: 2005
Solicitation Topic Code: AF05-193
Solicitation Number: 2005.1
Small Business Information
60 Broadhollow Rd., Melville, NY, 11747
DUNS: 012913265
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 David Eby
 Manager of Advanced Methods Develop
 (734) 453-2100
Business Contact
 William Clark
Title: Director of Software Business Unit
Phone: (734) 453-2100
Research Institution
Bladed disk assemblies found in jet engines feature random and intentional variations in blade geometries. These variations result in a phenomenon called mistuning, and are caused by manufacturing tolerances, operational wear, and/or intentional changes in geometry. Mistuning can lead to forced response amplitudes that are much larger than would be observed by a tuned assembly (i.e. all blades are structurally and aerodynamically identical). Even small mistuning effects can lead to large asymmetric forced response. Contrastingly, intentional mistuning seeks to minimize the system's forced response amplitudes. Since structural mistuning can dominate the system's forced response amplitudes, it can control the high cycle fatigue life of bladed discs. Tools generated in phase I and II of this proposal will create and translate high-fidelity CAD models into structural finite element analysis (FEA) elements and computational fluid dynamics (CFD) grids. The analysis capabilities developed in phase I and II include the ability to perform modal analysis, forced response, mistuning, sensitivity analysis, and damage tolerance, steady and unsteady aero calculations, and Fluid Structure Interaction Analysis (FSI).

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

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