Three-Dimensional Nonlinear Structural Analysis Methods for Gas Turbine Engine Metallic Components and Component Assemblies

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-07-C-5224
Agency Tracking Number: F061-095-1685
Amount: $1,191,010.00
Phase: Phase II
Program: SBIR
Awards Year: 2007
Solicitation Year: 2006
Solicitation Topic Code: AF06-095
Solicitation Number: 2006.1
Small Business Information
VEXTEC CORP.
750 Old Hickory Blvd, Building 2, Suite 270, Brentwood, TN, 37027
DUNS: 128193997
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Richard Holmes
 Director M&S
 (615) 372-0299
 rholmes@vextec.com
Business Contact
 Loren Nasser
Title: President
Phone: (615) 372-0299
Email: Lnasser@vextec.com
Research Institution
N/A
Abstract
The objective of this Phase II program is to implement, demonstrate and validate the computational techniques that were developed in Phase I that can be used for materials-damage based prognosis of gas turbine engine components and component assemblies. This approach will consist of a probabilistic multi-axial three-dimensional non-linear structural analysis method to enable the implementation of advanced life prediction and prognosis systems for aerospace gas turbine engine components and assemblies. The proposed methodology is based on key damage mechanisms including three dimensional crack growth in components and assemblies of components, material behavior, surface-treatment induced residual stress effects, and complex mission loading, coupled with detectable sensor parameters. Since the implementation of such advanced systems requires integration with the operation of the engines, close technical collaboration with OEMs will be maintained. This program will develop an efficient three-dimensional method that can be utilized for prediction of damage progression in a complex tri-axial stress state. Capability will be demonstrated through component life predictions and comparison with crack growth to failure results to be obtained from a scaled gas turbine engine testing.

* information listed above is at the time of submission.

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