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: FA8650-06-M-5230
Agency Tracking Number: F061-095-1685
Amount: $99,992.00
Phase: Phase I
Program: SBIR
Awards Year: 2006
Solicitation Year: 2006
Solicitation Topic Code: AF06-095
Solicitation Number: 2006.1
Small Business Information
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
 Mgr Technology
 (615) 372-0299
 rholmes@vextec.com
Business Contact
 Loren Nasser
Title: COO
Phone: (615) 372-0299
Email: Lnasser@vextec.com
Research Institution
N/A
Abstract
Air Force engines are required to satisfy both safe-life and fatigue crack growth (damage tolerant) design criteria under the engine structural integrity program (ENSIP). To achieve this requirement, nondestructive inspection techniques are used to detect cracks that can potentially grow to failure within the next inspection interval. However, these nondestructive inspections cannot be performed on wing and require a complete disassembly. Hence, the current life management approach is time consuming and expensive. Phase I will demonstrate feasibility for a three-dimensional nonlinear analysis method for advanced engine prognosis. The proposed methodology will include three dimensional crack growth in components and assemblies of components, non-linear material behavior, surface-treatment induced residual stress effects, and complex mission loading, coupled with detectable sensor parameters. The computational methods will be consistent with a probabilistic prognosis system and the design system developed for JSF. The approach will use engine sensor data acquired by the engine control and incorporate an analytical transfer function to obtain the instantaneous damage state. The resulting damage state will then be used to derive the remaining component durability.

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

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