Intelligent Virtual Rotor-Bearing System Design

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: F33615-03-M-2402
Agency Tracking Number: F031-2950
Amount: $99,904.00
Phase: Phase I
Program: SBIR
Awards Year: 2003
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
217 Billings Farm Road, White River Jct, VT, 05001
DUNS: 024355802
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 James Bielk
 Principal Investigator
 (781) 937-4637
 jrb@conceptsnrec.com
Business Contact
 Harold Keiling
Title: Executive Vice President
Phone: (802) 296-2321
Email: hak@conceptsnrec.com
Research Institution
N/A
Abstract
Lateral analysis of multi-level or multi-spool turbofan and turbojet engines has been regularly performed for more than 30 years by commercial engine manufacturers. Similarly, engine bearing designers also possess the ability to perform detailed analysisof bearing for the purpose of calculating operating characteristics (e.g., component operating temperatures) and determine statistical distributions of bearing life. Although the calculations involving both the rotors and the bearings are mutuallydependent, these analyses are currently performed using independent software tools that require significant human interaction and experience to perform a complete design iteration.The basic goal of the proposed project is to incrementally improve existing software tools so that accurate system rotor dynamics analysis of aircraft gas turbine engines can be performed using integrated rolling element bearing and squeeze film damperanalysis tools. This goal fits in nicely with Concepts NREC emphasis on development of interfaces which allow designers control of turbomachinery designs, as opposed developing new solvers. Basic code improvement and validation, as well as developmentof a series of test cases for the design tool, will still be addressed in this project. The basic goal of the proposed project is to incrementally improve existing software tools so that accurate system rotor dynamics analysis of aircraft gas turbine engines can be performed using integrated rolling element bearing and squeeze film damperanalysis tools.

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

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