Design and Evaluation of Advanced High-Speed Fuel Pump
Abstract
The purpose of this program was to develop both the technology and the experimental hardware to experimentally demonstrate that a main-engine fuel pump could be operated at turbine-engine shaft speeds. A single-lobe vane pump has been designed and successfully operated at speeds up to 49,500 rpm and outlet pressures up to 900 psig while pumping JP-4 turbine fuel. The promising capabilities demonstrated by this pump were the result of the successful application of hydrodynamic lubrication techniques to the vane design. The pivoting vane tip concept incorporated permits tip surface speeds up to 180 fps to be achieved without producing high mechanical power losses or sacrificing the pump endurance capabilities. The present experimental fuel pump represents a significant step toward the development of flight hardware capable of operating at engine shaft speed. It meets the basic performance requirements of a main- engine fuel pump typically required on small, high speed gas-turbine engines. In addition, it appears that a variable-displacement capability could be developed directly from the present hardware without altering the established high-speed capabilities.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1971
- Accession Number
- AD0729867
Entities
People
- Harry T. Johnson
Organizations
- Battelle Memorial Institute