INVESTIGATION OF A HIGH SPEED DIRECTLY DRIVEN ENGINE HYDRAULIC PUMP
Abstract
This report covers an exploratory development program to establish design technology for hydraulic pumps capable of being driven directly from aircraft gas turbine propulsion engines. The program was divided into a study phase, design phase, fabrication phase, and a test phase. After completing the study phase, the orbital type pump was chosen by the Air Force Propulsion Laboratory for design, fabrication, and test. Other pumping concepts were available that would theoretically reach the contract goals. However, it was desired that a unit be developed that would show growth potential beyond 10 gpm and 18,000 rpm. The .140 cubic inch per revolution orbital pump was designed from an existing .70 cubic inch per revolution unit by using a .585 scale factor. The porting was designed for 10 gpm flow, and the bearings were designed for 1000 hours life. The pump was designed to be compatible with MIL-H-5606 fluid in a Type II system. The test phase was conducted in accordance with the development test program for the E80108075 orbital piston pump. The tests were to determine pump performance and endurance capabilities. An investigation was also made to determine the horsepower loss for the various rotating parts of the pump. The orbital pump completed the Examination of Product, Break-in Run, Functional Test, Calibration, Proof Pressure Test, Sampling Test, and Low Temperature Test.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1966
- Accession Number
- AD0808449
Entities
People
- Frederick W. Perian