Over the shaft fuel pumping system

Patent · Tue Feb 05 04:00:00 EST 1991

OSTI ID:6360693

Hoopes, J N; Eick, C D; Williamson, J R

This patent describes a gas turbine engine apparatus. It comprises: a compressor adapted to compress air inducted into the engine; a combustor adapted to receive and burn a mixture of fuel and compressed air to produce motive gas, a metering valve adapted to receive fuel and deliver the fuel to the combustor; a turbine adapted to receive the motive gas and produce rotary motion in response thereto; a shaft connected to the turbine and the compressor for transmitting the rotary motion to the compressor; and a vortex pump having an impeller girdling the shaft intermediate the compressor and the turbine rotating therewith, a pump inlet adjacent the shaft in fluid communication with a source of the fuel, a pump outlet in fluid communication with the metering valve, and means for defining a flow path between the fuel source and the inlet whereby the fuel is directed into the inlet in an axial direction which is substantially parallel to the shaft while preventing substantial fuel contact with the shaft so that circumferential fuel swirl at the inlet is minimized.

• Assignee: Allied-Signal Inc., Morris Township, Morris County, NJ (USA)
• Patent Number(s): US 4989411; A
• Application Number: PPN: US 7-289957
• OSTI ID: 6360693
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
COMPRESSORS
DESIGN
ENGINES
FUEL SYSTEMS
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MACHINE PARTS
PUMPS
SHAFTS