Fuel control for gas turbine engines

Patent · Tue Dec 27 00:00:00 EST 1983

OSTI ID:6920365

Stearns, C F; Tutherly, H W

The basic gas turbine engine hydromechanical fuel control is adaptable to different engine configurations such as turbofan, turboprop and turboshaft engines by incorporating in the main housing those elements having a commonality to all engine configurations and providing a removable block for each configuration having the necessary control elements and flow passages required for that particular configuration. That is to say, a block with the elements peculiar to a turbofan engine could be replaced by a mating block that includes those elements peculiar to a turboshaft engine in adapting the control for a turboshaft configuration. Similarly another block with those elements peculiar to a turboprop engine could replace any of the other blocks in adapting the control to a turboprop configuration. Obviously the basic control has the necessary flow passages terminating at the interface with the block and these flow passages mate with corresponding passages in the block.

• Assignee: United Technologies Corp.
• Patent Number(s): US 4422287
• OSTI ID: 6920365
• Resource Relation: Patent File Date: Filed date 29 Sep 1980; Other Information: PAT-APPL-191548
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
GAS TURBINE ENGINES
CONTROL SYSTEMS
FUEL SYSTEMS
CONFIGURATION
DESIGN
DIGITAL SYSTEMS
ELECTRONIC CIRCUITS
GAS FLOW
ENGINES
FLUID FLOW
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
330103* - Internal Combustion Engines- Turbine