Transient control system for gas turbine engine

Details Transient control system for gas turbine engine Transient control system for gas turbine engine

1987-02-03

1989-03-07

Casaregola, Louis J.

Power plants

Reaction motor

Condition responsive thrust varying means

F02K 117

Patent

active

048095001

ABSTRACT:
A secondary control for a gas turbine engine powering fighter class of aircraft serves to modify the primary control solely during transient engine operation primarily in the combat box of between approximately 0.4 to 1.2 Mach number at an altitude between 10,000 to 30,000 feet of the flight envelope and does maintain higher compressor rpm, turbine inlet temperature, and engine air flow at the idle or part power thrust settings by concomitantly adjusting fuel flow and engine exhaust nozzle area thereby enhancing thrust response, low cycle fatigue life, and engine stability.

REFERENCES:
patent: 3041822 (1962-07-01), Embree
patent: 3656301 (1972-04-01), Katz
patent: 3747344 (1983-07-01), Porter et al.
patent: 4159625 (1979-07-01), Kerr
patent: 4467600 (1984-08-01), Peikert

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