Gas turbine engine fuel control system

Details Gas turbine engine fuel control system Gas turbine engine fuel control system

1995-05-11

1997-05-13

Casaregola, Louis J.

Power plants

Reaction motor

Condition responsive thrust varying means

60 39281, F02C 928

Patent

active

056281854

ABSTRACT:
A ducted fan gas turbine engine is provided with means for measuring the actual temperature of air exhausted from its high pressure compressor and means for computing a theoretical value of that temperature. The difference between the actual and theoretical temperatures is used to modulate the fuel flow to the engine so that in the event of the temperature difference being greater than a predetermined amount, the fuel flow to the engine during engine starting is reduced to prevent stalling of the high pressure compressor

REFERENCES:
patent: 4594849 (1986-06-01), Kenison et al.
patent: 5080496 (1992-01-01), Keim
patent: 5379584 (1995-01-01), Windish et al.

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