Automatic turbine engine bleed valve control for enhanced fuel m

Details Automatic turbine engine bleed valve control for enhanced fuel m Automatic turbine engine bleed valve control for enhanced fuel m

1992-12-10

1994-05-24

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

60 3929, F02C 918

Patent

active

053137787

ABSTRACT:
A bleed air control system for an aircraft gas turbine engine operates in a fuel saving mode in response to operation of the aircraft in a steady-state cruise condition (215,350) within a threshold flight envelope (202,310) during steady-state engine operation above a threshold range. During operation in the fuel saving mode, a gas turbine engine compressor bleed valve (10) is closed. The rate of bleed valve closure is determined as a function of bleed valve position (12,20) and gas generator speed (26,30) at the instant the fuel savings mode is initiated. The bleed air control system is returned to normal operation in response to actual or commanded engine acceleration above respective threshold magnitudes, in response to aircraft load factor differing from a reference load factor by a threshold magnitude, and in response to the discontinued operation of the aircraft at steady-state cruise conditions, discontinued steady-state operation of the engine above the transient range, or operation of the aircraft outside of the threshold flight envelope.

REFERENCES:
patent: 4502275 (1985-03-01), Petro
patent: 4756152 (1988-07-01), Krukoski et al.
patent: 4825639 (1989-05-01), Krukoski
patent: 4991389 (1991-02-01), Schafer

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