Fuel control for controlling helicopter rotor/turbine accelerati

Details Fuel control for controlling helicopter rotor/turbine accelerati Fuel control for controlling helicopter rotor/turbine accelerati

1982-04-16

1984-01-03

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

Multiple fluid-operated motors

60 39281, F02C 928

Patent

active

044235933

ABSTRACT:
The difference in the speed (54, 56) of a helicopter gas engine (20), free turbine (40) from a reference speed (62, 64) generates (80) a desired acceleration signal (81). The difference (82) in actual turbine acceleration (84, 86) from desired acceleration is integrated (100) to provide an engine fuel command signal (67-73) whenever (88) the speed error signal exceeds (90) a predetermined threshold magnitude.

REFERENCES:
patent: 2971338 (1961-02-01), Bodemoller
patent: 3638422 (1972-02-01), Loft et al.
patent: 4045955 (1977-09-01), Goran
patent: 4217754 (1980-08-01), Schmidt-Roedenbeck
patent: 4344141 (1982-08-01), Yates

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