Compressor vane control for gas turbine engines

Power plants – Reaction motor – Method of operation

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Details

60 3903, 60 3929, 60236, F02C 920

Patent

active

053577485

ABSTRACT:
In a gas turbine engine a method for thrust variation with reduced compressor RPM excursion is provided in two modes which includes adjusting pivotable compressor vanes mounted upstream of compressor rotor blades, ahead of the conventional vane schedule therefor in a closed loop fashion, responsive to compressor corrected RPM, so as to adjust the fuel demand and engine thrust thereof while maintaining relatively high scheduled compressor corrected RPM scheduled as a function of fan corrected RPM while retaining the conventional method of fuel flow scheduling. Thus mode 1 of the invention adjusts the compressor vanes in advance of the conventional schedule therefor, e.g. pre-closes them on the deceleration side of the Bodie transient and appropriately opens them on the acceleration side of such transient subject to closed loop monitoring of the corrected compressor RPM and being guided thereby so as to result in reduced excursion in such RPM, during both legs of such transient. Because of such reduced RPM excursion, fast changes in engine thrust are possible. In mode 2 of the invention, snap accelerations of a gas turbine engine and its compressor, are assisted by opening the compressor vanes ahead of the conventional schedule therefor in an open loop fashion, not so much for compressor corrected RPM excursion advantage as for improved compressor stall margin. The methods of the invention thus emphasize the primacy of vane control over fuel flow control for reduced compressor RPM excursion in the first mode and increased stall margin in the second mode.

REFERENCES:
patent: 4514137 (1985-04-01), Elliott
patent: 4594050 (1986-06-01), Gaston
patent: 4831535 (1989-05-01), Blotenberg
patent: 4944652 (1990-07-01), Blotenberg
patent: 4947643 (1990-08-01), Pollak et al.
patent: 4971516 (1990-11-01), Lawless et al.

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