Honeywell International Inc.

Honeywell Power Systems, Inc.

Mohamad Hanif Vhora

Gregory J Chapman

Daniel C Burns

Patrick L O'Brien

John Lipinski

Timothy Keller

Jeffrey J Aitchison

Ronnie Haugland

Tim Keller

Coung Van Nguyen

Dan Burnes

A system and method for controlling compressor inlet guide vanes of a gas turbine engine in an aircraft includes supplying, to a compressor inlet guide vane control algorithm, an inlet temperature value that is at least representative of sensed engine inlet total temperature. One or more gas turbine engine parameters are sensed with one or more sensors during operation of the gas turbine engine. The one or more gas turbine engine parameters are processed in the engine control unit to determine an inlet temperature modifier value that is an estimate of a difference between the sensed engine inlet total temperature and actual engine inlet total temperature. The inlet temperature modifier value is added to the inlet temperature value to derive a modified engine inlet total temperature. The modified engine inlet total temperature is used in the compressor inlet guide vane control algorithm, which controls the compressor inlet guide vanes.

Temperature inversion detection and mitigation strategies to avoid compressor surge

Control logic and a method for controlling turbine speed. In an embodiment, the inventive control logic controls turbine speed of turbine generators operating in a stand-alone mode and/or a grid mode.

Valve control logic for gas turbine recuperator

A control system and method for controlling the split between premix fuel flow and pilot fuel flow to a combustor in a gas turbine engine so that an acceptable emissions are maintained. Engine speed and exhaust gas temperature are used to obtain a combustor pilot zone temperature that will result in the desired level of emissions. From this pilot zone temperature a desired split between premix fuel flow and pilot fuel flow is obtained and compared to the actual split to generate an error signal. The actual premix fuel flow and pilot fuel flow are then adjusted until the desired split and hence the desired emission levels are obtained.

Fuel control method for gas turbine

Growing community of inventors

Albuquerque, NM, United States of America

Mohamad Hanif Vhora