Honeywell International Inc.

Rich Barrett

Larry K Ball

Raymond Gage

Alan Tiltman

Victor Reyes

Mike O'Brien

Douglas Spencer

Don Tillman

Don Rossi

Daniel Troller

James Ebken

A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud. Upon determining that the aircraft is flying at altitude cruise conditions, the compressor discharge air is directed to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud.

Gas turbine engine turbine blade tip active clearance control system and method

A lubrication system is provided for delivering a lubricant to a plurality of nozzles. The lubrication system includes a reservoir for the lubricant; a pump fluidly coupled to the reservoir and configured to remove a flow of the lubricant from the reservoir; a lubrication sensor positioned between the pump and the plurality of nozzles and configured to detect a blockage in the plurality of nozzles and to generate a blockage signal when the blockage is detected; and an indicator coupled to the lubrication sensor and configured to generate a warning based on the blockage signal from the lubrication sensor.

Lubrication systems with nozzle blockage detection systems

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Mesa, AZ, United States of America

Rich Barrett