United Technologies Corporation

Raytheon Technologies Corporation

Andrew P Berryann

Frederick M Schwarz

Brian M Fentress

Gary D Roberge

Jorn Axel Glahn

Charles E Lents

Gabriel L Suciu

Daniel Bernard Kupratis

James W Norris

Mark W Costa

Alan H Epstein

Stephen A Morford

Scott A Carr

Jams W Norris

A gas turbine engine includes a flow control mechanism operable to direct at least a portion of a fan airflow from a secondary flow path into a core flow path.

Start system for gas turbine engines

A gas turbine engine includes a high spool, a low spool mechanically connected to a fan, a gear system, an actuator, and a starter. The gear system is actuable to engage and disengage the low spool to and from the high spool. The actuator is connected to the gear system for selectively engaging and disengaging the gear system. The starter is connected to the low spool and can drive rotation of the high spool through the low spool when the gear system is engaged.

Mechanism for turbine engine start from low spool

A gas turbine engine system includes a fan and a fan bypass passage downstream of the fan for conveying a bypass airflow from the fan. A nozzle associated with the fan bypass passage includes a plurality of different positions that influence the bypass air flow. One or more sensors near the fan produce a signal representative of a foreign object near the fan. A controller commands the nozzle to move to a desired one of the plurality of different positions in response to the signal from the sensor to change a pressure ratio across the fan to thereby reduce a mechanical stress on the fan.

Variable area fan nozzle for accommodating a foreign object strike event

A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and a forward-flow low pressure turbine disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine disposed aft of the low pressure turbine, a combustor disposed aft of the high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor.

Reversed-flow core for a turbofan with a fan drive gear system

A gas turbine engine is provided with a first heat exchanger associated with a cooling air flow to deliver cooling air to a turbine section. A second heat exchanger is associated with a fuel supply line for delivering fuel into a combustion section. An intermediate fluid cools air at the first heat exchanger and heats fuel at the second heat exchanger.

Gas turbine engine with air and fuel cooling system

A power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine in an engine compartment in the aircraft with an air inlet in the aircraft that is curved along its extent in leading to an air compressor in the gas turbine engine having a compressor air transfer duct extending therefrom to an internal combustion engine provided as an intermittent combustion engine at an air intake thereof. An inlet duct manifold is positioned against the duct wall of the inlet duct to cover a perforated portion thereof on the air compressor side of a curve therein with the inlet duct manifold having an inlet air transfer duct extending therefrom that is coupled to the intermittent combustion engine air intake.

Aircraft combination engines inlet airflow control system

An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto.

Combination engines for aircraft

A power generation system for propelling, and generating electrical power in, an aircraft, using a gas turbine engine coupled to a turbine starter/generator unit having therein an electrical machine capable of being selected to be alternatively a motor and an electrical power generator and having a coupling shaft extending therefrom to be engaged with the air compressor in the gas turbine engine and further having an interconnection conductor for electrical energization. An internal combustion engine provided as an intermittent combustion engine in the aircraft has an air intake coupled through an air transfer duct connected to the air compressor to allow the transfer of compressed air thereto, and has in connection therewith a supply starter/generator unit with a coupling shaft extending therefrom to be engaged with the intermittent combustion engine power shaft. An interconnection conductor therein for electrical energization is electrically interconnected with the turbine starter/generator unit interconnection conductor.

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Manchester, CT, United States of America

Andrew P Berryann