Rtx Corporation

Raytheon Technologies Corporation

Ryan W Hunter

Andre M Ajami

Javier A Cue

Sami Chukrallah

Richard M Marshall

Orin G Avidane

A heat exchanger can comprise: a housing; a heat transfer region disposed within the housing; and an inlet manifold or an inlet conduit defined at least partially by an interior surface extending axially from a first end of the heat exchanger to an inlet defined by the heat transfer region, the inlet manifold or the inlet conduit comprising a dimple configuration disposed in the interior surface. The heat exchanger can further comprise an outlet manifold or an outlet conduit including a dimple configuration disposed on an interior surface of the outlet manifold or outlet conduit.

Heat exchanger systems and devices for reduced pressure loss

An engine system includes a gas turbine engine with a first compressor, a first combustor, and first turbine. The engine system also includes a secondary power unit with a second compressor, a second combustor, a second turbine, a third compressor coupled to the second compressor, and an electric motor-generator, where the secondary power unit is coupled to the gas turbine engine and includes a heat exchanger. A controller is operable to determine an operating mode of the engine system, select an input energy source and an output type of the secondary power unit based on the operating mode, control the secondary power unit based on the input energy source and the output type as selected, detect a change in the operating mode of the engine system, and modify the input energy source and/or the output type of the secondary power unit based on the change in the operating mode.

Engine and secondary power unit integrated operation

An engine system is provided that includes a compressor section, a combustor section, a turbine section, a flowpath and a flow regulator. The combustor section includes a combustion chamber. The flowpath extends sequentially through the compressor section, the combustor section and the turbine section. The flow regulator is configured to open the flowpath between the compressor section and the combustion chamber during a first mode of operation. The flow regulator is configured to at least substantially close the flowpath between the compressor section and the combustion chamber during a second mode of operation.

Multi-mode engine system with gas turbine engine and turbo-compressor

An engine system includes a gas turbine engine with a first compressor, a first combustor, and a first turbine. The engine system also includes a secondary power unit with a second compressor, a second combustor, a second turbine, a third compressor coupled to the second compressor, and an electric motor-generator, where the secondary power unit is coupled to the gas turbine engine. A controller is operable to determine an operating mode of the engine system, select an input energy source and an output type of the secondary power unit based on the operating mode, control the secondary power unit based on the input energy source and the output type as selected, detect a change in the operating mode of the engine system, and modify the input energy source and/or the output type of the secondary power unit based on the change in the operating mode.

A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first threshold is met. The first threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

Hydraulic starter assembly for a gas turbine engine

A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first predefined threshold is met. The first predefined threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

Growing community of inventors

North Palm Beach, FL, United States of America

Ryan W Hunter