Raytheon Technologies Corporation

Rtx Corporation

Sami Chukrallah

Andre M Ajami

Joshua R Seyler

Ryan W Hunter

Richard M Marshall

Lajos H Horvath

Richard D Konney

Robert B Davis

James D Hunter

A method is provided for treating a fuel system of a turbine engine. During this method, a treatment system is connected to the turbine engine. Preservation fluid is drawn out of the fuel system using the treatment system.

De-preserving a fuel system of a turbine engine

A system is provided for a powerplant. This powerplant system includes a core compressor section, a core combustor section, a core turbine section and a core flowpath extending longitudinally through the core compressor section, the core combustor section and the core turbine section between an inlet into the core flowpath and an exhaust from the core flowpath. The powerplant system also includes a first rotating assembly, a second rotating assembly and a clutch. The first rotating assembly includes a first compressor rotor and a first turbine rotor. The first compressor rotor is arranged in the core compressor section. The first turbine rotor is arranged in the core turbine section. The second rotating assembly includes a second compressor rotor and a second turbine rotor. The second turbine rotor is arranged in the core turbine section. The clutch is configured to selectively couple the first rotating assembly to the second rotating assembly.

Turbine engine with couplable rotating assemblies

A system includes a recirculation conduit that recirculates working fluid and a permanent magnet generator module in communication with the recirculation conduit. The working fluid from the recirculation conduit drives the permanent magnet generator module.

Flow recirculative power system

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 gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath, a turbine section fluidly connected to the combustor via the primary flowpath, and a plurality of fuel injectors disposed within the combustor. The plurality of fuel injectors including at least one start fuel injector. Also included is a controller having a memory and processor. The memory stores instructions configured to cause the at least one start fuel injector to pulse fuel through the start injector nozzle, thereby preventing stagnant fuel in the start injector nozzle from exceed a coking temperature threshold.

Method for reducing fuel nozzle coking in 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.

A fuel assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fuel valve that meters flow of fluid between a combustor and a fuel supply, and a controller in communication with the fuel assembly. The controller is programmed to receive data corresponding to a present rotational speed of a gas turbine engine component and data corresponding to at least one present flight condition, and is programmed to cause a flow rate from the fuel valve to change in response to determining that a rate of change in an acceleration rate relating to the present rotational speed meets at least one predetermined threshold. At least one predetermined threshold relates to an engine light-off event of the combustor and is based upon the at least one present flight condition.

Growing community of inventors

West Palm Beach, FL, United States of America

Sami Chukrallah