Hamilton Sundstrand Corporation

United Technologies Corporation

Kenneth W Winston

Xiaolan Hu

Michael E Mehrer

David Lloyd Ripley

Victor Pascu

Andre M Ajami

Paul E Hilgeman

Michael A Corson

Eric L Wolff

Ronald I Vicente

Michael Corson

Jason Eric Turner

Brent L Sherrill

Nelson Dacunha

Phillip Vessa

The present disclosure relates generally to a method for determining a failure of a flow divider within a fuel system, the method being performed by a controller and comprising the steps of: delivering a fuel command, calculating an expected fill time, wherein the expected fill time is indicative of the time required to fill a known fuel manifold volume, determining whether the actual fill time is greater than or equal to an expected fill time; and determining whether an actual fuel pressure value is less than or equal to an expect fuel pressure value based at least in part on at least one environmental signal.

Method for determining a fault within a flow divider

An example method of fuel delivery to a turbomachine includes reaching a light-off speed of a turbomachine and delivering fuel to a combustor of the turbomachine at a first rate. The method also increases the rate of the delivery. The combustor achieves light-off at a fuel flow rate on or in-between the first rate and a second rate that is greater than the first rate. An example turbomachine fuel delivery assembly includes a fuel delivery component and a controller configured to adjust the fuel pump to increase a rate of fuel delivery from a fuel supply to a combustor of a turbomachine.

Turbomachine fuel delivery method and assembly

A system for starting a gas turbine engine includes an engine controller and a fuel controller. The engine controller varies the engine speed between a minimum start speed and a maximum start speed until light-off of the engine occurs. The fuel controller operates a fuel command to vary fuel provided to a combustion chamber of the engine until light-off of the engine occurs.

High altitude start of a gas turbine engine using fuel pulsing and starter toggling

A method of starting a gas turbine engine includes maintaining the gas turbine engine at the dwelling speed after light-off until a predetermined magnitude of combustor warm-up is determined then increasing the speed of the starter motor to accelerate the gas turbine engine after the predetermined magnitude of combustor warm-up is achieved.

Starting a gas turbine engine to maintain a dwelling speed after light-off

A method for controlling a flow of fuel to a starting gas turbine engine includes controlling the flow of fuel to the engine by controlling fuel pressure to the engine, and modulating the flow of fuel to the engine if engine exhaust gas temperature approaches a given exhaust gas temperature to lower the engine exhaust gas temperature below the given exhaust gas temperature.

Fuel control method for starting a gas turbine engine

A system and method of controlling the acceleration of a load driven by a gas turbine engine detects the existence of an overload condition and reduces an acceleration setpoint when such condition arises.

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San Diego, CA, United States of America

Kenneth W Winston