United Technologies Corporation

Raytheon Technologies Corporation

Timothy J Gaudet

James B Hoke

Richard P Meisner

Dennis M Moura

Joshua Adams

Timothy J Crowley

Charles E Reuter

Jesse W Clauson

Martin Richard Amari

Chaohong Cai

Tyler J Selstad

Manuj Dhingra

David Gelwan

Jason B Solomonides

David Kwoka

Anthony Van

Thomas A Bush

Victor M Pinedo

Andrew B Thompson

Michael H Levesque

Matthew G Van Eck

A system for controlling a plurality of hydraulic effectors operably connected to an engine to control engine parameters. The system also includes a plurality of sensors operably connected to measure a state or parameter of each effector, a pump configured to supply fluid to the plurality of effectors, and a controller operably connected to the plurality of sensors, the plurality of effectors, and the pump. The controller executes a method for an adaptive model-based control for controlling each effector, The method includes receiving a request indicative of a desired state for each effector, receiving a weighting associated each request, obtaining information about a current state of each effector, and updating an adaptive model based control (MBC) based upon the information. The method also includes generating a control command for an effector based upon the adaptive MBC and commanding the effector based upon the control command.

Model predictive control sub-system hydraulic flow management

A system is provided for speed control during motoring of a gas turbine engine of an aircraft. The system includes an air turbine starter, a starter air valve operable to deliver compressed air to the air turbine starter, and a controller. The controller is operable to adjust the starter air valve to control motoring of the gas turbine engine based on measured feedback with lead compensation to reject disturbances attributable to dual to single or single to dual engine starting transitions.

Speed control during motoring of a gas turbine engine

An aircraft system is provided that includes a fuel reservoir, a turbine engine and a fuel-to-fuel heat exchanger. The heat exchanger is fluidly coupled between the fuel reservoir and the turbine engine.

Aircraft system with fuel-to-fuel heat exchanger

A load power sharing control system for a twin-engine rotorcraft having a first gas turbine engine and a second gas turbine engine is provided.

Twin-engine rotorcrafts and load power sharing control systems thereof and methods for load power sharing control

A hydromechanical control system for a variable delivery, positive displacement fuel pump includes a variable area orifice metering window through which fuel from the pump outlet passes on its way to a gas turbine aircraft engine. The fuel pressures on either side of the fuel metering window are ported to corresponding sides of a spool of a pump control valve. The position of the valve spool controls the fuel flow to either side of a pump control actuator, whose movement varies the displacement of the pump. A bypass fuel flow upstream of the fuel metering valve is also ported to the pump control valve. During steady-state pump operation, a relatively small and constant value of fuel flow is bypassed through the pump control valve and back to the pump inlet. However, upon increasing or decreasing pump speed transients, the bypass fuel flow is increased or decreased in a proportional amount. In this way, improved control of the pump during transient conditions is achieved.

Hydromechanical control for a variable delivery, positive displacement

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Southampton, MA, United States of America

Timothy J Gaudet