Honeywell International Inc.

Paul Futa

Larry A Portolese

David Tuttle

David Lawrence

Edward J Zielinski

Steven Alan Lewis

Matthew Arend

Brad McRoberts

Gregory Kline

Greg Lafferty

William Scott Rowan

Eric Mitchell Arnett

Gary Valencourt

Michael Albert McPherson

Charles Walejewski

Don Striker

Calin Bondariu

Elmer Greenbank

Eric Hechtl

Brad Mcroberts

An electrohydraulic poppet valve device control system includes a main body, an extend poppet valve, a retract valve body, a retract poppet valve, and an actuator. The actuator is movable to an extend position, a retract position, and a null position, and moves to, or remains in, the null position when electrical power is not supplied to the actuator. In the extend position, the extend poppet valve is in its open position and the retract poppet valve is in its closed position. In the retract position, the extend poppet valve is in its closed position and the retract poppet valve is in its open position. In the null position, the extend poppet valve is in its closed position and the retract poppet valve is in its closed position.

Electrohydraulic poppet valve device control that maintains the last commanded position of a device upon power interruption and provides back-up position control

A fuel system for a gas turbine engine includes a secondary flow lockout valve. The secondary flow lockout valve includes a valve body having a first end that defines an inlet and a second end. The valve body includes at least one primary outlet bore and at least one secondary outlet bore. The valve body defines a channel in fluid communication with the primary outlet bore. The secondary flow lockout valve includes a cover that cooperates with the second end of the valve body to define a chamber. The chamber is in fluid communication with the channel such that the valve body is movable between at least a first position in which the primary outlet bore is open and a second position in which both the primary outlet bore and the secondary outlet bore are open based on a pressure in the chamber.

Secondary flow lockout valve

A system uses a two-stage electrohydraulic servo valve that includes an additional control port that commands a fail-fixed valve to lock the position of a device in the last commanded position. The additional port is modulated by an existing land on the EHSV valve element, adding little to no complexity. Major technical benefits of the disclosed system are that it adds little to no cost, complexity, size, or weight the device being controlled. The disclosed configuration allows for the use of a relatively small and simple fail-fixed valve, and the control ports on the controlled device keep 'drift' to a minimum, when transitioning between normal operating mode and fail-fixed operating mode.

System that maintains the last commanded position of device controlled by a two-stage, four-way electrohydraulic servo valve upon power interruption

Embodiments of a combined overspeed and fuel stream selector system are provided. In an embodiment, the assembly includes a conduit network, a Discharge Select Valve (DSV), and a shutoff valve. The DSV is fluidly coupled to a primary fuel inlet, a secondary fuel inlet, and a primary fuel outlet included in the conduit network. The shutoff valve is fluidly coupled between the primary fuel inlet and the primary fuel outlet. In a standard operation mode, the shutoff valve is maintained in an open position, while fuel received at the primary fuel inlet is directed through the shutoff valve, through the DSV, and to the primary fuel inlet. Conversely, in a backup operation mode, the shutoff valve is closed to block fuel flow from the primary fuel inlet to the primary fuel outlet, while the DSV directs fuel flow received at the secondary fuel inlet to the primary fuel outlet.

Combined overspeed and fuel stream selector systems

A gas turbine engine fuel delivery system includes a mechanically-driven fuel pump, an electrically-driven fuel pump, and an engine control. The mechanically-driven fuel pump is adapted to receive a drive torque from a gas turbine engine draw fuel into its fuel inlet and discharge the fuel from its fuel outlet. The electrically-driven fuel pump has a first fuel inlet/outlet that is in fluid communication with the mechanically-driven fuel pump fuel inlet, and also has a second fuel inlet/outlet. The engine control is responsive to an engine start signal to cause the electrically-driven fuel pump to be temporarily energized to pump fuel from the first fuel inlet/outlet to the second fuel inlet/outlet, and is responsive to an engine shutdown signal to cause the electrically-driven pump to be temporarily energized to pump fuel from the second fuel inlet/outlet to the first fuel inlet/outlet.

Gas turbine engine mechanical-electrical hybrid fuel delivery system

A two-position, two-stage servo valve includes a valve body, a valve element, a control pressure chamber, and a control element. The valve body has an inner surface that defines a valve element chamber that includes a first control chamber and a second control chamber. The first control chamber is larger than the second control chamber. The valve element has first and second ends and is disposed within the valve element chamber and is movable between a first valve position and a second valve position. The first end is larger than the second end and is disposed within the first control chamber, and the second end is disposed within the second control chamber. The control pressure chamber includes a control pressure port that is in continuous fluid communication with the first control chamber. The control element is movable between a first control position and a second control position.

Two-position, two-stage servo valve

A gas turbine engine fuel supply system includes a primary gear pump and a secondary gear pump. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition. The secondary gear pump is sized to make up the remainder of the flow at high demand conditions, and actively delivers fuel to the downstream fuel system only during those conditions. To supply discharge fuel pressures in excess of gear pump capability, a supercharger pump is disposed upstream of the primary and secondary gear pumps. The supercharger pump is preferably activated only during high demand conditions as an additional energy conservation measure.

High efficiency, high pressure gas turbine engine fuel supply system

A fuel supply system includes a fuel supply line, a fuel filter, a filter bypass line, a first differential pressure sensor, a second differential pressure sensor, and a filter bypass valve. The fuel filter is disposed in series in the fuel supply line to remove particulate from the fuel. The filter bypass line has a fuel inlet upstream of the fuel filter, and an outlet that is downstream of the fuel filter. The first differential pressure sensor continuously senses differential pressure across the fuel filter, and the second differential pressure sensor selectively senses differential pressure across the fuel filter. The filter bypass valve is movable between a first non-bypassing position and a second bypassing position and controls whether only the first differential pressure sensor or both the first and second differential pressure sensors sense the differential pressure across the fuel filter.

Aircraft fuel filter impending and actual bypass indication system

A gas turbine engine fuel supply system includes a primary gear pump, a secondary gear pump, and a pump bypass valve. The primary gear pump always actively delivers fuel to the downstream fuel system, and is sized to supply 100% of the burn flow needed at a select low demand condition. The secondary gear pump is sized to make up the remainder of the flow at high demand conditions, and actively delivers fuel to the downstream fuel system only during those conditions. To supply discharge fuel pressures in excess of gear pump capability, a supercharger pump is disposed upstream of the primary and secondary gear pumps. The pump bypass valve is configured to regulate fuel pressure at the primary gear pump outlet to one of a plurality of preset differential pressures above one of a plurality of fuel load pressures and prevents reverse pressurization of the gear pumps.

High pressure, multiple metering zone gas turbine engine fuel supply system

A flow divider valve for a gas turbine engine fuel supply system is provided. The flow divider valve is configured, whenever fuel pressure at its inlet port is between a first predetermined pressure and a second predetermined pressure, to supply the fuel to a start nozzle manifold outlet port at a substantially constant flow rate, and to direct any fuel flow in excess of the substantially constant flow rate to a run nozzle manifold outlet port.

Fuel flow divider and ecology system for a gas turbine engine fuel flow control system

A system provides 'fail fixed' functionality and allows a user to manually manipulate fuel flow to a gas turbine engine in the unlikely event the primary control means is unavailable. The fuel metering unit includes a fuel metering valve, a flow increase valve, and a flow decrease valve. The flow increase valve and flow decrease valves are both in fluid communication with the fuel metering valve and are each adapted to selectively receive fuel flow commands from a primary fuel flow command source and from a secondary fuel flow command source. The flow increase and decrease valves are responsive to the fuel flow commands to selectively control the position of the fuel metering valve.

Gas turbine engine fuel metering valve adapted to selectively receive fuel flow increase/decrease commands from the engine control and from the back-up fuel control

A gas turbine engine fuel control system is provided that includes a fuel metering valve and a thrust control valve. The fuel metering valve includes a metering valve inlet and a metering valve outlet. The metering valve inlet is adapted to receive a flow of fuel, and is configured to control the flow of fuel through the metering valve outlet. The thrust control valve is adapted to receive thrust control valve override signals and is configured, in response thereto, to move from a first position, in which flow from the metering valve is not impacted, and a second position, in which flow from the metering valve is blocked while flow through a fixed-area orifice is allowed.

Gas turbine engine fuel control thrust control override system

A fuel return valve and system includes a flow-level select and shut-off valve and a servo control valve. The flow-level select and shut-off valve includes a first fuel inlet, a second fuel inlet, a return-to-tank fuel outlet, and a valve element movable between a shut-off position, a mid-flow position, and a max-flow position. The servo control valve is coupled to the flow-level select and shut-off valve and is configured to control relative fluid pressures therein to selectively move the valve element to the shut-off position, the mid-flow position, and the max-flow position.

Gas turbine engine fuel return valve and system

A direct metering fuel supply system includes a fuel pump, a burn flow fuel line, a servo flow fuel line, and a servo regulator. The fuel pump is adapted receive pump commands representative of a commanded fuel flow rate and is configured, in response to the pump commands, to discharge fuel at the commanded fuel flow rate. The burn flow fuel line is in fluid communication with the pump to receive a first portion of the fuel discharged therefrom. The servo flow fuel line is in fluid communication with the pump to receive a second portion of the fuel discharged therefrom. The servo regulator is mounted on the servo flow fuel line and configured to maintain fuel flow rate in the servo flow fuel line at a substantially constant fuel flow rate regardless of fuel flow rate in the burn flow fuel line.

Direct metering fuel system with constant servo flow

A fuel divider system includes a housing assembly and a flow passage network having an inlet, a primary outlet, and a secondary outlet. A fuel divider piston is slidably disposed within the housing assembly and movable between a flow biasing position and a flow equalizing position. A control chamber is fluidly coupled to the flow passage network and fluidly communicates with the piston. An inlet chamber, at least partially defined by the piston and the housing assembly, is fluidly coupled to the inlet. At least one channel is provided through the piston and configured to cooperate with the flow passage network to port the FD control chamber to: (i) the fuel pressure at the secondary outlet when the FD piston is in the flow biasing position, and (ii) the fuel pressure within the inlet chamber when the FD piston is in the flow equalizing position.

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North Liberty, IN, United States of America

Paul Futa