Honeywell International Inc.

Honeywell G.m.b.h.

Steven Alan Lewis

Paul W Futa, Jr

Gary David Havey

Gary Valencourt

Sammuel Tillich

Paul Futa

Christopher Douglas Eick

George Wieger

Michael Albert McPherson

Donald Striker

Michael J Spier

Larry A Portolese

Timothy D Mahoney

David Lawrence

Yathiraj Kasal

Gregory A Lafferty

James C Williams

Gregory Kline

Elliot Conrad

David J Hauck

James F Toth

John C Van Oosterum

Anthony M Gibbs

Gary A Valencourt

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 propeller oil control system for a turboprop engine of an aircraft includes an engine control unit and a propeller oil controller. The engine control unit is operable to determine a flight phase of the aircraft and is configured to supply control commands. The propeller oil controller is coupled to receive a supply of oil and to discharge the oil at a discharge oil pressure. The propeller oil controller includes an electrohydraulic servo valve that receives the control commands moves to a plurality of positions between a first position and a mid-position, and a plurality of positions between the mid-position and a second position. The engine control unit only commands the electrohydraulic servo valve to move out of the first position when the engine control unit determines the aircraft is conducting a take-off roll or the aircraft is in flight.

Propeller oil control system for aircraft turboprop engines

A propeller pitch control system for a turboprop engine of an aircraft includes an engine control unit and a pitch control unit. The engine control unit is operable to determine a phase of flight of the aircraft and is configured to supply control commands. The pitch control unit is coupled to receive the control commands from the engine control unit and includes a housing, a beta piston, a position sensor, a beta tube, and an electrohydraulic valve. The engine control unit only commands the electrohydraulic valve to move the beta piston from the fully retracted position when the engine control unit determines the aircraft is conducting pre-takeoff roll taxiing operations or is conducting post landing touchdown operations.

Propeller pitch control system for aircraft turboprop engines

Additively-manufactured flow restrictors are provided, as are methods for producing additively-manufactured flow restrictors. In various embodiments, the additively-manufactured flow restrictor includes a flowbody through which a flow path extends, a restricted orifice located in the flowbody and providing a predetermined resistance to fluid flowing along the flow path in a first flow direction, and a first internal perforated screen positioned in the flow path upstream of the restricted orifice taken in the first flow direction. The flowbody and the first internal perforated screen integrally formed as a single additively-manufactured piece utilizing, for example, Direct Metal Laser Sintering (DMLS) or another additive manufacturing process. In certain embodiments, the first internal perforated screen may include an endwall and a peripheral sidewall, which is integrally formed with the endwall and spaced from an inner circumferential surface of the flowbody by an annular clearance.

Additively-manufactured flow restrictors and methods for the fabrication thereof

Flow restrictor assemblies including a monolithic flow restrictor and methods for manufacturing the same are provided. The monolithic flow restrictor is configured for disposing in a fluid passage of a housing body. The monolithic flow restrictor comprises a first end and a second end, a first screen at the first end and a second screen at the second end, and a series of cross-sectional portions between the first screen and the second screen. Each cross-sectional portion has a plurality of slots formed in a radially outer surface thereof for connecting a series of restricting orifices formed in the monolithic flow restrictor for tortuously conducting a fluid through the series of cross-sectional portions.

Flow restrictor assemblies including a monolithic flow restrictor and methods for manufacturing the same

A pumping apparatus includes a gear pump in fluid communication with a boost pump. The gear pump includes a pump housing, a first gear, and a second gear. The first and second gear have gear teeth and trunnions on opposite sides thereof, and are disposed in the pump housing. The gear teeth of the first and second gear are meshed in a mesh region. An inlet cavity is defined adjacent to the first and second gear, on one side of the mesh region. A pump outlet is defined on an opposite side of the mesh region from the inlet cavity. A bearing is configured to support at least one trunnion of the first gear and/or the second gear. A bearing interface is defined between the bearing and the at least one trunnion. A flow path is defined between the bearing interface and the inlet cavity.

Gear pump, pumping apparatus including the same, and aircraft fuel system including gear pump

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 seal assembly is provided for sealing a gap with a high pressure side and a low pressure side between a first component and a second component. The seal assembly can include a primary seal configured to be arranged on the first component and spanning the gap on the high pressure side between the first and second component; and a backup ring configured to be arranged on the first component adjacent the primary seal on the low pressure side. The backup ring includes an inner diameter and a scarf cut slit at an angle that is a function of the inner diameter of the backup ring.

Scarf cut backup rings

A thermal recirculation throttle valve () for an aircraft fuel system includes a housing () having a throttling valve chamber; a cover () operatively engaging a first side of the housing (); a power piston () within a power piston sleeve (), the power piston () having a first () and second face () for control pressure to act upon, the power piston () and power piston sleeve () operatively engaged with the housing () within the throttling valve chamber; a Linear Variable Differential Transformer () for measuring a linear position of the power piston () within the housing (); a throttling valve () within a throttling valve sleeve (), the throttling valve () operatively engaged with the power piston () to transfer the linear movement of the piston () between a fully extended and a fully retracted operating position; and a flow deflector () engaged with the throttling valve () for protecting the housing () from flow erosion from fuel exiting flow windows (). The throttling valve () includes a pair of fail-safe operating positions, a fully open operating position, a low leakage shutoff operating position, and a variety of variable flow operating positions between the shutoff and fully open operating positions.

Four mode thermal recirculation throttle valve

A fuel system for a gas turbine engine having at least one augmentor zone which fuel system includes a fuel pump () drawing fuel from a fuel tank () and pumping the fuel in a downstream direction, at least one fuel line () connecting the fuel pump () to the at least one augmentor zone, at least one augmentor metering valve () in the at least one augmentor fuel line () for metering fuel to the at least one augmentor zone, and a fuel return path () returning fuel from a point in the fuel line () downstream of the fuel pump () to the fuel tank (), wherein the point is downstream of the at least one augmentor metering valve (). A selector valve () is provided to allow thermal recirculation of fuel using an augmentor metering valve. Also a method of controlling fuel recirculation in a gas turbine engine.

Augmentor flow control with thermal recirculation function using augmentor valves

A fuel distributor () and mounting arrangement that helps support the weight of the fuel distributor () during removal and replacement for improved maintainability. The mounting arrangement includes a hanger () mountable on a first support which hanger () includes a slot (), and a manifold () separate from the hanger () that has a first side () with a plurality of ports () arranged in a first configuration. The manifold () is connectable to a plurality of fluid lines on an engine (). A fuel distributor body () has a first surface, a second surface spaced from the first surface and a third surface between the first surface and the second surface with a hanging cleat () projecting from the first surface that is configured to be received within the slot (). The third surface has a main fuel inlet () and a plurality of additional fluid ports () arranged in the same configuration as the ports on the manifold (). A mounting pin () projects from the third surface. Also a method of mounting a fuel distributor.

Fuel distributor and mounting system therefor and method of mounting a fuel distributor

A method and system for controlling fuel flow in a fuel metering system that includes a metering valve and a proportional bypass valve that produces a differential pressure error across the metering valve includes supplying a first fraction of fuel through the metering valve. A second fraction of the fuel is directed through the proportional bypass valve. The differential pressure error produced by the bypass valve is determined, and fuel flow through the supply line is controlled by adjusting the metering valve based at least in part on the determined differential pressure error, and by adjusting the proportional bypass valve to maintain a substantially constant metering valve differential pressure across the metering valve.

Fuel metering system proportional bypass valve error compensation system and method

A high pressure valve assembly () comprising a valve sleeve () and a valve body () slidably mounted in the valve sleeve () is disclosed, the valve body () and valve sleeve () each having first ends () and second ends (). A sidewall () extends between the valve sleeve first end () and second end () which sidewall () has an inner surface () and an outer surface () and at least one opening () therethrough. The sidewall () also includes at least one channel () having a first end () facing the inner surface () at a first location closer to the first valve sleeve end () than to the second valve sleeve end () and a second end () facing the inner surface () at a second location closer to the second valve sleeve end () than to the first valve sleeve end (). A method of using the valve assembly () is also disclosed.

High accuracy low leakage valve for high pressure applications

A controlled piston () having a first end () mounted in a controlled piston sleeve () and a spool () movably mounted in a spool sleeve (), a first fluid passage () from the spool () to the controlled piston first end (), the position of the spool () affecting a position of the controlled piston (), an FFV () in an FFV sleeve () in the first fluid passage () having a first end section (), a second end section () and a central section () having a third diameter less than the diameters of the first and second sections, the FFV () being shiftable between a first position blocking the first fluid passage () and a second position allowing fluid flow past the central section () to the controlled piston (), and a second fluid passage () from the spool () to the FFV first end section (). Shifting the spool () to a failsafe position shifts the FFV () to the first position to fix the controlled piston () in place.

System for positioning a piston including a fail fixed valve for holding the piston in position during a power interruption and method of using same

The present invention is a portable electronic video display. The display is configured to be worn on the arm or wrist of a user, or stored in a pocket or backpack. The display is raised to eye level and the user looks through an eyepiece to view the video display. Control buttons are located on the display for generating point and click type commands. The display is meant to be used remotely from a computer. The computer would be worn or carried by the person or simply be free standing, some distance away. The computer is configured to convert video signal into a serial data stream and then transmit that stream via an RF signal. The display then receives that signal and converts it back into a video signal, displaying it on a miniature electronic video display. That image is then magnified through various optics to present a final image to the user. The point and click commands are separately transmitted back to the computer, where they are received and acted upon.

Growing community of inventors

South Bend, IN, United States of America

Steven Alan Lewis