Alliedsignal Inc.

Honeywell International Inc.

Christopher Douglas Eick

John R Williamson

Paul W Futa, Jr

Michael Albert McPherson

Donald Striker

Steven Alan Lewis

Sammuel Tillich

Jay N Hoopes

Paul J Powers

Timothy D Mahoney

David Tuttle

Steven F Fisher

Gary Valencourt

David D Jones

William Lorenz

Jonathan Seeley

Kevin Baker

Hannah Amor

Kenneth P Worcester

Paul W Futa Jr

Gary A Valencourt

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

A propeller pitch control system for a turboprop engine of an aircraft includes a negative torque sensor, a full feather control valve assembly, and a feather valve assembly. The feather valve assembly is responsive to fluid pressures from the negative torque sensor and the control valve assembly to move between a plurality of positions. An engine control unit or a manual user interface can also be used to control the position of the feather.

Aircraft turboprop engine propeller pitch control system including a controllable feather valve

A fuel system () for a gas turbine engine () having a shaft () and requiring fuel to be supplied at a first rate for engine start up, the fuel system () including: a main fuel pump () for providing fuel to the gas turbine engine (), the main fuel pump () having an output varying with shaft speed, the output being at a windmilling rate when the engine () is windmilling, the windmilling rate being less than the first rate; and an auxiliary fuel pump () for providing fuel to the gas turbine engine () and having an auxiliary output rate greater than or equal to the difference between the first rate and the windmilling rate. A method of operating such a fuel system () is also disclosed.

Reduced-weight fuel system for gas turbine engine, gas turbine engine having a reduced-weight fuel system, and method of providing fuel to a gas turbine engine using a reduced-weight fuel system

A fuel control system for a gas turbine engine is disclosed that includes a flow path carrying fuel from a fuel source to a combustion chamber, an ecology valvefor removing a quantity of fuel from the flow path, the ecology valvebeing shiftable in a first direction from a first position to a second position and in a second direction from said second position to said first position and a fuel lineconnected between the flow path and the ecology valvefor moving fuel between the flow path and the ecology valveto bias the ecology valvetoward the second position, where the fuel lineis configured, such as by the inclusion of an orificed check valve 150 therein, to allow fuel to move therethrough away from the ecology valveat a greater rate than toward the ecology valve

Fuel delivery system having an ecology valve

A control for a hydraulic propeller pitch actuator includes a low power pilot valve responsive to digital electronic input signals to control movement of a hydraulic servomotor driving a higher power servovalve. Negative feedback motion is delivered from the servomotor to both the pilot valve and the servovalve.

Full authority propeller pitch control

A large flow of high pressure fuel is supplied to a gas turbine engine by mounting a small modified vortex pump over or around a main high speed shaft. The pump includes a plurality of short, stubby impeller blades rotating at a very high speed within a fuel filled annular chamber having an axial fuel inlet and a tangential fuel outlet. A pump booster and priming system ensures the pump fills with fuel during operation.

Over the shaft fuel pumping system

A metering valve (10) having a bi-directional motor (11) with a linearly-displaceable output shaft (21) in which the shaft (21) is separated from but cooperates with a bi-directionally movable piston (16) to provide a variable flow aperture (102) in a secondary flow path (12,52,74,78,76,102,100,48) extending axially through the piston (16). Flow along a primary flow path (12,18,48,14) is varied by movement of the piston (16) in response to an imbalance of opposing hydraulic forces. The imbalance in forces results from varying the foresaid flow aperture (102) by displacing the output shaft (21). However, the flow aperture (102) is only transitorily varied by displacement of the shaft (21) since the valve (10) is designed to provide a follow-up servo function by which the piston (16) is kept at a substantially constant distance from the shaft (21).

Metering valve with follow-up servo

A high speed liquid vortex pump is fitted with an electrically controlled needle valve assembly which modulates the pressure of a small portion of the working fluid which in turn moves a spool valve to regulate the high volume, high pressure pump output flow.

Low cost fuel supply system for gas turbine engines

A high speed liquid vortex pump is fitted with a flexible tube in the discharge throat. The flow area of the flexible tube, and thus the pump output flow rate, is varied by surrounding the tube with a pressure modulated stream of the working fluid.

Growing community of inventors

Phoenix, AZ, United States of America

Christopher Douglas Eick