Hamilton Sundstrand Corporation

United Technologies Corporation

Pratt-Whitney Canada Corp

Robert H Perkinson

Frederick M Schwarz

Richard Andrew Himmelmann

David R Danielson

David V Arel

Paul A Carvalho

Richard Ullyott

Charles F Stearns

Chad M Henze

Charles E Reuter

Gerald P Dyer

Stephen Edward Tongue

Peter J Dowd

Brian G Donnelly

Matthew C Soule

Jesse Walter Smith

Carl S Dudash

Eric J Talasco

Mark Raes

Gerald J Gorneault

Charles DeGeorge

Rene F Belanger

Herbert J Holl

Richard A Himmelman

There is described a method and system for in-flight start of an engine. The method comprises rotating a propeller; generating electrical power at an electric generator embedded inside a propeller hub from rotation of the propeller; transmitting the electrical power from the electric generator to an engine starter mounted on a core of the engine via an electric power link; and driving the engine with the engine starter to a sufficient speed while providing fuel to a combustor to light the engine to achieve self-sustaining operation of the engine.

In flight restart system and method for free turbine engine

An aircraft control system includes a propeller shaft assembly. Also included is first rotor operatively coupled to the propeller shaft assembly, the first rotor having a first plurality of blades mounted thereto, the first blades disposed at a substantially identical nominal pitch during rotation of the first rotor, the first rotor rotatable in a first direction. Further included is a second rotor operatively coupled to the propeller shaft assembly and rotatable in a second direction, the second rotor having a second plurality of blades mounted thereto, wherein a pitch of the second blades cyclically changes during rotation of the second rotor, the first rotor and the second rotor disposed and rotated proximate a fixed wing of an aircraft about a common axis extending parallel to a longitudinal axis of the aircraft, cyclically changing the pitch of the second plurality of blades generating a moment for controlling the aircraft.

Aircraft control system and method

A propeller assembly is provided including a plurality of blades arranged in diametrically opposed pairs. Each of the plurality of blades has an electrical deicer located thereon. The propeller assembly also includes a slip ring, and a stationary brush arranged in contact with the slip ring. The brush is configured to transfer electrical power from a power source to the slip ring. A movable portion of an actuator is configured to sequentially couple the electrical deicers of each pair of blades to the rotating slip ring.

Brush design for propeller deicing system

A power generation unit for generating electric power within a rotating reference frame includes a generator and a gear assembly. The generator has a plurality of first generator parts disposed concentrically with and radially outward from a plurality of second generator parts. The gear assembly is rotatably attached to the second generator parts and configured to allow relative rotation between the first and second generator parts caused by a single rotating component. The generator and the gear assembly are axially disposed along a common rotational axis.

Propeller in-hub power generation and control

A method of controlling a Counter-Rotating Open-Rotor (CROR) includes mechanically linking a pitch change system of a first rotor with a pitch change system of a second rotor and commanding a Blade Angle (Beta1 commanded) of the first rotor such that a Blade Angle (Beta2 Actual) of the second rotor is a function of the commanded Blade Angle (Beta1 commanded) to provide a linear relationship between an actual Blade angle (Beta1 Actual) and Beta1 commanded of the first rotor and a non-linear relationship between Beta2 Actual and Beta1 commanded.

Counter-rotating open-rotor (CROR)

A wind turbine blade assembly comprises a rotatable hub, a blade secured to the hub, and a pitch system. The pitch system is disposed to rotate the blade with respect to the hub about a pitch axis not extending through an aerodynamic centroid of the blade. The pitch system comprises a hydraulic cylinder pitch actuator and a relief valve. The hydraulic cylinder pitch actuator has first and second pressure chambers. The relief valve is configured to aerodynamically unload the blade by equilibrating the first and second pressure chambers in response to a pressure differential between the first and second pressure chambers exceeding a critical threshold corresponding to a pre-strain blade twist.

Wind turbine load mitigation

An aircraft control system includes a co-axial, counter-rotating propeller shaft assembly. Also included is a first rotor operatively coupled to the propeller shaft assembly, the first rotor having a first plurality of blades mounted thereto, wherein the first plurality of blades are disposed at a substantially identical nominal pitch during rotation of the first rotor. Further included is a second rotor operatively coupled to the propeller shaft assembly, the second rotor having a second plurality of blades mounted thereto, wherein a pitch of the second plurality of blades is configured to cyclically change during rotation of the second rotor.

A propeller balancing device includes at least one stationary outer disc and a drive wheel arranged adjacent to the outer disc. The drive wheel includes magnets arranged at the periphery. A balancing weight is arranged in a groove formed in one of the outer disc or the drive wheel. A propeller including the propeller balancing device and a method of balancing a propeller are also disclosed.

Simplified propeller balancing system and method

A pitchlock system includes a ballscrew screw mounted along an axis of rotation of an actuator, the ballscrew screw has an internal ballscrew bore; a pitchlock nut mounted about the ballscrew screw, the pitchlock nut including an internal pitchlock nut thread; a ballscrew ballnut mounted about the ballscrew screw and axially adjacent the pitchlock nut; a pitchlock actuation rod mounted axially within the internal ballscrew bore, the pitchlock actuation rod having an internal pitchlock actuation bore and a ball bearing aperture for receiving multiple ball bearings; a pitchlock retainer pin mounted axially within the internal pitchlock actuation bore; and a belleville spring which biases the ballscrew screw towards an axially fixed surface of the actuator in a pitchlock position, the ballscrew screw being movable between an operational position and the pitchlock position.

Propeller pitchlock system with a rotating interface

A method of controlling a Counter-Rotating Open-Rotor (CROR) includes measuring a speed of a first rotor and deriving a speed of a second rotor and controlling a pitch of the first rotor and the second rotor.

A variable output pump includes a fluid input, a control stage pump having an input portion and an output portion, a main stage pump having an input portion and an output portion, and a differential linkage in mechanical communication with the control stage pump and the main stage pump. The input portion of the control stage pump is in fluid communication with the fluid input and the input portion of the main stage pump is in fluid communication with the fluid input and the output portion of the control stage pump.

Variable output pump

A retractable contact assembly includes an outer casing having a first opening and a piston located in the first opening of the outer casing and moveable axially within the opening. The piston has a second opening. The assembly further includes an inelastic force generating device configured to control an axial movement of the piston and a contact located in the second opening of the piston and movable axially in the second opening of the piston. The assembly further includes an elastic force biasing device configured to provide an elastic force to the contact in an axial direction outward from the second opening.

Retractable contact assembly

A blade assembly includes a blade body and at least one sheath assembly located at a leading edge of the blade assembly. The at least one sheath assembly is retained to the blade body in a chordwise direction via an interlocking arrangement between the at least one sheath assembly and the blade body. A tip cap is located at a tip portion of the blade and secured to the blade body thus securing the at least one sheath assembly to the blade body in a spanwise direction. A method of assembling an airfoil includes securing at least one sheath assembly to a leading edge of a blade body via an interlocking arrangement between the at least one sheath assembly and the blade body, and assembling a tip cap to the blade body, thereby retaining the at least one sheath assembly to the blade body in a spanwise direction.

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Somers, CT, United States of America

Robert H Perkinson