Hamilton Sundstrand Corporation

David S Behling

Glenn C Lemmers, Jr

Andrew P Grosskopf

Todd A Spierling

Aaron M Finke

Doren Smith

Timothy R Welch

Craig R LeGros

Aaron Cooling

Douglas J Turner

Erika M Danckers

Leroy R Rateike

Jonathan C Dell

Jan Henry Abels

Jean Thomassin

Dhaval S Patel

Ted A Martin

Charles E Reuter

Gregory Alan Rittmeyer

Mark J Franklin

Eric A Brust

Brady A Manogue

Mark F Franzen

Joseph Paul Krause

Joshua J Krecklow

Magdy A Kandil

Luke Wagner

Steven C Paul

Eric Alan Larson

Paul Michael Reinhard

Gregory E Horihan

Mark J Seger

Liangheng Qiu

Brandon M Grell

Timothy R Pieper

Alan Kasner

Alexander David White

Nathan D Kohnle

Abiodun Okoya

Andrew D Smith

Charles R Reuter

Paul K Seiler

Doren C Smith

Glenn C Lemmers Jr

Alexander White

Jr Glenn C Lemmers

Glen C Lemmers

A shaft system includes an outer shaft including an inner surface defining a conduit and an inner shaft extending within the conduit. The inner shaft includes a radially extending passage having a first end and a second end. A centrifugal force activated damper extends between the outer shaft and the inner shaft. The centrifugal force activated damper includes a first member arranged between the inner shaft and the inner surface at the first end of the radially extending passage, a second member arranged between the inner shaft and the inner surface at the second end of the radially extending passage, and a connecting member extending through the radially extending passage. Rotation of the shaft system causes the first member and the connecting member to shift away from the second member into the inner surface of the outer shaft.

Centrifugal force actuated damper

Aircraft engines include an engine housing, a core assembly arranged within the engine housing and comprising an engine shaft arranged axially within the engine housing extending in a forward-aftward direction, and a tail cone assembly attached to an aft end of the engine housing. The tail cone assembly includes a tail cone housing and an aircraft machine arranged within the tail cone housing the aircraft machine comprising a rotor shaft. An input shaft is configured between the engine shaft and the rotor shaft and a rotor coupling configured to sealing connect the rotor shaft and the input shaft, the rotor coupling configured to providing sealing engagement between the rotor shaft and the input shaft during at least one of relative axial displacement and relative radial displacement between the rotor shaft and the input shaft.

Aircraft tail cone mounted generators

A sealing assembly of an input shaft includes a support structure, a bearing assembly, and an input seal. The input seal including an input seal housing having a first portion and a second portion. The first portion is arranged adjacent the bearing assembly. At least one face plate anti-rotation pin is coupled to the input seal housing and positioned adjacent the input shaft. A face plate is positioned adjacent the second portion. The face plate is configured to directly contact the input shaft.

Disconnect bearing and input seal for a variable frequency starter generator

An aircraft hydraulic control system includes a pump system, a fluid circuit, and a controller. The pump system includes a hydraulic pump and a ram air turbine assembly. The fluid circuit delivers hydraulic fluid to the hydraulic pump and receives the hydraulic fluid output from the hydraulic pump. The controller is in signal communication with the hydraulic pump. The controller determines a rotational frequency of a ram air turbine included in the ram air turbine assembly, and controls the hydraulic pump so as to control the flow of hydraulic fluid in the fluid circuit. The flow of hydraulic fluid in the fluid circuit controls a fluid pressure of the aircraft.

Electronic controller with off-load and anti-stall capability for Ram air turbine variable displacement hydraulic pump

An aircraft power system includes an auxiliary power unit (APU), a transmission unit, and a generator. The APU is configured to output a first APU rotational power in response to determining a first condition and a second APU rotational power in response to a determining a second condition. The transmission unit is configured to receive the first APU rotational output power from the APU. The transmission unit outputs a transmission rotational power based on the first APU rotational output power and outputs the transmission rotational power based on the second APU rotational output power. The generator receives the transmission rotational power and produces an alternating current (AC) voltage having a target frequency based on the transmission rotational power.

Multi-speed transmission to control variable APU speed and constant generator output frequency

A seal includes a carbon seal that is disposed about an axis and extends between a first axial end and a second axial end. The second axial end includes a seal surface and a radially outer edge of the seal surface is axially spaced from a radially inner edge of the seal surface along the axis.

Carbon seal

A torsion shaft assembly includes a torque carrying shaft including a driven end configured for receiving torque input to the torque carrying shaft and a driving end configured for outputting torque output from the toque carrying shaft. The torque carrying shaft includes an axial facing damping interface surface axially between the driven end and the driving end. A friction tube is disposed outboard of the torque carrying shaft. The friction tube is connected at a first axial location to be driven by the torque carrying shaft. The friction tube includes an axial facing damping interface surface that abuts the axial facing damping interface surface of the torque carrying shaft, forming a damping interface to provide frictional dampening against angular vibrations occurring as differential angular displacement between the driven end and the driving end of the torque carrying shaft.

Friction tubes

An aircraft power system includes an auxiliary power unit (APU), a generator, and a constant speed drive (CSD). The APU drives an APU drive shaft at a first rotational speed during a first condition and a second rotational speed during a second condition. The generator is rotatably coupled to a generator shaft and produces an AC voltage having a target frequency in response to rotation of the generator shaft at a target rotational speed. The CSD unit receives the first rotational speed from the APU drive shaft and rotates the generator shaft at the target rotational speed based on the first rotational speed. The CSD further receives the second rotational speed from the APU drive shaft and rotates the generator shaft at the target rotational speed based on the second rotational speed.

Constant speed drive to control variable APU speed and constant generator output frequency

A generator including a stator winding, a rotor positioned radially inside the stator winding, including multiple coil assemblies each using a flat wire, a primary termination plate residing radially inside the rotor configured to connect a wire of a coil assembly to an adjacent wound coil and a secondary termination plate residing radially inside the rotor configured to connect a wound coil to an adjacent wound coil and connect the wound coil to a terminus connection.

Generator rotor flat wire winding

A hybrid drive system can include a shaft, an electrical machine comprising a rotor and a stator, and a mechanical disconnect system connecting the rotor to the shaft. The mechanical disconnect system is configured to mechanically connect the rotor to the shaft in a first state and to mechanically disconnect the rotor from the shaft in a second state such that rotor does not drive the shaft or such that the rotor is not driven by the shaft. The rotor can be a permanent magnet rotor, for example.

Electrical machine disconnection systems

An integrated turbo-compressor includes a compressor with a compressor outlet, a turbine with a turbine inlet, the turbine operatively connected to the compressor by an interconnect shaft, and a compounding drive. The compounding drive is connected to the turbine and has a variable gear ratio and an output member, the variable gear ratio coupling the turbine to the output member to compound output of an internal combustion engine using energy recovered from an exhaust flow received from the internal combustion engine and in excess of energy required to compress combustion air provided to the internal combustion engine. Internal combustion engines, aircraft, and methods of compounding output of internal combustion engines are also described.

Integrated turbo-compressor with variable gear ratio transmission for internal combustion engine

A system for relieving pressure from within a generator casing can include a generator shaft defining a shaft channel therein and at least one rotating valve disposed within the shaft channel of the generator shaft and in fluid communication with an interior of the generator casing and the atmosphere. The rotating valve is configured to allow fluid within the generator casing to flow through the generator shaft to the atmosphere in an open state and while rotating. The rotating valve is configured to prevent fluid within the generator casing from flowing in a closed state.

Pressure relief systems for generators

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Belvidere, IL, United States of America

David S Behling