Hamilton Sundstrand Corporation

Magdy A Kandil

David Everett Russ

Glenn C Lemmers, Jr

Andrew P Grosskopf

David S Behling

Doren Smith

Gary Sasscer

Laurence D Vanek

Stephen George Mican

David L Jacques

Keith R Magnus

James L Abbot

Don Baker

A ram air turbine (RAT) stowing system includes a closed loop hydraulic circuit configured to hold a quantity of a hydraulic fluid to be utilized only by the RAT stowing system and a RAT actuator disposed in fluid communication with the closed loop hydraulic circuit. A pump system is connected to the hydraulic circuit to selectively pump the hydraulic fluid to a stow reservoir portion of the RAT actuator to move the RAT actuator from a deployed position to a stowed position. A control valve is connected to the hydraulic circuit between the RAT actuator and the pump to selectively allow the hydraulic fluid to be drained from the stow reservoir portion of the RAT actuator in a drain state and to allow the hydraulic fluid to be pumped into the stow reservoir portion of the RAT actuator in a pump state.

Ram air turbine stowing system

A ram air turbine with a turbine assembly and a power train, the turbine assembly only coupling to the entire power train upon reaching a desired rotational speed of the turbine assembly, the ram air turbine having a clutch mechanism, the engagement of which couples the turbine assembly to at least a portion of the power train, and a speed control mechanism that engages the clutch mechanism only when the turbine assembly attains at least the desired rotational speed.

Ram air turbine with a speed engaged clutch

A hydraulic system for a ram air turbine includes a hydraulic pump having a high pressure fluid outlet port, a housing, a pivot post arranged to pass through the housing and defining a mechanical pivot relative to the housing about an axis, a transfer tube positioned between the high pressure fluid outlet port of the hydraulic pump and a port in the housing for the high pressure fluid outlet path, and seal elements positioned at or near opposite ends of the transfer tube. A fluid inlet path and a high pressure fluid outlet path pass through the housing and the pivot post. The transfer tube has a crowned end.

Fluid transfer tube for severe misalignment applications

A hydraulic differential with a variable displacement hydraulic unit of the axial piston type, a fixed displacement hydraulic unit of the axial piston type, a stationary housing for mounting the hydraulic units, an input shaft for coupling to a variable speed power source and an output shaft for coupling to a constant speed load, comprises: a wobbler and a port plate for the variable displacement hydraulic unit coupled to the stationary housing; an axial block and piston set for the variable displacement hydraulic unit, a port plate for the fixed displacement hydraulic unit and a wobbler for the fixed displacement hydraulic unit coupled to the input shaft; and an axial block and piston set for the fixed displacement hydraulic unit coupled to the output shaft; wherein the variable displacement hydraulic unit port plate and the fixed displacement hydraulic unit port plate couple together through a circumferential interface to minimise hydraulic thrust forces developed by the hydraulic unit.

Hydraulic differential for integrated drive generator

A starter-generator for an aircraft engine comprises a variable dynamoelectric machine alternatively operable as a motor or as a generator, having a rotor. A support motor is coupled to the variable dynamoelectric machine to assist the machine. A torque converter selectively couples and decouples the rotor to the engine, coupling the rotor to the engine at some point when the dynamoelectric machine is operated as a motor. The engine may be started by the dynamoelectric machine when operated as a motor through a first power train including the torque converter and may drive the dynamoelectric machine as a generator through a second power train.

Aircraft starter generator for variable frequency (vf) electrical system

A starter-generator for an aircraft engine comprises a dynamoelectric machine alternatively operable as a motor or as a generator, having a rotor. A support motor is coupled to the dynamoelectric machine to assist the machine. A torque converter selectively couples and decouples the rotor to the engine, coupling the rotor to the engine at some point when dynamoelectric machine is operated as a motor. A constant speed transmission has an input adapted to be connected to the engine and an output to be connected to the rotor. The unit provides a desired speed relation between input and output. The engine may be started by the dynamoelectric machine when operated as a motor through a first power train including the torque converter and may drive the dynamoelectric machine as a generator through a second power train including the constant speed transmission.

Integrated starter generator drive having selective torque converter and constant speed transmission for aircraft having a constant frequency electrical system

Growing community of inventors

Rockford, IL, United States of America

Magdy A Kandil