Hamilton Sundstrand Corporation

United Technologies Corporation

Goodrich Corporation

Raytheon Technologies Corporation

Leo J Veilleux, Jr

Lubomir A Ribarov

James S Elder

Richard J Carpenter

Boris N Grigorov

Charles E Reuter

Gary M McBrien

Kevin D Gibbons

Tyler J Selstad

Paul Mackenzie Colson

Douglas A Parsons

Jay W Kokas

Peter Joseph Padykula

Thomas James Killen

Rudolph Thomas Beaupre

Charles H Falke

Ethan Flow

Jacek F Gieras

Mark R Gurvich

Francis P Marocchini

Ryan Prescott Susca

Murtuza Lokhandwalla

Naison E Mastrocola

Gerald P Dyer

Richard A Poisson

Todd Haugsjaahabink

William E Rhoden

Kyle Stephen Ives

August M Coretto

Bruce D Paradise

Peter L Jalbert

David M Kucharski

Sachin Ramprashad

Thomas O Harris

Erick Ramos

David T Anzulewicz

Kevin Gibbons

Carl F Mueller

Sushant S Bhadange

Mark C Neumann

Nicholas Moura

Gary M Mcbrien

Jr James Elder

A cooling system includes a fuel supply system and a cooling fuel path. The fuel supply system includes a boost stage pump and a main stage pump, while the cooling fuel path includes a fuel bleed from an outlet of the boost stage pump, a fuel return to an inlet of the boost stage pump, and a cooler disposed fluidly between the fuel bleed and the fuel return.

Method and system for cooling of engine mounted components

A system can include a first controllable valve configured to output a control pressure on one or more first pressure control lines, a second controllable valve configured to output a control pressure on one or more second pressure control lines, a transfer valve in fluid communication with the first controllable valve and the second controllable valve, and a hydraulic centering system operatively associated with and/or forming part of the transfer valve. The transfer valve can be configured to move between a first position, a second position, and a third position. The hydraulic centering system can be configured to maintain the transfer valve in the first position.

Valve systems

A fluid delivery system is provided including a reservoir including oil, a hydraulic pump in fluid communication with the reservoir, and a heat exchanger system. The heat exchanger system is in fluid communication with the hydraulic pump, a generator, and an engine gearbox. The hydraulic pump is configured to deliver the oil to the heat exchanger system. The heat exchanger system is configured to provide the oil according to first temperature criteria to the generator and provide the oil according to second temperature criteria to the engine gearbox.

Multi temperature generator and engine shared oil

An electricity generation and propulsion system of an aircraft is provided. The electricity generation and propulsion system includes a fuselage, a hybrid-electric power generation system operably disposed in the fuselage and a ram air turbine (RAT) device. The RAT device is coupled with the hybrid-electric power generation system and is stowable in the fuselage and deployable to an exterior of the fuselage. The RAT device is operable as a RAT when deployed into an airstream that drives rotations of the RAT from which the hybrid-electric power generation system generates electricity, and the RAT device is operable as a propulsor when deployed and driven by the hybrid-electric power generation system.

Stowable electric-hybrid propfan

In accordance with at least one aspect of this disclosure, a system (e.g., for aircraft systems) includes an actuator cylinder. The actuator cylinder comprises, a composite cylinder body, the composite cylinder body being axi-symmetric across at least a longitudinal axis. In embodiments, the composite cylinder body can include, a first plurality of plies laid in a first direction relative to the longitudinal axis and second plurality of plies laid in a second direction relative to the longitudinal axis different from the first direction to form a hollow chamber. The actuator cylinder can include a first metallic reinforcing ring and a second metallic reinforcing ring disposed at respective axial ends of the cylinder body configured to anchor the first plurality of plies and provide an axial reaction under axial stress and configured to provide load transfer from the cylinder body to one or more adjacent actuator components.

Composite actuator systems and methods of making the same

A valve includes a housing. A stroking valve is operatively connected to the housing for valve stroking movement relative to the housing in a direction of a longitudinal axis of the housing. The stroking valve has an open position for flow through the housing and a closed position for blocking flow through the housing. The stroking valve is configured to make sealing contact with a second face seal between the seal block and the stroking valve after a first portion of a stroke from the open position to the closed position prior to making sealing contact with a first face seal between the stroking valve and the housing.

Multi-surface sealing for two-position valves

A hybrid propulsion system can include a turbomachine having a compressor, a combustion chamber, and a compressor turbine. The compressor can be connected to the compressor turbine via a first shaft. The system can include a hybrid drive assembly which can include a power turbine in fluid communication with an outlet of the compressor turbine to be driven by compressor turbine exhaust to drive a second shaft that is disconnected from the first shaft. The hybrid drive assembly can also include an electrical machine mechanically coupled to the second shaft either to convert rotational energy to electrical energy or to convert electrical energy to rotational energy of the second shaft.

Hybrid propulsion systems

A pressure vessel includes a first container and a second container surrounding the first container and including a fluid port. The pressure vessel further includes a barrier space extending between the first container and the second container and a leak detection mechanism connected to the fluid port on the second container that is configured to detect a leak in the pressure vessel.

Pressure vessel with barrier layer

In at least one aspect of this disclosure, a shut off valve for an ecology fuel return system can include an inlet for receiving a fluid, an outlet for effusing the fluid, and a valve member configured to move between an open position such that the valve member allows fluid to effuse from the outlet and a closed position such that the valve member prevents fluid from effusing from the outlet. The valve member can include a pressure deflector configured to prevent fluid flow from biasing the valve member toward the closed position.

Shut off valves and components thereof for ecology fuel return systems

A valve having a first segment between a first outer wall and a first inner wall and has a first outer port near the first outer wall and a side port between the first inner and outer walls; a second segment between a second outer wall and a second inner wall and has a second outer port near the second outer wall; a center segment between the first and second inner walls, and a center port; and a piston within the valve, having: a first piston head in the first segment that slides to block and unblock the side port; a second piston head in the second segment that slides between the second inner and outer walls, the second piston head having a surface area that is the same as the first piston head; and a shaft connecting the first and second piston heads.

Minimum pressure valve for aircraft fuel system

A last chance screen for a fuel system includes a mesh that includes a first plurality of members extending in a first direction and a second plurality of members extending in a second direction and intersecting the first members. Openings are formed in the mesh between the first plurality of members and the second plurality of members. The first plurality of members and the second plurality of members have an airfoil shaped cross-section.

Last chance screen for aircraft fuel system

A multi-disk brake system comprises an electrical generator disposed therein. The electrical generator is configured to convert mechanical energy to electrical energy. The mechanical energy may be generated during a braking event of the multi-disk brake system. The electric generator may power various electrical components on the aircraft or store the electrical energy in a capacitor bank. The electric generator may also act as a motor and/or power a landing gear in a motor configuration.

Hybrid regeneration brake system

An air data system includes an air data probe and a surface acoustic wave (SAW) sensor attached to the air data probe for detecting particulate accumulation. The air data probe includes a probe head, a strut connected to the head, and a mounting plate connected to the strut. The probe head has an inlet, an interior surface extending from the inlet, and an exterior surface extending from the inlet.

Surface acoustic wave sensors for air data probes

A brake system may comprise a hydraulic brake system or a hybrid brake system. The hydraulic brake system may include an inner axle disposed in an inner axle housing. The inner axle housing may include a working fluid therein. The inner axle may comprise a plurality of paddles extending radially from the inner axle. The working fluid may be pressurized and/or create friction with the plurality of paddles. The pressurized working fluid may impede a free rotation of the plurality of paddles.

Hydraulic brake system

A heat exchanger includes a fin body and a heat pipe having a first portion disposed on or at least partially within the fin body and a second portion extending from the fin body, wherein the heat pipe includes a hollow core filled with a heat pipe working fluid having a liquid phase that is configured to transition to gas and to be returned to the liquid phase at an operational temperature of the heat exchanger.

Heat transfer fins

Growing community of inventors

Wethersfield, CT, United States of America

Leo J Veilleux, Jr