Hamilton Sundstrand Corporation

United Technologies Corporation

Raytheon Technologies Corporation

Rohr, Inc.

Goodrich Corporation

Sikorsky Aircraft Corporation

Simmonds Precision Products, Inc.

Kidde Technologies Incorporated

Jhamilton Sundstrand Corporation

Rtx Corporation

Lubomir A Ribarov

Leo J Veilleux, Jr

Jacek F Gieras

James S Elder

Richard J Carpenter

Joel H Frank

Kevin D Gibbons

Charles E Reuter

Russell P Rourke

Thomas O Harris

Gregory I Rozman

Richard Andrew Himmelmann

Robert Scott Downing

Dharmendr Len Seebaluck

Aaron V Price

Ethan Flow

Mark R Jaworowski

Haralambos Cordatos

Stephen Michael Bortoli

Aaron F Rickis

Michael John Giamati

Gary M McBrien

Adam Chattaway

William E Seidel

Alan John Fahrner

Charles W Haldeman

Brandon T Kovach

Zachary Allen Ray Le Duc

David S Liscinsky

Meredith B Colket

Erick Ramos

Gregory C Hopkins

Michael D Schelonka

Mark Walter Corcoran

Bryan V Scala

Sushant S Bhadange

Samuel Schmidt

Brian K Burbank

Madi Kalibala

James J Kamm

Jack Sisson

Kevin Gibbons

Charles J Russo

William Luker

Geoffrey D Fenelon

William D Hodge

Leo J Veilleux

Leo J Veilleux Jr

Christopher J Davis

Jr Leo J Veilleux

Gary M Mcbrien

Russel P Rourke

Willliam Luker

Meredith B Iii Colket

Jr James Elder

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

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

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 fluid flow arrangement includes a manifold defining a fluid passage. A pressure sensor system is in fluid communication with the fluid passage. The pressure sensor system has a first sensor arranged along a first sense line and a second sensor arranged along a second sense line. The first and second sense lines are in fluid communication with the fluid passage. The first sense line has a first resonant frequency and the second sense line has a second resonant frequency. The second resonant frequency is different than the first resonant frequency.

Pressure ripple mitigation in pressure sensors

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 starter-generator module for a gas turbine engine includes an inner stator portion with an armature defining a rotation axis and an outer rotor portion disposed about the rotation axis. The outer rotor portion includes a permanent magnet and a gear teeth member. The permanent magnet is disposed about the rotation axis and the gear teeth member is defined on the outer rotor portion such that the gear teeth member transmits rotational energy to an accessory gearbox in a start mode and receives rotational energy from the accessory gearbox in a generate mode.

Starter-generator modules for gas turbine engines

A thermal management system for a gas turbine engine includes a primary vapor compression system including a primary evaporator defining thermal communication between a primary refrigerant and a flow of fuel to cool the fuel. A boost vapor compression system includes a boost heat exchanger defining thermal communication between the primary refrigerant. A boost refrigerant cools the primary refrigerant and a boost condenser in thermal communication with an air stream cools the boost refrigerant.

Integrated thermal management system for fuel cooling

An adaptive thermal management system for a gas turbine engine includes a heat exchanger transferring heat into a coolant, a temperature sensor measuring a temperature of the coolant, and a sensor assembly that measures a parameter of the coolant during operation of the gas turbine engine. The parameter measured by the sensor assembly is indicative of a capacity of the coolant to accept heat from the hot flow. A control valve governs a flow of coolant into the heat exchanger. A controller adjusts the control valve to communicate coolant to the heat exchanger based on a determined capacity of the coolant to accept heat in view of the measured temperature of the coolant and that the measured parameter of the coolant is within a predefined range.

Adaptive thermal management system for aircraft fuel system

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 thermal management system for a gas turbine engine includes a heat exchanger including a first coolant passage for a first coolant medium and a second coolant passage for a second coolant medium that is different than the first coolant medium. A first hot flow passage is in thermal communication with the first coolant passage. A second hot flow passage is in thermal communication with the second coolant passage all within a common housing. A first valve controls a flow of a hot medium into at least one of the first hot flow passage or the second hot flow passage. A controller configured to operate the first valve to direct the flow of hot medium into one of the first hot flow passage and the second hot flow passage for transferring thermal energy from the flow of hot medium into one of the first coolant medium and the second coolant medium.

Multiple stream heat exchanger

A thermal management system for a gas turbine engine includes a cooler including a first portion and a second portion, the first portion for cooling a hot flow with a coolant and the second portion for cooling the coolant with a refrigerant. A vapor compression system circulates the refrigerant through the second portion of the cooler. The vapor compression system is a closed system in communication with at least one heat load in addition to the second portion of the cooler.

Dynamic thermal load monitoring and mitigation for aircraft systems

Apparatus and associated methods relate to equalizing wearing of a plurality of electrical power generators of an aircraft. Such equalization is achieved by logging operating conditions of at least a powered subset of the electrical power generators and then comparing of the logged operating conditions of each of the plurality of electrical power generators. Based on the comparison of the logged operating conditions, one of the plurality of electrical power generators for use the aircraft is recommended. A signal indicative of the recommended one of the electrical power generators determined is then generated.

Equalizing wearing of two or more electrical power generators of an aircraft

A fuel pump system for a turbomachine engine can include a boost pump driven by an electric motor and configured to be in fluid communication with a fuel tank, a primary pump configured to be driven by a shaft connected to the turbomachine engine, wherein the primary pump is in fluid communication with the boost pump downstream of the boost pump by a boost branch, a bypass flow branch that connects the boost branch to a downstream branch that is downstream of the primary pump, the downstream branch is in fluid communication with one or more metering valves and/or one or more fuel nozzles, and a bypass valve disposed in the bypass flow branch and/or the downstream branch and configured to selectively directly fluidly communicate the boost branch and the downstream branch.

Fuel pump systems for turbomachines

An air to air heat exchanger is provided including a core having a plurality of alternately stacked first layers and second layers. Each first layer includes a plurality of first modules having corrugated fins that define a plurality of first fluid flow paths. The first modules are aligned to fluidly couple the first fluid flow paths. Each second layer includes at least one second module having corrugated fins that define a plurality of second fluid flow paths. At least one second layer includes a third module having a plurality of corrugated fins that define a plurality of third fluid flow paths. The third module is arranged such that the third fluid flow paths are parallel to the second fluid flow paths. A number of corrugated fins formed in the third module is less than a number of corrugated fins formed in the second module.

Heat exchanger

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West Hartford, CT, United States of America

Lubomir A Ribarov