Honeywell International Inc.

Honeywell G.m.b.h.

Eric Blumer

Cristian E Anghel

David K Jan

Yogendra Y Sheoran

Jason Smoke

Harry Lester Kington

Wayne T Pearson

Robbie Joseph Adams

Charles S Lo

Alexander M Bershitsky

Russell W Johnson

Dinkar A Mylaraswamy

Paul T Wingett

Rodolphe Dudebout

Peter M Michalakos

Kyusung Kim

Louie Timothy Gaines

Ming Xu

Yates Wong

Raj Mohan Bharadwaj

Mike S Koerner

Bijan F Hagh

Qixiang Li

Zedic Daniel Judd

Joseph B Borghese

John Thurston

Eduardo Guerra

Mario Scaini

Henry M Claeys

Dan Laboda

C Arthur Dins

Mukund Acharya

Michael Easley

John Linert

Garry H Lee

Audie Mak

Alexander Bershitsky

A hybrid electric aircraft propulsion system at least includes a motor with induction effect to drive a propeller or propulsion fan. The motor is directly supplied from the electrical output of a generator. The generator is driven by a variable speed engine and as such the generator has a output frequency proportional to the speed of the engine. A controller is operatively coupled to the motor, the generator and the engine. The controller is operable to control a speed of the engine and the excitation of the generator to provide an output at a target voltage and frequency to drive the motor at a desired torque and speed.

Hybrid electric aircraft propulsion system with motors using induction effect

A system for providing compressed air to pneumatic loads in a vehicle such as an aircraft, the system includes a gas turbine engine having; a) an engine compressor with an air inlet coupled to an interior of a cabin of the vehicle; and b) a load compressor coupled to the gas turbine engine having a compressed air outlet coupled to one or more pneumatic loads of the vehicle. One or more electrically driven cabin air compressors (CAC) have compressed air outlets coupled to the one or more pneumatic loads.

Hybrid pneumatic and electric secondary power integrated cabin energy system for a pressurized vehicle

A system for driving an environmental control system (ECS) of a vehicle with ground-based electrical power may include a turbine engine on board the vehicle, coupled to the ECS to pneumatically drive the ECS, and an electric machine, on board the aircraft, mechanically coupled to the turbine engine, to drive the turbine engine. A control system such that the electric machine provides motoring assistance to the turbine engine, and that the motoring assistance is limited to match the available current from the ground-based electrical power.

Motor-generator for high efficiency auxiliary power system

In one embodiment, a method is provided. The method comprises: receiving, in a vehicle, at least one pollution parameter; and adjusting at least one fluid flow regulating mechanism position, to regulate an intake of pollutants into an environmental control system of the vehicle, based upon the at least one pollution parameter.

Systems and methods for reducing environmental control system maintenance

A system for reducing drag on an aircraft includes an ambient air inlet positioned in or near a wingtip fence and or winglet of the aircraft and an air pressurization device, such as an air compressor, coupled to the ambient air inlet. The air pressurization device has an inlet oriented toward the ambient air inlet. The air pressurization device has an outlet oriented toward an interior of the aircraft.

Air distribution system with drag reducing inlet

Dual alloy Gas Turbine Engine (GTE) rotors and method for producing GTE rotors are provided. In one embodiment, the method include includes arranging bladed pieces in an annular grouping or ring formation such that shank-to-shank junctions are formed between circumferentially-adjacent bladed pieces. A first or bonding alloy is deposited along the shank-to-shank junctions utilizing a localized fusion deposition process to produce a plurality of alloy-filled joints, which join the bladed pieces in a bonded blade ring. The bonding alloy is preferably selected to have a ductility higher than and a melt point lower than the alloy from which the bladed pieces are produced. After deposition of the first alloy and formation of the alloy-filled joints, a hub disk is inserted into the central opening of the bonded blade ring. The hub disk and blade ring are then bonded utilizing, for example, a Hot Isostatic Pressing process.

Dual alloy gas turbine engine rotors and methods for the manufacture thereof

A combustor for a turbine engine is provided. A first liner has a first surface and a second surface. A second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second surface of the first liner. The plurality of effusion cooling holes includes a first effusion cooling hole extending from the first surface to the second surface and including an inlet portion extending from the first surface, a metering portion fluidly coupled to the inlet portion, and an outlet portion fluidly coupled to the metering portion and extending to the second surface. The inlet portion is larger than the metering portion.

Gas turbine engines with plug resistant effusion cooling holes

Bladed Gas Turbine Engine (GTE) rotors including deposited transition rings are provided, as are embodiments of methods for manufacturing bladed GTE rotors. In one embodiment, the method includes providing an outer blade ring having an inner circumferential surface defining a central opening, and depositing a deposited transition ring on the inner circumferential surface of the outer blade ring. The outer blade ring can be a full bladed ring or an annular grouping of individually-fabricated bladed pieces. After deposition of the transition ring, a hub disk is inserted into the central opening such that the transition ring extends around an outer circumferential surface of the hub disk. The transition ring is then bonded to the outer circumferential surface of the hub disk utilizing, for example, a hot isostatic pressing technique to join the transition ring and the outer blade ring thereto.

Bladed gas turbine engine rotors having deposited transition rings and methods for the manufacture thereof

An environmental control system (ECS) includes a controller; and a mode selector in communication with the controller and configured to select at least one of a plurality of modes. The mode is based on one of: number of occupants in an environment; activity of the occupants in the environment; destination of the environment; and performance of an engine that moves the environment. The controller is configured to change an ECS load on the system based upon the selected mode.

ECO mode ECS logic

An aircraft fuel deoxygenation system includes a boost pump, a contactor-separator, and a centrifuge-separator pump. The boost pump is adapted to receive fuel from a fuel source and inert gas from an inert gas source, and is configured to mix the fuel and inert gas and supply a fuel/gas mixture. The contactor-separator is coupled to receive the fuel/gas mixture and is configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel with entrained purge gas and separated purge gas. The centrifuge-separator pump is coupled to receive the deoxygenated fuel with entrained purge gas and is configured to separate and remove the entrained purge gas from the deoxygenated fuel and supply the deoxygenated fuel and additional purge gas.

Aircraft fuel deoxygenation system

A high efficiency multifunction power system for an aircraft is provided. The system includes an AC generator and a multifunction power converter-controller module including at least one multifunction power converter-controller. The at least one multifunction power converter-controller is configured to function as a power converter and a controller to perform multiple operation modes.

Power converter, generator and architecture for high efficiency auxiliary power unit

An aircraft fuel deoxygenation and tank inerting system includes an inert gas source, a fuel deoxygenation system, and an air/fuel heat exchanger. The inert gas source is configured to supply inert gas having an oxygen concentration of less than 3%. The fuel deoxygenation system is adapted to receive fuel from a fuel source and the inert gas from the inert gas source. The fuel deoxygenation system is configured to remove oxygen from the fuel and thereby generate and supply deoxygenated fuel and oxygen-rich purge gas. The air/fuel heat exchanger is adapted to receive compressed air from a compressed air source and the deoxygenated fuel from the fuel deoxygenation system. The air/fuel heat exchanger is configured to transfer heat from the compressed air to the deoxygenated fuel, to thereby supply cooled compressed air and heated deoxygenated fuel.

Fuel deoxygenation and fuel tank inerting system and method

The present invention relates to apparatus and methods for exchanging heat between various fluids. More particularly, the present invention relates to apparatus and methods for exchanging heat between fuel, fan-air, and bleed-air in an integrated heat exchanger. Thereby, a weight and size of the integral heat exchanger are reduced compared to known non-integral heat exchangers. Advantageously, the heat exchanger may heat fuel to improve engine specific fuel consumption (SFC).

Plate-fin tubular hybrid heat exchanger design for an air and fuel cooled air cooler

An inlet particle separator system for a vehicle engine includes a separator assembly and a liquid injection system. The separator assembly defines an inlet flow path for receiving inlet air and includes a scavenge flow path and an engine flow path downstream of the inlet flow path. The separator assembly is configured to separate the inlet air into scavenge air and engine air such that the scavenge air is directed from the inlet flow path into the scavenge flow path and the engine air is directed from the inlet flow path into the engine flow path. The liquid injection system is coupled to the separator assembly and configured to introduce a diffused liquid into the inlet air flowing through the separator assembly.

Liquid injection inlet particle separator systems and methods

A high voltage direct current (DC) tether for an airborne wind turbine includes one conductor in the center of the feeder and the shielding of the feeder as a second conductor. A mechanical strength element is disposed in between the center conductor and the shielding. In this configuration, the mechanical strength element acts also as an insulator. The center conductor and the shielding can be made of aluminum or copper. The strength element can be a high strength fiber composite, woven such as VECTRAN&#xae; or SPECTRA&#xae;. The shielding is typically used as the return conductor.

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Scottsdale, AZ, United States of America

Eric Blumer