United Technologies Corporation

Hamilton Sundstrand Corporation

Carrier Corporation

Utc Power Corporation

Other

Michael K Sahm

Charles E Lents

Daniel R Sabatino

Vincent C Nardone

Luca Bertuccioli

Richard C Welch

David S Liscinsky

Bernd R Noack

Fabio Paolo Bertolotti

Jules Ricardo Munoz

Jose Albero

Fabio R Bertolotti

Jay Fletcher

Louis J Bruno

Robert G Thompson

Mark E Marler

Timothy C Wagner

Wayne A Thresher

Sunghan Jung

Jinsang Ryu

Richard Dussault

Arthur Curtis Becker

Steve Squier

Jifeng Zhang

Jun Shi

Steven J Moss

David C Jarmon

Joseph J Sangiovanni

Louis J Spadaccini

Foster Philip Lamm

Thomas Henry Vanderspurt

Thomas Gregory Tillman

He Huang

Scott F Kaslusky

Kevin E Green

Steven E Squier

Stuart S Ochs

Eric Tremaine

Patrick Germain

J Axel Glahn

Timothy D DeValve

Rakesh Radhakrishnan

H Ezzat Khalifa

Lisa A Prill

Robert L Bayt

Per-Anders K Lof

Arthur Chris Becker

A solar energy driven power generation system includes a solar energy receiver configured to collect solar energy. A vapor generator is operably connected to the solar energy receiver. A vapor turbine is operably connected to the vapor generator and is configured to be driven by a flow of vapor from the vapor generator. An electrical power generator is operably connected to the vapor turbine and driven thereby. A thermal conditioning system is operably connected to the vapor turbine and is driven by a flow of output vapor or hot liquid from the vapor turbine. A method of power generation includes collecting solar thermal energy and generating vapor utilizing the solar thermal energy. A vapor turbine is driven by the vapor and electrical power is produced via the rotation of the vapor turbine. Output vapor from the vapor turbine is utilized to drive a thermal conditioning system.

Solar energy driven system for heating, cooling, and electrical power generation incorporating combined solar thermal and photovoltaic arrangements

In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening. Pairs of openings and associated collars maybe placed in symmetric relationship so as to promote mixing in particular applications, and nozzles maybe placed on the inner side of wall to enhance the flow characteristics of the primary fluid.

Arrangement for controlling fluid jets injected into a fluid stream of a bleed air discharge nozzle

Arrangement for controlling fluid jets injected into a fluid stream

In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream to enhance penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. Embodiments of the arrangement can comprise a collar around the openings, multiple openings that comprise a larger opening and a smaller opening positioned downstream, pairs of openings and associated collars symmetric relationship, and nozzles on the inner side of the wall.

A fluid recycling system includes a separator for physically separating glycol from at least a portion of other substances mixed with the glycol to produce a first effluent stream having separated glycol and a second effluent stream having the other substances and residual glycol. A catalytic reactor receives the second effluent stream and chemically reacts the other substances and residual glycol to produce a hydrogen stream and a remainder stream.

Glycol recycle system

A vane has an airfoil shell and a spar within the shell. The vane has an outboard shroud at an outboard end of the shell and an inboard platform at an inboard end of the shell. The spar has a first chamber essentially along the suction side and a second chamber along the pressure side opposite the first chamber.

Ceramic matrix composite turbine engine vane

Turbulators are disclosed for use in a high-stage generator for an exhaust-fired absorption chiller/heater. The turbulators are designed to minimize pressure drop across the turbulator, and thus minimize the efficiency loss to the exhaust source. One turbulator design has a number of flanges extending at a non-normal angle to a central web. Further, some of the flanges have cutout portions. The overall turbulator design is intended to minimize wake downstream of the turbulator blades, which could otherwise cause undesirable pressure drop. A second turbulator design incorporates flanges that extend at a normal angle relative to the central web, but wherein the flanges have a non-rectangular cross-sectional shape. Again, the goal of the turbulator designs here is to minimize wake, and potential pressure drop.

High-efficiency turbulators for high-stage generator of absorption chiller/heater

The present invention relates to an engine integrated auxiliary power unit. The engine comprises a high pressure spool which includes a high pressure compressor connected to a high pressure turbine and a low pressure spool which includes a low pressure compressor connected to a low pressure turbine. The engine further has a system for independently operating the high pressure spool and thus allowing the high pressure spool to function as an auxiliary power unit.

Engine integrated auxiliary power unit

A system for the management of thermal transfer in a gas turbine engine includes a heat generating sub-system in operable communication with the engine, a fuel source to supply a fuel, a fuel stabilization unit to receive the fuel from the fuel source and to provide the fuel to the engine, and a heat exchanger in thermal communication with the fuel to transfer heat from the heat generating sub-system to the fuel. A method of managing thermal transfer in an aircraft includes removing oxygen from a stream of a fuel fed to an engine used to drive the aircraft, transferring heat from a heat generating sub-system of the aircraft to the fuel, and combusting the fuel. A system for the thermal management of an aircraft provides for powering the aircraft, supplying a fuel deoxygenating the fuel, and transferring heat between a heat generating sub-system of the aircraft and the fuel.

System and method for thermal management

A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary power unit can be mounted within an engine core compartment of the main engine or at the main engine aft center body. The integration of the auxiliary power unit provides for installation and certification cost savings to the airframer by eliminating the need for mounting an auxiliary power unit to the tail section of the aircraft.

Main propulsion engine system integrated with secondary power unit

The present invention relates to an electrical power and cooling system for use in an aircraft having at least one engine. The electrical power and cooling system comprises a single shaft, a power turbine mounted on the shaft for receiving fresh pressurized air from the at least one engine, a cooling turbine mounted on the shaft and receiving the fresh pressurized air from the at least one engine, a generator mounted on the shaft, and a fan mounted on the shaft for creating a flow of cooling air. The system further has a condenser for removing moisture from the air exiting the cooling turbine and a mixing chamber for mixing the cooled dry air with recirculated cabin air. The electrical power and cooling system delivers conditioned air to a cabin and/or a flight deck onboard the aircraft and electrical power to the aircraft's electrical systems.

Electric power and cooling system for an aircraft

The present invention relates to an integrated enviromental control system for an aircraft. The system uses bleed air from a propulsion engine to drive an air turbine which provides power to at least one aircraft component such as an aircraft mounted accessory drive. The system uses the bleed air exiting the air turbine as an air source for the cabin and/or flight deck enviromental control system.

Integrated system for providing aircraft environmental control

The present invention relates to an integrated air turbine driving system for providing aircraft environmental control. The system has at least one air driven turbine for providing power to an aircraft mounted accessory drive and for providing heated air to an aircraft anti-ice system. The system further has a subsystem for supplying cooled pressurized air to a flight deck and/or cabin and to aircraft avionics. Still further, the subsystem provides cooling air to other aircraft components such as a generator and/or an aircraft mounted accessory drive.

Integrated air turbine driven system for providing aircraft environmental control

Growing community of inventors

Avon, CT, United States of America

Michael K Sahm