Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Purdue Research Foundation

Patrick C Sweeney

Douglas J Snyder

Igor Vaisman

Douglas David Dierksmeier

Kerry J Lighty

David C Farnum

Ben Moloney

Donald Klemen

Kenneth M Pesyna

Eric E Wilson

Stephen Douglas Heister

Carlo Scalo

Scott Schwenker

Steven A Hunt

Mario Tindaro Migliorino

Marto Tindaro Migliorino

Steven Alan Hunt

A heat exchanger assembly for a gas turbine engine includes an access panel configured to be removably coupled with an outer wall of a bypass duct arranged circumferentially around a central axis of the gas turbine engine. A heat exchanger is adapted to receive cooling fluid therein and is coupled with the access panel. A shroud extends between the access panel and the heat exchanger to collect a first portion of a flow of air through the bypass duct and direct the first portion through the heat exchanger.

Bypass duct heat exchanger with access panel for gas turbine engines

A bypass duct assembly for a gas turbine engine includes a bypass duct, a heat exchanger assembly, and an inlet cowl. The bypass duct is configured to direct bypass air around an engine core of the gas turbine engine. The heat exchanger assembly includes a heat exchanger located in the bypass duct and configured to transfer heat to the bypass air. The inlet cowl is coupled with the bypass duct and the heat exchanger assembly. The inlet cowl includes a cowl duct configured to collect a first portion of the bypass air and conduct the first portion of the bypass air into the heat exchanger and a flow diverter that guides a second portion of the bypass air around the heat exchanger.

Inlets for gas turbine engine bypass duct heat exchangers

Fuel-air heat exchange system and methods thereof for use in a gas turbine engine. The fuel-air heat exchanger allows heat transfer between a flow of cooling air used to cool components of the engine and a flow of fuel used to drive the engine.

Heat exchanger integrated with fuel nozzle

An improved system, apparatus and method may be configured for detecting coking in a gas turbine engine. The system may comprise one or more heatable collecting elements configured to be positioned in a fuel supply passage having an inlet and an outlet. The apparatus heatable collecting may be configured to generate heat at or over a fuel system temperature range to induce coking in at least one of the heatable collecting elements. The apparatus may also include a sensor configured to detect an indication of coking on the heatable collecting elements and, in response to the coking indication, communicate a coking condition signal to an engine control.

System and method for coking detection

A gas turbine engine includes devices, systems, and methods for design and operation of stabilizing heat exchangers for gas turbine engines in consideration of near supercritical fuel flow conditions.

System and method for stabilizing transcritical air-to-fuel heat exchange

Fuel injection assemblies for a gas turbine engine includes a fuel injector and heat exchanger in communication via a fuel line cavity to provide heated fuel for combustion.

Fuel injection assembly for gas turbine engine

A refrigeration system is described that includes a compression device configured to increase a pressure of a refrigerant. The refrigeration system further includes a first heat exchanger configured to reject heat from the refrigerant and reduce a temperature of the refrigerant. The refrigeration system further includes a storage device configured to store the refrigerant at a supercritical state. The refrigeration system further includes an expansion device configured to reduce the pressure of the refrigerant. The refrigeration system further includes a second heat exchanger configured to absorb heat into the refrigerant and increase the temperature of the refrigerant. The refrigeration system further includes a controller configured to release the refrigerant from the storage device to the expansion device to provide cooling capacity to the refrigeration system.

Supercritical transient storage of refrigerant

A propulsion system including a gas turbine engine is disclosed herein. The propulsion system further includes a heat exchanger arranged outside the gas turbine engine and adapted to cool fluid from the gas turbine engine.

Heat exchanger assembly for a gas turbine engine propulsion system

Fuel system coking sensor

A cooling system for an aircraft includes a first cooling circuit having a first evaporator and a second evaporator, and a second cooling circuit having a third evaporator and a fourth evaporator. One of the first and second cooling circuits includes a first set of valves arranged to direct refrigerant through a first cooling sub-circuit, a second cooling sub-circuit, or both the first and second cooling sub-circuits based on ambient conditions. Two of the evaporators are installed on a first side of the aircraft, and the other two of the four evaporators are installed on a second side of the aircraft opposite the first side, and the first and second cooling circuits reject heat, via a heat exchanger, from their respective cooling circuit to air passing into an engine of the aircraft.

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A cooling system includes a first heat exchanger, an evaporator coupled to a thermal load of an aircraft. first and second cooling circuits coupled to the heat exchanger, the first and second cooling circuits selectable via a set of cooling circuit valves that are arranged to direct a refrigerant through the first circuit, the second circuit, or both the first and second circuits based on air passing through the first heat exchanger at ambient conditions of the aircraft, and a receiver configured to accumulate reserve refrigerant to provide flexibility in system operation as the cooling system operates in sub-critical, trans-critical, and super-critical modes of operation.

Adaptive trans-critical carbon dioxide cooling systems

A multi-evaporator cooling system includes a compressor circuit that generates multiple levels of evaporating pressures, the circuit comprising at least one compressor configured to compress a refrigerant to a first pressure, a heat exchanger configured to receive the compressed refrigerant from the at least one compressor and cool the compressed refrigerant, a first evaporator circuit configured to receive the compressed refrigerant from the heat exchanger, expand the compressed refrigerant to a second pressure that is lower than the first pressure, and return the refrigerant to the compressor circuit, and a second evaporator circuit configured to receive the compressed refrigerant from the heat exchanger, expand the compressed refrigerant to a third pressure that is lower than the second pressure, and return the refrigerant to the compressor circuit.

Multi-evaporator trans-critical cooling systems

A cooling system includes a heat exchanger through which a refrigerant flows, and which rejects heat to a fluid, an evaporator, a first circuit having an expansion device, a second circuit having an expansion machine coupled to a compressor, and a set of valves arranged to direct the refrigerant through the first circuit, the second circuit, or both the first and second circuits based on ambient conditions.

Growing community of inventors

Indianapolis, IN, United States of America

Patrick C Sweeney