United Technologies Corporation

Raytheon Technologies Corporation

Other

William F Schneider

Rajendra K Agrawal

Christopher J Hanlon

Gabriel L Suciu

Michael E McCune

Jesse M Chandler

Joseph Brent Staubach

Coy Bruce Wood

Ravi Rajamani

Alan H Epstein

Steven M O'Flarity

Steven J Sirica

James A Kenyon

Daniel Bernard Kupratis

Michael L Greenfield

Walter A Ledwith

Robert H Bush

Benjamin Bellows

John Joseph Meyer

George Mozurkewich, Jr

Sean Danby

Leonard I Stiel

Rejendra K Agrawal

A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.

Gas turbine engine and an airflow control system

A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.

Gas turbine engine with distributed fans

A rotary-wing aircraft includes a retractable port movable between a closed position and an open position to selectively control flow of combustion gases into a bypass passage to change a power distribution between a rotor system and a secondary propulsion system.

Gas turbine engine with noise attenuating variable area fan nozzle

A convertible gas turbine propulsion system operates in multiple output modes. The convertible gas turbine propulsion system comprises a gas generator, a first power turbine, a secondary propulsion system and an exhaust duct. The gas generator is configured to produce exhaust gas. The first power turbine is aligned with the gas generator to receive the exhaust gas. The secondary propulsion system is in series with the gas generator and the first power turbine. The exhaust duct coaxially extends from the first power turbine to the secondary propulsion system. The exhaust duct includes an exhaust port for opening the exhaust duct to ambient air pressure and permitting exhaust gas to bypass the secondary propulsion system. In various embodiments of the invention, the first power turbine is connected to a first rotary propulsion system, and the secondary propulsion system comprises a second power turbine or a nozzle.

Convertible gas turbine propulsion system

An example method of estimating gas turbine engine performance deterioration includes monitoring debris in at least a portion of an engine and estimating performance deterioration of at least one component of the engine using information from the monitoring. The method may use gas path parameters, such as pressures, temperatures, and speeds to establish the estimated performance deterioration. An example gas turbine engine performance assessment system includes a debris monitoring system configured to monitor debris moving through a portion of an engine and a controller programmed to estimate performance deterioration of at least one component of the engine based on information from the debris monitoring system.

System and method of estimating gas turbine engine performance

An example method of assessing a component of a gas turbine engine includes monitoring debris in at least a portion of an engine and establishing an estimated thermal energy level for a component of the engine based on the monitoring. The method may use gas path parameters to establish the estimated thermal energy level. An example gas turbine engine component assessment system includes a debris monitoring system configured to monitor debris moving through a portion of an engine and a controller programmed to execute an engine deterioration model that assesses a thermal energy level of at least one component of the engine based on information from the debris monitoring system.

System and method of assessing thermal energy levels of a gas turbine engine component

A carbon dioxide/cofluid mixture is provided for use in a refrigeration cycle in which the carbon dioxide is alternately absorbed and desorbed from the cofluid. The mixture includes from 50% to 95% cofluid and from 5% to 50% carbon dioxide. The cofluid is selected so that the mixture falls within region A of the plot of p versus &Dgr;h shown in FIG. . The &Dgr;h of the mixture is the differential heat of solution of the carbon dioxide in the cofluid at 5 wt % and 0&deg; C. The p of the mixture is the vapor pressure of the carbon dioxide over the solution at 20 wt % and 40&deg; C.

Cofluids for use with carbon dioxide refrigerant

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Cromwell, CT, United States of America

William F Schneider