United Technologies Corporation

Arthur W Utay

Daniel Bernard Kupratis

Gabriel L Suciu

Brian D Merry

Mark F Zelesky

Thomas N Slavens

Tania Bhatia Kashyap

Kevin L Rugg

Francis R Moon

A gas turbine engine includes a spool configured to rotate about an axial centerline. The spool includes a fan rotor and a cold turbine rotor. The fan rotor is rotatably driven by the cold turbine rotor. A cold turbine inlet passage is configured to direct an airflow along a radial inward trajectory to the cold turbine rotor.

Gas turbine engine with cold turbine and multiple core flowpaths

A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.

Split compressor turbine engine

An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.

Twin centrifugal single spool engine

The present disclosure relates generally to a method of operating an inspection system, including a sensor and heating element operably coupled to a control module, to determine in-situ a coating integrity for a turbomachinery component within a turbomachinery system, the method comprising the steps of: placing the sensor and heating element at a distance from the desired turbomachinery component to be examine, operating the heating element for a predetermined amount of time, operating the sensor to detect an output from a surface of the turbomachinery component, and operating the control module to compare the output with at least one integrity parameter.

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South Windsor, CT, United States of America

Arthur W Utay