United Technologies Corporation

Donald C Eiler

Michael J Larkin

Thomas A Wynosky

Edward F Migliaro, Jr

Jerrold R Blatt

A gas turbine engine is provided with an oil cooler which receives cooling air from a turbo fan. At times when the turbo fan is operating at lower speeds, the volume of cooling air is also lowered. At such times, a supplemental airflow is provided over heat exchangers in the oil cooler. The supplemental airflow includes a supplemental airflow fan and valve for selectively controlling the supplemental airflow over the heat exchangers.

Supplemental oil cooler airflow for gas turbine engine

The present invention relates to a variable cycle boost propulsor system for use on an aircraft. The variable cycle boost propulsor system includes an engine, a turbine, a fan connected to the turbine, and a valve system for delivering the fluid output from the engine to the turbine for driving the turbine and the fan and thereby generating additional thrust for the aircraft. The engine is also used to provide power to one or more systems onboard the aircraft.

Variable cycle boost propulsor

The lobe mixer of a gas turbine engine is modified by judiciously extending chutes axially and radially inwardly toward the engine centerline permitting the use of a smaller cooperating centerbody while improving on engine performance and noise suppression.

Lobe mixer for gas turbine engine

A fairing added to the upstream end of the lobe of conventional lobed mixers or inverters for a gas turbine engine redirects the boundary layer so as to improve engine performance.

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Portland, CT, United States of America

Donald C Eiler