United Technologies Corporation

Raytheon Technologies Corporation

Douglas A Thonebe

Wendell V Twelves

James E Jones

Gary D Roberge

James W Norris

Stephen Karl Kramer

Gary M Perkins

Gary D Jones

Harvey L Klein

Bradley C Sammann

Russell L Coons

Jeffrey Prausa

Marsha E Perkins, Legal Representative

Arthur Salve

A supplemental cooling air system for a turbine engine may comprise a compressor having an inlet and an outlet, and an electric motor operatively coupled to the compressor and configured to drive the compressor. The inlet may receive air from at least one of a freestream flow path, a bypass flow path, or an engine bay. The outlet may supply the air to at least a portion of the turbine engine for cooling.

Supplemental cooling air for turbine exhaust components and surfaces

A turbine engine has a case with an axis. A fan is mounted for rotation about the axis. A turbine is mechanically coupled to the fan to drive rotation of the fan about the axis. A number of compressor/turbine units are downstream of the fan and upstream of the turbine along a core flowpath. A number of compressors are coupled to the compressor/turbine units to receive air and deliver combustion gas to drive the turbine.

Pulsed combustion engine

A pulsed combustion device includes a support structure and a combustor carousel supported by the support structure and rotating relative thereto about an axis. The carousel has a number of combustion conduits in a circumferential array. Each conduit cyclically receives a charge and discharges combustion products of the charge.

This disclosure relates to a system for purging of the nacelle of an aircraft and for cooling the edge pieces of the divergent flap of a gas turbine engine's two-dimensional exhaust system by use of long tubular air pump with axisymmetric supersonic nozzles, a rectangular mixing chamber for pumping nacelle air with fan discharge air and judiciously flowing the air in separate passageways formed in the double clamshell convergent flap of the exhaust nozzle. This reduces the overall aircraft and weapon system weight, with only a minimum increase in the engine's nozzle weight.

Aircraft nacelle ventilation and engine exhaust nozzle cooling

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Jupiter, FL, United States of America

Douglas A Thonebe