Honeywell International Inc.

Jeffrey A Turner

Yogendra Y Sheoran

Bruce Dan Bouldin

Robert G Hoover

Andrew Appleby

Kevin S Dittmar

Jonathan Luc Dion

A micro-auxiliary power unit for supplying electric power to a vehicle includes a thermal resistant enclosure having an intake duct for receiving air, and a source of fuel. A fuel valve is fluidly coupled from the enclosure, and the fuel valve is movable between an opened position and a closed position. The micro-auxiliary power unit includes a Wankel engine to drive an output shaft and a starter-generator coupled to the output shaft to generate electric power. The micro-auxiliary power unit includes a system that has at least one sensor disposed within the enclosure that observes a condition of the enclosure and generates sensor signals, and a controller having a processor that receives the sensor signals, determines the presence of a thermal event within the enclosure and based on the determination, outputs one or more control signals to the fuel valve to move the fuel valve to the closed position.

Micro-auxiliary power units

An exhaust muffler is provided for a turbine engine with at least first and second exhaust outlets. The exhaust muffler includes a first arm configured to be coupled to the first exhaust outlet of the turbine engine. The first arm includes an outer surface, and an inner surface that defines a first exhaust cavity. The first arm further includes a plurality of perforations extending between the inner and outer surfaces. The exhaust muffler further includes a second arm coupled to the first arm and configured to be coupled to the second exhaust outlet of the turbine engine. The second arm includes an outer surface, and an inner surface that defines a second exhaust cavity. The second arm also includes a plurality of perforations extending between the inner and outer surfaces.

Turbine engine diffusing exhaust muffler

A drainmast for discharging fluid from a body in motion, such as an aircraft in flight, may include a barrier disposed at a distal portion of the drainmast. The barrier may extend downstream from the drainmast trailing edge, and may be disposed at a negative angle of attack to a local free-stream airflow, thereby forming a downdraft over the barrier to prevent migration of discharged fluid towards an aircraft skin. In some embodiments, the drainmast may include one or more vanes, disposed internally within a discharge conduit of the drainmast, for deflecting fluid flow within the drainmast towards a direction of free-stream airflow outside the drainmast. Methods for channeling fluid away from an external surface of an aircraft in flight are also disclosed.

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Chandler, AZ, United States of America

Jeffrey A Turner