United Technologies Corporation

Terry A Clark

John P Nikkanen

Richard Sterling Tuthill

Justin R Urban

John H Roberts

James M Long

George L Muller

Robert H Larson

Mark W Peszko

An ice-processing device is configured to test a consequence of ice on an aircraft engine component by simulating an effect on the ice upstream of the component.

Ice-processing device

A method of operating a gas turbine engine for testing, comprising: providing an aircraft on a tarmac, the aircraft having a gas turbine engine with an inlet; selecting a power setting for the engine that is capable of producing a vortex between the inlet and the tarmac; and inhibiting formation of the vortex. A suppressor for preventing a vortex between an inlet of a gas turbine engine on an aircraft and a tarmac. The suppressor comprises: a base facing the tarmac; and an inclined surface extending in a direction from the tarmac towards the inlet at an angle to the base. The suppressor prevents formation of the vortex.

Apparatus and method for preventing inlet vortex

Inlet vortex ingestion is deterred when testing an engine (12) in a test cell (10). Ramp structures (26) are installed on the walls blocking 30% to 50% of the flow area. The apex (42) of these ramps is located adjacent the engine inlet (24) with the upstream faces (46) at about a 45.degree. angle.

Gas turbine engine test cell

An airblast fuel nozzel (16) for a gas turbine includes a central swirled airflow. The vanes (52) of the swirler (30) are cambered to provide smooth intercept and discharge of air, thereby effecting more uniform fuel distribution than the prior art.

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East Hartford, CT, United States of America

Terry A Clark