General Electric Company

Shiladitya Mukherjee

Clark George Wiberg

Douglas Marti Fortuna

Prashant Tiwari

Daniel Tyler Jarboe

Marcin Krzysztof Wachulec

Michal Truszczynski

Pawel Ziecina

Jaroslaw Weronko

Piotr Michalec

Pawel Trzepiota

Douglas Marti Fortura

An apparatus and method for a turbine engine including an engine core having a compressor section, a combustor, and a turbine section, which are arranged to define a stator and rotor. The engine further includes a swirler to increase the rotational speed of the air leaving the stator and entering the interior of the rotor.

Turbine engine with a swirler

An apparatus for improving heat transfer through a leading portion of an aircraft engine. The apparatus includes an annular channel that is defined by the leading portion. A source for gas that is fluidly connected to the channel and a narrow region that is defined within the annular channel.

Directed flow nozzle swirl enhancer

An aircraft anti-icing system includes an inlet lip that includes an outer shell attached to a bulkhead. The inlet lip encloses an annular housing volume. The system further includes one or more vanes extending from the bulkhead into the annular housing volume. Each vane of the one or more vanes includes a first end coupled to the bulkhead, a free end extending into the annular housing volume, and a vane body extending therebetween. The one or more vanes are positioned downstream from a nozzle configured to direct a high temperature gas stream into the annular housing volume in a first direction. The one or more vanes are configured to redirect the high temperature gas stream through a first turn angle from the first direction to a second direction. The second direction is configured to reduce a direct impingement of the high temperature gas stream on an inner surface of the inlet lip.

Nozzle and vane system for nacelle anti-icing

Growing community of inventors

West Chester, OH, United States of America

Shiladitya Mukherjee