Other

United Technologies Corporation

Starrotor Corporation

Daniel J Micka

Mark Thomas Holtzapple

Patrick Magari

Jeffery A Lovett

Darin A Knaus

Jeffrey J Breedlove

Scott David Phillips

A fuel injection system for a gas turbine engine includes a vane in an airflow path within the gas turbine engine, the vane includes an air channel with an outlet in communication with the airflow path; and a fuel nozzle within the vane operable to inject fuel into the air channel to at least partially premix and prevaporize the fuel with a secondary airflow from within the vane in the air channel prior to entry into the airflow path through the outlet. A method of injecting fuel within a gas turbine engine includes at least partially premixing and prevaporizing fuel with a secondary airflow from within a vane in an air channel within the vane, the vane within an airflow path of the gas turbine engine.

Carbureted fuel injection system for a gas turbine engine

A system and method are presented for improved performance of gerotor compressors and expanders. Certain aspects of the disclosure reduce porting losses in a gerotor system. Other aspects of the disclosure provide for reduced deflection in lobes of an outer rotor of a gerotor system. Still other aspects of the disclosure provide for reduced leakage through tight gaps between components of a gerotor system.

Gerotor with reduced leakage

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Enfield, NH, United States of America

Daniel J Micka