General Electric Company

Joseph D Cohen

Stephen John Howell

Neil Roger Brookes

Martin George Ray

Thomas Joseph McCarey

A gas turbine engine carburetor includes a fuel injector having a plurality of circumferentially spaced apart fuel outlets. A plurality of air swirlers (24) are circumferentially spaced apart around the fuel injector (22), with each swirler having a fuel inlet (24b) disposed in flow communication with a respective one of the fuel outlets for receiving fuel therefrom. Each swirler includes a plurality of swirl vanes to swirl air for mixing with the fuel from the fuel inlets. The multi-swirler carburetor having a common fuel injector increases injection points for reducing NO.sub.x emissions.

Fuel injector and multi-swirler carburetor assembly

A fuel nozzle including a hollow body having an inlet, an outlet and a stationary surface are disclosed. Means for modulating fuel flow from the inlet to the outlet are also disclosed and comprise a flexible pressure-responsive diaphragm fixedly mounted in the body and having a freely supported edge disposed adjacent to the body stationary surface for defining therebetween a discharge port. The flow area of the discharge port is increasable in response to increasing fuel pressure in the inlet as fuel pressure acts against the diaphragm to displace the edge away from the body stationary surface.

Fuel nozzle

In a gas turbine engine of the type which includes an inlet particle separator, there is provided apparatus for measuring the temperature of the air entering the engine compressor. A remote temperature probe is disposed in a feed duct having an inlet in flow communication with the engine inlet upstream of the particle separator and an outlet disposed intermediate the particle separator and inlet to the engine compressor. Airflow through the feed duct is generated by the pressure drop across the particle separator without the use of compressor bleed or other air sources which result in performance degradation of the engine. Temperature measurement errors during engine anti-icing are reduced by selectively cross-bleeding a predetermined quantity of anti-icing air into the feed duct during activation of the engine's anti-icing system. The response rate of the probe is significantly improved by enclosing the probe in an impingement heat transfer blanket.

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Danvers, MA, United States of America

Joseph D Cohen