Fuel Systems Textron Inc.

Fei P Lee

Theodore R Koblish

Robert M Halvorsen

Jerome R Bradley

Mike Guzowski

An improved airblast fuel injector for a gas turbine engine wherein the injector comprises an inner air discharge chamber, a first fuel discharge chamber disposed outboard of the inner air chamber, an intermediate air discharge chamber disposed radially outboard of the first fuel chamber, a second fuel discharge chamber disposed radially outboard of the first outer air chamber, and an outer air discharge chamber disposed radially outboard of the second fuel chamber. The fuel flow from the first fuel discharge chamber is subjected to inner and outer atomizing air flows from the inner and intermediate air chambers. The fuel flow from the second fuel discharge chamber is subjected to inner and outer atomizing airflows from the intermediate and outer air discharge chambers. The individual fuel flow streams discharged from the first and second fuel discharge chambers provide an aggregate, high mass flow of fuel necessary for engine operation. The individual, atomized fuel flow streams discharged from the injector face are blended together downstream of the discharge face.

Fuel injector assembly with first and second fuel injectors and inner,

A self-purging fuel injector for a combustor of a gas turbine engine wherein the fuel injector comprises an injector body having first and second air discharge orifices for discharging air to the combustor and first and second fuel passage means having respective first and second fuel discharge orifices for discharging fuel to the combustor. The first and second fuel passages are in communication upstream of the fuel discharge orifices. The first air and fuel discharge orifices have a relationship to establish a pneumatic pressure at the first fuel discharge orifice and the second air and fuel discharge orifices have a relationship to establish a different pneumatic pressure at the second fuel discharge orifice such that, in the event the supply of fuel to the first and second fuel discharge orifices is interrupted, the fuel residing in the fuel passages between the first and second fuel discharge orifices is subjected to a pressure differential effective to purge the resident fuel into the combustor.

Fuel purging fuel injector

The gas turbine combustor air swirler includes a spring temper swirler member having a plurality of air control doors or vanes so cut therein about the longitudinal axis of the combustor inlet as to be integrally and resiliently pivotally connected to the swirler member. The air control doors are progressively canted open to provide predetermined air flow rate and air swirl angle to the combustor inlet in response to increases in air pressure differential thereacross resulting from progressive increases in fuel flow through the nozzle during various regimes of engine operation. The swirler is free of linkages and sliding or other contacting components that are susceptible to binding and other malfunctions in service in the engine.

Growing community of inventors

Novi, MI, United States of America

Fei P Lee