United Technologies Corporation

Edmund E Striebel

Francis C Pane, Jr

Domingo Sepulveda

John A Matthews

Richard R Wright

Thomas J Madden

David Kwoka

Joseph E Faucher

James J Nolan

George W Austin, Jr

Robert A Breton

Roger Halsted James

Theodore Richard Koblish

A fuel injector assembly for a gas turbine combustor projects a hollow conical spray of fuel. A plurality of discrete surrounding air nozzles 42 project air directly toward the axis 46 of the injector at an angle of 15 degrees, establishing a fuel rich external recirculation zone 52.

Airblast fuel injector

Improvement to the starting characteristics of an annular combustor for a gas turbine engine that employs dual fuel nozzles (primary and secondary fuel flow systems) by redistributing the total fuel admitted to the nozzles in an asymmetrical pattern to deliver the requisite amount of fuel to the igniter by the primary flow system feeding fuel to that igniter.

Method of distributing fuel flow to an annular burner for starting of a

This invention minimizes wakes manifested by a fuel nozzle support structure extending through an annular diffuser engine to the burner in a gas turbine engine, spaced walls extending from the inner and outer wall of the diffuser project toward the nozzle support downstream of the support that passes transverse to the flow, one wall being shaped conically and the other being shaped bell-mouthed and convergent.

High blockage diffuser with means for minimizing wakes

A fuel nozzle designed to reduce pollutant emissions and minimize the buildup of coke in the secondary fuel passage of a dual orifice fuel nozzle for the combustor of a gas turbine engine sizes the orifices and passages of the air and fuel so as to increase the pressure in the secondary passage during its inoperative mode and when the primary fuel passage is in the operative mode and having the air and fuel issuing from both the primary and secondary orifices swirl in the same direction.

Fuel nozzle for gas turbine engine

Starting means for a gas turbine engine

A pressure atomizing fuel nozzle of the type that has a primary and secondary fuel system for a gas turbine engine and includes air swirl means and water injection is designed so that the water laden airstream is swirling in the same direction as both the fuels egressing from the primary fuel system and the secondary fuel system.

Fuel nozzles with water injection for gas turbine engines

This invention relates to an improvement of the cooling air flow distribution in proximity to the combustion and dilution air holes of a combustor liner fabricated from Finwall.RTM. material for a turbine type power plant.

Combustor liner for gas turbine engine

Apparatus for supplying fuel to the combustion chamber of a gas turbine engine is disclosed. Techniques for increasing combustion efficiency and for decreasing the percentage of noxious emissions in the effluent from the chamber are developed. Axially extending tubes are used extensively in the disclosed embodiments of the invention for premixing gaseous or vaporized fuel with air in the supply means upstream of the combustion chamber. In addition to operation on natural gas and vaporized liquid fuels, the embodiments shown are adaptable to efficiently burn gasified coal fuels having heating values as low as 80 BTU per standard cubic foot (BTU/scf).

Growing community of inventors

South Windsor, CT, United States of America

Edmund E Striebel