General Electric Company

Steven C Steffens

Stanley Kevin Widener

Willard J Dodds

Adrian M Ablett

Valeria Proano Cadena

Howard L Foltz

Hubert S Roberts, Jr

Douglas Downey Turner

Keith K Taylor

Mark M Glevicky

Marco Venturato

Brian Michael Royer

Kevin W Pendery

Clyde R Draper

A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner that at least partially define a combustion chamber. The annular dome defines a plurality of circumferentially spaced fuel injection ports and a plurality of mounting assemblies are configured for receiving and supporting a plurality of fuel injector assemblies within the fuel injection ports. Each mounting assembly includes a ferrule positioned adjacent to and extending around a peripheral edge of the respective fuel injection port. A spring finger is coupled to an interior surface of the ferrule and extends toward a centerline of the fuel injection port to form a seal with the fuel injector assembly.

Combustor mounting assembly having a spring finger for forming a seal with a fuel injector assembly

A combustor dome assembly includes an annular support plate fixedly joined to a combustion liner which confines combustion gases. The support plate includes a plurality of circumferentially spaced support openings for supporting respective carburetors, and respective splashplates fixedly joined coaxially to each of the support openings. Each of the splashplates includes an intermediate flared portion spaced axially downstream from an intermediate portion of the support plate to define a plenum, and a distal end spaced radially away from the liner to define a circumferential extending outlet gap in flow communication with the plenum. The support plate intermediate portion has a plurality of impingement holes disposed between the support openings and a proximal end of the support plate for channeling a first portion of compressed air as impingement air into the plenum to impinge against the splashplate intermediate portion. A plurality of circumferentially spaced air slots are disposed between the support plate proximal end and the liner for channeling a second portion of the compressed air therethrough and into the plenum for mixing with spent impingement air to form a cooling air film extending from the outlet gap along the liner for film cooling thereof.

Combustor dome assembly

A method of diluting combustion gases in a gas turbine engine combustor includes injecting primary dilution air into the combustion gases, and injecting trim dilution air into the combustion gases adjacent to the injected primary dilution air. A dilution air injector for practicing the method includes a plate, or centerbody in an exemplary embodiment, having a primary dilution hole for injecting a portion of compressed air into combustion gases as primary dilution air, and a trim dilution hole for injecting a portion of the compressed air into the combustion gases as trim dilution air. The primary and trim dilution holes are sized and configured so that the primary and trim dilution air cooperate with each other for penetrating into and diluting a predetermined portion of the combustion gases.

Method and apparatus for injecting dilution air

A double dome combustor for a gas turbine engine includes first and second domes joined to outer and inner liners. The first and second domes are joined together by two load transmitting structural paths for providing increased rigidity of the first and second domes for accommodating pressure loading from compressed airflow. In one exemplary embodiment, a dome cowl having first and second cowls is used to additionally join together the first and second domes.

Double dome combustor

Growing community of inventors

Cincinnati, OH, United States of America

Steven C Steffens