Honeywell International Inc.

Terrel Kuhn

Rodolphe Dudebout

Gregory O Woodcock

Sunil James

Douglas P Freiberg

Lawrence A Kobold

Kenneth A Struzek

William G Freeman

Francis S Maszk

Jason Smoke

Frank Joseph Zupanc

Paul Yankowich

Bradley Reed Tucker

Vinayender Kuchana

Stony Kujala

Raymond Gage

Lowell Frye

Mario Scaini

Veeraraghave Raju Hasti

Sossity A Flamand

Veeraraghava Raju Hasti

A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.

Reverse-flow annular combustor for reduced emissions

A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.

A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.

Combustor-turbine seal interface for gas turbine engine

Methods are provided of forming a plurality of fan-shaped effusion holes on a combustor having a surface, each hole having an outlet on the combustor surface. The method may include rotating the combustor relative to a laser beam, and positioning the combustor to a first position where the laser beam is at a first predetermined angle relative to the combustor surface. The laser beam is pulsed at the combustor surface to form a first plurality of trepan cuts. The first predetermined angle is adjusted to a second position where the laser beam is at a second predetermined angle relative to the combustor surface. The laser beam is pulsed at each trepan cut of the first plurality of trepan cuts, to thereby form a cut for at least a portion of the fan shape of each effusion hole outlet, wherein each cut overlaps a trepan cut of the first plurality of trepan cuts.

Methods of forming fan-shaped effusion holes in combustors

A premix chamber for a combustor of a gas turbine engine comprises a cylindrical chamber having a premix chamber wall, the cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along a central axis, a chamber inlet plate in communication with the premix chamber wall at the chamber inlet end, the chamber inlet plate having a fuel nozzle inlet hole disposed through the chamber inlet plate, the chamber inlet plate further comprising a plurality of swirler passages disposed through the chamber inlet plate, and the chamber outlet end being open. A method of producing turbine gas is also disclosed.

Rich quick mix combustion system

A method for controlling combustor liner carbon formation on repaired combustors includes making modular effusion panel subassemblies remote from the combustor liner; removing a non-effusion or damaged panel from the combustor liner; and replacing the non-effusion or damaged panel with the modular effusion panel.

Method for controlling carbon formation on repaired combustor liners

An apparatus and method for controlling combustor liner carbon formation is provided. The apparatus includes a dome subassembly that is removeably affixed to a modular outer panel subassembly and a modular inner panel subassembly. Each panel subassembly includes panels that are removeably affixed to one another.

Apparatus and method for controlling combustor liner carbon formation

Growing community of inventors

Mesa, AZ, United States of America

Terrel Kuhn