General Electric Company

George Eric Moertle

Peter W Mueller

Clifford Stephen Creevy

Scott Brensike

Arthur Wesley Johnson

Allen Michael Danis

Bhupendra Kumar Gupta

Raymond William Heidorn

Edward Charles Vickers

David Louis Burrus

Mark Anthony Mueller

David Albin Lind

Edward John Emilianowicz

Thomas John Tomlinson

Shui-chi Li

Ahmed Mostafa ELKady

Mark M Glevicky

Thomas George Holland

Scott Howard Pelletier

Tariq Kay Harris

Bruce Ernest Mills

James Patrick Holmes

Tariz Kay Harris

Eric Matthew Roberson

Ray Heidorn

Tom Tomlinson

A gas turbine engine combustor conical-flat heat shield includes an annular conical section extending upstream from and being integral with a flat section with a flat downstream facing surface which may be generally perpendicular to or canted with respect to a centerline. The flat section includes radially outer and inner edges at least one of which is circular and circumscribed about a centerline and circumferentially spaced apart clockwise and counter-clockwise radial edges having an origin on the centerline. A gas turbine engine combustor includes conical-flat heat shields in one or more circular rows arranged in a non-symmetrical or asymmetrical pattern. Two or more groups (A, B, C) of the conical-flat heat shields in the circular rows may be mounted on a domeplate and one or more of the conical-flat heat shields is different in one or more of the groups (A, B, C).

Conical-flat heat shield for gas turbine engine combustor dome

A method for applying a thermal barrier coating to an article having cooling holes and concurrently cleaning obstructions, such as TBC overspray or other debris, from those holes is disclosed. A thermal barrier coating is applied to a first surface of an article having cooling holes. Concurrently therewith, a plurality of particles are projected against a second surface of the article, such that at least some of the particles pass through the cooling holes, strike the overspray constituents prior to cooling, knocking at least some of the obstructions out of the cooling hole.

Method for concurrent thermal spray and cooling hole cleaning

A liner for a combustor of a gas turbine engine, including a shell having a first end adjacent to an upstream end of the combustor and a second end adjacent to a downstream end of the combustor, wherein at least one discrete region is subject to distress from impingement of hot gases, a plurality of cooling slots formed in the shell through which air flows for providing a cooling film along a hot side of the shell, and a group of cooling holes formed in the shell in the discrete region to augment the cooling film and provide convective bore cooling to the discrete region.

Multihole patch for combustor liner of a gas turbine engine

A method enables replacement of a gas turbine engine combustor liner. The combustor has a combustion zone formed by inner and outer liners. A plurality of cooling features are formed by overhanging portions of the inner and outer liner liners. The method comprises cutting through at least one of the combustor inner and outer liner aft of an overhanging portion, wherein the portion of the combustor liner upstream from the cut remains coupled within the combustor, removing the portion of the combustor liner that is aft of the cut, and installing a replacement liner within the combustor such that the replacement liner extends aftward from the portion of the combustor liner that is upstream from the cut.

Methods for replacing combustor liners

A fuel nozzle including a nozzle stem having an annular overhang and a heat shield secured to the overhang is described. More specifically, and in one embodiment, the nozzle stem includes an upstream end and a downstream end. The annular overhang is intermediate to the upstream end and the downstream end of the stem. The heat shield includes a first end and a second end, and the heat shield is welded to the annular overhang at the heat shield first end. An annular air gap is between the nozzle stem and the heat shield.

Methods for shielding heat from a fuel nozzle stem of a fuel nozzle

A liner for a gas turbine engine combustor, including an upstream section, a downstream section oriented at an angle to the upstream liner section, and a cooling nugget joining the upstream and downstream liner sections for providing mechanical stiffness at a junction of the upstream and downstream liner sections. The cooling nugget further includes a first portion connected to the upstream liner section, a second portion connected to the downstream liner section, and a third portion joining the first and second cooling nugget portions at a first end, the third cooling nugget portion extending radially from the first end, wherein the cooling nugget is in flow communication with a cool air supply and is configured to provide a starter film of cooling air along respective surfaces of the upstream liner section and the downstream liner section.

Cooling nugget for a liner of a gas turbine engine combustor having trapped vortex cavity

Methods and apparatus for shielding heat from a fuel nozzle stem of fuel

Growing community of inventors

Cincinnati, OH, United States of America

George Eric Moertle