General Electric Company

Gilbert Farmer

James Anthony Groeschen

Jeffrey Arnold Fehrenbach

James Michael Caldwell

Daniel Dale Brown

Myron Edward Rutherford

Steven Clayton Vise

Bhupendra Kumar Gupta

Thomas John Tomlinson

Marwan Al-Roub

Ronald Redden

William Lee Imhoff

Mehmet Muhittin Dede

Craig Douglas Young

Alan Majors Walker

Raymond William Heidorn

Jeffrey Michael Martini

Edward John Emilianowicz

Robert George Zimmerman, Jr

David Bruce Patterson

David Allen Kastrup

John Robert Staker

Mark Gerard Rettig

Ronald L Sheranko

Ella Christine Kutter

Shaun Michael DeVane

Steven Allen Stiverson

Edward Lee Howard

James Hollice Poynter

Gregory Thomas Lucas

Daniel Lee Durstock

Michael Philip Hagle

Thomas Anthony Leen

Stanford P Seto

William T Houchens

Jason Paul Hoppa

Karl S Fessenden

Tariq Kay Harris

Jerald M Kauffman

John Lawrence Vandike

Mohammad Ehteshami

Walter Byron Houchens, Iii

Xuenan Wang

James A Goreschen

Shaun M Devane

Thomas Carl Mills

Balena B Shorter

Walter Byron Houchens Iii

John L Vandike

A fabricated cowl for a double annular combustor of a gas turbine engine having a longitudinal axis extending therethrough, including an outer annular portion, an inner annular portion, and a middle annular portion. A plurality of circumferentially spaced radial slots are formed in at least one of the annular portions. The outer annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of outer radial members connecting the outer annular portion and the middle annular portion are provided between adjacent windows therein. Similarly, the inner annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of inner radial members connecting the inner annular portion and the middle annular portion are provided between adjacent windows therein. The cowl further includes a plurality of circumferentially spaced stiffening ribs, where each stiffening rib includes: a middle portion including a rear edge configured to substantially conform to a forward surface of the middle annular portion so that an area extending between the forward and rear edges is upstream of the middle annular portion; an outer portion including a forward edge configured to conform to a rear surface of the outer annular portion; and, an inner portion including a forward edge configured to conform to a rear surface of inner annular portion. The middle rib portion further includes a forward edge configured to extend through the radial slots when positioned in the middle annular portion, whereas the inner and outer rib portions further include a rear edge configured to extend through the radial slots when positioned in the inner and outer annular portions. Each stiffening rib is then connected to the inner, outer and middle annular portions.

Fabricated cowl for double annular combustor of a gas turbine engine

A method for adjusting the airflow in a turbine component having a plurality of airflow holes. The method comprises the step of depositing an overlay metallic coating on the surface of the turbine component in a manner such that at least some of the airflow holes are partially filled such that the volume of the partially filled airflow holes is changed so as to adjust the airflow through the turbine component. Also provided is a turbine component having a plurality of airflow holes, at least some of the airflow holes being partially filled with the overlay metallic coating to change the volume thereof so as to adjust the airflow through the turbine component.

Adjusting airflow in turbine component by depositing overlay metallic coating

A combustor liner is provided having first and second annular bands which define an overlapping circumferential joint area, wherein a weld is disposed in the joint area encompassing substantially all of the axial length of the joint area. A method for producing such a combustor liner is also provided.

Combustor linear and method for making thereof

A method of fabricating a test model of a gas turbine engine combustor dome, and the test model produced thereby. The method entails individually stamping a plurality of dome wall segments and first and second mounting band segments. Each wall segment comprises at least one cup between radially inward and outward edges of the wall segment, and an opening in the cup. At least one wall segment and its two corresponding mounting band segments are placed on a fixture that locates the opening of the wall segment, locates the first and second mounting band segments at the radially-inward and outward edges of the wall segment, and orients the wall segment to establish a dome angle of the fixtured dome assembly. The wall segment and mounting band segments are then joined while the fixtured dome assembly remains on the fixture to form at least a unitary sector of the test model.

Test model for a gas turbine combustor dome and method of fabricating

A process of removing deposits from through-holes in a component, such as metallic bond coat and ceramic materials from cooling holes in an air-cooled gas turbine engine. The process is particularly effective in removing a TBC material deposited in a cooling hole of a component as a result of depositing a coating of the TBC material on a surface of the component, in which the deposit is removed from the cooling hole without damaging the cooling hole or the TBC coating surrounding the cooling hole on the coated surface of the component. A preferred feature is that the cooling hole, including the entrance to the hole at a surface of the component opposite the coated surface and the coating surrounding the exit of the hole at the coated surface, exhibits improved surface characteristics that increase the discharge coefficient of the cooling hole, as evidenced by an increase in the effective area of the cooling hole.

Coated component with through-hole having improved surface finish

A method facilitates replacing a portion of a gas turbine engine combustor. The combustor includes a combustor liner and a wire-wrapped cowl assembly that includes an inner cowl and an outer cowl. The method comprises cutting through the wire-wrapped cowl assembly upstream from fastener openings used to couple the inner and outer cowls to the combustor liner, removing a portion of the cowl assembly from the combustor, and coupling a replacement cowl to the portion of the existing cowl assembly that is downstream from the cut, wherein the replacement cowl includes an inner annular portion, an outer annular portion, and a plurality of circumferentially-spaced radial ligaments extending therebetween.

Outer and inner cowl-wire wrap to one piece cowl conversion

A method of stripping coating from a portion of a coated surface of a component. The method includes fastening a mask sheet to the component over a region adjacent the portion of the coated surface. The mask sheet has a contour generally corresponding to a contour of the surface of the component. A high pressure fluid jet is sprayed from a spray head toward the portion of the coated surface after the mask sheet is fastened to the component to strip the coating from the portion of the surface. After the coating is stripped from the portion of the surface, the mask sheet is removed from the component.

Apparatus for stripping coating

A combustor for a gas turbine engine having a longitudinal axis extending therethrough, including an inner liner, an outer liner spaced radially from the inner liner, an annular dome connected to the inner and outer liners, a plurality of air/fuel mixers connected to the dome and circumferentially spaced within the dome, an outer cowl connected to the outer liner, and an inner cowl connected to the inner liner, wherein a combustion chamber is formed by the inner liner, the outer liner and the dome. The dome further includes a first end connected to a liner of the combustor, a second end spaced radially from the first end, a first portion extending rearwardly from the first end adjacent the liner, a second portion extending rearwardly from the second end and flaring radially outward from the longitudinal axis, and a nonlinear third portion connecting the first and second dome portions.

Combustor dome for gas turbine engine

A cowl for use with a combustor of a gas turbine engine, the cowl includes a main body with an annular corrugation. A combustor of a gas turbine engine, the combustor includes: a hollow body defining a combustion chamber, the hollow body having a liner; an outer cowl having an annular corrugation, the cowl connecting to the liner; and an inner cowl connecting to the liner. A method of configuring a cowl for a gas turbine engine combustor, the method includes forming an annular corrugation in a main body of the cowl.

Corrugated cowl for combustor of a gas turbine engine and method for configuring same

Process of removing a coating deposit from a through-hole in a component and component processed thereby

An annular one-piece liner for a combustor of a gas turbine engine, including a first end adjacent to an upstream end of the combustor, a second end adjacent to a downstream end of the combustor, and a plurality of corrugations between the first and second ends, each corrugation having an amplitude and a wavelength between an adjacent corrugation, wherein the amplitude of the corrugations and/or the wavelength between adjacent corrugations is variable from the first end to the second end.

Annular one-piece corrugated liner for combustor of a gas turbine engine

A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located either forward or aft of the slot film cooling portion, depending on the nature of the combustor that the liner is to be used in. In one possible embodiment, the liner includes a first annular panel, a second annular panel section joined at its forward end to the aft end of the first panel section, and a third annular panel section being joined at its forward end to the aft end of the second panel section. At least one of the panel sections has multi-hole film cooling and at least one other of the panel sections has slot film cooling.

Hybrid film cooled combustor liner

A multi-hole cooled combustor liner is provided which reduces hot streaks and associated material distress in the liner. Areas of increased cooling hole density are disposed upstream of the primary dilution holes and in circumferential alignment with fuel cup centers. Additional cooling holes are provided in between primary dilution holes are arranged in alternating pairs of circumferentially angled holes so as to provide a converging cooling air flow in the downstream direction.

Preferential multihole combustor liner

Combustor liner and method for making thereof

A method for fabricating a three-dimensional turbine engine combustor liner model includes coupling at least a first member to a second member to form an assembly that has an inner surface. The assembly inner surface simulates an inner surface of the aircraft engine combustor liner. The first member is at least one of a pre-formed conical member and a pre-formed cylindrical member, and the second portion is at least one of a pre-formed conical member and a pre-formed cylindrical member. The method also includes coupling the assembly to a baseplate, and coupling a plurality of templates to the assembly.

Methods and apparatus for modeling gas turbine engine combustor liners

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Cincinnati, OH, United States of America

Gilbert Farmer