General Electric Company

Daniel Dale Brown

Gilbert Farmer

Michael Terry Bucaro

Myron Edward Rutherford

Steven Clayton Vise

Craig Douglas Young

Glenn Edward Wiehe

James Thompson

Donald Michael Corsmeier

John Alan Manteiga

Duane Douglas Thomsen

Daniel J Kirtley

Mark Willard Marusko

John Christopher Brauer

Donald Lee Gardner

Jeffrey Michael Martini

Donald Scott Yeager

Gerardo Antonio Salazar Lois

David Bruce Patterson

Thomas Anthony Leen

Marwan Al-Roub

Steven Marakovits

Paul R Angel

Baha Mahmoud Suleiman

Joseph G Sabato

Ronald T Murach

Mina Dimov

Ella Christine Kutter

Stephen William Freund

Mohammad Ehteshami

Marlin S Brueggert

Michael Joseph Zerbe

Kevin W Raabe

Jeff Martini

A combustor for a gas turbine includes a cowl structure, a pseudo-dome structure, a ceramic matrix composite (CMC) dome, and a swirler assembly. The swirler assembly is connected to the pseudo-dome structure, which is connected to the cowl structure, and the CMC dome is separately connected to the cowl structure apart from the swirler assembly. The swirler assembly includes a swirler dome interface wall that interfaces with the CMC dome on an upstream side of the CMC dome, and a swirler outlet extends through a CMC dome swirler opening through the CMC dome.

Combustor swirler to pseudo-dome attachment and interface with a CMC dome

A method of assembling a combustion system for a gas turbine engine includes providing a combustion chamber frame, an inner casing structure, and an outer casing structure. The method also includes mounting the combustion chamber frame between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.

Combustion system and method of assembling the same

A combustor dome assembly includes a dome plate with upstream and downstream faces and an aperture therein; a deflector with body and a tube section, the deflector fixedly attached to the dome plate adjacent the downstream face with the tube section in the aperture; a retainer having an annular body with a central opening therein, an annular flange, and at least one hook defining a slot, the retainer being fixedly attached to the dome plate adjacent the upstream face of the dome plate with the flange received in the aperture; and an annular mixer with a radial array of swirl vanes and an annular mounting flange, with a retention tab extending radially outward from the mounting flange. The mixer is disposed adjacent the upstream face with the mounting flange against the retainer. The retention tab is engaged in the slot to prevent axial withdrawal of the mixer from the retainer.

Combustor dome with combined deflector/mixer retainer

A method of assembling a combustor for use in a turbine engine is disclosed. The method includes providing a dome assembly ring including a plurality of assembly ring openings, positioning a plurality of elongated rings on the dome assembly ring, providing a cowl assembly including an inner cowl portion and an outer cowl portion that are fabricated from sheet metal, and coupling the inner and outer cowl portions to the dome assembly ring such that each of the plurality of elongated rings is coupled to the dome assembly ring.

Combustor dome mixer retaining means

A method of assembling a dome assembly for use in a turbine engine combustor is disclosed. The method includes providing a dome assembly ring, an inner liner portion, and an outer liner portion. The method also includes coupling the inner liner portion and the outer liner portion to the dome assembly ring, positioning a plurality of rings on the dome assembly ring, and coupling at least one of an inner cowl and an outer cowl to the dome assembly ring such that each of the plurality of rings and at least one of the inner and outer cowls are removable without uncoupling the dome assembly ring from either the inner or outer liner portions.

Combustor dome and methods of assembling such

A combustor liner includes a liner having an upstream end and a downstream end having a longitudinal axis extending therethrough, and a plurality of cooling holes formed in the liner, the cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows that are variably spaced apart along the longitudinal axis.

Combustor liner and method of fabricating same

A method for assembling a gas turbine engine is provided. The method includes providing a combustor liner support including a first portion formed with a plurality of circumferentially-spaced recessed areas, and a second portion extending from the first portion. The method also includes coupling the combustor liner support within a combustor such that during engine operations cooling air is channeled through the plurality of recessed areas to facilitate cooling the combustor liner support.

Methods and apparatus for assembling gas turbine engines

A method enables a gas turbine engine multi-domed combustor including an outer liner and an inner liner that define a combustion chamber therebetween to be assembled. The method comprises coupling a first dome including a heat shield that includes an annular endbody that extends a first distance axially from the heat shield to the combustor outer liner, and coupling a second dome including a heat shield that includes an annular endbody that extends a second distance axially from the heat shield to the first dome, such that the second dome is radially aligned with respect to the first dome, and wherein the second dome second distance is less than the first dome first distance.

Methods and apparatus for operating gas turbine engines

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

An annular gas turbine engine combustor liner has a single piece annular shell circumscribed about a first axis of revolution. The shell has a hot side and a cold side, an annular dilution hole section, and a plurality of asymmetrical cylindrical dilution holes extending through the section. Pockets are circumferentially interdigitated between the dilution holes and extend into the shell from the cold side such that the pockets form dilution hole bosses between the pockets through which the dilution holes extend. Each of the dilution holes is circumscribed about a second axis of revolution which is not parallel to the first axis of revolution. The liner may further include forward and aft annular cooling nuggets located forward and aft of the dilution hole section and having annular film cooling slots which are open in the axially aftwardly direction. The shell is machined from a single piece integrally formed near net shape form such as a forging, a casting, or more particularly a spin or centrifugal casting. The invention includes a method for making the annular gas turbine engine combustor liner by forming a single piece integrally formed near net shape form and machining it to produce the shell and the above features in the shell.

Gas turbine combustor liner with asymmetric dilution holes machined from a single piece form

A heat shield for a gas turbine engine combustor of the type composed of multiple annular stages. The heat shield is particularly adapted for use in a middle stage disposed between radially inward and outward stages of a multistage combustor, and configured to form centerbodies that isolate the middle stage from the other stages of the combustor. The heat shield is composed of an annular array of single crystal superalloy segments. To achieve acceptable levels of durability for the superalloy segments, their primary and secondary crystal orientations are controlled to achieve a balance between the ability to withstand thermally-induced stresses and those stresses induced by high levels of acoustic energy, particularly those high levels attained as a result of a combustor operating with lean fuel/air ratios.

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Cincinnati, OH, United States of America

Daniel Dale Brown