General Electric Company

Gerardo Antonio Salazar Lois

Daniel J Kirtley

Shai Birmaher

Ryan Christopher Jones

Nicholas John Bloom

Gregory Allen Boardman

Hejie Li

Jeffrey Michael Martini

Rishikesh Prakash Karande

Trevor James Hahm

Pradeep Naik

Clayton Stuart Cooper

Mark Anthony Mueller

Daniel Dale Brown

Anquan Wang

Scott Matthew Bush

Ahmed Mostafa ELKady

Adam Robert Kahn

Nan Zong

Bassam Sabry Mohammad Abd El-Nabi

Nathan Richard Hermanson

Rajesh Sharma

A combustor for a gas turbine engine includes a dome-deflector structure and a fuel nozzle-swirler assembly having a mounting wall with a plurality of purge orifices extending therethrough. A circumferential purge cavity is defined between a fuel nozzle-swirler assembly housing, a fuel nozzle-swirler assembly opening of the dome-deflector structure, and the mounting wall. The purge orifices provide a purge airflow to the circumferential purge cavity. In a first state, when a radial height of the circumferential purge cavity is constant, the dome-deflector structure overlaps a portion of the purge orifices to block a portion of each purge orifice, and, in a second state when the fuel nozzle-swirler assembly is radially shifted, the dome-deflector structure increases blockage of at least one purge orifice on a second side of the circumferential purge cavity, and reduces blockage of at least one purge orifice on a first side of the circumferential purge cavity.

Combustor for a gas turbine engine

A combustor for a gas turbine engine includes a ceramic matrix composite (CMC) dome structure, a CMC outer liner, a CMC inner liner, and a cowl structure, that are connected together via at least one outer connection and at least one inner connection. An outer seal member is arranged to seal an outer gap between an outer liner connecting flange and an outer dome connecting flange, and an inner seal member is arranged to seal an inner gap between an inner liner connecting flange and an inner dome connecting flange.

Gas turbine engine combustor having a ceramic matrix composite liner and dome

A combustor of a turbine engine combusts fuel and air. The combustor includes a dome and a heat shield fastened to the dome. The heat shield is unconstrained relative to dome, to permit relative thermal expansion and contraction in a radial direction. A heat shield inner portion is generally annular in shape, is arranged about a dome eyelet longitudinal centerline axis, is smaller in diameter than a dome inner portion, and is assembled inside of the dome inner portion. A plurality of pinned assemblies fastens the heat shield to dome. Each pinned assembly includes a fastener with a pin end, the pin end assembled in a clearance fit into a hole in the heat shield inner portion. The fastener is fixed to the dome inner portion, the pin end sliding in the hole in the heat shield during relative thermal expansion and contraction between the dome and the heat shield.

Combustor including a heat shield for a turbine engine

A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome including a swirler opening therethrough with a flare interface surface surrounding the swirler opening, a swirler assembly including (a) a secondary swirler having a threaded flare attachment portion, and (b) a flare having (i) a threaded secondary swirler attachment portion, and (ii) a dome interface wall that interfaces with the flare interface surface of the CMC dome, and a swirler-dome attachment member. The flare is connected to the secondary swirler via the threaded flare attachment portion and the threaded secondary swirler attachment portion, and the swirler-dome attachment member applies a force to the CMC dome to engage the dome interface wall and the flare interface surface so as to connect the CMC dome and the swirler assembly.

Combustor swirler to dome attachment

A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.

Ceramic composite combustor dome and liners

A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome with a swirler mounting wall formed integral with the CMC dome, and a swirler assembly including a plurality of clevis dome attachment members for connecting the swirler assembly to the CMC dome. Bushings are arranged within a plurality of dome-side swirler assembly mounting openings of the swirler mounting wall, and the CMC dome is arranged within respective ones of the plurality of clevis dome attachment members of the swirler assembly. A swirler-dome connecting member is disposed through each of the clevis dome attachment members so as to mount the swirler assembly to the CMC dome.

Combustor swirler to CMC dome attachment

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 system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.

System and method having annular flow path architecture

A system includes a fuel nozzle including a first wall disposed about a central axis, a second wall disposed about the first wall, and a plurality of lobes disposed between the first and second walls, wherein the plurality of lobes is spaced about the central axis to define a plurality of flow passages, and the plurality of flow passages is configured to output a plurality of flows into a flame region.

Fuel nozzle assembly

A micromixer system includes a casing having a first side wall and a second side wall. Further, the micromixer system includes a plurality of pipes spaced apart from each other and disposed within the casing. Each pipe includes an inlet and an outlet formed in the first and second side walls respectively. The micromixer system includes a first plenum having a first inlet formed in the casing. The first plenum is disposed around a first portion of the plurality of pipes and fluidically coupled to the plurality of pipes. The micromixer system includes a second plenum having a second inlet formed in the casing and disposed around a second portion of the plurality of pipes. Further, the micromixer system includes a plurality of openings formed in the second side wall, surrounding the outlets of at least some pipes of the plurality of pipes, and fluidically coupled to the second plenum.

Growing community of inventors

West Chester, OH, United States of America

Gerardo Antonio Salazar Lois