Abstract: An improved gas turbine engine combustor with a liner and a dome connected to the liner trough small radius transition portions only, the dome having a plurality of fuel nozzles mounted therein and an interior directly exposed to a combustion region of the combustor, the dome including a plurality of effusion cooling holes provided non-perpendicularly to an entry surface of the holes, the dome being substantially planar.

Abstract: A seal for sealing a combustor heat shield against an interior surface of a combustor shell, the seal comprising: an upstream rail and an downstream rail defining an intermediate groove therebetween, each rail having a sealing surface with a plurality of slots extending between an upstream wall surface and a downstream wall surface, the sealing surface conforming to the interior surface of the combustor shell and defining a leakage gap therebetween.

Abstract: A gas turbine engine combustor having a dome heat shield includes a cooling scheme having a plurality of impingement cooling holes extending through the combustor and a plurality of adjacent ejector holes for directing cooling air past the heat shield lips of the dome heat shields. The impingement and ejector holes are preferably staggered to reduce interaction therebetween.

Abstract: A combustor heat shield comprises a heat shield member defining at least one opening for receiving a fuel nozzle. A louver is received in the opening. The louver has a flow diverting portion extending radially outwardly from the opening for directing air along the hot side of the heat shield member.

Abstract: A gas turbine engine combustor includes a liner having a dome portion with a plurality of openings defined therein for receiving fuel nozzles and a plurality of holes defined around each opening. The holes directing air into the combustion chamber in a spiral pattern around an axis along which fuel is injected into the combustor by the fuel nozzles.

Abstract: A gas turbine engine combustor has a dome and a shell extending axially from the dome. The dome and the shell cooperates to define a combustion chamber. A dome heat shield is mounted to the dome inside the combustion chamber. A front heat shield is mounted to the shell inside the combustion chamber. The dome heat shield and the front heat shield have axially overlapping portions cooperating to define a flow guiding channel. The flow guiding channel has a length (L) and a height (h). The length (L) is at least equal to the height (h).

Abstract: A gas turbine engine with: a compressor section; a turbine section; a combustor, disposed between the compressor and turbine sections, having at least one combustor mounting assembly connecting the combustor to the engine. Each combustor mounting assembly has: a longitudinal axis; and an articulating joint having a first and second portion constrained from relative translation transverse to the longitudinal axis, and where said first and second portion have a multiple rotational degrees of freedom relative to each other about axes transverse to the longitudinal axis.

Abstract: A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening with outlet openings fed by a channel in flow communication between each outlet opening and the inlet opening. Preferably, the circumferential member is made of arcuate segments of cast metal removably mounted to the interior surface of the combustor wall with threaded studs.

Abstract: A combustor wall louver for ducting a flow of compressed air through an inlet opening in the combustor wall from a source of compressed air outside the combustor where the louver is a circumferentially extending member, mounted to an interior surface of the combustor wall and covering the inlet opening with outlet openings fed by a channel in flow communication between each outlet opening and the inlet opening. Preferably, the circumferential member is made of arcuate segments of cast metal removably mounted to the interior surface of the combustor wall with threaded studs.

Abstract: A combustor heat shield assembly comprises a circumferential array of heat shield panels individually mounted to an inner surface of a combustor shell. Each heat shield panel has opposed front and back faces, the back face facing the inner surface of the combustor shell and being spaced therefrom to define an air gap. The front and back faces have a perimeter including opposed lateral edges extending between opposed circumferentially extending edges. The lateral edges of adjacent heat shield panels have complementary non-linear profiles defining an asymmetric heat shield panel interface.

Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.

Abstract: The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine by one or more fastening elements that are integrally formed with the annular ring. The fastening elements are mountable with corresponding features of the support element and removably fastened thereto.

Abstract: A combustor liner including a dome section having a positioning hole defined at a first radial distance and sized to receive a first heat shield fastener to at least substantially prevent radial and circumferential motion of the first fastener, a circumferential slot sized to receive a second heat shield fastener to at least substantially prevent radial motion of the second fastener while allowing limited circumferential motion of the second fastener, and a clearance hole defined at a second radial distance and sized to receive a third heat shield fastener to allow limited radial and circumferential motion of the third fastener.

Abstract: A combustor for a gas turbine engine includes an annular combustor shell having an inner liner and an outer liner respectively with inner and outer flanges at least partly overlapping to form a dome end portion of the shell, at least the outer flange including intersecting upstream and downstream wall portions defining a corner therebetween, the upstream wall portion having a plurality of cooling apertures defined therethrough immediately upstream of the corner, and the cooling apertures being oriented to direct a cooling air flow from outside the combustor shell therethrough and adjacent an inner surface of the downstream wall portion.

Abstract: A combustor liner for a gas turbine engine including first and second annular liner portions engaged to one another with an interference fit. The first liner portion includes at least one anti-rotation feature extending therefrom and engaging the second liner portion and having a threaded hole defined therethrough at least substantially perpendicularly to an adjacent radially extending surface of the second liner portion for threadingly receiving a pushing tool for pushing against that surface.

Abstract: A combustor heat shield has a body defining a fuel nozzle hole. The back face of the body is mounted adjacent and spaced-apart from a combustor dome. A ridge extends around the nozzle opening to a height adapted to substantially contact the combustor dome. The ridge thereby defines a cooling compartment between the body and the combustor dome. A plurality of slots is provided through the ridge. The slots are closed by the combustor dome to provide cooling holes when the heat shield is mounted on the combustor. The cooling holes direct pressurized cooling air from the compartment to adjacent regions of the back face of the heat shield body.

Abstract: A combustor for a gas turbine engine including a combustor shell, a heat shield mounted to the combustor shell spaced-apart from the combustor shell to define an air gap therebetween, a core dilution passageway extending through the combustor shell and the heat shield, and a sub-chamber disposed within the air gap in fluid communication with the core dilution passageway. The sub-chamber is separated from a remainder of the air gap by at least one intermediate rail projecting across the air gap and forming an outer boundary of a peripheral area of the core dilution passageway. Impingement holes are formed through the combustor shell and in fluid communication with the sub-chamber. A method of cooling an area surrounding a dilution hole in a combustor is also presented.

Abstract: A gas turbine engine combustor has a shell defining a combustion chamber having a primary zone and a dilution zone downstream of the primary zone. The shell has an outer skin and an inner skin defining an air gap therebetween. The inner skin in the upstream portion of the primary zone is free from effusion holes and has heat transfer augmenters projecting from a back side thereof into the air gap. Effusion holes in the inner skin are only disposed downstream towards the tail end of the primary zone in order to delay the injection of any disruptive cooling air that could potentially interfere with the combustion process.

Abstract: A combustor for a gas turbine engine having an inner combustor wall and an outer combustor wall with a number of heat shields mounted internally thereto with fasteners. Each combustor wall has an end wall defining a combustor dome with a number of: fuel nozzle openings; impingement air openings; and heat shield fastener openings. Each of the end walls has an overlapping portion with mutually engaging sealing surfaces with the openings within the overlapping portions being aligned in overlapping pairs, where an exterior overlapping portion has at least one of the aligned openings of one overlapping pair being of larger dimension than the aligned opening in an interior overlapping portion.

Abstract: A combustor heat shield for a gas turbine engine has a heat shield panel adapted to be mounted to an inner surface of a combustor shell with a back face of the panel spaced-apart from the combustor shell to define an air gap therewith. Studs project from the back face of the panel for engagement in corresponding mounting holes defined in the combustor shell. Each stud has a threaded distal end portion for engagement with a nut outside of the combustor shell. At least one of the studs has a channel defined in a peripheral surface thereof. The channel extends longitudinally along the stud from an inlet end connectable to a source of cooling air outside of the combustor shell to an outlet end disposed within the air gap for locally providing cooling air at the base of the stud.