In a combustor for a gas turbine engine, a radially outer end part of a dilution air introduction passage is radially slidably fitted into an inner periphery of an outer opening. A radially inner end part of the passage axially slidably abuts against an open edge of an inner opening. Therefore, even if outer and inner wall parts undergo relative movement in radial or axial direction due to difference in thermal expansion amount, it is possible to prevent occurrence of excessive stress and ensure airtightness for the outer and inner openings, stabilizing amount of dilution air introduced into a combustion chamber. Air does not leak into space between the outer and inner wall parts from the radially outer end part, therefore, air jet passing through an impingement cooling hole of the outer wall part collides with the inner wall part without disturbed, enhancing cooling effect of the inner wall part.

In a gas turbine engine, an inside turn duct portion and a nozzle guide vane are engaged together via an engagement part. An axially forward-facing load acting on a reverse flow combustor is transmitted to the vane via the engagement part. Therefore, it is possible to counteract an axially backward-facing load acting on the vane from combustion gas with the axially forward-facing load, thus reducing a bending moment acting on a support part of the vane and enhancing durability. Furthermore, part of the axially forward-facing load acting on the combustor acts on the support part via the vane. The axially forward-facing load acting on the support part of the combustor without via the vane is decreased by the above-mentioned part. Thus, it is possible to reduce bending moments acting on an outside turn duct portion and dome portion of the combustor and enhance durability, thereby preventing degradation of combustion performance.

A gas turbine engine may include a combustor having an inner wall and an outer wall defining a combustion chamber there between. The inner wall and the outer wall may each have at least one opening into the combustion chamber. The gas turbine engine may also include at least one mobile conduit through which a cooling fluid may flow. The mobile conduit may pass through the combustion chamber from the at least one opening in the outer wall to the at least one opening in the inner wall. The gas turbine engine may further include a first joint and a second joint fluidly connecting the mobile conduit to the at least one opening in the inner wall and the at least one opening in the outer wall, respectively. The first joint and the second joint may enable multiple degrees of freedom of the mobile conduit within the combustion chamber.

A gas turbine includes a compressor, a combustor, and a turbine. The compressor, the combustor, and the turbine are arranged along an extending direction of a rotating shaft. The gas turbine also includes a combustor casing housing the combustor and a turbine casing housing the turbine. The combustor casing and the turbine casing are joined to each other via respective flanges thereof projecting toward the outside. The gas turbine further includes a projection part on an inner face of the combustor casing. The projection part projects toward the inside in a radial direction in at least part of a range in the extending direction of the rotating shaft between the flanges and an end of a combustion chamber on the compressor side in the combustor.

The present invention reduces thermal stress that is applied to the weld zone of a cavity formed in the structural material of a burner. The burner includes the cavity distributing a fuel to fuel nozzles. The cavity is demarcated by a groove formed in the structural material of the burner so as to create a level difference at an opening, and a cover fitted into the level difference to close the groove. The cover is formed by a web covering the opening in the groove and a flange extending in the depth direction of the groove to be fitted into the level difference, and is joined by welding to the structural material in such a manner as to have an L-shaped cross-section. When viewed in a cross-section orthogonal to the groove, a cover-side inner surface that is an inner surface of the flange forming a lateral surface of the cavity is flush with a groove-side inner surface that is an inner surface of the groove forming a lateral surface of the cavity. The boundary between the cover-side inner surface and the groove-side inner surface is away from a first corner of the cavity sandwiched between the cover-side inner surface and the inner surface of the web forming a ceiling surface of the cavity.

The present invention reduces the concentration of thermal stress on a burner. A gas turbine combustor receiving compressed air from a compressor, mixing the compressed air with a fuel, burning the mixture to generate a combustion gas, and supplying the combustion gas to a turbine. The combustor includes: an inner cylinder internally forming a combustion chamber; an outer cylinder covering the inner cylinder and forming a cylindrical outer circumferential flow path between the inner and outer cylinders to allow the compressed air to flow; and a burner mounted on an end of the outer cylinder, which is positioned on an opposite side to a turbine side, and facing the combustion chamber. The burner includes a cylindrical base frame including a cavity distributing the fuel, and fuel nozzles circularly arranged as viewed from the combustion chamber and connected to the cavity. When viewed from the combustion chamber, slits extending radially are formed in the base frame such that each separate the circumferentially adjacent fuel nozzles from each other.

An annular combustor is disclosed in which free-vortices are generated which: enhance fuel air mixing, recirculate the air, provide cooling for the combustor walls, and provide low emissions and a substantially uniform exit temperature profile. The combustor is provided fuel and air through a plurality of fuel injectors which atomizes the fuel and promote individual vortices emanating from each injector. The combustor includes an annular prechamber, an annular main chamber, and an annular dilution zone. A first swirler is provided on the inner side of the annular prechamber and a second swirler on the outer side of the annular prechamber, the swirlers causing flow to rotate in mutually opposite directions to intensify the vortices imposed by the injectors. The vortices cause a pressure depression to promote some backflow that enhance mixing to: promote complete combustion, produce low emissions, and provide cooling.

A nozzle assembly includes a fuel distributor for issuing a spray of fuel. A fuel conduit is in fluid communication with the fuel distributor and has a first end and a second end. The first end and/or the second end of the fuel conduit is operatively connected to the fuel distributor. The fuel conduit is configured to allow relative movement between the first end and the second end to accommodate dimensional variations of at least one of the nozzle assembly or a combustor. A nozzle system includes the nozzle assembly and a combustor wall having a nozzle inlet. The nozzle assembly is positioned adjacent to the nozzle inlet.

A heat shield panel for use in a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side, a cold side and at least one attachment mechanism having a stud and a central axis extending through the stud and a plurality of standoff pins positioned circumferentially around the stud, the standoff pins having a radial extent, a circumferential extent that is greater than the radial extent, a radially outer surface having a radially convex shape and a radially inner surface having a radially concave shape.

A combustion chamber assembly comprises an annular combustion chamber casing, a combustion chamber, a fuel injector and a tubular seal. The combustion chamber comprises an upstream end wall having an aperture extending there-through. A fuel injector head of the fuel injector is locatable in the aperture in the end wall and the fuel injector head has an axis. The tubular seal is positioned between the fuel injector head and the aperture in the end wall and the tubular seal has a flange and an aperture extends there-through. The tubular seal is movable radially and circumferentially with respect to the axis of the casing. The fuel injector head is locatable in the tubular seal. The aperture in the upstream end wall has a major radial dimension and a minor circumferential dimension relative to the axis of the casing to allow insertion or removal of a lean burn fuel injector head.