An assembly for a turbomachine can include a fuel nozzle and a combustion liner. The fuel nozzle and the combustion liner can be attached to each using a plurality of clip joints such that the combustion liner is longitudinally fixed relative to the fuel nozzle but such that the combustion liner can radially move relative to the fuel nozzle.

A sleeve assembly for a combustion system includes a first duct including a first circumferential surface and a second duct including a second circumferential surface. The first circumferential surface radially overlaps the second circumferential surface such that the first duct and the second duct collectively define a continuous combustion chamber therein. The continuous combustion chamber is configured to receive high temperature gases flowing therethrough. The sleeve assembly further includes a wear insert removably coupled to the first circumferential surface and extending radially therefrom to engage the second circumferential surface.

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.

A gas turbine combustor includes a burner composed of a fuel nozzle group having a plurality of fuel nozzles for fuel supply, a fuel nozzle plate structurally supporting the fuel nozzles and serving to distribute the fuel flowing from an upstream side to the fuel nozzles, and a perforated plate located downstream of the fuel nozzles and having nozzle holes corresponding to the fuel nozzles. The fuel nozzle group includes outer circumferential fuel nozzles and inner circumferential fuel nozzles. Each outer diameter of at least a proximal end of the outer circumferential fuel nozzles is larger than that of the inner circumferential fuel nozzles.

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 embodiment prevents the buckling of a combustor liner without causing any increase in thermal stress when applied to a plant that uses supercritical carbon dioxide as a working fluid. A gas turbine combustor includes: a fuel nozzle; a cylindrical combustor liner provided downstream of the fuel nozzle; and a transition piece provided downstream of the combustor liner to guide a fuel gas to a gas turbine stator blade, wherein the combustor liner is divided into and composed of a plurality of liner composing members which are coupled in an axial direction.

An aft heat shield for a fuel nozzle tip includes: an annular shield wall; an annular shield flange extending radially outward from an aft end of the shield wall; an annular baffle flange surrounding the conical section, and disposed such that an axial gap is defined between the shield flange and the baffle flange, the baffle flange including a radially outer rim extending axially forward therefrom; and a plurality of impingement cooling holes passing through the baffle flange and oriented to as to direct air flow towards the shield wall.

A heat shield assembly of a combustion chamber has a supporting structure and heat shield elements arranged on the supporting structure. For fastening, the supporting structure has spring devices fastened therein, into each of which a fastening bolt can be screwed. In order to realize the pre-installation and the later removal of the spring elements contained in the spring device, at a holding sleeve, a contact plate is removably fastened in the holding sleeve on the side facing the heat shield element and a stationary securing plate is arranged on the opposite side.

A gas turbo machine having a combustion chamber. The combustion chamber includes a chamber bottom having an upstream wall and a downstream wall extending between inner and outer annular walls. Each upstream and downstream walls each having openings for mounting fuel injection devices for injecting fuel through said openings. The downstream wall is sectorised.

A fuel injector for a gas turbine engine of an aircraft having a fuel nozzle including a fuel swirler and/or an outer air swirler. The fuel swirler may include a manifold for receiving fuel from a fuel conduit, and a plurality of fuel passages to direct fuel from the manifold to discharge orifices that direct fuel with swirling flow. The fuel swirler may be configured to provide uniform spray while minimizing recirculation zones; reduce residence time as fuel enters the manifold; minimize flow disruptions, boundary layer growth, and/or pressure drop as fuel flows through the fuel passages; reduces coking internally of the nozzle; reduces thermal stresses; and is simple and low-cost to manufacture. The outer air swirler may include first and second outer air swirler portions with respective vanes and air passages that provide swirling air flow. The outer air swirler may be configured to improve atomization and spray uniformity with a wide spray angle; and minimize flow disruptions for enhancing flow performance.