Abstract: A nozzle guide vane support arrangement including a platform portion of a nozzle guide vane at a trailing edge is provided, the platform portion having a platform wall including a first platform wall portion and a second platform wall portion. A working fluid interaction surface and a cooling surface at least partly limit an inner cavity of the platform portion in which a cooling fluid is leadable. The second platform wall is connected to the first platform wall at an axial downsealing arrangement and gas turbinesealing arrangement for a nozzle guide vane and gas turbinestream end of the platform portion. A first surface of the second platform wall limits the inner cavity, and a support structure including a seal arranged in a recess between the support structure and a second surface of the second wall to reduce cooling liquid leakage from the inner cavity to a space downstream.

Abstract: A method for monitoring a combustor comprising: measuring several times a distance between a first wall of the combustor and either a second wall of the combustor or a sensor of the combustor by the sensor, and concluding from a variation in the distances a formation of deposit on the first and/or second wall and/or sensor, and/or a temperature change within the combustor, and/or a pressure change within the combustor.

Abstract: A method of operating a turbine engine, the turbine engine having an inlet, a shaft, a turbine, a control system, a fuel system and a modular liquid fuel burner system having at least two interchangeable liquid burners and a liquid-fuel manifold. The control system controls a fuel supply via the liquid-fuel manifold to the burners dependent on demanded output power. The at least two interchangeable liquid fuel burners have different operating power output ranges and having at least a high power output liquid fuel burner and a low power output liquid fuel burner. The method of operating the turbine engine includes the steps of controlling a liquid fuel supply to the high power output burner for a high power output having a turbine entry temperature limit and controlling a liquid fuel supply to the low power output burner for a low power output having a liquid fuel manifold pressure limit.

Abstract: A turbine includes a supporting structure which extends along a circumferential direction of the turbine, wherein the supporting structure has a groove to guide cooling air. The groove extends along the circumferential direction. The turbine has a first impingement ring element having a plurality of first cooling holes and a second impingement ring element having a plurality of second cooling holes, wherein the first and second impingement ring elements are mounted one after another along the circumferential direction to the groove such that the groove is covered by the first and second impingement ring elements. A first coupling ring element is arranged between the first and second impingement ring elements such that the groove is covered by the first coupling ring element between the first impingement ring element and the second impingement ring element. The first coupling ring element forms a sliding contact with the second impingement ring element.

Abstract: A swirler for mixing fuel and air is provided. The swirler includes a plurality of vanes arranged on a reference circle diameter which, together with a first longitudinal end face of the vanes disposed on a first wall and a second wall disposed on an opposing second longitudinal end face of the vanes, form a flow channel. In this arrangement at least one injection orifice in the first wall and at least one further injection orifice in the second wall open into a flow channel. The arrangement of the at least two mutually opposing injection orifices in the wall of the swirler makes for a homogeneous distribution of the fuel in the flow channel and ensures a uniform mixing of the air with the fuel. This results in uniform and low-NOx combustion of the fuel/air mixture in a burner.

Abstract: A platform seal strip, in particular for use in a gas turbine blade assembly, is provided. The platform seal strip includes an upper side, a lower side, a first portion and a second portion. The width of the first portion is smaller than the width of the second portion. The first portion and the second portion are at least partially bent downwards such that the upper side includes a convex surface portion and the lower side includes a concave surface portion.

Abstract: A swirler including a fuel distributor is provided. Each fuel distributor includes a distribution element defining a cavity, an inlet opening arranged in the distribution element, at least one outlet opening arranged in the distribution element, and at least one third opening arranged in the distribution element, the cross-section of the at least one third opening being larger than the cross-section of the at least one outlet opening.

Abstract: A nozzle guide vane support arrangement including a platform portion of a nozzle guide vane at a trailing edge is provided, the platform portion having a platform wall including a first platform wall portion and a second platform wall portion. A working fluid interaction surface and a cooling surface at least partly limit an inner cavity of the platform portion in which a cooling fluid is leadable. The second platform wall is connected to the first platform wall at an axial downsealing arrangement and gas turbinesealing arrangement for a nozzle guide vane and gas turbinestream end of the platform portion. A first surface of the second platform wall limits the inner cavity, and a support structure including a seal arranged in a recess between the support structure and a second surface of the second wall to reduce cooling liquid leakage from the inner cavity to a space downstream.

Abstract: A pilot burner of a gas turbine engine is provided. The pilot burner includes a front body with an axial expansion along a center axis of the pilot burner, the center axis having an axial direction towards a burning zone of the gas turbine engine. The front body includes a pilot burner face which is directed to the burning zone. A material is deposited in the front body progressing in the axial direction to form a high temperature resilient body in the axial direction of the front body and to form a high temperature resilient face of the pilot burner face.

Abstract: A burner for a gas turbine engine is provided. The burner includes a radial swirler for creating a swirling fuel/air mix, a combustion chamber where combustion of the swirling fuel/air mix occurs, and a pre-chamber located between the radial swirler and the combustion chamber. The radial swirler includes a plurality of vanes arranged in a circle, generally radially inwardly extending flow slots are defined between adjacent vanes in the circle, each flow slot includes a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending sides provided by adjacent vanes, and a base and top. A flow slot includes a first gas fuel injection hole in its base and a flow slot includes a second gas fuel injection hole in its first side wherein the amounts of gas fuel injected via the first and second gas fuel injection holes are independently variable.

Abstract: A transition duct is provided for coupling a combustor and a turbine section of a gas turbine. The transition duct includes a transition duct skin. The transition duct skin comprises a first surface section, a second surface section, and a clinch welded joint connecting the first surface section and the second surface section. Also provided is a method for manufacturing such a transition duct.

Abstract: A vane used on a swirler is provided. The vane includes a thin end and a broad end, the broad end has sharp edges and is arranged on the outside of the swirler, the thin end is arranged on the inside of the swirler. The vane also includes at least one swirl slot side profile, the at least one swirl slot side profile includes a unit providing turbulence to an air flow.

Abstract: A transition duct is provided for coupling a combustor and a turbine section of a gas turbine. The transition duct includes a transition duct skin. The transition duct skin comprises a first surface section, a second surface section, and a clinch welded joint connecting the first surface section and the second surface section. Also provided is a method for manufacturing such a transition duct.

Abstract: A swirler for mixing fuel and air is provided. The swirler includes a plurality of vanes arranged on a reference circle diameter which, together with a first longitudinal end face of the vanes disposed on a first wall and a second wall disposed on an opposing second longitudinal end face of the vanes, form a flow channel. In this arrangement at least one injection orifice in the first wall and at least one further injection orifice in the second wall open into a flow channel. The arrangement of the at least two mutually opposing injection orifices in the wall of the swirler makes for a homogeneous distribution of the fuel in the flow channel and ensures a uniform mixing of the air with the fuel. This results in uniform and low-NOx combustion of the fuel/air mixture in a burner.

Abstract: A pilot burner of a gas turbine engine is provided. The pilot burner includes a front body with an axial expansion along a centre axis of the pilot burner, the centre axis having an axial direction towards a burning zone of the gas turbine engine. The front body includes a pilot burner face which is directed to the burning zone. A material is deposited in the front body progressing in the axial direction to form a high temperature resilient body in the axial direction of the front body and to form a high temperature resilient face of the pilot burner face.

Abstract: A swirler vane for providing fuel, particularly liquid fuel, to a swirling zone of a burner assembly is provided. The swirler vane includes at least one injection hole for injecting the fuel to the swirling zone of the burner and an injection feed hole passage connecting the at least one injection hole with a main fuel feed. The swirler vane or a tip of the swirler vane, where the at least one injection hole is arranged, is manufactured by laser deposition or includes at least a surface manufactured by laser deposition. A swirler including a plurality of such swirler vanes and a burner assembly including the swirler with such swirler vanes are also provided.

Abstract: A burner for a gas turbine engine is provided. The burner includes a radial swirler for creating a swirling fuel/air mix, a combustion chamber where combustion of the swirling fuel/air mix occurs, and a pre-chamber located between the radial swirler and the combustion chamber. The radial swirler includes a plurality of vanes arranged in a circle, generally radially inwardly extending flow slots are defined between adjacent vanes in the circle, each flow slot includes a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending sides provided by adjacent vanes, and a base and top. A flow slot includes a first gas fuel injection hole in its base and a flow slot includes a second gas fuel injection hole in its first side wherein the amounts of gas fuel injected via the first and second gas fuel injection holes are independently variable.

Abstract: A housing for a combustion chamber assembly is provided. The housing includes a wall device made of metal material, and an insert device made of ceramic material. The insert device is attached to the wall device such that the insert device forms a part of an inner wall of the housing and the wall device forms an outer wall of the housing.

Abstract: A swirler including a fuel distributor is provided.

Abstract: A vane used on a swirler is provided. The vane includes a thin end and a broad end, the broad end has sharp edges and is arranged on the outside of the swirler, the thin end is arranged on the inside of the swirler. The vane also includes at least one swirl slot side profile, the at least one swirl slot side profile includes a unit providing turbulence to an air flow.