Patent application number | Description | Published |
20100170267 | BURNER FOR A GAS TURBINE - A burner for a gas turbine including a main burner and a pilot burner is provided. The main burner has a supporting structure, a heat shield and a holder for the heat shield, and wherein the holder is at least partially located within the supporting structure and the heat shield is at least partially located within the holder. The heat shield is fastened to the holder by a force-fit and/or a frictional connection. | 07-08-2010 |
20100300104 | BURNER, OPERATING METHOD AND ASSEMBLY METHOD - A burner incorporating a pilot cone and a mounting insert is provided. The pilot cone is constructed as a pilot cone assembly which is decoupled from the mounting insert. Further, an operating method for increasing the service life of a burner which incorporates a pilot cone assembly and a mounting insert is provided. The pilot cone assembly has a cone side and incorporates at least one further side where the further side is arranged to be essentially parallel to one of the sides of the mounting insert and spaced apart from it, so that between the further side and the side of the mounting insert there is a defined gap. In an operation of the burner, the gap is significantly reduced by the thermal expansion in at least at one point of contact between the further side and the side of the mounting insert. Finally, an assembly method is provided. | 12-02-2010 |
20100316966 | Burner arrangement for a combustion system for combusting liquid fuels and method for operating such a burner arrangement - A burner arrangement for a combustion system for combusting liquid fuels including a burner hub, at least one air supply channel and at least one fuel supply channel for each fuel type is provided. The at least one fuel supply channel is embodied at least partially in the burner hub, with a flow divider arranged in at least one fuel supply channel, which is distanced from the wall of the fuel supply channel so that an interspace associated with the flow path of the fuel flowing through the fuel supply channel is formed between the wall of the fuel supply channel and the flow divider. A method for operating such a burner arrangement is also provided. | 12-16-2010 |
20100330521 | Fuel Nozzle Having a Swirl Duct and Method for Producing a Fuel Nozzle - A method for producing a fuel nozzle is provided. In the method a swirl duct is mounted in an outer jacket surface of a pin and/or in an inner surface of a sleeve and the pin is attached in the sleeve so that the outer jacket surface of the pin is connected to the inner surface wherein the pin is disposed in the sleeve. The outer jacket surface of the pin and/or the inner surface of the sleeve includes at least one-swirl duct. A fuel nozzle and a burner are also further disclosed wherein the burner includes the fuel nozzle. | 12-30-2010 |
20110197590 | Burner inserts for a gas turbine combustion chamber and gas turbine - A burner insert for a gas turbine combustion chamber is provided. The burner insert includes a burner insert wall including a cold side and a hot side, an edge delimiting the burner insert wall. The edge includes an edge bar extending at least partially circumferentially and projecting beyond the cold side. A burner opening for inserting a burner is formed in the burner insert wall. | 08-18-2011 |
20110203283 | Burner arrangement - A burner arrangement is provided. The burner arrangement includes a support as well as at least two fuel nozzles, with fuel nozzle tips, attached to the support in the direction of flow and a gas feed system to the fuel nozzle tips extending through the support. Each fuel nozzle includes a support-side section which on the support side includes a contact surface with which the fuel nozzle rests on a supporting surface of the support, at least two fuel nozzle tips formed in one piece running from the support-side section in the direction of flow, the gas feed system including at least one gas feed line and its lead-through through the support, the lead-through being embodied as a fit. | 08-25-2011 |
20110203285 | BURNER ARRANGEMENT - A burner arrangement is provided. The burner arrangement includes a support and at least two fuel nozzles attached to the support in the direction of flow, with each fuel nozzle including a support-side section which includes a contact surface on the support side with which it rests on a supporting surface of the support, with at least two fuel nozzle tips embodied in one piece extending out from the support-side section in the direction of flow and the support-side contact surface including at least two extension parts projecting in the direction of the support, with the extension parts each embodying a channel through which fuel is fed in each case to the fuel nozzle tips through passages which are arranged in the support-side contact surface of the support-side section. | 08-25-2011 |
20110247338 | FUEL LANCE FOR A BURNER - Disclosed is a fuel lance for a burner, in particular a gas turbine burner, including a tip that has a nozzle surface including at least two fuel nozzles. The nozzle surface is provided with slots between the fuel nozzles. As a rule, the lance is provided for operation with a liquid fuel. | 10-13-2011 |
20110314826 | Burner Assembly - A burner assembly for a firing system for firing fluidic fuels is provided. The burner assembly has a burner hub, an air inlet channel and a fuel inlet channel, wherein the fuel inlet channel is at least partially designed in the burner hub. A screening wall is arranged in the fuel inlet channel. The screening wall is spaced apart from a wall of the fuel inlet channel so that an intermediate space is formed between the wall of the fuel inlet channel and the screening wall. A sleeve is equipped with at least one radial positioning means that ensures a clearance of the sleeve from the wall of the fuel inlet channel. The at least one radial positioning means of the sleeve is designed as a positioning projection arranged in a circular manner, protruding out radially. | 12-29-2011 |
20120137691 | Gas turbine assembly and method therefor - An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange. | 06-07-2012 |