Siemens Aktiengesellschaft

Siemens Energy, Inc.

Andreas J Heilos

Marc Tertilt

Holger Grote

Berthold Köstlin

Frank Hannemann

Gerhard Zimmermann

James Michael Zborovsky

Bernd Prade

Michael Huth

Stefan Hoffmann

Christian Scholz

Eberhard Deuker

Anil Gulati

There is described a heat shield element comprising a hot side which is turned towards the hot medium, a cold side which is turned away from the hot medium, peripheral sides which connect the hot side to the cold side and a material volume which is defined by the hot side, the cold side and the peripheral sides, wherein the material volume comprises at least two material areas which are made of different materials. The materials are different from each other at least in respect of their resistance and/or thermal expansion coefficient.

Heat shield element, method and mold for the production thereof, hot-gas lining and combustion chamber

A method for starting a burner for combusting synthesis gases is provided. The burner includes first and second fuel passages, the first fuel passage encompasses the second fuel passage in a substantially concentric manner and the gas transferred to the burner is mixed with combusting air and is combusted. In order to start the burner, the second fuel passage is first loaded with a synthesis gas to a predefined burner power at a first starting phase and the first fuel passage is loaded with the synthesis gas at a second starting phase.

Method for starting a burner

A method for operating a burner including a burner outlet opening with at least two sectors, each sector is assigned at least one fuel nozzle, is provided. The method is characterized in that fuel is supplied separately to the fuel nozzles of different sectors. Also described is a burner which includes at least two sectors wherein each sector is assigned at least one fuel nozzle. The burner includes at least two separate fuel supply lines and a device for adjusting the fuel mass flow which flows through the respective fuel supply line. The fuel supply lines supply fuel to the fuel nozzles of different sectors. Also described is a gas turbine which is fitted with at least one burner.

Burner and method for operating a burner

The invention relates to a method for starting a burner for combusting synthesis gases, wherein said burner comprises first and second fuel passages, the first fuel passage encompasses the second fuel passage in a substantially concentric manner and the gas transferred to the burner is mixed with combusting air and is combusted. According to said invention, in order to start the burner, the second fuel passage is first loaded with a synthesis gas to a predefined burner power at a first starting phase and the first fuel passage is loaded with the synthesis gas at a second starting phase.

A gas turbine transition duct apparatus is provided comprising first and second turbine transition ducts and a strip seal. The strip seal may comprise a sealing element and a spring structure.

Turbine transition duct apparatus

The invention relates to a heat shield element for lining a combustion chamber wall, to a combustion chamber and to a gas turbine. The heat shield element comprises a hot side that can be exposed to a hot medium, a wall side opposite said hot side, and a peripheral side adjoining the hot side and the wall side and having a peripheral side surface. Relief slots are introduced into the material in an area of the heat shield element that is susceptible to material cracks induced by thermal stress, thereby limiting crack propagation.

Heat shield element for lining a combustion chamber wall, combustion chamber and gas turbine

The present invention is directed to a seal for sealing a gap between transition sections of adjacent can annular combustors in a turbine engine such that the seal is usable in applications for sealing pressure drops of 0.5 bar or greater. The seal includes a plate configured to extend between adjacent transition sections and the plate may have at least one perforation extending from the front surface of the plate to the rear surface of plate. The seal further includes a porous matrix formed from materials capable of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix may be fixedly attached to a surface of the plate.

Gas turbine: seal between adjacent can annular combustors

The invention relates to a heat shield block, particularly for lining a combustion chamber wall, with a hot side that can be subjected to the action of hot medium and with a wall side situated opposite the hot side. A core area, which has a core material, extends inside the heat shield block from the hot side to the wall side. The core area is surrounded by an edge area with an edge material whose heat conductivity is lower than that of the core material. This targeted thermal insulation in the edge area provided in the form of a material bond between the core material and the edge material renders the heat shield block particularly unsusceptible to the formation and growth of cracks in the core area on the hot side. The invention also relates to a combustion chamber provided with heat shield blocks of the aforementioned type, and to a gas turbine provided with a combustion chamber comprising such a heat shield block.

Heat shield block for lining a combustion chamber wall, combustion chamber and gas turbine

A heat shield is provided on a supporting structure with a number of heat shield elements, which are fixed to a large area of the supporting structure leaving gaps between adjacent heat shield elements, a number of securing elements with which the heat shield elements are fixed to the supporting structure and which have a grip section engaging in the heat shield elements and a cooling system for cooling the securing elements, the cooling system being designed such that cooling fluid can be supplied directly to the grip sections of the securing elements.

Heat shield

A method is for operating a burner of a gas turbine. A fossil fuel is gasified and the gasified fossil fuel is fed as synthesis gas into the burner for combustion. The burner is connected to the gas turbine. The synthesis gas is divided into a first partial current and a second partial current and the partial currents are each fed into the burner for combustion. A power plant, particularly a gas and steam turbine system, includes a gasification device for a fossil fuel.

Method for operating a burner of a gas turbine and a power plant

The invention relates to a pre-mix burner for burning a low-calorie combustion gas, said burner comprising an air duct which extends along an axis of the burner and can be used to supply combustion air. A swirling device is arranged in the air duct and is used to apply a swirling motion to the combustion air. An injection device for the low-calorie combustion gas is provided downstream of the swirling device. The injection device comprises inlets for the combustion gas, such that the formation of wake regions in the air channel is prevented. The invention also relates to a method for burning a low-calorie combustion gas, according to which a swirling motion is applied to the combustion air, low-calorie combustion gas is injected into the swirled combustion air and intensively mixed therewith, and the mixture is then burned.

Premix burner and method for burning a low-calorie combustion gas

A mold for producing a ceramic heat shield element having a mold shell is provided. The mold shell comprises a plurality of mold surfaces and a casting aperture for pouring in a ceramic material. The mold shell is embodied as a single-piece mold shell during casting, and the casting aperture is embodied as an aperture in one of the mold surfaces. Separating or retaining elements enable graded or reinforced heat shield elements to be produced.

Growing community of inventors

Muelheim an der Ruhr, Germany

Andreas J Heilos