Kraftwerk Union Aktiengesellschaft

Siemens Aktiengesellschaft

Helmut Maghon

Wolfram Krockow

Wilhelm Schulten

The invention relates to a combustion chamber (6) for a gas turbine (6, 18, 19) through which a flow (2) of compressed air is allowed to pass, flowing along an axis (3) from a compressor part (18) to a turbine part (19), said flow (2) having a swirl relative to the axis (3). In this arrangement, an annular passage (4) is provided at the inlet of the combustion chamber (6) having an inflow part (8) for separating a partial flow (1) from the flow (2), which comprises means (11) for removing the swirl from the partial flow (1), and which communicates with the cooling passages (14) for cooling the combustion chamber (6) as well as with pilot burners (7) for stabilizing combustion in the combustion chamber (6). The combustion chamber (6) is configured in an especially favorable manner with regard to avoiding thermodynamic losses and permits the separation of a partial flow (1) which is outstandingly suitable both for cooling purposes and for stabilizing purposes.

Gas turbine combustor with means for removing swirl

In a heat shield on a load-bearing structure, the heat shield has a multiplicity of tiles which are in contact with the load-bearing structure, are adjacent one another for substantially covering an area and are fastened by means of approximately L-shaped metallic restraints that are anchored in grooves of the load-bearing structure. The restraints may be completely screened by hot sides of the tiles facing towards a hot fluid. It is also possible to avoid the use of expensive fastening devices for the restraints. The configuration of the heat shield on the load-bearing structure is very highly thermally load-resistant, simple to manufacture and does not expose the tiles to any stresses which could be critical with respect to the brittleness of the ceramic.

Ceramic heat shield on a load-bearing structure

A burner for operation with gas and/or includes a central pilot burner system selectively operable with gas and/or oil as a diffusion burner or as a separate pre-mixing burner and an annular main burner system surrounding the pilot burner system and carrying a primary air flow. The main burner system includes a multiplicity of first nozzles admixing gas with the primary air flow for pre-mixing operation and second inlet nozzles pre-mixing oil into the primary air flow.

Hybrid burner for a pre-mixing operation with gas and/or oil, in

A gas turbine combustion chamber, includes a common spherical purely mixing chamber having inlet openings and an outlet opening formed therein and being otherwise closed, the mixing chamber having a hemispherical end zone and a spherical segment zone disposed between the hemispherical end zone and the outlet opening, the inlet openings being formed in the hemispherical and spherical segment zones, a multiplicity of primary combustion chambers each being adjacent a respective one of the inlet openings for discharging into the mixing chamber, each of the primary combustion chambers having a respective longitudinal axis coinciding at least substantially at the center of the mixing chamber, a separate air supply and a separate fuel feed for each respective primary combustion chamber, the fuel feeds being switchable on and off in dependence on the load of the gas turbine.

Gas turbine combustion chamber

A heat shield assembly includes a supporting structure having an outer surface to be shielded from a hot fluid, the supporting structure having cooling fluid ducts formed therein; and an internal lining formed of heat-resistant material, the internal lining including mutually adjacent mushroom-shaped heat shield elements each having a cap portion in the form of a polygonal plate body having a central region, the plate bodies each covering a portion of the outer surface of the supporting structure and defining cooling fluid gaps therebetween, and a shaft portion thermally moveably anchoring the central region of the plate body to the supporting structure.

Heat sheild assembly, especially for structural parts of gas turbine

In a combustion chamber having a flame tube therein at an annular gap from a housing of the chamber, a burner apparatus including at least one pilot burner near an end face of the flame tube for generating a pilot flame from natural gas and/or heating oil, an air supply channel surrounding the head of the pilot burner, a premixing device for natural gas in the form of a ring channel system surrounding the head including flow conduction walls defining an inflow cross section at an air inflow side of the ring channel system open toward the annular gap for conducting a majority of combustion air from the annular gap to a combustion zone developing downstream of the burner head in the flame tube, the combustion air having flow vectors with components entering the combustion zone in directions from parallel to the burner axis to an acute angle to the burner axis, the combustion air components having swirl components superimposed thereon tangentially relative to the burner axis acting as a swirl center, a multiplicity of nozzle tubes penetrating the inflow cross section in a direction substantially transverse to the flow direction, the nozzle tubes each having a side with nozzle openings facing away from the air inflow side of the ring channel system, and a natural gas feeding system substantially concentrically surrounding the pilot burner and connected to one end of each nozzle tube, and a method of operating the same.

Combustion chamber apparatus for combustion installations, especially

A method of manufacturing a split spur gear having adjacent external teeth with tooth roots therebetween and of mounting the spur gear onto a shaft having a first cylindrical portion including a seating surface for the spur gear with a given diameter and a second cylindrical portion adjacent the seating surface for operating the spur gear with a diameter smaller than the given diameter includes subdividing an entire gear body having a region intended for tooth roots into gear rings for forming at least one separating surface therein normal to the axis of the gear, subdividing each gear ring into at least two toothless ring segments by forming separating gaps therein offset relative to each other in the circumferential direction of the gear through the region intended for tooth roots, interconnecting the gear rings by locking connection elements in place parallel to the axis of the gear, shrinking the gear body onto an auxiliary mandrel, making external teeth on the gear body after the gear body has been shrunk onto the mandrel, dismantling the gear body from the auxiliary mandrel, assembling the gear body onto the second cylindrical portion of the shaft, uniformly heating the gear body to a given shrink-fitting temperature, and shrinking the gear body onto the seating surface formed on the shaft.

Method of manufacturing and mounting a split spur gear with external

In a gas turbine rotor of disc-type construction with a tie rod braced at least at one location along the length thereof against compressor or turbine discs by ring-shaped intermediate members, the intermediate members includes substantially conically expansible turning rings having a wider diameter end engageable in a circular groove formed in a lateral surface of one of the discs, the turning rings having at the smaller diameter end thereof an inner peripheral surface with which they are braced on the tie rod.

Gas turbine disc rotor

In a gas turbine of disc-type construction having turbine discs mounted on a rotor shaft, with rings of U-shaped cross section interposed therebetween, the turbine discs having respective rotor blades secured in blade feet thereon, and a cooling system for the rotor blade feet including axial grooves formed in the feet as well as free annular gaps located between respective end faces of the turbine discs and the intermediate rings over the radial elevation of the feet, one of the annular gaps serving as a coolant gas feed chamber and being closed radially outwardly by a sealing ring and being connected radially inwardly to radial coolant gas feed channels, the other of the annular gaps being radially outwardly open and being sealed radially inwardly against the respective turbine disc, the improvement wherein the intermediate rings are formed with bores extending axially therein from the one annular gap serving as a coolant gas feed chamber from a location close to and radially inwardly of the sealing rings, the bores being traversible by coolant gas supplied from the one annular gap.

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Mulheim/Ruhr, Germany

Helmut Maghon