Patent application number | Description | Published |
20120134778 | AXIAL FLOW GAS TURBINE - An axial flow gas turbine ( | 05-31-2012 |
20120134779 | GAS TURBINE OF THE AXIAL FLOW TYPE - In an axial flow gas turbine ( | 05-31-2012 |
20120134780 | AXIAL FLOW GAS TURBINE - In an axial flow gas turbine efficient cooling and a long life-time can be achieved by providing the outer blade platforms ( | 05-31-2012 |
20120134781 | AXIAL FLOW GAS TURBINE - In an axial flow gas turbine ( | 05-31-2012 |
20120134785 | AXIAL FLOW GAS TURBINE - An axial flow gas turbine ( | 05-31-2012 |
20120134845 | BLADE FOR A GAS TURBINE, METHOD FOR MANUFACTURING A TURBINE BLADE, AND GAS TURBINE WITH A BLADE | 05-31-2012 |
20130004295 | TURBINE VANE - A stator for a turbine includes an arrangement of vanes including at least a first vane and a second vane circumferentially neighbouring the first vane. Each of the first vane and the second vane include: an airfoil; a channel system configured to cool the respective vane with cooling gas; and an inner diameter platform disposed at an inner end of the airfoil, the inner diameter platform including an inner diameter platform cavity and a circumferentially arranged side wall which delimits the inner diameter platform cavity, the inner diameter platform cavity being connected with the channel system so as to feed the cooling gas to the inner diameter platform. At least one sealing plate is disposed between the circumferentially arranged side walls of the first vane and the second vane so as to form an intermediate cavity that is fluidically separated from the inner diameter platform cavities. | 01-03-2013 |
20130011264 | TURBINE BLADE - A blade for a rotor of a turbine includes an airfoil, a shroud and a platform. The platform includes a top plate, a shank and a fixing part. An upstream wall projects in the circumferential direction away from the shank and extends from the top plate toward the fixing part, the upstream wall at least partially covering an upstream side of the shank. A downstream wall projects in the circumferential direction away from the shank and extends from the top plate toward the fixing part, the downstream wall at least partially covering a downstream side of the shank. A recess is disposed in at least one of the upstream wall and the downstream wall. The recess has an open side facing in a same direction as a respective one of the upstream wall and the downstream wall, in which the recess is disposed, is projecting. | 01-10-2013 |
20130263570 | FLUID FLOW MACHINE ESPECIALLY GAS TURBINE PENETRATED AXIALLY BY A HOT GAS STREAM - In a fluid flow machine, especially a gas turbine, axially penetrated by a hot gas stream, the rotor shaft is surrounded by heat shield segments or by base plates of the rotor blades on the rotor side. In the heat shield segments and in the base plates, cooling air chambers are provided, communicating with each other and with a cooling air source, which chambers communicate at least partially with gaps which extend in the longitudinal direction or peripheral direction of the rotor shaft between adjacent rotor blades or between heat shield segments and adjacent base plates of the rotor blades. These gaps are closed off by sealing bands such that a cooling air entry into the hot gas stream is only possible at the ends of the base plates of the rotor blades pointing contrary to the flow direction. | 10-10-2013 |
20130272849 | AXIAL-FLOW MACHINE - The invention relates to an axial flow machine, in particular a gas turbine with axial hot gas flow. Gaps between rotor-side heat shields are blocked by easily mountable sealing strips, which are arranged with their longitudinal edges in opposing grooves in the side walls of the respective gap. | 10-17-2013 |