Abstract: 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.

Abstract: 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.

Abstract: In an axial flow gas turbine (30), a substantial reduction of the consumption of cooling air can be achieved by providing, within a turbine stage (TS), structure (39-44) to reuse the cooling air that has already been used to cool, especially the airfoils of, the vanes (33) of the turbine stage (TS), for cooling the stator heat shields (38) of that turbine stage (TS) downstream of the vanes (33).

Abstract: 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.

Abstract: A blade (30?) for a gas turbine has an airfoil (31) and a blade root (32) for mounting the blade (30) on a rotor shaft of the gas turbine. The airfoil (31) is provided with cooling channels (33, 35) in the interior thereof, which cooling channels (33, 35) preferably extend along the longitudinal direction and can be supplied with cooling air (45) through cooling air supply passages (40-43) within the blade root (32). The blade root (32) includes a blade channel (40) running transversely through the blade root (32) and is connected to the cooling channels (33, 35), and an insert (41) is inserted into the blade channel (40) for determining the final configuration and characteristics of the connections between the blade channel (40) and the cooling channels (33, 35).

Abstract: A stator for a turbine includes an arrangement of vanes including at least a first vane and a second vane circumferentially neighboring 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.

Abstract: In an axial flow gas turbine (30), a reduction in cooling air mass flow and leakage in combination with an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by providing, within a turbine stage (TS), devices (43-48) to direct cooling air that has already been used to cool, especially the airfoils of the vanes (31) of the turbine stage (TS), into a first cavity (41) located between the outer blade platforms (34) and the opposed stator heat shields (36) for protecting the stator heat shields (36) against the hot gas and for cooling the outer blade platforms (34).

Abstract: An axial flow gas turbine (35) has a rotor with alternating rows of air-cooled blades (40) and rotor heat shields, and a stator with alternating rows of air-cooled vanes (41) and stator heat shields (47) mounted on inner rings (46A) reduction in cooling air mass flow and an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by adapting the stator heat shields (47) and outer vane platforms (38) within a turbine stage (TS) to one another such that air (37) leaking through the joints between the outer vane platforms (38) and the adjacent stator heat shields (47) into the hot gas path (42) is directed onto the blade crown (32) of the blades (40).

Abstract: An axial flow gas turbine (20) includes a rotor (13) and a stator, and a hot gas path through which hot gas passes. The rotor (13) includes a rotor shaft (15) with axial slots for receiving a plurality of blades (B1-B3) arranged in a series of blade rows, with rotor heat shields (R1, R2) interposed between adjacent blade rows. The rotor shaft (15) is configured to axially conduct a main flow of cooling air along the rotor heat shields (R1, R2) and the lower parts of the blades (B1-B3), and the rotor shaft (15) supplies the interior of the blades (B1-B3) with cooling air (18). Stable and predictable cooling air parameters at any blade row inlet are secured by providing air-tight cooling channels (21), which extend axially through the rotor shaft (15) separate from the main flow of cooling air (17), and supply the blades (B1-B3) with cooling air (18).

Abstract: In an axial flow gas turbine efficient cooling and a long life-time can be achieved by providing the outer blade platforms (45) with a plurality of outer teeth (46a-c) running parallel to each other in the circumferential direction and being arranged one after the other in the direction of the hot gas flow. The teeth (46a-c) are divided into first and second teeth (46a; 46b-c), the second teeth (46b-c) being located downstream of the first teeth (46a), the first teeth (46a) are opposite to a downstream projection (33) of the adjacent vanes (21) of the turbine stage (TS), and the second teeth (46b-c) are opposite to the respective stator heat shields (27).

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: In an axial flow gas turbine (30), a reduction in cooling air mass flow and leakage in combination with an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by providing, within a turbine stage (TS), devices (43-48) to direct cooling air that has already been used to cool, especially the airfoils of the vanes (31) of the turbine stage (TS), into a first cavity (41) located between the outer blade platforms (34) and the opposed stator heat shields (36) for protecting the stator heat shields (36) against the hot gas and for cooling the outer blade platforms (34).

Abstract: An axial flow gas turbine (20) includes a rotor (13) and a stator, and a hot gas path through which hot gas passes. The rotor (13) includes a rotor shaft (15) with axial slots for receiving a plurality of blades (B1-B3) arranged in a series of blade rows, with rotor heat shields (R1, R2) interposed between adjacent blade rows. The rotor shaft (15) is configured to axially conduct a main flow of cooling air along the rotor heat shields (R1, R2) and the lower parts of the blades (B1-B3), and the rotor shaft (15) supplies the interior of the blades (B1-B3) with cooling air (18). Stable and predictable cooling air parameters at any blade row inlet are secured by providing air-tight cooling channels (21), which extend axially through the rotor shaft (15) separate from the main flow of cooling air (17), and supply the blades (B1-B3) with cooling air (18).

Abstract: A blade (30?) for a gas turbine has an airfoil (31) and a blade root (32) for mounting the blade (30) on a rotor shaft of the gas turbine. The airfoil (31) is provided with cooling channels (33, 35) in the interior thereof, which cooling channels (33, 35) preferably extend along the longitudinal direction and can be supplied with cooling air (45) through cooling air supply passages (40-43() within the blade root (32). The blade root (32) includes a blade channel (40) running transversely through the blade root (32) and is connected to the cooling channels (33, 35), and an insert (41) is inserted into the blade channel (40) for determining the final configuration and characteristics of the connections between the blade channel (40) and the cooling channels (33, 35).

Abstract: In an axial flow gas turbine (30), a substantial reduction of the consumption of cooling air can be achieved by providing, within a turbine stage (TS), structure (39-44) to reuse the cooling air that has already been used to cool, especially the airfoils of, the vanes (33) of the turbine stage (TS), for cooling the stator heat shields (38) of that turbine stage (TS) downstream of the vanes (33).

Abstract: In an axial flow gas turbine efficient cooling and a long life-time can be achieved by providing the outer blade platforms (45)with a plurality of outer teeth (46a-c) running parallel to each other in the circumferential direction and being arranged one after the other in the direction of the hot gas flow. The teeth (46a-c) are divided into first and second teeth (46a; 46b-c), the second teeth (46b-c) being located downstream of the first teeth (46a), the first teeth (46a) are opposite to a downstream projection (33) of the adjacent vanes (21) of the turbine stage (TS), and the second teeth (46b-c) are opposite to the respective stator heat shields (27).

Abstract: An axial flow gas turbine (35) has a rotor with alternating rows of air-cooled blades (40) and rotor heat shields, and a stator with alternating rows of air-cooled vanes (41) and stator heat shields (47) mounted on inner rings (46A reduction in cooling air mass flow and an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by adapting the stator heat shields (47) and outer vane platforms (38) within a turbine stage (TS) to one another such that air (37) leaking through the joints between the outer vane platforms (38) and the adjacent stator heat shields (47) into the hot gas path (42) is directed onto the blade crown (32) of the blades (40).