Abstract: A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.

Abstract: A gas turbine has a cooling air passage which extends along the leading edge of the blade airfoil, which cooling air passage has an outlet opening which is arranged in the region of the blade tip. The contour of the outlet opening is geometrically similar to the cross section of the cooling air passage. As a result, flow inhomogeneities of the cooling air flow, which locally negatively influence heat transfer, and consequently cooling efficiency, are avoided.

Abstract: A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.

Abstract: A gas turbine has a cooling air passage which extends along the leading edge of the blade airfoil, which cooling air passage has an outlet opening which is arranged in the region of the blade tip. The contour of the outlet opening is geometrically similar to the cross section of the cooling air passage. As a result, flow inhomogeneities of the cooling air flow, which locally negatively influence heat transfer, and consequently cooling efficiency, are avoided.

Abstract: A sealing arrangement for a rotor of a turbomachine includes a blade (2), a heat shield (3, 4) and a sealing element (5, 6) for sealing between the blade (2) and the heat shield (3, 4) when the blade (2), heat shield (3, 4) and sealing element (5, 6) are assembled for use in the rotor. The heat shield (3, 4) includes a first slot (7, 8) for accommodating a first member (11, 12) of the sealing element (5, 6), and a root portion of the blade (2) includes a second and third slot (9, 10) for accommodating a second member (13, 14) of the sealing element (5, 6). The first slot (7, 8) extends in a direction which is substantially mutually perpendicular to a direction in which the second and third slot (9) extends, and the first member (11, 12) extends in a direction which is substantially mutually perpendicular to a direction in which the second member (13, 14) extends.

Abstract: A gas turbine arrangement with heat accumulation segments (3) which are arranged, opposite moving blades, on a casing of the gas turbine, and with guide vanes (1) which are arranged adjacently to the heat accumulation segments (3) over the circumference between the casing of the gas turbine and the rotor, the moving blades and the guide vanes (1) being arranged in a hot-gas duct (5) of the gas turbine. At least one sealing element (4) arranged over the circumference is present between the guide vanes (1) and the heat accumulation segments (3) and can be separated from the hot-gas duct (5) by means of a protective shield (6).

Abstract: A sealing arrangement for a rotor of a turbomachine includes a blade (2), a heat shield (3, 4) and a sealing element (5, 6) for sealing between the blade (2) and the heat shield (3, 4) when the blade (2), heat shield (3, 4) and sealing element (5, 6) are assembled for use in the rotor. The heat shield (3, 4) includes a first slot (7, 8) for accommodating a first member (11, 12) of the sealing element (5, 6), and a root portion of the blade (2) includes a second and third slot (9, 10) for accommodating a second member (13, 14) of the sealing element (5, 6). The first slot (7, 8) extends in a direction which is substantially mutually perpendicular to a direction in which the second and third slot (9) extends, and the first member (11, 12) extends in a direction which is substantially mutually perpendicular to a direction in which the second member (13, 14) extends.

Abstract: A gas turbine arrangement with heat accumulation segments (3) which are arranged, opposite moving blades, on a casing of the gas turbine, and with guide vanes (1) which are arranged adjacently to the heat accumulation segments (3) over the circumference between the casing of the gas turbine and the rotor, the moving blades and the guide vanes (1) being arranged in a hot-gas duct (5) of the gas turbine. At least one sealing element (4) arranged over the circumference is present between the guide vanes (1) and the heat accumulation segments (3) and can be separated from the hot-gas duct (5) by means of a protective shield (6).

Abstract: The invention relates to a gap seal (6) for sealing a gap (3) between two adjacent components (1, 2), in particular of turbo machines, with the following characteristics: each component (1) has one each groove (7) that is open towards the gap (3), the two grooves (7) are essentially facing each other in the gap (3), in each groove (7), a compensation body (16) is movably positioned transversely to the longitudinal groove direction and parallel to the gap plane (10), each compensation body (11) abuts the groove bottom (9) of the corresponding groove (7) in a sealing manner, each compensation body (11) has a V-shaped receiving groove (14) that is open towards the facing compensation body (11), a mutual sealing body (16) has a rhombus-shaped cross-section and projects with outer sides (17) into both receiving grooves (14), the straight inner sides (15) of each receiving groove (14) are angled towards each other at the same angle as the straight outer sides (17), in each receiving groove (14), at least one out

Abstract: A gap seal in a gas turbine for sealing off a cooling space, formed between a heat shield and a heat shield carrier, from a hot gas space of the gas turbine. A sealing body is retained in a movable manner on the heat shield, on the one hand, and on a blade carrier, on the other hand, adjacent to the heat shield carrier.

Abstract: The invention relates to a gap seal (6)for sealing a gap (3) between two adjacent components (1,2), in particular in turbo machines. A sealing body (7) has a band (18) with a cross-section that is bent in such a way that two contact zones (8) formed on it abut with a preloan against two facing sealing surfaces (9) of components (1,2). The contact zones (8) are able to deflect resiliently when the distance between the sealing surfaces (9) is reduced. A support zone (11) formed between the contact zones (8) is supported on a step (10) vertically to the spring movement. The step (10) is formed on one of the components (2) and projects from its sealing surface (9) towards the sealing surface (9) of the other component (1).

Abstract: The invention relates to a gap seal (6) for sealing a gap (3) between two adjacent components (1, 2), in particular of turbo machines, with the following characteristics:

Abstract: The invention relates to a gap seal in a gas turbine for sealing off a cooling space (6), formed between a heat shield (4) and a heat shield carrier (5), from a hot gas space (7) of the gas turbine. A sealing body (10) is retained in a movable manner on the heat shield (4), on the one hand, and on a blade carrier (2), on the other hand, adjacent to the heat shield carrier (5).