Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

Thomas Heinz-Schwarzmaier

Ulrich Rathmann

Ulrich Robert Steiger

Carlos Simon-Delgado

Martin Schnieder

Brian Kenneth Wardle

Marc Widmer

Sven Olmes

Paul Marlow

Jörg Krückels

Ronald Wifling

Selma Zahirovic

Thomas Duda

Tanguy Arzel

Alexander Schnell

A strip seal and method of configuration thereof for sealing portions of components of a gas turbine exposed to pressure pulsations. The strip seal has a sealing face that is configured to follow the contours of first portions of the components. The strip seal further has a pressure face that has a sinusoidal curvilinear shape with respect to the sealing face. The pressure face is configured to prevent localized movement of strip seal by configuring pressure face on its first side to contact sealing face at a plurality of points, on its second side to contact second portions of the components at a plurality of points.

Strip seal and method for designing a strip seal

A gas turbine is provided having a secondary combustion chamber and a first guide vane row of a low-pressure turbine, the row being arranged directly downstream of the chamber. The radially outer boundary of the secondary combustion chamber is formed by at least one outer wall segment, which is secured on at least one support element arranged radially outwardly. The flow path of the hot gases is bounded radially outwardly, in the region of the guide vane row, by an outer platform which is secured at least indirectly on at least one guide vane support. A substantially radially extending gap-shaped cavity having a width in the range of 1-25 mm in the axial direction in the inlet region is arranged between the wall segment and the outer platform. At least one step element, which reduces the width by at least 10% in at least one step, extending substantially perpendicularly to the direction of flow of the hot gas in the cavity, is arranged in the inlet region.

Transitional region for a secondary combustion chamber of a gas turbine

A cooled blade for a gas turbine includes a blade airfoil extending between leading and trailing edges in a flow direction and on suction and pressure sides is delimited by a wall, which include an interior space in which cooling air flows towards the trailing edge in the flow direction and discharges to the outside in the region of the trailing edge. The pressure-side wall terminates at a distance in front of the trailing edge in the flow direction, forming a pressure-side lip, such that the cooling air discharges from the interior space on the pressure side. Multiple ribs subdivides the interior space, parallel to the flow direction, into a plurality of parallel cooling passages which create a high pressure drop and in which turbulators are arranged for increasing cooling. Before the outlet, multiple flow barriers are provided in the cooling air flow path, distributed transversely to the flow direction.

Cooled blade for a gas turbine

A strip seal and method of configuration thereof for sealing two adjacent non-rotating gas turbine hot gas components exposed to pressure pulsations. The strip seal has at least two clamping projections distributed along discrete points of the strip seal length that extend out from a pressure face of the strip seal. The location of the projections are defined by two ratios. The first ratio, of less than 25, is the strip seal length extending free of clamping projections from any one of the ends of the strip seal to a clamping projection to the ratio of strip seal thickness. The second ratio, of less than 200, is the ratio of the strip seal length extending free of clamping projections between any two projections to the thickness of the strip seal. This seal arrangement ameliorates detrimental effects of induced resonance.

A gas turbine is provided that includes a rotor which is rotatable around an axis and equipped with rotor blades, and which is concentrically enclosed at a distance by a casing, which is equipped with stator blades, forming an annular hot gas passage. Rings with stator blades and rotor blades are arranged in a manner alternating in the axial direction. Between adjacent stator blades, heat shield segments are arranged, which delimit the hot gas passage on the outside in a region of the rotor blades and are cooled by impingement cooling where a cooling medium from an outer annular cavity flows into the heat shield segment.

Shroud seal segments arrangement in a gas turbine

An arrangement between blade elements in a blade row in a turbine is described. Each blade element has at least one shroud element and a blade airfoil which abuts on, and is connected to, the shroud element, and essentially extends radially with regard to a principal axis of the blade row. When installed, the shroud element sides, which extend circumferentially, abut on the respectively adjacent shroud element of the respectively adjacent blade element, each forming an essentially radial gap. At least one blade element has a projection which projects into the shroud element of the abutting blade element and extends in the circumferential direction, and at least one blade element has a recess which accommodates such a projection. In the region of the projection or recess there is a stepped region of the radial gap, and the guiding of the radial gap in this stepped region is a labyrinth seal.

Shiplap arrangement

A gap seal () radially seals a gap () which extends axially and radially between two blades () of a turbomachine which are adjacent in the circumferential direction (). The two blades () have, in each case, an axially extending longitudinal slot (), which is open towards the gap (), on its respective blade root (). A band-form or strip-form sealing element () engages with its longitudinal sides () in the two longitudinal slots () and bridges the gap (). The one blade () has a projection () on its blade root (), which projects from the blade root () in the circumferential direction () and extends in the circumferential direction () and radially, at least in the region of the respective longitudinal slot (), and bridges an axial longitudinal end of the gap () in the process. The other blade () has a step-shaped recess () on its blade root (), complementary to the projection () of the one blade () and in which the projection engages. The projection () has a transverse slot () which extends in the circumferential direction () and is open towards the gap (). The sealing element () engages with an end face () in the transverse slot ().

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Wettingen, Switzerland

Thomas Heinz-Schwarzmaier