Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Sergey Vorontsov

Alexander Anatolievich Khanin

Maxim Konter

Edouard Sloutski

Arkadi Fokine

Igor Kurganov

Alexander Ralph Beeck

Andrey Sedlov

Maxim Plodistyy

Alexander Burmistrov

Victor Vladimirovich Odinokov

Iouri Strelkov

Alexander Bone

Anton Sumin

Alexey Pavlovich Karelin

Anatoly Shunin

Alexey Karelin

Anton Soumine

Victor Odinokov

A stator heat shield for a gas turbine having a hot gas flow path, is disclosed. The stator heat shield includes a first surface configured to face the hot gas flow path of the gas turbine; a second surface opposite to the first surface; cooling channels for directing cooling fluid from the second surface towards the first surface; and cavities arranged at the first surface for receiving the cooling fluid from at least a part of the cooling channels; wherein at least a part of the cavities each have at least two corresponding cooling channels open thereto, the at least two corresponding cooling channels being inclined towards each other. In use, a vortex is created in the cavity.

Stator heat shield for a gas turbine, gas turbine with such a stator heat shield and method of cooling a stator heat shield

A gas turbine includes a turbine housing; a rotatable turbine rotor with turbine blades; and at least one heat shield segment for a stator. The heat shield segment is disposed radially between the rotor and the housing and attached to the housing and has a profile with a curved section in at least one region in an axial direction of the gas turbine and a radial outer surface. The heat shield segment includes a rib, a first boss, and a second boss disposed on the radial outer surface.

Heat shield segment for a stator of a gas turbine

A guide vane for a gas turbine includes a vane body having a leading edge and a trailing edge and a shroud extending at least between the leading edge and the trailing edge. The shroud has a first side wall and a second side wall extending essentially radially and in a longitudinal direction of the gas turbine. The first side wall has a groove disposed in a region of the trailing edge extending in a longitudinal direction of the shroud and is configured to receive a sealing plate. The first side wall also has a clearance extending from the groove in a region of the trailing edge, wherein a depth of the clearance in a circumferential direction of the gas turbine is equal to a depth of the groove, and wherein a width of the clearance in the longitudinal direction of the shroud is between one to three times the depth of the clearance.

Stator vane for a gas turbine engine

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.

Seal in gas turbine

A gas turbine () includes a rotor () which has two rotor blade rows () with a plurality of rotor blades (), and also a rotor heat shield (), which is arranged between them, with a plurality of heat shield elements (), and with a stator () which has a stator blade row (), with a plurality of stator blades (), which is arranged axially between the two adjacent rotor blade rows (). The stator blades () have a stator sealing structure () radially on the inside. The heat shield elements () have a rotor sealing structure () radially on the outside which interacts with the stator sealing structure () for forming an axial seal (). Furthermore, a blade radial seal () is formed between two adjacent rotor blades (), and also a heat shield radial seal () is formed between two adjacent heat shield elements (), and in each case separates a gas path () from the rotor (). For increasing efficiency, the heat shield elements () and the rotor blades () are matched to each other so that the heat shield radial seal () merges without interruption into the blade radial seals () of the two axially adjacent rotor blades () in such a way that a continuous radial seal () is formed from the one rotor blade (), via the heat shield element (), to the other rotor blade ().

Turbo machine and gas turbine

A fluid flow engine (), in particular a turbo engine, has at least one guide vane row () with a plurality of guide vanes () and at least one rotor blade row () with a plurality of rotor blades (). One guide vane row () and one rotor blade row () that follows the former directly downstream with respect to a working gas flow (), together form a stage () of the fluid flow engine (). To reduce the load on the rotor blades (), the guide vanes () and the rotor blades () are coordinated at least in one stage () so that in a reference relative position between the respective guide vane () and the respective rotor blade (), there is an axial distance (B) and a circumferential distance (C) between the outgoing flow edge () of the respective guide vane () and the oncoming flow edge () of the respective rotor blade () that is measured in the axial direction and is varied along a height (H) of a gas path () running axially between the blade rows () of this stage (), said height being measured radially.

Fluid flow machine

A stator heat shield () for a gas turbine () includes an outside () which in the installed state faces a hot gas path () of the gas turbine (), and an inside () facing away from the outside (). A plurality of ribs () are formed on the inside () and extend axially in the installed state with regard to an axis of rotation () of a rotor () of the gas turbine () and, in the circumferential direction, are spaced a distance apart from one another. At least one baffle plate () is arranged on the inside () and is in contact with the ribs (). At least one groove () is designed in an end face () bordering the stator heat shield () in the circumferential direction, into which at least one sealing element () can be inserted. A plurality of bores () are included, each opening at a distance from the groove () in the direction of the outside () at the inside () at one end and on the end face () at the other end and arranged a distance apart from one another in the axial direction.

Stator heat shield

A vane arrangement () of a turbo machine (), in particular of a gas turbine, includes at least one vane carrier () attached to a housing () of a turbo machine (), and several vanes () attached to the vane carrier () and circumferentially arranged side by side, wherein the attachment between the vane carrier () and respective vane () is adapted for being axially pluggable. In order to simplify dismounting of a single vane () at least one of the vanes () is provided with an extraction device () having at least one axially extending extraction through-hole (). The respective extraction through hole () is provided with an inner thread (), and the vane carrier () is provided with an abutment zone () axially opposing the extraction through hole (). The extraction device () is adapted for inducing axially oriented extraction forces into the respective vane () by an extraction tool, which is provided with an outer thread and which is in order to extract the respective vane () from the vane carrier () inserted into the extraction through-hole () and axially pressing against the abutment zone ().

Vane arrangement of a turbo machine

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

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Moscow, Russia

Sergey Vorontsov