Alstom Technology Limited

General Electric Company

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Alexander Anatolievich Khanin

Sergey Vorontsov

Maxim Konter

Edouard Sloutski

Valery Kostege

Dietrich Eckardt

Alexander Burmistrov

Victor Vladimirovich Odinokov

Alexander Bone

Andrey Petrovich Morozov

Anton Sumin

Igor Kurganov

Andrei Vladimirovich Pipopulo

Arkadi Fokine

Iouri Strelkov

Oleg Naryzhny

Alexey Pavlovich Karelin

Alexander Chekanov

Alexander Checkanov

Anatoly Shunin

Alexander Balakirev

Anastasiya Gorelova

Andrey Morozov

Alexey Karelin

Sergey Aleksandrovich Vorontsov

Iouri Alexandrovich Strelkov

Anton Soumine

Victor Odinokov

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.

Fluid flow machine especially gas turbine penetrated axially by a hot gas stream

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.

Axial-flow machine

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

Axial flow gas turbine

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.

Turbine blade

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

Blade for a gas turbine, method for manufacturing a turbine blade, and gas turbine with a blade

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.

Turbine vane

In an axial flow gas turbine (), 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 (-) to direct cooling air that has already been used to cool, especially the airfoils of the vanes () of the turbine stage (TS), into a first cavity () located between the outer blade platforms () and the opposed stator heat shields () for protecting the stator heat shields () against the hot gas and for cooling the outer blade platforms ().

Gas turbine of the axial flow type

An axial flow gas turbine () has a rotor with alternating rows of air-cooled blades () and rotor heat shields, and a stator with alternating rows of air-cooled vanes () and stator heat shields () mounted on inner rings (A) 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 () and outer vane platforms () within a turbine stage (TS) to one another such that air () leaking through the joints between the outer vane platforms () and the adjacent stator heat shields () into the hot gas path () is directed onto the blade crown () of the blades ().

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

In an axial flow gas turbine efficient cooling and a long life-time can be achieved by providing the outer blade platforms () with a plurality of outer teeth (-) 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 (-) are divided into first and second teeth (-), the second teeth (-) being located downstream of the first teeth (), the first teeth () are opposite to a downstream projection () of the adjacent vanes () of the turbine stage (TS), and the second teeth (-) are opposite to the respective stator heat shields ().

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 cast turbine blade is disclosed and includes an internal cooling passage that passes (e.g., zig-zags or meanders) through the blade from an inlet in the blade root to an outlet in the blade tip. The cooling passage can have a zone at a bend that is at a distance which is remote from the inlet of the cooling passage when the distance from the inlet is measured around the passage, but that is closer to the inlet when the distance from the inlet is measured in a straight line. During casting of the blade, the cooling passage can be defined by a core or cores having a leachable material, the cores being removed after casting by a chemical leaching process. A supplementary passage is also provided for connecting the remote zone to the inlet during the leaching process. The supplementary passage can likewise be defined by a leachable core, or it may be machined into the blade after casting. During the service life of the blade, a plug can be used to obturate the supplementary passage to prevent leakage of cooling air from the cooling passage through the supplementary passage.

Turbine blades

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 ().

Growing community of inventors

Moscow, Russia

Alexander Anatolievich Khanin