Alstom Technology Limited

General Electric Technology Gmbh

Remigi Tschuor

Russell B Jones

Hartmut Haehnle

Gregory Edwin Vogel

Heinz Neuhoff

Urs Benz

Luis Joaquin Rodriguez

Kenneth Hall

Edouard Sloutski

Uwe Rüdel

Sacha Parneix

Guenter Filkorn

Lothar Schneider

Emil Anner

Alen Markovic

Iouri Strelkov

Hartmut Hähnle

Bogdan Trbojevic

Marion Duggans (-Oneil)

Harmut Hähnle

Marion Duggan (-Oneil)

Sinisa Narancic

Alexandre Tchekanov

Russell Bond Jones

Nilze Isabel Seda-maurell

Marion Oneil Duggans

Gregory Vogel

Andreas De Fazio

A gas turbine includes a compressor, an annular combustion chamber, and a turbine, a combustion chamber shell of the combustion chamber adjoining the turbine inlet in a transition region in order to introduce the hot gases generated in the combustion chamber into the downstream turbine such that a thermal expansion-induced relative movement between the combustion chamber and the turbine inlet is possible. Combustion chamber shell support elements distributed on the periphery come into contact with a conical contour on the shaft cover due to the thermal expansion that occurs during operation and are supported on said contour. An improvement with respect to loading and service life is achieved in that the conical contour and the machine axis form an angle that allows the combustion chamber shell support elements to slide onto the conical contour.

Gas turbine support element permitting thermal expansion between combustor shell and rotor cover at turbine inlet

The combustion device () of a gas turbine includes burners () connected to a front plate () of a combustion chamber (). The front plate () has, spaced apart from one another, a front sheet () and an impingement sheet () with aligned holes () housing the burners (). A piston ring () is provided between the front sheet () and impingement sheet () to seal the holes (). The axial length of the border of the hole () of the front sheet () and/or impingement sheet () is longer than the thickness of the corresponding front sheet () and/or impingement sheet ().

Gas turbine combustion device

A gas turbine includes a turbine section; an annular combustor disposed upstream of the turbine section and configured to discharge a hot gas flow on an outlet side to the turbine section; an outer shell delimiting the combustor and splittable at a parting plane; a plenum enclosing the outer shell; a rotor; a turbine vane carrier encompassing the rotor; a plurality of stator vanes disposed on the vane carrier, and at least two sealing segments forming a ring, each of the at least two sealing segments having an inner edge and a head and a foot section and being movably mounted on the inner edge by the foot section to the outer shell and by the head section to the turbine vane carrier so as to mechanically connect the combustor to the turbine vane carrier.

Gas turbine

In order to provide an annular combustion chamber () which can be heated without thermal distortion, expands without distortion, and is reliably closed, and for repairs can be opened and permanently closed again and can be reconditioned, the inner and/or outer shell () of an annular combustion chamber () is produced from a rotationally symmetrical sheet metal. For assembly, the shells are cut open along a split line (), and the lower half of the inner and of the outer shell () is introduced into the lower casing half of a gas turbine. After the insertion of the rotor, the two upper shell halves can likewise be inserted and be connected to the lower halves by welding. In order to improve the service life of the split line weld seam (), film cooling of the weld seam is routed by an indentation. This may be implemented, for example, by welded-in split line elements () which are also suitable for retrofitting.

Gas turbine with welded combustor liners

A thermal machine, especially a gas turbine, includes an annular combustor which is outwardly delimited by an outer shell and an inner shell () and through which a hot gas axially flows. The outer shell and inner shell () are each provided with a concentric cooling shroud () which is attached at a distance on their outer side, forming a cooling passage () through which cooling passage () cooling air flows in a direction which is opposite to the hot gas flow. The cooling of the combustor is improved by at least one of the cooling shrouds (), on the side on which the cooling air enters the cooling passage (), having an outwardly curved, rounded inlet edge () for improving the inflow conditions.

Thermal machine

A thermal machine includes a hot gas channel; a shell bounding the hot gas channel; a cooling shirt surrounding the shell; and a cooling channel disposed between the shell and the cooling shirt and configured to convection cool the hot gas channel with a cooling medium, wherein the cooling shirt includes at least one local divergence in the guidance of the cooling medium so as to compensate for non-uniformities in at least one of a thermal load on the shell and a flow of the cooling medium in the cooling channel.

Gas turbine having an improved cooling architecture

A thermal machine including a wall defining a hot gas duct for transferring a hot gas stream and a cooling jacket disposed at a distance from the wall on an outside of the hot gas duct so as to define a cooling duct with an inlet and an outlet. The cooling duct is configured to conduct a cooling medium along an external face of the wall from the inlet to an outlet in a direction counter to a flow of hot gas in the hot gas duct. An impingement cooling plate is disposed at the inlet of the cooling duct and includes cooling baffle holes configured such that cooling medium entering the cooling duct through the cooling baffle holes flows in a direction perpendicular to the wall. The impingement cooling plate is positioned such that an inflow-side edge sealingly abuts the wall of the hot gas duct so as to reduce a transverse flow of the cooling medium through the cooling duct.

Impingement cooling plate for a hot gas duct of a thermal machine

An arrangement is disclosed for the admission of cooling air to the internal walls of a component rotating about a rotation axis, such as a moving blade in a rotary machine. A component root can be fastened to a rotor unit in a rotationally fixed manner and adjoining in a radially extending manner is a one piece component airfoil in which at least one radially extending cooling passage region (K) is provided which, in the region of the component root, opens out via an opening into a cooling-air supply passage passing at least partly through the component root longitudinally relative to the rotation axis. A distribution plate forms a fluid-tight connection with an opening margin, surrounding the opening of the cooling passage region (K), at least during the rotation of the component about the rotation axis. The distribution plate provides at least one through-opening in the region of the opening of the at least one cooling passage region (K), through which through-opening cooling air passes from the axial cooling-air supply passage into the radial cooling passage region (K).

Arrangement for the admission of cooling air to a rotating component, in particular for a moving blade in a rotary machine

A turbomachine blade, in particular a turbine blade of a gas turbine includes a blade root with a cooling-fluid feed, a blade tip formed with a shroud element. At least one throughflow passage which extends in the blade longitudinal direction is arranged inside the airfoil. A shroud cooling passage is formed in the shroud element at least along a section of the latter, the shroud cooling passage being connected via an opening to the throughflow passage, and a cooling fluid flowing through this shroud cooling passage during operation of the turbomachine blade. At least one flow-guiding element for guiding at least some of the cooling-fluid flow flowing through the shroud cooling passage is arranged in the shroud cooling passage and/or in an inflow or outflow to or from the shroud cooling passage.

Turbomachine blade with fluidically cooled shroud

A thermally loaded component has at least one cooling passage for the flow of a cooling fluid passing through it. In the region of a bend, at least one diverter device for the integral capturing of the flow of the cooling fluid is provided within the cooling passage. The diverter device comprises, over the height of the cooling passage, two diverter parts which are spaced apart from one another. The diverter maybe cast with a notch therein so that during cooling, the diverter breaks into separated portions proximate the notch.

Thermally loaded component

A rotor blade () for a flow machine includes an aerodynamic blade () and a foot (). The foot () has an anchoring section () on a side facing away from the blade (). A rotor () of the flow machine has an axial anchoring groove () which is complementary to the anchoring section (). The anchoring section () can be inserted axially into the anchoring groove () in order to radially attach the rotor blade () to the rotor (). At least one pulling-off contour () is formed on the foot (), via which an axial pulling-off force can be introduced into the rotor blade (), which is attached to the rotor () with the aid of a pulling-off tool () which is complementary to this pulling-off contour ().

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Windisch, Switzerland

Remigi Tschuor