Siemens Aktiengesellschaft

Michael Händler

Christian Lerner

Stefan Baldauf

Hans-Thomas Bolms

Peter Schröder

Fathi Ahmad

Kevin Kampka

Nihal Kurt

Christian Kowalzik

Stefan Schmitt

Christian Kowalski

A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.

Gas turbine and mounting method

An insert element fastens to an annular segment body of a turbine of a gas turbine. The annular segment body has a recess on a hot-gas side. The insert element is designed to cover the recess and has a concave front side and a rear side having at least one shaped portion for positioning on the annular segment body. An annular segment has the insert element, a gas turbine has the insert element, and a mounting method mounts the insert element.

A turbine blade is presented including a vane that runs along a blade axis and a platform region, which is located at the root of the vane and has a platform that extends transversally to the blade axis. An improved cooling of a platform region and the transition region is provided from a turbine blade to a platform of a turbine blade. The platform includes a first platform wall that does not support the vane and a second platform wall that supports the vane. At the root of the vane and over the course of the transition region from the turbine blade to the platform, the first platform wall is aerodynamically curved and the course of the second platform wall has a receding shoulder in relation to the first platform wall, as a continuation of the vane.

Turbine blade and gas turbine equipped with a turbine blade

The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.

There is described a turbine blade of a gas turbine comprising a suction-side blade wall and a pressure-side blade wall that, in the trailing edge area, runs toward the suction-side blade wall. This suction-side blade wall has a trailing edge projection projecting over the end edge of the pressure-side blade wall at least in a partial section of the trailing edge area. A turbine blade of the aforementioned type is designed for a particularly long serviceable life while requiring little cooling air. To this end, the pressure-side surface of the trailing edge projection has a number of trough-shaped recesses that increase the transfer of heat from the trailing edge projection by a local swirling of the cooling air.

Turbine blade for a gas turbine, use of a turbine blade and method for cooling a turbine blade

The invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region, which is located at the root of the vane having a platform that extends transversally to the blade axis. The aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner. Therefore, the platform is configured by an elastic sheet metal part that rests on the vane. Said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine, said conduit having an annular cross-section for a working medium and a second vane stage that is situated downstream of a first vane stage, which runs along the axis.

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Erkrath, Germany

Michael Händler