Alstom Technology Limited

General Electric Corporation Gmbh

E2s Power Ag

Ansaldo Energia Switzerland Ag

Vladimir Vassiliev

Alexander Trishkin

Sasha Savic

Fulvio Magni

Dmitry V Vinogradov

Arkadi Fokine

Andrey Sedlov

Igor Baibuzenko

Victor Vladimirovich Odinokov

Sergey Pancheshnyi

Dmitri Vinogradov

Erich Herold Kisi

Dylan Cuskelly

Sergey Anatolievich Chernyshev

Harald Kissel

Rico Poser

Dimitri Vinogradov

Alexandre Trishkin

Dimtry Vinogradov

An energy storage device is provided with at least one energy storage unit (). The energy storage unit () comprises a thermal storage element () made of a solid material and an electrical heating device () for heating the thermal storage element (). According to a first concept, the electrical heating device () is adapted to heat the thermal storage element () by means of generating an electric current within the material of the thermal storage element (). According to a second concept, an electric gas insulation () is provided, in order to electrically insulate the electrical heating device () from the thermal storage element (). Furthermore, a method for storing energy by means of such an energy storage device is provided.

Energy storage device and method for storing energy

A combustor includes a combustor shell, an inner liner disposed inside the combustor shell and having an inner surface defining a cavity configured to receive hot combustion gases from a combustion chamber of the combustor, and an outer surface, the combustor shell and the inner liner defining an annular flow channel therebetween, and a segment carrier operatively connected to the inner liner and operative to receive an upper portion of the inner liner, the segment carrier and the inner liner defining a purging cavity therebetween. The inner liner includes a plurality of impingement jet holes configured to direct a flow of cooling air from the annular flow channel to the purging cavity.

System and method for impingement cooling of turbine system components

A seal arrangement for a silo combustor includes a first casing and a second casing each forming a passageway for a gas, an end portion of the first casing being disposed radially inside an end portion of the second casing such that the first and the second casing form an overlapping region having a radial gap. A segmented seal has at least two adjacent segments disposed in the overlapping region so as to seal the radial gap, wherein the first casing includes at least one opening disposed in a region between the at least two adjacent segments.

Seal arrangement

A gas turbine has a cooling air passage which extends along the leading edge of the blade airfoil, which cooling air passage has an outlet opening which is arranged in the region of the blade tip. The contour of the outlet opening is geometrically similar to the cross section of the cooling air passage. As a result, flow inhomogeneities of the cooling air flow, which locally negatively influence heat transfer, and consequently cooling efficiency, are avoided.

Convectively cooled gas turbine blade

A fluid flow machine blade () is provided on the outer contour of the airfoil () with a thermal barrier coating (). In this context, quite purposefully, only part-regions of the airfoil have the thermal barrier coating, while well-defined second part-regions of the airfoil () are realized purposefully without thermal barrier coating. In particular, along the trailing edge () of the airfoil, a region () is realized without thermal barrier coating. In further embodiments of the invention, regions of the airfoil () which lie adjacent to foot-side () or tip () platforms of the blades are realized without thermal barrier coating.

Fluid flow machine blade

Growing community of inventors

Turgi, Switzerland

Vladimir Vassiliev