Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Hanspeter Knopfel

Stefan Rofka

Robert Marmilic

Sergei Riazantsev

Ennio Pasqualotto

Sergey Shchukin

A gas turbine having a compressor, a combustor downstream from the compressor in a gas flow direction, and a turbine downstream from the combustor in the gas flow direction is described herein. The turbine includes a rotating part and a stationary part arranged around the rotating part. A gap between the rotating part and the stationary part, extends in a substantially radial direction relative to the rotation axis of the rotating part. A cooling fluid flows from the compressor to the gap, wherein at least a part of the cooling path extends in the stationary part, and wherein a pre-swirl nozzle is arranged adjacent to the gap and within the cooling path in the stationary part.

Gas turbine cooling systems and methods

A premix burner of the multi-cone type for a gas turbine, that includes a plurality of shells, which are arranged around a central burner axis and are parts of a virtual, axially extending common cone, which opens in a downstream direction, whereby the parts are displaced perpendicular to the burner axis such that a tangential slot is defined between each pair of adjacent shells. A disadvantageous transition piece between the shells and a downstream mixing tube is avoided by bordering the downstream ends of the shells by intersecting planes, which are defined by intersecting the shells with a virtual coaxial cylinder of a predetermined radius.

Premix burner of the multi-cone type for a gas turbine

Growing community of inventors

Dottikon, Switzerland

Hanspeter Knopfel