Alstom Technology Limited

General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Gaurav Pathak

Christopher Michael Robson

Shailendra Naik

Giovanni Cataldi

Andreas Rueter

Guenter Filkorn

The application describes a method of operating a gas turbine during a cool-down phase. The gas turbine provides a compressor, a combustor downstream of the compressor, and a turbine downstream of the combustor, with the turbine providing a turbine vane carrier. The method includes feeding a flow of cooling air from the compressor to the turbine vane carrier, measuring a temperature of the flow of cooling air and measuring a temperature of the turbine vane carrier. In the method, the flow of cooling air is fed at a first flow rate when the temperature of the turbine vane carrier is lower than the temperature of the cooling air, and the flow of cooling air is fed at a second flow rate when the temperature of the turbine vane carrier is higher than the temperature of the cooling air, wherein the first flow rate is higher than the second flow rate.

Gas turbine cool-down phase operation methods for controlling turbine clearance by adjusting air flow rate

The maintenance assembly, for workers to perform maintenance activities within a gas turbine engine, is capable of being arranged within a cavity, generally around a combustor, accessible from a manhole of the gas turbine engine. The maintenance assembly includes a platform, and an inflatable member cooperatively configured to the platform. The inflatable member is at a normal condition, when placed outside of the cavity, being at a deflated position and is at a working condition, when arranged within the cavity, being at inflated position so as to accommodate a shape coordinating the cavity in such a manner that the platform is advance within the cavity up to a predetermined level to enable the workers on the platform to reach at a predetermined position within the cavity to perform the maintenance activities.

Maintenance assembly adaptable within gas turbine engine

A blade for a gas turbine includes an airfoil extending in radial direction of the turbine or longitudinal direction of the blade, respectively, between a platform and a blade tip. The airfoil is bordered across the airfoil by a leading edge and a trailing edge and has a suction side and a pressure side. At the trailing edge a first cooling passage runs parallel to the trailing edge from the platform to the blade tip in the interior of the airfoil. The cooling passage is supplied with a cooling air flow from the platform side, and from which cooling air is discharged through a plurality of cooling holes arranged all over the blade. For such a blade the cooling is optimized by providing a first cooling passage, the passage area of which is tapered in radial direction by between 35% and 59%.

Cooled blade for a gas turbine, method for producing such a blade, and gas turbine having such a blade

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Ennetbaden, Switzerland

Gaurav Pathak