General Electric Technology Gmbh

Ansaldo Energia Switzerland Ag

Ansaldo Energia IP UK Limited

Christopher Michael Robson

Gaurav Pathak

Klaus Doebbeling

Giovanni Cataldi

Andreas Rueter

Guenter Filkorn

Massimo Giusti

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 present invention relates to a method of decelerating a turbine rotor of a turbine engine. At least one electric motor is engaged with the turbine rotor. A braking system, preferably the starting system, is engaged with the at least one electric motor, preferably the generator of the turbine engine, so as to use the at least one electric motor to apply a negative (braking) torque on the turbine rotor. The method includes after flame off, the braking system being used for dissipating kinetic energy available in the turbine engine after flame off by means of the at least one electric motor.

Method of operating a turbine engine after flame off

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

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Ennetbaden, Switzerland

Christopher Michael Robson