Alstom Technology Limited

General Electric Technology Gmbh

Karsten Franitza

Matthias Hoebel

Peter Marx

Ulrich Robert Steiger

Bernd Fehrmann

Anton Nemet

Darrel Shayne Lilley

Peter Lang

Christoph Kohles

Andrea Brighenti

Disclosed is a method for operating a gas turbine () comprising a compressor (), which is equipped with variable inlet guide vanes () and receives at its inlet an inlet air flow, which has passed a temperature-affecting air inlet system (), a combustor (') and a turbine (&#x2032;). In a closed loop control scheme, a control variable indicative of the turbine outlet temperature (TAT) is generated, and the air inlet system () and/or the variable inlet guide vanes () are controlled in accordance with said control variable such that the turbine outlet temperature (TAT) is kept at or above a desired setting value (TAT).

Method for operating a combined cycle power plant and plant to carry out such a method

A measuring apparatus () for contactless detection of a distance between a surface () of a measurement object () and the measuring apparatus (), and for simultaneous contactless visual detection of the surface (), has a measuring head () holding a distance measuring device (), a camera apparatus () and an illumination device (), the illumination device () illuminating an operating point () on the surface () of the measurement object () that is simultaneously focused by the camera apparatus () and the distance measuring device (). On an optical axis (), between the illumination device () and the operating point (), a mirror and filter device (), that has at least one dichroic mirror () that transmits or reflects light beams as a function of wavelength, and thereby splits light reflected by the operating point () between the distance measuring device () and the camera apparatus (), is provided.

Measuring apparatus

A method of removing unwanted coating material from cooling passages of a turbine component includes determining coordinates of the position and orientation of cooling passages at the surface of the turbine component and determining reference points in the region of the cooling passages. After coating of the turbine component, the reference points are measured once again and the thickness of the coating is calculated. In a basic processing program, the data for the position, passage orientation and coating thicknesses and also CAD data for the cooling passages are interlinked and a laser processing program is automatically adapted for each individual cooling passage. Using the laser processing program, a pulsed laser is guided over disk-shaped volume segments of the unwanted coating material and the material is removed in the process.

Method of processing turbine components

Growing community of inventors

Baden, Switzerland

Karsten Franitza