Abstract: A fuel supply arrangement for a gas turbine burner is provided. The fuel distribution arrangement includes a rear section external to the burner located between a turbine wall and a fuel distribution system interface directing fuel into fuel supply circuits. The fuel distribution system interface has four fuel connections. An intermediate section is located between the turbine wall and the backside wall of a distribution chamber; and a front section in front of the second section located between said backside wall of the distribution chamber and a burner central backside block. The fuel distribution arrangement includes pipes for gaseous fuel, liquid fuel, as well as pilot gas, and liquid pilot fuel. In the rear section the pipes for gaseous fuel and for liquid fuel are arranged concentrically, and in at least one portion of the intermediate section the pipe for gaseous fuel is arranged non-concentrically with the liquid fuel pipe.

Abstract: The invention relates to a method for determining the thickness of multi-layer films (13) comprising layers consisting of various non-conductive materials. According to said method, the thickness of the multi-layer film (13) is measured by a first sensor (17) and a second sensor (16) and optionally additional sensors. The first sensor (17) measures the profile of the total thickness in a short cycle with a duration of approximately 1-2 minutes, but with a large measuring error margin. The second sensor (16) measures the profile of the total thickness with a small measuring error margin but in a long cycle with a duration of approximately 10 to 30 minutes. A correction profile for the first sensor (17) can be calculated by comparing the two thickness profiles.

Abstract: The invention relates to a method for determining the thickness of multi-layer films (13) comprising layers consisting of various non-conductive materials. According to said method, the thickness of the multi-layer film (13) is measured by a first sensor (17) and a second sensor (16) and optionally additional sensors, whereby all the sensors take a measurement at the same location under the same conditions if possible. The first sensor (17) and the second (16) or additional sensors generate different measured values for layers of the multi-layer film (13) of the same thickness consisting of the same material (13). The measured signals of the sensors (16, 17) are fed to a computer (18), which determines the total thickness of the multi-layer film (13) and/or the thickness of the individual layers of the multi-layer film (13) from the different measured values of the first sensor (17) and the second (16) or additional sensors.

Abstract: The invention relates to a method for determining the thickness of multi-layer films (13) comprising layers consisting of various non-conductive materials. According to said method, the thickness of the multi-layer film (13) is measured by a first sensor (17) and a second sensor (16) and optionally additional sensors. The first sensor (17) measures the profile of the total thickness in a short cycle with a duration of approximately 1-2 minutes, but with a large measuring error margin. The second sensor (16) measures the profile of the total thickness with a small measuring error margin but in a long cycle with a duration of approximately 10 to 30 minutes. A correction profile for the first sensor (17) can be calculated by comparing the two thickness profiles.

Abstract: A fuel supply arrangement for a gas turbine burner is provided. The fuel distribution arrangement includes a rear section external to the burner located between a turbine wall and a fuel distribution system interface directing fuel into fuel supply circuits. The fuel distribution system interface has four fuel connections. An intermediate section is located between the turbine wall and the backside wall of a distribution chamber; and a front section in front of the second section located between said backside wall of the distribution chamber and a burner central backside block. The fuel distribution arrangement includes pipes for gaseous fuel, liquid fuel, as well as pilot gas, and liquid pilot fuel. In the rear section the pipes for gaseous fuel and for liquid fuel are arranged concentrically, and in at least one portion of the intermediate section the pipe for gaseous fuel is arranged non-concentrically with the liquid fuel pipe.

Abstract: The present invention relates to a burner, substantially comprising a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream, the swirl generator having combustion-air inlet openings for the combustion air stream that enters the burner, and the means for introducing fuel into the combustion air stream comprising one or more first fuel feeds having a group of first fuel outlet openings, arranged distributed around the burner axis at a combustion chamber-side end of the burner. The burner is distinguished by the fact that the one or more first fuel feeds having the group of first fuel outlet openings are mechanically decoupled from the swirl generator. The present burner allows reliable and safe use of synthesis gas in both dilute and undiluted form as fuel.

Abstract: The present invention relates to a burner, substantially comprising a swirl generator for a combustion air stream and means for introducing fuel into the combustion air stream, the swirl generator having combustion-air inlet openings for the combustion air stream that enters the burner, and the means for introducing fuel into the combustion air stream comprising one or more first fuel feeds having a group of first fuel outlet openings, arranged distributed around the burner axis at a combustion chamber-side end of the burner. The burner is distinguished by the fact that the one or more first fuel feeds having the group of first fuel outlet openings are mechanically decoupled from the swirl generator. The present burner allows reliable and safe use of synthesis gas in both dilute and undiluted form as fuel.