Abstract: A gas turbine unit as well as a method for operating a gas turbine with high-pressure turbine and a low-pressure turbine unit are disclosed. A very quick and at the same time easily controllable augmentation or reduction of the shaft power of the gas turbine unit can be achieved by providing at least one liquid droplet injection device on the upstream side of said compressor for injecting liquid into the stream of intake air in order to increase the shaft power generated by the gas turbine unit. The amount of water mass flow corresponding to the desired increase or decrease of shaft power output of the gas turbine unit is added or reduced in the form of liquid droplets in a substantially stepless manner and immediately within a time interval that is determined by the design characteristics of the liquid droplet injection device.

Abstract: A gas turbine unit and method of operation thereof are disclosed. A very quick and easily controllable augmentation or reduction of shaft power produced by the gas turbine unit, in particular of large gas turbine units exhibiting a pressure ratio larger than 15 bar, is achieved by providing at least one liquid droplet injection device on the upstream side of the compressor for injecting liquid into the stream of intake air. The injection device allows the addition of liquid mass flow in the form of liquid droplets corresponding to the desired increase of shaft power. The amount of water mass flow corresponding to the desired increase or decrease of shaft power output is added or reduced in a substantially stepless manner immediately within a time interval determined by design characteristics of the injection device. Water mass flow is preferentially injected substantially across the entire cross-section of the intake air guide.

Abstract: A gas turbine unit and method of operation thereof are disclosed. A very quick and easily controllable augmentation or reduction of shaft power produced by the gas turbine unit, in particular of large gas turbine units exhibiting a pressure ratio larger than 15 bar, is achieved by providing at least one liquid droplet injection device on the upstream side of the compressor for injecting liquid into the stream of intake air. The injection device allows the addition of liquid mass flow in the form of liquid droplets corresponding to the desired increase of shaft power. The amount of water mass flow corresponding to the desired increase or decrease of shaft power output is added or reduced in a substantially stepless manner immediately within a time interval determined by design characteristics of the injection device. Water mass flow is preferentially injected substantially across the entire cross-section of the intake air guide.

Abstract: A gas turbine unit as well as a method for operating a gas turbine with high-pressure turbine and a low-pressure turbine unit are disclosed. A very quick and at the same time easily controllable augmentation or reduction of the shaft power of the gas turbine unit can be achieved by providing at least one liquid droplet injection device on the upstream side of said compressor for injecting liquid into the stream of intake air in order to increase the shaft power generated by the gas turbine unit. The amount of water mass flow corresponding to the desired increase or decrease of shaft power output of the gas turbine unit is added or reduced in the form of liquid droplets in a substantially stepless manner and immediately within a time interval that is determined by the design characteristics of the liquid droplet injection device.

Abstract: A support (1) for a reflective target to be mounted on a turbine casing, which is used in casing bending measurements. The support (1) comprises a tube (2), which was chosen to ensure a thermal expansion coefficient near zero at the operating temperatures of the casing. The tube (2) is located at one end in a steel holder (3). In the middle of the tube (2) is arranged a metal rod (9), which is fixed to the holder (3). At the opposite end of the tube (2) is an insert (7), which has an apertures through which passes the metal rod (9). Within the insert (7) the metal rod (9) is screw threaded so it can be turned to provide always enough tension at all operating temperatures and the metal tube (9) is held tight, secure, and has minimal vibration.

Abstract: A support (1) for a reflective target to be mounted on a turbine casing, which is used in casing bending measurements. The support (1) comprises a tube (2), which was chosen to ensure a thermal expansion coefficient near zero at the operating temperatures of the casing. The tube (2) is located at one end in a steel holder (3). In the middle of the tube (2) is arranged a metal rod (9), which is fixed to the holder (3). At the opposite end of the tube (2) is an insert (7), which has an apertures through which passes the metal rod (9). Within the insert (7) the metal rod (9) is screw threaded so it can be turned to provide always enough tension at all operating temperatures and the metal tube (9) is held tight, secure, and has minimal vibration.

Abstract: In a method of generating a third gas flow of medium pressure and medium temperature, which can be particularly employed as cooling air for a gas turbine, from a first gas flow of high-pressure and high temperature, a high effectiveness with simultaneous simple process control is achieved in an arrangement wherein the reduction is undertaken by stepwise energy exchange between the first gas flow and a second gas flow of low pressure and low temperature in a cascade consisting of a plurality of energy exchangers connected in series.