Abstract: A method includes providing a furnace including a radiant heating zone having metal heating coils and burners, concurrently applying a combustion media, having a combustibility, and a diluent to the burners, the burners burning the combustion media producing flames heating the radiant heating zone, and the diluent reducing the combustibility of the combustion media for reducing heat generated by the flames for reducing heat degradation of the metal heating coils.

Abstract: A method includes providing a furnace including a radiant heating zone having metal heating coils and burners, concurrently applying a combustion media, having a combustibility, and a diluent to the burners, the burners burning the combustion media producing flames heating the radiant heating zone, and the diluent reducing the combustibility of the combustion media for reducing heat generated by the flames for reducing heat degradation of the metal heating coils.

Abstract: Combustion driven pressure pulsations may limit the range of operating conditions where a modern gas turbine can operate with low emission and high efficiency performance. The control of acoustic vibrations has been consequently growing as an essential issue in gas turbine design, development and maintenance. The basic idea of the present invention is to use cooling air leakage through the gaps (7) of combustor liner segments (3;4) to get acoustic damping of combustion pulsations. The main component of the design is the sealing device (8) which covers the gap (7) between the two liner segments (3) and (4). The sealing device (8) collects in the plenum (9) some of the cooling air (6) flowing between the outer casing (1) and the inner liner structure (2). For this purpose the sealing device (8) is provided with openings (12) along the side walls (10) which allow the cooling air (6) to enter the plenum (9).

Abstract: A rotor for a gas turbine is disclosed. The rotor has a plurality of rotor disks arranged one behind the other on a rotor axis. The rotor extends between a compressor part and a turbine part, and has a central bore running between the compressor part and the turbine part. Fluid passages are arranged to conduct cooling air from the compressor part and direct cooling through the central bore and direct cooling air from the turbine part radially outward through the rotor. The rotor disks have fluid cavities that are connected to the central bore by having an outer diameter that is greater than the inside diameter of the central bore. The fluid cavities are subdivided into individual chambers by a plurality of radial ribs.

Abstract: Combustion driven pressure pulsations may limit the range of operating conditions where a modern gas turbine can operate with low emission and high efficiency performance. The control of acoustic vibrations has been consequently growing as an essential issue in gas turbine design, development and maintenance. The basic idea of the present invention is to use cooling air leakage through the gaps (7) of combustor liner segments (3;4) to get acoustic damping of combustion pulsations. The main component of the design is the sealing device (8) which covers the gap (7) between the two liner segments (3) and (4). The sealing device (8) collects in the plenum (9) some of the cooling air (6) flowing between the outer casing (1) and the inner liner structure (2). For this purpose the sealing device (8) is provided with openings (12) along the side walls (10) which allow the cooling air (6) to enter the plenum (9).

Abstract: Between the rotor and stator of an axial turbo machine, sealing strips of a labyrinth seal that are mortised into sealing strip grooves are provided. Between the sealing strips relief grooves are provided in such a way that the axial stiffness of the rotor or stator is essentially steady. This may be achieved by one or more flat relief grooves, a corrugated surface, or by filling the relief grooves entirely or partially with a suitable, elastic material so that a more even axial tension distribution is achieved between the sealing strip grooves and relief grooves along the rotor or stator section.

Abstract: The present invention relates to a method for monitoring the creep behavior of rotating components of a compressor stage or turbine stage. In the method, at least one test element (2) is mounted in a region of the compressor stage or turbine stage in which the test element is exposed to an operating load comparable to that of the component to be monitored. The test element (2) is investigated after a predeterminable operating period of the component to be monitored. Finally, the creep behavior of the component to be monitored is derived from the creep behavior of the test element. The method makes it possible to detect exactly the creep behavior or creep damage of the component to be monitored, during the useful life of this component.

Abstract: Between the rotor and stator of an axial turbo machine, sealing strips of a labyrinth seal that are mortised into sealing strip grooves are provided. Between the sealing strips relief grooves are provided in such a way that the axial stiffness of the rotor or stator is essentially steady. This may be achieved by one or more flat relief grooves, a corrugated surface, or by filling the relief grooves entirely or partially with a suitable, elastic material so that a more even axial tension distribution is achieved between the sealing strip grooves and relief grooves along the rotor or stator section.