Abstract: The invention relates to a component for holding down measuring leads and measuring devices in a groove (6), provided therefor and having holes (7), of a machine part (5). It is characterized in that the component is designed in the form of a disk (1) which has a cutting edge (3) on its circumference, the cutting edge (3) not being formed continuously over the entire circumference but consisting of two partial cutting edges (3′, 3″) circumferentially opposite one another. In addition, the disk (1) has a central opening (2) in the form of a hexagon socket. For fitting, the disk (1) is put into the hole (7) in such a way that its two partial cutting edges (3′, 3″) point in the longitudinal direction of the groove (6), then a hexagon socket key is inserted into the opening (2) of the disk (1) and the key is turned while the disk (1) is pressed down at the same time, so that the cutting edges (3′, 3″) cut into the material of the machine part (5) and jam tight.

Abstract: A probe for measuring pressure oscillations includes an inner tube functioning as a measuring tube, an outer tube positioned so as to envelop the measuring tube, a toroidal space open to one side being defined between an outer wall of the measuring tube and an inner wall of the outer tube, a pressure transmitter, which is in connection with the interior of the measuring tube in the area of a transmitter end of the measuring tube, and a semi-infinite tube, which is connected at a first end to the transmitter end of the measuring tube, and which is connected at a second end to the toroidal space. The semi-infinite tube is constructed as a winding positioned around at least one of the measuring tube and the outer tube, thereby providing a compact and robust construction of a probe module, which is suitable especially for continuous use in the measuring of combustor pulsations in gas turbines.

Abstract: The invention pertains to a probe for measuring pressure pulsations. The probe comprises an inner tube (1) functioning as a measurement tube; an outer tube (12) arranged to envelop the measurement tube, and forming a toroidal space (14) between the inner and the outer tube; a pressure transmitter (6) which is in connection with the interior of the measurement tube on a transmitter side of said tube; a semi-infinite tube (8) with a first end in connection with the transmitter side end (3) of the measurement tube, and with a second end (11) in connection with the toroidal space. The semi-infinite tube (8) is arranged as a winding around the inner and/or outer tube, resulting in a compact and robust design of the probe, which is especially suited for a long-duration use for the measurement of combustor pulsations of gas turbines.(FIG.

Abstract: The invention relates to a component for holding down measuring leads and measuring devices in a groove (6), provided therefor and having holes (7), of a machine part (5). It is characterized in that the component is designed in the form of a disk (1) which has a cutting edge (3) on its circumference, the cutting edge (3) not being formed continuously over the entire circumference but consisting of two partial cutting edges (3′, 3″) circumferentially opposite one another. In addition, the disk (1) has a central opening (2) in the form of a hexagon socket. For fitting, the disk (1) is put into the hole (7) in such a way that its two partial cutting edges (3′, 3″) point in the longitudinal direction of the groove (6), then a hexagon socket key is inserted into the opening (2) of the disk (1) and the key is turned while the disk (1) is pressed down at the same time, so that the cutting edges (3′, 3″) cut into the material of the machine part (5) and jam tight.

Abstract: The invention relates to a ceramic lining for combustion chambers (8) consisting of several juxtaposed elements (1) that are attached by means of a retention bolt (3) to the inside of a thermally highly stressed metallic support wall (4), whereby at least one insulation body (5) is arranged between the metallic support wall (4) and the ceramic elements (1). It is characterized in that the ceramic elements (1) essentially have the shape of a straight, regular pyramid whose base (2) has n corners, preferably three corners, and faces the combustion chamber (8), and into whose tip the retention bolt (3) is integrated.

Abstract: In the case of a ceramic lining for combustion spaces, comprising at least one wall panel (3) of high temperature resistant structural ceramic with at least one through-opening (6) and comprising one fastening element (4) per opening (6), the fastening element (4) being fastened by its foot in a metallic holding device (5) fastened on the metallic supporting wall (1), and the head of the fastening element (4) resting in the opening (6) of the wall panel (3), and there being an insulating layer (2) arranged between the metallic supporting wall (1) and the ceramic wall panel (3), the fastening element (4) consists of high temperature resistant structural ceramic. The wall panel (3) is drawn-in in the direction of the metallic supporting wall (1) in the region of the opening (6) and the fastening element (4) is resiliently linked to a special holding device (5).

Abstract: In a gas turbine combustion chamber having an annular combustion space, the combustion chamber inlet is equipped with a plurality of burners, which are uniformly distributed in the peripheral direction and are fastened to a front plate. Scavenged Helmholtz resonators (21) consisting of supply tube (51), resonance volume (50) and damping tube (52) are arranged in the region of the burners. The damping tubes (52) are designed so as to be exchangeable, for which purpose the walls of the combustion space are provided with a manhole.