Abstract: A filter element for use in a filter disc, wherein a plurality of filter elements are arranged on a rotor shaft in a manner allowing liquid communication between the inside of the filter elements and the inside of the rotor shaft. The filter element has at least one passage in an edge structure for liquid communication between the inside of adjacent filter elements when the filter elements are assembled forming a filter disc. The passage has different passage area along the edge structure.

Abstract: A filter element for use in a filter disc, wherein a plurality of filter elements are arranged on a rotor shaft in a manner allowing liquid communication between the inside of the filter elements and the inside of the rotor shaft. The filter element has at least one passage in an edge structure for liquid communication between the inside of adjacent filter elements when the filter elements are assembled forming a filter disc. The passage has different passage area along the edge structure.

Abstract: A filter element for use in a filter disc, wherein a plurality of filter elements are arranged on a rotor shaft in a manner allowing liquid communication between the inside of the filter elements and the inside of the rotor shaft. The filter element has at least one passage in an edge structure for liquid communication between the inside of adjacent filter elements when the filter elements are assembled forming a filter disc. The passage has different passage area along the edge structure.

Abstract: A filter element for use in a filter disc, wherein a plurality of filter elements are arranged on a rotor shaft in a manner allowing liquid communication between the inside of the filter elements and the inside of the rotor shaft. The filter element has at least one passage in an edge structure for liquid communication between the inside of adjacent filter elements when the filter elements are assembled forming a filter disc. The passage has different passage area along the edge structure.

Abstract: A gas-turbine engine includes stator vanes (1) angularly variable about their longitudinal axes by actuating elements in order to control airflow supplied to downstream rotor blades (6). The actuating elements are arranged in the most confined downstream stages of the compressors and/or turbines, with these stages being exposed to high temperatures, so that stable and efficient operation is ensured. The actuating elements (8) fixed to the inner or the outer casing (4, 12) are made of a material expanding, contracting or deforming in dependence of the temperature and transmit the respective deformation to the swivellably borne stator vanes (1).

Abstract: A gas-turbine engine includes stator vanes (1) angularly variable about their longitudinal axes by actuating elements in order to control airflow supplied to downstream rotor blades (6). The actuating elements are arranged in the most confined downstream stages of the compressors and/or turbines, with these stages being exposed to high temperatures, so that stable and efficient operation is ensured. The actuating elements (8) fixed to the inner or the outer casing (4, 12) are made of a material expanding, contracting or deforming in dependence of the temperature and transmit the respective deformation to the swivellably borne stator vanes (1).

Abstract: A turbine shroud segment attachment with a casing (1) and several shroud segments (2) arranged in the casing (1), wherein the individual shroud segments (2) are located in the casing (1) with a circumferential clearance (3) between the individual shroud segments (2), in that the clearance (3) is reduced to zero at a given temperature difference between the casing (1) and the shroud segments (2), and in that the shroud segments (2) are retained on the casing (1) by way of an elastically deformable locating arrangement.

Abstract: A turbine shroud segment attachment with a casing (1) and several shroud segments (2) arranged in the casing (1), wherein the individual shroud segments (2) are located in the casing (1) with a circumferential clearance (3) between the individual shroud segments (2), in that the clearance (3) is reduced to zero at a given temperature difference between the casing (1) and the shroud segments (2), and in that the shroud segments (2) are retained on the casing (1) by way of an elastically deformable locating arrangement.

Abstract: This invention relate to a retaining arrangement for rotor blades of axial-flow turbomachinery which features blade roots slots on a rotor disk for the accommodation and radial fixation of roter blades and which further features a continues, circumferential retaining ring for the axial fixation of the rotor blades in the blade root slots and a locking arrangement for the axial retention of the retaining ring. The retaining arrangement is characterized in that the retaining ring has recesses which correspond with sections of the blade root slots and projecting sections on its outer circumference. The present invention provides a cost-effective retaining arrangements for blade of axial-flow turbomachinery which provides for better control of the leakage flows in the blade root area, generally improved flow conditions in the inter-stage area, lower centrifugal forces and ease of assembly.