Abstract: A filter system for filtering a fluid has a filter housing with housing top part and housing bottom part, wherein the housing top and bottom parts extend along a housing axis. A filter pack arranged in the filter housing separates fluid-tightly a clean fluid side and a raw fluid side from each other. The filter pack has a filter element with a hollow cylinder-type filter bellows arranged about a longitudinal axis of the filter element. The filter element has a first substantially closed end face and a first end disk arranged thereat, wherein the first end disk is positioned opposite a second end disk of the filter element. The second end disk has a fluid passage for filtered fluid. A resonator with an end closed by a bottom is arranged inside the filter pack such that the bottom is oriented toward the first end disk of the filter element.

Abstract: A filter element for a filter system has a hollow cylinder-type filter bellows with an end face and a substantially closed bottom provided thereat. At least one resonator structure provided at the bottom provides noise attenuation of a flowing fluid. The resonator structure has two or more grooves arranged at an outer side of the bottom and separated from each other by a partition. At least one of the grooves is connected in fluid communication through an opening to an interior of the filter element. The resonator structure, when installed in a filter housing of the filter system as intended, seals tightly relative to a complementary resonator structure of the filter housing. The grooves are connected in fluid communication through connection openings arranged in the resonator structure of the filter element and/or the complementary resonator structure of the filter housing. A filter system with such a filter element is provided.

Abstract: A blade, in particular a rotor blade or a stator vane, for a gas turbomachine, in particular a turbojet engine, the blade having an airfoil (1) for deflecting a flow of working fluid and a first platform (3) connected thereto, in particular integrally connected thereto, to radially bound a flow duct for the working fluid, the airfoil having a suction side and a pressure side (1.1) which are connected at a leading edge (1.2) and at a trailing edge (1.3). The trailing edge has a first minimum wall thickness in a first region (A) of a radial longitudinal extent (R) of the airfoil proximal to the first platform (3), and a maximum wall thickness that is smaller than the first minimum wall thickness in a platform-distal region (C) of the radial longitudinal extent.

Abstract: A turbine or compressor stage of a gas turbine, the rotor blade having a radially outer shroud (1) which has a sealing fin array having a first sealing fin (3.1) and a second sealing fin (3.2) which is adjacent to the first sealing fin and connected thereto by a first groove base (10) having a circumferential region (13) of maximum radial height, which is located at a first circumferential position is provided. The sealing fin array has a third sealing fin (3.3) adjacent to the second sealing fin and opposite to the first sealing fin, the third sealing fin being connected to the second sealing fin by a second groove base (20) having a circumferential region (23) of maximum radial height, which is located at a second circumferential position different from the first circumferential position.

Abstract: A turbine or compressor stage of a gas turbine, the rotor blade having a radially outer shroud (1) which has a sealing fin array having a first sealing fin (3.1) and a second sealing fin (3.2) which is adjacent to the first sealing fin and connected thereto by a first groove base (10) having a circumferential region (13) of maximum radial height, which is located at a first circumferential position is provided. The sealing fin array has a third sealing fin (3.3) adjacent to the second sealing fin and opposite to the first sealing fin, the third sealing fin being connected to the second sealing fin by a second groove base (20) having a circumferential region (23) of maximum radial height, which is located at a second circumferential position different from the first circumferential position.

Abstract: A blade, in particular a rotor blade or a stator vane, for a gas turbomachine, in particular a turbojet engine, the blade having an airfoil (1) for deflecting a flow of working fluid and a first platform (3) connected thereto, in particular integrally connected thereto, to radially bound a flow duct for the working fluid, the airfoil having a suction side and a pressure side (1.1) which are connected at a leading edge (1.2) and at a trailing edge (1.3). The trailing edge has a first minimum wall thickness in a first region (A) of a radial longitudinal extent (R) of the airfoil proximal to the first platform (3), and a maximum wall thickness that is smaller than the first minimum wall thickness in a platform-distal region (C) of the radial longitudinal extent.