Abstract: A method for the manufacture of a double-row blade wheel for a fluid-flow machine that includes a first grid row with a plurality of first blades and a second grid row with a plurality of second blades is provided. The method includes the following steps: manufacturing a first grid row or segments of the first grid row; manufacturing a second grid row or segments of the second grid row, independently of the first row; and after the respective manufacture, connecting the first grid row to the second grid row or connecting segments of the first grid row and/or of the second grid row to one another or to one of the grid rows.

Abstract: The invention relates to an engine nacelle, including: a nacelle wall that has an inner side and an outer side; an inlet lip that is embodied at that end of the engine nacelle that is formed upstream; and an engine intake that takes in the air required for the respective engine and that is formed by the inner side of the nacelle wall. It is provided that the nacelle wall includes an air-permeable structure that extends from the outer side to the inner side of the nacelle wall, and that is configured for passing air that flows against the outer side from the outer side to the inner side. The invention further relates to a method for influencing the flows inside an engine nacelle.

Abstract: A flow guiding device in a turbomachine with at least one rotor module that is arranged on a shaft is provided. The rotor module has at least two rotor discs between which respectively one rotor cavity is arranged. The rotor cavities are connected to each other in an air-guiding manner for an airflow by means of openings inside the rotor discs and at least one pressure sink device for creating a localized negative pressure is arranged inside the last rotor cavity as viewed in the main flow direction of the turbomachine.

Abstract: A method for the manufacture of a double-row blade wheel for a fluid-flow machine that includes a first grid row with a plurality of first blades and a second grid row with a plurality of second blades is provided. The method includes the following steps: manufacturing a first grid row or segments of the first grid row; manufacturing a second grid row or segments of the second grid row, independently of the first row; and after the respective manufacture, connecting the first grid row to the second grid row or connecting segments of the first grid row and/or of the second grid row to one another or to one of the grid rows.

Abstract: A compressor for a gas turbine, in particular an aircraft gas turbine, has a rotor hub carrying rotor blades, a stator equipped with stator vanes, a shroud associated to the stator vanes, and an arrangement providing sealing between the shroud and rotor hub to prevent leakage. To achieve almost complete suppression of leakage air and, concurrently, simplification of design and manufacture, the sealing arrangement (20) between the shroud (8) and rotor hub (3) is formed by a discharge arrangement (23) for leakage air.