Abstract: A masking arrangement for a gas turbine engine includes a plurality of annular elements arranged overlapping one another when these are viewed in an axial direction so as to mask at least a substantial portion of any interior hot and rotating gas turbine engine part at an aft end of the gas turbine engine from rear view when the masking arrangement is applied downstream the interior part in the gas turbine engine.

Abstract: A rotor element includes at least one irregularity with regard to rotational properties in its circumferential direction and the irregularity is positioned so as to separate the mechanical natural frequencies of the rotor element.

Abstract: A wheel for a rotating flow machine, comprising a rotor (1) on which a plurality of blades (2) are arranged projecting radially from the rotor (1), with each blade (2) having a root (3) attached to the rotor (1) and a blade top (4). In addition, the wheel comprises a ring (5) arranged concentrically in relation to the rotor (1) outside the blade tops (4) in such a way that the ring (5) and the blades (2) overlap each other when the ring and the blades are viewed in a radial direction, which ring (5) is arranged to be caused to rotate by the blades (2) when the rotor (1) rotates. The extent (9) of the blades (2) in a radial direction and the internal dimension (10) of the ring (5) are matched to each other in such a way that there is a clearance (?) between each blade top (4) and the ring (5) in radial direction when the rotor (1) is not rotating.

Abstract: In a blade intended to be exposed to a gas flow at high speed during operation of a flow machine comprising the blade, the blade includes a front end designed to face towards the incoming gas flow and a rear end. The front end is provided with a concave area that is such that during operation a stagnation point for the incoming gas flow arises at a distance in front of an outer blade surface that defines the concave area and such that the outer blade surface is thereby at least partially protected from the incoming gas flow.

Abstract: A cooling system for an aircraft includes a cooling circuit for transporting a coolant, with the cooling circuit running to a component in the aircraft that is heated up during flying in order to take up heat from the heated-up component via the coolant. The cooling circuit runs to a jet engine for propulsion of the aircraft in order to release heat to a flow of gas in the jet engine via the coolant.

Abstract: A bleed structure for a bleed passage in a gas turbine engine includes a first wall portion defining a first side of an opening for the passage, and a second wall portion defining a second side, opposite the first side of the opening. The first and second wall portions end at different positions in an extension direction of the opening.

Abstract: Bleed structure (17) for a bleed passage in a gas turbine engine. The structure includes a first wall portion (18) defining a first side of an opening for the passage and a second wall portion (19) defining a second side opposite the first side of the opening. The first and second wall portions (18, 19) end at different positions in an extension direction of the opening.

Abstract: An insulating composition for an electric power cable, and an electric power cable comprising a conductor surrounded by an inner semiconducting layer, an insulating layer, and an outer semiconducting layer, where the insulating layer consists of said insulating composition, are disclosed. The insulating composition comprises a crosslinkable multimodal ethylene copolymer obtained by coordinating catalysed polymerization of ethylene and at least one alpha-olefin, and has a density of 0.890-0.940 g/cm3 and an MFR2 of 0.1-10 g/10 min. The insulating composition is characterized in that the ethylene copolymer has an MWD of 3-12, a melting temperature of at most 125° C., and a viscosity of 2500-7000 Pa.s at 135° C. and a shear rate of 10 s−1, 1000-1800 Pa.s at 135° C. and a shear rate of 100 s−1, and 250-400 Pa.s at 135° C.