Abstract: A front centre body (FCB) structure for a geared turbofan engine comprises a plurality of vanes extending across the inlet duct to a low pressure compressor and integrates a heat exchanging arrangement to control the temperature of the gearbox of the turbofan engine.

Abstract: A gas turbine engine comprises at least one radially extending bleed passage optionally in fluid communication with at least one generally circumferentially extending plenum. The passage has an upstream inlet in fluid communication with a bleed passage and an outlet for releasing air from the plenum. The upstream leading edge of the inlet or the downstream trailing edge of the inlet has a non-uniform profile.

Abstract: The disclosure concerns a compressor blade for gas turbine engine. Specifically the blades of the compressor are modified according to predetermined requirements for both aerodynamic stability and fuel economy in multiple planes.

Abstract: A front centre body (FCB) structure for a geared turbofan engine comprises a plurality of vanes extending across the inlet duct to a low pressure compressor and integrates a heat exchanging arrangement to control the temperature of the gearbox of the turbofan engine.

Abstract: There is provided herein a pharmaceutical formulation having one or more component comprising valproic acid (VPA) and/or a pharmaceutically acceptable salt thereof; and one or more secondary acid, and optionally comprising one or more pharmaceutically acceptable excipient. There is also provided uses of such formulations.

Abstract: The present invention relates to a method of and a vertical pumping device (1) for internally distributing Hg in a fluorescent tube body (3). The bottom (7) of the fluorescent tube body (3) is closed. The device (1) arranges, in a first position, a first solid body (9?) comprising a predetermined first amount of bound Hg. The device (1) arranges, in a second position, a second solid body (9?) comprising a predetermined second amount of bound Hg. A first release (E1) of the first amount of Hg is achieved in the fluorescent tube body (3) by gasification with heat and under pressure for purification of contaminant particles in the fluorescent tube body. A second release (E2) of the second amount of Hg is achieved in the fluorescent tube body (3) by gasification attained for the occluded mercury vapour of the fluorescent tube body (3).

Abstract: The invention relates to a cable having a conductor surrounded by at a least one polymer layer having a polymer composition of the invention which has a polymer component and optionally a carbon black (CB) component, to a production process of the cable and to a polymer composition of the invention which has a polymer component and optionally a carbon black (CB) component and which is for use in a cable layer.

Abstract: The present invention relates to a method of and a vertical pumping device (1) for internally distributing Hg in a fluorescent tube body (3). The bottom (7) of the fluorescent tube body (3) is closed. The device (1) arranges, in a first position, a first solid body (9?) comprising a predetermined first amount of bound Hg. The device (1) arranges, in a second position, a second solid body (9?) comprising a predetermined second amount of bound Hg. A first release (E1) of the first amount of Hg is achieved in the fluorescent tube body (3) by gasification with heat and under pressure for purification of contaminant particles in the fluorescent tube body. A second release (E2) of the second amount of Hg is achieved in the fluorescent tube body (3) by gasification attained for the occluded mercury vapour of the fluorescent tube body (3).

Abstract: A strut for application between an outer ring and an inner ring in a gas turbine structure and a gas turbine structure including such a strut are provided. The strut includes an end portion which has a diverging shape so that an internal space is formed in the end portion for receiving at least part of an engine mount. Engine mounting lugs can be positioned at such struts.

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 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: 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: The invention relates to a cable comprising a conductor surrounded by at a least one polymer layer comprising a polymer composition of the invention which comprises a polymer component and optionally a carbon black (CB) component, to a production process of the cable and to a polymer composition of the invention which comprises a polymer component and optionally a carbon black (CB) component and which is for use in a cable layer.

Abstract: The present invention relates to a compact fluorescent tube (1) designed for cold spaces, which compact fluorescent tube (1) comprises at least one fluorescent tube body (13) formed into a U-shape and comprising two fluorescent tube body legs (17), which latter have an interspace (19) between them and each comprise a base part (9), enclosing a cathode chamber (11), and a top part (15) facing away from the said base parts (9), which base parts are fixed to a socket part (3), comprising current feeder members (5) for electrical contact with the cathode chambers (11). An insulating member (21, 47, 55) is arranged on the top part (15) of the compact fluorescent tube and is configured with at least one insulating cavity (23, 49), which, during operation of the compact fluorescent tube (1), is heated by the self-produced heat of the compact fluorescent tube (1).

Abstract: An arrangement for cooling a gas turbine engine component includes a gas turbine engine component provided with at least one cooling channel through which a cooling medium is intended to flow during operation of the arrangement, a feeding system configured to supply cooling medium to the cooling channel, a cooling channel inlet, and a cooling channel outlet. The feeding system is arranged in flow communication with both the inlet and the outlet of the cooling channel such as to form a closed flow system. A gas turbine engine provided with such a component and a method for cooling such a component are also provided.

Abstract: A strut for application between an outer ring and an inner ring in a gas turbine structure and a gas turbine structure including such a strut are provided. The strut includes an end portion which has a diverging shape so that an internal space is formed in the end portion for receiving at least part of an engine mount. Engine mounting lugs can be positioned at such struts.

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 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: 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.