Abstract: A coupling for pipe-in-pipe pipeline tubing formed of an assembly of sections each incorporating an inner pipe and an outer pipe butt-welded to the inner pipe, two successive sections being joined together by the welding of respective inner pipes delimiting a segment of inner pipe. The coupling is formed by a sleeve arranged perpendicularly to the segment and a filler material constituted by a quick-set mortar based on aluminous cement and sand, the filler material being arranged in the free space delimited by the sleeve, the segment and the outer pipes of two successive sections.

Abstract: The invention regards an acoustic liner which comprises: a facing sheet that comprises holes, the facing sheet having a porosity and a facing sheet thickness, a backing sheet, and a plurality of cells arranged between the facing sheet and the backing sheet, the cells having a cell depth and each cell defining a cavity. A plurality of internal necks are provided that extend from the inner side of the facing sheet towards the backing sheet, each internal neck being located around a hole of the facing sheet, thereby extending the longitudinal length of the hole. The invention further regards a gas turbine engine with such acoustic liner.

Abstract: A turbine arrangement includes a turbine rotor arrangement, a turbine seal arrangement and a turbine outlet stator vane arrangement. Turbine rotor arrangement includes a rotor and a plurality of turbine blades that extend radially. Each turbine blade has a turbine shroud. Turbine seal arrangement is spaced radially around the turbine shrouds. Turbine outlet stator vane arrangement includes radially inner and outer annular members arranged coaxially and a plurality of vanes extending radially between the radially inner and outer annular members. The vanes are arranged downstream of the turbine blades. Liner is spaced radially inwardly from a radially inner surface of the annular member to define a chamber. Turbine shrouds and the upstream end of the liner are arranged such that in operation any leakage flow of gas between the turbine shrouds and the turbine seal arrangement flows into the chamber to manage the temperature of the radially outer annular member.

Abstract: A device for sealing off a segment of pipe-in-pipe pipeline including an inner pipe and an outer pipe between which an insulating material is interposed, and including a water detector. The device includes: a first plug for closing off the inner pipe, a tubular extension welded to the end of the outer pipe, the free end of the extension extending beyond the first plug and being closed off by a second plug, and a means for fixing the position of the inner pipe and outer pipe, integral with the extension.

Abstract: The disclosure provides a powerplant for an aircraft comprising: at least two gas turbine engines, and at least one closed-cycle arrangement for recuperating heat from the at least two gas turbine engines and supplying power to at least one power-demanding system, wherein the closed-cycle arrangement comprises: a closed circuit channeling a working fluid subjected to a thermodynamic cycle; at least one pre-cooler configured to transfer heat from the working fluid to a heat sink; the heat sink in thermal communication with the pre-cooler, the heat sink being a fuel tank and/or an airframe surface; at least one pumping element configured to move the working fluid through the closed circuit; at least two primary heat exchangers, each one configured to transfer heat from a respective gas turbine engine to the working fluid; at least one expanding element configured to drive a gearbox and an output shaft by the expansion of the working fluid; wherein the output shaft driven by the expanding element is connected to

Abstract: A bladed rotor wheel of an aero turbine stage includes a portion of a rotor blade with a shank portion and a bottom surface; a portion of a forged rotor disk with a rim portion and an outer surface; and a joining structure provided by an additive manufacturing process configured for integrally merging the portion of a rotor blade with the portion of a forged rotor disk. An aero turbine can include such bladed rotor wheel, and an aircraft can include such aero turbine.

Abstract: A turbine arrangement includes a turbine rotor arrangement, a turbine seal arrangement and a turbine outlet stator vane arrangement. Turbine rotor arrangement includes a rotor and a plurality of turbine blades that extend radially. Each turbine blade has a turbine shroud. Turbine seal arrangement is spaced radially around the turbine shrouds. Turbine outlet stator vane arrangement includes radially inner and outer annular members arranged coaxially and a plurality of vanes extending radially between the radially inner and outer annular members. The vanes are arranged downstream of the turbine blades. Liner is spaced radially inwardly from a radially inner surface of the annular member to define a chamber. Turbine shrouds and the upstream end of the liner are arranged such that in operation any leakage flow of gas between the turbine shrouds and the turbine seal arrangement flows into the chamber to manage the temperature of the radially outer annular member.

Abstract: A guide vane for a vane assembly of a turbo machine, the guide vane can include: an aerofoil body including: a forward portion, a rear portion, and opposite outer surfaces, extending between the forward portion and the rear portion, a liner shaped with a sheet like geometry, the liner being configured for being fixed to the aerofoil body, the liner including: a first portion configured for being connected to the forward portion of the aerofoil body, a trailing edge portion shaped with a convex geometry, a first coupling portion extending between the first portion and the trailing edge portion, and configured for being fixed to an outer surface of the aerofoil body, a second portion extending from the trailing edge portion and configured for being connected to the rear portion of the aerofoil body, wherein when the first coupling portion of the liner is fixed to an outer surface of the aerofoil body: the trailing edge portion of the liner extends from the rear portion of the aerofoil body, and the second porti

Abstract: A sealing structure for a gas turbine engine including a plurality of cells connected to each other is provided. Each cell includes a plurality of walls and the plurality of walls defines a polygonal shape therebetween in a cell plane. The polygonal shape includes a plurality of edges and a plurality of vertices defining a cell area in the cell plane. Each wall is shared by two adjacent cells such that each wall defines corresponding edges of the two adjacent cells. Each cell is connected to a set of adjacent cells at corresponding vertices, such that each cell and the set of adjacent cells form a plurality of connections at the corresponding vertices. The plurality of connections forms a total overlap area between each cell and the set of adjacent cells. The total overlap area is less than or equal to 10% of the cell area.

Abstract: The present invention provides a bladed rotor wheel for a gas turbine engine comprising at least a rotatable forged disc, the rotatable forged disc comprising a front surface and a back surface, at least one rim surface, and a plurality of projections located on at least a portion of at least one of the front or back surface and/or on the rim surface; wherein the projections are 3D printed features protruding outwards from the front, back and/or rim surface; the projections are arranged forming a pattern so that a heat transfer capability is created at the front, back and/or rim surface; and the ratio of the distance between projections to the forged disc external radius is lower than 0.15. Furthermore, the present invention also provides a method for manufacturing a rotatable forged disc for a bladed rotor wheel.

Abstract: A blade assembly for a gas turbine engine includes a rotor, a stator, a seal plate, and a sealing member. The rotor includes a rotor blade and a rotor disc. The rotor disc defines a bucket groove which receives a cooling fluid from a first cavity upstream of the rotor. The sealing member includes a control arm. The sealing member and the rotor define a flow cavity therebetween in fluid communication with an aperture of the seal plate. The flow cavity receives the cooling fluid flowing through the bucket groove and the aperture. The control arm and the seal plate define a gap therebetween fluidly communicating the flow cavity with a second cavity between the stator and the rotor. The control arm deflects at least a portion of the cooling fluid entering the flow cavity.

Abstract: The present invention relates to a panel for tip clearance control formed by: a first perforated sheet adapted for being seated on the turbine casing; a second sheet arranged on said first sheet and configured for being attached to the first sheet leaving a gap between both sheets; and a third sheet arranged between both first sheet and second sheet such that respective spaces in fluid connection by at least one hole are configured: a distribution chamber and an impingement chamber, both chambers extending from one end of the panel to the other. The panel further comprises a closure element together with a sealing element at one of its lateral ends for allowing the passage of fluid with another adjacent panel, whereas the sealing element is configured for allowing relative movement between both adjoining panels.

Abstract: A blade assembly for a gas turbine engine includes a rotor, a stator, a seal plate, and a sealing member. The rotor includes a rotor blade and a rotor disc. The rotor disc defines a bucket groove which receives a cooling fluid from a first cavity upstream of the rotor. The sealing member includes a control arm. The sealing member and the rotor define a flow cavity therebetween in fluid communication with an aperture of the seal plate. The flow cavity receives the cooling fluid flowing through the bucket groove and the aperture. The control arm and the seal plate define a gap therebetween fluidly communicating the flow cavity with a second cavity between the stator and the rotor. The control arm deflects at least a portion of the cooling fluid entering the flow cavity.

Abstract: A coupling for pipe-in-pipe pipeline tubing formed of an assembly of sections each incorporating an inner pipe and an outer pipe butt welded to the inner pipe, two successive sections being joined together by the welding of respective inner pipes delimiting a segment of inner pipe, wherein it is formed by a sleeve arranged perpendicularly to the segment and a filler material constituted by a quick-set mortar based on aluminous cement and sand, said filler material being arranged in the free space delimited by the sleeve, said segment and the outer pipes of two successive sections.

Abstract: The invention relates to a heated pipe for the transportation of a fluid comprising: a fluid transportation casing, one or several electric heating cables each arranged along the transportation casing, each cable comprising an electrically conductive core arranged in an electrically insulating and thermally conductive sheath, a thermally insulating material applied onto said heating cable or cables and onto the transportation casing, an external casing arranged around the thermally insulating material and made integral with the transportation casing in a sealed manner so as to define at least one annular space enabling its pressure to be reduced, the pipe additionally comprises means to reduce partial electrical discharges between said heating cable or cables and the transportation casing.

Abstract: A heating installation for hydrocarbon extraction pipes via a well linking the surface to an extraction zone, including a substantially cylindrical casing consolidating the drill hole, a hydrocarbon extraction method and method to enable a hot fluid to be made to circulate from the surface to the well zone to be heated. The injection method includes in the casing first thermally insulated heating tubing to inject the hot fluid from the surface to the required depth and second heating tubing surrounding the first tubing to bring the hot fluid towards the surface and the extraction method includes a pumping tubing surrounding the first and second heating tubing for the extraction of hydrocarbons.

Abstract: A gas turbine engine for an aircraft includes an engine core with a turbine, a compressor, and a core shaft connecting them. The engine includes a fan, with a plurality of fan blades, located upstream of the core and a gearbox receiving an input from the core shaft and outputting drive so the fan is at a lower rotational speed than the core shaft. The turbine includes a plurality of stages of axially spaced rotor blades mounted on a rotor, which are surrounded by a turbine casing. The turbine has an inlet defined at an upstream end of a first stage of blades and an outlet defined at a downstream end of a last stage of blades and a ratio of the area of the outlet to the inlet is at between 2.5 and 3.5. This increases the pressure ratio of and power extracted from the turbine and the engine.

Abstract: A gas turbine engine for an aircraft includes an engine core with a turbine, a compressor, and a core shaft connecting them. The engine includes a fan, with a plurality of fan blades, located upstream of the core and a gearbox receiving an input from the core shaft and outputting drive so the fan is at a lower rotational speed than the core shaft. The turbine includes a plurality of stages of axially spaced rotor blades mounted on a rotor, which are surrounded by a turbine casing. The turbine has an inlet defined at an upstream end of a first stage of blades and an outlet defined at a downstream end of a last stage of blades and a ratio of the area of the outlet to the inlet is at between 2.5 and 3.5. This increases the pressure ratio of and power extracted from the turbine and the engine.

Abstract: A cooling module for a photovoltaic unit, whereby a core is provided which is in the form of a panel-type 3D fabric, is designed as a knitted fabric spacer and can be penetrated by a fluid.

Abstract: The invention relates to a segment of pipe-in-pipe pipeline comprising an annulus under reduced pressure sealed and delimited by a metallic internal pipe inserted into a metallic external pipe and provided with a measurement system to determine in a non-intrusive manner the state of the annulus, the measurement system being composed of a first internal emitter/receiver assembly placed inside the annulus and cooperating with means to measure a first physical quantity such as pressure, hygrometry or temperature inside the reduced pressure annulus and a second external emitter/receiver assembly arranged to the exterior of the segment and facing said first assembly.