Abstract: The invention relates to a gas turbine intermediate structure (14) for being arranged between a first and a second gas turbine structure (8 and 9) in an axial direction (18) of a gas turbine (1). The intermediate structure (14) comprises an gas duct (5c) arranged for guiding a gas flow from a gas duct (5a) in the first structure (8) to a gas duct (5b) in the second structure (9). An inlet (19) of the intermediate structure gas duct (5c) is substantially displaced in a radial direction in relation to an outlet (20) of the intermediate structure gas duct (5c). At least one guide vane (28,29) is arranged in the intermediate structure gas duct (5c) for guiding the gas flow.

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: Method and arrangement for providing and controlling a gas turbine (1) at least one turbine (11, 20, 20?), at least one compressor (2, 5) driven by the turbine and a combustion chamber (16) arranged between the compressor and the turbine in the airflow path. The gas turbine includes devices (8) for direct measurement of the air mass flow at a position upstream of the combustion chamber in the airflow path, with the aim of regulating the quantity of fuel that is delivered to the combustion chamber (16) on the basis of the measured air mass flow.

Abstract: The invention relates to a gas turbine compression system (1) comprising a gas channel (5), a low pressure compressor section (8) and a high pressure compressor section (9) for compression of the gas in the channel and a compressor structure (14) arranged between the low pressure compressor section (8) and the high pressure compressor section (9). The compressor structure (14) being designed to conduct a gas flow in the gas channel and comprises a plurality of radial struts (15,16,21,24,25) for transmission of load, wherein at least one of said struts (15,16,21,24,25) is hollow for housing service components. The compressor structure (14) is arranged directly downstream a last rotor (10) in the low pressure compressor section (8) and designed for substantially turning a swirling gas flow from said rotor (10) by a plurality of said struts (15,16,21,24,25) having a cambered shape.

Abstract: A turbine including a rotor (1) that is driven by gas and that has a housing (2) enclosing the rotor. The turbine includes a component (6) suspended from the housing (2) that is arranged inside the housing (2) and at least partially beside the rotor (1) with respect to the direction (5) of the gas flow in order to impede any fragments which may come loose from the rotor from penetrating the housing in radial direction.

Abstract: Stator (1) for a gas turbine including a stator structure (2) having a continuous through-duct (3) for a gas through-flow, a circumferential member (6), which is arranged at a radial distance from the stator structure and is operatively coupled to the stator structure, and at least one member for maintaining the distance between the stator structure and the circumferential member. The spacing member has resilient characteristics in the radial direction of the stator.

Abstract: A turbine including a rotor (1) that is driven by gas and that has a housing (2) enclosing the rotor. The turbine includes a component (6) suspended from the housing (2) that is arranged inside the housing (2) and at least partially beside the rotor (1) with respect to the direction (5) of the gas flow in order to impede any fragments which may come loose from the rotor from penetrating the housing in radial direction.

Abstract: A fuel injector (1) having a chamber (7) with a fuel inlet (8) and a plurality of fuel outlets (10), and including a fuel distributor (18) that is arranged in the chamber (7) for the purpose of distributing fuel introduced into the chamber (7) via the fuel inlet (8) to the outlets (10). The fuel distributor (18) includes a generally rotary symmetric distributor body (19).

Abstract: A device for a combustion chamber of a gas turbine for controlling the intake of gas into the combustion zone of the combustion chamber. The device includes a control element that is arranged outside the combustion chamber. This control element has a first covering for at least a first inlet to the combustion zone and is displaceable in relation to the combustion chamber. There is also a support for the control element that is connected to the cover. The cover is displaceable relative to the combustion chamber and a support (16) for the control element (12, 12?) is connected to the cover. The support (16) is accommodated in a structure (4) at a rear of the combustion chamber.

Abstract: A wall structure (2) configured to be exposed to a thermal load. The wall structure having at least two layers including a first layer (5) and a second layer (6). The second layer (6) is located closer to a source of the thermal load than the first layer (5), and the layers (5, 6) are arranged so that heat is allowed to be conducted from the second layer (6) to the first layer (5). Each of the first and second layers (5, 6) are adapted to carry a significant portion of a structural load, and the second layer (6) exhibits a higher thermal conductivity and/or a lower thermal expansion than the first layer (5). The invention reduces the thermal strain in the wall structure (2).

Abstract: Method and apparatus for providing an afterburner fuel-feed arrangement including an elongate fuel spraybar for distributing fuel to the afterburner section of a turbo-combustion engine. The spraybar has a longitudinal axis and includes a fuel-receiving spray head in fluid communication with a plurality of elongate fuel pipes surrounded by an elongate, aerodynamic-shaped shroud. The spray head is configured to be mounted in a casing of a turbo-combustion engine which projects the surrounded fuel pipes into an interior through-core of the engine in cross-wise orientation to a core gas flow thereof. The shroud has an interior lateral sidewall that includes a pipe-receiving portion configured to abuttingly engage a corresponding shroud-engaging portion of an exterior surface of one of the fuel pipes. The pipe-receiving portion is configured to substantially radially fix a fuel pipe, received therein, relative to the shroud.

Abstract: The invention relates to a method for manufacturing a stator component that is intended in operation to guide a gas flow and to transfer loads. The component is constructed of at least two sectors in the direction of its circumference. The sectors are cast in separate pieces, positioned adjacent to each other and joined together by welding.

Abstract: Method for manufacturing a stator or rotor component which is intended during operation to conduct a gas flow. A first wall part (14, 15) is placed with its one edge bearing against the flat side of a second wall part (9, 10), extending in the radial direction of the component, in such a way that the first wall part extends in the circumferential direction of the component. The edge of the first wall part is then laser-welded to the second wall part from an, in the circumferential direction, opposite side of the second wall part in relation to the first wall part in such a way that the joined-together portions of the wall parts form a T-shaped joint.

Abstract: Method for manufacturing a stator component that is intended during operation to conduct a gas flow. The component is made up of at least two sections (113) in its circumferential direction, which sections each have at least one wall part (101,102) The sections are placed adjacent to each other and two wall parts, one from each of two adjacent sections, are connected in order together to form a means, extending in the radial direction of the component, for guidance of said gas flow and/or transmission of load during operation of the component.

Abstract: The invention relates to a method for preparation of test bodies for analysis of porous, preferably thermally sprayed, surface layers, which are incorporated by casting in plastic. The method according to the invention is carried out by placing one or more test pieces of the surface layer in a mold introduced into a vacuum chamber, the pressure of which is lowered, pouring a ready-mixed, liquid casting resin into the mold containing the test pieces, again letting the air into the chamber, lifting the test pieces out of the casting resin and allowing the excess resin to drip from the test pieces. After that, they are placed in a mold cavity together with the test pieces with a pulverized resin, and applying pressure and heat to the mold cavity for a predetermined period of time, whereupon the test body is ready to be taken out and lapped.

Abstract: A wall structure capable of withstanding high thermal load, including a wall structure with an inner wall, an outer wall positioned about the inner wall, and distancing elements located between the inner and outer walls. The distancing elements are joined to at least one of the inner and outer walls by means of laser welding and thereby establishing a plurality of cooling ducts between the inner and outer walls and a weld joint formed by the laser welding and having a cross-section taken through the wall structure that is substantially T-shaped and which displays a rounded shape towards an inside one of the plurality of cooling ducts.

Abstract: Method and arrangement for providing a component (1) for being subjected to high thermal load during operation. The component includes a wall structure, which defines an inner space for gas flow. The component is formed by at least a first part (5) that includes an inner wall (8), an outer wall (9) and at least one cooling channel (11) between the walls. An end portion of said inner wall of the first part of the component is joined to a second part (6). The joint (18) is located at a distance from the interior of the component.

Abstract: Method and arrangement for providing liquid fuel rocket engine member (10). The member forms a body of revolution having an axis of revolution and a cross section that varies in diameter along said axis. The wall structure includes a plurality of cooling channels (11). The outside of the wall structure includes a continuous sheet metal wall (14). The cooling channels (11) are longitudinally attached to the inside of the sheet metal wall. The method for manufacturing the rocket engine member (10) includes the steps of forming a sheet metal wall (14) having a wall section corresponding to the desired nozzle section, providing a plurality of channel members (15), and attaching the channel members (15) to the inside of the sheet metal wall (14).

Abstract: Method and device (1) for supplying fuel to a combustion chamber that includes at least one main injector (3) and at least one pilot injector (2). The device includes a fuel tank (4), a line system (5) coupled from the fuel tank to the injectors (2, 3), a pump (6) for pumping fuel from the tank to the injectors, and a first regulator valve (7) for regulating the flow of fuel in a first line (8) in the system which is connected to the pilot injector (2). The device further includes a second regulator valve (9) for regulating the flow of fuel through a second line (10) in the system, which is connected to the pilot injector (2). The second regulator valve (9) is designed to regulate a substantially smaller flow than the first regulator valve (7).

Abstract: A device for a combustion chamber of a gas turbine for controlling the intake of gas into the combustion zone of the combustion chamber. The device includes a control element that is arranged outside the combustion chamber. This control element has a first covering for at least a first inlet to the combustion zone and is displaceable in relation to the combustion chamber. There is also a support for the control element that is connected to the cover. The cover is displaceable relative to the combustion chamber and a support (16) for the control element (12, 12?) is connected to the cover. The support (16) is accommodated in a structure (4) at a rear of the combustion chamber.