Abstract: Method and arrangement for providing a turbine or compressor device having a rotor (1), that includes a first rotor section (2) having at least one disc-shaped or annular element (3) which has a multiplicity of blades (4) arranged in series on a circumferential path for guiding a gas flow, and a second, elongate rotor section (5) which projects at right-angles from the rotor disc (3) and which has a rotor shaft (6) connected to the rotor disc. A first and second bearing (8, 9) are fitted at a distance from one another along the rotor shaft (6), and the first bearing (8) is arranged closer to the rotor disc (3) than the second bearing (9). The bearing holder (25) of the first bearing (8) has a greater outside width than other than other components (9, 14, 15, 31) arranged on the rotor shaft (6) between the first bearing (8) and the free end of the rotor shaft (7).

Abstract: Method and arrangement for providing a turbine or compressor device having a rotor (1), that includes a first rotor section (2) having at least one disc-shaped or annular element (3) which has a multiplicity of blades (4) arranged in series on a circumferential path for guiding a gas flow, and a second, elongate rotor section (5) which projects at right-angles from the rotor disc (3) and which has a rotor shaft (6) connected to the rotor disc. A first and second bearing (8, 9) are fitted at a distance from one another along the rotor shaft (6), and the first bearing (8) is arranged closer to the rotor disc (3) than the second bearing (9). The bearing holder (25) of the first bearing (8) has a greater outside width than other than other components (9, 14, 15, 31) arranged on the rotor shaft (6) between the first bearing (8) and the free end of the rotor shaft (7).

Abstract: An engine includes a first element, a second element, an exhaust duct which extends from the first element into the second element, a connecting element which connects the first element to the second element and delimitates the exhaust duct at the transition between the first and second elements, the connecting element being flexible to allow relative movements between the first and the second elements. The connecting element includes a ring whose fastening to the first element is offset radially relative to its fastening to the second element.

Abstract: Method and arrangement for providing a gas turbine (1) having a duct (11) for carrying gas from a gas turbine inlet (9) to a gas turbine outlet (10) and an outer housing (19, 20, 21) arranged radially outside a wall structure (12, 13, 14), which defines the radially outer limits of the gas duct (11). The gas turbine (1), between the inlet (9) and outlet (10), is constructed from a plurality of modules (6, 7, 8), each of which constitutes a part of the outer housing (19, 20, 21) and a part of the wall structure (12, 13, 14) of the gas duct. At least two adjacent parts of the wall structure (12, 13, 14) of the gas duct are arranged at a distance from one another.

Abstract: Method and arrangement for providing a gas turbine (1) having a duct (11) for carrying gas from a gas turbine inlet (9) to a gas turbine outlet (10) and an outer housing (19, 20, 21) arranged radially outside a wall structure (12, 13, 14), which defines the radially outer limits of the gas duct (11). The gas turbine (1), between the inlet (9) and outlet (10), is constructed from a plurality of modules (6, 7, 8), each of which constitutes a part of the outer housing (19, 20, 21) and a part of the wall structure (12, 13, 14) of the gas duct. At least two adjacent parts of the wall structure (12, 13, 14) of the gas duct are arranged at a distance from one another.

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 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: 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.

Abstract: Method for manufacturing a vane (1) to a gas turbine component intended for guiding a gas flow. The vane (1) is produced by casting, and an internal hole (3) for coolant is then cut out of the cast vane (1). The vane (1) is provided with a starter hole (5), either during casting or once casting is completed, following which the internal hole (3) for coolant is cut out of the vane, proceeding from the starter hole. A method is also disclosed for manufacturing a gas turbine component including a plurality of vanes (1) for guiding a gas flow. The gas turbine component is cast in such a way that it includes the vanes and an internal hole (3) for coolant is then cut out of each of the vanes.

Abstract: Method and arrangement for providing a gas turbine (1) having a first compressor (2), a combustion chamber (16) and a first turbine (11), the turbine being adapted to drive the compressor via a first shaft (10a, 10b). The gas turbine also has a bleed valve (12) arranged upstream of the first turbine for conducting part of a gas compressed by the compressor past it during engine braking. The invention also relates to a method for engine-braking a gas turbine.

Abstract: A gas turbine arrangement (1) including a gas turbine (2), a generator (3) and a gearbox (4). The gearbox (4) is connected to an output shaft (5) from the gas turbine and an input shaft (6) to the generator. The gas turbine arrangement (1) also has a starter motor (7) that is connected to an output shaft (8) from the generator (3).

Abstract: Device for a heat exchanger (1), preferably for co-operation with a gas turbine, where the heat exchanger includes flow channels and a heat emitting medium (6) flows through every alternate channel and a heat absorbing medium (7) flows through every other alternate channel. A collecting channel (4) is connected to an outlet section of a combined inlet and outlet pipe joint (2, 3) for the heat emitting and absorbing media (6, 7) via a pipe section. The pipe section has a substantially straight section (10, 13) including at least one straight sub-section where a first sub-section (10) is deformable both in its axial direction and in all directions transverse to the axial direction. A partially curved second sub-section (11, 21) is included and the pipe section has a central load-absorbing-through element (14) attached at ends (14a, 14b) to the outer side of the pipe section.

Abstract: A gas turbine arrangement having a transmission (1) of planetary gear type with fixed planet carrier, and an arrangement for driving one or more auxiliary units (12), and is characterized in that at least one of the auxiliary units (12) is operatively connected to a planet wheel shaft (10) forming part of the transmission (1). The invention helps to simplify the design construction of the transmission.

Abstract: Method and arrangement for providing a gas turbine (1) having a first compressor (2), a combustion chamber (16) and a first turbine (11), the turbine being adapted to drive the compressor via a first shaft (10a, 10b). The gas turbine also has a bleed valve (12) arranged upstream of the first turbine for conducting part of a gas compressed by the compressor past it during engine braking. The invention also relates to a method for engine-braking a gas turbine.

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: Method for manufacturing a vane (1) to a gas turbine component intended for guiding a gas flow. The vane (1) is produced by casting, and an internal hole (3) for coolant is then cut out of the cast vane (1). The vane (1) is provided with a starter hole (5), either during casting or once casting is completed, following which the internal hole (3) for coolant is cut out of the vane, proceeding from the starter hole. A method is also disclosed for manufacturing a gas turbine component including a plurality of vanes (1) for guiding a gas flow. The gas turbine component is cast in such a way that it includes the vanes and an internal hole (3) for coolant is then cut out of each of the vanes.

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 chair that includes a frame and a seat disposed there above, and an upwardly protruding back support that is located in an area behind the seat. A front part of the back support has a lumbar support device that is disposed a certain level above the seat to support the lumbar spine and/or pelvis rim of the user. The seat is movable relative to the frame between the forward starting position, on the one hand, in which the seat is remote from the back support and is the normal position when the seat is not used by a sitting person and a rear end position, on the other hand, has a lumbar support in which the seat has moved closer to the back support. More particularly, it is closer for the purpose of bringing the pelvis of the person sitting on the seat to partially shift in against or below the lumbar support device.

Abstract: A chair that includes a frame, a seat, and a back support that has a lumbar support device to support the back bone of the user. The seat includes a soft cushion and a support panel that includes a front and rear disc part of which the latter protrudes as a free end from the first and is not in contact with the back support. The cushion has a rear seating area that is recessed relative to a forward seating area so that a transition area is formed that provides a knob against which the user's sitting bones may bear against with a view to prevent forward gliding of the user's thigh bones along the seat. The rear disc part is also lowerable from an upper starting position to enable a variation of the height level.