Volvo Aero Corporation

Bertil Jönsson

Lars Sundin

Patrik Johansson

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

Turbine or compressor device and method for assembling the device

Method and arrangement for providing a gas turbine () having a duct () for carrying gas from a gas turbine inlet () to a gas turbine outlet () and an outer housing () arranged radially outside a wall structure (), which defines the radially outer limits of the gas duct (). The gas turbine (), between the inlet () and outlet (), is constructed from a plurality of modules (), each of which constitutes a part of the outer housing () and a part of the wall structure () of the gas duct. At least two adjacent parts of the wall structure () of the gas duct are arranged at a distance from one another. At least one pressure dividing element () is provided and configured to divide off a pressure area (P, P, P, P, P) in the gas duct () at the junction between the two adjacent parts of the wall structure () from another pressure area () situated between the wall structure () of the gas duct and the outer housing (). The pressure dividing element () consists of a pressure wall extending from the wall structure () of the gas duct to the outer housing ().

Modular gas turbine

Stator () for a gas turbine including a stator structure () having a continuous through-duct () for a gas through-flow, a circumferential member (), 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.

Gas turbine stator

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 () for the control element () is connected to the cover. The support () is accommodated in a structure () at a rear of the combustion chamber.

Device for a combustion chamber in a gas turbine for controlling the intake of gas to a combustion zone

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

Method and a device for supplying fuel to a combustion chamber

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

Method for manufacturing a vane to a gas turbine component and a method for manufacturing a gas turbine component

Method and arrangement for providing a gas turbine () having a first compressor (), a combustion chamber () and a first turbine (), the turbine being adapted to drive the compressor via a first shaft (). The gas turbine also has a bleed valve () 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.

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Bjärred, Sweden

Bertil Jönsson