A gas turbine engine component having a cooling passage includes a first wall defining an inlet of the cooling passage, a second wall generally opposite the first wall and defining an outlet of the cooling passage, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The metering section includes an upstream side and a downstream side generally opposite the upstream side. At least one of the upstream and downstream sides includes a first passage wall and a second passage wall where the first and second passage walls intersect to form a V-shape.

A gas turbine engine is disclosed having a turbine, one or more hydrocarbon gas combustors, and a compressor. The compressor has a rotor assembly with one or more rotor blade rows extending radially outward from an inner wheel disk. The compressor also has a stator assembly with one or more stator vane rows extending radially inward from an inner casing and positioned between adjacent rotor blade rows. The inner casing extends circumferentially around the rotor assembly and is constructed from at least one low-alpha metal alloy.

A gas turbine including a turbine driven by a combustion gas, a gas turbine casing that includes an exhaust casing having an inner tube and an outer tube, a bearing that rotatably supports a shaft of the turbine, a bearing casing that holds the bearing, a support leg that supports the gas turbine casing, struts that connect the inner tube and the outer tube, and a first support and a second support that support the bearing casing on the inner tube. The first support is located on a side same as the support leg relative to the struts in a flow direction of the combustion gas. The struts are located between the first support and the second support. The first support is fixed to the inner tube and the bearing casing. The second support is fixed to the inner tube and is in slidable contact with the bearing casing.

A casing component is configured to form part of a flow path in a turbine. The casing component includes a base made of nodular cast iron, and a repaired region in the base. The repaired region includes a butter layer applied on the base and a fill layer applied on the butter layer.

A casing component is configured to form part of a flow path in a turbine. The casing component includes a base made of nodular cast iron, and a repaired region in the base. The repaired region includes a butter layer applied on the base and a fill layer applied on the butter layer.

The invention relates to a modular nozzle ring for a turbine stage of a continuous flow machine. The modular nozzle ring has a carrier system having an an adjustment ring, and a blade module having a blade leaf. The blade module is detachably connected to the carrier system. Furthermore, an adjustment angle of the blade leaf by the carrier system, in particular by the adjustment ring spaced apart from a flow channel, is specified, which adjustment angle is unchangeable during operation. The blade module is designed to be detachably pressed to a turbine housing part on the flow side, in particular by the adjustment ring. The invention furthermore relates to a blade module for a modular nozzle ring of a turbine stage and the use of a carrier system for a modular nozzle ring.

A mobile machine tool for segmentally machining, in situ, a component, in particular a component of a turbine, which is rotatable about an axis of rotation. The machine tool has a main body, a support element which is held on the main body so as to be movable about a C-axis along a circular-arc-shaped guide path, and a tool module which is held on the support element and is designed to receive a tool. The tool module is located on the support element so as to be linearly movable. A method segmentally machines, in-situ, a component which is mounted in a stationary body so as to be rotatable about an axis of rotation.

A centering device (10) for centering a turbine housing (40) with respect to a central axis (33) of a radial turbine of a turbo system is described. The centering device (10) includes a ring-shaped body (11) having an outer diameter D1 and an inner diameter D2, wherein a ratio of D1/D2 is ≤2. Additionally, the centering device (10) includes two or more centering elements (16) provided on a side surface (12) of the ring-shaped body (11) for engaging with respective complementary centering elements (21) provided on a bearing housing (20). The two or more centering elements (16) are configured for allowing a radial thermal expansion of the ring-shaped body (11) during engagement of the two or more centering elements (16) with the respective complementary centering elements (21). Further, a turbo system, including such a centering device as well as a method of centering a turbine housing are described.

A centering device (10) for centering a turbine housing (40) with respect to a central axis (33) of a radial turbine of a turbo system is described. The centering device (10) includes a ring-shaped body (11) having an outer diameter D1 and an inner diameter D2, wherein a ratio of D1/D2 is ≤2. Additionally, the centering device (10) includes two or more centering elements (16) provided on a side surface (12) of the ring-shaped body (11) for engaging with respective complementary centering elements (21) provided on a bearing housing (20). The two or more centering elements (16) are configured for allowing a radial thermal expansion of the ring-shaped body (11) during engagement of the two or more centering elements (16) with the respective complementary centering elements (21). Further, a turbo system, including such a centering device as well as a method of centering a turbine housing are described.

A fan casing for an engine having a fan with fan blades that each have a centre of gravity (CoG) that lies on a fan blade CoG plane, the fan casing having a central axis and comprising a main impact region comprising carbon-fibre reinforced polymer (CFRP) blocks and glass-fibre reinforced polymer (GFRP) blocks having a constant thickness throughout the axial extent of the main impact region, wherein the total depth of the main impact region is equal to the sum of the thicknesses of the CFRP blocks and GFRP blocks, each of the GFRP blocks is positioned between two CFRP blocks, and the thickness of at least one of the GFRP blocks is different to the thickness of another of the GFRP blocks.