Abstract: A gas turbine is provided including a rotor which includes a rotor portion of a fluid bearing for rotatably supporting the rotor, a radially outer stator portion, a radially inner stator portion including a stator portion of the fluid bearing, a compressor air passage extending between the radially outer stator portion and the radially inner stator portion, and an annular gap between the rotor and the radially inner stator portion partially forming an annular air passage in communication with the compressor air passage, wherein along a flow direction of air flowing within the annular air passage a radius of the air passage decreases in a first portion and then increases in a second portion. Further a method for operating a gas turbine is described.

Abstract: A device, system, or method to position variable guide vanes disproportionately is provided. An adjusting device for guide vanes of an axial-flow machine, includes a plurality of rotatably mounted rings of variable guide vanes, a plurality of levers which are arranged on the outer sides of a guide vane carrier for rotating the variable guide vanes, a plurality of adjusting rings, each of the adjustment rings is arranged coaxially to the guide vane carrier and to which a first end of one of the levers is connected, and an adjusting drive with which the adjusting rings may be moved in the peripheral direction. At least one of the levers is set up to perform at least partly a disproportionate longitudinal movement of the first end of the at least one lever.

Abstract: An assembling aid for assembling or de-assembling a turbine assembly having at least two aerofoil assemblies connected to each other by at least two interlocking platforms, wherein the at least two aerofoil assemblies are brought from a free-state untwisted position to an assembled twisted position during assembling, including at least one slot embodied to receive at least one part of an aerofoil assembly, wherein the at least one slot has an entry aperture and an exit aperture. A width of the entry aperture of the at least one slot is wider than a width of the exit aperture of the at least one slot.

Abstract: Discrete bleed behind stator vane platform is provided. The discrete bleed behind stator vane platform relates to a system for bleeding off a working fluid from an inner volume (Vi) of a turbo-machine. The system includes a vane carrier with an annular rail and a vane device comprising at least one vane element, a vane platform and a vane root. The vane element is mounted to the vane platform and the vane root is mounted to the annular rail. A first annular cavity is formed between the vane platform and the annular rail, wherein an annular gap is formed between an edge of the vane platform and the vane carrier such that a part of the working fluid of the turbo-machine is bleedable through the annular gap into the first annular cavity. A second annular cavity is formed between the vane root, the annular rail and the vane carrier, wherein at least one inlet hole is formed into the annular rail for coupling the first annular cavity and the second annular cavity.

Abstract: A drive lever arrangement is provided. The drive lever arrangement includes a unison ring which has a groove; a drive lever having connection means for connecting the drive lever to the unison ring; a drive lever pin having a transversal throughbore hole; and a clip, wherein the drive lever pin connects the drive lever to the unison ring, and wherein the clip is inserted in the groove through the throughbore hole of the drive lever pin, and engages with the groove of the unison ring.

Abstract: A rotor assembly and a method of assembling the rotor assembly typically for a turbine engine. The rotor assembly has a rotational axis, at least one rotor, a shaft having an axially extending bore, a tension stud extending axially through the rotor and into the bore for applying an axial load across the rotor and/or shaft. The rotor assembly further has a sleeve located at least partly within the bore and connected to the shaft by a first attachment and to the tension stud by a second attachment, the first attachment is located between the rotor and the second attachment.

Abstract: A bore-scope sealing apparatus is provided for removably sealing a bore-scope opening in a turbomachine wall with a plug. The bore-scope sealing apparatus includes a bayonet coupling via which the plug is mountable to the bore-scope opening. The bayonet coupling has a projection at the plug and a corresponding recess at the bore-scope opening. A resilient retaining device is arranged at the recess being compressed by the projection in a sealing position to retain the plug in the bore-scope opening.

Abstract: A mounting apparatus includes a mounting pin having first and second ends, and a support having first and second sides. The support includes a passage between the first and second sides for receiving the mounting pin so that the first end of the pin protrudes from the first side and the second end of the pin protrudes from the second side. The second end of the pin engages an article to be mounted by the mounting apparatus. The first end rotates the pin about the axis of the pin to vary the position of a mounted article. A clamping plate clamps the first end of the mounting pin to the first side of the support for securing the rotational position of the pin with respect to the support.

Abstract: A diffuser for decelerating a compressed gas, is provided, which includes a ring divided at circumferential positions around the ring into several arcuate sections, the complete ring is assembled from these sections. The ring defines one or more passages, the cross-section of which increases in the direction of flow of a fluid through the diffuser. The interface between adjacent sections is configured so that relative movement between the sections is prevented. The interface is configured to have a series of interlocking serrations along the axial length of the diffuser. In an embodiment, there are two arcuate sections involving two interfaces, and the peaks and troughs of the serrations of each of the two sections are arranged at an angle to a longitudinal axis of the diffuser. A small relative movement between the sections is achieved when the two angles at the two interfaces have opposite signs.

Abstract: Discrete bleed behind stator vane platform is provided. The discrete bleed behind stator vane platform relates to a system for bleeding off a working fluid from an inner volume (Vi) of a turbo-machine. The system includes a vane carrier with an annular rail and a vane device comprising at least one vane element, a vane platform and a vane root. The vane element is mounted to the vane platform and the vane root is mounted to the annular rail. A first annular cavity is formed between the vane platform and the annular rail, wherein an annular gap is formed between an edge of the vane platform and the vane carrier such that a part of the working fluid of the turbo-machine is bleedable through the annular gap into the first annular cavity. A second annular cavity is formed between the vane root, the annular rail and the vane carrier, wherein at least one inlet hole is formed into the annular rail for coupling the first annular cavity and the second annular cavity.

Abstract: A drive lever arrangement is provided. The drive lever arrangement includes a unison ring which has a groove; a drive lever having connection means for connecting the drive lever to the unison ring; a drive lever pin having a transversal throughbore hole; and a clip, wherein the drive lever pin connects the drive lever to the unison ring, and wherein the clip is inserted in the groove through the throughbore hole of the drive lever pin, and engages with the groove of the unison ring.

Abstract: A gas turbine is provided including a rotor which includes a rotor portion of a fluid bearing for rotatably supporting the rotor, a radially outer stator portion, a radially inner stator portion including a stator portion of the fluid bearing, a compressor air passage extending between the radially outer stator portion and the radially inner stator portion, and an annular gap between the rotor and the radially inner stator portion partially forming an annular air passage in communication with the compressor air passage, wherein along a flow direction of air flowing within the annular air passage a radius of the air passage decreases in a first portion and then increases in a second portion. Further a method for operating a gas turbine is described.

Abstract: A bore-scope sealing apparatus is provided for removably sealing a bore-scope opening in a turbomachine wall with a plug. The bore-scope sealing apparatus includes a bayonet coupling via which the plug is mountable to the bore-scope opening. The bayonet coupling has a projection at the plug and a corresponding recess at the bore-scope opening. A resilient retaining device is arranged at the recess being compressed by the projection in a sealing position to retain the plug in the bore-scope opening.

Abstract: An annular vane assembly for a gas turbine engine is provided. The assembly includes a vane segment, the vane segment includes an arcuate rail and a vane that extends radially inwardly from the arcuate rail. The assembly also includes a hollow cylindrical casing, the inside curved surface of which an annular groove is formed that receives the arcuate rail. The arcuate rail is secured in the annular groove using a resilient strip interposed between the rail and the groove. The resilient strip includes a planar main body and sprung wings that extend to either side of the main body. The wings are angled with respect to the plane of the main body. The resilient strip is moveable circumferentially between a first position in which the strip exerts a force radially on the arcuate rail and a second position in which the wings occupy recesses in the assembly.

Abstract: An airfoil suitable for being arranged in a compressor section of the gas turbine includes a platform, a pressure surface and a suction surface, and a tip region. The tip region is located between the pressure and the suction surface opposite to the platform in respect of the pressure and the suction surfaces, being a distant end of the airfoil in direction along the first direction perpendicular to the platform. The tip region includes a first surface with a first distance to the platform along the first direction, and a second surface with a second distance to the platform along the first direction. The first distance is greater than the second distance and the first surface and the second surface together build a profiled surface. The profiled surface is a ribbed surface. The material of the first surface is deformable to bend away from the rotation direction of the airfoil.

Abstract: A mounting apparatus includes a mounting pin having first and second ends, and a support having first and second sides. The support includes a passage between the first and second sides for receiving the mounting pin so that the first end of the pin protrudes from the first side and the second end of the pin protrudes from the second side. The second end of the pin engages an article to be mounted by the mounting apparatus. The first end rotates the pin about the axis of the pin to vary the position of a mounted article. A clamping plate clamps the first end of the mounting pin to the first side of the support for securing the rotational position of the pin with respect to the support.

Abstract: A fluid intake assembly adapted for use with a turbo-machine is provided. The fluid intake assembly provides an efficient fluid inlet assembly including a casing adapted to guide fluid into the turbo-machine. The casing includes an inner wall, the inner wall having a lining of a resin infused composite material. A method of producing a fluid intake assembly for use with a turbo-machine is also provided.

Abstract: A device, system, or method to position variable guide vanes disproportionately is provided. An adjusting device for guide vanes of an axial-flow machine, includes a plurality of rotatably mounted rings of variable guide vanes, a plurality of levers which are arranged on the outer sides of a guide vane carrier for rotating the variable guide vanes, a plurality of adjusting rings, each of the adjustment rings is arranged coaxially to the guide vane carrier and to which a first end of one of the levers is connected, and an adjusting drive with which the adjusting rings may be moved in the peripheral direction. At least one of the levers is set up to perform at least partly a disproportionate longitudinal movement of the first end of the at least one lever.

Abstract: A fluid intake assembly adapted for use with a turbo-machine is provided. The fluid intake assembly provides an efficient fluid inlet assembly including a casing adapted to guide fluid into the turbo-machine. The casing includes an inner wall, the inner wall having a lining of a resin infused composite material. A method of producing a fluid intake assembly for use with a turbo-machine is also provided.

Abstract: A guide vane for a compressor with an airfoil, and a base plate for mounting the guide vane to a compressor casing is provided. The base plate includes an air duct sized and configured to guide compressor air off the airfoil through the air duct. Further disclosed is a guide vane arrangement.