Abstract: A method of setting a clearance between a rotor and a stator of a rotor assembly for a turbine engine. The rotor assembly has a plurality of rotor-to-stator stages and the stator has a nominal centerline. Typically the stator is a casing or an array of vane tips. The method includes (i) correlating in-service rotor-to-stator rub patterns for a rotor-to-stator stage of a number of turbine engines, (ii) setting a position of a machining centerline relative to the nominal centerline of the stator, the position being towards a heavy rub, (iii) machining the stator about the machining centerline, (iv) repeating steps (i) to (ii) for each rotor-to-stator stage of the plurality of the rotor-to-stator stages, wherein the machined stator having been formed by at least two machining steps having different center-lines.

Abstract: A turbine airfoil has a suction side wall and a pressure side wall of an airfoil cavity, through which a cooling fluid flows for cooling of the side walls. The suction side wall has one or more protrusions extending therefrom into the airfoil cavity. The protrusions are arranged such that: a number of the one or more protrusions on the suction side wall is higher than a number of protrusions on the pressure side wall; and/or a protrusion density on the suction side wall is higher than a protrusion density on the pressure side wall, and/or a total protrusion surface area on the suction side wall is larger than a total protrusion surface area on the pressure side wall, so that the heat transfer from the suction side wall to the cooling fluid is higher compared to that of the pressure side wall during operation of the turbomachine.

Abstract: A method of setting a clearance between a rotor and a stator of a rotor assembly for a turbine engine. The rotor assembly has a plurality of rotor-to-stator stages and the stator has a nominal centreline. Typically the stator is a casing or an array of vane tips. The method includes (i) correlating in-service rotor-to-stator rub patterns for a rotor-to-stator stage of a number of turbine engines, (ii) setting a position of a machining centreline relative to the nominal centreline of the stator, the position being towards a heavy rub, (iii) machining the stator about the machining centreline, (iv) repeating steps (i) to (ii) for each rotor-to-stator stage of the plurality of the rotor-to-stator stages, wherein the machined stator having been formed by at least two machining steps having different centre-lines.

Abstract: A gas turbine engine including a rotor is disclosed. The rotor includes a stud extending along an axis, rotating elements of a first section, and rotating elements of a second section. The stud includes a first and second external end, the first external end adapted to engage a first pre-load nut or a shaft and the second external end adapted to engage a second pre-load nut or a shaft such that the set of rotating elements are secured. Thus stud includes a first shank connected to the first external end and a second shank connected to the second external end. The first shank is located in the first section and has a first diameter. The second shank is located in the second section and has a second diameter which is greater than the first diameter.

Abstract: A turbine airfoil for a turbomachine is provided. The airfoil includes a suction side wall and a pressure side wall bordering an airfoil cavity, which receives a cooling fluid for cooling the airfoil. The suction side wall includes one or more protrusions extending inside the cavity. The number of protrusions on the suction side may be higher than the number of protrusions on the pressure side. The density of protrusions on the suction side may be higher than the density of protrusions on the pressure side and/or the surface of protrusions on the suction side may be larger than the surface of protrusions on the pressure side, so that heat transfer from the suction side to the cooling fluid is higher compared to heat transfer from the pressure side to the cooling fluid during operation of the turbomachine.

Abstract: A preparation of liquid fuel for combustion, particularly for ignition, in the burners of a gas turbine is proposed. A source of heated liquid fuel, particularly heated pressurized fuel, is arranged in a reservoir. The reservoir is arranged in parallel with a main fuel feed of a combustion system. The reservoir can be filled by the main fuel feed and/or evacuated into the main fuel feed. The reservoir contains a heating means, which heat the liquid fuel filled in the reservoir, particularly while circulating in the reservoir.

Abstract: A turbine nozzle segment of a turbo-machine includes a platform defining a segment of a boundary for a main fluid path, the platform having a section, particularly a trailing section of the platform. The section has a surface along which a main fluid flows during operation of the turbo-machine. The surface further includes a plurality of alternating elevations and depressions, wherein the elevations and the depressions both are arranged substantially perpendicular to a direction of a main fluid flow of the main fluid.

Abstract: A gas turbine engine including a rotor is disclosed. The rotor includes a stud extending along an axis, rotating elements of a first section, and rotating elements of a second section. The stud includes a first and second external end, the first external end adapted to engage a first pre-load nut or a shaft and the second external end adapted to engage a second pre-load nut or a shaft such that the set of rotating elements are secured. Thus stud includes a first shank connected to the first external end and a second shank connected to the second external end. The first shank is located in the first section and has a first diameter. The second shank is located in the second section and has a second diameter which is greater than the first diameter.

Abstract: A turbine and a method for converting energy are provided, wherein an angular position of an exit of a cooling duct in the casing depends on angular positions of a downstream edge 21 of a guide vane and on an angular position of a fluid entry duct for supplying streaming fluid to the turbine. Further, unnecessary cooling of components in the turbine not subjected to high temperature and high pressure is avoided by providing a consolidated casing at particular angular and axial positions.

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: An apparatus for supporting a rotating shaft comprising: a housing surrounding the shaft; interposed between the housing and the shaft a plurality of tilting pads which extend in contiguous manner circumferentially around the shaft, each tilting pad being able to rock in the rotation of the shaft; and interposed between each pair of adjacent tilting pads retaining means for preventing circumferential movement of the pads around the housing due to rotation of the shaft, wherein the physical relationship between at least one tilting pad and its adjacent retaining means is such that said rocking of the pad takes place without circumferential slippage of the pad around the housing.

Abstract: A turbine engine component, particularly an aerofoil, including a body is provided. The turbine engine component includes a first surface exposed to a working fluid of high temperatures during operation, a second surface including a depression, the depression is exposed to a cooling fluid during operation and oriented such that, starting from the second surface, the depression deepens in the direction of a back face of the first surface. Furthermore the body includes a body portion between the back face and the first surface. The depression is defined such that a diameter of the depression decreases from the second surface in direction of the back face.

Abstract: A mechanical coupling for transferring torque from a first component that rotates about an axis to a second component that also rotates about the axis is provided. The coupling allows different rates of expansion of the first and second components in the radial direction by permitting sliding in the radial direction of the components relative to one another. The coupling comprises first and second circular arrays of teeth formed on the first component and second component, respectively, and centered on the axis. The first circular array of teeth are intermeshed with the second circular array of teeth, wherein rotation of the first component causes first mating sides on the first circular array of teeth to bear against second mating sides on the second circular array of teeth transferring torque to the second component. The first and second mating sides extend both axially and radially and are essentially curved.

Abstract: Disclosed is a radial tilt pad bearing assembly comprising: an outer carrier; a plurality of tilt pads retained within the outer carrier; and a corresponding plurality of retaining pins to retain the tilt pads in given circumferential positions, each fixed in the bearing assembly outer carrier so as to abut a side face of a cavity in the corresponding tilt pad. At least one retaining pin and the corresponding cavity are respectively shaped such that, when in use, a clearance in a plane transverse to the axes of the bearing assembly and the tilt pad between the retaining pin and the side face is lesser at a first location which lies substantially at the inner surface of the carrier, than at all corresponding locations at radially inner portions of the side face, with respect to the first location. A contact point between the retaining pin and the tilt pad when in use, lies substantially at the inner surface of the outer carrier.

Abstract: An apparatus for supporting a rotating shaft comprising: a housing surrounding the shaft; interposed between the housing and the shaft a plurality of tilting pads which extend in contiguous manner circumferentially around the shaft, each tilting pad being able to rock in the rotation of the shaft; and interposed between each pair of adjacent tilting pads retaining means for preventing circumferential movement of the pads around the housing due to rotation of the shaft, wherein the physical relationship between at least one tilting pad and its adjacent retaining means is such that said rocking of the pad takes place without circumferential slippage of the pad around the housing.

Abstract: The invention provides a radial tilt pad bearing assembly comprising: an outer carrier (12); a plurality of tilt pads (14) retained within the outer carrier; and a corresponding plurality of retaining pins (50) to retain the tilt pads in given circumferential positions, each fixed in the bearing assembly outer carrier so as to abut a side face (38) of a cavity (28) in the corresponding tilt pad. At least one retaining pin (50) and the corresponding cavity (28) are respectively shaped such that, when in use, a clearance (c) in a plane transverse to the axes of the bearing assembly and the tilt pad between the retaining pin (50) and the side face (38) is lesser at a first location (54) which lies substantially at the inner surface of the carrier (12), than at all corresponding locations at radially inner portions of the side face, with respect to the first location.

Abstract: A turbine nozzle support assembly includes nozzle segments each having an inner band with an integral retention flange extending radially inwardly therefrom. A plurality of retention tabs extend radially inwardly and are spaced axially aft of the retention flange to define a capture slot therebetween. A nozzle support includes a radially outwardly extending upper flange having a plurality of support pins extending axially, forwardly therefrom and disposed in complementary retention apertures in the retention flanges of the nozzle segments. A retention key is disposed in the capture slot axially between the upper flange and the retention tabs for axially retaining the nozzle segments on the nozzle support.

Abstract: A high pressure turbine in a gas turbine engine contains an arrangement of channels, holes and windows through components controlling the operating clearance between tips of turbine blades and casing shroud segments wherein the arrangement defines a serial supply path for a single cooling airflow through the clearance control components. The arrangement also includes a plurality of holes defined through a cover located between shroud holders and segments.

Abstract: In a gas turbine engine having an annular casing with a stationary support structure, a high pressure turbine, and an annular high pressure turbine nozzle having at least one stage which includes a plurality of circumferentially aligned nozzle segments and which is disposed in the annular casing between a combustor and the high pressure turbine, a nozzle support arrangement is provided for mounting each nozzle segment to the stationary support structure. The arrangement includes a single mounting pin mounted on and extending from an annular nozzle support flange on the casing support structure and a hole defined in an oval shape in the one end portion of an inner band flange for receiving the mounting pin in an interference fitting relation.

Abstract: A gas turbine engine nozzle includes outer and inner bands and a plurality of spaced apart vanes extending therebetween. The inner band includes an outer surface facing the outer band over which is flowable combustion gases, and a radially inwardly facing inner surface. A plurality of circumferentially spaced apart turbulators are joined to the inner band inner surface adjacent the trailing edges of the vanes for increasing cooling of the inner band by cooling air channeled over the turbulators.