Abstract: An apparatus, especially a steam turbine, including a first delimiting part and a second delimiting part is provided. The delimiting parts are attached to one another forming a joint and enclosing at least a part of a first pressure chamber. A shielding element is also provided on the sides of the delimiting parts facing towards the first pressure chamber and is arranged to form a seal completely covering the joint, so that a cavity is formed between the delimiting parts and the shielding element. A line is routed in the cavity connecting the cavity to a second pressure chamber. In addition, a method for decreasing the force acting on a joint, which is formed by the joining together of a first delimiting part and a second delimiting part of an apparatus, especially a steam turbine, and for reducing the attachment forces acting on the joint is provided.

Abstract: A combustor (14) is placed next to a turbine (16), on the side opposite a compressor (12). A heat insulation device (20) for reducing the transmission of heat from the high-temperature side to the low-temperature side is provided between the combustor/turbine and the compressor. A connection shaft (18) has an axial hole (18a) open on the inlet side of the compressor and axially extending to near a turbine impeller, and also has a radial hole (18b) open near the turbine impeller to the outside of the connection shaft and radially extending to be in communication with the axial hole.

Abstract: A system to cool the air inside a nacelle of a wind turbine including the heat generating components such as the drivetrain, the electrical generator, the converter, and the transformer. The system has an upper cooling circuit, with a reservoir disposed below the nacelle. The reservoir has at least one pair of annular chambers and a lid that freely rotates about its axis and about the nacelle yaw axis. Coolant flows from a first annular chamber to a second annular chamber through a heat exchanger in the nacelle, thereby carrying heat from the nacelle to the second annular chamber. The system also has a lower cooling circuit, having a coil that connects the first annular chamber to the second annular chamber and being exposed to the outside of the wind turbine. Coolant flows from the second annular chamber to the first annular chamber through the coil, thereby dissipating the heat to ambient air.

Abstract: A compressor end head for providing a thermal barrier near a mechanical seal includes an inner end head and an outer end head. The outer end head includes an opening in the center for enclosing the inner end head, an outlet and grooves alongside surfaces radially adjacent the opening. The inner end head has an opening in the center, an inlet, grooves in the opening for enclosing an end portion of a compressor shaft and a flow path along an outer surface.

Abstract: Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction.

Abstract: An apparatus and method for maintaining separation of two journal foil bearing assemblies, where each journal foil bearing assembly comprises one or more foils with lugs formed thereon for insertion into axial grooves of a bore, the means comprising a pin for insertion into each groove so that an edge of the lug that is inserted into the groove abuts the pin and is prevented from axially drifting along the bore. The pin provides a broad area along the lug edge so that the lug edge does not cut into the pin.

Abstract: An example fan assembly impeller moves air along a secondary flow path when driven by a motor. The motor also drives a fan rotor to move air along a primary flow path of the fan assembly. Air moving along the primary flow path moves in a first direction. Air moving along the secondary flow path moves in a second direction opposite the first direction. An example fan shroud communicates air used to cool a motor into a primary flow path of a fan assembly. The shroud communicates the air into the primary flow path so that the flow of air is at least partially aligned with air moving through the primary flow path of the fan assembly.

Abstract: A pressure and temperature actuation system is provided having a high-temperature low-pressure zone, a low-temperature high-pressure zone, a boundary, a pressure actuated mechanism, and a temperature mechanism. A gas located in the high-temperature low-pressure zone has a greater gas temperature than the gas located in the low-temperature high-pressure zone. The gas located in the low-temperature high-pressure zone has a greater gas pressure than the gas located in the high-temperature low-pressure zone. The boundary separates the high-temperature low-pressure zone from the low-temperature high pressure zone. The pressure actuated mechanism is located within the boundary and is configured for opening at a specified gas pressure in either the high-temperature low-pressure zone or the low-temperature high-pressure zone.

Abstract: A high pressure turbine includes a stator, a rotor, a tangential on-board injector, and a heat shield. The rotor is located downstream of the stator and the tangential on-board injector directs cooling air to the rotor. The heat shield is retained by abutment with the stator and the tangential on-board injector.

Abstract: A cooling system for the rear bearing capsule of a turbine in a gas turbine engine supported by an exhaust cone attached to multiple exit guide vanes that extend radially from the exhaust cone to an exhaust housing, comprises: an inlet air flow path through each guide vane between a source of cool ambient air and the rear bearing capsule; and at least one discharge air flow path that receives air from the inlet air flow path through each guide vane and passes the air through the exhaust cone from the rear bearing capsule to a high velocity gas flow path in the exhaust housing.

Abstract: A seal assembly for a gas turbine engine is provided that includes a seal support member, at least one knife edge seal blade member, and at least one cooling member. The seal support member is configured for rotation within the gas turbine engine around an axial centerline of the engine. The support member has a thickness extending between a first surface and a second surface. The blade member extends outwardly from the first surface of the support member. The blade member has a central portion that extends between a base end and a distal knife edge end. The base end is attached to the first surface of the seal support member. The cooling member extends outwardly from the second surface, and is oppositely aligned with the blade member.

Abstract: Assemblies for cooling an aft bearing assembly mounted to a rotor are provided. An assembly includes a static aft bearing structure configured to surround the aft bearing assembly and including a cylindrical section defining a cavity for disposal of the aft bearing assembly, a plurality of hollow struts extending from the static aft bearing structure, each hollow strut including an outer radial end configured to receive a gas from an air source and to provide a pathway for the gas to flow into the cavity, and a center-body cap disposed over an end of the static aft bearing structure, the center-body cap including a rim configured to create a low pressure region at an interface between the static aft bearing structure and the center-body cap, wherein the low pressure region has a pressure that is lower than a pressure within the cavity.

Abstract: A turbomachine comprises a housing (71) defining a bearing cavity (71) and a turbine chamber (77a) separated by a first wall. A heat shield (72) is disposed between the first wall and the turbine wheel (77), a heat shield cavity (78) being defined between the first wall and the heat shield (72). The shaft (81) extends through a passage (85) defined at least in part by a first aperture (86) in said wall and a second aperture (87) in the heat shield (72). A first seal (88) is provided between the shaft (81) and said first aperture (86). The housing defines a first gas channel (79) communicating with the heat shield cavity (78) for connection to a pressure source for raising pressure within the heat shield cavity (78). A second channel (92) is provided between the heat shield cavity (78) and said passage (85), the second channel opening to said passage (85) on the opposite side of said first seal (88) to said bearing assembly (82).

Abstract: A steam turbine includes a turbine rotor, a generator end having a generator end first stage with a first reaction, and a turbine end having a turbine end first stage with a second reaction not equal to the first reaction. The steam turbine includes a tub section disposed between the generator end and the turbine end, the turbine rotor and the tub section defining an annulus therebetween. A difference between the first reaction and second reaction is capable of urging a steam flow through the annulus for reducing a temperature of the turbine rotor. A method of cooling the turbine rotor is also disclosed.

Abstract: A turbine rotor 300 includes: a high-temperature turbine rotor constituent part 301 where high-temperature steam passes; low-temperature turbine rotor constituent parts 302 sandwiching and weld-connected to the high-temperature turbine rotor constituent part 301 and made of a material different from a material of the high-temperature turbine rotor constituent part 301; and a cooling part cooling the high-temperature turbine rotor constituent part 301 by ejecting cooling steam 240 to a position, of the high-temperature turbine rotor constituent part 301, near a welded portion 120 between the high-temperature turbine rotor constituent part 301 and the low-temperature turbine rotor constituent part 302. A value equal to a distance divided by a diameter is equal to or more than 0.

Abstract: Means for cooling a bearing assembly supporting a rotor stage of a gas turbine engine after engine shutdown. The engine comprises a combustion section, a compressor for the delivery of air to the combustion section, and a bearing assembly supporting a rotor stage. The means for cooling a bearing assembly comprises a means operable to generate a signal representative of turbine duct temperature immediately prior to engine shutdown, a means for determining the duration for cooling after engine shutdown as a function of the signal representative of turbine duct temperature, and the compressor operable as a cooling means to deliver cooling air to the rotor stage after engine shutdown. Thereby the amount of heat conducted to the bearing assembly is limited such that the temperature of the bearing assembly is limited to below a predetermined temperature.

Abstract: A steam turbine is provided. The steam turbine includes a rotor shaft including a plurality of buckets coupled thereto. The steam turbine further includes a stationary component coupled to a steam turbine casing, wherein the stationary component is coupled upstream from the buckets such that a wheelspace is defined between the buckets and the stationary component. The stationary component includes a first ring coupled to the steam turbine, a second ring coupled to the steam turbine radially inward from the first ring, and at least one airfoil extending between the first ring and the second ring. The steam turbine includes a cooling fluid flowpath defined through at least the first ring, the airfoil, and the second ring. The cooling fluid flowpath is configured to channel a cooling fluid to the wheelspace.

Abstract: A fluid cooled fastener assembly for use in a high temperature environment and a method of fluid cooling a fastener assembly are provided. The fastener has a coolant passage extending axially through the fastener and a coolant collector coupled to an end of the fastener. The coolant collector includes a collector opening configured to capture a portion of a cooling fluid flowing past the coolant collector and a contoured passage in communication with the collector opening and the passage in the fastener. The contoured passage is configured to accelerate the cooling fluid captured by the coolant collector and to direct it into the coolant passage in the fastener.

Abstract: Embodiments of the present invention include a method and system for carrying out vapor-phase lubrication of a component, such as a bearing for example. The method and apparatus can be applied to a turbine engine. The method includes the step of directing a first stream of fluid containing atomized lubricant to the component at a first velocity. The system provides a first fluid injection system configured to perform the first step. The method also includes the step of directing a second stream of fluid at a second velocity less than the first velocity to the component. The second stream is for controlling a temperature of the component. The system provides a second fluid injection system configured to perform the second step. Both of the directing steps are carried out concurrently.

Abstract: A wind turbine having a cooling system, which wind turbine includes a nacelle in connection with which one or more wind turbine components are arranged, is disclosed. The cooling system includes at least one cooling circuit arranged to lead a heat transfer medium to and from one or more of the wind turbine components, at least one cooling device arranged to cool the heat transfer medium, at least one pump arranged in connection with the at least one cooling circuit to circulate the heat transfer medium in the cooling circuit, and at least one medium tank arranged in connection with the cooling circuit. The at least one medium tank is arranged inside the nacelle.

Abstract: An air cycle machine includes a housing, and a shaft rotationally supported within the housing includes a thrust runner. Air bearings are provided on either side of the thrust runner. An inlet plate is arranged radially outward of the air bearings. The inlet plate has inner and outer peripheries provided between lateral sides. One side includes four circumferentially arranged slots extending from the outer periphery to the inner periphery and having a width and a depth providing a first ratio of 4:1.

Abstract: In one embodiment, a turbine may include a bearing housing for a rotor with a passage along an axis of rotation of the rotor shaft. A cooling gland configured to transfer cooling fluid to the passage may be mounted to the bearing housing with a mounting structure configured to mount the cooling gland substantially in-line with the passage of the rotor.

Abstract: A rotating machine cooled by a cooling medium directed through the rotating machine in a main flow and a secondary flow includes a rotor. A stator includes a swirl passage configured to guide the secondary flow so as to be discharged from a pre-swirl nozzle. At least one control device includes a shape-memory alloy disposed in an area of the pre-swirl nozzle and is configured to control the secondary flow based on a temperature in an automated manner.

Abstract: A service tube apparatus for a gas turbine engine includes a service tube assembly having: (a) an elongated, hollow service tube; and (b) a service tube baffle surrounding the service tube which is pierced with a plurality of impingement cooling holes.

Abstract: The present application provides a compressor clearance control system for a gas turbine engine. The gas turbine engine includes a turbine producing exhaust gases and a compressor with a casing and a number of rotor blades. The compressor clearance control system may include a casing heat exchanger positioned about the casing of the compressor and an extraction port for exhaust gases from the turbine. The extraction port is in communication with the casing heat exchanger so as to heat the casing of the compressor with the exhaust gases from the turbine.

Abstract: A turbocompressor assembly is provided, which is divided along a rotor axis into at least three sections. The three sections include a bearing section having an active magnetic bearing, a motor section including a motor having a stator arranged along the rotor axis, the stator enclosing a circumferential motor gap formed between the stator and the rotor, and a compressor section having a compressor for compressing a cooling fluid. A gas-tight housing encloses the rotor, the bearing section, the motor section and the compressor section. A cooling system is provided having an inlet for supplying the pressurized cooling fluid to the bearing section and the motor section through a fluid channel positioned between the bearing section and the motor section. The cooling system includes a throttling device positioned adjacent to the motor gap for limiting the flow of cooling fluid from the fluid channel to the motor gap.

Abstract: An inducer for a casing of a gas turbine system is disclosed. The inducer includes a plurality of orifices defined in the casing, the plurality of orifices disposed in an annular array about the casing, and a plurality of cartridges, each of the plurality of cartridges configured to mate with one of the plurality of orifices. Each of the plurality of cartridges includes an inlet and an outlet for flowing a cooling medium therethrough. The inducer further includes at least one flow modifier disposed in each of the plurality of cartridges for modifying the flow of the cooling medium through each of the plurality of cartridges. Each of the plurality of cartridges is independently removable from each of the plurality of orifices.

Abstract: According to an aspect of the invention, a method for ventilating a turbine compartment is provided, the method comprising directing an air flow from an air intake to a first air conduit, transferring a first heat between the air flow and a first fluid within a heat exchange apparatus and pumping the first fluid through a fluid circuit in fluid communication with the heat exchange apparatus, wherein a portion of the fluid circuit is located underground. The method further includes transferring a second heat between the first fluid and a surrounding ground and directing a conditioned air flow from the heat exchange apparatus to a turbine compartment via a second air conduit.

Abstract: The present application provides a compressor clearance control system for a gas turbine engine having an oil recirculation system with a flow of oil therein and a compressor with a casing and a number of rotor blades. The compressor clearance control system may include a casing heat exchanger positioned about the casing of the compressor and a conduit in communication with the casing heat exchanger and the oil recirculation system so as to heat the casing of the compressor with the flow of oil from the oil recirculation system.

Abstract: A component of a turbine stage of a gas turbine engine is provided. The component forms an endwall for the working gas annulus of the stage. The component has one or more internal passages behind the endwall which, in use, carry a flow of cooling air providing convective cooling for the component at the endwall. Each passage is formed by a plurality of straight passage sections. The passage sections connect end-to-end such that the connections between nearest-neighbour passage sections form angled bends. A first portion of the passage sections lie in a first plane. A second portion of the passage sections lie in a second plane which is spaced from and parallel to the first plane. A third portion of the passage sections extend between the first and the second planes.

Abstract: A ring segment for a gas turbine engine includes an outer panel defining a structural body for the ring segment. An outer side of an inner panel is attached to an inner side of the outer panel at an interface, and an inner side of the inner panel defines a portion of a hot gas path through the gas turbine engine. An outer side of the outer panel, opposite from the interface, is in communication with a source of cooling air. A plurality of impingement holes extend through the outer panel from the outer side to the inner side of the outer panel for directing impingement air to the outer side of the inner panel. The outer and inner panels define a plurality of flow channels at the interface for effecting convective cooling of the outer panel along the flow channels between the outer and inner panels.

Abstract: In accordance with one embodiment, a system includes a multi-stage turbine including a first turbine stage including a first wheel having multiple first slots spaced circumferentially about the first wheel, and multiple first blade segments each coupled to at least one of the multiple first slots. The multi-stage turbine also includes a second turbine stage including a second wheel having multiple second slots spaced circumferentially about the second wheel, and multiple second blade segments each coupled to at least one of the multiple second slots. The multi-stage turbine further includes a one-piece interstage seal extending axially between the first and second turbine stages, wherein the one-piece interstage seal comprises a first radial support coupled to the first wheel and a second radial support coupled to the second wheel, and the one-piece interstage seal extends circumferentially across at least two of the multiple first slots or at least two of the multiple second slots.

Abstract: A turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring held by a casing of the turbine, and an annular thermal protection sheet mounted between the casing and the sealing ring is disclosed. The annular thermal protection sheet is formed by a plurality of curved plates mounted end-to-end and attached by pins to the casing.

Abstract: An assembly for a turbocharger that includes a bearing housing with a cylindrical portion with a bore configured for receipt of a bearing, an extension that extends radially outwardly from the cylindrical portion to a base, the base configured with one or more features for securing the bearing housing to another component, a compressor fitting, a turbine fitting, and lubricant flow paths; and a fluid jacket that includes a cylindrical wall configured for placement over at least a portion of the cylindrical portion of the bearing housing where the cylindrical wall includes a recess configured to accommodate at least a portion of the extension of the bearing housing, a fluid inlet, and a fluid outlet. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A method of cooling a double flow steam turbine includes supplying steam flow to each nozzle of the sections of the turbine; reversing a portion of each steam flow to provide a reverse steam flow from an aft side to a forward side of each section. Each reverse steam flow is directed to an annular space between a rotor and a tub. The method further includes removing the reverse steam flows through a pipe, the pipe having a first end at the annular space at a first pressure and a second end at a second pressure that is lower than the first pressure. A double flow steam turbine, includes a pair of nozzles, each nozzle being provided at a section of the turbine; a rotor supporting buckets of the sections; a tub supporting the pair of nozzles; and a pipe extending from an annular space between the tub and the rotor. The pipe has a first end at the annular space and second end. A pressure at the first end of the pipe is greater than a pressure at the second end.

Abstract: A cooling arrangement for a first stage nozzle of a turbine includes a slot formed in a forward face of the first stage nozzle, the slot opening in a direction facing a combustor transition piece and adapted to receive a flange portion of a seal extending between the first stage nozzle and the transition piece. The slot has a closed end formed with at least one cooling cavity provided with at least one cooling passageway extending between the cavity and an external surface of the first stage nozzle.

Abstract: There are provided first and second water supply passages to supply cooling water from an engine to first and second center housings of first and second turbochargers, and first and second return passages to return the cooling water from the first and second turbochargers to the engine. A cooling-water connection portion of the first water supply is located above the level of a cooling-water connection portion of the second water supply passage. A vapor releasing passage is provided between the second turbocharger and an upper tank provided on the outside of an engine body at a position located above the connection portion of the second return passage of the second turbocharger. Accordingly, the function of vapor releasing from the first and second turbochargers can be improved, thereby increasing the layout flexibility around the engine.

Abstract: A cooling system for a turbocharger that has a cooling jacket in the bearing housing wherein air is bled from the area behind the compressor wheel and introduced into the cooling jacket, through which it circulates and then exits into the atmosphere. In addition, a pressure relief valve located behind the compressor wheel is set to open at a predetermined charge air pressure level to introduce additional cooling air into the cooling jacket and also acts to limit the maximum rotational speed of the turbocharger over the high-speed range of the engine on which the turbocharger is mounted. In an alternate embodiment of the invention, cooling air can be taken from the intake manifold system of a turbocharged engine downstream of an air-to-air aftercooler and ducted to the cooling jacket in the turbocharger bearing housing.

Abstract: A cooling fluid metering system for a turbine blade of a gas turbine engine is disclosed. The cooling fluid metering system may include a cooling channel positioned between a root of a turbine blade and an offset rotor sealing plate for supplying cooling fluids to turbine blades. At one point, a portion of the cooling channel may include a gap between the root and the offset rotor sealing plate. The gap may be sealed with teardrop shaped seal positioned within a teardrop shaped cavity at the gap. The cavity and seal may be positioned such that during operation, the seal is forced radially outward and into the gap, thereby effectively metering cooling fluid flow through the cooling channel.

Abstract: A seal assembly limits gas leakage from a hot gas path to one or more disc cavities in a gas turbine engine. The seal assembly includes a seal apparatus associated with a blade structure including a row of airfoils. The seal apparatus includes an annular inner shroud associated with adjacent stationary components, a wing member, and a first wing flange. The wing member extends axially from the blade structure toward the annular inner shroud. The first wing flange extends radially outwardly from the wing member toward the annular inner shroud. A plurality of regions including one or more recirculation zones are defined between the blade structure and the annular inner shroud that recirculate working gas therein back toward the hot gas path.

Abstract: A lubrication system for a bearing assembly includes a fan shaft with a plurality of conduits, a first bearing rotatably supporting the fan shaft, and a second bearing rotatably supporting the fan shaft where the second bearing is axially spaced from the first bearing. The plurality of conduits includes at least a first conduit aligned with the first bearing and a second conduit aligned with the second bearing. A spray bar includes a plurality of supply orifices that direct lubricating fluid to the first and second bearings via at least the first and second conduits.

Abstract: A turbine rotor is provided. The turbine rotor has a plurality of blades assembled into blade rows and arranged on a turbine disk. Each blade has a blade root arranged in a blade retaining slot of the turbine disk extending in an axial direction. A locking plate is arranged between the respective blade root and a base of the blade retaining slot, for securing blades against a displacement along the blade retaining slot. The locking plate is fixed to the turbine disk by folds. The locking plate comprises a plurality of cooling air holes for the passage of cooling medium from a cooling air feed passage. The respective blade root comprises two grooves extending substantially azimuthally in relation to a turbine axis, and the respective locking plate comprises two tongues which are arranged such that they are connected to the two grooves of the blade root for sealing.

Abstract: A multiport valve suitable for use with a gas-turbine allowing switching of a mode of gas-turbine operation between a Brayton cycle and an inverse Brayton cycle, and a gas-turbine configured to switch between a high-pressure operation mode according to a Brayton cycle and a low-pressure operation mode according to an inverse Brayton cycle employing the valve are provided. Also provided are a method and apparatus for operating a gas-turbine according to an inverse Brayton cycle.

Abstract: A gas turbine engine comprises a pre-swirl structure coupled to a shaft cover structure and located radially between a supply of cooling fluid and a flow path. The pre-swirl structure defines a flow passage and includes a plurality of swirl members in the flow passage. A flow direction of cooling fluid passing through the flow passage is altered by the swirl members such that the cooling fluid has a velocity component in a direction tangential to the circumferential direction. The bypass passages provide cooling fluid into a turbine rim cavity associated with a first row vane assembly to prevent hot gas ingestion into the turbine rim cavity from a hot gas flow path associated with a turbine section of the engine.

Abstract: A turbocharger assembly includes a turbocharger housing, an elongated cylindrical center housing, a turbine in a turbine housing, a compressor in a compressor housing and a bearing assembly on a rotary shaft. The bearing assembly including balls, ball retainers, an inner and outer ring with raceways thereon, a lubrication port and a cooling port. The cooling port is located towards the outside of the bearing and directed away from the bearing, whereas the lubrication port is directed towards the bearing and is located towards an inside surface of the bearing.

Abstract: A compressor rotor compresses and delivers compressed air across a turbine rotor. The turbine rotor is connected to the compressor rotor such that rotation of the turbine rotor drives the compressor rotor. A shaft is connected to rotate with the turbine rotor and the compressor rotor. A thrust bearing is provided by a member extending perpendicular and radially outwardly of the shaft. The member rotates with the shaft and faces a first housing wall. A hollow chamber is formed on an opposed side of the first housing wall. A cooling air path supplies air across a thrust bearing surface, and between the member and the first housing wall. The first housing wall has a communication hole for communicating cooling air from the cooling air path into the hollow cavity to drive air within the hollow chamber. Also, a housing incorporating the communication hole is disclosed.

Abstract: An oil cooled runner, for a rotary seal between an engine case and a shaft rotationally mounted to the case, includes an annular runner ring having a platform with a radially outer seal engagement surface and a radially inner surface, and an oil distributor having a radially inner portion in communication with a source of liquid lubricant and an outer lubricant casting cone with a rim disposed radially inwardly from the inner surface of the platform.

Abstract: A small twin spool gas turbine engine with a forward end of the engine supported by bearings that are cooled by passing a cooling fluid such as cooling air bled off from the compressor with a liquid lubricant sprayed into the cooling air that is then passed through the bearing to prevent overheating. The cooling fluid is then discharged from the bearing cooling circuit out the front end of the engine through a number of discharge holes formed within the threaded nut that secures the fan blade assembly to the low speed rotor shaft. The threaded nut includes a plurality of slanted holes that slant outward from the rotational axis in the direction of fluid discharge.

Abstract: A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes.

Abstract: A gas turbine is provided that includes a rotor which is rotatable around an axis and equipped with rotor blades, and which is concentrically enclosed at a distance by a casing, which is equipped with stator blades, forming an annular hot gas passage. Rings with stator blades and rotor blades are arranged in a manner alternating in the axial direction. Between adjacent stator blades, heat shield segments are arranged, which delimit the hot gas passage on the outside in a region of the rotor blades and are cooled by impingement cooling where a cooling medium from an outer annular cavity flows into the heat shield segment.