Abstract: A centrifugal pump assembly includes a pump head, a pump base defining a pump inlet and a pump outlet, a fluid outlet channel from the pump head to the pump outlet, impellers, defining an impeller fluid channel between an impeller inlet and outlet and connected with one of rotor shaft segments including a positive fit coupling for torque transfer between at least two rotor shaft segments, and one or more pump stage housing segments arranged between the pump base and the pump head. The pump stage housing segments have a structure defining a guide passage for receiving pumped fluid from the impeller outlet of the impellers and for guiding pumped fluid to the impeller inlet of another one of the impellers or to the pump head. The pump stage housing segments each have a structure defining at least a part of a wall section of the fluid outlet channel.

Abstract: One exemplary embodiment of this disclosure relates to a refrigerant compressor for use in a chiller system. The compressor includes an electric motor arranged upstream of a stage of a compressor in the main refrigerant flow path. This disclosure also relates to an axial flow compressor of a relatively high capacity, and a recirculation feature for the same.

Abstract: An article of manufacture includes a rotor blade configured for use with a turbomachine. The blade is configured for attachment to a rotor wheel. The blade is configured to substantially reduce the possibility of attachment with an undesired rotor wheel by modification of at least one characteristic of the blade, so that the modification of the characteristic is matched by a complementary characteristic of the rotor wheel. The characteristic of the blade is, neck width, platform length, platform angle, platform height, tang height, or circumferential width. The blade and the wheel comprise a first stage of the turbomachine. The undesired rotor wheel is in a second stage of the turbomachine, where the first stage is different from the second stage. The complementary characteristic of the wheel is, slot opening width, platform opening depth, slot neck width, slot neck angle, slot tang depth, or slot tang width.

Abstract: A bladed disk may be arranged to rotate about an axis of rotation and including a rotor disk having an axial length extending from a first end to a second end, along the axis of rotation and a radial thickness extending between a first radius from the axis of rotation and a second radius from the axis of rotation, less than the first radius. The bladed disk may include a plurality of blades formed integrally with the rotor disk and arranged circumferentially around the rotor disk, and a first set of divides and a second set of divides, each divide comprising a partial break in the rotor disk extending axially from the first end of the rotor disk to the second end of the rotor disk and radially from the first radius to a third radius, less than the first radius and greater than the second radius.

Abstract: A gas turbine engine comprising a fan, a bypass duct positioned downstream of the fan and defined by an inner casing and an outer casing, a series of outlet guide vanes arranged downstream of the fan, the outlet guide vanes extending between the inner casing and the outer casing of the bypass duct; and a bifurcation positioned downstream of the outlet guide vanes and extending between the inner casing and the outer casing. The bifurcation comprises a leading edge, and the leading edge of the bifurcation is shaped so as to protrude axially forward by a varying distance from the inner casing to the outer casing so as to improve uniformity of a static pressure field formed, in use, immediately upstream of the bifurcation.

Abstract: An assembly includes a first vane pack, a second vane pack, and a liner lock segment. The first vane pack has a plurality of vanes each vane with an airfoil, a platform, and forward and aft mounting hooks. The second vane pack has a plurality of vanes each vane with an airfoil, a platform, and forward and aft mounting hooks. The second vane pack is disposed to abut the first vane pack. The liner lock segment is disposed between the first vane pack and the second vane pack.

Abstract: The present invention provides a casing assembly for a gas turbine engine comprising a radially inner casing and a radially outer casing. The assembly further comprises an axial mounting arrangement for mounting the inner casing and outer casing in a fixed axial relationship. The axial mounting arrangement allows radial movement of the outer casing relative to the inner casing such that distortion of the inner casing as a result of engine carcass loads on the outer casing is obviated as the inner casing is radially isolated from the outer casing.

Abstract: A retaining clip for use in limiting radial movement between a first section and a second section of a split fairing is provided. The first section includes a first clip tab and the second section includes a second clip tab extending therefrom, wherein the first and second clip tabs form a slot when the first section and the second section are substantially aligned. The retaining clip includes a first portion sized for insertion into the slot, a third portion coupled to the first and second clip tabs such that the first and second clip tabs are positioned between the first portion and the third portion, and a second portion extending between the first portion and the third portion.

Abstract: A rotor (10) of a rotary machine (T1) according to the invention includes a plurality of rotor members (20, 30, and 40) which are joined to each other in the axial direction in which the axis (P) extends, and among the plurality of rotor members (20, 30 and 40), the first rotor member (30) in hydraulic fluid injection portions (3a and 3b) of a passageway (3) is formed of Ni-based alloy so that the inside thereof is hollow throughout the entire length in the axial direction.

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170.

Abstract: A gas turbine stator for aircraft engines has a blade array with a plurality of blades constituted by a series of first blades and a series of second blades with different geometries; the array is formed by a plurality of sectors, each having an inner portion, an outer portion, at least one first blade and a least one second blade, and each defined by a body made in one piece; a single first blade is alternated with a single second blade for the entire circumference of the stator.

Abstract: a serial fan device including two fans linked serially is provided. Each of the two fans has a housing, a driving member and a fan wheel, the housing has an outer frame and a base, the outer frame has two openings and a guiding channel linking the two openings, the driving member is disposed on the base, and the fan wheel is rotatably coupled with the driving member. At least one of the two fans has a positioning rim on the outer frame for the base to couple therewith, and a radial buffer gap is formed between an outer periphery of the base and an inner periphery of the positioning rim. Accordingly, the radial buffer gap can largely reduce the vibration transmitted from the base to the outer frame.

Abstract: An axial turbomachine compressor drum rotor stage includes an axis of rotation, a wall generally symmetrical in revolution about the axis of rotation. The wall forms a hollow body and includes a veil and an annular area integrally formed with the veil for supporting a row of vanes. The annular area includes a central part raised in relation to that of the veil.

Abstract: A shaft assembly for a gas turbine engine that includes a shaft with a threaded shaft segment, an annular rotor disposed on the shaft, and annular stack nut. The stack nut includes a base nut segment and a clamping nut segment. The base nut segment includes a threaded nut bore that is mated with the threaded shaft segment. The clamping nut segment axially extends from the base nut segment to a load bearing surface. The clamping nut segment includes a radial thickness that decreases as the clamping nut segment extends from the load bearing surface towards the base nut segment. The load bearing surface exerts a force against the rotor securing the rotor to the shaft.

Abstract: The present invention relates to an inducer geometry which can optimize the behavior stability of cavitation in an inducer having a plurality of blades of the same geometry. In the inducer having a plurality of blades of the same geometry, a blade loading at a tip side in a front half of a blade is larger than that in a rear half of the blade; and when a blade angle from a circumferential direction of the inducer is expressed by ?b (degree) and a meridional distance is expressed by m (mm), an increase rate d?b/dm of the blade angle at the tip side is not less than 0.2 from a blade leading edge to a non-dimensional meridional location of 0.15, and the increase rate d?b/dm of the blade angle at a mid-span is not less than 0.25 from the blade leading edge to the non-dimensional meridional location of 0.15.

Abstract: A volumetric expander (20) configured to transfer a working fluid and generate useful work includes a housing. The housing includes an inlet port (24) configured to admit relatively high-pressure working fluid and an outlet port (26) configured to discharge to a relatively low-pressure working fluid. The expander also includes first and second twisted meshed rotors (30,32) rotatably disposed in the housing and configured to exp/and the relatively high-pressure working fluid into the relatively low-pressure working fluid. Each rotor has a plurality of lobes, and when one lobe of the first rotor is leading with respect to the inlet port, one lobe of the second rotor is trailing with respect to the inlet port. The expander additionally includes an output shaft (38) rotated by the relatively high-pressure working fluid as the fluid undergoes expansion. A system for generating work using the expander in a Rankine cycle is also disclosed.

Abstract: A pump for a fluid which can be blood has a stator housing and a rotor hub with leading and trailing portions and an intermediate portion disposed therebetween. At least one impeller blade at the leading portion drives circumferential and axial components of a flow into a pump annulus or intermediate pathway portion. At least one stator blade extends radially inward from the stator housing within the intermediate pathway portion and is configured to reduce a circumferential component of the flow.

Abstract: A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to a bypass area is less than about 170.

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

Abstract: A gas turbine engine comprises a fan and a turbine section having a first turbine rotor. The first turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from a fan drive turbine rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor: (the number of blades×the rotational speed)/(60 seconds/minute)?5500 Hz; and the rotational speed being in revolutions per minute. A compressor module and a method of designing a gas turbine engine are also disclosed.

Abstract: A fan impeller with multiple blades shaped and disposed to provide high air-power efficiency. The fan impeller includes a hub, a first plurality of primary blades and a second plurality of secondary blades. The leading edge of the first secondary blade is disposed proximately to the trailing edge of the first primary blade. A leading edge portion of the first secondary blade is also disposed in an inter-blade space between the first primary blade and a second primary blade. A trailing edge portion of the first secondary blade is disposed outside of the inter-blade space and towards a bottom of the hub. A cooling fan including the fan impeller, and an electrical apparatus including the cooling fan that includes the fan impeller are also provided.

Abstract: A mount interface between two rotating gas turbine engine components includes a rigid ring to provide radial deflection restraint. In one example, the rigid ring is comprised of a metal matrix composite material.

Abstract: A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s?5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine and a compressor module are also disclosed.

Abstract: A fluid conduit has a constant diameter and a chamber in the conduit has a larger diameter than the diameter of the conduit. Within the chamber, an impeller is rotatable by fluid moving through the conduit and the chamber. The impeller includes blades extending spirally along an impeller shaft. When rotated, the impeller blades define a cylinder having a diameter greater than the conduit diameter and less than the chamber diameter.

Abstract: A turbine apparatus includes: A first nozzle comprising an array of first vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; A rotor downstream from the first nozzle comprising a plurality of blades carried by a rotatable disk; and a second nozzle disposed downstream from the rotor comprising an array of second vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; wherein the first and second vanes of the first and second nozzles are circumferentially clocked relative to each other such that, in a predetermined operating condition, wakes discharged from the first vanes are aligned in a circumferential direction with the leading edges of the second vanes, wherein a stacking axis of the first vanes is nonlinear. An inner band of the first nozzle is contoured in a non-axisymmetric shape.

Abstract: A gas turbine engine has a fan, a compressor section having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a low pressure portion. The low pressure turbine portion drives the low pressure compressor portion and the fan. A gear reduction effects a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor portion. At least one of the low pressure turbine portion and low pressure compressor portion has a number of blades in each of a plurality of rows. The blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the at least one of the low pressure turbine portion and/or the low pressure compressor sections: (number of blades×rotational speed)/60?5500. The rotational speed is an approach speed in revolutions per minute.

Abstract: A turbine that allows for the conversion of the kinetic energy of waterway to mechanical power for use in an energy accepting apparatus is described. The turbine has complimentary components that improve the power efficiency of the turbine. The turbine may include a blade shroud and a plurality of blades that are connected to the blade shroud. On the external surface of the blade shroud, a drive mechanism and/or a brake mechanism may be disposed. An inlet nozzle and outlet diffuser may be used in combination with the turbine. The turbine may be useful in a number of settings, including, but not limited to, streams, rivers, dams, ocean currents, or tidal areas that have continuous or semi-continuous water flow rates and windy environments.

Abstract: A stage of a steam turbine, having a rotor extending along a longitudinal axis, has a fixed stage and a movable stage arranged successively along a flow channel for feeding steam in a direction substantially parallel to the longitudinal axis; the fixed stage has an inner ring coaxial with the longitudinal axis, and a number of stator blades arranged radially about the inner ring; each stator blade is fixed to an annular top portion of the inner ring, which has a top surface facing the flow channel and crosswise to the longitudinal axis; and the movable stage has a number of rotor blades arranged radially about the rotor and fixed to the rotor.

Abstract: A main flow path of a fluid flow machine includes N adjacent member blade rows firmly arranged relative to each other in both a meridional direction m and a circumferential direction u. A number of the member blade rows, N, is greater than/equal to 2 and (i) designates a running index with values between 1 and N. A trailing edge HK (i) of a blade of the member blade row (i) is spaced from a leading edge VK(i+1) of a blade of the adjacent, downstream member blade row (i+1) by a meridional edge distance D in a meridional plane established by axial direction x and radial direction r. A value of D along a height of the main flow path increases towards the main flow path confinement at least along a part of the area between the main flow path center and the main flow path confinement.

Abstract: A gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in operational noise that is above a sensitive range for human hearing. A method and turbine module are also disclosed.

Abstract: An integrally bladed rotor is utilized in at least a stage of one of a compressor and turbine section. Airfoils extend radially outwardly from a platform, and there is an undercut inward from the platform at a downstream edge of the airfoil.

Abstract: A rotor for an axial flow turbomachine is provided. The rotor includes a plurality of rotor discs that are arranged in stacks and clamped together with at least one tie rod. At least one of the rotor discs of the rotor comprises a smaller outer diameter than one of the neighboring rotor discs and that the difference in diameter is compensated by a drum surrounding the rotor disc with the smaller outer diameter as a ring. The drum may be made of a heat resistant material. The rotor discs surrounded by the drum may be made of a less expensive material. Furthermore, the drum may include at least one more blade ring than the rotor discs that are surrounded by the drum.

Abstract: A turbine of a turbomachine is provided and includes opposing endwalls defining a pathway into which a fluid flow is receivable to flow through the pathway; and a nozzle stage at which adjacent nozzles extend across the pathway between the opposing endwalls to aerodynamically interact with the fluid flow. The adjacent nozzles are configured to define a throat distribution exhibiting endwall throat decambering and pitchline throat overcambering.

Abstract: A system for installing and extracting a flowing water turbine below the surface of the water includes a flow inducer assembly for improving the conversation of the kinetic energy of a waterway to mechanical energy. The flow inducer assembly includes a nozzle that may be shaped as a cowling and a outlet diffuser. The system may be useful in a number of settings, including, but not limited to, streams, rivers, dams, ocean currents, or tidal areas that have continuous or semi-continuous water flow rates and windy environments.

Abstract: A gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in operational noise that is above a sensitive range for human hearing. A method and turbine module are also disclosed.

Abstract: A hybrid gas compressor has at least one rotor and shroud which define a compressor gas path extending from an inlet to an outlet. The compressor includes at least two compression stages and one diffusion stage between the inlet and outlet, the compression stages including respective circumferential arrays of blades extending from the rotor and the diffusion stage including a circumferential array of vanes between the compression stages. Blade aerodynamic loadings may be controlled, particularly in the last stage, to provide desired compression characteristics across the compressor. A bleed outlet is optionally located between the inlet and outlet for bleeding from the gas path.

Abstract: When a gas turbine is operated with inlet guide vanes (IGVs) closed during part load operation or the like, the degradation of aerodynamic performance and of reliability may potentially occur since the load on rear stage side vanes of a compressor increases. An object of the present invention is to suppress the degradation of the aerodynamic performance and of reliability of an axial compressor. The axial compressor includes a rotor; a plurality of rotor blade rows installed on the rotor; a casing located outside of the rotor blade rows; a plurality of stator vane rows installed on the casing; and exit guide vanes installed on the downstream side of a final stage stator vane row among the stator vane rows. An incidence angle of a flow toward the final stage stator vane row is equal to or below a limit line of an incidence operating range.

Abstract: A nozzle stage for a turbine engine includes two substantially cylindrical rings, respectively an inner ring and an outer ring, with, extending between them: vanes carried by a first one of the rings; vanes carried by the second ring; and spacer-forming vanes interconnecting the two rings; the vanes of the first and second rings being arranged in alternation.

Abstract: At the time of an operation, high-pressure air 8 fed through an inlet 6 passes a stator vane 4 within a duct 15, so as to adjust its flow, and is supplied to a tip turbine rotor vane 3. The tip turbine rotor vane 3 is supplied with the high-pressure air 8 from the exhaust side 17 toward the intake side 16, so as to drive an upper fan 2 and a lower fan 14 to rotate in the same direction. This can shorten the distance H from a rotation surface 12 of the upper fan 2 to the end part of a fan casing 1 on the intake side 16, and thus reduce an area where a negative pressure occurs when receiving a crosswind 9, thereby lowering an external force 11 caused by the negative pressure.

Abstract: A component for a gas turbine engine having an engine axis includes a rotor disk and a plurality of airfoils. The rotor disk comprises a web and a rim. The web has a first outer surface at least partially defining a plurality of holes and a plurality of slots. Each of the plurality of slots extends from a corresponding one of the plurality of holes and forms a first angle with the engine axis at the point of intersection with the corresponding one of the plurality of holes. The rim has a second outer surface also at least partially defining the plurality of slots. Each of the plurality of slots forms a second angle with the engine axis at the second outer surface, the second angle being different from the first angle. Each of the plurality of airfoils extends from the second outer surface.

Abstract: The present invention discloses an improved stator structure of a turbo molecular pump and a method for manufacturing the same. The stator comprises a plurality of stator blade assemblies, and each stator blade assembly comprising an inner shroud ring, an outer shroud ring and a plurality of stator blades, wherein the inner shroud ring, the outer shroud ring and the plurality of stator blades are integrated so that the rigidity of the stator is increased and the stator is not easily to be deformed; the method for manufacturing the stator comprises the steps of: laying a raw material on a computer numerical control (CNC) lathe; proceeding an outline treatment to a shape of each stator blade assembly by a turnery process; and shaping the plurality of stator blades of each stator blade assembly with a five-axis processing machine.

Abstract: A steam turbine has a stationary section, a turbine rotor, nozzle diaphragms, a steam passage section, a nozzle box and a sealing. The stationary section includes a casing. The turbine rotor includes moving blade stages. Each of the moving blade stages has turbine moving blades. Each of the nozzle diaphragms has turbine nozzles. The moving blade portions and the turbine nozzle portions constitute the steam passage. The nozzle box is held by the stationary section and arranged at an upstream side of the steam passage coaxially with the turbine rotor. The sealing divides a space between the turbine rotor and the casing into a first space provided at an inner side and a second space provided at an outer side of the nozzle box.

Abstract: Disclosed herein are turbines and turbine systems that may be used to generate power and/or electricity from flowing water or may be used in various other applications such as the pumping of water. One embodiment of the disclosed turbines includes a plurality of blades that may be connected to a turbine housing by a hinge so that the blades are movable between an active state, wherein the blade is configured to contribute to the rotational movement of the turbine, and a passive state, wherein the blade is configured to minimally resist the rotation of the turbine. Turbine blades are disclosed with specific features that more efficiently capture water flow power.

Abstract: Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially therefrom. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.

Abstract: A connection structure is applied to a serial fan assembly, which includes an upstream fan and a downstream fan. The upstream fan and the downstream fan have different sizes. The connection structure connects the upstream fan and the downstream fan so that the upstream fan and the downstream fan are arranged in series. The connection structure has a housing, a base and a plurality of ribs for connecting the base, and the housing is formed with an air guiding passage and a chamber. The upstream fan or the downstream fan is accommodated in the chamber or the air guiding passage is located between the upstream fan and the downstream fan.

Abstract: A rotor stage of an axial turbomachine compressor drum includes a symmetrical wall in rotation around the axis of rotation. The wall comprises a veil defining the general form of the drum and an annular area intended to support a row of vanes, the aforesaid area being integrally formed with the veil. This area has a particular form in that it has an exterior surface delimiting the fluid stream, which is elevated in relation to the veil. This area has a “U”-shape cross-section, of which the open part is directed towards the axis of rotation. The annular area comprises two wall parts, one upstream and one downstream, ensuring the connection with the veil and being used as stiffeners. They are preferably perpendicular to the axis of rotation or inclined in relation to the perpendicular. The junction of each upstream and downstream wall part with the central part of the support area is at the distance of the corresponding edge of the central part, so as to avoid certain stress concentrations.

Abstract: An axial flow machine having an asymmetrical air inlet and, downstream therefrom, a compressor having an inlet guide baffle composed of guide vanes is characterized in that at least some of the guide vanes of the inlet guide baffle have a vane profile and/or an angle of attack that deviate(s) from the remaining guide vanes. The inlet flow angle of the first compressor stage is hereby evened out circumferentially symmetrically. This is accomplished in that the different inlet angles resulting at various circumferential positions of the inlet guide baffle due to the asymmetry of the air inlet, are influenced by selective profiling and/or by selectively modifying the angle of incidence of individual guide vanes in such a way that a circumferentially symmetrical outflow angle from the inlet vane ring results.

Abstract: A serial axial fan unit includes a first axial fan arranged to rotate about a central axis, a flow control device connected to the first axial fan along the central axis, and a second axial fan connected to the flow control device along the central axis. The flow control device preferably includes a wind tunnel portion, a base portion, and a plurality of flow control vanes. A flow of air caused by rotation of first blades has a whirl velocity component in substantially the same direction as the rotation direction thereof. This whirl velocity component is converted to a velocity component in a direction parallel or substantially parallel to the central axis by interference of first stationary vanes. The above arrangement provides an improvement in air volume characteristics of a serial axial fan unit including two axial fans arranged in series.

Abstract: A heating apparatus and a system that utilize friction to generate thermal energy. The heating apparatus comprises a housing unit, a plurality of heating chambers for generating heat, an actuating unit, a shaft; and at least one blade unit. Each heating chamber comprises a stationary disc member, a rotating disc member, and a medium disposed between the stationary disc member and the rotating disc member. The actuating unit drives the rotating disc member in the heating chamber to generate thermal energy by friction among the stationary disc member, the rotating disc member, and the medium. Thermal energy generation is controlled by rotating speed, diameter of the disc member, and contact pressure between the rotating disc member and the stationary disc member. Tube members can also be used in the heating chambers.

Abstract: High-temperature steam at 620° C. or higher is introduced to a reheat steam turbine 100, and a turbine rotor 113 of the reheat steam turbine 100 includes: a high-temperature turbine rotor constituent part 113a positioned in an area extending from a nozzle 114a on a first stage to a moving blade 115a on a stage where temperature of the steam becomes 550° C. and made of a corrosion and heat resistant material; and low-temperature turbine rotor constituent parts 113b connected to and sandwiching the high-temperature turbine rotor constituent part 113a and made of a material different from the material of the high-temperature turbine rotor constituent part 113a.