Abstract: Aspects of the invention are directed to a system for improving engine performance by reducing vane tip clearances in the compressor section of a turbine engine. According to aspects of the invention, an abrasive material can be attached to a rotor disc. Thus, if a vane tip contacts the rotor disc during engine operation, the vane tip is worn away by the abrasive material. The system can reduce the risk of substantial component damage resulting from a vane tip rubbing event. The abrasive material can be provided in the form of an insert that can be removably attached to the rotor disc. Thus, the insert can be readily removed and replaced when necessary.

Abstract: A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, circumferentially mixing the cooling air in a plenum defined within the leading edge to substantially uniformly distribute the cooling air throughout the gap, and directing the cooling air in the gap through at least one cooling hole formed between the plenum and the inner surface.

Abstract: According to the invention, the stator is made by radially assembling together at least two stator sectors (21, 22) about a rotor (18). Each stator sector (21, 22) comprises a peripheral shell sector (24, 25) provided with internal annular grooves (24a-24j) in which stator vane sectors (26a-26j) are engaged individually. This facilitates assembly and provision of subassemblies constituting the turbomolecular pump.

Abstract: An 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: The invention relates to a rotor for a non-positive-displacement machine provided with a hollow shaft, which is arranged coaxial to the rotation axis, is supported, on both sides and on the face, on two axially opposed sections of the rotor, and which encloses an inner hollow space. In order to provide a rotor for a non-positive-displacement machine, which has a higher serviceable life and is less susceptible to mechanical defects, the invention provides that the hollow shaft, in the axial direction of the rotor, is formed from a number of adjoining rings, and the rings are outwardly sealed against one another an with regard to the sections of the hollow space. Each ring has an I-shaped cross-section and the web of the I shape extends in the radial direction of the rotor.

Abstract: The invention relates to a compressor, which is axially flowed through, for a gas turbine having an axially displaceable rotor. An annular flow channel, which narrows in an axial direction, is formed between a rotationally fixed outer delimiting surface and an inner delimiting surface on the rotor. A stationary ring comprised of guide profiles and at least one ring comprised of moving profiles attached to the rotor are placed inside said annular flow channel. The end of each moving or guide blade is located opposite an axial section of one of both delimiting surfaces while forming a radial gap. The aim of the invention is to provide a non-positive-displacement machine having an axially displaceable rotor whose velocity losses are at least not increased during an axial displacement of the rotor.

Abstract: An axial flow fan unit includes an intake side axial flow fan, an exhaust side axial flow fan, and at least one intermediate axial flow fan. Each of the axial flow fans includes an impeller having blades rotatable about a central rotation axis, a motor arranged to rotate the intake side impeller, and a housing having an inner circumferential surface that surrounds the impeller. The rotational direction of the impeller in the intermediate axial flow fan is different from that of the impellers adjacent thereto.

Abstract: Disclosed herein is a rotor assembly for a steam turbine. The steam turbine includes a retention portion having a stacked rotor section. The steam turbine further includes a first shaft end disposed at a first end of the retention portion. The steam turbine yet further includes a second shaft end disposed at a second end of the retention portion that is opposite to the first end of the retention portion.

Abstract: A vapor compressor for use with a distillation system, the compressor including a housing defining an interior volume. The housing includes an inlet and an outlet. A shaft has a first end and a second end and extends along a longitudinal axis of the housing. A first compression stage includes a first impeller and a first stator, the first impeller including a first plurality of impeller blades having a first dimension. The first stator includes a first plurality of stator blades having a second dimension. A second compression stage includes a second impeller and a second stator, the second impeller including a second plurality of impeller blades having a third dimension. The second stator includes a second plurality of stator blades having a fourth dimension. The first dimension and the third dimension are measured along corresponding portions of the first plurality of impeller blades and the second plurality of impeller blades, and the first dimension is greater than the third dimension.

Abstract: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity are provided. In this regard, a representative turbine stage for a gas turbine engine includes a first set of rotatable blades operative to be positioned downstream of and adjacent to a first set of vanes, a number of blades of the first set of blades being less than a number of vanes of the first set of vanes.

Abstract: Disclosed herein is a stator assembly for a steam turbine. The stator assembly includes a stacked stator section and a retention device. The stacked stator section has a plurality of adjacently disposed stator plates. The retention device retains the adjacent stator plates proximate to each other.

Abstract: A compression and vacuum-producing machine includes a housing, at least one rotating disk having a plurality of blades rotationally supported within the housing, and at least one stationary disk having a plurality of blades fixedly attached to the housing. A drive shaft includes a generally tapered surface and rotatably drives the rotating disks to increase the energy of a fluid stream disposed within the housing. The compression machine includes a transmission in mechanical communication with the drive shaft to convert a rotational input to a desired rotational speed and drive the shaft at the desired speed.

Abstract: An axial turbine includes a plurality of stages each comprising a plurality of stationary blades arranged in a row along the turbine circumferential direction and a plurality of moving blades in a row parallel to the stationary blades, each of the moving blade being disposed downstream of a respective one of the corresponding stationary blade in a flow direction of a working fluid so as to be opposed to the corresponding stationary blade. Herein, each of the stationary blades is formed so that the intersection line between the outer peripheral portion of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer peripheral portion of the stationary blade and that is parallel to the turbine central axis.

Abstract: A gas turbine engine airfoil has a platform cooling scheme including an impingement hole for directing cooling air against an undersurface of the airfoil platform.

Abstract: A gas turbine engine is provided with a seal disk that rotates in a closely spaced relationship to a stationary vane. The stationary vane is provided with an abradable tip. The seal disk is provided with alternating portions of a relatively insulating material and a relatively abrasive material. The insulating material can assist the seal disk in resisting thermal expansion. The abrasive material abrades the abradable tip of the stationary vane, ensuring a close, rotating fit.

Abstract: A hydrocarbon well pump has impellers and diffusers configured with inner and outer sections. The central section contains impeller passages configured for pumping liquid. The outer section contains turbine blades for compressing gas. A cylindrical sidewall separates the two sections. A driven shaft rotates the central and outer sections in unison.

Abstract: Disclosed herein is a rotor assembly for a steam turbine including a stacked rotor section having rotor plates. The rotor plates include a main body portion having a plate shape and a first axial face and a second axial face opposite to the first axial face. The rotor plates also include an airfoil base surface at an outer radial edge of the main body portion. The rotor plates further include buckets which extend radially outward from the airfoil base surface. And the rotor plates yet further include a seal disposed to prevent steam exposure to the first and second axial faces.

Abstract: An electric turbine compressor fan for hybrid propulsion wherein the compressor contains one or more rotor stages (compressor and diffuser), each being driven by one or more electric ring motors, such that the compressor rotor stages are designed and tuned more precisely to the compression ratio to be attained within the turbine design operating characeristics, thrust requirements and flight envelope.

Abstract: A turbine, e.g., a high pressure (HP) turbine, has a conventional drum-type structure with reaction turbine stages. A preceding or following turbine, e.g. an intermediate pressure (IP) turbine, on a common axis and on the same steam path, has rotor drum which carries an annular row of moving blades having root portions held within a slot in the periphery of the drum. A turbine casing surrounds the drum and carries a static blade assembly with an annular row of static blades which, together with the annular row of moving blades, constitutes a modified turbine stage. The static blade assembly has a radially inner static ring with a radially inner side confronting the periphery of the drum. A seal acts between the inner static ring and the rotor.

Abstract: One turbine, e.g. a high pressure (HP) turbine, has a conventional diaphragm and disc structure with impulse turbine stages. A preceding or following turbine, e.g. an intermediate (IP) turbine, on a common axis and on the same steam path, has a rotor drum which carries an annular row of moving blades having root portions held within a slot in the periphery of the drum. A turbine casing surrounds the drum and carries a static blade assembly with an annular row of static blades which, together with the annular row of moving blades, constitutes a modified turbine stage. The static blade assembly has a radially inner static ring with a radially inner side confronting the periphery of the drum. A seal acts between the inner static ring and the rotor.

Abstract: A fan device capable of increasing air pressure and air supply includes a frame, a first blade wheel, a second blade wheel and a guide flow part. The frame is a hollow casing to define a flow passage with a first air port and a second air port available for air passing through. The guide flow part is held with a support in the flow passage and a driving device is received in the support. The first blade wheel with first fan blades and the second blade wheel with second fan blades are disposed in the flow passage next to the support for being driven by the driving device. The number of the first fan blades is more than that of the second fan blades. Once the first and second fan wheels are in operation, air induced by the fan wheels is guided by the guide flow part and air pressure and air supply of the fan system are increased substantively due to number of the first fan blades being greater than that of the second fan blades.

Abstract: A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.

Abstract: Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.

Abstract: A gas turbine section of a gas turbine engine, including a first stage turbine disk, a forward outer seal carried on the turbine disk and a forward shaft cooperating with the first stage turbine disk for transmitting torque generated by the turbine section to a compressor section of the engine. The forward shaft intersects the first stage turbine disk at a non-perpendicular angle in the area of the disk hub for directing sufficient hot air against the disk hub to balance the thermal response rate of the disk hub to the thermal expansion rate of the forward outer seal.

Abstract: An axial fan unit includes two or more impellers accommodated in a housing. Each impeller has a plurality of blades disposed about a center axis and is rotated by an associated motor. The rotation of the impellers creates a flow of air generally flowing along the center axis. A plurality of ribs are disposed between the impellers and connected to the housing. The ribs support an associated motor. At least one of an air-inlet side edge and an air-outlet side edge of each rib is inclined with respect to a direction that is perpendicular or substantially perpendicular to the center axis, such that it gets closer to one of an air-inlet side end and an air-outlet side end of the axial fan unit as it moves away from the center axis.

Abstract: A gas turbine engine rotor stack may be engineered or reengineered to include one or more longitudinally outwardly concave spacers. The spacers may provide a longitudinal compression force that increases with rotational speed.

Abstract: A heat dissipating device includes an outer frame, a first rotor, a base, a second rotor and a driving device. The first rotor comprises a shaft, a first hub and a plurality of first rotor blades disposed around the first hub. The base is disposed in the outer frame. The second rotor comprises a plurality of second rotor blades, coupled to the shaft of the first rotor and disposed next to the first rotor. The driving device is supported by the base for driving the first rotor and the second rotor.

Abstract: An axial flow turbine provided with a stage composed of a turbine nozzle and a turbine rotor blade arranged in an axial flow direction. Both end portions of a nozzle blade of the turbine nozzle are supported by a diaphragm inner ring and a diaphragm outer ring, and a flow passage is formed to have its diameter expanded from an upstream stage to a downstream stage. In such axial flow turbine, trailing edges at ends of the nozzle blade supported by the diaphragm inner ring and the diaphragm outer ring are curved as a curvature to an outlet side, and an intermediate portion between the trailing edges is formed to be straight.

Abstract: A turbomolecular pump includes a plurality of rotor and stator discs arranged alternatively one behind another and producing together a pumping effect, a plurality of spacer rings for retaining the stator discs at a distance from each other; and connection elements for fixedly connecting adjacent spacer rings with each other, so that the spacer rings together provide for securing and centering of the stator discs, taking over the function of a pump housing that is eliminated.

Abstract: The steampath for a steam turbine includes stacked stator rings each mounting inwardly directed nozzles and stacked rotor wheels each mounting outwardly directed buckets mounting blades. By alternately stacking the stator rings and rotor wheels, the nozzles and buckets of the various stages are interdigitated to form a steampath. Each bucket includes a blade and a root received in a generally complementary shaped groove on a wheel.

Abstract: The invention relates to a rotor for a turbomachine, in particular a low-pressure turbine rotor for a gas turbine, having at least one stage, each stage comprising a rotor disk having rotor blades attached to the rotor disk, and the rotor disk of each stage being removably connected either to oppositely situated rotor disks of adjoining stages or to a rotor connection of a rotor shaft by at least one respective attachments. According to the invention, the, or each of the, attachment means extends through the rotor disk of at least one stage, whereby the, or each of the, attachment means is guided with radial play into at least one borehole passing through the respective rotor disk, so that an interior borehole surface is not subjected to load or force.

Abstract: The invention relates to a hybrid cycle HP compressor (104) for a turbine engine, comprising in particular a first rotor wheel (16), a first rectifier (118) and a second rotor wheel (20), as well as a separation slot (22) fitted between the first rectifier and the second rotor wheel in order to supply the turbine engine with a secondary air flux. According to the invention, the first rectifier is a double grid rectifier comprising a grid of vanes upstream (30) as well as a grid of vanes downstream (34), these upstream and downstream vane grids being associated respectively with variable setting systems upstream and downstream (38,40) controlled in autonomous manner.

Abstract: A turbine nozzle for a gas turbine engine includes a nozzle segment having an airfoil-shaped vane with a root, a tip, a leading edge, a trailing edge and opposed curved pressure and suction sides. An arcuate inner band segment is attached to the root of the vane. The inner band segment includes an inner flowpath surface bounded at forward and aft ends thereof by a forward-facing surface and an aft-facing surface, respectively. A convex curved blended corner is formed between the inner flowpath surface and the aft-facing surface.

Abstract: A steam turbine power generation system, comprising a high-pressure turbine, an intermediate-pressure turbine and a low-pressure turbine, wherein the intermediate-pressure turbine has an inlet steam temperature of 650–720° C., and the low-pressure turbine has an inlet steam temperature of 410–430° C.; and a low-pressure turbine rotor of the low-pressure turbine is made of a heat-resisting steel which contains, in weight percent, C: 0.28 or less, Si: 0.03 or less, Mn: 0.05 or less, Cr: 1.5 to 2.0, V: 0.07 to 0.15, Mo: 0.25 to 0.5, Ni: 3.25 to 4.0, and the balance of Fe, unavoidable impurities and unavoidable gases, and the unavoidable impurities contain, in weight percent, P: 0.004 or less, S: 0.002 or less, Sn: 0.01 or less, As: 0.008 or less, Sb: 0.005 or less, Al: 0.008 or less and Cu: 0.1 or less.

Abstract: A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The spacers may provide a longitudinal compression force that increases with rotational speed.

Abstract: In an electronic system, a method for operating a cooling fan comprises rotating an impeller about a rotational axis and detecting fan failure. The impeller is spatially expanded in response to the detected fan failure whereby airflow through the failed fan is blocked.

Abstract: Gas flow is redirected by a feature disposed on a trailing edge of at least one segment of a peripheral gas path defining surface to improve alignment with a downstream portion of the gas path.

Abstract: A rotor (10) for a thermal machine, in particular a steam or gas turbine, includes a plurality of rotor disks (12, 13, 14) which are arranged one behind the other in the rotor axis (11) and are welded to one another, at least one first rotor disk (13), which is arranged in a section of the rotor (10) which is subject to particularly high thermal loads, including a nickel-base alloy which is able to withstand high temperatures and is welded to at least one second, adjacent rotor disk (12, 14), which includes a steel which is able to withstand high temperatures.

Abstract: In an axial compressor (10), in particular for a gas turbine, with a plurality of stages (ST1, . . . , ST5) which are arranged one behind the other between a compressor inlet (14) and a compressor outlet (15) and include in each case at least one ring of rotor blades (R) and one ring of stator blades (S), a substantial improvement is achieved in that, to minimize the losses in the individual stages (ST1, . . . , ST5), during operation of the axial compressor (10) in which water is injected into the compressor inlet (14) and evaporates on its way though the compressor (10) (what is known as “wet compression”), the variations, caused by the injected water, in the flow velocities (c1, cm1, w1) of the medium flowing though the compressor (10) are largely compensated by a controlled change in the geometry of the blades (R, S).

Abstract: An axial-flow fan with double impellers is provided that can produce a larger amount of air and a higher static pressure than can be achieved with conventional fans. The axial-flow fan with double impellers has a first axial-flow fan unit and a second axial-flow fan unit. The first axial-flow fan unit includes a first case, a first impeller and a plurality of webs that fix a first motor to the first case. The second axial-flow fan unit includes a second case, a second impeller and a plurality of webs that fix a second motor to the second case. The first case and the second case are coupled together to form a housing. The webs of the first axial-flow fan unit and the webs of the second axial-flow fan unit are combined together to form a plurality of stationary webs arranged in the housing. The number of front blades provided at the first impeller is set to five, the number of stationary blades is set to three, and the number of rear blades provided at the second impeller is set to four.

Abstract: A method for assembling a fan assembly for a gas turbine engine includes coupling a plurality of fan blades in a row to a rotor disk, wherein each fan blade includes an airfoil having a first sidewall and a second sidewall connected together at a leading edge and a trailing edge, and wherein each airfoil extends radially between a root and a tip. The method also includes coupling at least one shroud to at least one of the plurality of rows of fan blades, such that the shroud is coupled to at least one fan blade tip extending within the same row of fan blades, and coupling at least one row of rotor blades to the shroud, such that the rotor blades extend radially outward from the shroud.

Abstract: A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. The spacers may provide a longitudinal compression force that increases with rotational speed.

Abstract: Disclosed is a composite heat-dissipating system and its used fan guard which can impart a supercharging function to the heat-dissipating fans of the composite heat-dissipating system for efficient heat dissipation and reduces the noise generated when the heat-dissipating fans are operated. The fan guard includes a frame and a set of guard blades arranged inside and fixed onto an inner surface of the frame. The fan guard can be arranged upstream or downstream of the rotor blades of the heat-dissipating fans and assembled with the heat-dissipating fans in series or in parallel to supercharge the airflow out of the heat-dissipating fans.

Abstract: A fluid-flow machine (turbomachine) includes at least one rotor equipped with blades and at least one stator equipped with vanes, the rotor being supported in a casing by means of a rotating shaft. A form of annulus is provided whose cross-sectional area in a stage consisting of at least one rotor and one stator results in a rotor-stator contraction ratio QRS which satisfies the equation: [0.2+(KT?0.45)0.1]<QRS<3.0, where KT is the total-stage contraction.

Abstract: A first stage rotor disk (50a) and a connecting member (30) on the compressor side are fixed by a spindle bolt (20). The spindle bolt (20) is covered with a tubular member (100), between the first stage rotor disk (50a) and the connecting member (30) on the compressor side.

Abstract: A wedge-like nozzle radial loading pin, preferably formed from steel, that contacts the bottom of a reaction nozzle along a graduated, that is inclined or stepped, surface. This contact will secure the reaction nozzle radially inward against the retaining surface of the carrier dovetail with sufficient force to maintain the designed airfoil pre-twist.

Abstract: A method facilitates assembling a seal assembly for a gas turbine engine rotor assembly. The method comprises coupling a disk retainer to a first stage disk, and coupling an interstage seal assembly including an outer shell within the rotor assembly such that a downstream arm extending from the outer shell engages a second stage disk while an upstream arm extending from the outer shell engages the disk retainer.

Abstract: An object of the present invention is to reduce the adverse effect of interference between stationary blades and moving blades on the performance of an axial-flow turbine and to provide a high-performance turbine stage. Each of the stationary blades has a trailing edge convex toward a face side with respect to a radial line radially extending from the axis of the rotor shaft, and the each of the moving blades has a blade center-of-gravity line convex toward the face side with respect to a radial line radially extending from the axis of the rotor shaft, and shapes of the stationary blades and the moving blades meet conditions expressed by: 1<?nr/?nt 1<?bt/?br where, ?nt and ?nr are angles between the stationary blade tip and the stationary blade root, and radial lines, and ?bt and ?br are angles between the blade center-of-gravity line of the moving blade at the tip of the same, and the blade center-of-gravity line of the moving blade at the tip of the moving blade, and radial lines.

Abstract: A vacuum pump adopts a positioning structure in which stator blades and spacers are arranged in the radial direction of a pump case by the contact between the outer peripheries portion of the stator blades and the inner periphery portion of the pump case and the contact between the outer periphery portions of the spacers and the inner periphery portion of the pump case. Accordingly, the spacer interposed between the upper and lower stator blades can have a simplified shape that serves a function of only setting the spacing between the stator blades to a prescribed length, thus decreasing the number of steps and costs of processing the spacer, and accordingly reducing the costs of the entire vacuum pump.