Abstract: A heat dissipating fan structure of a dual motor includes: a base device, having a fan base, and the fan base having a fan motor; a fan, connected and rotated by the fan motor, and the fan having a plurality of vanes; a support frame device, installed at the fan base, and having a frame-fan motor; a frame-fan device, connected and rotated by the frame-fan motor, and having a frame-fan frame, and a plurality wing plates disposed around the frame-fan frame, and the wing plates being disposed around the external periphery of the fan and perpendicular to the vane, so that the plurality wing plates on the frame-fan base can produce an auxiliary airflow to increase the airflow of the fan and give a better heat dissipating effect.

Abstract: A damping system for damping the vibrations of a blade union is provided. The blades arranged in a neighboring manner are coupled to one another via a coupling element, wherein the coupling element is arranged fixed in a first blade and extends into the second blade, wherein the coupling element is not arranged in the second blade but rather solely contacts there such that, as a consequence of centrifugal forces, a free end of the coupling element presses against the second blade and a friction force thus occurs, leading to an energy dissipation and vibrations being thus damped.

Abstract: A turbine bucket that may include an airfoil having a tip shroud, the tip shroud having an edge; wherein the edge has a profile substantially in accordance with values of X and Y in a Cartesian coordinate system set forth in Table 1 at points 1-14, wherein X and Y represent distances that may be proportionally scaled by a common multiplier which, once scaled and connected, define the profile of the edge of the tip shroud.

Abstract: A turbine blade that may include a tip shroud, the tip shroud having one or more cooling cavities defined therein, an airfoil, the airfoil having at least one coolant passage defined therein, and a plurality of exit apertures defined through an outer wall of at least one of the cooling cavities that, in use, may allow a pressurized coolant to exit at least one of the cooling cavities. The coolant passage may extend through the airfoil such that the coolant passage is in fluid communication with the cooling cavity. And, the plurality of exit apertures may include at least one round exit aperture and at least one non-round exit aperture.

Abstract: A turbine blade including a root section at an end of the turbine blade, a first airfoil section adjacent to the root section, and a tip section adjacent to the airfoil section and including a material block that is incongruous with the airfoil section. A midspan section may also include a material block. Each material block can be selectively machined to customize the length of the turbine blade and the position of a tip shroud connection or midspan connection. The turbine blade can be sized for retrofitting last stage blades of older turbines. A radial position of the root mounts for the turbine blade may also be adjusted to provide further customization.

Abstract: A passive fan includes a frame, at least one impeller and at least one driving device. The impeller is disposed in the frame. The driving device is disposed in the body of the frame and separated from the impeller, and drives the impeller to rotate. The driving device is an independent motor, a driver, a rotating wheel or a driving gear.

Abstract: A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a skewed axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. The cover comprises a first flat section, a second flat section, and a depression section located laterally between the first flat section and second flat section. The depression section is located below the first flat section at a first end where the first flat section and depression section are contiguous. The depression section rises above to the second flat section at a second end where the second flat section and depression section are contiguous. The second flat section is raised above the first flat section.

Abstract: A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a straight axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. The cover has a first portion that overhangs a pressure side of the airfoil portion and a second portion that overhangs a suction side of the airfoil portion. The cover is positioned at an angle relative to the tip section, wherein the angle ranges from about 15 degrees to about 35 degrees.

Abstract: A turbine bucket includes a bucket airfoil having a tip shroud with a leading edge comprising two scalloped faces and a trailing edge comprising a third scalloped face defining leading and trailing edge profiles substantially in accordance with Cartesian coordinate values of X and Y as points 1-41 set forth in Table I. The X and Y values are distances in inches which, when respective points are connected by smooth, continuing arcs define the leading and trailing edge tip shroud scalloped profiles. The tip shroud further has first and second, upper and lower, Z form edge profiles substantially in accordance with Cartesian coordinate values of X and Y as points 42-59 and 60-77, respectively of Table II.

Abstract: The blower designed particularly for fitting in a chamber furnace has the hub of the rotor wheel in the shape of a solid of revolution with its slant height described by n degree polynomial and its Dp2 outlet diameter greater than Dp1 inlet diameter and the outward diameter of the axial and radial rotor wheel with spatially shaped blades monotonically increasing towards the flow from D1z inlet diameter to D2z outlet diameter.

Abstract: The invention relates to a turbine blade with a cover plate shaped onto the pan of the blade. The aim of the invention is to provide a turbine blade of this type that, while having a high level of efficiency, is designed for a particularly reliable and safe operation in a turbine, particularly of a steam turbine. To this end, the invention provides that a protective layer made on an alternative material is applied to the surface of the cover plate facing away from the pan of the blade. The friction behavior with regard to a turbine component, particularly a sealing strip, which is opposite the protective layer, can be specifically influenced whereby enabling favorable emergency running properties to be provided in the event of rubbing.

Abstract: A free-tipped axial fan assembly has a skew distribution which reduces fan noise while minimizing radial tip deflection. The difference between the maximum value of leading-edge skew and the value of leading-edge skew at the fan radius is at least 10 degrees. The ratio of the difference of the leading-edge skew between the maximum value and the value at the fan radius to the difference of the trailing-edge skew between the maximum value and the value at the fan radius is at least 2.5.

Abstract: A hub is supported rotatably about an axis of rotation, and the diameter thereof increases from upstream to downstream sides along a fluid flow. A plurality of impeller blades extend radially outward from an outer circumferential surface of the hub. A shroud is formed in a cylindrical shape whose diameter increases from the upstream to downstream sides along the fluid flow and joins outer circumferential ends of the plurality of impeller blades. The impeller blades are composed of upstream blade segments and downstream blade segments bonded at a bonding surface extending in a direction substantially perpendicular to the axis of rotation. The upstream blade segments are integral with at least a portion of the shroud, and the downstream blade segments are integral with at least a portion of the hub. This improves the reliability and performance of an impeller and a compressor.

Abstract: A turbine bucket including a bucket airfoil having a hollow tip shroud, the hollow tip shroud having a hollow core having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, in inches, wherein the shape of the core is defined by the cloud of points listed which are distributed around each surface of the shroud, and the complete hollow portion of the tip shroud could be constructed by defining smooth sheet surfaces through the listed points.

Abstract: A turbine for a hydroelectric power plant intended to equip a water stream at the level of a very low head lower than 10 meters, and preferably from 1 to 5 meters, comprising a helix-shaped wheel, the ratio between the kinetic energy of the water flow coming out of the wheel and the potential energy of the head being smaller than 20%.

Abstract: The present application further describes a turbine blade that may include an airfoil, a tip shroud that is positioned at one end of the turbine blade, a coolant passage that extends through the airfoil to the tip shroud, and a continuous cooling cavity that is defined within the tip shroud and that is in fluid communication with the coolant passage. The continuous cooling cavity may form a labyrinth cooling circuit within the tip shroud.

Abstract: A turbine blade that may include a tip shroud that comprises one or more cooling cavities formed therein. At least one of the cooling cavities may include a plurality of ribs and a first interior wall that generally opposes a second interior wall across the cooling cavity. The plurality of ribs may be configured such that some of the ribs originate at the first interior wall of the cooling cavity and extend toward the second interior wall of the cooling cavity and some of the ribs originate at the second interior wall of the cooling cavity and extend toward the first interior wall of the cooling cavity. The ribs that originate at the first interior wall of the cooling cavity and extend toward the second interior wall of the cooling cavity may be oriented and sized so that at least some of the ribs extend across at least a majority of the distance across the cooling cavity.

Abstract: An impeller is provided that may be used in compressors or turbines. In another aspect of the present invention, a fiber or a bundle of fibers is woven to form at least two blades of an impeller. Yet another aspect of the present invention employs a peripheral component woven around impeller blades. An additional conductive fiber or bundle of fibers is woven into the impeller in a further aspect of the present invention. Moreover, an aspect of the present invention provides a chilling system that includes at least one compressor, at least one wave rotor, and a refrigerant.

Abstract: A method of repairing a damaged notch fillet radius of a turbine blade shroud includes a replacement notch fillet radius and a hardface nugget. The damaged notch fillet radius is blended out and a hardface structure positioned proximate the damaged notch fillet radius is removed. A replacement notch fillet radius is formed with weld filler and the hardface nugget is welded to at least a portion of the replacement notch fillet radius.

Abstract: The Thermal Airfoil Turbine, as it is conceived, is used to generate mechanical energy, from the thermal energy of an airflow, the energy applied by the airflow to the airfoils in the Thermal Airfoil Turbine, is less by a large factor, usually ten or more than the power generated when the Thermal Airfoil Turbine spins at a certain rotational velocity. This generated power comes from the thermal energy lost, by the airflow passing through the Thermal Airfoil Turbine. It must be emphasized that the difference between this Generator and others that uses airflow, is that the others work with the kinetic energy of the airflow, reducing its velocity so to use it in producing power, on the contrary the Thermal Airfoil Turbine intends not to reduce this velocity at all, producing its power from transforming the thermal energy of the airflow into mechanical energy.

Abstract: An improved coaxial rotor assembly for a helicopter includes an upper rotor system having a multiple of upper rotor blades each having outer tips and mounted on and extending outwards from a central rotor shaft and a lower rotor system having a multiple of lower rotor blades each having outer tips and mounted on and extending outwards from the central rotor shaft with the upper rotor system spaced an axial distance from the lower rotor system on the central rotor shaft. A rotor blade support ring extends circumferentially around each of the upper and lower rotor systems which movably engages and supports the outer tips of the upper and lower rotor blades in spaced apart relation such that the upper and lower rotor systems rotate in opposite directions and the rotor blade support ring means prevents contact between the upper and lower rotor systems during operation thereof.

Abstract: A two blade row inducer for a low pressure pump in a turbopump of a rocket engine. The inducer includes a first set of blades and a second set of blades or partial blades in which the partial set of blades is covered with a shroud and the shroud includes a row of turbine blades extending outward to form a turbine to drive the inducer. The first set of blades is spiral or screw thread blades that end just upstream from the leading edges of the second set of blades covered with the shroud. In another embodiment, the screw thread blades can extend toward the aft end of the inducer and in-between adjacent partial blades in which the shroud also covers the aft ends of the screw thread blades. A second fluid reacts with the turbine blades to rotate the inducer and pump the first fluid.

Abstract: An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.

Abstract: A centrifugal blower includes a casing, a motor fixed in the casing, a fan structure, and an anti-leakage element. The casing has a top portion having an inlet, a bottom portion, and a side wall respectively connecting the top and bottom portions and having an outlet. The fan structure disposed in the casing and driven by the motor has a body connected to the motor and blades surrounding the body and being connected to the body, and rotates about an axis in a first rotation direction. The anti-leakage element extends from at least part of an edge of the inlet to an interior of the casing, partially covers parts of the blades, and extends from neighborhood of the outlet in a second rotation direction against the first rotation direction. A range of the anti-leakage element extending to the interior of the casing is gradually reduced along the second rotation direction.

Abstract: In one embodiment, a turbine bucket includes: a tip shroud with a front edge and a following edge, the front edge and the following edge including a Z-Notch profile according to the Cartesian coordinate values of X, Y and Z set forth in Table I; wherein the coordinate values are dimensional values representing a distance from an origin of an internal coordinate system for the bucket; and wherein when the X and Y values are connected by smooth continuing arcs, the Z-Notch profile is defined. A turbine is provided.

Abstract: A fan-turbine rotor assembly for a tip turbine engine includes an outer periphery scalloped by a multitude of elongated openings which define an inducer receipt section to receive an inducer section and a hollow fan blade section. Each fan blade section includes a turbine section which extends from a diffuser section.

Abstract: A method of making a fan (20) includes making a subassembly (48) comprising a backplate (22) and a plurality of blades (24) extending from the backplate (22), making a fan shroud (26), positioning the fan shroud (26) adjacent to the blades (24) of the subassembly (48), providing ferromagnetic particles at a first weld location, and directing electromagnetic energy toward the ferromagnetic particles at the first weld location to melt surrounding material and structurally join the fan shroud (26) and at least one of the blades (24).

Abstract: The present invention broadly comprises a torque converter including a cover arranged to accept torque from a drive unit and an impeller. The cover and the impeller are joined by a crimped connection. In some aspects, the converter includes a sealing element disposed between the cover and the impeller and the sealing element is selected from the group consisting of an o-ring and a gasket. In some aspects, the cover is a cast piece. In some aspects, the cover is formed by a process selected from the group consisting of: molding, compression molding, and pressed metal forming. In some aspects, the cover is a stamped metal piece. The present invention also broadly comprises a torque converter including a cover, an impeller, and an induction brazed connection joining the cover and impeller. In some aspects, the cover further comprises axially disposed fingers engaged with the impeller.

Abstract: A propulsor apparatus for a mobile platform, for example an aircraft is provided. The propulsor apparatus includes an aerodynamically shaped propeller duct that houses at least a portion of a turboprop engine, and fully houses a propeller driven by the engine. Inside the propeller duct is a circumferential ring that closely surrounds the propeller such that only a small clearance is provided between the outermost tips of the propeller blades and an inner surface of the circumferential ring. The circumferential ring includes sound deadening material that attenuates noise generated by the tip vortices created at the outermost tips of the propeller blades. The propeller duct and circumferential ring are supported by a plurality of structural rods that couple to structure of the mobile platform, for example to the spars within a wing of an aircraft. The apparatus and method significantly reduces the noise associated with a turboprop engine.

Abstract: Two embodiments of a portable fan for use in the cup holder of a recreational vehicle such as a golf cart are shown and described. In the first embodiment, a bottle-shaped body has a cup-shaped lower portion separated from the body by a shoulder which acts as a limit stop when inserting the base into a cup holder. A shrouded impeller is pivotally connected to the top of the base and exhibits an integral carry handle. The entire structure is made of a suitable plastic such as high density polyethylene. In the second embodiment, the impeller is located intervally of the body for safety and a bell-shaped outlet directs air through a diffuser with circular louvers.

Abstract: An axial tip turbine driven pump in which a first fluid pumped by an inducer is driven by a second fluid that reacts with a turbine blade extending from a shroud on the inducer. The inducer includes a set of screw thread blades and a second set of partial blades that are covered by a shroud in the aft section of the inducer. A row of turbine blades extends from the shroud and into a manifold that forms the outer casing for the pump. The fluid flow through the manifold reacts with the turbine blades and drives the inducer to pump the fluid from the inlet and through guide vanes downstream from the inducer. The fluid passing through the turbine blades is collected in an outlet collector manifold and discharged into the fluid flowing through the guide vanes. The inducer with the turbine blades is rotatably supported within the housing formed by the guide vane support member and the manifold casing. The swirl flow direction of the turbine blades is opposite to that of the swirl flow in the inducer.

Abstract: A fan assembly comprises a hub and fan blades. The hub includes a plurality of sockets configured to receive complementary mounting blocks of the fan blades. The mounting blocks each include at least one tapered shoulder portion. The mounting blocks are each tapered along three dimensions. Each mounting block comprises a rear face seated against a complementary rear face of the corresponding socket and a front face that is exposed relative to the hub. A cap secures the fan blades to the hub. The fan assembly may also include one or more shrouds positioned about the fan blades. The one or more shrouds may be substantially straight cylinders, may be flared or bell-shaped, may comprise a cage, may have any other suitable configuration, or may be omitted altogether.

Abstract: The present invention provides an axial fan including a hub adapted for rotation about a central axis and a plurality of blades extending radially outwardly from the hub and arranged about the central axis. Each of the blades includes a root, a tip, a leading edge between the root and the tip, and a trailing edge between the root and the tip. Each of the blades defines a blade radius between the blade tips and the central axis. Each of the blades defines a decreasing skew angle within the outer 20% of the blade radius. The ratio of blade pitch to average blade pitch increases from a lowest value to a highest value within the outer 20% of the blade radius. The highest value is about 30% to about 75% greater than the lowest value.

Abstract: The invention relates to a radial fan impeller (1), in particular for using in gas fans with a steep fan characteristic curve, with the following features: with a plurality of blades (2) distributed around the periphery; viewed in the radial direction, the blades (2) extend from an inner inlet region (4) to an outer discharge region (6); the blades (2) extend axially, i.e.

Abstract: Injection molded ring fan embodiments and methods for making them. The methods influence material flow during the injection molding process such that a major portion of the materials flowing in opposite directions in the outer rings preferably flow past one another, intermix in a swirling relationship, and/or collide at an angle relative to one another. This results in better material mixing or integration of the flow fronts. In one embodiment, the thickness of the outer ring varies in different portions between adjacent fan blades.

Abstract: A cooling fan assembly for cooling a heat exchanger includes a shroud having a plurality of stators extending radially to support a hub. A flow-guide including an outer rim and inner rim surrounds the shroud and extends to the heat exchanger. The outer rim extends from the heat exchanger to the stators. The inner rim extends annularly about the axis and curves convexly from the outer rim. A fan unit includes a plurality of fan blades extending radially from a motor supported by the hub. Each fan blade includes a leading edge facing the stators and a trailing edge facing in the opposite direction with a blade tip extending therebetween. A fan section extends from the inner rim and axially about the fan blades. The stators are disposed between the heat exchanger and the fan blades. The stators have a front edge facing the heat exchanger and a back edge facing the fan blades. Each stator is connected to the inner rim with the front edge extending radially outward and farther than the back edge.

Abstract: A cover member defining a rotor chamber adjacent to a rotor wheel that supports a rotating blade in a turbine includes a first aperture for introducing a cooling gas stream into the rotor chamber, and a second aperture positioned in a radially outward portion of the cover member for allowing a portion of the cooling gas stream to exit the rotor chamber. The portion of the cooling gas stream exiting the rotor chamber carries dirt particles to purge the rotor chamber.

Abstract: The present invention provides an axial fan assembly including a motor having an output shaft rotatable about a central axis and a shroud coupled to the motor. The shroud includes a substantially annular outlet bell centered on the central axis. The axial fan assembly also includes an axial fan having a hub coupled to the output shaft for rotation about the central axis, a plurality of blades extending radially outwardly from the hub and arranged about the central axis, a substantially circular band coupled to the tips of the blades, and a plurality of leakage stators positioned radially outwardly from the band and adjacent the outlet bell.

Abstract: A fan impeller having fan blades, a base plate, a support ring and fasteners to releasably hold the fan blades between the base plate and the support ring. The base a plate includes channels each having two or more sockets that receive and releasably seat at least a portion of the fan blade. The position of the fan blade relative the axis of rotation of the impeller can be selected from the two or more sockets. The support ring includes grooves in which at least a portion of the fan blade releasably seats to hold the fan blades static relative the base plate and the support ring. The fasteners can extend between the base plate and the support ring to releasably hold the two or more blades.

Abstract: An array of blades for use in a turbomachine is provided comprising a plurality of blades mounted to a rotor disk. A plurality of first blades form a first set of blades and a plurality of second blades form a second set of blades. A blade-to-blade flow field defined between successive ones of the first set of blades is interrupted by the second set of blades to form an asymmetric blade-to-blade flow field around the array of blades. The trailing edges of the second set of blades are positioned forwardly from a line connecting the trailing edges of the first set of blades such that shock forces in the flow field around the array of blades will generally impinge on a stable region of the first set of blades.

Abstract: A centrifugal fan includes a space in which the dimension between a shroud-facing wall and a shroud, from the outer peripheral side to the inner peripheral side of the shroud, is substantially uniform, wherein the shroud-facing wall includes a recess extending in the circumferential direction, the recess being disposed at the inner peripheral side of the outer peripheral end of the shroud-facing wall forming the space having the uniform dimension so that the recess forms a space larger than the other part.

Abstract: An inlet assembly for an aircraft engine nacelle includes an inner barrel, an outer barrel radially spaced from the inner barrel, and a rear support for supporting the outer barrel relative to the inner barrel. The rear support includes at least one radially extending stiffener and at least one energy absorber defining a zone of deformation adjacent the inner barrel. The rear support is deformable in the zone of deformation in response to forces applied during a fan blade-out event to prevent fracture of the rear support.

Abstract: An outer seal assembly of a turbine rotor stage is secured within a circumferential groove of the turbine casing in such a manner as to both fix the outer seal assembly in its installed position and also provide for sealing around its outer periphery so as to thereby prevent the leakage of cooling air therearound. A plurality of arcuate elements having an angle-shaped cross sectional profile are provided to interface between radially extending arms of the outer seal assembly and the inner surface of the casing, with a locking mechanism then being applied to secure the two structures in their installed positions. Each of the arcuate elements includes a radially extending panel, a plurality of forwardly extending hooks that are disposed within a groove in the casing, and a second forwardly extending flange that engages the rear surface of the outer seal assembly arm.

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: An airflow apparatus comprising a stator section, at least one stator blade and a plurality of mounting flanges disposed on the stator section is provided. Additionally, the airflow apparatus includes at least one slot disposed between the plurality of mounting flanges, a rotor assembly coupled to the at least one stator blade, whereby the rotor assembly has a proximal end and a distal end. Furthermore, the airflow apparatus includes at least one fan blade coupled to the rotor assembly. The airflow apparatus also includes a locking apparatus, whereby the locking apparatus includes at least one mounting member and at least one coupling member, wherein the at least one slot is coupled to the at least one coupling member.

Abstract: The present invention provides a coating material, a method of manufacturing the coating material and a coating method using the coating material that are capable of forming a coating film that retains high abrasion resistance while offering improved oxidation resistance at high temperatures, and also provides a moving blade fitted with a shroud. A coating material is used that comprises not less than 14% by mass and not more than 30% by mass of Mo, not less than 13% by mass and not more than 20% by mass of Cr, and not less than 0.5% by mass and not more than 4% by mass of Si, may further comprise not more than 1.5% by mass of Ni, not more than 1.5% by mass of Fe, and not more than 0.08% by mass of C, and comprises a balance of Co and unavoidable impurities, wherein the material further comprises at least one added component selected from the group consisting of not less than 0.01% by mass and not more than 3% by mass of Y, not less than 0.01% by mass and not more than 10% by mass of Al, and not less than 0.

Abstract: A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a skewed axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. A part span shroud is attached at an intermediate section of the airfoil portion between the ends thereof. The blade includes an exit annulus area of about 47.7 ft2 (4.43 m2) or greater.

Abstract: An impeller, a fan apparatus, and a method of manufacturing the impeller are provided. The impeller includes a support portion, a plurality of rotor blades, and a joining member. The joining member is a substantially annular member provided to strengthen the rotor blades against influence of a centrifugal force, and extends in a circumferential direction along a circle centered on a central axis so as to join the rotor blades to one another. In each of the rotor blades, a point of intersection of a leading edge of the rotor blade with a radially outer end of the rotor blade is positioned forward, with respect to a rotation direction, relative to a point of intersection of the leading edge with an outside surface of the support portion. The joining member is positioned radially inwards of the radially outer end of each of the rotor blades.

Abstract: Embodiments include apparatus and methods of fluid energy conversion. One embodiment relates to a tube for a fluid energy converter. The tube may include a generally cylindrical and hollow body having an interior surface, an exterior surface, and a longitudinal axis. Another embodiment includes a fluid energy converter having a longitudinal axis and a rotatable tube coaxial about the longitudinal axis. In some embodiments, the rotatable tube converts kinetic energy in a fluid into rotating mechanical energy, or converts rotating mechanical energy into kinetic energy in a fluid.

Abstract: An cooling arrangement for a turbine shroud provides an air stream directed from a passage extending through a radial wall to impinge on a surface in an area of a back side of the turbine shroud, the surface defining a plane which improves the attack angle of the air stream to the surface.