Abstract: A turbomachine compressor module, comprising an annular array of structural arms defining inter-arm spaces between two circumferentially adjacent arms; and an annular array of stator vanes with variable orientation about a respective axis (A) and disposed at least partially within the inter-arm spaces. The arms are provided with flaps pivotable about a respective axis (B). Also, a turbomachine provided with such a module and a row of rotor blades directly downstream of the module.

Abstract: There is provided apparatuses and methods for a gas turbine engine. The embodiments include a core section with a flow path. The flow path includes a stator vane array having outlet vanes. Each outlet vane has a trailing edge. A strut has a leading edge that is upstream of the trailing edges. Alternatively, the flow path includes a stator vane array having inlet vanes. Each inlet vane has a leading edge. The strut has a trailing edge that is downstream of the leading edges. There also is increased spacing between adjacent vanes and rotor blades.

Abstract: There is provided a turbine power generation system with a single casing configuration capable of easily executing the inhibition of an over-rotation speed. A turbine power generation system in an embodiment includes: a turbine including a turbine casing and a turbine rotor that rotates by a working medium to be introduced into the turbine casing; and a power generator including a power generator rotor connected to the turbine rotor, the power generator being caused to generate power by rotation of the power generator rotor caused by the rotation of the turbine rotor. The turbine casing of the turbine is single, and a moment of inertia of the power generator rotor is larger than a moment of inertia of the turbine rotor.

Abstract: A vane system for an aircraft engine, comprising: an inner wall extending circumferentially about a duct axis; an outer wall extending circumferentially about the duct axis radially outward of the inner wall relative to the duct axis; at least one vane extending from an inner end attached to the inner wall to an outer end rotatably connected to the outer wall, the outer end rotatable relative to the outer wall about a vane axis at an angle to the duct axis; a ring extending circumferentially about the duct axis radially outward of the outer wall relative to the duct axis, the ring rotatable about the duct axis; and at least one transmission member located radially outward of the outer wall relative to the duct axis and coupling the ring to the outer end such that rotating the ring about the duct axis rotates the outer end about the vane axis.

Abstract: The present invention relates to a guide vane, in particular an outlet guide vane and/or a guide vane for a compressor stage of a gas turbine, wherein the vane has a vane blade with a first vane blade portion and a second vane blade portion, and the first vane blade portion can be reversibly rotated in relation to the second vane blade portion about an axis of rotation from a first position to a second position, wherein, in at least one profile portion of the vane blade, the axis of rotation is arranged outside of a profile of the first vane blade portion, and/or a profile of the first vane blade portion has a suction side with a first contour portion and a second contour portion, which, in particular, is adjoined thereto, and a profile of the second vane blade portion has a pressure-side contour portion.

Abstract: A device for masking the inner periphery of a disc of a turbine engine generally includes a lower element, an upper element, and an elastic annular seal. The lower element, the upper element, and the elastic annular seal are coaxial, the elastic annular seal arranged longitudinally between the lower element and the upper element. The seal generally includes a lower annular part bearing radially and internally against the lower element, and an upper annular part bearing radially and internally against the upper element. The lower part and the upper part are connected to one another by an annular central part forming a return element. The elastic annular seal is configured to bear longitudinally, radially, and externally against each longitudinal end of said inner periphery of the disc to mask said inner periphery, and a clamping system capable of clamping the seal between the lower element and the upper element.

Abstract: A non-transitory computer readable medium with instructions stored thereon, the instructions executable by one or more processors for calculating base swirl in a gas turbine; and calculating relative swirl in the gas turbine. Also, a method for gas turbine maintenance, comprising identifying a combustor in need of repair or replacement within a gas turbine; and repairing or replacing the combustor; wherein said identifying comprises calculating base swirl of the gas turbine and calculating relative swirl of the gas turbine in order to associate a gas path from a thermocouple to the combustor in need of repair or replacement.

Abstract: A casing surrounds a rotary shaft and impellers (4), and includes a return flow path through which a fluid discharged from the impeller (4) on a front stage side between the impellers (4) adjacent to each other is guided inward in a radial direction so as to be introduced to the impeller (4) on a rear stage side, and a plurality of return vanes (50) disposed at an interval in a circumferential direction inside the return flow path. An exit angle of the return vane (50) is inclined forward in a rotation direction of the impeller (4), according to the radial direction, and the exit angle of the return vane (50) decreases toward the return vane (50) on the rear stage side.

Abstract: The invention relates to a system of vanes with adjustable orientation, also called a system of variable stator vanes, for a low-pressure compressor of an axial turbine engine. The system comprises vanes, each having a vane extending radially in a flow of the turbine engine and a spindle having a cylindrical portion connected to a telescopic actuating lever. The cylindrical portion comprises radially extending slot, and the actuating lever comprises a pivot joint housed in the slot, that is configured to communicate a rotary movement to the vane about its spindle. The invention also proposes a compressor and a turbine engine.

Abstract: An intake structure of a compressor includes an intake duct forming an intake port opening in a direction away from a central axis of the compressor and a bellmouth forming an annular channel expanding from an inlet of the compressor toward an inner space of the intake duct. The bellmouth includes a plurality of struts connecting an inner casing positioned inside the annular channel and an outer casing positioned outside the annular channel. At least one of a plurality of transverse struts, of the plurality of struts, which are located on both sides of a center plane passing through the central axis of the compressor and the center of the intake port has a trailing edge positioned on a virtual plane passing through the central axis of the compressor and a leading edge positioned on a side of the intake port with respect to the virtual plane.

Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes first and second airfoil pieces. The first airfoil piece defines a portion of the airfoil profile and has a first slot. The second airfoil piece defines a different portion of the airfoil profile and has a second slot. The first slot and the second slot together form a seal slot, and a seal is disposed in the seal slot.

Abstract: A securing device having a radial pin which is inserted into a through-hole having an outside hole and an inside hole and penetrating an outside member in the radial direction of a rotary machine, the outside hole being open to the outside of the outside member in the radial direction of the rotary machine, the inside hole communicating with the outside hole, having a smaller diameter than the outside hole, and being open to the inside in the radial direction of the rotary machine, the radial pin having a portion on the inside in the radial direction of the rotary machine inserted into a recess formed in an inside member, and including a flange portion having an outer diameter larger than a diameter of the inside hole; and a pin support unit which is inserted into the outside hole on the outside in the radial direction of the rotary machine.

Abstract: A compressor includes an impeller having a rotational axis. An annular diffuser is provided around the rotational axis to surround the impeller in order to decelerate the fluid discharged from the impeller in a centrifugal direction with respect to the rotational axis. The annular diffuser includes first vanes and second vanes. The first vanes are arranged in a first blade row extending in a circumferential direction around the rotational axis such that two adjacent vanes among the first vanes do not define a throat therebetween viewed along the rotational axis. The second vanes are arranged in a second blade row which extends in the circumferential direction and which is provided farther than the first blade row in the centrifugal direction from the rotational axis. A number of the second vanes is two times or more as large as a number of first vanes.

Abstract: A tandem tip blade includes a main blade body, a front blade and a rear blade. The front blade extends from a main body end. Each of a front blade pressure and a front blade suction side extends between a front blade leading edge and a front blade trailing edge and a front blade tip extending from the front blade pressure side to the front blade suction side. The rear blade extends from the main body end. Each of a rear blade pressure side and a rear blade suction side extends between a rear blade leading edge and a rear blade trailing edge, and a rear blade tip extending from the rear blade pressure side to the rear blade suction side.

Abstract: A turbine frame for a turbine engine having an axial centerline, the turbine frame comprising an inner hub, an outer hub encircling the inner hub, a plurality of struts extending between the inner and outer hubs and having a maximum width portion relative to the axial centerline and an airfoil comprising at least first and second fairings mounted to the inner and outer hubs and encircling one of the struts.

Abstract: The invention relates to a hydraulic machine having an impeller wheel that comprises a plurality of impeller blades; having a spiral housing that encloses the impeller wheel and that is open toward said impeller wheel by a circumferential slit formed by two circumferential edges; having a traverse ring, comprising two traverse ring decks that are connected to one another by tension anchors; wherein the spiral housing is composed of segments that meet in the flow direction and that are welded to each other, the ends of which segments stand on the respective traverse ring deck and are welded to said deck; wherein at the meeting point between two segments that are adjacent to one another and one traverse ring deck a stiffening element is provided that protrudes into the inner space of the spiral housing; and wherein the extension of the stiffening element into the inner space of the spiral housing is so small that the flow is not affected in a significant manner.

Abstract: An inlet guide vane actuation apparatus is provided. The inlet guide vane actuation apparatus comprises an actuation ring with a first connector for connecting an actuator rod, wherein the first connector positions the actuator rod over the rotational axial center of the actuation ring, a plurality of crank rods with a first end connected respectively to a plurality of second connectors located on the rotational axial center of the actuation ring; and a plurality of cranks with each having a third connector connected respectively to a second end of the plurality of crank rods and respectively to vanes associated with a nozzle, wherein the third connector located on the rotational axial center of the actuation ring.

Abstract: Inlet guide vanes and gas turbine engine systems involving such vanes are provided, In this regard, a representative an inlet guide vane for a gas turbine engine includes: a fixed strut; and a variable flap located downstream of the fixed strut and being movable with respect thereto; the fixed strut having a leading edge, a trailing edge and side surfaces extending between the leading edge and the trailing edge, the side surfaces being asymmetric with respect to each other.

Abstract: A device for adjusting variable guide vanes of an axial-flow machine includes a control rod that adjusts an angular position of the variable guide vanes and is pivotably connected to a shaft. Each of a first and a second bracket has a first end connectable to a casing of the machine. A first joint is fixed to a second end of the first bracket and provides adjustable positioning of a first end of the shaft. A second joint is fixed to a second end of the second bracket and provides adjustable positioning of a second end of the shaft. The two joints are spatially positioned to each other solely via a first fixed connection between the first end of the first bracket to the casing and via a second fixed connection between the first end of the second bracket to the casing.

Abstract: Various systems and methods are described for a variable geometry turbine. In one example, a turbine nozzle comprises a central axis and a nozzle vane. The nozzle vane includes a stationary vane and a sliding vane. The sliding vane is positioned to slide in a direction substantially tangent to an inner circumference of the turbine nozzle and in contact with the stationary vane.

Abstract: A method and system for accepting or rejecting a curved surface of a body under evaluation involves conducting a comparison between the curvature of a surface profile for the surface under evaluation and higher and lower curvature tolerance boundaries. The higher and lower curvature tolerance boundaries are determined from a desired surface profile. The curvature at a plurality of locations on the curve profile under evaluation may be defined with reference to a geometric variable for said curved surface and may be plotted on a graph. The higher and lower curvature tolerance boundaries may also be plotted on the graph so as to determine whether the plot of curvature for the surface under evaluation falls within the bounds of the higher and lower tolerance boundaries.

Abstract: A compressor performance adjustment system includes a compressor chassis defining an inlet passageway, a diffuser passageway coupled to the inlet passageway, and a return passageway extending from the diffuser passageway. At least one inlet vane is located in the inlet passageway. At least one diffuser vane is located in the diffuser passageway. At least one return vane is moveably coupled to the compressor chassis and located in the return passageway. The return vanes may be adjusted without disassembling the compressor chassis in order to adjust the flow incident on compressor components and adjust the performance of a compressor.

Abstract: A turbocharger includes an annular bypass passage to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member. The turbine includes a nozzle having a vane assembly. In one embodiment the vane assembly has only fixed vanes. In another embodiment the vane assembly includes both fixed vanes and variable vanes, and the variable vanes are part of a rotor that rotates together with the rotary valve member.

Abstract: A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition.

Abstract: A variable vane actuation system is disclosed herein. The variable vane actuation system includes a ring member disposed for pivoting movement about a centerline axis. The ring member is engaged with a plurality of vanes in a turbine engine such that the plurality of vanes pivot in response to the pivoting movement of the ring member. The variable vane actuation system also includes a ring moving device engaged with the ring member at first and second positions spaced from one another about the centerline axis. The ring moving device is operable to apply first and second forces, respectively, at the first and second positions to pivot the ring member.

Abstract: A variable vane arm has a hook portion comprising a radially inner leg connected to a radially outer leg by an arcuate connection, and an actuation lever extending from the hook portion. The hook portion and actuation lever are formed from a singular piece of material.

Abstract: Gas turbine engines and related systems involving variable vanes are provided. In this regard, a representative vane assembly for a gas turbine engine includes: a first inner diameter platform; a first outer diameter platform spaced from the first inner diameter platform; and a variable vane airfoil rotatably attached to and extending between the first inner diameter platform and the first outer diameter platform such that at least a portion of the vane airfoil extends beyond a periphery of at least one of the first inner diameter platform and the first outer diameter platform.

Abstract: An improved actuating rod end connector is connected with an actuating rod that extends from a turbocharger assembly actuator mechanism. The rod end connector has a body with an opening at one longitudinal end, and the actuator rod is disposed through the opening. An adjustment member is rotatably disposed within the body and has a threaded inside cavity in communication with the opening. The inside cavity is threadably engaged with a threaded outside surface of the actuator rod. The body includes an actuator rod opening disposed therethrough adjacent the adjustment member to receive a section of the actuator rod therein to facilitate contacting the actuator rod disposed within the body from outside of the rod end connector. An attachment opening is disposed through the body to facilitate attachment of the rod end connector with a linkage member, e.g., a linkage member connected with a movable member of the turbocharger.

Abstract: A bushing assembly for a turbine vane includes a bushing and a housing. The bushing includes a bore for receiving a trunnion of the vane, a first electrical contact carried on an outer surface thereof, and a first conductor extending from the first electrical contact. The first electrical contact is adapted to be connected to a heater element disposed on the vane. The housing is positioned over the bushing and rotatable relative to the bushing. The housing includes a second electrical contact disposed in contact with the first electrical contact and a second conductor extending from the second electrical contact for connection to an electrical power source.

Abstract: A ring vane nozzle for a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of fixed turbine vanes between an inner vane ring and an outer vane ring and a multiple of rotational turbine vanes between the inner vane ring and the outer vane ring, each of the rotational turbine vanes rotatable about an axis of rotation.

Abstract: There is provided an apparatus 2 for generating electrical charge from a motive power source 3. The apparatus 2 comprises an alternator 3a and a worm drive assembly 4 connectable to the motive power source 3. The worm drive assembly 4 comprises a drive shaft 14 a worm gear 20; and, a worm wheel 32 configured so as to mesh with the worm gear 20 and as is further arranged so as to be operatively associated with the alternator 3a. During use, rotation of the drive shaft 14 by the motive power source 3 effects generation of electrical charge by the alternator 3a.

Abstract: The present invention broadly comprises a blade for a torque converter stator including a first blade segment connected to inner and outer circumferential sections of the stator and a second blade segment, separately formed from the first blade segment, and connected to the circumferential sections. In some aspects, the blade segments are: in contact along edges, overlapped, circumferentially misaligned, at least partially folded, stamped, or cast. Configurations of the blade segments can be selected to modify performance characteristics of the stator such as torque ratio, efficiency, and capacity. In some aspects, the blade segments are in a circumferential alignment, and the stator includes an alignment element operatively arranged to control the circumferential alignment, for example, in response to pressure from fluid in the stator upon the blade. In some aspects, the stator includes axial halves, separately formed and fixedly connected and the blade segments are connected to respective halves.

Abstract: A device is for adjusting guide blades of a gas turbine. The guide blades are each connected to an adjusting ring via an adjusting lever, so as to be able to swivel, a first end of the, or each, adjusting lever engaging with the adjusting ring, and a second end of the, or each, adjusting lever, opposite to the first end, engaging with an end of a shaft or shank of the respective guide blade. The adjusting ring is assigned a rotor of a torque motor, a stator of the torque motor concentrically surrounding the rotor of the torque motor.

Abstract: A securing arrangement 32 for securing an actuating lever 20 to a spindle 14, for example a spindle 14 of a variable inlet guide vane 10 in a gas turbine engine, comprises a fastening formation 38 rotatably co-operable, in use, with a corresponding fastening formation 30 on the spindle 14. The securing arrangement 32 is rotatable relative to the spindle 14 to a securing position in which the respective fastening formations 30, 38 co-operate so that the securing arrangement 32 secures the actuating lever 20 to the spindle 14. The securing arrangement 32 includes anti-rotation means 42, preferably in the form of anti-rotation tabs 44, for preventing rotation of the securing arrangement 32 from the securing position.

Abstract: A variable-setting stator blade guidance device of an axial turbomachine is provided. The blade includes an airfoil, a platform and a pivot mounted in the casing of the turbomachine. The device includes a bearing integrated into the platform. In particular, the device includes a bush sandwiched between the platform and the casing, and the integrated bearing is formed between the bush and the platform. In particular, the bush includes a cylindrical surface portion on the side of the platform cooperating with a matching cylindrical surface portion on the platform to form the integrated bearing.

Abstract: The invention relates to a ceramic-based bushing for mounting in a turbomachine casing to provide a smooth bearing for a pivot of a variable-pitch vane. The bushing is constituted by a metal jacket and a ceramic ring secured to the inside wall of said jacket by brazing. The invention also provides a turbomachine compressor having variable-pitch stator vanes with pivots mounted in the casing by means of such bushings.

Abstract: A variable geometry inlet guide vane assembly that reduces stress placed on downstream compressor blades in gas turbine engines. The invention circumferential leans upstream guide vanes, pushing engine core air flow radially. This allows for aerodynamic stresses on the downstream blades to be reduced. The invention overcomes the difference in movement between a unison ring and a vane arm by providing a hinge in conjunction with a spherical bearing that couples to the unison ring.

Abstract: An inlet guide vane provides improved, smooth airflow and avoids separation of flow even at high incidence angles. The inlet guide vane includes a strut having opposite side surfaces that are continuously curved to provide a controlled velocity distribution at the trailing edge of the strut. The inlet guide vane further includes a flap having a leading edge aligned behind the trailing edge of the strut. Generally, the strut and the flap are designed together so that low momentum air in the gap between the strut and the flap will be energized and entrained in the boundary layer of the flap. The airflow from the gap will remain attached to the flap to improve the flow from the flap.

Abstract: Disclosed is an air intake for a turbocharger for an internal combustion engine, said air intake including a series of variable position guide vanes for directing the air such that it is swirling in a rotational sense on reaching the impeller of the compressor of the turbocharger. The variable position guide vanes are made comprised of sound absorbent material such as to achieve a substantial reduction in turbocharger noise at the air intake.

Abstract: A vane system for a centrifugal compressor (10), comprising two rows (15, 20) of vanes (15?, 20?) installed in series inside a suction duct (14), the first row (15) of fixed vanes (15?) being suitable for homogenizing the gas flow that passes through them and sending it to the second row (20) of adjustable vanes (20?) equipped with a guiding mechanism comprising a mechanical system (30) suitable for varying the orientation of the vanes (20?).

Abstract: The invention is an Exit Stay Apparatus with Intermediate Flange for Francis and propeller hydraulic turbines. The purpose of the invention is to improve the effectiveness of known Exit Stay Apparatus (U.S. Pat. No. 6,918,744, July 2005, for Hydraulic Turbine and Exit Stay Apparatus therefor) in eliminating the axial central vortex and, therefore, in increasing the efficiency and decreasing the flow pressure pulsations in draft tube cone at off optimum operating regimes. The new Exit Stay Apparatus has an intermediate flange between exit stay crown and periphery and two sets of exit stay vanes: crown exit stay vanes secured to the exit stay crown and the intermediate flange and peripheral exit stay vanes secured to the intermediate flange and following to the periphery. When installed in the turbine the peripheral exit stay vanes are secured at the periphery.

Abstract: A variable inlet guide vane assembly in a turbomachine in which the vanes can vary in angle to control the flow through into the turbomachine, each guide vane having a leading edge portion and a trailing edge portion, and where the entire vane can pivot or the trailing edge portion can pivot about the leading edge portion. The leading edge and trailing edge portions each have a magnetic field generating material located within the portion of the vane or one a surface of the vane. The vanes are offset in the shroud such that the trailing edge portion of a first vane is located closer to the leading edge portion of an adjacent vane than to the trailing edge portion of the adjacent vane. An electric current is passed through at least one of the trailing edge and leading edge portions to produce a magnetic field. The magnetic field causes the trailing edge portion to move toward the leading edge portion of the adjacent vane.

Abstract: There is provided an adjustable vane turbine and turbine generator using the same, in which hydrodynamic properties are employed to adjust adjustable vanes automatically in response to flow condition such as the flow rate of the working fluid, thereby simplifying the system using the adjustable vanes and reducing cost. In the adjustable vane turbine, a turbine wheel is installed in a turbine housing and rotatably supported by a shaft, and a plurality of adjustable vanes are movably installed between the turbine housing and the turbine wheel, wherein each of the adjustable vanes includes an adjustable vane member having one end portion rotatably fixed to the turbine housing, a vane control element attached on one side of the adjustable vane member at a set angle, and a guide element attached on the other side of the adjustable vane member, the plurality of adjustable vanes being connected using links between neighboring vanes.

Abstract: An attachment system for use with a variable incidence vane is disclosed. The attachment system includes a vane arm for joining a unison ring to a vane spindle. The vane arm has an arm portion and a bushing connected to the arm portion. The attachment system further has a pin for joining the vane arm to the unison ring. The pin fits within an interior bore in the bushing and is joined to the unison ring by a dual swage.

Abstract: A stay ring of a hydraulic turbine has: a ring-shaped upper wall, a ring-shaped lower wall arranged below the upper wall forming a ring-shaped flow channel between the upper wall and the lower wall; and stay vanes arranged in array with spaces in a peripheral direction in the ring-shaped flow channel and rigidly secured to the upper and lower walls. The upper wall and the lower wall are inclined so as to reduce height of the ring-shaped flow channel toward outlet at least near inlet end thereof. The straightening bodies are arranged along inner surfaces of the upper wall and the lower wall at least near inlet end to reduce inclination of water flow in the stay ring.

Abstract: The present invention relates to a variable-setting stator blade guidance device of an axial turbomachine, the blade comprising an airfoil (22), a platform (23) and a pivot (24) mounted in the casing of the turbomachine. The device is characterized in that it comprises a bearing integrated into the platform. In particular, the device comprises a bush (26b) between the platform and the casing, and the integrated bearing is formed between the bush and the platform. In particular, the bush comprises a cylindrical surface portion (26b1) on the side of the platform interacting with a matching cylindrical surface portion (23b1) on the platform to form said integrated bearing.

Abstract: A compressor or pump employs principles of unsteady delayed stall to enhance the head increase produced by the compressor or pump. Plural airfoil-shaped lifting elements are spaced from each other in a cascade and the fluid is directed into the cascade by a device that varies a parameter of the flow relative to each lifting element in repeating cycles to cause the flow relative to each lifting element to begin to separate from the lifting element and then reattach thereto during each cycle. The cascade can comprise an axial flow impeller with plural impeller blades arranged around a hub capable of rotating on an axis. The device for varying the flow parameter can be a stator with a plurality of stator blades upstream of the impeller, or a second, counter-rotating axial flow impeller. In either case, the parameter is a flow angle at which the flow is directed to the downstream impeller.

Abstract: The invention is an Exit Stay Apparatus for Francis and propeller hydraulic turbines. The purpose of the invention is to eliminate the loss of turbine efficiency and strong pulsations in draft tube caused by the axial circular vortex in all turbine operating regimes other than optimum without a noticeable decrease in maximum efficiency. It can be incorporated not only into newly fabricated hydraulic turbines, but also retrofitted into existing turbines. The Exit Stay Apparatus has a crown and exit stay vanes secured to the the crown. When installed in the turbine, the exit stay crown is located immediately after the runner crown, which is truncated at the bottom by a plane perpendicular to the central axis of the turbine. The exit stay crown together with the truncated runner crown forms water passages after the runner blade crown profile exit.

Abstract: The invention is an Exit Stay Apparatus for Francis and propeller hydraulic turbines. The purpose of the invention is to eliminate the loss of turbine efficiency and strong pulsations in draft tube caused by the axial circular vortex in all turbine operating regimes other than optimum without a noticeable decrease in maximum efficiency. It can be incorporated not only into newly fabricated hydraulic turbines, but also retrofitted into existing turbines. The Exit Stay Apparatus has a crown and exit stay vanes secured to the the crown. When installed in the turbine, the exit stay crown is located immediately after the runner crown, which is truncated at the bottom by a plane perpendicular to the central axis of the turbine. The exit stay crown together with the truncated runner crown forms water passages after the runner blade crown profile exit.

Abstract: A method for assembling an articulated fan front frame for a gas turbine engine facilitates improving engine performance. The method includes forming a strut including a pair of sidewalls connected at a leading edge and a trailing edge, forming a flap including a first sidewall and a second sidewall connected at a leading edge and a trailing edge, and extending in radial span between a root endwall and a tip endwall, wherein each endwall extends between the first and second sidewalls, and wherein at least one of the root endwall and the tip endwall is contoured in a radial direction extending between the flap leading and trailing edges, and pivotally coupling the flap downstream from the strut such that a gap is defined between the flap and the strut.