US20140140822A1 - Contoured Stator Shroud - Google Patents

Contoured Stator Shroud Download PDF

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Publication number
US20140140822A1
US20140140822A1 US13/679,093 US201213679093A US2014140822A1 US 20140140822 A1 US20140140822 A1 US 20140140822A1 US 201213679093 A US201213679093 A US 201213679093A US 2014140822 A1 US2014140822 A1 US 2014140822A1
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US
United States
Prior art keywords
vane
shroud
elevation
stator shroud
contoured
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US13/679,093
Other languages
English (en)
Inventor
Joseph Capozzi
David Vickery Parker
Jeffrey Carnes
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US13/679,093 priority Critical patent/US20140140822A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CARNES, JEFFREY, CAPOZZI, JOSEPH, Parker, David Vickery
Priority to JP2015542683A priority patent/JP2015537150A/ja
Priority to CA2891070A priority patent/CA2891070A1/en
Priority to EP13824424.9A priority patent/EP2920430A1/en
Priority to CN201380059853.6A priority patent/CN104781509B/zh
Priority to PCT/US2013/068421 priority patent/WO2014078121A1/en
Priority to BR112015011191A priority patent/BR112015011191A2/pt
Publication of US20140140822A1 publication Critical patent/US20140140822A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY CORRECTIVE ASSIGNMENT TO CORRECT THE THIRD ASSIGNORS NAME PREVIOUSLY RECORDED AT REEL: 029502 FRAME: 0285. ASSIGNOR(S) HEREBY CONFIRMS THE ASSIGNMENT. Assignors: CARNES, JEFFREY DANIEL, CAPOZZI, JOSEPH, Parker, David Vickery
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour

Definitions

  • the disclosed embodiments generally pertain to gas turbine engines. More particularly, present embodiments relate to shrouds within gas turbine engines which are utilized with pivoting vanes.
  • a typical gas turbine engine In a gas turbine engine a typical gas turbine engine generally possesses a forward end and an aft end with its several components following inline therebetween.
  • An air inlet or intake is at a forward end of the engine. Moving toward the aft end, in order, the intake is followed by a compressor, a combustion chamber, a turbine, and a nozzle at the aft end of the engine.
  • additional components may also be included in the engine, such as, for example, low-pressure and high-pressure compressors, high-pressure and low-pressure turbines, and an external shaft. This, however, is not an exhaustive list.
  • An engine also typically has an internal shaft axially disposed through a center longitudinal axis of the engine. The internal shaft is connected to both the turbine and the air compressor, such that the turbine provides a rotational input to the air compressor to drive the compressor blades.
  • a high pressure turbine first receives the hot combustion gases from the combustor and includes a stator nozzle assembly directing the combustion gases downstream through a row of high pressure turbine rotor blades extending radially outwardly from a supporting rotor disk.
  • a second stage stator nozzle assembly is positioned downstream of the first stage blades followed in turn by a row of second stage rotor blades extending radially outwardly from a second supporting rotor disk. The turbine converts the combustion gas energy to mechanical energy.
  • Vanes or airfoils are typically designed with a primary or optimal position for operation. However, depending on the desired operating condition of the turbine engine, the vanes may be actuated to alternate positions.
  • Current stator shroud designs utilize a circular cross-section across which vanes are actuated. As the vanes move from the open design position to off design closed positions, clearance between the vane and shroud increases due to the curvature of the shroud, the flow path geometry and the lower edge shape of the vane, all of which are required to meet the compressor operating requirements.
  • a contoured stator shroud vane assembly in a gas turbine engine having an inlet end, an outlet end and a plurality of propulsor components comprises a stator shroud having a generally circular cross-section, the shroud having a forward end, an aft end and at least one surface extending between said first end and said second end, the shroud having a plurality of pivots disposed circumferentially about the shroud to support a trunnion of a vane, the at least one surface of varying elevation adjacent to said plurality of pivots and extending in a circumferential direction.
  • a contoured stator shroud comprises a forward end, an aft end and at least one surface extending between the forward end and the aft end, the at least one surface being tapered from the forward end to the aft end, a plurality of areas of varying elevation disposed about the at least one surface, the plurality of areas each having a peak and a valley, a plurality of pivot apertures spaced about a forward end of the at least one surface.
  • a contoured stator shroud comprises a forward end and an aft end, at least one surface extending between the forward end and the second end, the at least one surface having a scalloped chord overhang area, the scalloped area extending in a circumferential direction, a plurality of vane mounting locations disposed circumferentially between the forward end and the aft end.
  • FIG. 1 is a side section view of a gas turbine engine
  • FIG. 2 is an exploded perspective view of a stator shroud vane assembly
  • FIG. 3 is a perspective view of the stator shroud vane assembly
  • FIG. 4 is a side section view of an exemplary stator shroud vane assembly
  • FIG. 5 is a detail perspective view of stator shroud vane assembly
  • FIG. 6 is an aft view of the stator shroud vane assembly in a first position
  • FIG. 7 is an aft view of the stator shroud vane assembly in a second position
  • FIG. 8 is an aft view of the stator shroud vane assembly in a third position.
  • FIG. 9 is a graph of vane position as related to clearance between the shroud and the vane.
  • stator shroud capable of use with pivoting vanes.
  • the stator shroud includes a stator shroud overhang surface over which vanes are pivoted during engine operation.
  • the stator shroud overhang surface has varying elevations to eliminate leakage between the vane and the shroud which would normally occur when a vane pivots an outer surface of the shroud. This reduces any flow disruptions or flow disturbances along the vane or airfoil.
  • axial refers to a dimension along a longitudinal axis of an engine.
  • forward used in conjunction with “axial” or “axially” refers to moving in a direction toward the engine inlet, or a component being relatively closer to the engine inlet as compared to another component.
  • aft used in conjunction with “axial” or “axially” refers to moving in a direction toward the engine nozzle, or a component being relatively closer to the engine nozzle as compared to another component.
  • the terms “radial” or “radially” refer to a dimension extending between a center longitudinal axis of the engine and an outer engine circumference.
  • proximal or “proximally,” either by themselves or in conjunction with the terms “radial” or “radially,” refers to moving in a direction toward the center longitudinal axis, or a component being relatively closer to the center longitudinal axis as compared to another component.
  • distal or disally, either by themselves or in conjunction with the terms “radial” or “radially,” refers to moving in a direction toward the outer engine circumference, or a component being relatively closer to the outer engine circumference as compared to another component.
  • lateral refers to a dimension that is perpendicular to both the axial and radial dimensions.
  • FIG. 1 a schematic side section view of a gas turbine engine 10 is shown having an engine inlet end 12 wherein air enters the propulsor 13 which is defined generally by a compressor 14 , a combustor 16 and a multi-stage high pressure turbine 20 . Collectively, the propulsor 13 provides thrust or power during operation.
  • the gas turbine 10 may be used for aviation, power generation, industrial, marine or the like. Depending on the usage, the engine inlet end 12 may alternatively contain multi-stage compressors rather than a fan.
  • the gas turbine 10 is axis-symmetrical about engine axis 26 or shaft 24 so that various engine components rotate thereabout.
  • the compressed air is mixed with fuel and burned providing the hot combustion gas which exits the combustor 16 toward the high pressure turbine 20 .
  • energy is extracted from the hot combustion gas causing rotation of turbine blades which in turn cause rotation of the shaft 24 .
  • the shaft 24 passes toward the front of the engine to continue rotation of the one or more compressor stages 14 , a turbofan 18 or inlet fan blades, depending on the turbine design.
  • the axis-symmetrical shaft 24 extends through the through the turbine engine 10 , from the forward end 12 to an aft end.
  • the shaft 24 is journaled along its length.
  • the shaft 24 may be hollow to allow rotation of a low pressure turbine shaft 28 therein and independent of the shaft 24 rotation. Both shafts 24 , 28 may rotate about the centerline axis 26 of the engine.
  • the shafts 24 , 28 rotate along with other structures connected to the shafts such as the rotor assemblies of the turbine 20 and compressor 14 in order to create power or thrust depending on the area of use, for example power, industrial or aviation.
  • the inlet 12 includes a turbofan 18 which has a plurality of blades.
  • the turbofan 18 is connected by the shaft 28 to the low pressure turbine 19 and creates thrust for the turbine engine 10 .
  • the low pressure air may be used to aid in cooling components of the engine as well.
  • FIG. 2 an exploded perspective view of a stator shroud vane assembly 30 is depicted.
  • a plurality of vanes 40 are spaced about the shroud 32 , most of which are not shown.
  • Three vanes 40 are shown exploded from the outer surface of the shroud.
  • the shroud 32 of the exemplary embodiment is circular in cross section and frusto-conical in shape having a forward end 34 , an aft end 36 .
  • the exemplary shroud 32 is located in the compressor 14 area of the engine.
  • a multi-stage compressor typically includes several rows of rotating blades mounted on a rotor and several rows of stator vanes 40 mounted between a stator casing and the shroud 32 .
  • the shroud is axisymmetric to the shaft 24 ( FIG. 1 ) of engine 10 .
  • a plurality of pivots 38 which are represented in the exemplary embodiment as a number of circular pockets wherein the vanes 40 are seated for rotation relative to the shroud 32 .
  • the shroud 32 also tapers from a smaller diameter near the forward end 34 to a larger diameter near the aft end 36 .
  • a clearance is created between a lower edge of the vanes 40 and the outer surface of the shroud 32 when the vanes 40 are seated within the pivots 38 .
  • the circular cross-section results in increased clearance between the vane and the shroud when the vane is rotated to off design positions.
  • present embodiments provide for a wavy or variable surface height to reduce clearance in the off-design positions of the vane 40 .
  • the vane 40 includes an outer spindle 44 and an inner spindle 45 .
  • the spindles 44 , 45 may be formed as a vertical line or at an angle to the vertical.
  • the depicted spindles are at an angle of between 10 and 15 degrees from the vertical.
  • a button 42 which along with the spindle 45 is seated within the pivot 38 .
  • An upper button 56 also controls rotation within the casing of the engine, through which the outer spindle passes.
  • FIG. 3 a perspective view of a stator shroud vane assembly 30 is depicted.
  • the instant shroud assembly 30 is located within the compressor 14 of the turbine engine.
  • the principles embodied in the contoured stator shroud 32 may be utilized in alternate locations of the engine wherein shrouds and vanes or air foils are utilized, such as the stator vanes of a turbine, for example.
  • the stator shroud 32 depicted is at an inner diameter of the vanes 40 .
  • An engine casing (not shown) may be used to provide the outer diameter pivot location for the vanes 40 .
  • the stator vane shroud assembly 30 utilizes a shroud 32 having a forward end 34 and aft end 36 .
  • the shroud 32 is generally circular in cross section as partially shown in the view depicted.
  • the diameter at the forward end 34 may be larger than the diameter at the aft end 36 .
  • the forward end includes a plurality of pivots 38 wherein vanes 40 may be positioned.
  • the pivots 38 are recessed areas wherein the vane or air foils 40 are positioned for pivoting utilizing buttons or guides 42 .
  • a spindle 44 which may be utilized to mount the second end of the vanes 40 to provide guided pivoting or rotation.
  • the spindle 44 may pass through an aperture in an engine casing to stabilize the spindle and allow for pivoting motion.
  • a lever arm (not shown) guides the rotation through the desired angular displacement providing the different positions for improved efficiency and performance of the engine at multiple operating conditions.
  • the plurality of vanes 40 extend about the circumference of the shroud 32 near the forward end 34 of the shroud, although some are not shown for clarity.
  • At least one shroud surface 46 Extending rearwardly from the pivots 38 is at least one shroud surface 46 , for example a stator chord overhang surface 46 .
  • the stator chord overhang surface 46 tapers from a smaller diameter near the pivots 38 to a larger diameter near the aft end 36 . This axial direction taper or change in elevation may be curved or may be linear.
  • stator chord overhang surface 46 is contoured so that the elevation changes in the circumferential direction.
  • the curvature 48 of the broken lines depicts the contour of the stator chord overhang surface 46 which varies between a lower elevation and an upper elevation in a circumferential direction.
  • the broken line depicts the contour 48 along wavy or sinuous surface 46 .
  • the stator chord overhang surface 46 has a wavy contour 48 to reduce clearance between the vane 40 and the shroud 32 during movement of the vane 40 .
  • the variation in elevation in the circumferential direction may be linear.
  • the surface 48 includes a plurality of peaks and valleys.
  • the axis of the peaks or valleys are generally parallel to the axis of the engine 26 ( FIG. 1 ) or at an angle to engine axis 26 as the shroud tapers from forward to aft end.
  • the contour 48 significantly reduces the flow field disruptions created by the clearance between the vanes 40 and shroud 32 . These clearances would normally adversely affect the intended purpose of the vane airfoil shape, function and configuration when the vane moves between open and closed angular positions.
  • the exemplary vane or air foil 40 includes a leading edge 50 , and a trailing edge 52 and opposed surfaces extending between.
  • the opposed surfaces define a suction side and a pressure side which will be understood by one skilled in the art.
  • an outer enlarged portion or button 56 At a radially outward end of the vane 40 an outer enlarged portion or button 56 .
  • the spindle or trunion 44 may be connected to a lever arm or other feature to actuate the vane 40 to a desired position.
  • the rotation of the vane 40 provides more than one optimal condition for the vane or air foil to provide improved efficiency and performance at differing operating conditions of the gas turbine engine 10 .
  • a fillet 54 connects the vane 40 to the button 42 at the radially inner end.
  • the lower edge 58 of the vane 40 or vane overhang, is curved and during movement of the vane 40 , the lower edge 58 moves away from the typical shroud surface ( FIG. 6 ) which is purely circular in cross section and represented by line 70 .
  • the increased clearance which occurs with prior art to systems reduces performance, air flow turn and increases loss in this region which is undesirable and inhibits improvements in engine performance.
  • the contour represented by the wavy or curved broken line 48 decreases clearance between the shroud 32 and the vane 40 improving the air turning performance and reducing loss in this region.
  • FIG. 4 a side section view of the assembly 30 of FIG. 3 is depicted.
  • the shroud 32 is shown sectioned vertically between the forward end 34 and the aft end 36 so as to depict the button 42 which is seated within the pivot 38 .
  • the vane 40 further includes a lower spindle or trunnion 45 which extends downwardly into the pivot so that the vane 42 is pivotally secured in the shroud 32 and, as previously described, the upper spindle 44 is pivotally retained through an engine casing.
  • the stator chord overhang 46 is curved in the axial direction between the forward end 34 and the aft end 36 , and more specifically aft of the pivots 38 .
  • the surface 46 is tapered linearly in the axial direction between forward end 34 and the aft end 36 .
  • FIG. 5 a detailed perspective view of the shroud 32 and vanes 40 are depicted.
  • the detailed view shows a pivot 38 in both an empty condition and a filled by a vane 40 .
  • a button 42 is seated within the generally circularly shaped pivot 38 and the vane 40 is connected to the button 42 by fillet 54 .
  • a clearance 60 is shown between a lower edge 58 of the vane and the stator chord overhang 46 .
  • the clearance is reduced relative to prior art stators due to the curvature in the axial direction, between the forward end 34 and the aft end 36 .
  • the clearance is decreased through the arcuate movement of the vane 40 within the pivot 38 due to the contour 48 along the circumferential direction of the overhang surface 46 .
  • the contour 48 is more clearly shown due to the curvature of the broken line 48 which represents the contour of the stator shroud 32 .
  • a plurality of axially extending contour lines 49 also are shown on the stator chord overhang surface 46 which depict another curvature of the stator 32 .
  • the vanes 40 are closed when the engine speed is at or very near zero. In this closed position, the vanes 40 are near the uppermost elevation of the contour surface 48 . Alternatively, as engine speed increases and approaches a maximum, the vane 40 approaches the lowermost elevation of the contour surface 48 .
  • the shroud 32 is shown in an aft view looking forward with a vane 40 shown move in multiple positions.
  • the contour of the stator chord overhang surface 46 is best described in reference to this view.
  • the wavy or sinuous surface 48 is formed by a plurality of scallop-like humps which change between first and second elevations.
  • sinuous is used, it should not be limited to mathematically exact sin curve. The term is instead used in a general sense to indicate a repeating change in elevation.
  • a broken line 70 is shown in the view to represent a circular reference shape of a prior art shroud.
  • the line 70 may also represent a base or first elevation of the stator chord overhang surface 46 .
  • the line 70 of the instant embodiment may be above or below the valley or lower elevation of the stator chord overhang surface since, as shown, the surface 46 also changes elevation in the axial direction.
  • the contour 48 elevation changes are shown by referencing the difference between first elevation 70 and the second upper elevation 72 of the contour.
  • the overhang surface 46 changes elevation between a first elevation and a second elevation and with such changing elevation, the clearance between the vane 40 is reduced throughout the positions depicted in FIGS. 6-8 .
  • the vane 40 may rotate from, for example, minus 3 degrees and about 25 degrees.
  • the exemplary vane 40 may move about 14 degrees from the center position in either of two rotational directions.
  • this is exemplary and alternate angular ranges may be designed into the vane movement.
  • the vane is shown in a central position which more clearly depicts the lower edge 58 of the vane.
  • the vane 40 is in the 11 degree position, according to the exemplary range as previously described. This is generally a central position.
  • a pair of clearance arrows are shown in FIG. 7 .
  • Clearance 60 depicts the clearance provided by the contoured 48 in cooperation with the lower edge 58 of vane 40 .
  • the clearance P is shown which depicts the larger clearance between the lower edge 58 and the prior art circular shroud reference previously described as line 70 . From this embodiment, one skilled in the art can clearly see the reduced differential that the contour 48 provides.
  • FIG. 8 a second extreme position of the vane 40 is depicted, for example at the 25 degree position. Again the clearance 60 is much smaller than the prior art clearance P as related to the circular shroud reference 70 .
  • vanes may take various shapes and forms depending upon the design characteristics of the engine. Accordingly, the shape of the contours may be formed to correspond to the shape of the vane lower edge through a preselected arcuate motion.
  • the shroud surface, spindle angle, amount of vane chord overhang and travel are all designed/optimized with reduced clearance for reduced loss and improved performance in mind when optimizing the variable vane system.
  • FIG. 9 a chart is shown depicting a relationship between the vane's angle measured in degrees and the clearance between the vane lower edge 58 and the shroud chord overhang 46 .
  • line 80 having diamond-shaped data points, the clearance between an angle of minus 10 degrees and 25 increases rather constantly.
  • the stator shroud 32 of this prior art embodiment is circular in shape and is lacking the contour shape of the instant embodiments.
  • line 82 represented by square-shaped data points begins at the previously defined range of minus 3 degrees and moves to a position of 25 degrees.
  • the clearance represented by line 82 is generally constant from about 0 degrees to about 12 degrees, before increasing up to the 25 degree position.
  • the clearance is much less in the contoured stator shroud than that of the prior art.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
US13/679,093 2012-11-16 2012-11-16 Contoured Stator Shroud Abandoned US20140140822A1 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US13/679,093 US20140140822A1 (en) 2012-11-16 2012-11-16 Contoured Stator Shroud
JP2015542683A JP2015537150A (ja) 2012-11-16 2013-11-05 曲線輪郭のステータシュラウド
CA2891070A CA2891070A1 (en) 2012-11-16 2013-11-05 Contoured stator shrouds
EP13824424.9A EP2920430A1 (en) 2012-11-16 2013-11-05 Contoured stator shrouds
CN201380059853.6A CN104781509B (zh) 2012-11-16 2013-11-05 波状的定子护罩
PCT/US2013/068421 WO2014078121A1 (en) 2012-11-16 2013-11-05 Contoured stator shrouds
BR112015011191A BR112015011191A2 (pt) 2012-11-16 2013-11-05 conjunto de pá de cobertura de estator contornada e cobertura de estator contornada

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/679,093 US20140140822A1 (en) 2012-11-16 2012-11-16 Contoured Stator Shroud

Publications (1)

Publication Number Publication Date
US20140140822A1 true US20140140822A1 (en) 2014-05-22

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ID=50002832

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/679,093 Abandoned US20140140822A1 (en) 2012-11-16 2012-11-16 Contoured Stator Shroud

Country Status (7)

Country Link
US (1) US20140140822A1 (ja)
EP (1) EP2920430A1 (ja)
JP (1) JP2015537150A (ja)
CN (1) CN104781509B (ja)
BR (1) BR112015011191A2 (ja)
CA (1) CA2891070A1 (ja)
WO (1) WO2014078121A1 (ja)

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US20150176418A1 (en) * 2013-12-19 2015-06-25 Pratt & Whitney Canada Corp. Compressor variable vane assembly
US20150275916A1 (en) * 2014-03-28 2015-10-01 Pratt & Whitney Canada Corp. Compressor variable vane assembly
US20150285085A1 (en) * 2014-04-02 2015-10-08 Solar Turbines Incorporated Variable guide vane extended variable fillet
US20160108821A1 (en) * 2014-09-19 2016-04-21 United Technologies Corporation Radially fastened fixed-variable vane system
US20170037741A1 (en) * 2015-08-03 2017-02-09 MTU Aero Engines AG Guide vane ring element for a turbomachine
EP3176385A1 (de) * 2015-12-04 2017-06-07 MTU Aero Engines GmbH Leitschaufelkranzgehäuse für eine strömungsmaschine und strömungsmaschine mit leitschaufelkranzgehäuse
US20170159471A1 (en) * 2015-12-04 2017-06-08 MTU Aero Engines AG Inner ring and guide vane cascade for a turbomachine
US20170370343A1 (en) * 2015-01-30 2017-12-28 Alstom Renewable Technologies Turbine unit for hydraulic installation
US20180058263A1 (en) * 2016-08-23 2018-03-01 MTU Aero Engines AG Positioning element with recesses for a guide vane arrangement
US10287901B2 (en) 2014-12-08 2019-05-14 United Technologies Corporation Vane assembly of a gas turbine engine
US10794392B2 (en) * 2016-02-25 2020-10-06 Safran Aircraft Engines Hub for propeller having variable-pitch blades, with radial and axial dimensioning variation
US10815811B2 (en) 2017-11-28 2020-10-27 General Electric Company Rotatable component for turbomachines, including a non-axisymmetric overhanging portion
DE102019216634A1 (de) * 2019-10-29 2021-04-29 MTU Aero Engines AG Leitschaufelanordnung für eine strömungsmaschine
WO2021110192A1 (de) * 2019-12-04 2021-06-10 MTU Aero Engines AG Leitschaufelanordnung für eine strömungsmaschine
US20220162956A1 (en) * 2020-11-23 2022-05-26 Pratt & Whitney Canada Corp. Variable guide vane assembly with bushing ring and biasing member
US20220333489A1 (en) * 2019-09-06 2022-10-20 Safran Aircraft Engines Turbomachine polyspherical hub for variable pitch blades
US11572794B2 (en) 2021-01-07 2023-02-07 General Electric Company Inner shroud damper for vibration reduction
US11608747B2 (en) 2021-01-07 2023-03-21 General Electric Company Split shroud for vibration reduction
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US20220162956A1 (en) * 2020-11-23 2022-05-26 Pratt & Whitney Canada Corp. Variable guide vane assembly with bushing ring and biasing member
US11572794B2 (en) 2021-01-07 2023-02-07 General Electric Company Inner shroud damper for vibration reduction
US11608747B2 (en) 2021-01-07 2023-03-21 General Electric Company Split shroud for vibration reduction
US20240044259A1 (en) * 2022-08-02 2024-02-08 Pratt & Whitney Canada Corp. Variable guide vane assembly for gas turbine engine
US11965422B2 (en) * 2022-08-02 2024-04-23 Pratt & Whitney Canada Corp. Variable guide vane assembly for gas turbine engine
US11879480B1 (en) 2023-04-07 2024-01-23 Rolls-Royce North American Technologies Inc. Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines

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EP2920430A1 (en) 2015-09-23
BR112015011191A2 (pt) 2017-07-11

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