US20150125301A1 - Platform seal strip, turbine blade assembly and method for assembling it - Google Patents

Platform seal strip, turbine blade assembly and method for assembling it Download PDF

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Publication number
US20150125301A1
US20150125301A1 US14/405,826 US201314405826A US2015125301A1 US 20150125301 A1 US20150125301 A1 US 20150125301A1 US 201314405826 A US201314405826 A US 201314405826A US 2015125301 A1 US2015125301 A1 US 2015125301A1
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US
United States
Prior art keywords
platform
disc
seal strip
cover plate
turbine
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
US14/405,826
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English (en)
Inventor
Paul Headland
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.)
Siemens AG
Original Assignee
Siemens AG
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Filing date
Publication date
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Assigned to SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED reassignment SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: HEADLAND, PAUL
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SIEMENS INDUSTRIAL TURBOMACHINERY LIMITED
Publication of US20150125301A1 publication Critical patent/US20150125301A1/en
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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the present invention relates to a platform seal strip, a turbine blade assembly and a gas turbine. It further relates to a method for assembling a turbine blade assembly, for example a gas turbine blade assembly.
  • EP 2 053 285 A1 and EP 2 053 286 A1 describe a seal strip with varying width that is bent at a downstream end and trapped between a blade platform and the locking plate in the assembly.
  • a sealing member such as a wire is mounted in a groove between blade platforms of a gas turbine engine to seal between the adjacent platforms.
  • U.S. Pat. No. 6,561,764 B1 describes a gas turbine rotor comprising blade platforms with recesses into which insert strips are inserted.
  • the recess reaches as far as the disc-side base of the blade platform and the insert strip to have a form fit to the disc, which protects against axial displacement in a direction of inserting of the gas turbine blade.
  • U.S. Pat. No. 3,834,831 disclosures gas turbine engine, wherein cooling fluid may escape through radially directed passageways within the turbine blade or through a space between the adjacent blade platforms.
  • a first objective of the present invention to provide an advantageous seals strip, in particular for use in a gas turbine blade assembly.
  • a second objective of the present invention is to provide an advantageous turbine blade assembly and an advantageous gas turbine.
  • a third objective of the present invention is to provide an advantageous method for assembling a turbine blade assembly, for example a gas turbine blade assembly.
  • the first objective is solved by a platform seals strip as claimed.
  • the second objective is solved by a turbine blade assembly as claimed and by a gas turbine as claimed.
  • the third objective is solved by a method for assembling a turbine blade assembly as claimed.
  • the inventive platform seals strip in particular for use in a gas turbine blade assembly, comprises an upper side and a lower side. It further comprises a first portion and a second portion.
  • the first portion may be a leading portion.
  • the second portion may be a main platform part.
  • the width of the first portion is smaller than the width of the second portion, which means that the width of the first portion has a smaller value than the width of the second portion.
  • the first portion and the second portion are at least partially bent downwards such that the upper side comprises a convex surface portion and the lower side comprises a concave surface portion. In other words, the first portion and the second portion are bent towards the lower side.
  • Downward may mean, once the seal strip is installed, in direction of an axis of rotation of the machine. “Downward” also defines the orientation of the bend in respect of the upper side and the lower side, meaning that “downward” is a motion in direction of the lower side.
  • “Upper” and “lower” may merely define two opposite sides of the seal platform strip. Particularly “upper” may also mean, once the seal strip is installed, a direction away from of the axis of rotation of the machine. “Lower” may mean, once the seal strip is installed, a direction directed to the axis of rotation of the machine.
  • the invention seal strip may for example have an U-shape or a shape like an U.
  • Convex surface portion or concave surface portion means that at least part of the surface has a curvature or bending which is convex if seen from the upper side or upper surface and which is concave if seen from the lower side or lower surface of the first portion or of the second portion.
  • the first portion may comprise an upper surface portion with a surface normal
  • the second portion may comprise an upper surface portion with a surface normal which includes an angle a with the surface normal of the first portion between 0° and 180°, which means 0° ⁇ a ⁇ 180°, advantageously between 90° and 180°.
  • the inventive seal strip has the advantage that inter seal leakage, for example between two adjacent blade platforms can be overcome by using a single piece seals strip.
  • the inventive seal strip comprises a transition portion which is located between the first portion and the second portion.
  • the width of the transition portion increases from the first portion to the second portion.
  • the width of the transition portion continuously increases from the first portion to the second portion.
  • the strip seal may comprise a trailing portion extending downwards from the second portion.
  • the width of the first portion may be constant and/or the width of the second portion may be constant. Constant width means that the width has the same value at each position of the mentioned portion.
  • the width of the first portion has a value w 1 , which is constant at each position along length of the first portion
  • the width of the second portion has a value w 2 , which is constant at each position along length of the second portion and which is higher than the width w 1 of the first portion (w 1 ⁇ w 2 ).
  • a transition portion with a width, which continuously increases from the first portion to the second portion is located between the first and the second portion.
  • the second portion may comprise or may define the widest section of the seal strip.
  • the second portion can advantageously have only one width changing section, for example only at one of its end.
  • second portion can have only a width changing section at each end of the second portion.
  • the width of the width changing section may change continuously, for instance only increase continuously or only decrease continuously.
  • the platform seal strip may comprise metal or may consist of metal.
  • the inventive seal strip comprises at least one nose.
  • the nose may be located at the first portion or at the second portion.
  • Advantageously one nose is located the first portion and an additional nose is located at the second portion.
  • the nose is at least partially bent upwards such that the upper side of the seals strip with the nose comprises a concave surface portion and the lower side of the seal strip with the nose comprises a convex surface portion.
  • the term nose describes a portion of the seal strip which is bent with respect to the adjacent first or second portion.
  • the nose may have a surface portion with a surface normal.
  • the first portion or the second portion may comprise a surface adjacent to the nose.
  • This surface may have a surface normal which may include an angle ⁇ with the surface normal of the nose portion between 0° and 180°, which means 0° ⁇ 180°, and in an advantageous embodiment between 60° and 90°.
  • the inventive turbine blades assembly comprises a number of platform seal strip, as previously described, a disc and a number of blades. Each blade comprises a blade platform. The blades are connected to the disc, for example loaded onto the disc. Each seal strip is placed in a gap between the blade platforms of adjacent blades.
  • the disc may comprise a rotation axis.
  • the platform of each blade may comprise a side surface with a surface normal which includes a right angle with the rotation axis, especially when the blade is loaded onto a disc.
  • the side surface of the platform may comprise a slot and part of the second portion of the seal strip engages in the slot.
  • the turbine blade may comprise a main platform part and a leading wall and the slot may extend along the main platform part and the leading wall.
  • the turbine blade may comprise the platform having a trailing wall and the slot extends along the main platform part and the trailing wall.
  • the slot may be continuous along a side surface defined by the main platform part and/or the leading wall and/or the trailing wall.
  • the platform may comprise a leading edge side or upstream side and a trailing edge side or downstream side.
  • the slot may extend up to the trailing edge side or downstream side.
  • leading edge side of the platform is defined such that it corresponds to the leading edge of the aerofoil portion of the blade and the trailing edge side of the platform is defined such that it corresponds to the trailing edge of the aerofoil portion of the blade.
  • the disc can comprise a front face or upstream side and a rear face or downstream side, which are defined with respect to a hot gas flow through the turbine.
  • a first cover plate or cover disc may be attached to the rear face of the turbine disc and/or a second cover plate may be attached to the front face of the turbine disc.
  • Adding cover plates or cover discs to the front and/or rear face of the turbine disc assembly allows for making more efficient use of the cooling air.
  • the cover plates or discs contain and direct cooling air in a more efficient manner than previously used, since they may comprise fluid channels for guiding cooling air.
  • the seal strip may comprise a nose which engages into a groove of the first cover plate or into a groove the second cover plate.
  • the seal strip comprises a first nose at the first portion and a second nose at the second portion. The first nose can engage into a groove of the cover plate at the front face and the second nose can engage into a groove of the cover plate at the rear face.
  • only one seal strip is located between two adjacent blades. This reduces the number of necessary components to be assembled and reduces the time for assembling.
  • the cover discs may comprise a seal means, for example a C-seal or O-ring or rope seal as appropriate.
  • the seal means my comprise metal or may consist of metal.
  • the seal means may be located such that it faces the leading edge side or the trailing edge side of the platform of the blade or the blade root.
  • the inventive gas turbine comprises a turbine blade assembly as previously described. It generally has the same properties and advantages as described in conjunction with the inventive seal strip and the inventive turbine blade assembly.
  • the inventive method for assembling a turbine blade assembly is related to a turbine blade assembly as previously described.
  • the method comprises the steps of loading the number of blades onto the disc leaving a gap between the platforms of adjacent blades, inserting a seal strip into the gap between the platforms of two adjacent blades, and retaining the seal strips by attaching a first cover plate to the disc.
  • a second cover plate for example a forward cover disc, may be attached to the disc before loading the blades onto the turbine disc. If the second cover plate is identical with a forward cover disc, than the first cover plate is identical with an aft cover disc.
  • the forward cover disc may be connected to the front face of the disc and the aft cover disc may be connected to the rear face of the disc.
  • a seal strip with at least one nose is used and the at least one nose is inserted into a groove in the first or in the second cover plate.
  • the seal strip comprises two noses and a first nose is inserted into a groove in the forward cover disc and the second nose is inserted into a groove in the aft cover disc.
  • a seal means can be positioned between the first cover plate, for example the aft cover disc, and the turbine disc. Additionally or alternatively a seal means can be positioned between the second cover plate, for example a forward cover disc, and the turbine disc.
  • a C-seal or an O-ring or a rope seal can be used as seal means.
  • the used seal means may comprise metal or may consist of metal.
  • the present invention improves the sealing of turbine hot blade components.
  • the improved sealing includes improved retention of the cooling fluid supplied to the blade under platform cavity to prevent the coolant escaping the cavity via the gap.
  • more of the cooling fluid is used for better cooling the blade.
  • the improved sealing includes preventing hot working gases ingressing the blade under platform cavity and mixing with and reducing the effectiveness of the cooling fluid.
  • FIG. 1 schematically shows a gas turbine.
  • FIG. 2 schematically shows part of an inventive turbine blade assembly in a sectional and perspective view.
  • FIG. 3 schematically shows the cooling fluid flow part of an inventive turbine blade assembly a sectional and perspective view.
  • FIG. 4 schematically shows an inventive platform seal strip 1 in a perspective view.
  • FIGS. 5 and 6 schematically show part of an inventive turbine blade assembly in a perspective view during the insertion of the platform seal strip.
  • FIG. 7 schematically shows part of an inventive turbine blade assembly in a sectional and perspective view when the assembling process is finished.
  • FIG. 1 schematically shows a gas turbine.
  • a gas turbine comprises a rotation axis with a rotor.
  • the rotor comprises a shaft 107 .
  • a suction portion with a casing 109 a compressor 101 , a combustion portion 151 , a turbine 105 and an exhaust portion with a casing 190 are located.
  • the combustion portion 151 communicates with a hot gas flow channel which may have a circular cross section, for example.
  • the turbine 105 comprises a number of turbine stages. Each turbine stage comprises rings of turbine blades. In flow direction 103 of the hot gas in the hot gas flow channel a ring of turbine guide vanes 117 is followed by a ring of turbine rotor blades 115 .
  • the turbine guide vanes 117 are connected to an inner casing of a stator.
  • the turbine rotor blades 115 are connected to the rotor.
  • the rotor is connected to a generator, for example.
  • FIG. 2 schematically shows part of an inventive turbine blade assembly in a sectional and perspective view.
  • the turbine blade assembly comprises a disc 12 , a number of rotor blades 151 , a first cover plate or aft cover disc 7 and a second cover plate or forward cover disc 6 .
  • the rotor blades 151 are mounted onto the disc 12 .
  • the disc 12 comprises a front face or upstream side 26 and a rear face or downstream side 27 , which are defined with respect to the hot gas flow direction 103 .
  • the forward cover disc 6 is connected to the front face 26 .
  • the aft cover disc 7 is connected to the rear face 27 .
  • the aft cover disc 7 is fitted after the blades 151 and seal strips 1 are loaded to the disc 12 .
  • a seal means 8 is placed between the forward cover disc 6 and the blades 151 , for example part of the platforms 3 of the blades, especially for preventing a hot gas flow into the blade root cavity 15 .
  • a further seal means 16 is placed between the forward cover disc 6 and the front face 26 of the disc 12 .
  • the seal means 8 and/or the seal means 16 may comprise metal or may consist of metal.
  • the seal means 8 and/or seal means 16 may be a C-seal or an O-ring or a rope seal.
  • a seal means 9 is positioned, for example to prevent a hot gas flow into the blade root cavity 15 .
  • the seal means 9 may have the same properties as the previously described seal means 8 or seal means 16 .
  • the blades 151 comprise an aerofoil portion 2 , a blade platform 3 and a blade root 19 , which is not shown in FIG. 2 .
  • the blade platform 3 is located between the aerofoil portion 2 and the blade root 19 .
  • the blade aerofoil portion 2 comprises a leading edge 4 and a trailing edge 5 .
  • a small gap occurs between the platforms 3 of the adjacent blades 151 .
  • an inventive platform seal strip 1 is inserted between the adjacent platforms 3 .
  • only one platform seal strip 1 is inserted between each two adjacent platforms 3 .
  • FIG. 3 schematically shows the cooling fluid flow in part of an inventive turbine blade assembly in a sectional and perspective view.
  • the blades 151 comprise a blade under platform cavity 15 , which is located inside the blade 151 below the platform 3 towards the blade root 19 .
  • cooling fluid for example cooling air, can be guided into the aerofoil portion 2 .
  • a flow channel 17 is formed, through which cooling fluid can be guided into the blade under platform cavity 15 .
  • the direction of the cooling fluid flow is indicated by arrows 18 .
  • the platform portion 3 of the blade 151 comprises a leading edge side 21 , corresponding to the leading edge of the aerofoil portion 4 , a trailing edge side 22 , corresponding to the trailing edge 5 of the aerofoil portion 2 , and a side surface 23 .
  • the side surfaces 23 of adjacent blades 151 are facing towards each other.
  • the side surface 23 comprises a surface normal 25 .
  • the surface normal 25 includes a right angle with a rotation axis 102 of the disc 12 .
  • the rotation axis 102 of the disc 12 may correspond to the rotation axis 102 of a gas turbine.
  • the blade 151 further comprises a leading wall 80 and a trailing wall 82 as seen in FIG. 3 . It can also be said that the leading wall 80 and the trailing wall 82 form extensions of the platform 3 .
  • the platform 3 has a main platform part 3 A that extends both generally axially and circumferentially and along with a neighbouring platform, defines a gas-wash surface at least between adjacent blades.
  • the main platform part 3 A extends generally between the leading edge side 21 and the trailing edge side 22 .
  • the leading wall 80 is located at the forward or upstream part of the blade 151 and the trailing wall 82 is located at the rearward or downstream part of the blade 151 .
  • the leading wall 80 and trailing wall 82 are located radially inwardly of the main platform part 3 A.
  • the leading wall 80 extends from the main platform part 3 A, in this example from about the leading edge side 21 , and in a generally radially inward direction and towards the disc 12 .
  • the trailing wall 82 extends from the main platform part 3 A, in this example from a downstream or rearward part of the platform, and in a generally radially inward direction and towards the disc 12 .
  • the main platform part 3 A, the leading wall 80 and the trailing wall 82 at least partly define the blade under platform cavity 15 .
  • a small gap occurs between the respective platforms 3 , the leading walls 80 and the trailing walls 82 of the adjacent blades 151 .
  • This small gap is referred to as a circumferential gap.
  • a second gap 84 occurs between a radially inner part of the leading wall 80 and the disc 12 .
  • cooling fluid flow 18 enters the blade under platform cavity 15 via the second gap.
  • a third gap 86 occurs between a radially inner part of the trailing wall 80 and the disc 12 .
  • cooling fluid flow 18 can exit the blade under platform cavity 15 via the third gap 86 to cool the downstream face 27 of the disc.
  • the second and third gaps may be referred to as radial gaps 84 , 86 .
  • the side surface 23 of the platform 3 including the main platform part 3 A, the leading walls 80 and the trailing walls 82 comprise a slot 24 .
  • the slot runs nearly parallel to the rotation axis 102 along the main platform part 3 A and extends up to the trailing edge side 22 .
  • Part of the platform seal strip 1 engages into the slot 24 .
  • the platform seal strip 1 comprises a first nose or rebate 13 and a second nose or rebate 14 .
  • the first nose 13 engages into a corresponding groove 10 in the forward cover disc 6 .
  • the second nose 14 engages into a corresponding groove 11 in the aft cover disc 7 . This provides a very effective seal between the forward cover disc 6 , the platform 3 and the aft cover disc 7 , as well as between adjacent blade platforms 3 .
  • FIG. 4 schematically shows an inventive platform seal strip 1 in a perspective view.
  • the seal strip 1 comprises a first portion 31 and a second portion 32 .
  • the first portion 31 has a width 33 , advantageously a constant width.
  • the second portion 32 has a width 34 , preferably a constant width, which is larger than the width 33 of the first portion 31 .
  • the platform seals strip 1 further comprises an upper side 36 and a lower side 37 .
  • the first portion 31 comprises a bending towards the lower side 37 .
  • the bending forms a convex surface portion 41 of the upper side 36 and a concave surface portion 43 of the lower side 37 .
  • the second portion 32 also comprises a bending towards the lower side 37 .
  • the bending forms a convex surface portion 42 of the upper side 36 and a concave surface portion 44 of the lower side 37 .
  • the first portion 31 comprises an upper side surface portion with an surface normal 71 and the second portion 32 comprises an upper side surface portion with a surface normal 72 , which includes an angel a having a value between 0° and 180° (0° ⁇ a ⁇ 180°).
  • the angle a has a value between 160° and 180°.
  • the platform seal strip 1 has a shape of a U in a side view, as for example shown in FIG. 3 .
  • the first portion 31 further comprises a nose 13 .
  • the nose 13 is bent such that the upper side 36 comprises a concave surface portion 53 and the lower side 37 comprises a convex surface portion 51 .
  • the second portion 32 also comprises a nose 14 , which is at least partially bent towards the upper side 36 .
  • the bending of the nose 14 forms a concave surface portion 54 at the upper side 36 and a convex surface portion 52 at a lower side 37 .
  • the noses 13 and 14 may have a surface portion with a surface normal.
  • the surface normal 73 of the nose 14 is shown as example.
  • the first portion or the second portion may comprise a surface adjacent to the nose.
  • This surface may have a surface normal, for example the surface normal 72 of the second portion, which includes an angle ⁇ with the surface normal 73 of the nose portion 14 between 0° and 180°, which means 0° ⁇ 180°, and in an advantageous embodiment between 60° and 90°.
  • the first portion 31 of the seal strip 1 may be referred to as a leading portion 31 and which engages into the part of the slot 24 defined by the leading wall 80 .
  • the leading portion 31 extends in a generally radially inward or downward direction from the second portion 32 .
  • the nose 13 extends from a radially inward part of the leading portion 31 and in use extends under or radially inwardly of the leading wall 80 to engage the corresponding groove 10 in the forward cover disc 6 .
  • the nose 13 extends into or through the second gap 84 .
  • the nose 13 may extend through the leading wall 80 to engage the forward cover disc 6 .
  • the second portion 32 may be referred to as a main portion 32 and the portion of the seal strip 1 that engages the slot 24 defined in the trailing wall 82 may be referred to as a third portion 38 .
  • the third portion 38 may be referred to as a trailing portion 38 of the seal strip.
  • the third portion 38 comprises the nose 14 at its radially inward end.
  • a third portion 31 may be referred to as a trailing portion 31 and which engages into the part of the slot 24 defined by the trailing wall 82 .
  • the leading portion 31 extends in a generally radially inward or downward direction from the second portion 32 .
  • the nose 14 extends from a radially inward part of the trailing portion 38 and in use extends to engage the corresponding groove 11 in the rear cover disc 7 .
  • the slot 24 runs out of the trailing wall 82 and creates an opening positioned radially outwardly of the radially inward end of the trailing wall 82 .
  • the seal strip 1 can therefore extend rearward out of the downstream face of the trailing wall 82 and engage the groove 11 .
  • the slot 24 may extend to the radially inward end of the trailing wall 82 where the nose 14 may extend into or through the third gap.
  • leading and trailing portions 31 , 38 are shown as extending from the second portion 32 in a generally radially inward direction and it should be appreciated that this direction is not limited to perpendicular to the axis 102 and may typically be angled relative to a radial line from the axis 102 .
  • the slot 24 is continuous across the circumferentially facing side surface 23 of the main platform part 3 A and the leading wall 80 .
  • the slot 24 may also be continuous across the circumferentially facing side surface 23 of the main platform part 3 A and the trailing walls 82 .
  • the trailing portion 38 of the seal strip is shown reducing in width between the main platform part 3 A and the nose 14 .
  • the reduction in width may be a regular or irregular taper.
  • the noses 13 and 14 are also shown tapering to their free ends; however, the noses 13 , 14 may have a constant width.
  • the noses 13 , 14 may have a width equal to or less than the leading or trailing portions 31 , 38 respectively.
  • the noses 13 , 14 may have a width equal to or less than the leading or trailing portions 31 , 38 respectively at their radially inward most part.
  • the width of the first portion is constant and/or the width of the second portion is constant.
  • the first portion may change in width between the main platform part 3 A and the nose 13 .
  • This change in width may be a regular or irregular taper. The taper may be towards the nose 13 .
  • FIGS. 5 and 6 schematically show part of an inventive turbine blade assembly in a perspective view during the insertion of the platform seal strip.
  • FIG. 7 schematically shows part of an inventive turbine blade assembly in a sectional and perspective view when the assembling process is finished.
  • the forward cover disc 6 was attached to the disc 12 .
  • the blades 151 were loaded onto the disc 12 , for example by inserting at least part of the blade root 19 into corresponding grooves 20 in the disc 12 .
  • Between adjacent platforms 151 a gap is left.
  • the seal strips 1 are inserted into the gap between the platforms 3 of adjacent blades 151 .
  • FIGS. 5 and 6 This is schematically shown in FIGS. 5 and 6 .
  • the first portion 31 is inserted into the blade root cavity 15 via an opening between two adjacent blades 151 close to the slot 24 in the platforms 3 . In doing so the seal strip 1 is canted over or turned.
  • the seal strip 1 is turned back into a correct position.
  • the second portion 32 and part of the transition portion 35 slide into the slot 24 .
  • the finished insertion is shown in FIG. 7 .
  • Part of the second portion 32 and part of the transition portion 35 of the seals strip 1 engages into the slots 24 of the adjacent blades 151 .
  • the nose 13 of the first portion 31 is inserted into the corresponding groove 10 in the forward cover disc 6 .
  • a first cover plate, in FIG. 7 the aft cover disc 7 , is attached to the disc 12 .
  • the nose 14 of the second portion 32 of the seal strip 1 is inserted or engages into the corresponding groove 11 of the aft cover disc 7 .
  • the present invention uses a single piece seal strip 1 to overcome inter seal leakage in order to make more efficient use of the cooling air.
  • Cover discs 6 and 7 have been added to the front face 26 and the rear face 27 of the, for example CT, disc assembly.
  • the cover discs 6 and 7 can contain and direct cooling air in a more efficient manner then in previously known solutions.
  • the present layout gives the opportunity to improve the sealing at the blade platform as shown in FIGS. 3 and 5 to 7 .
  • the seal strip 1 is a single piece, for example of metal, eliminating leaks and joint inter faces and making assembly easier.
  • the assembly of the single piece strip is allowed due to profile of the strip as shown in FIG. 4 .
  • the narrow nose 13 allows it to be inserted into the gap between adjacent blades 151 .
  • the wider portion 32 of the strip then engages in the seal groove 24 machined into the side 23 of each blade 151 , directly beneath the platform 3 .
  • the seal strip 1 is then pushed fully into the gap as shown in FIGS. 5 to 7 . Following the insertion of seal strips 1 the aft cover plate 7 is attached to retain the strip 1 .
  • an embodiment of the invention is related to a platform seal strip 1 , in particular for use in a gas turbine blade assembly, the platform seal strip 1 having sections that are substantially planar and sections that are curved.
  • the platform seal strip 1 comprises an upper side 36 and a lower side 37 .
  • the platform seal strip 1 particularly being a sheet of metal that is three-dimensionally formed.
  • the platform seal strip 1 comprises a first portion 31 —the first portion 31 being substantially planar—and a second portion 32 —the second portion 32 being substantially planar—, the width 33 of the first portion 31 being smaller than the width 34 of the second portion 32 .
  • the first portion 31 and the second portion 32 are connected via bent or curved sections, such that the upper side 36 comprises a convex surface portion 41 , 42 and the lower side 37 comprises a concave surface portion 43 , 44 .
  • the convex surface portion 41 and the concave surface portion 43 are opposite surfaces of the platform seal strip 1 .
  • the convex surface portion 42 and the concave surface portion 44 are also opposite surfaces of the platform seal strip 1 .
  • a first bend defined by the convex surface portion 42 and the concave surface portion 44 may be sharper than a second bend defined by the convex surface portion 41 and the concave surface portion 43 .
  • the first bend may have a substantially sharp edge whereas the second bend defines a smooth transition between the first portion 31 and the second portion 32 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/405,826 2012-06-26 2013-06-12 Platform seal strip, turbine blade assembly and method for assembling it Abandoned US20150125301A1 (en)

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EP12173650.8 2012-06-26
EP20120173650 EP2679770A1 (de) 2012-06-26 2012-06-26 Dichtstreifen für Turbinenschaufelplattform
PCT/EP2013/062115 WO2014001084A1 (en) 2012-06-26 2013-06-12 Platform seal strip, turbine blade assembly and method for assembling it

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150354379A1 (en) * 2014-06-05 2015-12-10 Honeywell International Inc. Dual alloy turbine rotors and methods for manufacturing the same
US20160032751A1 (en) * 2014-07-31 2016-02-04 United Technologies Corporation Reversible blade rotor seal
US20170159440A1 (en) * 2015-12-04 2017-06-08 General Electric Company Turbomachine blade cover plate having radial cooling groove
US10655489B2 (en) 2018-01-04 2020-05-19 General Electric Company Systems and methods for assembling flow path components
US20210115804A1 (en) * 2019-10-22 2021-04-22 United Technologies Corporation Vane with l-shaped seal
US20210189887A1 (en) * 2019-12-20 2021-06-24 General Electric Company Rotor blade sealing structures
US11162366B2 (en) * 2019-02-19 2021-11-02 Safran Aircraft Engines Rotor disc with axial stop of the blades, assembly of a disc and a ring and turbomachine
US11486252B2 (en) 2018-09-04 2022-11-01 Safran Aircraft Engines Rotor disc with axial retention of the blades, assembly of a disc and a ring, and turbomachine

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2886800A1 (de) * 2013-12-18 2015-06-24 Rolls-Royce Deutschland Ltd & Co KG Leitschaufelanordnung für eine Gasturbine und zugehöriger Streifendichtung
US9719427B2 (en) * 2014-01-21 2017-08-01 Solar Turbines Incorporated Turbine blade platform seal assembly validation
EP3034805B1 (de) * 2014-12-17 2019-11-13 United Technologies Corporation Dichtstreifen mit einem konischen radialabschnitt und abschnitt eines gasturbinenmotors mit einem solchen dichtstreifen
US9822644B2 (en) 2015-02-27 2017-11-21 Pratt & Whitney Canada Corp. Rotor blade vibration damper
US10196915B2 (en) 2015-06-01 2019-02-05 United Technologies Corporation Trailing edge platform seals
US10683756B2 (en) * 2016-02-03 2020-06-16 Dresser-Rand Company System and method for cooling a fluidized catalytic cracking expander
EP3438410B1 (de) 2017-08-01 2021-09-29 General Electric Company Dichtungssystem für eine rotationsmaschine
FR3092863B1 (fr) * 2019-02-15 2021-01-22 Safran Aircraft Engines Roue de turbine pour turbomachine d’aéronef comprenant des organes d’étanchéité de cavités inter-aubes

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5460489A (en) * 1994-04-12 1995-10-24 United Technologies Corporation Turbine blade damper and seal
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US20060056974A1 (en) * 2004-09-13 2006-03-16 Jeffrey Beattie Turbine blade nested seal damper assembly
US20090116953A1 (en) * 2007-11-02 2009-05-07 United Technologies Corporation Turbine airfoil with platform cooling
US8011892B2 (en) * 2007-06-28 2011-09-06 United Technologies Corporation Turbine blade nested seal and damper assembly
US8613599B2 (en) * 2007-10-25 2013-12-24 Siemens Aktiengesellschaft Turbine blade assembly and seal strip

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3834831A (en) 1973-01-23 1974-09-10 Westinghouse Electric Corp Blade shank cooling arrangement
GB1460714A (en) 1973-06-26 1977-01-06 Rolls Royce Bladed rotor for a gas turbine engine
FR2710103B1 (fr) * 1993-09-16 1995-10-20 Snecma Flasque de rotor de turbomachine et assemblage de ce flasque avec un rotor.
US6561764B1 (en) 1999-03-19 2003-05-13 Siemens Aktiengesellschaft Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms
EP2053285A1 (de) 2007-10-25 2009-04-29 Siemens Aktiengesellschaft Turbinenschaufelanordnung
EP2053286A1 (de) 2007-10-25 2009-04-29 Siemens Aktiengesellschaft Dichtstreifen und Turbinenschaufelanordnung

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5460489A (en) * 1994-04-12 1995-10-24 United Technologies Corporation Turbine blade damper and seal
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US20060056974A1 (en) * 2004-09-13 2006-03-16 Jeffrey Beattie Turbine blade nested seal damper assembly
US8011892B2 (en) * 2007-06-28 2011-09-06 United Technologies Corporation Turbine blade nested seal and damper assembly
US8613599B2 (en) * 2007-10-25 2013-12-24 Siemens Aktiengesellschaft Turbine blade assembly and seal strip
US20090116953A1 (en) * 2007-11-02 2009-05-07 United Technologies Corporation Turbine airfoil with platform cooling

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9724780B2 (en) * 2014-06-05 2017-08-08 Honeywell International Inc. Dual alloy turbine rotors and methods for manufacturing the same
US10399176B2 (en) 2014-06-05 2019-09-03 Honeywell International Inc. Dual alloy turbine rotors and methods for manufacturing the same
US20150354379A1 (en) * 2014-06-05 2015-12-10 Honeywell International Inc. Dual alloy turbine rotors and methods for manufacturing the same
US20160032751A1 (en) * 2014-07-31 2016-02-04 United Technologies Corporation Reversible blade rotor seal
US10030530B2 (en) * 2014-07-31 2018-07-24 United Technologies Corporation Reversible blade rotor seal
CN106968719A (zh) * 2015-12-04 2017-07-21 通用电气公司 具有径向冷却凹槽的涡轮机叶片盖板
JP2017101670A (ja) * 2015-12-04 2017-06-08 ゼネラル・エレクトリック・カンパニイ 半径方向冷却溝を有するターボ機械ブレードのカバープレート
US10066485B2 (en) * 2015-12-04 2018-09-04 General Electric Company Turbomachine blade cover plate having radial cooling groove
US20170159440A1 (en) * 2015-12-04 2017-06-08 General Electric Company Turbomachine blade cover plate having radial cooling groove
US10655489B2 (en) 2018-01-04 2020-05-19 General Electric Company Systems and methods for assembling flow path components
US11486252B2 (en) 2018-09-04 2022-11-01 Safran Aircraft Engines Rotor disc with axial retention of the blades, assembly of a disc and a ring, and turbomachine
US11162366B2 (en) * 2019-02-19 2021-11-02 Safran Aircraft Engines Rotor disc with axial stop of the blades, assembly of a disc and a ring and turbomachine
US20210115804A1 (en) * 2019-10-22 2021-04-22 United Technologies Corporation Vane with l-shaped seal
US11125093B2 (en) * 2019-10-22 2021-09-21 Raytheon Technologies Corporation Vane with L-shaped seal
US20210189887A1 (en) * 2019-12-20 2021-06-24 General Electric Company Rotor blade sealing structures
US11566528B2 (en) * 2019-12-20 2023-01-31 General Electric Company Rotor blade sealing structures

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EP2864593A1 (de) 2015-04-29
EP2679770A1 (de) 2014-01-01

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