EP3388634B1 - Gasturbinenschaufel mit haltermontagestruktur und gasturbine damit - Google Patents

Gasturbinenschaufel mit haltermontagestruktur und gasturbine damit Download PDF

Info

Publication number
EP3388634B1
EP3388634B1 EP17192813.8A EP17192813A EP3388634B1 EP 3388634 B1 EP3388634 B1 EP 3388634B1 EP 17192813 A EP17192813 A EP 17192813A EP 3388634 B1 EP3388634 B1 EP 3388634B1
Authority
EP
European Patent Office
Prior art keywords
retainer
turbine blade
gas turbine
blade assembly
insertion hole
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.)
Active
Application number
EP17192813.8A
Other languages
English (en)
French (fr)
Other versions
EP3388634A1 (de
Inventor
Sungchul Jung
Dongwoo HAM
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.)
Doosan Heavy Industries and Construction Co Ltd
Original Assignee
Doosan Heavy Industries and Construction Co Ltd
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 Doosan Heavy Industries and Construction Co Ltd filed Critical Doosan Heavy Industries and Construction Co Ltd
Publication of EP3388634A1 publication Critical patent/EP3388634A1/de
Application granted granted Critical
Publication of EP3388634B1 publication Critical patent/EP3388634B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • 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
    • 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
    • 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
    • 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
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present disclosure relates generally to a gas turbine blade assembly having retainer assembling structure, and a gas turbine having the same. More particularly, the present disclosure relates to a gas turbine blade assembly having a structure capable of being easily disassembled and assembled and achieving sealing, and a gas turbine having the same.
  • a turbine is a mechanical device that obtains torque by impulsive force or reaction force using flow of compressible fluid such as steam or gas. It is called as a steam turbine when steam is used and a gas turbine when combustion gas is used.
  • a thermodynamic cycle of the gas turbine is the Brayton Cycle, which is as follows: a compressor for sucking and boosting air from the atmosphere and supplying combustion air to a combustor; the combustor for mixing and combusting the introduced compressed air with fuel to produce a combustion gas of high energy; and a turbine for converting the high temperature and high pressure combustion gas from the combustor into mechanical energy when the combustion gas expands to apply the impulsive and reaction force to rotating blades of the turbine.
  • the mechanical energy obtained from the turbine is supplied to the compressor (approximately 60% of the total turbine power) required to compress the air and the remainder is used to drive a generator to produce power.
  • the operation principle of the gas turbine is the following four steps: compression, heating, expansion, and heat dissipation. That is, the air in the atmosphere is sucked first, compressed by the compressor, then sent to the combustor to generate high temperature and high pressure gas to operate the turbine, and the exhaust gas is discharged to the atmosphere.
  • a retainer is provided adjacent to a blade and a rotating disk to form a sealing and flow path for the cooling air flowing from the rotating disk.
  • FIGS. 1 and 2 are sectional views partially showing a gas turbine blade assembly provided with a retainer according to the related art.
  • the retainer is locked to the blade or to a side of the rotating disk by force fitting or by using a coupling member.
  • US 3853425 A discloses a turbine rotor blade cooling and sealing system, having an exhaust sealing and locking plate, i.e. the last plate, mounted between a blade platform groove and a disc groove.
  • the last plate is provided with a chamfered or beveled edge on one face thereof, in order that it may pass a ledge of the groove of the blade platform. This allows the beveled portion to be first inserted into the groove of the disc, so that the top of the last plate can clear the ledge of the blade platform as the plate is thrust toward the downstream face of blade root. After the last plate is located between grooves, it is raised into the groove of the blade platform. The last plate is then secured in this position by lock screws or bolts, threaded into the last plate and disposed within recesses provided in the downstream face of the blade root.
  • a turbomachinery blade retention system comprising: a disk, a plurality of blades, each having a dovetail disposed in one of an array of slots formed in the outer periphery of the disk, an annular inner retainer attached to the disk, and a plurality of arcuate blade retainers, the blade retainers being secured to the inner retainer by a hooked rabbet joint.
  • the retainer according to the related art is problematic in that it requires a very complicated structure to form the cooling gas sealing and the flow path, so it is not easy to manufacture and install.
  • a gas turbine blade assembly as an assembly provided with a plurality of gas turbine blades on an outer circumferential surface of a rotating disk along a circumferential direction to be spaced apart from each other at predetermined intervals, the gas turbine blade assembly including: a retainer insertion hole provided in a blade-fixing end, and depressed by a predetermined depth to correspond to a lower end of a retainer; a retainer coupler provided at a lower end of each of the gas turbine blades, and depressed by a predetermined depth to correspond to an upper end of the retainer; and a coupling member coupled at a location adjacent to the retainer coupler to couple the retainer and each of the gas turbine blades together.
  • each of the gas turbine blades may be mounted to a dovetail slot provided on the outer circumferential surface of the rotating disk along the circumferential direction, and the gas turbine blades may be aligned in an axial direction by the retainer.
  • the rotating disk may be provided with a protruding structure protruding by a predetermined length at a side thereof, and the protruding structure may be provided with the retainer insertion hole at an upper surface thereof.
  • the protruding structure may be provided along the circumferential direction of the rotating disk, and may be in an annular shape in a plan view.
  • the retainer insertion hole may be provided with a bearing surface on an inner surface thereof to be in surface contact with the retainer.
  • the lower end of the retainer may be spaced apart from a bottom surface of the retainer insertion hole at a predetermined distance, and the depth of the retainer coupler may be equal to or less than the distance between the lower end of the retainer and the bottom surface of the retainer insertion hole.
  • the gas turbine blade assembly may further include a coupling member insertion hole provided at a location adjacent to the retainer coupler at the lower end of each of the gas turbine blades, and depressed to correspond to the coupling member.
  • a slot groove in a shape corresponding to an outer surface of the coupling member may be provided between the coupling member insertion hole and the retainer coupler.
  • the slot groove may be provided in a direction parallel to an extension direction of the retainer.
  • the coupling member may be in a bolt structure, with a bolt head thereof inserted into the coupling member insertion hole, and with a threaded part thereof protruding by a predetermined length in a direction toward the retainer coupler to be engaged with the upper end of the retainer.
  • the threaded part of the coupling member may be engaged with a nut to couple the coupling member and the retainer together, and an outer surface of the nut may be formed as curved surface continuous with an outer surface of the lower end of each of the gas turbine blades.
  • each of the gas turbine blades may be provided with a sealing protrusion protruding by a predetermined length in a direction toward a neighboring gas turbine blade.
  • the upper end of the retainer may be provided with an auxiliary sealing protrusion protruding by a predetermined length to correspond to the sealing protrusion.
  • a side surface of the retainer may be provided with a support protrusion extending in a direction toward the lower end of each of the gas turbine blades and having a contact surface corresponding to a side surface of each of the gas turbine blades, with a sealing wire mounted to the contact surface of the support protrusion.
  • a gas turbine having the gas turbine blade assembly.
  • the gas turbine includes a blade assembly provided with a plurality of gas turbine blades on an outer circumferential surface of a rotating disk along a circumferential direction to be spaced apart from each other at predetermined intervals, wherein the blade assembly includes: a retainer insertion hole provided in a blade-fixing end, and depressed by a predetermined depth to correspond to a lower end of a retainer; a retainer coupler provided at a lower end of each of the gas turbine blades, and depressed by a predetermined depth to correspond to an upper end of the retainer; and a coupling member coupled at a location adjacent to the retainer coupler to couple the retainer and each of the gas turbine blades together.
  • the rotating disk may be provided with a protruding structure protruding by a predetermined length at a side thereof, and the protruding structure may be provided with the retainer insertion hole at an upper surface thereof.
  • the protruding structure may be provided along the circumferential direction of the rotating disk, and may be in an annular shape in plan view.
  • the lower end of the retainer may be spaced apart from a bottom surface of the retainer insertion hole at a predetermined distance, and the depth of the retainer coupler may be equal to or less than the distance between the lower end of the retainer and the bottom surface of the retainer insertion hole.
  • the gas turbine blade assembly may further include a coupling member insertion hole provided at a location adjacent to the retainer coupler at the lower end of each of the gas turbine blades, and depressed to correspond to the coupling member.
  • an exemplary gas turbine blade assembly of the present disclosure provided with a retainer insertion hole, a retainer coupler, and a coupling member having predetermined structures, it is possible to provide a gas turbine blade assembly having a structure capable of being easily disassembled and assembled and may achieve complete sealing, and a gas turbine having the same.
  • an exemplary gas turbine blade assembly of the present disclosure that includes a protruding structure having a predetermined structure is provided at a side of a rotating disk, with the protruding structure provided with the retainer insertion hole at an upper surface thereof, it is possible to facilitate easy assembly and disassembly and possible to achieve complete sealing.
  • an exemplary gas turbine blade assembly of the present disclosure that includes a retainer insertion hole provided with a bearing surface on an inner surface thereof to be in surface contact with the retainer, it may be possible to achieve complete sealing of the gas turbine blade, the rotating disk, and the retainer.
  • the lower end of the retainer is spaced apart from a bottom surface of the retainer insertion hole at a predetermined distance, and the depth of the retainer coupler is equal to or less than the distance between the lower end of the retainer and the bottom surface of the retainer insertion hole, assembly and disassembly of the retainer may be performed more easily than the related art.
  • an exemplary gas turbine blade assembly of the present disclosure that includes a coupling member insertion hole, a coupling member, and a retainer coupler having predetermined structures, it is possible to easily assemble and disassemble the retainer, and possible to achieve a stable coupling structure.
  • an exemplary gas turbine blade assembly of the present disclosure that includes a slot groove in a predetermined shape provided between the coupling member insertion hole and the retainer coupler, and the retainer and the gas turbine blade are coupled together after the coupling member is mounted by using the slot groove, it is possible to perform easy assembly, and possible to achieve a stable coupling structure.
  • an exemplary gas turbine blade assembly of the present disclosure that includes a sealing protrusion, an auxiliary sealing protrusion, a support protrusion, and a sealing wire having predetermined structures, it is possible to provide a structure capable of facilitating easy assembly and disassembly and may achieve complete sealing.
  • an exemplary gas turbine of the present disclosure that includes a gas turbine blade assembly having a predetermined structure, it is possible to provide a gas turbine having a structure capable of being easily disassembled and assembled and may achieve complete sealing.
  • FIG. 3 is a sectional view partially showing a gas turbine blade assembly according to an embodiment of the present disclosure.
  • a gas turbine blade assembly 100 which is as an assembly provided with a plurality of gas turbine blades 110 on an outer circumferential surface of a rotating disk 120 along a circumferential direction to be spaced apart from each other at predetermined intervals, includes a retainer insertion hole 122, a retainer coupler 112, and a coupling member 140 having predetermined structures, whereby it is possible to provide a gas turbine blade assembly having a structure capable of being easily disassembled and assembled and may achieve complete sealing, and a gas turbine having the same.
  • FIG. 4 is a partial enlarged view showing a rotating disk provided with a dovetail slot, to which the gas turbine blade according to the embodiment of the present disclosure is mounted;
  • FIG. 5 is an enlarged view of area A of FIG. 3 ;
  • FIG. 6 is a partial enlarged view showing a slot groove of a retainer shown in FIG. 3 .
  • the retainer insertion hole 122 may be provided at a side of an upper end 121 of the rotating disk, and may be depressed by a predetermined depth to correspond to a lower end of a retainer 130.
  • the rotating disk 120 may be provided with a protruding structure 124 protruding by a predetermined length at a side thereof, and the protruding structure 124 may be provided with the retainer insertion hole 122 at an upper surface thereof.
  • the protruding structure 124 may be provided along the circumferential direction of the rotating disk 120, and may be in an annular shape in a plan view.
  • the retainer insertion hole 122 may be provided with a bearing surface 125 on an inner surface thereof to be in surface contact with the retainer 130.
  • the retainer coupler 112 may be provided at a lower end of each of the gas turbine blades 110, and may be depressed by a predetermined depth to correspond to an upper end of the retainer 130.
  • the lower end of the retainer 130 is spaced apart from a bottom surface of the retainer insertion hole 122 at a predetermined distance d1, and the depth d2 of the retainer coupler 112 is equal to or less than the distance between the lower end of the retainer 130 and the bottom surface of the retainer insertion hole 122.
  • the coupling member 140 may be coupled at a location adjacent to the retainer coupler 112 to couple the retainer 130 and each of the gas turbine blades 110 together.
  • each of the gas turbine blades 110 may be mounted to a dovetail slot 123 provided on the outer circumferential surface of the rotating disk 120 along the circumferential direction.
  • the gas turbine blades 110 may be aligned in an axial direction by the retainer 130.
  • a coupling member insertion hole 113 may be provided at a location adjacent to the retainer coupler 112 at the lower end of each of the gas turbine blades 110.
  • the coupling member insertion hole 113 be in a shape corresponding to the coupling member 140.
  • a slot groove 114 in a shape corresponding to an outer surface of the coupling member 140 may be provided between the coupling member insertion hole 113 and the retainer coupler 112.
  • the slot groove 114 be provided in a direction parallel to an extension direction of the retainer 130.
  • the coupling member 140 can be easily coupled or separated using the slot groove 114, so that assembly and disassembly of the retainer can be more easily induced.
  • the coupling member 140 which is in a bolt structure, may include a bolt head 141, and a threaded part 142.
  • the bolt head 141 of the coupling member 140 be inserted into the coupling member insertion hole, and the threaded part 142 of the coupling member protrude by a predetermined length in a direction toward the retainer coupler 112 to be engaged with the upper end of the retainer 130.
  • the threaded part 142 of the coupling member 140 may be engaged with a nut 143 to couple the coupling member 140 and the retainer 130 together.
  • an outer surface of the nut 143 is formed as a curved surface 145 continuous with an outer surface of the lower end of each of the gas turbine blades 110.
  • FIG. 7 is a sectional view partially showing a gas turbine blade assembly according to another embodiment of the present disclosure.
  • the gas turbine blade assembly 100 may further include a sealing protrusion 115 that is provided at the lower end of each of the gas turbine blades 110 and protrudes by a predetermined length in a direction toward a neighboring gas turbine blade 110.
  • the upper end of the retainer 130 may be provided with an auxiliary sealing protrusion 131 protruding by a predetermined length to correspond to the sealing protrusion 115.
  • a side surface of the retainer 130 may be provided with a support protrusion 132 extending in a direction toward the lower end of each of the gas turbine blades 110 and having a contact surface corresponding to a side surface of each of the gas turbine blades 110.
  • a sealing wire 133 be mounted to the contact surface of the support protrusion 132.
  • the gas turbine blade assembly 100 of the present disclosure since it is provided with the sealing protrusion 115, the auxiliary sealing protrusion 131, the support protrusion 132, and the sealing wire 133 having predetermined structures, it is possible to provide a structure capable of facilitating easy assembly and disassembly and may achieve complete sealing.
  • the present disclosure further provides a gas turbine having the above described gas turbine blade assembly 100, in which, as shown in FIG. 8 , it is possible to provide a gas turbine having a structure capable of being easily disassembled and assembled and achieving complete sealing.
  • Figure 8A illustrates the gas turbine blade assembly 100 in an assembled state.
  • Figure 8B illustrates the removal of the nut 143 from the coupling member 140 and the displacement of the retainer 130 downwardly into the insertion hole 122.
  • Figure 8C illustrates the removal of the coupling member 140 and the retainer 130.
  • Figure 8D illustrates the gas turbine blade assembly 100 in a disassembled state. While the present disclosure has been described in conjunction with exemplary embodiments thereof, it is to be understood that the present description does not limit the present disclosure to those exemplary embodiments. On the contrary, the present disclosure covers not only the exemplary embodiments, but also various alternatives, modifications, equivalents and other embodiments that may be included within the scope of the present invention as defined by the appended claims.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Claims (11)

  1. Gasturbinen-Schaufelanordnung (100), umfassend:
    eine Turbinenschaufel (110), die eine Halterkupplung (112) aufweist;
    wobei die Halterkupplung eine Tiefe (d2) hat, die sich über eine erste Strecke von einem unteren Ende der Turbinenschaufel erstreckt;
    eine Drehscheibe (120), die ein Schaufelbefestigungsende und eine Haltereinführöffnung (122) aufweist, die in dem Schaufelbefestigungsende definiert ist, wobei eine Tiefe der Haltereinführöffnung (122) zumindest der ersten Strecke entspricht;
    einen Halter (120), der zum Anordnen in der Haltereinführöffnung (122) bemessen ist;
    eine Verbindungselement-Einführöffnung (113), die an einer zu der Halterkupplung (112) benachbarten Position an einem unteren Ende der Turbinenschaufel (110) vorgesehen ist;
    ein Verbindungselement (140), das zum Anordnen an einer zu der Halterkupplung (112) benachbarten Position konfiguriert ist, um den Halter (130) und die Turbinenschaufel (110) miteinander zu verbinden, wobei das Verbindungselement (140) eine Schraube aufweist, wobei die Schraube einen Schraubenkopf (141) umfasst, der zum Anordnen in der Verbindungselement-Einführöffnung (113) konfiguriert ist, und ein Gewindeteil (142) der Schraube dafür konfiguriert ist, in einer Richtung hin zu der Halterkupplung (112) vorzustehen, um mit dem Halter (130) in Eingriff zu gehen; und
    wobei der Halter (130) eine Stecknut (114) umfasst, mit einer Form, die einer Außenfläche des Gewindeteils (142) der Schraube entspricht, und vorgesehen in einer Richtung, die zu einer Erstreckungsrichtung des Halters (130) parallel ist; und
    eine Mutter (143) für einen Eingriff mit dem Gewindeteil (142) der Schraube, um das Verbindungselement (140) mit dem Halter (130) zu verbinden.
  2. Gasturbinen-Schaufelanordnung (100) nach Anspruch 1, wobei
    die Drehscheibe (120) eine Schwalbenschwanznut (123) an einer Außenumfangsfläche aufweist,
    die Turbinenschaufel (110) zum Befestigen an der Schwalbenschwanznut (123) bedienbar ist, und
    die Turbinenschaufel (110) in einer Axialrichtung durch den Halter (130) ausgerichtet ist.
  3. Gasturbinen-Schaufelanordnung (100) nach Anspruch 1 oder 2, wobei die Drehscheibe (120) eine vorstehende Struktur (124) an einer oberen Fläche aufweist, die die Haltereinführöffnung (122) bereitstellt.
  4. Gasturbinen-Schaufelanordnung (100) nach Anspruch 3, wobei die vorstehende Struktur (124) entlang einer Umfangsrichtung der Drehscheibe (120) angeordnet ist und in einer Draufsicht eine ringförmige Form hat.
  5. Gasturbinen-Schaufelanordnung (100) nach einem der vorhergehenden Ansprüche, wobei eine Innenfläche der Haltereinführöffnung (122) eine Lagerfläche (125) aufweist, die zum Bringen in Kontakt mit dem Halter (130) bedienbar ist.
  6. Gasturbinen-Schaufelanordnung (100) nach einem der vorhergehenden Ansprüche, wobei in einem zusammengebauten Zustand ein unteres Ende des Halters (130) von einer Bodenfläche der Haltereinführöffnung (122) beabstandet ist, und
    eine Tiefe d2 der Halterkupplung (112) gleich der oder kleiner als die Strecke d1 zwischen dem unteren Ende des Halters (130) und der Bodenfläche der Haltereinführöffnung (122) ist.
  7. Gasturbinen-Schaufelanordnung (100) nach einem der Ansprüche 1 bis 6, wobei
    eine Außenfläche der Mutter (143) eine gekrümmte Fläche (145) aufweist, die einer Außenfläche eines Endes der Turbinenschaufel (110) entspricht.
  8. Gasturbinen-Schaufelanordnung (100) nach einem der vorhergehenden Ansprüche, wobei das erste Ende der Turbinenschaufel (110) einen Abdichtvorsprung (115) aufweist, der zu einer benachbarten Gasturbinenschaufel (111) hin vorsteht.
  9. Gasturbinen-Schaufelanordnung (100) nach Anspruch 8, wobei der Halter (130) einen Hilfsdichtungsvorsprung (131) aufweist, der um eine Länge vorsteht, um einer Länge des Abdichtvorsprungs (115) zu entsprechen.
  10. Gasturbinen-Schaufelanordnung (100) nach einem der vorhergehenden Ansprüche, wobei
    eine Seitenfläche des Halters (130) einen Stützvorsprung (132) aufweist, der sich in einer Richtung hin zu dem ersten Ende der Turbinenschaufel (110) erstreckt, der Halter (130) aufweist und eine Kontaktfläche, die einer Seitenfläche der Turbinenschaufel (110) entspricht, und
    ein Abdichtkabel zum Anordnen an der Kontaktfläche des Stützvorsprungs (132) konfiguriert ist.
  11. Gasturbine, umfassend:
    eine Gasturbinen-Schaufelanordnung (100) nach einem der vorhergehenden Ansprüche.
EP17192813.8A 2017-04-12 2017-09-25 Gasturbinenschaufel mit haltermontagestruktur und gasturbine damit Active EP3388634B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020170047337A KR101878360B1 (ko) 2017-04-12 2017-04-12 리테이너 조립구조를 포함하는 가스터빈 블레이드 조립체 및 이를 포함하는 가스터빈

Publications (2)

Publication Number Publication Date
EP3388634A1 EP3388634A1 (de) 2018-10-17
EP3388634B1 true EP3388634B1 (de) 2019-12-25

Family

ID=59966609

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17192813.8A Active EP3388634B1 (de) 2017-04-12 2017-09-25 Gasturbinenschaufel mit haltermontagestruktur und gasturbine damit

Country Status (4)

Country Link
US (1) US20180298766A1 (de)
EP (1) EP3388634B1 (de)
JP (1) JP6459134B2 (de)
KR (1) KR101878360B1 (de)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101882109B1 (ko) * 2016-12-23 2018-07-25 두산중공업 주식회사 가스 터빈
KR102142141B1 (ko) 2018-08-17 2020-08-06 두산중공업 주식회사 터빈, 가스 터빈, 및 터빈 블레이드 분리 방법
KR102134812B1 (ko) 2018-08-17 2020-07-16 두산중공업 주식회사 터빈, 이를 포함하는 가스 터빈, 터빈의 조립 방법, 및 터빈의 분해 방법
KR102478172B1 (ko) * 2021-02-02 2022-12-14 두산에너빌리티 주식회사 회전 기계, 이를 포함하는 가스 터빈, 회전 기계의 조립 방법

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3266770A (en) * 1961-12-22 1966-08-16 Gen Electric Turbomachine rotor assembly
US3501249A (en) * 1968-06-24 1970-03-17 Westinghouse Electric Corp Side plates for turbine blades
US3853425A (en) * 1973-09-07 1974-12-10 Westinghouse Electric Corp Turbine rotor blade cooling and sealing system
US4021138A (en) * 1975-11-03 1977-05-03 Westinghouse Electric Corporation Rotor disk, blade, and seal plate assembly for cooled turbine rotor blades
FR2502690B1 (fr) * 1981-03-27 1985-09-13 Snecma Dispositif de verrouillage d'aubes de soufflante et de fixation de capot avant d'un turboreacteur
FR2524933B1 (fr) * 1982-04-13 1987-02-20 Snecma Dispositif de verrouillage axial d'aubes de rotor de turbine ou de compresseur
JPS6151406U (de) * 1984-09-07 1986-04-07
JPS6247703U (de) * 1985-09-13 1987-03-24
FR2694046B1 (fr) * 1992-07-22 1994-09-23 Snecma Dispositif d'étanchéité et de rétention pour un rotor entaillé de brochages recevant des pieds d'aubes.
FR2715975B1 (fr) * 1994-02-10 1996-03-29 Snecma Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées.
US6884028B2 (en) * 2002-09-30 2005-04-26 General Electric Company Turbomachinery blade retention system
ATE520863T1 (de) * 2006-03-28 2011-09-15 Siemens Ag Anordnung zur axialsicherung an laufschaufeln in einem rotor sowie gasturbine mit einer solchen anordnung
EP1944471B1 (de) * 2007-01-09 2009-09-02 Siemens Aktiengesellschaft Axialer Rotorabschnitt für einen Rotor einer Turbine
US8128371B2 (en) * 2007-02-15 2012-03-06 General Electric Company Method and apparatus to facilitate increasing turbine rotor efficiency
US8727735B2 (en) * 2011-06-30 2014-05-20 General Electric Company Rotor assembly and reversible turbine blade retainer therefor
FR2982635B1 (fr) * 2011-11-15 2013-11-15 Snecma Roue a aubes pour une turbomachine
US9181810B2 (en) * 2012-04-16 2015-11-10 General Electric Company System and method for covering a blade mounting region of turbine blades
US9366151B2 (en) * 2012-05-07 2016-06-14 General Electric Company System and method for covering a blade mounting region of turbine blades
FR3025317B1 (fr) 2014-08-26 2022-09-23 Imabiotech Methode de caracterisation d'un echantillon par imagerie par spectrometrie de masse

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
JP6459134B2 (ja) 2019-01-30
US20180298766A1 (en) 2018-10-18
EP3388634A1 (de) 2018-10-17
KR101878360B1 (ko) 2018-07-13
JP2018178985A (ja) 2018-11-15

Similar Documents

Publication Publication Date Title
EP3388634B1 (de) Gasturbinenschaufel mit haltermontagestruktur und gasturbine damit
EP3339576B1 (de) Gasturbine
EP1321630B1 (de) Verbindungs- und Verriegelungssystem für die Laufschaufeln eines Axialverdichters
US6984108B2 (en) Compressor stator vane
US8425194B2 (en) Clamped plate seal
US7984548B2 (en) Method for modifying a compressor stator vane
EP3054169B1 (de) Statorschaufel-anordnung und gasturbine
EP2216505A2 (de) Turbinenabdeckplattensysteme
JP5662477B2 (ja) ガスタービンエンジンおよびメインエンジンロータの組み立ておよび分解
CN110836130B (zh) 涡轮机、燃气涡轮机及涡轮叶片分离方法
US8776347B2 (en) Tool for rotor assembly and disassembly
US11008877B2 (en) Turbine, gas turbine including the same, and method of assembling and disassembling the same
US8545184B2 (en) Locking spacer assembly
EP3339577B1 (de) Verriegelungsabstandshalter und zugehöriges montageverfahren
JP7275445B2 (ja) 回転機械、これを含むガスタービン、回転機械の組立方法
US10378383B2 (en) Alignment apparatus for coupling diaphragms of turbines
KR102031935B1 (ko) 씰플레이트, 이를 포함하는 터빈 및 가스터빈
KR102141626B1 (ko) 터빈장치
KR102405750B1 (ko) 로터 및 이를 포함하는 터보머신
RU2741685C1 (ru) Рабочее колесо ротора компрессора газотурбинного двигателя
KR20220032896A (ko) 로터 및 이를 포함하는 터보머신
KR20190096641A (ko) 연소기 및 이를 포함하는 가스터빈

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20170925

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190802

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1217339

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200115

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602017010040

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200325

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200326

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200325

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200520

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200425

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602017010040

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1217339

Country of ref document: AT

Kind code of ref document: T

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

26N No opposition filed

Effective date: 20200928

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200925

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200930

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200925

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200930

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200930

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20210925

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20191225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210925

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20230802

Year of fee payment: 7