EP3025028B1 - Aube de turbine et turbine à gaz - Google Patents

Aube de turbine et turbine à gaz Download PDF

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Publication number
EP3025028B1
EP3025028B1 EP14759175.4A EP14759175A EP3025028B1 EP 3025028 B1 EP3025028 B1 EP 3025028B1 EP 14759175 A EP14759175 A EP 14759175A EP 3025028 B1 EP3025028 B1 EP 3025028B1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
turbine
blade root
retaining
root
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.)
Not-in-force
Application number
EP14759175.4A
Other languages
German (de)
English (en)
Other versions
EP3025028A1 (fr
Inventor
Peter Schröder
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
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 Siemens AG filed Critical Siemens AG
Priority to EP14759175.4A priority Critical patent/EP3025028B1/fr
Publication of EP3025028A1 publication Critical patent/EP3025028A1/fr
Application granted granted Critical
Publication of EP3025028B1 publication Critical patent/EP3025028B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the 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
    • F01D5/30—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
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor

Definitions

  • the invention relates to a turbine blade with a turbine blade and a turbine blade root for securing the turbine blade in a turbine shaft groove of a turbine shaft, wherein the turbine blade root comprises a holding device for holding securing means for securing a flat cover element arranged on the head side on the turbine blade root.
  • the invention also relates to a gas turbine having a plurality of turbine blades and to a turbine shaft to which the turbine blades are respectively secured by means of a turbine blade root.
  • the respective turbine blade has a turbine blade root, with which it is fixed in a correspondingly formed on a turbine shaft turbine shaft groove.
  • the respective turbine blade with its turbine blade root in the axial insertion direction, which is aligned with the axis of rotation of the turbine shaft, inserted and fixed in the corresponding turbine shaft groove.
  • the turbine blade feet and the turbine shaft grooves are lined with sealing plates.
  • the sealing plates are inserted on the one hand in a circumferential groove of the turbine shaft and on the other hand secured by means of securing means to the turbine blade feet.
  • the securing means comprise at least one bolt element and a locking plate element.
  • For holding the securing means At the turbine blade roots material recesses in the form of pockets, which are introduced into the turbine blade feet, are provided. These pockets are introduced, for example, by erosion in the turbine blade feet, as in particular WO 2010/094539 A1 is known.
  • the holding plate has substantially two functional portions, namely, first, a sealing portion for sealing cooling passages located between the turbine disk and the turbine blade root, and second, a holding portion, by means of which the turbine blade can be held in position within a turbine blade receiving groove, with the retaining plate over the Seal portion is attached by means of a screwed into the turbine disk screw. By means of this screw, the retaining plate is secured, wherein the screw is screwed into a designed as a holding device internal thread. A holding device arranged on the turbine blade root for holding additional securing means is not shown there.
  • an arrangement comprising a rotor disk and a plurality of rotor blades arranged thereon, the rotor blades each having a rotor blade, a rotor blade root and a rotor blade platform disposed between the rotor blade root and the rotor blade.
  • a radially inwardly opened receiving groove for receiving a retaining ring is incorporated, by means of which an axial migration of the rotor blade from a Rotorschaufelfußability the rotor disk is prevented.
  • the receiving groove is thereby inserted into the rotor blade root, whereby the flow of forces is negatively influenced within the turbine blade.
  • the object of the invention is achieved by a turbine blade with a turbine blade and a turbine blade root for securing the turbine blade in a turbine shaft groove of a turbine shaft, wherein the turbine blade root comprises a holding device for holding securing means for securing a flat cover element arranged on the head side of the turbine blade root, wherein the Holding device is arranged starting from the outside of the turbine blade root above the surface of the turbine blade root.
  • the holding device comprises two spaced-apart holding web elements which at least partially surround a receiving space for arranging a bolt element of the securing means. Characterized in that the holding means retaining the securing means outside of the turbine blade root on this Turbine blade root is arranged, the properties of absorbing forces through specifically the turbine blade root and to pass through significantly improved.
  • the holding device is generated by an accumulation of material on the outside of this material body or of the turbine blade root.
  • head-side in the context of the invention describes the head side of the turbine blade root, which is also the short side of this turbine blade foot at the same time. Accordingly, the head side extends transversely or at right angles to the direction of insertion of the turbine blade root into a turbine shaft groove receiving the turbine blade root, the insertion direction being aligned with the direction of the rotational axis of the turbine shaft.
  • the head side is in this case preferably flat. This head side extends, for example, at right angles to a corrugated outside of a fir-tree-shaped turbine blade root.
  • cover element in the sense of the invention describes any elements by means of which both the turbine shaft in the region of its turbine shaft grooves and at least partially the turbine blade feet on the fluid inlet side of the turbine blade and / or on the fluid outlet side of the turbine blade on the turbine shaft can be covered areally.
  • a cover element preferably comprises a sealing plate for producing a lateral seal in the area of the turbine blade feet.
  • the securing means can be designed in many ways. In any case, they are different from the flat cover member educated. This means that the securing means can be fixed rotationally independently of the cover element on the holding device in the circumferential direction of the turbine shaft.
  • the securing means are plugged through the flat cover member to be supported in the holding device provided therefor.
  • the securing means comprise one or preferably at least two securing elements which can be inserted through an opening of the flat cover element.
  • Generic securing means are well known from the prior art and can be used in the present essentially. They comprise at least one bolt element and a locking plate element, which are at least partially fixed to the holding device.
  • the present holding device is a securing means holding device. This holding device is therefore not used for insertion of the flat cover.
  • the holding device provided on the turbine blade root is also arranged at a distance from a circumferential groove arranged on the turbine blade or on the turbine blade root into which the cover element can be inserted.
  • the invention is characterized in particular by a spaced from a circumferential groove for insertion of an end of a cover plate holding means, by means of which the present securing means can be fixed rotationally fixed to the turbine blade root in the circumferential direction of the turbine shaft.
  • the retainer is disposed beneath a turbine blade platform disposed between the turbine bucket blade and the turbine blade root on the turbine blade root. This means that the holding device is located on a side of the turbine blade platform facing away from the turbine blade, namely on the side on which the turbine blade root is located.
  • a particularly advantageous embodiment also provides that the holding device comprises a receiving space configured outside the turbine blade root for arranging a bolt element of the securing means.
  • this receiving space is arranged outside the turbine blade root, it is possible to dispense with a pocket which has hitherto been used and is unfavorably located in the power flow and projects into the turbine blade root.
  • the load capacity of the turbine blade can be increased positively at least in the region of the turbine blade root, or the turbine blade root can - be built smaller - with the same load capacity.
  • the holding device is arranged outside on the outside of the turbine blade root and thus protrudes from the head-side surface.
  • the holding device is arranged above the surface of the turbine blade root, starting from the outside of the turbine blade root, the space available for installation of coolant lines or the like within the turbine blade root can advantageously be increased substantially.
  • the assembly of the securing means and thus also of the cover can be particularly easily and quickly done when the holding device comprises a receiving space for arranging a bolt element of the securing means, wherein the receiving space of more than one side, preferably from three sides, is accessible.
  • the receiving space is present outside the outside of the turbine blade root. This means that the receiving space is arranged outside the material body of the turbine blade root, whereby no material removal and thus no material weakening of this turbine blade root forming material body takes place on the turbine blade root. As a result, the flow of forces within the turbine blade root can be significantly improved.
  • the receiving space is accessible at least from the head side of the turbine blade root in the direction of insertion of the turbine blade.
  • a related receiving space can be particularly easily generated on the turbine blade root, when the two holding web elements are arranged to extend parallel to each other.
  • the securing means can be set and stored very well with respect to acceleration forces acting in the circumferential direction of the turbine shaft when the two holding web elements are arranged extending in the longitudinal direction of the turbine bucket blade on the turbine blade root.
  • the two holding web elements are arranged side by side in the circumferential direction of the turbine shaft.
  • the two holding web elements are arranged perpendicular to the peripheral surface of the turbine shaft on the head side of the turbine blade root.
  • the cover can be advantageously supported on the present holding device.
  • the cover element can be secured very reliably by means of the securing elements on the turbine blade, if the two holding web element are arranged radially above the peripheral surface of the turbine shaft.
  • a significantly improved support of the cover element on the turbine blade root can be achieved if the two retaining web elements have a length which is greater than their height and / or thickness. By means of such a length, an elongated support surface for the cover element can additionally be formulated on the holding device.
  • the holding device can in particular be mechanically reworked easily if the two holding web elements are arranged on the short side of the turbine blade root.
  • the holding device arranged outside the turbine blade root can be easily integrated on an arrangement of a multiplicity of turbine blades and a turbine shaft.
  • the holding of the securing means on the holding device can be further simplified if the two holding web elements are chamfered on their mutually facing web sides at the longitudinal side edges.
  • a bevel on the longitudinal edge, which faces away from the surface of the turbine blade root, can advantageously simplify the mounting of the securing means.
  • the two holding web elements can be produced in terms of setting technology in different ways on the turbine blade root. For example, they can be milled or cast from the solid together with the turbine blade root. Or they are attached as a separate components cohesively to the turbine blade root.
  • the two holding web elements are milled, cast, welded or glued to the turbine blade root.
  • the generation of the retaining web elements is also often less expensive than, for example, the erosion of corresponding pockets within the turbine blade root.
  • the turbine blade root is designed fir-tree-shaped.
  • the object of the invention is also achieved by a gas turbine with a plurality of turbine blades and with a turbine shaft to which the turbine blades are respectively secured by means of a turbine blade root, wherein the gas turbine turbine blades according to one of the features described herein.
  • the sealing element can also be set particularly low vibration on a gas turbine, since it can be supported on the two holding web elements in addition, if it is secured by the securing means.
  • the present holding device is applicable to turbine blades of any kind of gas turbine.
  • turbine blade 1 has a turbine blade 2 only partially shown here and a turbine blade root 3.
  • the turbine blade 1 is further characterized by a turbine blade platform 2A disposed between the turbine blade 2 and the turbine blade root 3 so that the turbine blade root 3 is spaced from the turbine blade 2 by the turbine blade platform 2A.
  • the turbine blade 1 is determined by means of the turbine blade root 3 in a turbine shaft groove 4 of a turbine shaft 5 rotatable about a rotation axis, not shown here.
  • the turbine screw 3 is formed fir-tree-like in this embodiment. Accordingly, the turbine shaft groove 4 is designed to be complementary thereto. By means of the fir tree-like shape, the turbine blade 1 is secured in a known manner in the radial direction 8 on the turbine shaft 5.
  • the turbine blade 1 at its turbine blade root 3 comprises a holding device 9 for holding securing means 10 (see FIG. 3 ) for securing a planar cover element 11 arranged on the turbine blade root 3, which is inserted on the underside in a fixing groove 12 circumferentially encircling the turbine shaft 5 and on the upper side in a side groove 13 formed by the turbine blades 1, 1A.
  • the flat cover member 11 embodies a known per se sealing sheet for sealing the end of the arrangement of the plurality of turbine blades 1 and 1A, etc., and the turbine shaft 5 in the region of the respective turbine blade root 3 (only exemplified).
  • the holding device 9 is arranged outside the turbine blade root 3 on the turbine blade root 3, so that the latter can be made more massive, since a material recess in the form of a pocket on the turbine blade root 3 can be dispensed with.
  • the holding device 9 is arranged at a distance from the turbine blade platform.
  • the holding device 9 is spaced apart both from the fixing groove 12 and from the side groove 13 and thus formed differently from these.
  • the holding device 9 has a receiving space 14 for arranging a bolt element 15 and at least one locking plate element 16 of the securing means 10, wherein the receiving space 14 is arranged on or in front of the head side 17 of the turbine blade root 3.
  • the holding device 9 is in this case on the head side 17, which simultaneously represents the short side (not numbered here again) of the turbine blade root 3, placed that it is arranged starting from the outer side 18 of the turbine blade root 3 above the surface 19 of the turbine blade root 3.
  • the holding device 9 comprises a receiving space 14 configured outside the turbine blade root 3 for arranging at least the bolt element 15, a pocket which has hitherto been incorporated into the turbine blade root 3 can be dispensed with in its entirety.
  • the receiving space 14 is not very deeply arranged on the arrangement and is therefore easily accessible.
  • the holding device 9 is such that the receiving space 14 for arranging the securing means 10 is accessible from three sides 20, 21 and 22, so that it is structurally simply provided, wherein the side 20 corresponds to the insertion side 6A.
  • the constructive effort is further reduced, since the receiving space 14 of the holding device 9 is defined only by two mutually objected holding web elements 23 and 24, which are milled in this embodiment together with the turbine blade root 3 from the solid.
  • These two holding web elements 23 and 24 are arranged parallel to one another and aligned with their longitudinal extent 25 (shown here only by way of example) in the longitudinal direction 26 of the turbine blade 2.
  • the two holding web elements 23 and 24 are perpendicular to the circumferential surface 7 of the turbine shaft 5 and also radially, so seen in the radial direction 8, arranged above this peripheral surface 7 on the head side 17 of the turbine blade root 3, whereby the accessibility of the receiving space 14 is further improved.
  • the retaining web elements 23 and 24 are actually completely covered by the flat cover 11 during assembly of the securing means 10, it is advantageous that the retaining web elements 23 and 24 each have a chamfer at their longitudinal side edges 27 and 28 facing away from the surface 19 of the turbine blade root 3 29 (only exemplified). These chamfered longitudinal side edges 27 and 28 are located on the mutually facing web sides 30 and 31 of the holding web elements 23 and 24th
  • Each of the two holding web elements 23 and 24 has a length 32 which is greater than the height 33 of the respective holding web element 23 or 24. Likewise, the length 32 is greater than the thickness 34 of the respective holding web element 23 or 24.
  • the two mutually facing web sides 30 and 31 are designed flush below the respective chamfer 29, so that the receiving space 14 correspondingly includes plane boundary inner wall surfaces on which the securing means 10 can be supported.
  • the two holding web elements 23 and 24 each have a wider base area 35 (numbered only as an example) in order to give the holding web elements 23 and 24 good stability.
  • a planar cover 11 is disposed in front of the turbine blade root 3 of the other turbine blade 1A, wherein after placing this flat cover member 11, first the bolt element 15 is inserted through an opening 36 of the flat cover 11 and inserted into the receiving space 14. In addition, the bolt element 15 is clamped captive by means of the likewise inserted through the opening 36 of the flat cover member 11 and inserted into the receiving space 14 locking plate member 16 within the receiving space 14.

Landscapes

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

Claims (13)

  1. Aube (1) de turbine ayant une lame (2) et une emplanture (3) pour fixer l'aube (1) de turbine dans une rainure (4) d'un arbre (5) de turbine, dans laquelle l'emplanture (3) comprend un dispositif (9) de retenue pour retenir des moyens (10) d'assujettissement pour assujettir un élément (11) de recouvrement plat mis du côté de la tête sur l'emplanture (3),
    dans laquelle le dispositif (9) de retenue est, en partant du côté (18) extérieur de l'emplanture (3), disposé au dessus de la surface (19) de l'emplanture (3),
    caractérisée
    en ce que le dispositif (9) de retenue comprend deux éléments (23, 24) d'entretoise de retenue à distance l'un de l'autre, qui entourent au moins en partie un espace (14) de réception pour mettre un élément (15) de boulon des moyens (10) d'assujettissement.
  2. Aube (1) de turbine suivant la revendication 1,
    dans laquelle le dispositif (9) de retenue comprend, pour mettre un élément (15) de boulon des moyens (10) d'assujettissement, un espace (14) de réception conformé à l'extérieur de l'emplanture (3).
  3. Aube (1) de turbine suivant la revendication 1 ou 2,
    dans laquelle le dispositif (9) de retenue comprend un espace (14) de réception pour mettre un élément (15) de boulon des moyens (10) d'assujettissement,
    l'espace (14) de réception étant accessible de plus d'un côté (20), de préférence de trois côtés (20, 21, 22).
  4. Aube (1) de turbine suivant l'une des revendications 1 à 3, dans laquelle les deux éléments (23, 24) d'entretoise de retenue s'étendent parallèlement l'un à l'autre.
  5. Aube (1) de turbine suivant l'une des revendications 1 à 4,
    dans laquelle les deux éléments (23, 24) d'entretoise de retenue sont montés sur l'emplanture (3) en s'étendant dans la direction (26) longitudinale de la lame (2) de l'aube de turbine.
  6. Aube (1) de turbine suivant l'une des revendications 1 à 5, dans laquelle les deux éléments (23, 24) d'entretoise de retenue sont disposés perpendiculairement à la surface (7) périphérique de l'arbre (5) de la turbine, du côté (17) de la tête de l'emplanture (3).
  7. Aube (1) de turbine suivant l'une des revendications 1 à 6, dans laquelle les deux éléments (23, 24) d'entretoise de retenue sont disposés radialement au-dessus de la surface (7) périphérique de l'arbre (5) de la turbine.
  8. Aube (1) de turbine suivant l'une des revendications 1 à 7, dans laquelle les deux éléments (23, 24) d'entretoise de retenue sont disposés du petit côté de l'emplanture (3).
  9. Aube (1) de turbine suivant l'une des revendications 1 à 8, dans laquelle les deux éléments (23, 24) d'entretoise de retenue sont disposés du côté (6A) de l'insertion des rainures (4) ménagées dans l'arbre (5) de la turbine.
  10. Aube (1) de turbine suivant l'une des revendications 1 à 9, dans laquelle les deux éléments (23, 24) d'entretoise de retenue sont biseautés sur les bords (27, 28) longitudinaux sur leurs côtés (30, 31) d'entretoise tournés l'un vers l'autre.
  11. Aube (1) de turbine suivant l'une des revendications 1 à 10,
    dans laquelle les deux éléments (23, 24) d'entretoise de retenue ont une longueur (32), qui est plus grande que leur hauteur (33) et/ou leur épaisseur (34).
  12. Aube (1) de turbine suivant l'une des revendications 1 à 11,
    dans laquelle les deux éléments (23, 24) d'entretoise de retenue sont fraisés, coulés, soudés ou collés sur l'emplanture (3).
  13. Turbine (37) à gaz ayant une pluralité d'aubes (3) de turbine et un arbre (5) de turbine, sur lequel les aubes (3) de la turbine sont fixées, chacune au moyen d'une emplanture (3) d'aube de turbine, dans laquelle la turbine (37) à gaz comprend des aubes (3) de turbine suivant l'une des revendications précédentes.
EP14759175.4A 2013-10-10 2014-09-04 Aube de turbine et turbine à gaz Not-in-force EP3025028B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14759175.4A EP3025028B1 (fr) 2013-10-10 2014-09-04 Aube de turbine et turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP20130187991 EP2860349A1 (fr) 2013-10-10 2013-10-10 Aube de turbine et turbine à gaz
EP14759175.4A EP3025028B1 (fr) 2013-10-10 2014-09-04 Aube de turbine et turbine à gaz
PCT/EP2014/068800 WO2015051955A1 (fr) 2013-10-10 2014-09-04 Aube de turbine et turbine à gaz

Publications (2)

Publication Number Publication Date
EP3025028A1 EP3025028A1 (fr) 2016-06-01
EP3025028B1 true EP3025028B1 (fr) 2018-05-09

Family

ID=49378089

Family Applications (2)

Application Number Title Priority Date Filing Date
EP20130187991 Withdrawn EP2860349A1 (fr) 2013-10-10 2013-10-10 Aube de turbine et turbine à gaz
EP14759175.4A Not-in-force EP3025028B1 (fr) 2013-10-10 2014-09-04 Aube de turbine et turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP20130187991 Withdrawn EP2860349A1 (fr) 2013-10-10 2013-10-10 Aube de turbine et turbine à gaz

Country Status (5)

Country Link
US (1) US20160222805A1 (fr)
EP (2) EP2860349A1 (fr)
JP (1) JP2016536504A (fr)
CN (1) CN105612312B (fr)
WO (1) WO2015051955A1 (fr)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2662533A2 (fr) * 2012-05-07 2013-11-13 General Electric Company Segment de recouvrement pour zone de montage d'aubes, système et procédé de montage associés
EP2860350A1 (fr) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Aube de turbine et turbine à gaz

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Publication number Priority date Publication date Assignee Title
US4480958A (en) * 1983-02-09 1984-11-06 The United States Of America As Represented By The Secretary Of The Air Force High pressure turbine rotor two-piece blade retainer
US4816213A (en) * 1987-08-24 1989-03-28 Westinghouse Electric Corp. Thermal distortion isolation system for turbine blade rings
US5137420A (en) * 1990-09-14 1992-08-11 United Technologies Corporation Compressible blade root sealant
DE19950109A1 (de) * 1999-10-18 2001-04-19 Asea Brown Boveri Rotor für eine Gasturbine
DE19960896A1 (de) * 1999-12-17 2001-06-28 Rolls Royce Deutschland Rückhaltevorrichtung für Rotorschaufeln einer Axialturbomaschine
US7530791B2 (en) * 2005-12-22 2009-05-12 Pratt & Whitney Canada Corp. Turbine blade retaining apparatus
US7566201B2 (en) * 2007-01-30 2009-07-28 Siemens Energy, Inc. Turbine seal plate locking system
US8206119B2 (en) * 2009-02-05 2012-06-26 General Electric Company Turbine coverplate systems
EP2218873A1 (fr) * 2009-02-17 2010-08-18 Siemens Aktiengesellschaft Section de rotor pour un rotor d'une turbomachine, aube directrice pour une turbomachine et élément de blocage
US8727730B2 (en) * 2010-04-06 2014-05-20 General Electric Company Composite turbine bucket assembly
US8740573B2 (en) * 2011-04-26 2014-06-03 General Electric Company Adaptor assembly for coupling turbine blades to rotor disks
US9217334B2 (en) * 2011-10-26 2015-12-22 General Electric Company Turbine cover plate assembly
EP2642079A1 (fr) * 2012-03-21 2013-09-25 Alstom Technology Ltd Structure de diaphragme de turbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2662533A2 (fr) * 2012-05-07 2013-11-13 General Electric Company Segment de recouvrement pour zone de montage d'aubes, système et procédé de montage associés
EP2860350A1 (fr) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Aube de turbine et turbine à gaz

Also Published As

Publication number Publication date
CN105612312B (zh) 2017-12-15
JP2016536504A (ja) 2016-11-24
CN105612312A (zh) 2016-05-25
EP3025028A1 (fr) 2016-06-01
EP2860349A1 (fr) 2015-04-15
US20160222805A1 (en) 2016-08-04
WO2015051955A1 (fr) 2015-04-16

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