EP2860349A1 - Aube de turbine et turbine à gaz - Google Patents

Aube de turbine et turbine à gaz Download PDF

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Publication number
EP2860349A1
EP2860349A1 EP20130187991 EP13187991A EP2860349A1 EP 2860349 A1 EP2860349 A1 EP 2860349A1 EP 20130187991 EP20130187991 EP 20130187991 EP 13187991 A EP13187991 A EP 13187991A EP 2860349 A1 EP2860349 A1 EP 2860349A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
turbine
blade root
holding
web elements
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.)
Withdrawn
Application number
EP20130187991
Other languages
German (de)
English (en)
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 EP20130187991 priority Critical patent/EP2860349A1/fr
Priority to US15/026,006 priority patent/US20160222805A1/en
Priority to JP2016521759A priority patent/JP2016536504A/ja
Priority to EP14759175.4A priority patent/EP3025028B1/fr
Priority to CN201480055802.0A priority patent/CN105612312B/zh
Priority to PCT/EP2014/068800 priority patent/WO2015051955A1/fr
Publication of EP2860349A1 publication Critical patent/EP2860349A1/fr
Withdrawn legal-status Critical Current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
    • 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 planar cover arranged on the head side of 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.
  • material recesses in the form of pockets which are introduced into the turbine blade feet, are provided on the turbine blade feet. These pockets are introduced, for example, by erosion into the turbine blade feet, like this particular out WO 2010/094539 A1 is known.
  • 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 outside of the turbine blade root on this turbine blade root.
  • the holding device holding the planar covering element is arranged outside the turbine blade root on this turbine blade root, the properties of absorbing and guiding forces through the turbine blade root are significantly improved.
  • 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.
  • Generic securing means are well known in the art and may be used substantially herein. 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.
  • 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 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 made particularly simple and fast when the holding means 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 accessible at least from the head side of the turbine blade root in the direction of insertion of the turbine blade.
  • the receiving space can be designed structurally particularly simple if the holding device two from each other comprising spaced retaining web elements which at least partially surround a receiving space for arranging a bolt element of the securing means.
  • 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 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 (numbered only as an example).
  • 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 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 flat cover 11 is disposed in front of the turbine blade root 3 of the other turbine blade 1A, wherein after placing this flat cover 11, first the bolt member 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)
EP20130187991 2013-10-10 2013-10-10 Aube de turbine et turbine à gaz Withdrawn EP2860349A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP20130187991 EP2860349A1 (fr) 2013-10-10 2013-10-10 Aube de turbine et turbine à gaz
US15/026,006 US20160222805A1 (en) 2013-10-10 2014-09-04 Turbine blade and gas turbine
JP2016521759A JP2016536504A (ja) 2013-10-10 2014-09-04 タービンブレード及びガスタービン
EP14759175.4A EP3025028B1 (fr) 2013-10-10 2014-09-04 Aube de turbine et turbine à gaz
CN201480055802.0A CN105612312B (zh) 2013-10-10 2014-09-04 涡轮叶片和燃气涡轮
PCT/EP2014/068800 WO2015051955A1 (fr) 2013-10-10 2014-09-04 Aube de turbine et turbine à gaz

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP2860349A1 true EP2860349A1 (fr) 2015-04-15

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 After (1)

Application Number Title Priority Date Filing Date
EP14759175.4A Not-in-force EP3025028B1 (fr) 2013-10-10 2014-09-04 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 (4)

* Cited by examiner, † Cited by third party
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
US5137420A (en) * 1990-09-14 1992-08-11 United Technologies Corporation Compressible blade root sealant
DE19960896A1 (de) * 1999-12-17 2001-06-28 Rolls Royce Deutschland Rückhaltevorrichtung für Rotorschaufeln einer Axialturbomaschine
WO2010094539A1 (fr) 2009-02-17 2010-08-26 Siemens Aktiengesellschaft Segment de rotor pour le rotor d'une turbomachine, aube mobile pour une turbomachine

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4816213A (en) * 1987-08-24 1989-03-28 Westinghouse Electric Corp. Thermal distortion isolation system for turbine blade rings
DE19950109A1 (de) * 1999-10-18 2001-04-19 Asea Brown Boveri Rotor für eine Gasturbine
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
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
US9366151B2 (en) * 2012-05-07 2016-06-14 General Electric Company System and method for covering a blade mounting region of turbine blades
EP2860350A1 (fr) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Aube de turbine et turbine à gaz

Patent Citations (4)

* Cited by examiner, † Cited by third party
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
US5137420A (en) * 1990-09-14 1992-08-11 United Technologies Corporation Compressible blade root sealant
DE19960896A1 (de) * 1999-12-17 2001-06-28 Rolls Royce Deutschland Rückhaltevorrichtung für Rotorschaufeln einer Axialturbomaschine
WO2010094539A1 (fr) 2009-02-17 2010-08-26 Siemens Aktiengesellschaft Segment de rotor pour le rotor d'une turbomachine, aube mobile pour une turbomachine

Also Published As

Publication number Publication date
EP3025028B1 (fr) 2018-05-09
CN105612312A (zh) 2016-05-25
JP2016536504A (ja) 2016-11-24
WO2015051955A1 (fr) 2015-04-16
US20160222805A1 (en) 2016-08-04
CN105612312B (zh) 2017-12-15
EP3025028A1 (fr) 2016-06-01

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