EP1584791A1 - Turbomachine et rotor pour turbomachine - Google Patents

Turbomachine et rotor pour turbomachine Download PDF

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Publication number
EP1584791A1
EP1584791A1 EP04008485A EP04008485A EP1584791A1 EP 1584791 A1 EP1584791 A1 EP 1584791A1 EP 04008485 A EP04008485 A EP 04008485A EP 04008485 A EP04008485 A EP 04008485A EP 1584791 A1 EP1584791 A1 EP 1584791A1
Authority
EP
European Patent Office
Prior art keywords
rotor
groove
annular groove
retaining
blade
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Withdrawn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
EP04008485A
Other languages
German (de)
English (en)
Inventor
Bernard Dr. Becker
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 EP04008485A priority Critical patent/EP1584791A1/fr
Priority to CNB2005800108918A priority patent/CN100404795C/zh
Priority to EP05716050A priority patent/EP1733124B1/fr
Priority to DE502005011334T priority patent/DE502005011334D1/de
Priority to PCT/EP2005/002710 priority patent/WO2005100751A1/fr
Priority to US11/547,943 priority patent/US7628589B2/en
Publication of EP1584791A1 publication Critical patent/EP1584791A1/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Withdrawn legal-status Critical Current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
    • F01D5/32—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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/293—Three-dimensional machined; miscellaneous lathed, e.g. rotation symmetrical
    • 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 invention relates to a rotor for a turbomachine according to the preamble of claim 1 and a turbomachine according to the preamble of claim 9.
  • FIG. 7 shows a section of a compressor disk 19 according to the prior art.
  • retaining grooves 21 in the outer circumference 23 of Compressor disk 19 is provided.
  • recesses 29 on the two end faces 25 of the compressor disk 23 arranged, respectively in the groove bottom 27 of the radially outside go over lying holding groove 21.
  • FIG. 8 shows the cross section through a compressor disk 19 according to FIG. 7 along the section VIII-VIII.
  • the recess 29 is formed as a chamfer 30 at an angle of 45 °.
  • the solution of the task provides that at least in one Face of the shaft collar in an axial direction extending to the axis of rotation of the rotor coaxial annular groove provided is so connected to the groove bottom of the retaining grooves is that material of the blade root of the blade is plastically displaceable in the annular groove.
  • the invention is based on the knowledge that a Receiving area, which below the groove bottom of the retaining groove lies in the coaxial annular groove and for receiving the material the blade foot serves, one for the by the caulking shaped projection has more favorable shape. That after one Anstemmung plastically deformed material of the blade root is better at the annular groove, so that a lossy axial play of the blade is avoided. Additional fastening components omitted.
  • each bevel was in a separate Milling process produced.
  • the annular groove can during of the turning process are produced, with which the contour the front side is made.
  • the receiving area created displaceable in the material of the blade root is. This reduces the manufacturing costs and the production time of the rotor.
  • the annular groove a Ringnutground and two flanks, at each flank the annular groove passes over a curve in the Ringnutground.
  • the annular groove formed cut edge close this one Tangent angle, which is in a plane that is of radius of the rotor and the axis of rotation of the rotor is clamped.
  • the groove base of the retaining groove can be located radially further inward Cut the rounding of the ring groove.
  • the tangent angle may be due to the rounding thereby in an order of magnitude between 50 ° and 90 ° so that the shape of the receiving area
  • the shape of the projection is very close to geometrically.
  • a projection be at an angle of 50 ° to 90 ° to the groove bottom of Holding has.
  • the most effective part of the projection is the, which at an angle of 90 ° to the groove bottom of the retaining groove is trained.
  • the shaft collar is through a disc, in particular formed by a compressor disk.
  • the ring groove can be made when turning the compressor disk, so that the individual milling of each chamfer is eliminated.
  • the retaining groove in cross section dovetailed or fir-tree-shaped.
  • Gas turbines and their ways of working are well known.
  • the gas turbine essentially points along a rotor a compressor, a combustion chamber and a turbine unit on.
  • the sucked and compressed air from the compressor is mixed with a fuel and in the combustion chamber to a Hot gas burned, which subsequently in the turbine unit working on the rotor of the gas turbine to perform work.
  • the rotor of the gas turbine drives the compressor and a Work machine, for example, a generator.
  • two blade rings each form a compressor stage, each seen in the flow direction rotatable ring of blades attached to the rotor following a fixed ring of vanes.
  • two blade rings each form a turbine stage, each seen in the flow direction, a fixed Vane ring a rotatable ring attached to the rotor out of blades follows.
  • the rotor of the gas turbine points for each blade ring a disk or a shaft collar on which the blades are attached to the respective wreath.
  • FIG. 1 shows a segment of such a disk as a compressor disk 19 according to the invention.
  • the compressor disk forms a shaft collar 22, which at its outer circumference 23 itself transversely extending retaining grooves 21 for receiving blades 16 has.
  • In the groove bottom 27 of the retaining groove 21 is a coaxial with the fulcrum of the rotor and arranged provided in the axial direction A extending annular groove 31.
  • the annular groove 31 is during the manufacture of the compressor disk 19 when turning the front side 25 and thus within the previous step can be produced.
  • the annular groove 31 cuts each retaining groove 21 in the region of the groove bottom 27.
  • a receiving area 34 available, in the material of the blade root 33 e.g. plastically displaceable by prying is.
  • Figure 2 shows a section through the cross section of a Compressor disk 19 according to Figure 1.
  • the through the compressor disk 19 formed shaft collar 22 has at each end face 25 on the cross-sectionally U-shaped annular groove 31.
  • a Depth T extends each annular groove 31 in the axial direction, so that the axial length of the groove bottom 27 of the retaining groove 21 opposite a slice thickness D (see Figure 1) is shortened.
  • the annular groove 31 has in cross section as a side wall respectively a flank 37, which has a rounding 41, which as Radius, ellipse, concave shape or similar formed may be in the ring groove bottom 39 passes.
  • the annular groove 31 is on both end faces 25 of the compressor disk 19 provided so that each blade 16 by two Anstemmvortician can be secured axially.
  • FIG. 3 shows the section through a compressor disk 19 a blade 16, the blade root 33 already plastic is deformed.
  • the material of the blade root 33 protrudes as Projection 35 radially inwardly into the annular groove 31 in.
  • Of the Ringnutground 39 serves as an abutment for the projection 35, thus securing the blade 16 against axial displacement.
  • FIG. 4 shows a section from the side view of the compressor disk 19 shown in FIG.
  • the blade foot 33 of the blade 16 is deformed by the Anstemmvorgang.
  • An Anstemmung 36 is in the lower part of the Shovel 33 arranged and covers about a third of the Width of the blade root 33.
  • FIGS. 5 and 6 show the section through the compressor disk 19 with the coaxial annular groove 31 in detail.
  • a tangent which with the groove bottom 27 of the retaining groove 21 includes a tangent angle ⁇ .
  • This lies in an imaginary plane, which was created by the Rotary axis of the rotor and of the radial direction of the rotor is spanned, which passes through a retaining groove 21. ever points according to the distance of the groove bottom 27 to the axis of rotation of the rotor the tangent angle ⁇ has a size of 50 ° to 90 °.
  • the Ringnutgrund 39 cuts the groove bottom 27 of the retaining 21, so there is a tangent angle ⁇ of 90 °. But it is arranged the annular groove 21 radially further out, so that the radially inner curve 41 the groove bottom 27 of the retaining 21st cuts, so the tangent angle ⁇ decreases accordingly the selected rounding 41.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP04008485A 2004-04-07 2004-04-07 Turbomachine et rotor pour turbomachine Withdrawn EP1584791A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP04008485A EP1584791A1 (fr) 2004-04-07 2004-04-07 Turbomachine et rotor pour turbomachine
CNB2005800108918A CN100404795C (zh) 2004-04-07 2005-03-14 涡轮机以及用于涡轮机的转子
EP05716050A EP1733124B1 (fr) 2004-04-07 2005-03-14 Turbomachine et rotor pour turbomachine
DE502005011334T DE502005011334D1 (de) 2004-04-07 2005-03-14 Strömungsmaschine und rotor für eine strömungsmaschine
PCT/EP2005/002710 WO2005100751A1 (fr) 2004-04-07 2005-03-14 Turbomachine et rotor pour turbomachine
US11/547,943 US7628589B2 (en) 2004-04-07 2005-03-14 Turbo-engine and rotor for a turbo-engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04008485A EP1584791A1 (fr) 2004-04-07 2004-04-07 Turbomachine et rotor pour turbomachine

Publications (1)

Publication Number Publication Date
EP1584791A1 true EP1584791A1 (fr) 2005-10-12

Family

ID=34896011

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04008485A Withdrawn EP1584791A1 (fr) 2004-04-07 2004-04-07 Turbomachine et rotor pour turbomachine
EP05716050A Not-in-force EP1733124B1 (fr) 2004-04-07 2005-03-14 Turbomachine et rotor pour turbomachine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05716050A Not-in-force EP1733124B1 (fr) 2004-04-07 2005-03-14 Turbomachine et rotor pour turbomachine

Country Status (5)

Country Link
US (1) US7628589B2 (fr)
EP (2) EP1584791A1 (fr)
CN (1) CN100404795C (fr)
DE (1) DE502005011334D1 (fr)
WO (1) WO2005100751A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018077589A1 (fr) * 2016-10-26 2018-05-03 Siemens Aktiengesellschaft Ensemble de rotor de turbine et procédé de fabrication d'une pale de rotor de turbine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010053141B4 (de) * 2009-12-07 2018-10-11 General Electric Technology Gmbh Turbinenaggregat mit möglicher Überdrehung des Fußes einer Schaufel bis zum Einbau einer letzten Schaufel
US8753090B2 (en) 2010-11-24 2014-06-17 Rolls-Royce Corporation Bladed disk assembly
US8764402B2 (en) 2011-06-09 2014-07-01 General Electric Company Turbomachine blade locking system
US11098729B2 (en) * 2016-08-04 2021-08-24 General Electric Company Gas turbine wheel assembly, method of modifying a compressor wheel, and method of mounting a blade to a gas turbine wheel
WO2021059678A1 (fr) * 2019-09-27 2021-04-01 本田技研工業株式会社 Procédé de revêtement de métal
CN114837748A (zh) * 2021-02-02 2022-08-02 中国航发商用航空发动机有限责任公司 航空发动机

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH489698A (de) * 1968-09-02 1970-04-30 Bbc Brown Boveri & Cie Vorrichtung zur Sicherung von in axialen Nuten einer Welle formschlüssig gehaltenen Laufschaufeln von Strömungsmaschinen, insbesondere für Turbinen
DE2606565A1 (de) * 1975-03-12 1976-09-23 Stal Laval Turbin Ab Laufrad fuer eine axialturbine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3157385A (en) * 1961-10-17 1964-11-17 Ass Elect Ind Blade locking means for turbines or compressors
US4439107A (en) * 1982-09-16 1984-03-27 United Technologies Corporation Rotor blade cooling air chamber
US4507052A (en) * 1983-03-31 1985-03-26 General Motors Corporation End seal for turbine blade bases
US5211407A (en) * 1992-04-30 1993-05-18 General Electric Company Compressor rotor cross shank leak seal for axial dovetails
US6190131B1 (en) * 1999-08-31 2001-02-20 General Electric Co. Non-integral balanced coverplate and coverplate centering slot for a turbine
FR2824870B1 (fr) * 2001-05-16 2003-08-15 Alstom Power Nv Disque de rotor basse pression de turbine a vapeur equipe d'ailettes montees chacune sur le disque avec une fixation crantee dite a pied de sapin
US6533550B1 (en) * 2001-10-23 2003-03-18 Pratt & Whitney Canada Corp. Blade retention

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH489698A (de) * 1968-09-02 1970-04-30 Bbc Brown Boveri & Cie Vorrichtung zur Sicherung von in axialen Nuten einer Welle formschlüssig gehaltenen Laufschaufeln von Strömungsmaschinen, insbesondere für Turbinen
DE2606565A1 (de) * 1975-03-12 1976-09-23 Stal Laval Turbin Ab Laufrad fuer eine axialturbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018077589A1 (fr) * 2016-10-26 2018-05-03 Siemens Aktiengesellschaft Ensemble de rotor de turbine et procédé de fabrication d'une pale de rotor de turbine

Also Published As

Publication number Publication date
CN1950590A (zh) 2007-04-18
CN100404795C (zh) 2008-07-23
DE502005011334D1 (de) 2011-06-16
US20080267781A1 (en) 2008-10-30
EP1733124B1 (fr) 2011-05-04
WO2005100751A1 (fr) 2005-10-27
EP1733124A1 (fr) 2006-12-20
US7628589B2 (en) 2009-12-08

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