EP1703079A1 - Solide de rotation pour la fixation d'une aube d'une turbo-machine - Google Patents

Solide de rotation pour la fixation d'une aube d'une turbo-machine Download PDF

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Publication number
EP1703079A1
EP1703079A1 EP05018594A EP05018594A EP1703079A1 EP 1703079 A1 EP1703079 A1 EP 1703079A1 EP 05018594 A EP05018594 A EP 05018594A EP 05018594 A EP05018594 A EP 05018594A EP 1703079 A1 EP1703079 A1 EP 1703079A1
Authority
EP
European Patent Office
Prior art keywords
rotary body
relief slot
tooth
rotor
relief
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Withdrawn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
EP05018594A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Ying Dr. Pan
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 EP05018594A priority Critical patent/EP1703079A1/fr
Publication of EP1703079A1 publication Critical patent/EP1703079A1/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Withdrawn legal-status Critical Current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

Definitions

  • the invention relates to a rotary body for fastening rotor blades of a turbomachine, with an axis of rotation and with a provided between a first front side surface and a second end side surface peripheral surface and with uniformly distributed along the peripheral surface, extending between the two end side surfaces holding grooves, each retaining groove has at least one circumferentially extending undercut.
  • a generic device is for example from the WO 2003/036049 A1 known.
  • a rotor disk axially extending and in cross-section fir-tree-shaped retaining grooves for blades are distributed along the circumference.
  • Each blade has a corresponding to the retaining groove formed on the blade root, so that they can each be inserted and secured in one of the retaining grooves.
  • each retaining groove has at its two side walls in the circumferential direction extending teeth and intervening undercuts, which produce with the corresponding recesses and teeth of the blade root teeth, with which the blade is held on the rotor disk.
  • the rotor disk rotates as part of the rotor at a predetermined speed, so that the blades attached thereto strive under the action of centrifugal force to the outside and bear against the toothed disk formed by Nuthinterschneidungen on the rotor disk.
  • the object of the invention is to provide a rotary body for fastening blades of a turbomachine whose life is extended.
  • the object is achieved by a rotary body having the features of patent claim 1.
  • the invention proposes a generic rotary body in whose frontal side surface a relief slot arranged in the region of the tooth is provided.
  • the invention is based on the recognition that the position of the maximum occurring in the region of the tooth of the rotating body and caused by the outwardly aspiring blade during operation voltage can be displaced locally from a critical area in a non-critical area by a discharge slot.
  • This maximum stress was previously on each front side surface, on the contour of the tooth and thus on the contour of the retaining groove on which rests the blade root. Due to the relief slot, this maximum stress no longer occurs directly at the contour of the Tooth or the retaining groove, but in a second remote therefrom, in which the emergence or presence of a crack or defect for the operation of the turbomachine is not critical.
  • the crack inspection is substantially simplified, since an improved possibility of checking for cracks or other indications, for example defects, with known test methods is possible due to the relief slot machined into the rotary body.
  • a particularly advantageous reduction in stress in the material close to the surface near the surface of the rotational body can be achieved if the relief slot is provided only partially between the undercut and the peripheral surface when viewed in the radial direction.
  • the other part of the discharge slot is thus provided in a section which lies between two adjacent retaining grooves.
  • the discharge slot is kidney-shaped or U-shaped. It has been found that in particular the kidney shape and / or the U-shape in each case can bring about a particularly great reduction in the material tension and a significant local displacement of the maximum of the tension. Accordingly, the material of the rotary body can be effectively spared with such a relief slot.
  • the maximum material tension occurring is displaced out of the region immediately adjacent to the retaining groove and into the second region in which the relief slot is arranged, in a further advantageous development at least the material surrounding the two ends of the relief slot Surface-hardened rotating body.
  • a particularly durable rotary body can be produced, since in this case cracking is further reduced in the second area remote from the holding groove or the tooth and crack growth continues to be delayed.
  • the relief slot has a penetration depth of 1 mm to 25 mm, preferably from 5 mm to 20 mm. This penetration depth leads to a particularly effective relief of the material.
  • the retaining grooves may be formed in fir-tree cross section, hammer-shaped or dovetailed in cross section. In the case of a hammer or dovetail shape, each retaining groove has an undercut on both sides, ie in the circumferential direction, so that the rotational body has one tooth for each undercut, one provided on the respective side wall of the retaining groove and extending into it.
  • each side wall of the Holding groove arranged teeth which protrude into the retaining groove and each one on the respective tooth radially inwardly adjacent (groove) undercut form, to which a correspondingly designed blade root can rest.
  • Each tooth formed on the retaining groove serves during operation of the turbomachine as an abutment for a correspondingly configured tooth provided on the blade root.
  • a plurality of radially spaced undercuts are provided, only the radially outer undercuts may have an associated relief slot and the radially inner undercuts not.
  • This embodiment is based on the knowledge that especially at the radially outer undercuts, the largest mechanical stress in the material of the rotating body, caused by the centrifugal force loads of the blade and the rotating body occur. According to the invention, these maximum mechanical stress loads are displaced out of the area directly forming the retaining groove by the relief slots. At the radially inner undercuts occur no unacceptable material stresses, so that, if necessary, can be dispensed with relief slots here.
  • the rotary body may be formed on the one hand as a rotor disk or as a welded rotor rotor, for example, are provided on the provided in a shaft collar, extending in the axial direction retaining grooves for turbine blades or compressor blades. Accordingly, the meaning of the invention is independent of the selected embodiment of the rotor and used for both embodiments.
  • a turbomachine equipped with this rotary body advantageously has an increased service life and reduced service life due to the extended service life.
  • FIG. 1 shows a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17 which communicates with an annular hot gas channel 18.
  • There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 is formed of two blade rings.
  • vanes 13 Viewed in the flow direction of a hot gas 11 produced in the annular combustion chamber 6, follows in the hot gas channel 18 in each case one row of vanes 13 a formed of blades 15 row 14.
  • the vanes 12 are attached to the stator, whereas the blades 15 of a row 14 means a turbine disk are mounted on the rotor 3.
  • a generator or a working machine (not shown) is coupled.
  • FIG 2 shows a detail of a rotary body 30, which may be formed as a rotor disk 19 or as a shaft collar of a rotor rotor.
  • the rotary body 30 has two end-side side surfaces 32, which are connected to each other by a peripheral surface 36.
  • uniformly distributed retaining grooves 38 are provided, in which in the axial direction, based on the axis of rotation 34, not shown in FIG 2 blades for an axial flow machine, such as a gas turbine 1, a compressor 3 or a steam turbine, are inserted.
  • the retaining grooves 38 have a fir-tree-shaped contour in the illustrated cross-section. This results in each retaining groove 38 four circumferentially extending undercuts 20.
  • each undercut 20 each have a radially outwardly adjacent to the undercut 20 and also protruding in the circumferential direction tooth 22 whose radially inner part surface as an abutment for Blades not shown is used so that they are held by the rotary body 30 during operation of the turbomachine.
  • the invention proposes that in one or both front side surfaces 32 to the undercuts 20 adjacent relief slots 26, 28 are provided, the respective contour or contour describes, for example, a kidney shape or a U-shape.
  • the relief slot 26, 28 is located in the root region of the tooth 22, slightly displaced radially inwardly to the undercuts 20, into which projects the corresponding tooth 22 of the blade root, which transmits the load of the blade for each tooth 22.
  • the orientation of the slightly curved relief slot 26, 28 is chosen so that its ends preferably point away from the retaining groove 38.
  • the material directly surrounding the retaining grooves 38 of the rotating body 30 is thus still charged during operation of the turbomachine by the blades held in the retaining grooves 38, but occurs a lower maximum stress in the material at a displaced location in the vicinity of the discharge slot 26, thereby the life of the rotating body 30 improved in a decisive way. Accordingly, a more uniform loading of the material, seen both in the axial direction and in the radial and circumferential direction, is achieved overall.
  • the relief slots 26 are provided in the radial direction partially between the undercut 20 and the peripheral surface 36 and have an axially extending penetration depth E in the order of 1 mm to 25 mm, but preferably from 5 mm to 20 mm.
  • each undercut 20 at one or each end-side side surface 32 associated with it Relief slot 26, 28 have.
  • the retaining groove 38 is formed as a fir-tree shape, only only the radially outermost undercuts 22 can each have a discharge slot 28 assigned to them.
  • the stress maximum in the material displaced away from the contour profile 24 can advantageously lead to a life extension.
  • a particular advantage of the present invention is also due to the fact that the relief slots 26, 28 can act as a crack stopper. If defects occur in the form of cracks adjacent to the tearstoppers, they can possibly leak into the relief slots 26, 28 without these exceeding a critical crack length.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP05018594A 2005-08-26 2005-08-26 Solide de rotation pour la fixation d'une aube d'une turbo-machine Withdrawn EP1703079A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05018594A EP1703079A1 (fr) 2005-08-26 2005-08-26 Solide de rotation pour la fixation d'une aube d'une turbo-machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05018594A EP1703079A1 (fr) 2005-08-26 2005-08-26 Solide de rotation pour la fixation d'une aube d'une turbo-machine

Publications (1)

Publication Number Publication Date
EP1703079A1 true EP1703079A1 (fr) 2006-09-20

Family

ID=35759205

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05018594A Withdrawn EP1703079A1 (fr) 2005-08-26 2005-08-26 Solide de rotation pour la fixation d'une aube d'une turbo-machine

Country Status (1)

Country Link
EP (1) EP1703079A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2911632A1 (fr) * 2007-01-18 2008-07-25 Snecma Sa Disque de rotor de soufflante de turbomachine
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

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB280221A (en) * 1926-11-06 1928-02-23 Alfred Buechi Improvements in blading for gas and steam turbines
EP1048821A2 (fr) * 1999-04-30 2000-11-02 General Electric Company Pied d'aube avec une forme diminuant la tension
US20030129060A1 (en) * 2001-10-13 2003-07-10 Knott David S. Indentor arrangement

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB280221A (en) * 1926-11-06 1928-02-23 Alfred Buechi Improvements in blading for gas and steam turbines
EP1048821A2 (fr) * 1999-04-30 2000-11-02 General Electric Company Pied d'aube avec une forme diminuant la tension
US20030129060A1 (en) * 2001-10-13 2003-07-10 Knott David S. Indentor arrangement

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2911632A1 (fr) * 2007-01-18 2008-07-25 Snecma Sa Disque de rotor de soufflante de turbomachine
EP1950381A1 (fr) * 2007-01-18 2008-07-30 Snecma Disque de rotor de soufflante de turbomachine
JP2008180219A (ja) * 2007-01-18 2008-08-07 Snecma ターボ機械ファン用のロータディスク
US8246309B2 (en) 2007-01-18 2012-08-21 Snecma Rotor disk for turbomachine fan
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

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