EP1840338A1 - Arrangement pour la fermeture axiale des palettes d'une turbine dans un rotor et gasturbine avec un tel arrangement - Google Patents

Arrangement pour la fermeture axiale des palettes d'une turbine dans un rotor et gasturbine avec un tel arrangement Download PDF

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Publication number
EP1840338A1
EP1840338A1 EP06006400A EP06006400A EP1840338A1 EP 1840338 A1 EP1840338 A1 EP 1840338A1 EP 06006400 A EP06006400 A EP 06006400A EP 06006400 A EP06006400 A EP 06006400A EP 1840338 A1 EP1840338 A1 EP 1840338A1
Authority
EP
European Patent Office
Prior art keywords
securing
hole
arrangement
groove
rotor
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.)
Granted
Application number
EP06006400A
Other languages
German (de)
English (en)
Other versions
EP1840338B1 (fr
Inventor
Harald Hoell
Harald Nimptsch
Reimar Dr. Schaal
Peter Schröder
Werner Dr. Setz
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP06006400A priority Critical patent/EP1840338B1/fr
Priority to AT06006400T priority patent/ATE520863T1/de
Publication of EP1840338A1 publication Critical patent/EP1840338A1/fr
Application granted granted Critical
Publication of EP1840338B1 publication Critical patent/EP1840338B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts

Definitions

  • the invention relates to an arrangement for axial securing of rotor blades in a rotor, having a shaft collar, on the outer circumference of which are provided in the axial direction of the rotor blade holding grooves, in each of which blades are arranged with the bucket feet corresponding blade feet, with a front side surface of the shaft collar, arranged in the region of the retaining projection, in which a radially outwardly open circumferential groove is provided and arranged in each blade radially inwardly open securing grooves, which in each case the circumferential groove radially opposite, wherein for axial securing of the blades in the circumferential groove and in the securing groove engaging sheet metal-shaped sealing elements are provided which form a frontal sealing ring in the circumferential direction, wherein for securing the sealing elements against displacement in the circumferential direction of at least one of the sealing elements a means having. Furthermore, the invention relates to a gas turbine with such an arrangement.
  • FIG. 1 shows such an arrangement in a plan view and FIG. 2 in a cross section according to section line II-II in FIG. 1.
  • two slightly overlapping sealing plates 16 are provided as sealing elements. which each cover the frontal opening of the blade holding groove 12 in half.
  • Each sealing plate 16 is inserted at its radially inner end 18 in an end face provided on a rotor disk 19 circumferential groove 20 and at its radially outer end 22 in a securing groove 24 which is provided on the underside 26 of a platform 28 of the blade 14.
  • a rectilinear sheet metal strip 30 is fixed to each, which extend substantially in the radial direction of the rotor 23.
  • Each sheet metal strip 30 terminates at its radially outer end 32 in a uniformly converging tip 34.
  • Chamfered edges 36 are provided on the platforms 28 of the blades 14, two opposite edges 36 of immediately adjacent turbine blades 14 forming a tapered recess 38 into which the tip 34 of the sheet metal strip 30 can protrude against the shift in the circumferential direction U to secure the sealing plate 16 and can rest.
  • the sealing plates 16 also provide for a separation of two areas 37, 39, in which on the one hand cooling air and on the other hand may enter a part of the hot gas.
  • two parallel slots 40 are provided in the latter, through which the already U-shaped pre-bent sheet metal strip 30 is used.
  • the tip 34 opposite end 41 of the sheet metal strip 30 is bent before the assembly of the sealing plate 16 on the rotor disk 19 in the position shown in FIG 2 for fixing the sheet metal strip 30.
  • the sealing plates 16 are successively threaded with the pre-assembled metal strips 30 in the endless circumferential, arranged on the rotor disk 19 circumferential groove 20 and arranged in the bottom 26 of the platform 28 securing groove 24.
  • the sealing plates 16 are positioned along the circumference of the circumferential groove 20 such that each sheet metal strip 30 faces a recess 38. Subsequently, the tips 34 of the sheet metal stiffeners 30 are bent into the recesses 38 in order to preclude a displacement of the sealing plates 16 in the circumferential direction U.
  • the metal strips may be bent only once due to the enormously high mechanical requirements, in the service case when replacing a blade of the then unfurled sheet metal strip is replaced by a new sheet metal strip.
  • the slots provided for receiving the metal strips in the sealing sheets weaken the sealing sheets.
  • Object of the present invention is to provide an alternative arrangement for securing the sealing elements against a threat of circumferential displacement, in which the assembly and disassembly times are improved.
  • Another object of the invention is to provide a gas turbine with such an arrangement.
  • the invention provides that in the generic arrangement, the means for securing the sealing elements against displacement in the circumferential direction provided in the sealing element opening and provided in the side surface of the shaft collar, with the opening approximately aligned hole and a seated in the hole and in the opening position-secured blocking element comprises.
  • the invention differs from the previous embodiment, in which a sheet metal strip entangled with the sealing element engages positively in a recess. Instead of the metal strip now a blocking element is provided, which can be used in the front side provided on the shaft collar hole.
  • the blocking element blocks a displacement of the sealing element in the circumferential direction, since it, arranged in the region of the sealing element, extends transversely to the circumferential groove, in which the sealing element sits and engages in the opening provided on the sealing element.
  • a slight and tolerable play of the sealing element along the circumferential groove is only possible insofar as the width seen in the circumferential direction of the opening is greater than the width of the blocking element to be considered in the circumferential direction.
  • a particularly reliable and simple axial securing of the sealing element against displacement in the circumferential direction can be achieved, which is required for assembly and disassembly.
  • the blocking element in each case used several times, i. can be assembled and disassembled, so that in the service case, the duration of maintenance can be reduced cost, since the recycling of each already used sealing element with a new sheet metal strip deleted. This reduces the service life of the gas turbine.
  • the sealing element previously debilitating slots, which were provided for attachment of the locking plate on the sealing element.
  • the rigidity of the sealing element is consequently further increased.
  • the blocking element formed as a bolt is secured in its position by the side wall of the hole has an endless annular groove and the bolt has an endless annular groove opposite recess in which a bolt securing clamping ring sits.
  • a clamping ring engages both in the arranged on the side wall endless annular groove and in this endless ring groove opposite, provided on the bolt circumferential recess.
  • the hole is a blind hole.
  • the blind bore has a depth which corresponds substantially to the length of the bolt. This ensures that the bolt for disassembly can be particularly easily removed from the hole and is not unnecessarily deep in this. Likewise, this achieves a simple and defined position of the bolt in the hole, so that it is always ensured that the provided in the side wall of the hole endless annular groove of the bolt provided on the circumferential recess is almost exactly opposite. This leads to a particularly simple and reliable installation of the clamping ring.
  • the clamping ring is designed as an open retaining ring for bores.
  • the retaining rings for holes are commercially available and have at its two opposite ends holes in which a tool for mounting and dismounting of the locking ring on the bolt and in the endless ring groove can engage. With the tool engaging in the holes, it is possible to move the ends toward one another and reduce the diameter of the clamping ring, which is necessary for insertion and release of the bolt in the hole equipped with the clamping ring.
  • the hole extending in the axial direction of the rotor in the side surface of the shaft ring is arranged such that it extends through the circumferential groove.
  • a weakening of the shaft collar or a rotor disk, which preferably forms the shaft collar, is thereby avoided.
  • the opening provided on the sealing element is then provided at the radially inner end of the sealing element. This area of the sealing element heats up the least during operation, so that the rigidity and the temperature resistance of the sealing element are not impaired by the opening.
  • every second or each sealing element has the means for securing the sealing elements against displacement.
  • the arrangement is provided on a rotor of a stationary gas turbine flowing in the axial direction.
  • FIG. 3 shows a section of the frontal plan view of the shaft collar 21 formed by a rotor disk 21 of a rotor 23 of a gas turbine.
  • the about the axis of rotation 50th rotatable rotor 23 has at its outer periphery 52 along the circumference U distributed, extending in the axial direction blade holding grooves 12, in each of which a blade 14 with the blade holding groove 12 corresponds executed blade root 54 can be inserted.
  • a blade 14 has already been inserted.
  • a projection 58 extending in the axial direction or widening with a circumferential groove 20 open radially outwards is arranged on an end face of the rotor disk 19 or on an end face 56 of the shaft collar 21.
  • the circumferential groove 20 is arranged, for example, radially further inward than the blade retaining grooves 12.
  • the rotor blade 14 has a platform 28 arranged between the blade root 54 and the profiled blade, on the underside of which a securing groove 24 open to the circumferential groove 20 is provided and in the process lies opposite to it.
  • a sealing element 42 is inserted into the endless circumferential groove 20 and into the securing groove 24 which secures the blade 14 against displacement along the blade retaining groove.
  • the sealing element 42 completely covers the end opening of one of the blade retaining grooves 12.
  • the sealing elements 42 are secured by one of the sealing elements 42 against displacement along the blade retaining groove 12.
  • sealing elements 42 may also be distributed over the circumference, as in the prior art, so that two immediately adjacent sealing elements each engage in half in the securing groove 24 of the blade 14. Then, two adjacent sealing elements secure one of the blades 14 against axial displacement.
  • an opening 63 is provided at the radially inner end 61 of the sealing element 42, which may be a notch, but also a bore.
  • a hole 65 is respectively provided on the side surface 56 of the shaft collar 21 in the region of the projection 58, which hole is substantially in the axial direction of the rotor 23, d. H. runs parallel to the axis of rotation 50.
  • a blocking element preferably a round bolt 67 is inserted, which is secured in its operating position.
  • the means for securing the sealing element 42 against displacement in the circumferential direction U thus comprises the opening 63 in the sealing element 42 and arranged in the end face of the rotor disk 19 hole 65, in which the sealing element 42 blocking bolt 67 is inserted.
  • the hole 65 is provided with an internal thread, as a blocking element also a screw screwed into the hole 65 can be used, which blocks the displacement.
  • a slight and tolerable play of the sealing element 42 along the circumferential groove 20 is only possible in so far as the width seen in the circumferential direction of the opening 63 is greater than the width to be considered in the circumferential direction or the diameter D B of the bolt 67.
  • the rotor disk 19 has, on its side surface 56, the hole 65 extending parallel to the axis of rotation 50, which hole is formed as a blind hole with a diameter D L.
  • the hole 65 is located radially so far from the axis of rotation 50, that it is arranged in the region of the projection 58, which is formed by the circumferential groove 20.
  • the hole 65 for example, conventionally produced by drilling, penetrates the projection 58, is interrupted by the circumferential groove 20 and continues in the rotor disk 19 as far as the bottom 66.
  • the sealing element 42 inserted from radially outward into the circumferential groove 20 is, as seen in the radial direction, held radially outward by the blade 14 seated in the blade retaining groove 12.
  • the seated in the hole 65 bolt 67 blocks a displacement of the sealing element 42, since the opening 63 limiting material of the sealing element 42 on the bolt 67 on one side, or on both sides, in einschender construction.
  • an endless circumferential annular groove 71 is provided on the circular cross-section in the side wall 69 of the hole 65, whereby the hole 65 has a slightly larger diameter D A in the axial section of the annular groove 71.
  • the enlarged diameter D A can be selected larger, for example, in up to three millimeters than the diameter D L of the hole 65 designed as a bore.
  • the bolt 67 has an in-mounted position of the endless annular groove 71 opposite, circumferential recess 75.
  • the diameter D B of the bolt 67 is reduced in the region of the recess 75 to a diameter D I.
  • a trained as an open locking ring 79 according to FIG 5 clamping ring 77 has at its two opposite ends 81 each have an opening 83 in which a suitable, not shown scissor-like or pincer-like Tool can engage to change the diameter D s of the clamping ring 77.
  • the clamping ring 77 usually made of resilient steel, can be reduced by means of the tool in its diameter D s by the two ends 81 are moved toward each other by means of the tool.
  • the corresponding sealing element 42 When mounting the assembly 10 for axial securing of blades 14 in a rotor 23, the corresponding sealing element 42 is inserted into the circumferential groove 20 from the outside after the introduction of a blade 14 in its retaining groove 12.
  • the outer end of the sealing element 42 is inserted into the arranged on the blade 14 securing groove 24 until the inner end 61 of the sealing element 42, the opening 63 of the sealing element 42 is approximately aligned with the hole 65.
  • the bolt 67 can be inserted into the hole 65 and the opening 63. Accordingly, the material surrounding the opening 63 of the sealing element 42 may not cover the hole 65.
  • a clamping ring 77 is slipped over the loose bolt 67, so that the clamping ring 77 rests in the endless circumferential recess 75 of the bolt 67 with play.
  • the outer diameter D s of the clamping ring 77 is reduced by the mutually moving the ends 81 so that it is smaller than the diameter D L of the hole 65. This makes it possible insert the pin 67 with the thus compressed clamping ring 77 in the blind hole 65 until the pin rests against the bottom of the blind hole. Then, the clamping ring 77 is disposed in the region of the endless annular groove 71.
  • the clamping ring 77 After removal of the tool, the clamping ring 77 expands and increases its outer diameter D s to a size which is greater than the diameter D L of the hole 65. At the same time then its inner diameter is smaller than the diameter D B of the bolt 67th Der Spannring 77 engages in this position in the arranged on the side wall 69 endless annular groove 71, without leaving the endless circumferential recess 75 to solve. Consequently, the clamping ring 77 is then hooked both with the bolt 67 and with the endless annular groove 71 and secured against unintentional release from the blind hole 65.
  • the tool is to be introduced from the front side of the rotor disk 19 into a gap 85 which is formed between the cylindrical surface of the bolt 67 and the side wall 69, so that this in the openings 83 of the clamping ring 77th can intervene.
  • the outer diameter D s of the clamping ring 77 is reduced by moving the two opposite ends 81 relative to each other.
  • the outer diameter D s of the clamping ring 77 is reduced so far that it is smaller than the diameter D L of the hole 65 and the surrounding of the side walls 69 cross-sectional opening.
  • the bolt 67 with the compressed clamping ring 77 can be pulled out of the hole 65.
  • the sealing element 42 is displaced in the circumferential direction until its outer end is no longer engaged in the securing groove 24, so that it can then be removed to the outside.
  • FIG 6 shows an alternative embodiment of the blocking element as a - relative to the bolt 67 shown in Figure 4 - shortened bolt 87.
  • the inserted in the rotor disk 19 bolt 87 secures the same way the sealing element 42 against displacement as the bolt 67th Der Bolt 87 is secured with a commercially available clamping ring 89 shown in FIG 7 against loosening from the hole 65, since in the operating position at least the clamping ring 89 inwardly projecting teeth 91 obstruct the displacement of the bolt 87 along the drilling axis of the drilled hole 65.
  • the assembly and disassembly of the clamping ring 89 is carried out separately, ie without bolts, but as described with a suitable tool which can engage in the openings 83 to change the diameter. To remove the bolt 87 from the hole 65, this has an end-side thread 93, in which a suitable tool can be screwed.
  • the invention provides an arrangement in which the known from the prior art disadvantages are eliminated by a bolt inserted from the front side of the shaft collar into a hole bolt blocks the displacement of the sealing element.
  • the bolt itself is secured against accidental loosening, this is hooked by means of a clamping ring with the rotor disk.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06006400A 2006-03-28 2006-03-28 Arrangement pour la fermeture axiale des palettes d'une turbine dans un rotor et gasturbine avec un tel arrangement Expired - Lifetime EP1840338B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP06006400A EP1840338B1 (fr) 2006-03-28 2006-03-28 Arrangement pour la fermeture axiale des palettes d'une turbine dans un rotor et gasturbine avec un tel arrangement
AT06006400T ATE520863T1 (de) 2006-03-28 2006-03-28 Anordnung zur axialsicherung an laufschaufeln in einem rotor sowie gasturbine mit einer solchen anordnung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06006400A EP1840338B1 (fr) 2006-03-28 2006-03-28 Arrangement pour la fermeture axiale des palettes d'une turbine dans un rotor et gasturbine avec un tel arrangement

Publications (2)

Publication Number Publication Date
EP1840338A1 true EP1840338A1 (fr) 2007-10-03
EP1840338B1 EP1840338B1 (fr) 2011-08-17

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ID=36829745

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EP06006400A Expired - Lifetime EP1840338B1 (fr) 2006-03-28 2006-03-28 Arrangement pour la fermeture axiale des palettes d'une turbine dans un rotor et gasturbine avec un tel arrangement

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EP (1) EP1840338B1 (fr)
AT (1) ATE520863T1 (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2008169838A (ja) * 2007-01-09 2008-07-24 Siemens Ag タービンロータにおけるロータ軸方向セグメント
EP2439378A3 (fr) * 2010-10-06 2014-08-13 General Electric Company Prévention de rotation de fil à freiner d'aube de turbine
EP2933436A1 (fr) * 2014-04-15 2015-10-21 Siemens Aktiengesellschaft Disque de roue doté d'au moins une tôle d'étanchéité
US20160265378A1 (en) * 2013-11-18 2016-09-15 Siemens Aktiengesellschaft Sealing system and gas turbine
KR101878360B1 (ko) * 2017-04-12 2018-07-13 두산중공업 주식회사 리테이너 조립구조를 포함하는 가스터빈 블레이드 조립체 및 이를 포함하는 가스터빈
CN114458391A (zh) * 2022-02-22 2022-05-10 中国联合重型燃气轮机技术有限公司 一种透平叶片锁紧组件
CN114810220A (zh) * 2021-01-29 2022-07-29 中国航发商用航空发动机有限责任公司 航空发动机
US11629604B2 (en) 2020-08-21 2023-04-18 Doosan Enerbility Co., Ltd. Structure for assembling turbine blade seals, gas turbine including the same, and method of assembling turbine blade seals
US12188375B2 (en) 2022-02-15 2025-01-07 Doosan Enerbility Co., Ltd. Structure for assembling turbine blade seals and gas turbine including the same

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1258662B (de) * 1964-10-28 1968-01-11 Goerlitzer Maschb Veb Deckscheibe fuer die Kuehlgasfuehrung von Gasturbinenlaeufern
GB1209419A (en) * 1968-06-24 1970-10-21 Westinghouse Electric Corp Side plates for turbine blades
US3572966A (en) * 1969-01-17 1971-03-30 Westinghouse Electric Corp Seal plates for root cooled turbine rotor blades
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
FR2524933A1 (fr) * 1982-04-13 1983-10-14 Snecma Dispositif de verrouillage axial d'aubes de rotor de turbine ou de compresseur

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1258662B (de) * 1964-10-28 1968-01-11 Goerlitzer Maschb Veb Deckscheibe fuer die Kuehlgasfuehrung von Gasturbinenlaeufern
GB1209419A (en) * 1968-06-24 1970-10-21 Westinghouse Electric Corp Side plates for turbine blades
US3572966A (en) * 1969-01-17 1971-03-30 Westinghouse Electric Corp Seal plates for root cooled turbine rotor blades
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
FR2524933A1 (fr) * 1982-04-13 1983-10-14 Snecma Dispositif de verrouillage axial d'aubes de rotor de turbine ou de compresseur

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8226366B2 (en) 2007-01-09 2012-07-24 Siemens Aktiengesellschaft Axial rotor section for a rotor of a turbine
JP2008169838A (ja) * 2007-01-09 2008-07-24 Siemens Ag タービンロータにおけるロータ軸方向セグメント
EP2439378A3 (fr) * 2010-10-06 2014-08-13 General Electric Company Prévention de rotation de fil à freiner d'aube de turbine
US8905717B2 (en) 2010-10-06 2014-12-09 General Electric Company Turbine bucket lockwire rotation prevention
US10087769B2 (en) * 2013-11-18 2018-10-02 Siemens Aktiengesellschaft Sealing system and gas turbine
US20160265378A1 (en) * 2013-11-18 2016-09-15 Siemens Aktiengesellschaft Sealing system and gas turbine
EP2933436A1 (fr) * 2014-04-15 2015-10-21 Siemens Aktiengesellschaft Disque de roue doté d'au moins une tôle d'étanchéité
KR101878360B1 (ko) * 2017-04-12 2018-07-13 두산중공업 주식회사 리테이너 조립구조를 포함하는 가스터빈 블레이드 조립체 및 이를 포함하는 가스터빈
US11629604B2 (en) 2020-08-21 2023-04-18 Doosan Enerbility Co., Ltd. Structure for assembling turbine blade seals, gas turbine including the same, and method of assembling turbine blade seals
CN114810220A (zh) * 2021-01-29 2022-07-29 中国航发商用航空发动机有限责任公司 航空发动机
CN114810220B (zh) * 2021-01-29 2024-02-20 中国航发商用航空发动机有限责任公司 航空发动机
US12188375B2 (en) 2022-02-15 2025-01-07 Doosan Enerbility Co., Ltd. Structure for assembling turbine blade seals and gas turbine including the same
CN114458391A (zh) * 2022-02-22 2022-05-10 中国联合重型燃气轮机技术有限公司 一种透平叶片锁紧组件

Also Published As

Publication number Publication date
EP1840338B1 (fr) 2011-08-17
ATE520863T1 (de) 2011-09-15

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