EP1788198A2 - Befestigungssystem für Turbinenschaufeln und Verfahren - Google Patents

Befestigungssystem für Turbinenschaufeln und Verfahren Download PDF

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Publication number
EP1788198A2
EP1788198A2 EP20060124286 EP06124286A EP1788198A2 EP 1788198 A2 EP1788198 A2 EP 1788198A2 EP 20060124286 EP20060124286 EP 20060124286 EP 06124286 A EP06124286 A EP 06124286A EP 1788198 A2 EP1788198 A2 EP 1788198A2
Authority
EP
European Patent Office
Prior art keywords
retention
dovetail
hole
slot
connector
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Withdrawn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
EP20060124286
Other languages
English (en)
French (fr)
Inventor
Steven Eric Tomberg
Nick Martin
Stephen Paul Wassynger
Bruce Busbey
Lynn Charles Gagne
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP1788198A2 publication Critical patent/EP1788198A2/de
Withdrawn legal-status Critical Current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

Definitions

  • the invention relates to a retention system used to prevent axial and/or radial movement of a shaped object in a correspondingly shaped slot and, more particularly, to a retention system and method for retaining a turbine blade dovetail in a retention ring dovetail slot.
  • FIG. 1 is a cross section showing turbine blades in a conventional compressor.
  • the blades are typically secured via a dovetail section engaging a correspondingly shaped dovetail slot in a retaining ring.
  • Conventional practice for retaining a blade to a ring is through a process called staking, which locally deforms material around the blade dovetail using a hammer with a chisel or center punch.
  • a drawback of this practice is that the staking process is manual, which thereby allows for variation and may lead to disengagement of the fit during engine startup and shutdown.
  • the fit between the blade and the dovetail slot in the ring is loose to allow for assembly and tolerances. Therefore, if the blades are not properly retained, the loose fit may allow the hardware to move in the slot, leading to excessive wear. The excessive wear would eventually fail the part, requiring the unit to be shut down until a repair can be made.
  • radial movement of the blade in the dovetail slot allows for a variation of the tip radius during the machining process. Reduced variation in radial clearance could potentially increase performance and avoid excessive tip rubs.
  • a retention system retains a shaped object, such as a turbine blade dovetail, in a correspondingly shaped slot formed in a retention member.
  • the retention system includes a retention opening formed in the shaped object.
  • a through hole is formed in the retention member, wherein the through hole is positioned such that it is aligned with the retention opening when the shaped object is assembled in the correspondingly shaped slot.
  • a connector disposed in the through hole and engages the retention opening.
  • a method of retaining a turbine blade dovetail in a retention ring dovetail slot includes the steps of forming a retention opening in the blade dovetail; forming a through hole in the retention ring, wherein the through hole is positioned such that it is aligned with the retention opening when the dovetail is assembled in the dovetail slot; and securing a connector in the through hole and engaging the retention opening.
  • FIG. 2 is an exploded perspective view of the retention system of the invention for securing a gas turbine compressor blade 12 in a retention ring 14.
  • the turbine blade 12 includes a dovetail 16 at an end thereof which is assembled into a correspondingly-shaped dovetail slot 18 in the retention ring 14.
  • a retention slot 20 is formed in the blade dovetail 16. As shown in FIG. 2, the retention slot 20 is oriented substantially perpendicular to an insertion direction A of the dovetail 16 into the dovetail slot 18.
  • a through hole 22 is formed in the retention ring 14. The through hole 22 extends through the retention ring 14 and into the dovetail slot 18. In this context, the through hole 22 is positioned in the retaining ring 14 such that it is aligned with the retention slot 20 when the dovetail 16 is assembled in the dovetail slot 18.
  • a connector 24 such as a set screw, dowel pin, cap screw, flat head screw/bolt through the ring, or the like, is secured in the through hole 22 to engage the retention slot 20.
  • the turbine blade 12 is retained from displacement in at least an axial direction (corresponding to direction A in FIG. 2).
  • the connector 24 is preferably a set screw including a screw pin 26 and a head 28.
  • a diameter of the through hole 22 may be larger than a width of the retention slot 20.
  • a threaded fastener could be put in from the bottom before a blade is installed and tightened up from the outside.
  • the retention slot 20 is sized to receive the screw pin 26 either loosely, in a clearance fit, or in contact.
  • the through hole 22 preferably includes internal threads that are engaged by corresponding external threads on the set screw head 28. Any of multiple types of set screws may be used including without limitation, a flat point, a cup point, an oval point, a cone point, a half-dog point, and the like.
  • the assembled turbine blade is shown in FIG. 3.
  • the assembly provides retention of the compressor blade to prevent unnecessary movement in the slot and thereby prevent undesirable wear.
  • FIGS. 6-12 illustrate alternative configurations of the retaining system.
  • the retention slot 20 from the FIGS. 2 and 5 embodiment may alternatively be replaced with a hole 30 through the retention ring 14, and a the illustrated connector 24 is a half-dog point set screw.
  • This assembly can be added to an existing configuration by first drilling a hole through the retention ring 14 and into the dovetail 16, the hole 30 being sized to receive the point of the screw pin 26. A second hole sized for the set screw head 28 is then drilled in the retention ring 14. With the use of a hole 30 rather than a slot 20, the blade can be retained axially, circumferentially, and/or radially.
  • FIG. 7 illustrates a related embodiment wherein a length of the screw pin 26 is generally equal to a depth L of the retention opening, whether it be the retention slot 20 or the retention hole 30. In this manner, a radial load can be applied via the set screw 24 to the dovetail 16, the effect of which is described in more detail below.
  • the dovetail 16 does not include a slot or hole, but rather the connector 24 affixed in the through hole 22 engages a surface of the dovetail 16.
  • FIG. 9 shows a similar embodiment using a cup point set screw as the connector 24. Although such a configuration may have only limited retention capabilities, the radial load on the dovetail 16 by the connector 24 will serve to reduce undesirable relative movement of the dovetail 16 in the dovetail slot 18. Additionally, the radial load will affect damping characteristics of the blade.
  • FIG. 10 illustrates an embodiment using a relatively shallow slot/hole 20, 30 and a cone or oval point set screw as the connector 24.
  • FIG. 11 illustrates an embodiment using a V-shaped slot/hole 20, 30 and a cone point set screw as the connector 24.
  • FIG. 12 illustrates an alternative arrangement where the connector 24 is a dowel pin.
  • the through hole 22 has a consistent diameter substantially equivalent to a width of the retention slot 20 or a diameter of the retention hole 30 and is sized to receive the dowel pin.
  • a radial load can be applied to the dovetail 16, which causes a change in the damping characteristics of the blade.
  • aeromechanical damping can be tuned by controlling a radial load on the dovetail.
  • the damping characteristics can be further controlled by using plural retention openings, through holes and connectors for each dovetail to be retained.
  • the damping may also be tuned by varying the depth and/or width of the slot or hole to retain the blade axially, circumferentially and/or radially.
  • damping characteristics can be further tuned. Contact points in the exemplary embodiments are shown in FIGS. 5-12.
  • the retention system of various embodiments of the invention utilizes a simple connector in a compressor stator ring and blade assembly in order to fix a blade in a dovetail slot.
  • the system is applicable for newly manufactured machines and can be added to existing machines with a simple and inexpensive process.
  • the secure fit with the retention system prevents undesirable relative movement of parts that would result in excessive wear. Reduced variation in the radial clearance also potentially increases performance and avoids excessive tip rubs.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20060124286 2005-11-21 2006-11-17 Befestigungssystem für Turbinenschaufeln und Verfahren Withdrawn EP1788198A2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US28260305A 2005-11-21 2005-11-21

Publications (1)

Publication Number Publication Date
EP1788198A2 true EP1788198A2 (de) 2007-05-23

Family

ID=37685034

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20060124286 Withdrawn EP1788198A2 (de) 2005-11-21 2006-11-17 Befestigungssystem für Turbinenschaufeln und Verfahren

Country Status (2)

Country Link
EP (1) EP1788198A2 (de)
JP (1) JP2007138944A (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180347586A1 (en) * 2017-05-30 2018-12-06 Doosan Heavy Industries & Construction Co., Ltd. Vane ring assembly and compressor and gas turbine including the same
DE102009003714B4 (de) * 2008-04-04 2020-12-17 General Electric Co. Turbinenstatorschaufelhaltesystem und -verfahren
US11053805B2 (en) * 2018-01-22 2021-07-06 Doosan Heavy Industries & Construction Co., Ltd. Vane ring assembly, method of assembling the same, and gas turbine including the same
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

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8133019B2 (en) * 2009-01-21 2012-03-13 General Electric Company Discrete load fins for individual stator vanes
EP2295724B1 (de) * 2009-08-28 2012-02-29 Siemens Aktiengesellschaft Leitschaufel für eine axial durchströmbare Turbomaschine und zugehörige Leitschaufelanordnung
JP5598056B2 (ja) * 2010-03-30 2014-10-01 ヤマハ株式会社 カラオケ装置およびカラオケ曲紹介プログラム
JP5358559B2 (ja) * 2010-12-28 2013-12-04 株式会社日立製作所 軸流圧縮機
JP6229837B2 (ja) * 2013-12-24 2017-11-15 三菱日立パワーシステムズ株式会社 静翼セグメント、及びこれを備えている軸流流体機械
WO2016207942A1 (ja) * 2015-06-22 2016-12-29 三菱日立パワーシステムズ株式会社 静翼セグメント、及びこれを備えている軸流流体機械
JP5980405B1 (ja) 2015-12-24 2016-08-31 三菱日立パワーシステムズ株式会社 翼の取外方法、この方法を実行するための装置及び治具、この装置を備える翼セット

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009003714B4 (de) * 2008-04-04 2020-12-17 General Electric Co. Turbinenstatorschaufelhaltesystem und -verfahren
US20180347586A1 (en) * 2017-05-30 2018-12-06 Doosan Heavy Industries & Construction Co., Ltd. Vane ring assembly and compressor and gas turbine including the same
US11098732B2 (en) * 2017-05-30 2021-08-24 Doosan Heavy Industries & Construction Co., Ltd. Vane ring assembly and compressor and gas turbine including the same
US11053805B2 (en) * 2018-01-22 2021-07-06 Doosan Heavy Industries & Construction Co., Ltd. Vane ring assembly, method of assembling the same, and gas turbine including the same
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

Also Published As

Publication number Publication date
JP2007138944A (ja) 2007-06-07

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