EP2378080A2 - Ensemble entretoise de blocage pour fixation circonférentielle d'aubes rotoriques - Google Patents

Ensemble entretoise de blocage pour fixation circonférentielle d'aubes rotoriques Download PDF

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Publication number
EP2378080A2
EP2378080A2 EP11162650A EP11162650A EP2378080A2 EP 2378080 A2 EP2378080 A2 EP 2378080A2 EP 11162650 A EP11162650 A EP 11162650A EP 11162650 A EP11162650 A EP 11162650A EP 2378080 A2 EP2378080 A2 EP 2378080A2
Authority
EP
European Patent Office
Prior art keywords
end portion
spacer assembly
locking spacer
profile
securing device
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Withdrawn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
EP11162650A
Other languages
German (de)
English (en)
Other versions
EP2378080A3 (fr
Inventor
Brian Denver Potter
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 EP2378080A2 publication Critical patent/EP2378080A2/fr
Publication of EP2378080A3 publication Critical patent/EP2378080A3/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Withdrawn legal-status Critical Current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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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

Definitions

  • the subject matter disclosed herein relates generally to turbine engines and, more particularly, to a blade assembly that may be used with a turbine engine.
  • At least some known turbine engines include a rotor, such as an axial compressor rotor, that includes a rotor blade assembly coupled thereto.
  • Known rotor blade assemblies include a plurality of circumferentially-spaced rotor blades arranged in rows spaced axially along the rotor.
  • the plurality of rotor blades are removably coupled to a wheel.
  • at least some known wheels include a groove defined therein that is sized and shaped to receive the plurality of rotor blades therein such that a blade root of each rotor blade is inserted in the groove.
  • a spacer is inserted into the groove to fill any remaining space in the groove between the first and last circumferentially spaced blades coupled in the groove.
  • At least some known spacers include multiple components that are assembles together to be locked into position.
  • centrifugal forces generated during operation of the turbine engine may cause known spacers to undesirably separate, which may enable the blades to shift circumferentially within the groove. Over time, continual movement of the rotor blades may cause damage to the rotor blade assembly and/or decrease the efficiency of the turbine engine.
  • a locking spacer assembly for use with a rotor blade assembly.
  • the locking spacer assembly includes a first end portion, a second end portion, at least one securing device, and a center portion positioned between the first end portion and the second end portion.
  • An opening is defined between the center portion and at least one of the first end portion and the second end portion. The opening is configured to receive the securing device.
  • a rotor blade assembly for use with a turbine engine.
  • the rotor blade assembly includes a wheel, a plurality of rotor blades coupled to the wheel, and a locking spacer assembly coupled to the wheel.
  • the locking spacer assembly includes a first end portion, a second end portion, at least one securing device, and a center portion positioned between the first end portion and the second end portion. An opening is defmed between the center portion and at least one of the first end portion and the second end portion. The opening is configured to receive the securing device.
  • a turbine engine in yet another aspect, includes a rotor and a rotor blade assembly.
  • the rotor blade assembly includes a wheel, a plurality of rotor blades coupled to the wheel, and a locking spacer assembly coupled to the wheel.
  • the locking spacer assembly includes a first end portion, a second end portion, at least one securing device, and a center portion positioned between the first end portion and the second end portion. An opening is defmed between the center portion and at least one of the first end portion and the second end portion. The opening is configured to receive the securing device.
  • a locking spacer assembly for use with a rotor blade assembly.
  • the locking spacer assembly includes a first end portion, a second end portion, at least one securing device, and a center portion that is positioned between the first and second end portions.
  • An opening is defined between the center portion and either the first end portion and/or the second end portion. The opening is sized and shaped to receive the securing device therein.
  • the locking spacer assembly may be used with circumferential attachments assembles with or without a loading groove. Notably, the locking spacer assembly described herein does not require a loading slot or a modified blade for the rotor blade assembly to be assembled.
  • FIG. 1 is a schematic illustration of an exemplary gas turbine engine system 100.
  • gas turbine engine system 100 includes, coupled in serial flow arrangement, a filter house 102, a compressor 104, a combustor assembly 106, and a turbine 108 that is rotatably coupled to compressor 104 via a rotor shaft 110.
  • ambient air enters filter house 102, wherein the ambient air is filtered. More specifically, in the exemplary embodiment, the filtered air is channeled through an air inlet (not shown) an is directed downstream towards compressor 104, wherein the filtered air is compressed prior to being discharged towards combustor assembly 106. The compressed air is mixed with fuel, and the resulting fuel-air mixture is ignited within combustor assembly 106 to generate combustion gases that flow towards turbine 108.
  • turbine 108 extracts rotational energy from the combustion gases and rotates a rotor shaft 110 that drives compressor 104.
  • gas turbine engine system 100 drives a load 112, such as a generator, coupled to rotor shaft 110.
  • FIGS. 2 and 3 are perspective illustrations of an exemplary rotor blade assembly 200 that is coupled to rotor shaft 110 (shown in FIG. 1 ).
  • rotor blade assembly 200 includes a wheel 202 and a plurality of rotor blades 204 that extend outward from a circumference 206 of wheel 202. More specifically, in the exemplary embodiment, each rotor blade 204 includes a blade root 208 that is inserted within a groove 210 that extends about circumference 206. Groove 210 is substantially similar about an entire circumference 206 of wheel 202. In the exemplary embodiment, each blade 204 has a shape and/or size that is substantially similar to the other blades 204.
  • wheel 202 includes a pair of flanges 212 that are positioned within groove 210. Flanges 212 cooperate with rotor blade root 208 to securely retain rotor blades 204 within groove 210. More specifically, each blade root 208 includes a recess 214 defined therein that is shaped and/or sized to engage flange 212 such that at least a portion of flange 212 is retained therein. Alternatively, each rotor blade 204 may include a flange, and wheel 202 may include a recess defined therein.
  • rotor blade assembly 200 also includes a plurality of spacers 216 that are positioned within groove 210 between adjacent circumferentially-spaced blades 204 to facilitate maintaining a distance therebetween.
  • groove 210 retains a plurality of alternating blade roots 208 and spacers 216.
  • spacers 216 include at least one locking spacer assembly 218, described in more detail below.
  • each spacer 216 includes a recess (not shown) defined therein that is shaped and/or sized to engage flange 212 such that at least a portion of flange 212 is retained therein.
  • the recess defined in spacer 216 is substantially similar in shape and size to recess 214.
  • blade 204 is coupled to wheel 202 as each blade root 208 is inserted within groove 210 and after each blade 204 is rotated until recess 214 engages flange 212.
  • spacer 216 is coupled to wheel 202 by inserting spacer 216 into groove 210 and by then rotating spacer 216 until the recess defined in spacer 216 engages flange 212.
  • a void 222 is defined to receive locking spacer assembly 218 therein.
  • FIGS. 4 and 5 are illustrations of an exemplary locking spacer assembly 218.
  • locking spacer assembly 218 includes a first end portion 402, a second end portion 404, and a center portion 406 that includes a first side 408 shaped and/or sized to engage first end portion 402 and a second side 410 shaped and/or sized to engage second end portion 404.
  • each end portion 402 and 404 is formed with a first profile 412
  • each side 408 and 410 is formed with a second profile 414 that is complementary to first profile 412.
  • first profile 412 is a female sliding dovetail profile
  • second profile 414 is a male sliding dovetail profile that is shaped complementarily to first profile 412.
  • first profile 412 mates against second profile 414 such that end portions 402 and 404 sufficiently interlock with center portion 406 to enable axial stresses to be transmitted along a longitudinal axis 416 of wheel 202 and/or to enables circumferential or hoop stresses to be transmitted along circumference 206.
  • end portions 402 and 404 are substantially similar in shape and size, and, as such, end portions 402 and 404 are interchangeable. More specifically, in the exemplary embodiment, first side 408 is substantially similar to second side 410. Alternatively, first end portion 402 may have a first configuration, first side 408 may have a first complementary configuration, second end portion 404 may have a second configuration that is different from the first configuration, and second side 410 may have a second complementary configuration that is different from first side 408. It should be understood that any of first end portion 402, second end portion 404, first side 408, and/or second side 410 may have any suitable shape and/or size that enables locking spacer assembly 218 to function as described herein.
  • first opening 418 is defined between first end portion 402 and center portion 406, and a second opening 420 is defined between second end portion 404 and center portion 406.
  • first opening 418 is shaped and/or sized to receive a first securing device 422 therein
  • second opening 420 is shaped and/or sized to receive a second securing device 424 therein.
  • securing devices 422 and 424 are each dowels that securely couple end portions 402 and 404 to center portion 406 such that portions 402, 404, and/or 406 do not move relative to one another.
  • Each securing device 422 and 424 is insertable such that a top 426 of each securing device 422 and 424 does not extend above a top of portion 402, 404, and/or 406.
  • securing devices 422 and 424 are set screws and/or grub screws that include a socket head such that a top of each securing device 422 and 424 does not extend above a top of portion 402, 404, and/or 406.
  • opening 418 and 420 are substantially similar in shape and size. As such, first securing device 422 and second securing device 424 are interchangeable. Alternatively, first opening 418 may have a first configuration, and second opening 420 may have a second configuration that is different from the first configuration such that first securing device 422 is different than second securing device 424. It should be understood that any of first opening 418, second opening 420, first securing device 422, and/or second securing device 424 may have any suitable shape and/or size that enables locking spacer assembly 218 to function as described herein. In the exemplary embodiment, openings 418 and 420 receive securing devices 422 and 424, respectively, to enable radial stresses to be transmitted along a radial direction 428 of wheel 202.
  • each end portion 402 and 404 includes a recess 430 defined therein that is positioned opposite first profile 412. More specifically, in the exemplary embodiment, recess 430 is shaped and/or sized to engage flange 212 such that at least a portion of flange 212 is retained therein. Notably, in the exemplary embodiment, recess 430 is shaped and sized substantially similarly to recess 214 and to the recess defined in spacer 216.
  • end portions 402 and 404 are inserted within void 222 and are moved in opposite directions along circumference 206 such that recess 430 engages flange 212.
  • center portion 406 is inserted between end portions 402 and 404 such that first side 408 engages first end portion 402 and second side 410 engages second end portion 404.
  • first securing device 422 is inserted into first opening 418
  • second securing device 424 is inserted into second opening 420 to securely couple end portions 402 and 404 to center portion 406 such that portions 402, 404, and/or 406 do not move relative to one another.
  • openings 418 and 420 receive securing devices 422 and 424, respectively, to enables radial stresses to be transmitted along a radial direction 428 of wheel 202.
  • the exemplary methods and systems provide a blade assembly that facilitates inserting blade roots and/or spacers within a groove that is substantially similar about a circumference of a wheel.
  • the methods and systems described enable locking a blade assembly such that adjacent turbine blades are not moved, thereby enabling repairing and/or replacing one turbine blade without disturbing the other turbine blades.
  • implementing the locking assembly facilitates reducing a time and/or cost associated with assembling the turbine engine.
  • the exemplary systems and methods are not limited to the specific embodiments described herein, but rather, components of each system and/or steps of each method may be utilized independently and separately from other components and/or method steps described herein. Each component and each method step may also be used in combination with other components and/or method steps.
EP11162650.3A 2010-04-16 2011-04-15 Ensemble entretoise de blocage pour fixation circonférentielle d'aubes rotoriques Withdrawn EP2378080A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/761,749 US20110255978A1 (en) 2010-04-16 2010-04-16 Locking Assembly For Circumferential Attachments

Publications (2)

Publication Number Publication Date
EP2378080A2 true EP2378080A2 (fr) 2011-10-19
EP2378080A3 EP2378080A3 (fr) 2013-12-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP11162650.3A Withdrawn EP2378080A3 (fr) 2010-04-16 2011-04-15 Ensemble entretoise de blocage pour fixation circonférentielle d'aubes rotoriques

Country Status (4)

Country Link
US (1) US20110255978A1 (fr)
EP (1) EP2378080A3 (fr)
JP (1) JP2011226475A (fr)
CN (1) CN102220885A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2672068B1 (fr) * 2012-06-06 2020-10-14 General Electric Company Ensemble de rotor de turbine et d'aubes avec un verrouillage d'aube en plusieurs parties

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Publication number Priority date Publication date Assignee Title
US9726026B2 (en) * 2012-06-06 2017-08-08 General Electric Company Turbine rotor and blade assembly with multi-piece locking blade
CN103362565B (zh) * 2013-07-04 2015-01-21 西安交通大学 一种汽轮机叶片阶梯状叶根结构及其与隔叶块配合结构
US9512732B2 (en) * 2013-10-16 2016-12-06 General Electric Company Locking spacer assembly inserted between rotor blades
US9416670B2 (en) * 2013-10-16 2016-08-16 General Electric Company Locking spacer assembly
US9518471B2 (en) * 2013-10-16 2016-12-13 General Electric Company Locking spacer assembly
KR101884712B1 (ko) * 2016-12-21 2018-08-03 두산중공업 주식회사 로터 블레이드용 로킹 스페이서
KR101920070B1 (ko) * 2016-12-23 2018-11-19 두산중공업 주식회사 로터 블레이드용 로킹 스페이서
US10800128B2 (en) * 2018-01-24 2020-10-13 General Electric Company Composite components having T or L-joints and methods for forming same

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US3721506A (en) * 1971-05-25 1973-03-20 Gen Electric Split-nut blade locking assembly
EP1028231B1 (fr) * 1999-02-12 2003-09-03 ALSTOM (Switzerland) Ltd Fixation d'aubes de rotor d'une turbomachine
DE10134611A1 (de) * 2000-12-16 2002-06-27 Alstom Switzerland Ltd Fixiervorrichtung für eine Beschaufelung einer Strömungsmaschine
DE10310432A1 (de) * 2003-03-11 2004-09-23 Alstom Technology Ltd Rotor-Schluss
DE10310431A1 (de) * 2003-03-11 2004-09-23 Alstom Technology Ltd Rotor-Schluss
CN2620090Y (zh) * 2003-05-30 2004-06-09 上海汽轮机有限公司 汽轮机转子反动式t型叶根末动叶片周向胀紧装置
US6929453B2 (en) * 2003-12-11 2005-08-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
DE102004011508A1 (de) * 2004-03-08 2005-09-29 Alstom Technology Ltd Rotor-Schluss
US7435055B2 (en) * 2005-03-29 2008-10-14 Siemens Power Generation, Inc. Locking spacer assembly for a turbine engine
EP1803900A1 (fr) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Ensemble de fermeture pour clore l'interstice restant entre la première et la dernière des aubes d'un anneau aubagé disposées dans la rainure circonférencielle d'une turbomachine, et turbomachine correspondante
EP1803899A1 (fr) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Ensemble de verrouillage d'aube pour une turbomachine
EP1978211A1 (fr) * 2007-04-04 2008-10-08 Siemens Aktiengesellschaft Dispositif de sécurité axiale sur des aubes mobiles d'un moteur tout comme turbine à gaz dotée d'un tel dispositif
US8425194B2 (en) * 2007-07-19 2013-04-23 General Electric Company Clamped plate seal

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2672068B1 (fr) * 2012-06-06 2020-10-14 General Electric Company Ensemble de rotor de turbine et d'aubes avec un verrouillage d'aube en plusieurs parties

Also Published As

Publication number Publication date
JP2011226475A (ja) 2011-11-10
EP2378080A3 (fr) 2013-12-18
US20110255978A1 (en) 2011-10-20
CN102220885A (zh) 2011-10-19

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