US20140356178A1 - Blade of a turbine - Google Patents

Blade of a turbine Download PDF

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Publication number
US20140356178A1
US20140356178A1 US14/279,959 US201414279959A US2014356178A1 US 20140356178 A1 US20140356178 A1 US 20140356178A1 US 201414279959 A US201414279959 A US 201414279959A US 2014356178 A1 US2014356178 A1 US 2014356178A1
Authority
US
United States
Prior art keywords
blade
locking pin
rotor disc
root portion
protrusion
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.)
Abandoned
Application number
US14/279,959
Other languages
English (en)
Inventor
Ivan Luketic
Marcel Koenig
Laura BOGDANIC
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 Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Assigned to ALSTOM TECHNOLOGY LTD reassignment ALSTOM TECHNOLOGY LTD ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KOENIG, MARCEL, LUKETIC, IVAN, Bogdanic, Laura
Publication of US20140356178A1 publication Critical patent/US20140356178A1/en
Assigned to GENERAL ELECTRIC TECHNOLOGY GMBH reassignment GENERAL ELECTRIC TECHNOLOGY GMBH CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: ALSTOM TECHNOLOGY LTD
Abandoned 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
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
    • 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
    • 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
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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
    • 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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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 present invention relates to a turbine, in particular, to a blade of turbine, more particularly, to a blade with a locking member to make axial fixation of the blade relative to the rotor disc.
  • a gas turbine has a rotor assembly which generally includes blades attached to a rotor disc.
  • Each blade comprises a root, a platform and an airfoil.
  • the root of each blade is usually of a so-called “fir tree” configuration to enable it to be firmly attached to the periphery of the disc and still have room for thermal expansion.
  • the “fir tree” attachment of a blade to the rotor disc is effective in restraining the radial and circumferential movements of the blades, relative to the rotor disc, against radial centrifugal forces.
  • a conventional solution is applying a tab washer to fix the blade root relative to the slots in the rotor disc.
  • the tab washer needs to be bent at assembly, which increases the complexity for the assembly process and may cause errors.
  • U.S. Pat. No. 4,349,318 discloses a blade retaining assembly including a continuous wire-type retainer, a generally cylindrical retaining plate and a split retainer ring. Annular grooves or recesses are machined out of the rotor disc and the roots of the blades for accommodating the individual retaining elements.
  • EP0,761,930A1 discloses a retention plate carried in radially inner and outer slots preventing axial movement of the blade roots in their slots.
  • a locking member is interposed between an adjacent pair of retention plates to prevent their circumferential movement relative to the disc. The locking member in turn interacts with the disc to anchor itself to the disc.
  • a blade of turbine comprising an aerofoil, a platform and a root portion configured to be slidingly received in mounting slots of a rotor disc.
  • the blade further comprises a locking member disposed on the root portion and engaged with the rotor disc to make axial fixation of the blade to the rotor disc.
  • the locking member is a locking pin disposed between the root portion and the rotor disc, the locking pin comprising a first protrusion to engage with a first groove in the root portion and a second protrusion to engage with a second groove in the rotor disc.
  • the first and second protrusions are arranged at one end of the locking pin to be received by the first and second groove respectively.
  • the locking pin comprises a third protrusion at the other end thereof to abut on a component arranged next to the blade in the axial direction of the rotor.
  • the component comprises a heat shield with an anti-rotation member to engage with the third protrusion of the locking pin.
  • the anti-rotation member is sized and positioned so that the anti-rotation member is engaged with the third protrusion of the locking pin as the first and second protrusions of the locking pin are engaged with the first and second grooves respectively.
  • the locking member or the locking pin is disposed at the both sides of the root portion.
  • the technical solution of the present invention provides a blade with simple and cost effective axial locking system to make axial fixation of the blade relative to the rotor disc, and also a fail-safe solution during assembly process.
  • FIG. 1 shows a schematic perspective view of a blade assembly of turbine with a locking pin according to embodiments of the present invention
  • FIG. 2 shows a front view of the blade assembly in FIG. 1 ;
  • FIG. 3 shows a cross-section side view of the blade assembly.
  • FIG. 1 shows a schematic view of a blade assembly of turbine according to embodiments of the present invention.
  • the blade 100 comprises an aerofoil 111 , a platform 112 and a root portion 101 .
  • the “fir tree” type root portion is configured to be received in the mounting slots of a rotor disc 102 .
  • the rotor disc 102 is not shown in FIG. 1 , but can be seen from FIG. 3 , which shows a cross section view of the assembly of the root portion 101 and the rotor disc 102 .
  • the blade 100 further comprises a locking member disposed on the root portion 101 and engaged with the rotor disc 102 , so as to make axial fixation of the blade relative to the rotor disc 102 .
  • the locking member is embodied as a locking pin 106 as shown in FIG. 1 .
  • the locking pin 106 is disposed between the rotor portion 101 and the rotor disc 102 , which can be seen from the cross-section view of FIG. 3 .
  • a first protrusion 107 and a second protrusion 108 are respectively disposed on the locking pin 106 in the radial direction.
  • a first groove 104 is arranged on the root portion 101 to receive the first protrusion 107 ; a second groove 105 is arranged on the rotor disc 102 to receive the second protrusion 108 .
  • the first protrusion 107 and the second protrusion 108 are arranged at one end of the locking pin 106 in the radial direction.
  • the first groove 104 and the second groove 105 are respectively formed on the root portion 101 and the rotor disc 102 at the corresponding position to receive the first protrusion 107 and the second protrusion 108 .
  • the two protrusions are not necessarily arranged at the same end of the locking pin 106 .
  • the protrusions 107 , 108 may also be staggered along the axial direction of the locking pin 106 , as long as they are received in the corresponding grooves respectively.
  • a third protrusion 109 is arranged at the other end of the locking pin 106 opposite to the one end where the protrusions 107 , 108 is disposed.
  • a heat shield 103 is arranged next to the root portion 101 of the blade in the axial direction.
  • the heat shield 103 comprises an anti-rotation member 110 .
  • the anti-rotation member 110 is sized and positioned so that it is engaged with the third protrusion 109 of the locking pin 106 as the first and second protrusions 107 and 108 of the locking pin 106 are engaged with the first and second grooves 104 and 105 respectively.
  • the locking pin 106 will be inserted between the root portion 101 and the rotor disc 102 .
  • the locking pin 106 needs to be rotated by a certain degrees so that the first and second protrusions 107 and 108 can be locked into the corresponding grooves 104 and 105 , respectively.
  • the protrusions 107 , 108 and grooves 104 , 105 may not be visible after insertion of the locking pin 106 , it is difficult to evaluate whether the pin is installed in position.
  • the anti-rotation member 110 may also function as position element for the locking pin 106 .
  • the heat shield 103 will be assembled in axial direction next to the root portion 101 .
  • the anti-rotation member 110 will be stuck on the third protrusion 109 .
  • the heat shield 103 cannot be assembled in position. Only when the locking pin 106 is rotated into lock position, the heat shield 103 can be installed correctly with the anti-rotation member 110 being engaged with the third protrusion 109 .
  • a fail-safe feature for assembling the locking pin is achieved.
  • the anti-rotation member may also be arranged on other components than the heat shield as far as the fail-safe feature for assembling the locking pin is achieved.
  • the locking pins 106 can be disposed at the both sides of each root portion 101 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/279,959 2013-05-29 2014-05-16 Blade of a turbine Abandoned US20140356178A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP13169635.3 2013-05-29
EP13169635.3A EP2808490A1 (en) 2013-05-29 2013-05-29 Turbine blade with locking pin

Publications (1)

Publication Number Publication Date
US20140356178A1 true US20140356178A1 (en) 2014-12-04

Family

ID=48482990

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/279,959 Abandoned US20140356178A1 (en) 2013-05-29 2014-05-16 Blade of a turbine

Country Status (6)

Country Link
US (1) US20140356178A1 (zh)
EP (1) EP2808490A1 (zh)
JP (1) JP5970020B2 (zh)
KR (1) KR101642983B1 (zh)
CN (1) CN104213941B (zh)
RU (1) RU2585579C2 (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180179903A1 (en) * 2016-12-22 2018-06-28 Nuovo Pignone Tecnologie Srl Turbine blade and locking set

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7385992B2 (ja) * 2018-12-28 2023-11-24 川崎重工業株式会社 回転体の動翼およびディスク

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2942842A (en) * 1956-06-13 1960-06-28 Gen Motors Corp Turbine blade lock
US20110176923A1 (en) * 2010-01-19 2011-07-21 General Electric Company Seal plate and bucket retention pin assembly

Family Cites Families (19)

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Publication number Priority date Publication date Assignee Title
US4349318A (en) 1980-01-04 1982-09-14 Avco Corporation Boltless blade retainer for a turbine wheel
JPS60192201U (ja) * 1984-05-30 1985-12-20 株式会社東芝 蒸気タ−ビンの動翼固定構造
SU1714170A1 (ru) * 1990-02-23 1992-02-23 Ленинградский Кораблестроительный Институт Устройство дл фиксации от осевого смещени рабочих лопаток турбомашины
GB9517369D0 (en) 1995-08-24 1995-10-25 Rolls Royce Plc Bladed rotor
US5713721A (en) * 1996-05-09 1998-02-03 General Electric Co. Retention system for the blades of a rotary machine
UA66385C2 (uk) * 2001-01-03 2004-05-17 Центр Науково-Дослідних Та Дослідно-Конструкторських Робіт "Машпроект" Державного Підприємства "Науково-Виробничий Комплекс Газотурбобудування "Зоря"-" Машпроект" Вузол кріплення робочих лопаток ротора осьової турбомашини та спосіб його складання
US6652237B2 (en) * 2001-10-15 2003-11-25 General Electric Company Bucket and wheel dovetail design for turbine rotors
CN1497131A (zh) * 2002-10-18 2004-05-19 通用电气公司 有利于防止燃气涡轮发动机的叶片损坏的方法和装置
US6893224B2 (en) * 2002-12-11 2005-05-17 General Electric Company Methods and apparatus for assembling turbine engines
GB2406144A (en) * 2003-09-19 2005-03-23 Rolls Royce Plc Gas turbine engine blade retention system using a key
JP4869616B2 (ja) * 2005-04-01 2012-02-08 株式会社日立製作所 蒸気タービン動翼と蒸気タービンロータ及びそれを用いた蒸気タービン並びにその発電プラント
DE602005005988T2 (de) * 2005-08-12 2009-05-20 Siemens Aktiengesellschaft Turbine für eine Wärmekraftanlage mit Haltevorrichtung
RU2330163C1 (ru) * 2006-11-01 2008-07-27 Открытое акционерное общество "Силовые машины-ЗТЛ, ЛМЗ, Электросила, Энергомашэкспорт" (ОАО "Силовые машины") Рабочее колесо газовой турбины
US8061995B2 (en) * 2008-01-10 2011-11-22 General Electric Company Machine component retention
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RU2557826C2 (ru) * 2010-12-09 2015-07-27 Альстом Текнолоджи Лтд Газовая турбина с осевым потоком горячего воздуха и осевой компрессор
US20120177498A1 (en) * 2011-01-07 2012-07-12 General Electric Company Axial retention device for turbine system
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Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2942842A (en) * 1956-06-13 1960-06-28 Gen Motors Corp Turbine blade lock
US20110176923A1 (en) * 2010-01-19 2011-07-21 General Electric Company Seal plate and bucket retention pin assembly

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180179903A1 (en) * 2016-12-22 2018-06-28 Nuovo Pignone Tecnologie Srl Turbine blade and locking set
US10669868B2 (en) * 2016-12-22 2020-06-02 Nuovo Pignone Tecnologie Srl Turbine blade and locking set

Also Published As

Publication number Publication date
RU2585579C2 (ru) 2016-05-27
KR101642983B1 (ko) 2016-07-27
JP5970020B2 (ja) 2016-08-17
EP2808490A1 (en) 2014-12-03
CN104213941B (zh) 2016-03-23
JP2014231839A (ja) 2014-12-11
CN104213941A (zh) 2014-12-17
KR20140140497A (ko) 2014-12-09
RU2014120542A (ru) 2016-01-10

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Legal Events

Date Code Title Description
AS Assignment

Owner name: ALSTOM TECHNOLOGY LTD, SWITZERLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:LUKETIC, IVAN;KOENIG, MARCEL;BOGDANIC, LAURA;SIGNING DATES FROM 20140706 TO 20141013;REEL/FRAME:033940/0779

AS Assignment

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, SWITZERLAND

Free format text: CHANGE OF NAME;ASSIGNOR:ALSTOM TECHNOLOGY LTD;REEL/FRAME:039714/0578

Effective date: 20151102

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO PAY ISSUE FEE