EP2808490A1 - Turbine blade with locking pin - Google Patents

Turbine blade with locking pin Download PDF

Info

Publication number
EP2808490A1
EP2808490A1 EP13169635.3A EP13169635A EP2808490A1 EP 2808490 A1 EP2808490 A1 EP 2808490A1 EP 13169635 A EP13169635 A EP 13169635A EP 2808490 A1 EP2808490 A1 EP 2808490A1
Authority
EP
European Patent Office
Prior art keywords
blade
locking pin
rotor disc
protrusion
root portion
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Withdrawn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
EP13169635.3A
Other languages
German (de)
English (en)
French (fr)
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
Priority to EP13169635.3A priority Critical patent/EP2808490A1/en
Priority to US14/279,959 priority patent/US20140356178A1/en
Priority to RU2014120542/02A priority patent/RU2585579C2/ru
Priority to KR1020140062809A priority patent/KR101642983B1/ko
Priority to JP2014110844A priority patent/JP5970020B2/ja
Priority to CN201410233327.3A priority patent/CN104213941B/zh
Publication of EP2808490A1 publication Critical patent/EP2808490A1/en
Withdrawn legal-status Critical Current

Links

Images

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.
  • US4,349,318 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 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 protrusions107,108 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. After inserted, 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. However, as 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)
EP13169635.3A 2013-05-29 2013-05-29 Turbine blade with locking pin Withdrawn EP2808490A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP13169635.3A EP2808490A1 (en) 2013-05-29 2013-05-29 Turbine blade with locking pin
US14/279,959 US20140356178A1 (en) 2013-05-29 2014-05-16 Blade of a turbine
RU2014120542/02A RU2585579C2 (ru) 2013-05-29 2014-05-21 Лопаточный узел и способ его сборки
KR1020140062809A KR101642983B1 (ko) 2013-05-29 2014-05-26 터빈의 블레이드
JP2014110844A JP5970020B2 (ja) 2013-05-29 2014-05-29 タービンのブレード
CN201410233327.3A CN104213941B (zh) 2013-05-29 2014-05-29 涡轮的叶片

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP2808490A1 true EP2808490A1 (en) 2014-12-03

Family

ID=48482990

Family Applications (1)

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

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
US10669868B2 (en) 2016-12-22 2020-06-02 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 (10)

* Cited by examiner, † Cited by third party
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
EP0761930A1 (en) 1995-08-24 1997-03-12 ROLLS-ROYCE plc Seal and retention segments for the blades of an axial turbomachine
US5713721A (en) * 1996-05-09 1998-02-03 General Electric Co. Retention system for the blades of a rotary machine
GB2406144A (en) * 2003-09-19 2005-03-23 Rolls Royce Plc Gas turbine engine blade retention system using a key
EP1752611A1 (en) * 2005-08-12 2007-02-14 Siemens Aktiengesellschaft Turbine for a thermal power plant comprising a locking device
DE102009003320A1 (de) * 2008-01-10 2009-07-16 General Electric Company Turbinenkomponentenhalterungssystem
WO2012076581A1 (en) * 2010-12-09 2012-06-14 Alstom Technology Ltd Axial-flow machine
US20120177498A1 (en) * 2011-01-07 2012-07-12 General Electric Company Axial retention device for turbine system
US20120301308A1 (en) * 2011-05-26 2012-11-29 General Electric Company Gas turbine compressor last stage rotor blades with axial retention

Family Cites Families (11)

* 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
SU1714170A1 (ru) * 1990-02-23 1992-02-23 Ленинградский Кораблестроительный Институт Устройство дл фиксации от осевого смещени рабочих лопаток турбомашины
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
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
RU2330163C1 (ru) * 2006-11-01 2008-07-27 Открытое акционерное общество "Силовые машины-ЗТЛ, ЛМЗ, Электросила, Энергомашэкспорт" (ОАО "Силовые машины") Рабочее колесо газовой турбины
US8459953B2 (en) * 2010-01-19 2013-06-11 General Electric Company Seal plate and bucket retention pin assembly
US8714929B2 (en) * 2010-11-10 2014-05-06 General Electric Company Turbine assembly and method for securing a closure bucket
US8840375B2 (en) * 2011-03-21 2014-09-23 United Technologies Corporation Component lock for a gas turbine engine

Patent Citations (10)

* Cited by examiner, † Cited by third party
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
EP0761930A1 (en) 1995-08-24 1997-03-12 ROLLS-ROYCE plc Seal and retention segments for the blades of an axial turbomachine
US5713721A (en) * 1996-05-09 1998-02-03 General Electric Co. Retention system for the blades of a rotary machine
GB2406144A (en) * 2003-09-19 2005-03-23 Rolls Royce Plc Gas turbine engine blade retention system using a key
EP1752611A1 (en) * 2005-08-12 2007-02-14 Siemens Aktiengesellschaft Turbine for a thermal power plant comprising a locking device
DE102009003320A1 (de) * 2008-01-10 2009-07-16 General Electric Company Turbinenkomponentenhalterungssystem
WO2012076581A1 (en) * 2010-12-09 2012-06-14 Alstom Technology Ltd Axial-flow machine
US20120177498A1 (en) * 2011-01-07 2012-07-12 General Electric Company Axial retention device for turbine system
US20120301308A1 (en) * 2011-05-26 2012-11-29 General Electric Company Gas turbine compressor last stage rotor blades with axial retention

Cited By (1)

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

Also Published As

Publication number Publication date
US20140356178A1 (en) 2014-12-04
RU2585579C2 (ru) 2016-05-27
KR101642983B1 (ko) 2016-07-27
JP5970020B2 (ja) 2016-08-17
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

Similar Documents

Publication Publication Date Title
US7390170B2 (en) Device for assembling annular flanges together, in particular in a turbomachine
US7708529B2 (en) Rotor of a turbo engine, e.g., a gas turbine rotor
US4676723A (en) Locking system for a turbine side entry blade
US2749026A (en) Stator construction for compressors
EP2964886B1 (en) Disc arrangement and method of retaining two separate rotating members of a gas turbine engine
EP2660426B1 (en) Turbine assembly
JP2009507176A (ja) ロータにおける動翼の軸方向固定装置とその利用方法
US20170096903A1 (en) Retaining device for axially retaining a blade and rotor device with such a retaining device
US9784114B2 (en) Rotating assembly for a turbomachine
EP2841720B1 (en) System and method of limiting axial movement between a hanger and a fairing assembly in a turbine assembly
US8585369B2 (en) Device for axial retention of mobile vanes mounted on a rotor disc
US2722373A (en) Compressor casing and stator assembly
EP2808490A1 (en) Turbine blade with locking pin
EP3103966B1 (en) Anti-rotation knife edge seals and gas turbine engines including the same
US10570757B2 (en) Rotary assembly of a turbomachine equipped with an axial retention system of a blade
RU2692863C2 (ru) Ротор газотурбинного двигателя, содержащий лопатки с присоединяемыми платформами, и газотурбинный двигатель, содержащий такой ротор
US9982566B2 (en) Turbomachine, sealing segment, and guide vane segment
CN109072706B (zh) 用于包括分配器、涡轮机的结构元件和连接装置的涡轮机的组件
CN112189097B (zh) 改进的涡轮机风扇盘
US8277179B2 (en) Turbine or compressor stage for a turbomachine
US20080003100A1 (en) Methods and apparatus to facilitate sealing in a turbine
US10526978B2 (en) Assembly for attaching a nozzle to a structural element of a turbine engine
EP3926145A1 (en) Turbine stator blade
CN112534119A (zh) 具有设置在两个转子盘之间的转子构件的转子
WO2019109197A1 (zh) 涡轮轮罩

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20130529

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

R17P Request for examination filed (corrected)

Effective date: 20150601

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20181201