EP1164251A1 - Schloss zur Sicherung von Laufschaufeln - Google Patents

Schloss zur Sicherung von Laufschaufeln Download PDF

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Publication number
EP1164251A1
EP1164251A1 EP01401535A EP01401535A EP1164251A1 EP 1164251 A1 EP1164251 A1 EP 1164251A1 EP 01401535 A EP01401535 A EP 01401535A EP 01401535 A EP01401535 A EP 01401535A EP 1164251 A1 EP1164251 A1 EP 1164251A1
Authority
EP
European Patent Office
Prior art keywords
groove
locking element
screw
blades
locking
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
EP01401535A
Other languages
English (en)
French (fr)
Other versions
EP1164251B1 (de
Inventor
Christian Yvon Goga Jean-Luc
Naudet Jacky
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1164251A1 publication Critical patent/EP1164251A1/de
Application granted granted Critical
Publication of EP1164251B1 publication Critical patent/EP1164251B1/de
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
    • F01D5/32—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
    • F01D5/3023—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

Definitions

  • the invention relates to a device for blocking blades in the peripheral groove of a turbomachine disk, said blades with hammer-type feet likely to be introduced into said groove through a loading window and held in said groove by form cooperation with the side walls of the latter, said blocking device being capable of being introduced in said groove through said loading window and comprising a locking element capable of being reassembled in a housing latch formed in the side walls of said groove under the action a radial operating screw whose head is supported on the bottom of the groove.
  • the screw head which is wider than the barrel is housed in an imprint made in the bottom of the groove to the right of the housing corresponding lock. Because the screw head is wider than the barrel, the screw is made captive.
  • the locking element consists of a protrusion formed on the upper face of a body which in the locked position of the device is resting against the side walls of the groove in the vicinity of the groove of the groove. This body has a lower base which, in the position of locking device, is away from the screw head, to allow the sliding of said body in the groove during assembly of the blades. Indeed to allow this sliding, the protrusion formed on the body must be in the groove, the base of the body is then in support on the screw head and located near the bottom of the groove.
  • the one-piece piece formed by the body and its protrusion does not include positive guiding means during sliding in the groove during assembly.
  • the screw head can therefore be poorly positioned in its imprint during tightening, which may result in a subsequent displacement of the screw head during the operation of the turbomachine and by a loss of the bracing effect. Tightening the incorrectly positioned screw can also lead to seizure of the thread, which can maintain the protuberance in the latch housing, but which subsequently causes difficulties in dismantling the device during maintenance operations.
  • the object of the invention is to propose a device for locking of the type mentioned in the preamble which, in operating mode of the turbomachine, cannot loosen and which prevents the seizure of the screw during assembly.
  • the invention achieves its object by the fact that the element of locking device is axially sliding in a radial opening of a body having a section adapted to the section of the groove and by the causes the screw head to be trapped between the bottom of the groove and the base of the body.
  • the body is guided when it slides in the groove, which ensures a precise radial direction of the axis of the screw and prevents seizures.
  • the screw head is radially immobilized with respect to the body, and the action of centrifugal forces on the element of locking, in the event of partial loosening of the screw, prevents it from turn, because the screw head is then in positive support against the base from the body.
  • the proposed device is characterized by the has a body arranged between the feet of a pair of blades and having a section adapted to the section of said groove, said body having a lower base located above the bottom of the groove and a through radial opening of non-circular cross section in which the locking element is slidably mounted under the action of the operating screw, and by the fact that the screw head is dimensioned so as to remain trapped between the bottom of the groove and the base of the body.
  • the device also comprises means for limit the rise of the locking element.
  • the means to limit the rise of the element of interlocking have cooperating abutment surfaces formed in correspondence on the locking element and the body.
  • the locking element can be retracted into the body. This guarantees the sliding of the device in the groove during assembly.
  • Figure 3 shows in section a wheel disc 1 of turbomachine which has at its periphery a groove 2 intended for maintain the feet of blades with hammer attachment type.
  • This groove 2 delimited by side walls 3a and 3b of curvilinear section, opens outwards by a groove 4 which has a dimension, in the direction of the axis of rotation of the wheel, less than the dimension of the cavity 5 formed in the bottom of groove 2.
  • the feet of the blades have a section according to the plan radial passing through the axis of rotation of the disc 1 adapted to the section of the groove 2 in order to be held there by form cooperation.
  • FIG. 1 is a top view of part of the disc 1.
  • the side walls 3a and 3b have opposite a first pair of radial notches 6a and 6b which constitute a loading window, allowing the introduction feet 7 of the blades 8 in the groove 2 during the mounting of these blades 8, as well as a second pair of radial notches 9a, 9b which constitute a housing for the lock of a device for locking vanes object of the invention.
  • the second pair of notches 9a, 9b is angularly offset from the first pair of notches 6a, 6b by a distance equal to the angle formed by two consecutive blades or at a multiple of this angle.
  • the same wheel disc 1 can include several locking devices according to the invention.
  • FIG. 2 shows the same disc part 1 fitted with its blades 8.
  • Each blade 8 has, between its foot 7 and its part aerodynamics 10, a platform 11 which covers the periphery of the disc 1, all of the platforms 11 of the vanes 8 delimiting internally the gas flow vein.
  • each blade 8 is successively introduced in groove 2 through the window formed by the first pair notches 6a, 6b and the blade 8 is made to slide in the direction of the arrow F until its platform 11 abuts against the platform of the dawn previously introduced.
  • vanes 8 are identical except for the penultimate climb, referenced 8a, and the last climb, referenced 8b, which have on the adjacent edges of their platforms 11a and 11b notches 12a and 12b which constitute an orifice 13 whose function will be explained later in this brief.
  • the blocking device 14 shown in perspective is introduced in Figure 4 through the loading window in the groove 2, then we position the foot 7 of the last dawn 8b in the loading window between the last dawn on 8a and the first dawn on and we do slide the assembly of all the vanes 8 in the direction of the arrow F, an angle corresponding to the half measure of the angle between two blades consecutively, so that platforms 11 and 11b of the first blade up and the last blade 8b joined according to the median plane of the loading window constituted by the first pair of notches 6a and 6b. In this position, the blocking 14 disposed between the feet 7 of the vanes 8a and 8b is located opposite of the second pair of notches 9a and 9b.
  • the notches 9a and 9b have axial dimensions and peripheral lower than those of the notches 6a and 6b of the window loading the vanes 8, to prevent the vanes from escaping 8 when they pass in front of these notches 9a and 9b.
  • the blocking 14 consists of three parts, namely a body 15, shown in detail in Figures 5 to 7, a locking element 16, shown in detail in FIGS. 8 to 10 and an operating screw 17 visible in FIG. 11.
  • the body 15 has a section along a radial plane passing through the axis of rotation of the disc 1, substantially equal to that of a foot 7 of the blade 8, except that this body 15 has a lower base 20 located at little distance from the bottom of the groove 2 and which delimits with this bottom a sufficient space 21 to accommodate the head of the screw 17, so that the screw 17 is practically immobilized radially with respect to the body 15, as well as this is explained later in this brief.
  • the body 15 is thus held in groove 2 by form cooperation with the walls lateral 3a and 3b of groove 2 and is perfectly guided during its sliding in the groove 2.
  • the body 15 has an orifice radial through 22, of non-circular cross section, generally rectangular, in which the locking element slides.
  • the locking element 16 has a substantially equal section to the section of the radial through hole 22. Its height is substantially equal to the height of the body 15, and preferably this height is slightly less than the height of the body 15, so that in the position lowered, shown in Figure 4, the locking element 16 is completely retracted into the radial orifice 22 of the body 15. This position lowered corresponds to the position of assembly or disassembly of the blades 8.
  • the locking element 16 also has a radial thread 30 equipped with a thread 31 intended to cooperate with the thread of the barrel 40 of the operating screw 17. On the sides of the locking element 16, located facing the windows 22a and 22b of the body 15, are formed stops side 32a and 32b which slide respectively in the windows 22a and 22b.
  • the operating screw 17 has a large screw head 41 dimension which accommodates in the space 21 delimited by the base 20 of the body 15 and the bottom of the groove 2.
  • the diameter of this head 41 is such that its face upper 42 can be in abutment against the base 20 of the body 15.
  • the end 43 of the operating screw 17 opposite the screw head 41 is housed in the orifice 13 formed by the notches 12a and 12b of the platforms 11a and 11b. This end 43 is provided with means cooperating with a key tightening, a hexagon key or an Allen key for example.
  • the locking device 14 Before mounting the locking device 14 in the groove 2, first screwing the operating screw on the locking element 16 by the underside of the latter, then we mount the assembly in the orifice passing through radial 22 of the body 15 through the base 20, so that the base 20 is in abutment against the upper face 42 of the screw head 41, and in such a way that the locking element 16 completely accommodates in the radial through hole 22.
  • the locking device 14 By retaining the operating screw 17 by its end 43, the locking device 14 can be mounted in the groove 2 through the blade loading window 8.
  • the operating screw 17 is pivoted by means of a screwing tool cooperating with the end 43, in order to reassemble the locking element 16 partially in the housing lock formed by the notches 9a and 9b, until the faces upper stops 32a and 32b of the locking element 16 are resting on the upper faces 23a and 23b of the windows 22a and 22b of the body 15.
  • the screw head is in contact with the bottom of the groove 2 and the body 15 is supported on the side walls 3a and 3b of groove 2.
  • the locking element 16 can come out of its lock housing, it would require a significant rotation of the screw to drive the locking element in the radial transverse orifice 22, then that it is naturally pushed outward by centrifugal forces.
  • the invention thus ensures a secure blocking of the blades 8 on the disc 1.

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)
  • Clamps And Clips (AREA)
EP01401535A 2000-06-15 2001-06-14 Schloss zur Sicherung von Laufschaufeln Expired - Lifetime EP1164251B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0007610A FR2810366B1 (fr) 2000-06-15 2000-06-15 Dispositif de blocage d'aubes a attaches marteau sur un disque
FR0007610 2000-06-15

Publications (2)

Publication Number Publication Date
EP1164251A1 true EP1164251A1 (de) 2001-12-19
EP1164251B1 EP1164251B1 (de) 2006-01-04

Family

ID=8851276

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01401535A Expired - Lifetime EP1164251B1 (de) 2000-06-15 2001-06-14 Schloss zur Sicherung von Laufschaufeln

Country Status (10)

Country Link
US (1) US6464463B2 (de)
EP (1) EP1164251B1 (de)
JP (1) JP4043733B2 (de)
CA (1) CA2349692C (de)
DE (1) DE60116460T2 (de)
ES (1) ES2251446T3 (de)
FR (1) FR2810366B1 (de)
RU (1) RU2222700C2 (de)
UA (1) UA57883C2 (de)
WO (1) WO2001096711A1 (de)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1321630A2 (de) * 2001-12-21 2003-06-25 Nuovo Pignone Holding S.P.A. Verbindungs- und Verriegelungssystem für die Laufschaufeln eines Axialverdichters
WO2012110735A1 (fr) 2011-02-16 2012-08-23 Snecma Dispositif de blocage circonferentiel d'aubes pour turbomachine, a deploiement radial par mouvement de rotation d'un organe du dispositif
FR2973066A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
FR2973068A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
FR2973067A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
WO2012131227A1 (fr) * 2011-03-21 2012-10-04 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
CN103726885A (zh) * 2012-10-12 2014-04-16 航空技术空间股份有限公司 在转子周向槽中的鼓轮叶片锁件
CN104481594A (zh) * 2014-10-28 2015-04-01 哈尔滨汽轮机厂有限责任公司 用于压气机周向环状燕尾型叶根的锁紧装置
EP3696380A1 (de) * 2019-02-04 2020-08-19 Rolls-Royce plc Adapter zur positionierung eines bearbeitungswerkzeugs zwischen zwei tragflügeln

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2832455B1 (fr) * 2001-11-22 2004-04-02 Snecma Moteurs Dispositif de blocage des aubes dans une rainure d'un disque
US6929453B2 (en) * 2003-12-11 2005-08-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
FR2873745B1 (fr) 2004-07-28 2008-10-10 Snecma Moteurs Sa Disque de rotor de turbomachine
US7435055B2 (en) * 2005-03-29 2008-10-14 Siemens Power Generation, Inc. Locking spacer assembly for a turbine engine
FR2886336B1 (fr) * 2005-05-26 2007-08-24 Snecma Moteurs Sa Perfectionnement a une roue aubagee de rotor pour renforcer le verrouillage des aubes
US8206116B2 (en) * 2005-07-14 2012-06-26 United Technologies Corporation Method for loading and locking tangential rotor blades and blade design
EP1801355B1 (de) * 2005-12-23 2015-02-11 Techspace Aero Laufschaufelschloss für eine Turbomaschinenrotorscheibe
US8608446B2 (en) * 2006-06-05 2013-12-17 United Technologies Corporation Rotor disk and blade arrangement
US7581931B2 (en) * 2006-10-13 2009-09-01 Siemens Energy, Inc. Gas turbine belly band seal anti-rotation structure
JP4886735B2 (ja) * 2008-05-26 2012-02-29 株式会社東芝 タービン動翼組立体および蒸気タービン
FR2940354B1 (fr) * 2008-12-23 2015-01-09 Snecma Dispositif de fixation d'aubes a attache marteau et disque de compresseur adapte.
GB0908502D0 (en) * 2009-05-19 2009-06-24 Rolls Royce Plc A balanced rotor for a turbine engine
US8523529B2 (en) 2009-11-11 2013-09-03 General Electric Company Locking spacer assembly for a circumferential entry airfoil attachment system
US8414268B2 (en) * 2009-11-19 2013-04-09 United Technologies Corporation Rotor with one-sided load and lock slots
FR2965008B1 (fr) * 2010-09-16 2013-08-02 Snecma Disque a aubes pour rotor de turbomachine, et turbomachine equipee d'un tel disque
JP5730085B2 (ja) * 2011-03-17 2015-06-03 三菱日立パワーシステムズ株式会社 ロータ構造
US9004872B2 (en) * 2011-07-18 2015-04-14 United Technologies Corporation Bearing surface combined load-lock slots for tangential rotors
US10107114B2 (en) 2011-12-07 2018-10-23 United Technologies Corporation Rotor with relief features and one-sided load slots
US9341070B2 (en) * 2012-05-30 2016-05-17 United Technologies Corporation Shield slot on side of load slot in gas turbine engine rotor
US9341071B2 (en) * 2013-10-16 2016-05-17 General Electric Company Locking spacer assembly
DE102013223583A1 (de) 2013-11-19 2015-05-21 MTU Aero Engines AG Schaufel-Scheiben-Verbund, Verfahren und Strömungsmaschine
DE102013223607A1 (de) * 2013-11-19 2015-05-21 MTU Aero Engines AG Rotor einer Strömungsmaschine
RU2570087C1 (ru) * 2014-08-22 2015-12-10 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Рабочее колесо ротора газотурбинного двигателя с демпфированием вибрационных колебаний
RU2674812C1 (ru) * 2017-10-05 2018-12-13 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Устройство фиксации лопаток ротора компрессора газотурбинного двигателя
KR102454379B1 (ko) * 2020-09-08 2022-10-14 두산에너빌리티 주식회사 로터 및 이를 포함하는 터보머신

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2315631A (en) * 1942-02-14 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade locking apparatus
GB659592A (en) * 1948-09-17 1951-10-24 Sulzer Ag Improvements relating to rotors for turbines or axial flow compressors
US3088708A (en) * 1961-12-29 1963-05-07 Seymour J Feinberg Compressor blade locking device
US3216700A (en) * 1963-10-24 1965-11-09 Gen Electric Rotor blade locking means
DE2237348B1 (de) * 1972-07-29 1974-01-24 Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur sicherung der laufschaufeln von stroemungsmaschinen
GB2156908A (en) * 1984-03-30 1985-10-16 Rolls Royce Bladed rotor assembly for gas turbine engine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2315631A (en) * 1942-02-14 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade locking apparatus
GB659592A (en) * 1948-09-17 1951-10-24 Sulzer Ag Improvements relating to rotors for turbines or axial flow compressors
US3088708A (en) * 1961-12-29 1963-05-07 Seymour J Feinberg Compressor blade locking device
US3216700A (en) * 1963-10-24 1965-11-09 Gen Electric Rotor blade locking means
DE2237348B1 (de) * 1972-07-29 1974-01-24 Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur sicherung der laufschaufeln von stroemungsmaschinen
GB2156908A (en) * 1984-03-30 1985-10-16 Rolls Royce Bladed rotor assembly for gas turbine engine

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1321630A2 (de) * 2001-12-21 2003-06-25 Nuovo Pignone Holding S.P.A. Verbindungs- und Verriegelungssystem für die Laufschaufeln eines Axialverdichters
EP1321630A3 (de) * 2001-12-21 2005-01-12 Nuovo Pignone Holding S.P.A. Verbindungs- und Verriegelungssystem für die Laufschaufeln eines Axialverdichters
KR100779289B1 (ko) 2001-12-21 2007-11-23 누보 피그노네 홀딩 에스피에이 블레이드의 연결 및 록킹 시스템
WO2012110735A1 (fr) 2011-02-16 2012-08-23 Snecma Dispositif de blocage circonferentiel d'aubes pour turbomachine, a deploiement radial par mouvement de rotation d'un organe du dispositif
FR2973067A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
FR2973068A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
FR2973066A1 (fr) * 2011-03-21 2012-09-28 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
WO2012131227A1 (fr) * 2011-03-21 2012-10-04 Snecma Dispositif de blocage d'aubes dans une rainure d'un disque de turbomachine
CN103726885A (zh) * 2012-10-12 2014-04-16 航空技术空间股份有限公司 在转子周向槽中的鼓轮叶片锁件
CN103726885B (zh) * 2012-10-12 2017-05-24 赛峰航空助推器股份有限公司 在转子周向槽中的鼓轮叶片锁件
RU2633308C2 (ru) * 2012-10-12 2017-10-11 Сафран Аэро Бустерс Са Замок лопатки барабана в круговой канавке ротора
CN104481594A (zh) * 2014-10-28 2015-04-01 哈尔滨汽轮机厂有限责任公司 用于压气机周向环状燕尾型叶根的锁紧装置
EP3696380A1 (de) * 2019-02-04 2020-08-19 Rolls-Royce plc Adapter zur positionierung eines bearbeitungswerkzeugs zwischen zwei tragflügeln

Also Published As

Publication number Publication date
DE60116460D1 (de) 2006-03-30
DE60116460T2 (de) 2006-09-07
UA57883C2 (uk) 2003-07-15
US6464463B2 (en) 2002-10-15
FR2810366A1 (fr) 2001-12-21
US20010055527A1 (en) 2001-12-27
JP2002021504A (ja) 2002-01-23
CA2349692A1 (fr) 2001-12-15
FR2810366B1 (fr) 2002-10-11
CA2349692C (fr) 2009-01-13
WO2001096711A1 (fr) 2001-12-20
ES2251446T3 (es) 2006-05-01
JP4043733B2 (ja) 2008-02-06
EP1164251B1 (de) 2006-01-04
RU2222700C2 (ru) 2004-01-27

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