EP0077236A1 - Befestigung von Schaufelsektoren auf einer Rotorscheibe einer Turbomaschine - Google Patents

Befestigung von Schaufelsektoren auf einer Rotorscheibe einer Turbomaschine Download PDF

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Publication number
EP0077236A1
EP0077236A1 EP82401746A EP82401746A EP0077236A1 EP 0077236 A1 EP0077236 A1 EP 0077236A1 EP 82401746 A EP82401746 A EP 82401746A EP 82401746 A EP82401746 A EP 82401746A EP 0077236 A1 EP0077236 A1 EP 0077236A1
Authority
EP
European Patent Office
Prior art keywords
disc
sector
foot
flange
blades
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Withdrawn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
EP82401746A
Other languages
English (en)
French (fr)
Inventor
Alain M.J. Lardellier
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0077236A1 publication Critical patent/EP0077236A1/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Withdrawn legal-status Critical Current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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/3046—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses the rotor having ribs around the circumference

Definitions

  • the present invention relates to a device for installing a sector of blades on a rotor disc of a turbomachine.
  • the casting of the turbomachine blades by sectors makes it possible to lower the cost price, to produce a more watertight stream by eliminating numerous vanishing points, and to increase the life of the blades because the embedding of several blades both on a single stand provides better resistance to vibration and better impact resistance.
  • the present invention relates to a blade sector fixing device which makes it possible to remedy these drawbacks.
  • the blade sector comprises a single foot which has at least one circular rib cooperating with at least one circular groove provided on the upstream face of the rim of the disc, said sector being held in abutment against the disc by a flange fixed on the upstream face of the disc.
  • FIGS. 1 and 3 there is shown a sector 1 comprising in particular six blades 2 which are connected at their ends by a single foot 3 and by a peripheral heel 4.
  • the foot 3 of the blade sector has two circular ribs 5, 6 which are offset radially and longitudinally and which are respectively engaged in circular grooves 7, 8 provided on the upstream face of the rim of a disc 9 ( Figures 2 and 3) of the turbomachine rotor.
  • All of the sectors 1 are locked axially by a flange 10 fixed by means of bolts 11 on the disc 9, said flange being supported by a lip 12 (FIGS. 3 and 4) against the upstream face of the foot 3 of the sectors 1.
  • An annular seal 13 (FIGS. 3 and 8) with a U section is placed in a housing formed between the flange 10 and the upstream face of the sector foot 3.
  • a tooth 14 constituting a circumferential stop for the sectors which is engaged in a housing 15 (FIG. 4) formed on the downstream face of the flange 10.
  • a housing 15 formed on the downstream face of the flange 10.
  • grooves 16, 17 are provided in which metal plates 18, 19 are engaged which provide radial sealing between the adjacent sectors.
  • the orientation of the lower plates 18, affected by a slight curvature, is such that it contributes to giving a better incidence to the air joining the vein after having cooled the foot 3 of the blades or the rim of the disc 9.
  • FIG. 6 a heel of a portion of the blade sector has been represented, as an alternative to that illustrated in FIG.
  • the configuration in Z of the circumferential ends of the heel allows the assembly by interlocking of several sectors in succession.
  • the sector which is only represented with a single blade, could of course, with a heel of the same configuration, comprise for example six blades as in FIG. 1.
  • the sector may include only a foot 3 having ribs 5 and 6, the upper part of the blades having no heel.
  • the heel 4 can have a cross-section in a straight shape (FIG. 1) or a Z-shape as in FIG. 6.
  • conduits 20, 21 which open, on one side in the annular capacity limited by the flange 10 and the disc 9 and, on the other side, between the foot and the disk.
  • FIG. 5 there is shown an alternative embodiment in which the foot 3 has only one rib 5 which is engaged in a circular groove 7 of the rim of the disc 9, and the underside of the foot 3 comprises, at l 'downstream, a bearing surface 22 which comes to bear in operation on a corresponding bearing surface 23 of the disc 9.
  • the flange 10 is fixed by means of bolts to the disc 9 by means of spacers leaving a clearance for ventilation.
  • the spacer can be replaced by an extra thickness of the flange 10 comprising a milling for ventilation.

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)
EP82401746A 1981-10-09 1982-09-28 Befestigung von Schaufelsektoren auf einer Rotorscheibe einer Turbomaschine Withdrawn EP0077236A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8119001 1981-10-09
FR8119001A FR2514409B1 (fr) 1981-10-09 1981-10-09 Dispositif d'implantation d'aubes en secteurs sur un disque de rotor de turbomachine

Publications (1)

Publication Number Publication Date
EP0077236A1 true EP0077236A1 (de) 1983-04-20

Family

ID=9262870

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82401746A Withdrawn EP0077236A1 (de) 1981-10-09 1982-09-28 Befestigung von Schaufelsektoren auf einer Rotorscheibe einer Turbomaschine

Country Status (3)

Country Link
EP (1) EP0077236A1 (de)
JP (1) JPS5879605A (de)
FR (1) FR2514409B1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2566835A1 (fr) * 1984-06-27 1986-01-03 Snecma Dispositif de fixation de secteurs d'aubes sur un rotor de turbomachine
FR2641573A1 (fr) * 1989-01-11 1990-07-13 Snecma Rotor de turbomachine muni d'un dispositif de fixation des aubes
US5067877A (en) * 1990-09-11 1991-11-26 United Technologies Corporation Fan blade axial retention device
DE102009030397A1 (de) * 2009-06-25 2010-12-30 Mtu Aero Engines Gmbh Befestigungsvorrichtung einer Turbinen- oder Verdichterschaufel
US7874802B2 (en) * 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US7878762B2 (en) * 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
DE102010025238A1 (de) * 2010-06-26 2011-12-29 Mtu Aero Engines Gmbh Rotor und Schaufelsegment für eine Strömungsmaschine
US8152469B2 (en) * 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2552159B1 (fr) * 1983-09-21 1987-07-10 Snecma Dispositif de liaison et d'etancheite de secteurs d'aubes de stator de turbine
FR2585069B1 (fr) * 1985-07-16 1989-06-09 Snecma Dispositif de limitation du debattement angulaire d'aubes montees sur un disque de rotor de turbomachine
US5030063A (en) * 1990-02-08 1991-07-09 General Motors Corporation Turbomachine rotor
JP4807113B2 (ja) * 2006-03-14 2011-11-02 株式会社Ｉｈｉ ファンのダブテール構造

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR336322A (fr) * 1903-07-20 1904-03-05 Postel Vinay Ets Perfectionnements apportés à la construction des aubes de turbines
FR345730A (fr) * 1903-09-15 1904-12-09 Wilkinson Steam Turbine C Perfectionnements apportés aux roues à augets des turbines
FR519206A (fr) * 1919-06-27 1921-06-07 Thomson Houston Comp Francaise Perfectionnements à la fabrication et aux modes de fixation des ailettes det urbines
FR634020A (fr) * 1926-05-15 1928-02-08 Thomson Houston Comp Francaise Perfectionnements aux turbines à fluide élastique
US1876067A (en) * 1926-09-20 1932-09-06 Bendix Aviat Corp Blade structure for turbines
FR1053118A (fr) * 1952-03-27 1954-02-01 Soc D Const Et D Equipements M Ailetage de turbine
US3393894A (en) * 1965-12-28 1968-07-23 Rolls Royce Blade assembly
GB2001398A (en) * 1977-07-22 1979-01-31 Rolls Royce Bladed Rotor for Gas Turbine Engine
GB2001708A (en) * 1977-07-22 1979-02-07 Rolls Royce Bladed rotor for a gas turbine engine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR336322A (fr) * 1903-07-20 1904-03-05 Postel Vinay Ets Perfectionnements apportés à la construction des aubes de turbines
FR345730A (fr) * 1903-09-15 1904-12-09 Wilkinson Steam Turbine C Perfectionnements apportés aux roues à augets des turbines
FR519206A (fr) * 1919-06-27 1921-06-07 Thomson Houston Comp Francaise Perfectionnements à la fabrication et aux modes de fixation des ailettes det urbines
FR634020A (fr) * 1926-05-15 1928-02-08 Thomson Houston Comp Francaise Perfectionnements aux turbines à fluide élastique
US1876067A (en) * 1926-09-20 1932-09-06 Bendix Aviat Corp Blade structure for turbines
FR1053118A (fr) * 1952-03-27 1954-02-01 Soc D Const Et D Equipements M Ailetage de turbine
US3393894A (en) * 1965-12-28 1968-07-23 Rolls Royce Blade assembly
GB2001398A (en) * 1977-07-22 1979-01-31 Rolls Royce Bladed Rotor for Gas Turbine Engine
GB2001708A (en) * 1977-07-22 1979-02-07 Rolls Royce Bladed rotor for a gas turbine engine

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2566835A1 (fr) * 1984-06-27 1986-01-03 Snecma Dispositif de fixation de secteurs d'aubes sur un rotor de turbomachine
FR2641573A1 (fr) * 1989-01-11 1990-07-13 Snecma Rotor de turbomachine muni d'un dispositif de fixation des aubes
EP0378474A1 (de) * 1989-01-11 1990-07-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomaschinenrotor mit Einrichtung zur Schaufelbefestigung
US5018941A (en) * 1989-01-11 1991-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation"S.N.E.C.M.A. Blade fixing arrangement for a turbomachine rotor
US5067877A (en) * 1990-09-11 1991-11-26 United Technologies Corporation Fan blade axial retention device
US7874802B2 (en) * 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US7878762B2 (en) * 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
US8152469B2 (en) * 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
DE102009030397A1 (de) * 2009-06-25 2010-12-30 Mtu Aero Engines Gmbh Befestigungsvorrichtung einer Turbinen- oder Verdichterschaufel
WO2010149146A3 (de) * 2009-06-25 2011-07-21 Mtu Aero Engines Gmbh Befestigungsvorrichtung einer turbinen- oder verdichterschaufel
DE102010025238A1 (de) * 2010-06-26 2011-12-29 Mtu Aero Engines Gmbh Rotor und Schaufelsegment für eine Strömungsmaschine

Also Published As

Publication number Publication date
FR2514409A1 (fr) 1983-04-15
FR2514409B1 (fr) 1986-03-21
JPS5879605A (ja) 1983-05-13

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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: 19821008

AK Designated contracting states

Designated state(s): DE FR GB

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

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18W Application withdrawn

Withdrawal date: 19840614

RIN1 Information on inventor provided before grant (corrected)

Inventor name: LARDELLIER, ALAIN M.J.