EP0043300B1 - Kühlvorrichtung für Schaufeln und Rotoren von Turbinen - Google Patents

Kühlvorrichtung für Schaufeln und Rotoren von Turbinen Download PDF

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Publication number
EP0043300B1
EP0043300B1 EP19810400931 EP81400931A EP0043300B1 EP 0043300 B1 EP0043300 B1 EP 0043300B1 EP 19810400931 EP19810400931 EP 19810400931 EP 81400931 A EP81400931 A EP 81400931A EP 0043300 B1 EP0043300 B1 EP 0043300B1
Authority
EP
European Patent Office
Prior art keywords
blade
root
disc
discs
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.)
Expired
Application number
EP19810400931
Other languages
English (en)
French (fr)
Other versions
EP0043300A2 (de
EP0043300A3 (en
Inventor
André Alexandre Morlon
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
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 filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0043300A2 publication Critical patent/EP0043300A2/de
Publication of EP0043300A3 publication Critical patent/EP0043300A3/fr
Application granted granted Critical
Publication of EP0043300B1 publication Critical patent/EP0043300B1/de
Expired 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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

Definitions

  • the present invention relates to an improvement to the ventilation systems of blades and discs of turbines.
  • the supply of cooling air to the base of the turbine blades and to the walls of the disc cavities is generally ensured, from a capacity comprised between the flange and the front face of the disc.
  • the flange is bolted to the lower part of the disc and also comes to bear, either on the front face of the disc teeth and on the blade root, or only on the front edge of the blade platforms.
  • each blade comprises a foot engaged in one of the axial cells formed at the periphery of the disc then a platform at the radial end of the extension of the foot and a profiled part extending radially starting from the platform, an enclosure being formed between the bottom of the cell and the underside of the foot and the axial locking of the blade towards the front being ensured by a flange fixed on the disc and against which abuts part of dawn.
  • This flange comes, according to FR-A-2 323 007, in abutment against the upstream face of the turbine disc and has openings for the passage of cooling air in said enclosure, while ensuring a seal both with a seal on the main gas stream side, with the blade, with the disc on the downstream side and with a labyrinth seal carried by another disc on the upstream side.
  • the seal is difficult to obtain both at several points between a single piece and at least two pieces at least upstream side and two pieces downstream side.
  • US-A-3 034 763 shows an axial locking of a blade by a biased tab abutting against the face of the disc.
  • the foot of the blade has at its lower front part a tab or spoiler which has an opening for the passage of the cooling air in said enclosure said tab ensuring the axial locking towards the rear, coming in abutment against the upstream face of the turbine disk.
  • the present invention therefore allows a good seal between the flange, the blades and the disc by means of a very simple device ensuring both the supply of cooling air to the root of the blades and their axial locking towards the rear, each part cooperating by a single support zone with only one other part.
  • a rotor disc 1 in which are arranged at its periphery axial cells 2 each receiving a foot 3 of a turbine blade 4 which comprises a platform 5 and a profiled part 6 extending radially to from each platform.
  • the foot of the blade 3 has at its lower front part a tab or spoiler 7 abutting against the upstream face 1a of the turbine disc, said tab having an opening 8 for the passage of the cooling air in an enclosure 9 formed between the bottom of the cell 2 and the underside 3a of the foot 3.
  • the underside of the foot 3 of the blade also has a recess at the front 12 to facilitate the passage of air.
  • the enclosure 9 opens towards the downstream face of the disc through an orifice 10 so that the air escapes backwards in a deflected manner according to arrow F where it joins the vein between the movable stage of the blades 4 and a rectifier stage 11.
  • the tab or spoiler 7 ensures the axial locking of the blade 4 towards the rear while the locking towards the front is obtained by means of a flange 13 which comes to bear on the platform 5 of the blades 4.
  • Locking forwards can also be obtained by means of the flange 13 which comes to bear simultaneously on the front face of the foot 3 of the blade and on the teeth 1b of the disc 1.
  • conduit 16 connecting the enclosure 9 with the cavity 17 formed inside the profiled part 6 of the blade 4, said cavity 17 being in communication with the outside by conduits 18 and 19 provided respectively in the leading edge and in the trailing edge. In this way the air cools the profiled part 6 of the blade itself which is provided with well known means of air circulation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (7)

1. Vorrichtung zur Ventilationskühlung von Schaufeln und Scheiben von Turbinen, wobei jede Schaufel einen in eine von am Umfang der Scheibe vorgesehenen axialen Hohlnuten (2) eingesetzten Fuß (3), eine in dem radialen Endbereich der Verlängerung des Fußes (3) vorgesehene Plattform (5) sowie einen profilierten Abschnitt (6) besitzt, der sich in radialer Richtung von der Plattform (5) aus erstreckt, wobei ferner zwischen dem Boden der Hohlnut (2) und der Unterseite (3a) des Fußes ein Kanal (9) vorgesehen ist und wobei die axiale Verriegelung der Schaufel nach vorn durch einen an der Scheibe befestigten Flansch (13) gewährleistet ist, gegen den sich ein Teil der Schaufel abstützt, dadurch gekennzeichnet, daß der Fuß (3) der Schaufel (4) in seinem unteren frontalen Bereich einen Überwurflappen (7) besitzt, der eine Öffnung (8) für den Durchtritt der Kühlluft in den genannten Kanal (9) aufweist und der durch seinen Anschlag gegen die Hochdruckseite (1a) der Turbinenscheibe die axiale Verriegelung der Schaufel nach hinten sichert.
2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß der zwischen dem Boden der Hohlnut (2) und der Unterseite (3a) des Fußes der Schaufel gebildete Kanal (9) an der Niederdruckseite der Scheibe (1) mündet, derart, daß die Kühlluft nach hinten entweicht und dabei in einen Luftstrom zwischen einer Laufstufe und einer Leitstufe (11) abgelenkt wird.
3. Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, daß der zwischen dem Boden der Hohlnut (2) und der Unterseite des Fußes (3) der Schaufel gebildete Kanal (9) zur Niederdruckseite der Scheibe hin verschlossen ist und über eine in dem Fuß der Schaufel angebrachte Leitung (16) in einem Hohlraum (17) des profilierten Abschnittes (6) der Schaufel (4) mündet und daß der genannte Hohlraum (17) des profilierten Abschnittes (6) der Schaufel Öffnungen (18,19) aufweist, die ihn mit dem Außenraum verbinden.
4. Vorrichtung nach Anspruch 3, dadurch gekennzeichnet, daß der zwischen dem Boden der Hohlnut (2) und der Unterseite des Fußes der Schaufel gebildete Kanal (9) zu der Niederdruckseite der Schaufel hin durch einen elastischen Ring (14) verschlossen ist, weicher unter einem Zahn (15) der Schaufel (4) gehalten ist.
5. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die Unterseite des Schaufelfußes (3) im vorderen Bereich eine Ausnehmung (12) aufweist, die den Durchtritt der Kühlluft begünstigt.
6. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die Verriegelung nach vorn durch den Flansch (13) gesichert ist, gegen den sich der vordere Rand der Plattform (5) der Schaufel (4) abstützt.
7. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die Verriegelung nach vorn durch den Flansch (13) gesichert ist, gegen den sich die Vorderseite (5) des Fußes (3) der Schaufel (4) und die Zähne (1b) der Scheibe (1) abstützen.
EP19810400931 1980-06-30 1981-06-12 Kühlvorrichtung für Schaufeln und Rotoren von Turbinen Expired EP0043300B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8014498A FR2485632B1 (fr) 1980-06-30 1980-06-30 Perfectionnement aux systemes de ventilation des aubes et disques de turbines
FR8014498 1980-06-30

Publications (3)

Publication Number Publication Date
EP0043300A2 EP0043300A2 (de) 1982-01-06
EP0043300A3 EP0043300A3 (en) 1982-01-13
EP0043300B1 true EP0043300B1 (de) 1984-05-16

Family

ID=9243661

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19810400931 Expired EP0043300B1 (de) 1980-06-30 1981-06-12 Kühlvorrichtung für Schaufeln und Rotoren von Turbinen

Country Status (3)

Country Link
EP (1) EP0043300B1 (de)
DE (1) DE3163609D1 (de)
FR (1) FR2485632B1 (de)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3835932A1 (de) * 1988-10-21 1990-04-26 Mtu Muenchen Gmbh Vorrichtung zur kuehlluftzufuehrung fuer gasturbinen-rotorschaufeln
FR2695161B1 (fr) * 1992-08-26 1994-11-04 Snecma Système de refroidissement d'un compresseur de turbomachine et de contrôle des jeux.
US5403156A (en) * 1993-10-26 1995-04-04 United Technologies Corporation Integral meter plate for turbine blade and method
US5511945A (en) * 1994-10-31 1996-04-30 Solar Turbines Incorporated Turbine motor and blade interface cooling system
US5759012A (en) * 1996-12-13 1998-06-02 Caterpillar Inc. Turbine disc ingress prevention method and apparatus
DE19950109A1 (de) * 1999-10-18 2001-04-19 Asea Brown Boveri Rotor für eine Gasturbine
DE102009007664A1 (de) * 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Abdichtvorrichtung an dem Schaufelschaft einer Rotorstufe einer axialen Strömungsmaschine
US8622702B1 (en) * 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
FR2969209B1 (fr) * 2010-12-21 2019-06-21 Safran Aircraft Engines Etage de turbine pour turbomachine d'aeronef, presentant une etancheite amelioree entre le flasque aval et les aubes de la turbine
US9777575B2 (en) 2014-01-20 2017-10-03 Honeywell International Inc. Turbine rotor assemblies with improved slot cavities
US20190323361A1 (en) * 2018-04-20 2019-10-24 United Technologies Corporation Blade with inlet orifice on forward face of root
FR3091722B1 (fr) 2019-01-11 2020-12-25 Safran Aircraft Engines Rotor, turbine équipée d’un tel rotor et turbomachine équipée d’une telle turbine
FR3095234B1 (fr) * 2019-04-19 2021-07-09 Safran Aircraft Engines Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi
CN112196628B (zh) * 2020-09-25 2022-06-07 中国航发沈阳发动机研究所 一种低压涡轮气冷叶片
FR3127255A1 (fr) * 2021-09-23 2023-03-24 Safran Aircraft Engines Ensemble rotatif pour turbomachine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB701263A (en) * 1950-08-03 1953-12-23 Rolls Royce Improvements in or relating to turbo-machines
US2758832A (en) * 1951-02-28 1956-08-14 Hickman Developments Inc Spring suspension for vehicles
GB753224A (en) * 1953-04-13 1956-07-18 Rolls Royce Improvements in or relating to blading for turbines or compressors
US3034763A (en) * 1959-08-20 1962-05-15 United Aircraft Corp Rotor construction
IT1063518B (it) * 1975-09-08 1985-02-11 Gen Electric Sistema di utilizzazione della perdita di aria di raffreddamento in un turbomotore a gas
GB2001708A (en) * 1977-07-22 1979-02-07 Rolls Royce Bladed rotor for a gas turbine engine

Also Published As

Publication number Publication date
EP0043300A2 (de) 1982-01-06
FR2485632A1 (fr) 1981-12-31
EP0043300A3 (en) 1982-01-13
FR2485632B1 (fr) 1985-07-05
DE3163609D1 (en) 1984-06-20

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