EP0043300A2 - Kühlvorrichtung für Schaufeln und Rotoren von Turbinen - Google Patents

Kühlvorrichtung für Schaufeln und Rotoren von Turbinen Download PDF

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Publication number
EP0043300A2
EP0043300A2 EP81400931A EP81400931A EP0043300A2 EP 0043300 A2 EP0043300 A2 EP 0043300A2 EP 81400931 A EP81400931 A EP 81400931A EP 81400931 A EP81400931 A EP 81400931A EP 0043300 A2 EP0043300 A2 EP 0043300A2
Authority
EP
European Patent Office
Prior art keywords
blade
disc
blades
foot
improvement
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
EP81400931A
Other languages
English (en)
French (fr)
Other versions
EP0043300A3 (en
EP0043300B1 (de
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
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 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.
  • the foot of the blade has at its lower front part a tab or spoiler ensuring axial locking towards the rear, abutting against the upstream face of the turbine disc, said tab having an opening for the passage of the cooling air in an enclosure formed between the bottom of the cell and the underside of the foot, the axial locking towards the front being ensured by a flange fixed on the disc and against which comes to bear part of the dawn.
  • 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.
  • a rotor disc 1 in which are formed 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 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 a chamber 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 the arrow F where it joins the vein between the stage. 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 bears simultaneously on the front face of the foot 3 of the blade and on the teeth 1b of the disc 1.
  • FIGS 3 and 4 there is shown an alternative embodiment in which the enclosure 9 between the bottom of the cell 2 and the underside of the foot 3 of the blade is closed towards the downstream face of the disc by an elastic ring 14 engaged under a downstream spoiler 15 of the disc in which the ring 14 is held by elasticity on the one hand, but above all by centrifugal force.
  • 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)
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
FR8014498 1980-06-30
FR8014498A FR2485632B1 (fr) 1980-06-30 1980-06-30 Perfectionnement aux systemes de ventilation des aubes et disques de turbines

Publications (3)

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

Cited By (13)

* 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
EP0649975A1 (de) * 1993-10-26 1995-04-26 United Technologies Corporation Kühlluftmengenregelung bei Turbinenschaufeln
EP0709547A1 (de) * 1994-10-31 1996-05-01 Solar Turbines Incorporated Kühlung des Randes einer Gasturbinenrohrscheibe
US5759012A (en) * 1996-12-13 1998-06-02 Caterpillar Inc. Turbine disc ingress prevention method and apparatus
EP1094199A1 (de) * 1999-10-18 2001-04-25 ABB (Schweiz) AG Roton für eine Gasturbine
WO2010088881A1 (de) * 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Abdichtvorrichtung an dem schaufelschaft einer rotorstufe einer axialen strömungsmaschine
FR2969209A1 (fr) * 2010-12-21 2012-06-22 Snecma Etage de turbine pour turbomachine d'aeronef, presentant une etancheite amelioree entre le flasque aval et les aubes de la turbine
US8622702B1 (en) * 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
EP2896786A1 (de) * 2014-01-20 2015-07-22 Honeywell International Inc. Turbinenrotoranordnungen mit verbesserten Spalthohlräumen
EP3556996A1 (de) * 2018-04-20 2019-10-23 United Technologies Corporation Schaufel mit einlassöffnung auf der vorderen stirnseite des fusses
EP3680451A1 (de) * 2019-01-11 2020-07-15 Safran Aircraft Engines Rotor, mit einem solchen rotor ausgerüstete turbine und turbinentriebwerk, das mit einer solchen turbine ausgestattet ist
FR3095234A1 (fr) * 2019-04-19 2020-10-23 Safran Aircraft Engines Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi
CN112196628A (zh) * 2020-09-25 2021-01-08 中国航发沈阳发动机研究所 一种低压涡轮气冷叶片

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2695161B1 (fr) * 1992-08-26 1994-11-04 Snecma Système de refroidissement d'un compresseur de turbomachine et de contrôle des jeux.
FR3127255A1 (fr) * 2021-09-23 2023-03-24 Safran Aircraft Engines Ensemble rotatif pour turbomachine

Citations (5)

* 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
CH322022A (de) * 1953-04-13 1957-05-31 Rolls Royce Hohlschaufel für Turbomaschinen
US3034763A (en) * 1959-08-20 1962-05-15 United Aircraft Corp Rotor construction
FR2323007A1 (fr) * 1975-09-08 1977-04-01 Gen Electric Dispositif de refroidissement d'aube de turbine
GB2001708A (en) * 1977-07-22 1979-02-07 Rolls Royce Bladed rotor for a gas turbine engine

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2758832A (en) * 1951-02-28 1956-08-14 Hickman Developments Inc Spring suspension for vehicles

Patent Citations (5)

* 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
CH322022A (de) * 1953-04-13 1957-05-31 Rolls Royce Hohlschaufel für Turbomaschinen
US3034763A (en) * 1959-08-20 1962-05-15 United Aircraft Corp Rotor construction
FR2323007A1 (fr) * 1975-09-08 1977-04-01 Gen Electric Dispositif de refroidissement d'aube de turbine
GB2001708A (en) * 1977-07-22 1979-02-07 Rolls Royce Bladed rotor for a gas turbine engine

Cited By (21)

* 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
EP0649975A1 (de) * 1993-10-26 1995-04-26 United Technologies Corporation Kühlluftmengenregelung bei Turbinenschaufeln
EP0709547A1 (de) * 1994-10-31 1996-05-01 Solar Turbines Incorporated Kühlung des Randes einer Gasturbinenrohrscheibe
US5759012A (en) * 1996-12-13 1998-06-02 Caterpillar Inc. Turbine disc ingress prevention method and apparatus
EP1094199A1 (de) * 1999-10-18 2001-04-25 ABB (Schweiz) AG Roton für eine Gasturbine
US6416282B1 (en) 1999-10-18 2002-07-09 Alstom Rotor for a gas turbine
WO2010088881A1 (de) * 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Abdichtvorrichtung an dem schaufelschaft einer rotorstufe einer axialen strömungsmaschine
US8870542B2 (en) 2009-02-05 2014-10-28 Mtu Aero Engines Gmbh Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine
US8622702B1 (en) * 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
FR2969209A1 (fr) * 2010-12-21 2012-06-22 Snecma Etage de turbine pour turbomachine d'aeronef, presentant une etancheite amelioree entre le flasque aval et les aubes de la turbine
EP2896786A1 (de) * 2014-01-20 2015-07-22 Honeywell International Inc. Turbinenrotoranordnungen mit verbesserten Spalthohlräumen
US9777575B2 (en) 2014-01-20 2017-10-03 Honeywell International Inc. Turbine rotor assemblies with improved slot cavities
EP3556996A1 (de) * 2018-04-20 2019-10-23 United Technologies Corporation Schaufel mit einlassöffnung auf der vorderen stirnseite des fusses
EP3680451A1 (de) * 2019-01-11 2020-07-15 Safran Aircraft Engines Rotor, mit einem solchen rotor ausgerüstete turbine und turbinentriebwerk, das mit einer solchen turbine ausgestattet ist
FR3091722A1 (fr) * 2019-01-11 2020-07-17 Safran Aircraft Engines Rotor, turbine équipée d’un tel rotor et turbomachine équipée d’une telle turbine
CN111434892A (zh) * 2019-01-11 2020-07-21 赛峰飞机发动机公司 转子，配备有该转子的涡轮和配备有该涡轮的涡轮机
US11261745B2 (en) 2019-01-11 2022-03-01 Safran Aircraft Engines Rotor, turbine equipped with such a rotor and turbomachine equipped with such a turbine
CN111434892B (zh) * 2019-01-11 2024-05-14 赛峰飞机发动机公司 转子，配备有该转子的涡轮和配备有该涡轮的涡轮机
FR3095234A1 (fr) * 2019-04-19 2020-10-23 Safran Aircraft Engines Ensemble de turbomachine comprenant un dispositif de limitation de temperature pour fond d’alveole non refroidi
CN112196628A (zh) * 2020-09-25 2021-01-08 中国航发沈阳发动机研究所 一种低压涡轮气冷叶片
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

Also Published As

Publication number Publication date
FR2485632B1 (fr) 1985-07-05
EP0043300A3 (en) 1982-01-13
FR2485632A1 (fr) 1981-12-31
DE3163609D1 (en) 1984-06-20
EP0043300B1 (de) 1984-05-16

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