EP1489266A1 - Feststellung der Schaufel mit asymmetrischem Hammerkopffuss mittels Versteifung der eingebauten Plattform - Google Patents

Feststellung der Schaufel mit asymmetrischem Hammerkopffuss mittels Versteifung der eingebauten Plattform Download PDF

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Publication number
EP1489266A1
EP1489266A1 EP04291450A EP04291450A EP1489266A1 EP 1489266 A1 EP1489266 A1 EP 1489266A1 EP 04291450 A EP04291450 A EP 04291450A EP 04291450 A EP04291450 A EP 04291450A EP 1489266 A1 EP1489266 A1 EP 1489266A1
Authority
EP
European Patent Office
Prior art keywords
downstream
upstream
disk
blade
rib
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
EP04291450A
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English (en)
French (fr)
Other versions
EP1489266B1 (de
Inventor
Claude Lejars
Patrick Reghezza
Jérôme Mace
Christophe Follonier
Bruce Pontoizeau
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
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Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1489266A1 publication Critical patent/EP1489266A1/de
Application granted granted Critical
Publication of EP1489266B1 publication Critical patent/EP1489266B1/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
    • F01D5/3023—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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the invention relates to a turbomachine blisk which extends into a conical vein and is retained in a throat device of said disk by hammer-type fasteners, each said vanes further comprising a platform whose face radially outer delimits the vein of the gas flow and whose face radially inner has an upstream rib and a downstream rib arranged in planes perpendicular to the axis of rotation of said disk and respectively adjoining an upstream ring and a downstream ring formed at the periphery of said disk on either side of said groove to ensure sealing in these areas.
  • the radius of the primary flow vein decreases from upstream to downstream in the compressor low pressure.
  • the conicity of this vein is very high at the level of last stages of this compressor.
  • the blades of these floors extend obliquely in the vein relative to the plane perpendicular to the axis of compressor rotation, that is to say, obliquely to the radial direction of centrifugal forces.
  • the invention relates more specifically to the blisk discs of this type, in which the blades are retained by a fastener type hammer in a peripheral groove of the disc, this groove being delimited by an upstream lip and a downstream lip, whose surfaces connected to the bottom of the groove form spans on which the flanks of the dawn feet are supported during the operation of the turbomachine, these spans supporting reaction forces whose resultant is preferably in the plane of the centrifugal forces to which the blades are subject.
  • EP 0 695 856 proposed a fastener Asymmetrical hammer, that is to say that the angle of the reach of the lip upstream, which has the largest diameter, with respect to a perpendicular plane to the axis of rotation, is greater than the angel formed between the scope of the downstream lip and said plane.
  • Figure 4B of this document shows the link dawn-disk in the case where dawn, subjected to axial stress significant, as a result of a shock of a debris ingested by the turbomachine, has tendency to rotate around a center of rotation C located at the end upstream of the range of the downstream lip. Due to the conformation of the throat and the dawn foot, the dawn can be released in case of significant shock.
  • No. 5,271,718 describes blades of the symmetrical hammer tie type which have platforms having on their radially inner face ribs which extend in the circumferential and axial direction and which are intended to avoid vibratory resonances, two these circumferential ribs cooperating with rings formed at the periphery of the disk to ensure sealing in these areas.
  • the axial thickness of these ribs is substantially equal to the thickness of the rings.
  • This document shows that the axial ribs formed on the radially inner face of the platforms have a height less than that of the ribs cooperating with the rings.
  • the downstream rib supports a large part of the generated forces and can skip axially on the downstream ring, which can cause the release of the blade.
  • the ends of these ribs can rip on the rings which, failing to cause the release of the blade, may cause an overlap of the adjacent edges of two neighboring blades.
  • the object of the invention is to provide a modified blade that overcomes these disadvantages.
  • This arrangement makes it possible to offer a flat contact surface and homogeneous between the rib and the disc ring that presents possibly a groove for receiving a sealing ring.
  • the thickness of the upstream rib in the axial direction is greater than the thickness of the upstream ring.
  • the height of said ribs is sufficiently large to limit the possibility of overlapping platforms.
  • Figure 1 shows a blade 1 whose foot 2 in the form of dovetail comprises an upstream flank 3a and a downstream flank 3b whose surfaces are supported on bearings 4a, 4b of the internal faces of a upstream lip 5 and a downstream lip 6 which delimit a groove 7 formed in the periphery of a disk 12 and whose bottom 8 is connected to the bearings 4a and 4b by rounded surfaces respectively 9a and 9b.
  • dawn 1 extends into a vein strongly conical, that is to say that the upstream lip 5 has a larger diameter than the downstream lip 6, and the bearings 4a and 4b are, with the plane perpendicular to the axis of rotation of the disk 2, different angles.
  • the disc 12 presents upstream a first radial extension 20, referred to as upstream ring in this specification, thin axial, and downstream a second radial extension 21, called downstream ring, which has a groove 22 intended to receive a sealing ring shown in the drawings for the sake of clarity.
  • the upstream and downstream rings 21 have surfaces cylindrical peripherals 20a and 21a, of revolution about the axis of rotation of the disc 12.
  • Dawn 2 presents between the foot 2 and the aerodynamic part a platform 30 whose radially outer face 30a delimits the conical vein, and whose radially inner face 30b has a upstream rib 32 and a downstream groove 33 which extend circumferentially in the immediate vicinity of the peripheral surfaces 20a and 21a of the upstream and downstream rings 20 and 21.
  • These ribs 32 and 33 have portions of cylindrical surfaces, respectively 32a and 32b, of revolution around the axis of rotation of the disc 1 which covers the peripheral surfaces 20a and 21a upstream 21 and downstream 22 rings, and whose width in the direction axial is greater than the width of the peripheral surfaces 20a and 21a.
  • the width of the surfaces 32a and 33a is calculated so as to always provide sufficient seating on rings 20 and 21 in all the ranges of movement of the blade 1 in operation.
  • the height of the ribs 32 and 33 is calculated in such a way that regardless of the displacement of the adjacent blades, as a result of a tangential stress, the adjacent edges of the platforms 30 of two consecutive vanes 1a and 1b can not overlap, as this is shown in Figure 2.
  • This figure 2 shows blades 1a and 1b which present in in addition to other stiffening ribs disposed between the upstream rib 32 and the downstream rib 33.

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)
EP04291450A 2003-06-16 2004-06-10 Feststellung der Schaufel mit asymmetrischem Hammerkopffuss mittels Versteifung der eingebauten Plattform Expired - Lifetime EP1489266B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0307214 2003-06-16
FR0307214A FR2856105B1 (fr) 2003-06-16 2003-06-16 Amelioration de la capacite de retention d'une aube a attache marteau dissymetrique a l'aide des raidisseurs de plates-formes

Publications (2)

Publication Number Publication Date
EP1489266A1 true EP1489266A1 (de) 2004-12-22
EP1489266B1 EP1489266B1 (de) 2007-08-15

Family

ID=33396778

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04291450A Expired - Lifetime EP1489266B1 (de) 2003-06-16 2004-06-10 Feststellung der Schaufel mit asymmetrischem Hammerkopffuss mittels Versteifung der eingebauten Plattform

Country Status (9)

Country Link
US (1) US7080974B2 (de)
EP (1) EP1489266B1 (de)
JP (1) JP4227077B2 (de)
CA (1) CA2470073C (de)
DE (1) DE602004008153T2 (de)
ES (1) ES2291833T3 (de)
FR (1) FR2856105B1 (de)
RU (1) RU2333366C2 (de)
UA (1) UA81901C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2282010A1 (de) * 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Laufschaufel für eine axial durchströmbare Turbomaschine

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004051116A1 (de) * 2004-10-20 2006-04-27 Mtu Aero Engines Gmbh Rotor einer Turbomaschine, insbesondere Gasturbinenrotor
FR2897099B1 (fr) * 2006-02-08 2012-08-17 Snecma Roue de rotor de turbomachine
US8608447B2 (en) * 2009-02-19 2013-12-17 Rolls-Royce Corporation Disk for turbine engine
US9097131B2 (en) 2012-05-31 2015-08-04 United Technologies Corporation Airfoil and disk interface system for gas turbine engines
US9140136B2 (en) 2012-05-31 2015-09-22 United Technologies Corporation Stress-relieved wire seal assembly for gas turbine engines
US9267386B2 (en) 2012-06-29 2016-02-23 United Technologies Corporation Fairing assembly
EP2885506B8 (de) 2012-08-17 2021-03-31 Raytheon Technologies Corporation Profilierte durchflusswegfläche
GB201800732D0 (en) 2018-01-17 2018-02-28 Rolls Royce Plc Blade for a gas turbine engine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2398140A (en) * 1943-12-08 1946-04-09 Armstrong Siddeley Motors Ltd Bladed rotor
US2494658A (en) * 1946-05-10 1950-01-17 United Aircraft Corp Blade mounting
US2656147A (en) * 1946-10-09 1953-10-20 English Electric Co Ltd Cooling of gas turbine rotors
US4460315A (en) * 1981-06-29 1984-07-17 General Electric Company Turbomachine rotor assembly
EP0530097A1 (de) * 1991-08-28 1993-03-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomaschinenrotor mit Winkelpositionierung der Schaufeln

Family Cites Families (6)

* 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
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
US5622475A (en) * 1994-08-30 1997-04-22 General Electric Company Double rabbet rotor blade retention assembly
FR2758364B1 (fr) * 1997-01-16 1999-02-12 Snecma Disque aubage a aubes tripodes
GB2332024B (en) 1997-12-03 2000-12-13 Rolls Royce Plc Rotary assembly
FR2812906B1 (fr) 2000-08-10 2002-09-20 Snecma Moteurs Bague de retention axiale d'un flasque sur un disque

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2398140A (en) * 1943-12-08 1946-04-09 Armstrong Siddeley Motors Ltd Bladed rotor
US2494658A (en) * 1946-05-10 1950-01-17 United Aircraft Corp Blade mounting
US2656147A (en) * 1946-10-09 1953-10-20 English Electric Co Ltd Cooling of gas turbine rotors
US4460315A (en) * 1981-06-29 1984-07-17 General Electric Company Turbomachine rotor assembly
EP0530097A1 (de) * 1991-08-28 1993-03-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomaschinenrotor mit Winkelpositionierung der Schaufeln

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2282010A1 (de) * 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Laufschaufel für eine axial durchströmbare Turbomaschine
US8951016B2 (en) 2009-06-23 2015-02-10 Siemens Aktiengesellschaft Rotor blade for an axial flow turbomachine and mounting for such a rotor blade

Also Published As

Publication number Publication date
CA2470073C (fr) 2011-08-16
FR2856105B1 (fr) 2007-05-25
JP2005009492A (ja) 2005-01-13
RU2004118078A (ru) 2006-01-10
EP1489266B1 (de) 2007-08-15
ES2291833T3 (es) 2008-03-01
RU2333366C2 (ru) 2008-09-10
JP4227077B2 (ja) 2009-02-18
US7080974B2 (en) 2006-07-25
DE602004008153T2 (de) 2008-05-15
DE602004008153D1 (de) 2007-09-27
US20040253113A1 (en) 2004-12-16
CA2470073A1 (fr) 2004-12-16
UA81901C2 (uk) 2008-02-25
FR2856105A1 (fr) 2004-12-17

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