EP1489266B1 - 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
EP1489266B1
EP1489266B1 EP04291450A EP04291450A EP1489266B1 EP 1489266 B1 EP1489266 B1 EP 1489266B1 EP 04291450 A EP04291450 A EP 04291450A EP 04291450 A EP04291450 A EP 04291450A EP 1489266 B1 EP1489266 B1 EP 1489266B1
Authority
EP
European Patent Office
Prior art keywords
disk
upstream
downstream
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.)
Expired - Lifetime
Application number
EP04291450A
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English (en)
French (fr)
Other versions
EP1489266A1 (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 SAS
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1489266A1 publication Critical patent/EP1489266A1/de
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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 blade which extends in a conical vein and which is retained in a peripheral groove of said disk by hammer-type fasteners, each of said blades further comprising a platform whose radially outer face delimits the vein of the gas flow and whose radially inner face has an upstream rib and a downstream rib disposed 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 from and other of said groove to ensure sealing in these areas.
  • the radius of the vein of the primary flow decreases from upstream to downstream in the low pressure compressor.
  • the conicity of this vein is very high in the last stages of this compressor.
  • the blades of these stages extend obliquely in the vein relative to the plane perpendicular to the axis of rotation of the compressor, that is to say, obliquely with respect to the radial direction of the centrifugal forces.
  • the invention relates more specifically to the bladed discs of this type, in which the blades are retained by a hammer-type fastener 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 blade roots are supported during the operation of the turbomachine, these bearing surfaces supporting reaction forces whose resultant is preferably in the plane of the centrifugal forces to which the blades are subjected .
  • EP 0 695 856 proposed an asymmetrical hammer clip, that is to say that the angle of the range of the upstream lip, which has the largest diameter, with respect to a plane perpendicular to the axis of rotation, is greater than 1 angel formed between the scope of the downstream lip and said plane.
  • FIG. 4B of this document shows the blade-disk connection in the case where the blade, subjected to a large axial stress, as a result of an impact of a debris ingested by the turbomachine, tends to pivot around a center of rotation C located at the upstream end of the range of the downstream lip. Because of the conformation of the throat and the blade root, dawn can be released in case of significant shock.
  • US 5,271,718 discloses symmetrical hammer-blade type blades having platforms having on their radially inner face circumferentially and axially extending ribs which are intended to avoid vibratory resonances, two of these circumferential ribs cooperating with rings formed at the periphery of the disc to seal in these areas.
  • the axial thickness of these ribs is substantially equal to the thickness of the rings.
  • the downstream rib supports a large part of the forces generated and can skip axially on the downstream ring, which can cause the release of the blade.
  • the ends of these ribs can slip 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 provide a plane and homogeneous contact surface between the rib and the ring of the disc which optionally has 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 large enough to limit the possibility of overlapping platforms.
  • FIG. 1 shows a blade 1 whose dovetail shaped foot 2 comprises an upstream flank 3a and a downstream flank 3b whose surfaces bear on bearing surfaces 4a, 4b of the internal faces of an upstream lip 5 and of a downstream lip 6 which delimit a groove 7 formed at the periphery of a disc 12 and whose bottom 8 is connected to the bearing surfaces 4a and 4b by rounded surfaces 9a and 9b respectively.
  • the blade 1 extends in a strongly conical vein, that is to say that the upstream lip 5 has a greater diameter than the downstream lip 6, and the bearings 4a and 4b are, with the plane perpendicular to the axis of rotation of the disc 2, different angles.
  • the disc 12 has upstream a first radial extension 20, called upstream ring in the present memory, of small axial thickness, and downstream a second radial extension 21, called downstream ring, which has a groove 22 for receiving a rod of sealing not shown in the drawings for the sake of clarity.
  • the upstream and downstream rings 21 have cylindrical peripheral surfaces 20a and 21a, of revolution about the axis of rotation of the disc 12.
  • the blade 2 has between the foot 2 and the aerodynamic portion a platform 30 whose radially outer face 30a delimits the conical vein, and whose radially inner face 30b has an 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 in particular cylindrical surface portions, respectively 32a and 32b, of revolution about the axis of rotation of the disc 1 which cover the peripheral surfaces 20a and 21a of the upstream and downstream rings 21 and 22, and whose width in the axial direction 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 the rings 20 and 21 in all ranges of movement of the blade 1 in operation.
  • the height of the ribs 32 and 33 is calculated such 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 blades 1a and 1b can not overlap as shown in Figure 2.
  • FIG. 2 shows blades 1a and 1b which furthermore have other stiffening ribs, arranged between the upstream rib 32 and the downstream rib 33.
  • This blade could also include ribs directed axially without departing from the scope of the invention.

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)

Claims (3)

  1. Schaufelscheibe einer Turbomaschine mit Schaufeln (1), die sich in einem kegelförmigen Kanal erstrecken und die in einer Umfangsnut (7) der Scheibe (12) durch Befestigungselemente vom Typ Hammer festgehalten sind, wobei eine jede der Schaufeln ferner eine Plattform (30) aufweist, deren radial äußere Fläche (30a) den Kanal des Gasstroms begrenzt und deren radial innere Fläche (30b) eine stromaufwärtige Rippe (32) sowie eine stromabwärtige Rippe (33) aufweist, die in zur Rotationsachse der Scheibe senkrechten Ebenen angeordnet sind und die radial an einen stromaufwärtigen Ring (20) bzw. an einen stromabwärtigen Ring (21), die am Umfang der Scheibe (12) auf beiden Seiten der Nut (7) ausgebildet sind, angrenzen, um in diesen Bereichen Dichtigkeit zu gewährleisten, dadurch gekennzeichnet, daß die Dicke der stromabwärtigen Rippe (33) in axialer Richtung größer ist als die Dicke des stromabwärtigen Rings (21).
  2. Scheibe nach Anspruch 1, dadurch gekennzeichnet, daß die Dicke der stromaufwärtigen Rippe (32) in axialer Richtung größer ist als die Dicke des stromaufwärtigen Rings (20).
  3. Scheibe nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß die Höhe der Rippen groß genug ist, um die Möglichkeit einer Überlappung der Plattformen zu begrenzen.
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 EP1489266A1 (de) 2004-12-22
EP1489266B1 true 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)

Families Citing this family (9)

* 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
EP2282010A1 (de) 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Laufschaufel für eine axial durchströmbare Turbomaschine
US9140136B2 (en) 2012-05-31 2015-09-22 United Technologies Corporation Stress-relieved wire seal assembly for gas turbine engines
US9097131B2 (en) 2012-05-31 2015-08-04 United Technologies Corporation Airfoil and disk interface system 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

Family Cites Families (11)

* 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
GB612097A (en) * 1946-10-09 1948-11-08 English Electric Co Ltd Improvements in and relating to the cooling of gas turbine rotors
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
US4460315A (en) * 1981-06-29 1984-07-17 General Electric Company Turbomachine rotor assembly
FR2680828A1 (fr) * 1991-08-28 1993-03-05 Sev Motorola Rotor de turbomachine a positionnement angulaire ameliore des aubes.
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

Also Published As

Publication number Publication date
US20040253113A1 (en) 2004-12-16
EP1489266A1 (de) 2004-12-22
RU2333366C2 (ru) 2008-09-10
DE602004008153D1 (de) 2007-09-27
RU2004118078A (ru) 2006-01-10
JP2005009492A (ja) 2005-01-13
FR2856105B1 (fr) 2007-05-25
US7080974B2 (en) 2006-07-25
DE602004008153T2 (de) 2008-05-15
JP4227077B2 (ja) 2009-02-18
CA2470073A1 (fr) 2004-12-16
ES2291833T3 (es) 2008-03-01
UA81901C2 (uk) 2008-02-25
CA2470073C (fr) 2011-08-16
FR2856105A1 (fr) 2004-12-17

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