EP1469165B1 - Verminderung des Blattspitzenspiels bei einer Gasturbine - Google Patents

Verminderung des Blattspitzenspiels bei einer Gasturbine Download PDF

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Publication number
EP1469165B1
EP1469165B1 EP04290819A EP04290819A EP1469165B1 EP 1469165 B1 EP1469165 B1 EP 1469165B1 EP 04290819 A EP04290819 A EP 04290819A EP 04290819 A EP04290819 A EP 04290819A EP 1469165 B1 EP1469165 B1 EP 1469165B1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
stubs
blades
turbine according
casing
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
EP04290819A
Other languages
English (en)
French (fr)
Other versions
EP1469165A1 (de
Inventor
Claude Daniel Nottin
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1469165A1 publication Critical patent/EP1469165A1/de
Application granted granted Critical
Publication of EP1469165B1 publication Critical patent/EP1469165B1/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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials

Definitions

  • the invention essentially relates to means for reducing clearances between the tops of the blades and the inner surface of the casing of a gas turbine, such as in particular a high pressure turbine for an aircraft engine.
  • peripheral heels at the top of the blades to limit radial clearances between the tops of the blades and a layer of abradable material carried by a ring fixed to the casing of the turbine.
  • These beads may comprise circumferential ribs or wipers which are substantially in contact with the abradable material to provide an axial seal between the casing and the tops of the blades.
  • peripheral heels have the disadvantage of forming an additional mass at the periphery of the turbine wheel, this mass being subjected to centrifugal forces in operation and posing problems of mechanical strength and vibratory behavior of the blades.
  • this radial clearance can locally vary between a minimum value and a maximum value, due to an ovalization of the housing, a difference in height of the blades, a lack of concentricity between the housing and the turbine wheel , etc ...
  • the object of the invention is in particular to provide a simple, satisfactory and economical solution to these problems.
  • a gas turbine in particular for aircraft engine, comprising a turbine wheel rotatably mounted in a housing and carrying blades whose vertices are at a small radial distance from an inner surface of the housing, and means for reducing the clearances between the tops of the blades and the inner surface of the casing, the means for reducing the clearances comprising heels mounted radially sliding at the top of the blades, characterized in that the beads are guided in an annular groove of the casing .
  • the heels are automatically biased towards the inner surface of the casing by centrifugal forces without exerting force on the vanes of the wheel. This avoids the mechanical vibration problems encountered in the mobile blade turbines equipped with fixed peripheral heels and increases the performance of the turbine by eliminating radial clearances between the blade tips and the inner surface of the housing.
  • the heels are of lightweight material and resistant to wear and high temperatures, this material is preferably a ceramic.
  • the aforementioned beads each comprise a curved plate intended to extend along the inner surface of the housing.
  • This curved plate has a surface greater than that of the top of the blade on which it is mounted, which further improves the aforementioned axial seal between the tops of the blades and the inner surface of the housing.
  • At least two circumferential parallel ribs forming wipers are presented by the face of this plate facing the inner face of the housing.
  • each aforementioned heel is at least partially fitted into a bath formed at the top of the blade.
  • each aforementioned heel is fitted on the top of the blade.
  • the invention is applicable to turbines whose inner casing surfaces define veins of constant cylindrical section or diverging section.
  • FIGS. 1 and 2 schematically show the technique prior to the present invention, the reference 10 denoting a blade of a high pressure turbine wheel mounted in rotation around an axis 12 in a casing 14 comprising a fixed metal ring 16 surrounding the turbine wheel and whose inner cylindrical surface is covered with a layer 18 of an abradable material of a type well known in the art.
  • the top of the blade 10 is located at a relatively very small distance from the layer 18 of abradable material and comprises a cavity 20 called a "bathtub" in the art, the bottom of which has dusting holes 22, forming the duct exits. circulation of cooling air which are formed in the dawn 10.
  • the radial clearance 24 between the top of the blade 10 and the layer 18 of abradable material forming the inner surface of the casing must be as small as possible to avoid any deterioration of the performance of the turbine.
  • the invention proposes, as shown in Figures 3 to 5, to mount a radially sliding peripheral bead 26 at the top of the blade 10, the peripheral bead 26 being partially inserted or housed in the bath 20 of the top of the dawn 10.
  • this bead 26 comprises a radially inner portion 28 inserted in the bath 20 of the vane 10 and a radially outer portion 30 in the form of a curved plate in a cylindrical portion, with a parallelepipedic contour as shown in FIG. 4, which extends along the layer 18 of abradable material at a very short distance from it and which has an area or area in the plane of FIG. 4 substantially greater than that of the portion 28 inserted. in the bath 20.
  • the radially outer face of this plate 30 is formed with circumferential parallel ribs 32, for example two in number as shown, whose vertices are in contact with the layer 18 of abradable material and form therewith a labyrinth seal intended to prevent any air circulation in the axial direction between the plate 30 and the layer 18 of abradable material during operation of the turbine.
  • the heel 26 mounted at the end of the blade 10 is partially housed and guided in a groove or annular groove 34 of the ring 16, at the bottom of which is disposed the layer 18 of abradable material. This assembly holds in place the heel 30 at the end of the blade 10, both in the axial direction and in the radial direction.
  • the heels 26 are made of a material which is preferably light and resistant to wear as well as to high temperatures, this material being in particular a ceramic.
  • the beads 26 are rotated around the axis of the turbine with the blades 10 and are subjected to centrifugal forces which apply them to the layer 18 of abradable material.
  • the support of the vertices of the ribs 32 on the layer 18 results in a removal of the radial clearances air passage axially between the tops of the blades 10 and the inner surface of the housing, which increases the performance of the turbine. This support of the heels 26 on the layer 18 does not impose any additional effort on the blades 10.
  • the sliding assembly of the heels 26 on the tips of the blades allows automatic adaptation to the geometric defects of the blades and the ring, due for example to ovalization of the housing, to differences in the height of the blades, to a lack of concentricity of the casing and turbine wheel, etc.
  • the cooling air of the blade 10 which exits through the dedusting holes formed in the bottom of the bath 20, circulates in passages which are formed between the heel 26 and the walls. side 36 of the bath and thus contributes to cooling of these walls.
  • the top of the blade 10 does not include a bath and the peripheral heel 26 is then fitted on the top of the blade 10 and comes for example to cap a peripheral rib 38 of the vertex dawn.
  • the heel 26 has wipers 32 on its radially outer face and is guided and retained in a groove or annular groove 34 of the ring 14.
  • the insertion means or interlocking heels 26 on the tops of the blades 10 are dimensioned and shaped appropriately to avoid single-sided risk of disengagement of the heels.
  • the annular grooves 34 formed in the inner surface of the housing are an additional guarantee of retaining heels and could possibly be removed.
  • the plates 30 forming the radially outer portions of the beads 26 may have a greater or lesser extent than the dimensions of the tops of the blades 10 and, if necessary, these plates 30 may comprise a reinforcement, for example metal, stiffening.
  • the heels 26 can be held on the tops of the blades by gluing or by a link such as a ring or strapping, surrounding the heels 26 and the crown of blading.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (13)

  1. Gasturbine, insbesondere für einen Luftfahrzeugmotor, mit einem Rad, das drehbar in einem Gehäuse (14, 16) angebracht ist und Schaufeln (10) trägt, deren Scheitel in einem geringen radialen Abstand von einer Innenfläche des Gehäuses sind, und Mitteln zur Reduzierung der Spiele zwischen den Scheiteln der Schaufeln und der Innenfläche des Gehäuses, wobei die Mittel zur Reduzierung der Spiele Ansätze (26) aufweisen, die radial gleitend am Scheitel der Schaufeln (10) angebracht sind, dadurch gekennzeichnet, dass die Ansätze (26) in einer ringförmigen Nut (34) des Gehäuses (14, 16) geführt werden.
  2. Gasturbine nach Anspruch 1, dadurch gekennzeichnet, dass die Ansätze (26) aus einem leichten Material bestehen, das verschleißfest und hitzebeständig ist.
  3. Gasturbine nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Ansätze (26) keramisch sind.
  4. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Ansätze (26) radial äußere Teile (30) in Form von einwärts gekrümmten Platten aufweisen, die dazu bestimmt sind, sich entlang der Innenfläche des Gehäuses zu erstrecken.
  5. Gasturbine nach Anspruch 4, dadurch gekennzeichnet, dass der radial äußere plattenförmige Teil (30) der Ansätze (26) eine Versteifungsarmatur aufweist.
  6. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass jeder Ansatz parallele Umfangsrippen (32) aufweist, die an seiner zu der Innenfläche des Gehäuses gewandten Seite Scheibchen bilden.
  7. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Innenfläche des Gehäuses gegenüber den Ansätzen (26) eine Schicht (18) aus abreibbarem Material aufweist.
  8. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Ansätze (26) an den Scheiteln der Schaufeln (10) eingepasst sind.
  9. Gasturbine, insbesondere nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß die Ansätze (26) wenigstens teilweise in Wannen (20) eingefügt sind, die am Scheitel der Schaufeln (10) ausgebildet sind.
  10. Gasturbine nach Anspruch 9, dadurch gekennzeichnet, dass die Ansätze (26) mit den Wänden (36) der Wannen (20) Kühluftzirkulationsdurchgänge abgrenzen, die durch Kanäle gespeist werden, die in den Boden der Wannen münden.
  11. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass sie Mittel (20, 34, 38) zum axialen und radialen Halten der Ansätze (26) an den Scheiteln der Schaufeln (10) aufweist.
  12. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass für die Montage die Ansätze (26) an den Scheiteln der Schaufeln durch Klebung oder durch ein Band gehalten werden, das die Schaufeln umgibt.
  13. Gasturbine nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Innenfläche des Gehäuses gegenüber der Ansätze (26) zylindrisch auseinander gehend oder mit konstantem Querschnitt ist.
EP04290819A 2003-04-16 2004-03-26 Verminderung des Blattspitzenspiels bei einer Gasturbine Expired - Lifetime EP1469165B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0304736A FR2853931A1 (fr) 2003-04-16 2003-04-16 Reduction de jeux dans une turbine a gaz
FR0304736 2003-04-16

Publications (2)

Publication Number Publication Date
EP1469165A1 EP1469165A1 (de) 2004-10-20
EP1469165B1 true EP1469165B1 (de) 2006-10-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP04290819A Expired - Lifetime EP1469165B1 (de) 2003-04-16 2004-03-26 Verminderung des Blattspitzenspiels bei einer Gasturbine

Country Status (6)

Country Link
US (1) US6976824B2 (de)
EP (1) EP1469165B1 (de)
CA (1) CA2463182C (de)
DE (1) DE602004002798T2 (de)
ES (1) ES2274395T3 (de)
FR (1) FR2853931A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006062451A1 (en) 2004-12-08 2006-06-15 Volvo Aero Corporation A wheel for a rotating flow machine

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8434997B2 (en) * 2007-08-22 2013-05-07 United Technologies Corporation Gas turbine engine case for clearance control
US9133726B2 (en) * 2007-09-17 2015-09-15 United Technologies Corporation Seal for gas turbine engine component
FR2940352B1 (fr) 2008-12-23 2014-11-28 Snecma Roue mobile de turbomachine a aubes en materiau composite munies de lechettes metalliques.
US8585356B2 (en) * 2010-03-23 2013-11-19 Siemens Energy, Inc. Control of blade tip-to-shroud leakage in a turbine engine by directed plasma flow
US8500404B2 (en) 2010-04-30 2013-08-06 Siemens Energy, Inc. Plasma actuator controlled film cooling
US9938845B2 (en) * 2013-02-26 2018-04-10 Rolls-Royce Corporation Gas turbine engine vane end devices
US9771870B2 (en) 2014-03-04 2017-09-26 Rolls-Royce North American Technologies Inc. Sealing features for a gas turbine engine
FR3025555B1 (fr) * 2014-09-09 2019-08-16 Safran Aircraft Engines Aube de turbine et turbomachine
JP6595926B2 (ja) * 2016-02-02 2019-10-23 三菱日立パワーシステムズ株式会社 回転機械
US10487679B2 (en) * 2017-07-17 2019-11-26 United Technologies Corporation Method and apparatus for sealing components of a gas turbine engine with a dielectric barrier discharge plasma actuator
KR101974736B1 (ko) * 2017-09-27 2019-05-02 두산중공업 주식회사 블레이드의 실링구조와 이를 포함하는 로터 및 가스터빈
FR3085712B1 (fr) * 2018-09-06 2021-07-02 Safran Aircraft Engines Aube de roue mobile pour turbomachine d'aeronef, presentant un talon decouple de la pale de l'aube
FR3118105B1 (fr) * 2020-12-17 2023-11-24 Safran Aircraft Engines Ensemble rotatif comportant un disque aubagé entouré par un anneau

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US3117716A (en) * 1963-04-10 1964-01-14 Bell Aerospace Corp Ducted rotor
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006062451A1 (en) 2004-12-08 2006-06-15 Volvo Aero Corporation A wheel for a rotating flow machine

Also Published As

Publication number Publication date
CA2463182C (fr) 2011-09-27
US6976824B2 (en) 2005-12-20
US20050008481A1 (en) 2005-01-13
FR2853931A1 (fr) 2004-10-22
EP1469165A1 (de) 2004-10-20
DE602004002798T2 (de) 2007-08-23
ES2274395T3 (es) 2007-05-16
CA2463182A1 (fr) 2004-10-16
DE602004002798D1 (de) 2006-11-30

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