EP1026367A1 - Système d'étanchéité pour les extrémités d'aubes mobiles de turbomachine - Google Patents

Système d'étanchéité pour les extrémités d'aubes mobiles de turbomachine Download PDF

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Publication number
EP1026367A1
EP1026367A1 EP99101655A EP99101655A EP1026367A1 EP 1026367 A1 EP1026367 A1 EP 1026367A1 EP 99101655 A EP99101655 A EP 99101655A EP 99101655 A EP99101655 A EP 99101655A EP 1026367 A1 EP1026367 A1 EP 1026367A1
Authority
EP
European Patent Office
Prior art keywords
sealing material
gap
blade tip
blade
fluid machine
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.)
Withdrawn
Application number
EP99101655A
Other languages
German (de)
English (en)
Inventor
Gerhard Döpper
Beate Heimberg
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP99101655A priority Critical patent/EP1026367A1/fr
Publication of EP1026367A1 publication Critical patent/EP1026367A1/fr
Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, with a gap between a blade and a stationary component opposite the blade.
  • the invention further relates to a method for sealing of such a gap.
  • the invention also relates the production of a fluid machine.
  • U.S. Patent No. 4,936,745 discloses an abrasive ceramic gap seal for a gas turbine. Run blades of the gas turbine are rotatable in an annular flow channel of the gas turbine arranged. Each blade has a blade tip on. The blade tip is through a gap separated from an opposite flow channel wall in order to brushing the blade tip during rotation and to avoid the following damage.
  • the flow channel wall is along an annular walkway for the opposite blade tips with an abrasive ceramic coating. When touching The blade tip is covered by the ceramic coating Material removed. This material removal ensures that that the blade tips are touching not be harmed.
  • the ceramic coating is one zirconium compound stabilized with yttrium MCrAlY oxidation protection layer applied by means of plasma spraying is.
  • Such a layer system resists the thermal Loads in the hot gas duct. Due to the abrasion ability of the ceramic material becomes an effective gap seal provided, d. H. the space between the Blade tips and the flow channel wall is kept small, so that the amount of hot gas flowing through the gap and thus gap losses are kept small.
  • U.S. Patent No. 5,355,637 also discloses a gap seal using an abrasive, ceramic material. This is applied to the blade tip and contains cubic Boron nitride which is coated with aluminum nitride.
  • US Pat. No. 4,289,446 shows a durable gap seal by means of an abrasive ceramic material that part of the flow channel wall forming guide ring for the blades are applied. Under the ceramic material a porous metallic material is arranged, so that regarding one through warming up and cooling down processes resulting thermal load an increased service life of the layer system results.
  • the object of the invention is to provide a turbomachine with a durable and effective gap seal. Another task the invention is the specification of a method for sealing of a gap in a turbomachine. Finally is also an object of the invention to provide a method for the production of a turbomachine.
  • a turbomachine Problem solved by a fluid machine with a Blade which has a blade tip and with a resting component opposite the blade tip and with a gap between the blade tip and the stationary component, one by moving the blade deformable sealing material is arranged in the gap.
  • the invention is based on the finding that in one purely abrasive sealing material due to the cutting Cracks are introduced into the sealing material, which too local chipping and thus a reduced service life the gap seal can lead.
  • through the cutting removal of sealing material when brushing the Blade tips released material which is in the flow channel is carried away by the hot gas. This has one eroding effect for in the flow direction in the flow channel subsequently arranged blades result.
  • Farther are usually comparatively abrasive sealing materials hard ceramics, which may already be some damage to the blade tips can come to a streak. Especially with single crystals running blades can be problematic.
  • the ductility of the Sealing material an increased long-term stability of the sealing material safe against abrasive sealing materials because it hardly any training from increasing with time Cracking is coming. Furthermore, the sealing material is characterized by ductility so resilient that damage when touched almost excluded are.
  • the sealing material is so ductile that it is almost completely deformed and practically not removed.
  • the sealing material is preferably arranged on the blade tip. There is enough space for at the blade tip deformation of the sealing material, d. H. the sealing material can e.g. be displaced to the side deforming.
  • the sealing material is preferably on the stationary component arranged. This is particularly simple in terms of production technology, if not every blade tip with the sealing material to be coated.
  • the sealing material can also at the same time both on the blade tip and be arranged on the stationary component.
  • the turbomachine is preferably designed as a gas turbine.
  • the sealing material must be one gap-sealing effect even under high thermal loads can withstand the hot gas.
  • sealing material can also be of considerable importance in a steam turbine Be an advantage.
  • the sealing material preferably contains an intermetallic phase. At least one component of the sealing material is preferably selected from the group of the following compounds: NiAl, NiAlTaCr, FeAl, FeCrAl. Here are the first three examples of an intermetallic phase.
  • the sealing material preferably contains a silicide, in particular molybdenum silicide (MoSi 2 ). MoSi 2 is also an intermetallic phase.
  • the sealing material preferably consists entirely of one of the aforementioned substances.
  • the stationary component is preferably a guide ring for the Blade.
  • Cooling fluid can e.g. by the interior of the blade to the blade tip become. There it enters the flow channel through openings out. These openings also lead through the sealing material, when this is applied to the blade tip is.
  • the openings are preferably arranged so that there is film cooling by the cooling fluid.
  • the cooling fluid can also be used to cool the stationary component and in this case is directed to openings in the stationary component and exits into the flow channel from there. Here the openings pass through the sealing material when it is open the stationary component is applied.
  • purely abrasive Sealing materials can be removed by machining Sealing material for clogging the openings and out of them resulting in local overheating. This danger is significantly lower with the deformable sealing material, since at most there is a small amount of material removed could clog the openings.
  • the gap is preferably designed like a labyrinth.
  • a labyrinth seal With a labyrinth seal, the blade tip grips interlocked in the stationary component, d. H. in the stationary component and on the blade tip are projections against each other staggered so that a serpentine Flow path through the gap results. Even with one Training can be done on both the sealing tip on the blade as well as on the resting component or on both be upset.
  • the rotor blade and / or the stationary one is further preferred Component with an oxidation and / or corrosion protection layer coated, on which a ceramic thermal barrier coating is applied is.
  • a layer system serves to protect the components exposed to hot gas before thermal overload.
  • the sealing material is in this version applied to the protective layer system.
  • According to the invention is based on a method for sealing a Column-directed task solved by a method for Sealing a gap between a blade tip and a stationary component of a turbomachine, in particular a gas turbine by moving the blade a sealing material is deformed in the gap so that in Gap almost no free space remains.
  • a fluid machine directed problem solved by a Procedure in which on a blade tip of a blade and / or on one of the rotor blade tips in the turbomachine opposite resting component, a deformable Sealing material for sealing a gap between the blade tip and the stationary component in the turbomachine is applied.
  • the sealing material is preferably by means of a thermal Spraying process, e.g. Electron beam physical vapor deposition or thermal plasma spraying. Prefers the sealing material is evaporated.
  • the sealing material is preferably only on the blade tip upset.
  • a silicide in particular molybdenum silicide (MoSi 2 ), is more preferably used as the sealing material.
  • An intermetallic phase is preferably used as the sealing material.
  • a turbomachine designed as a gas turbine 1.
  • a combustion chamber 5 connects to a compressor 3.
  • a turbine part in turn connects to the combustion chamber 5 7 on.
  • the turbine part 7 comprises an annular channel-shaped flow channel 9 with a flow channel wall 10.
  • In the flow channel 9 are alternately successive guide vanes 11 and blades 13 arranged.
  • Each vane 11 and each blade 13 is in a respective ring of guide blades 11 or arranged by blades 13 and covered the height of the widening in the flow direction Flow channel 9.
  • Each blade 13 has a blade tip 14 on.
  • the blades 13 are with their Blade tip 14 arranged opposite a stationary component 15, the resting component 15 forms part of the flow channel wall 10 forms.
  • the component at rest 15 a respective one assigned to a moving blade ring Guide ring for the blades 13.
  • a sealing material 19 arranged in the gap 17.
  • This sealing material 19 is deformable so that when the blade tips rub against the sealing material 19 brought about a deformation of the sealing material 19 will that the surfaces of the blade tip 14 and adapt the sealing material 19 to each other. This leads to, that a space between the blade tip 14 and the Sealing material 19 remains very small and thus gap losses be practically avoided, that is, the amount of by the Gap 17 flowing hot gas is small.
  • the guide ring 15 is made from a base material 31.
  • an oxidation and corrosion protection layer 33 applied, preferably an MCrAlY coating.
  • a ceramic Thermal insulation layer preferably based on zirconium.
  • the sealing material is on the ceramic thermal insulation layer 35 19 applied.
  • FIG. 3 schematically shows a labyrinth-like embodiment of the Gap 17.
  • Towards these ledges 51 are offset in the spaces between the Protrusions 51 engaging counter-protrusions 53 on the blade tip 14 arranged.
  • the blade tip 14 together with the counter protrusions 53 with the sealing material 19 coated.
  • touching the blade 13 comes to the stationary component 15 there is a deformation of the sealing material 19 with the above Advantages.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP99101655A 1999-02-05 1999-02-05 Système d'étanchéité pour les extrémités d'aubes mobiles de turbomachine Withdrawn EP1026367A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP99101655A EP1026367A1 (fr) 1999-02-05 1999-02-05 Système d'étanchéité pour les extrémités d'aubes mobiles de turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP99101655A EP1026367A1 (fr) 1999-02-05 1999-02-05 Système d'étanchéité pour les extrémités d'aubes mobiles de turbomachine

Publications (1)

Publication Number Publication Date
EP1026367A1 true EP1026367A1 (fr) 2000-08-09

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP99101655A Withdrawn EP1026367A1 (fr) 1999-02-05 1999-02-05 Système d'étanchéité pour les extrémités d'aubes mobiles de turbomachine

Country Status (1)

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EP (1) EP1026367A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2309098A1 (fr) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Profil et aube directrice, aube rotorique, turbine à gaz et turbomachine associées
CN113090341A (zh) * 2021-05-14 2021-07-09 中国航发湖南动力机械研究所 一种能适应转子双向旋转的指尖密封装置

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4289446A (en) 1979-06-27 1981-09-15 United Technologies Corporation Ceramic faced outer air seal for gas turbine engines
US4540336A (en) * 1984-04-19 1985-09-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Oxidizing seal for a turbine tip gas path
US4936745A (en) 1988-12-16 1990-06-26 United Technologies Corporation Thin abradable ceramic air seal
US5238364A (en) * 1991-08-08 1993-08-24 Asea Brown Boveri Ltd. Shroud ring for an axial flow turbine
US5355637A (en) 1991-06-04 1994-10-18 Rolls-Royce Plc Abrasive medium

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4289446A (en) 1979-06-27 1981-09-15 United Technologies Corporation Ceramic faced outer air seal for gas turbine engines
US4540336A (en) * 1984-04-19 1985-09-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Oxidizing seal for a turbine tip gas path
US4936745A (en) 1988-12-16 1990-06-26 United Technologies Corporation Thin abradable ceramic air seal
US5355637A (en) 1991-06-04 1994-10-18 Rolls-Royce Plc Abrasive medium
US5238364A (en) * 1991-08-08 1993-08-24 Asea Brown Boveri Ltd. Shroud ring for an axial flow turbine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2309098A1 (fr) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Profil et aube directrice, aube rotorique, turbine à gaz et turbomachine associées
US20120230818A1 (en) * 2009-09-30 2012-09-13 Andrew Shepherd Airfoil and corresponding guide vane, blade, gas turbine and turbomachine
CN113090341A (zh) * 2021-05-14 2021-07-09 中国航发湖南动力机械研究所 一种能适应转子双向旋转的指尖密封装置

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