EP2725202A1 - Agencement de support d'étanchéité d'anneau intérieur pour assemblage des aubes statoriques variables d'une turbomachine - Google Patents

Agencement de support d'étanchéité d'anneau intérieur pour assemblage des aubes statoriques variables d'une turbomachine Download PDF

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Publication number
EP2725202A1
EP2725202A1 EP12189946.2A EP12189946A EP2725202A1 EP 2725202 A1 EP2725202 A1 EP 2725202A1 EP 12189946 A EP12189946 A EP 12189946A EP 2725202 A1 EP2725202 A1 EP 2725202A1
Authority
EP
European Patent Office
Prior art keywords
ring
parts
inner ring
angle
carrier
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Withdrawn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
EP12189946.2A
Other languages
German (de)
English (en)
Inventor
Werner Humhauser
Holger Laubert
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP12189946.2A priority Critical patent/EP2725202A1/fr
Publication of EP2725202A1 publication Critical patent/EP2725202A1/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Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Definitions

  • the invention relates to an inner ring seal carrier assembly according to the preamble of patent claim 1 and a turbomachine.
  • Inner ring seal carrier assemblies for variable nozzle vanes of a turbomachine such as an aircraft engine or stationary gas turbine each have an inner ring to the radially inner guide blade bearing, which often has two joinable in a machine housing parting ring ring halves, and a pushed onto the inner ring or its ring halves seal carrier for sealing a radial gap to Rotor with two carrier halves which can be joined in the same parting plane.
  • Such inner ring seal carrier assembly is for example in the DE 10 2006 024 085 A1 and WO 2010/081468 A1 .
  • the two ring halves are conventionally pinned together in the circumferential direction.
  • at least one pin protrudes from one half of the ring beyond the dividing plane and enters a pin receptacle of the other half of the ring.
  • the formation of the pin connections is relatively expensive. In particular, the pins formed as loose items can be lost before and during assembly.
  • the object of the invention is to provide an inner ring seal carrier assembly of an adjustable vane grille of a turbomachine, which eliminates the aforementioned disadvantages and prevents relative movement of ring members and support members in the assembled state. Furthermore, it is an object of the invention to provide a turbomachine with improved efficiency.
  • An inner ring seal carrier arrangement according to the invention of an adjustable guide vane grille of a turbomachine has an inner ring for the radially inner guide vane bearing, which has two ring parts separated at least in a first parting plane. Furthermore, the inner ring seal carrier assembly has a pushed onto the inner ring seal carrier for sealing a radial gap to the rotor of the two separate at least in a second parting plane support members. According to the dividing planes are rotated in the mounted state in the circumferential direction of the guide vane against each other or offset.
  • the butt joints of the inner ring and the seal carrier are offset from each other, whereby an end overlap of the ring parts with the carrier parts or vice versa takes place.
  • the ring parts and support parts fix each other in the region of their butt joints, whereby relative movements of the ring parts and the support parts to each other and to each other are prevented.
  • a separate pinning of the ring parts and / or the carrier parts is not necessary.
  • the seal carrier closes by the staggered assembly, the usual separation gaps between the opposing ring parts, whereby leakage currents are at least greatly reduced or completely prevented by the inner ring seal carrier assembly in the butt joints.
  • the ring members and the support members each enclose an angle of 180 °, wherein the support members and the ring members are twisted to each other.
  • the inner ring and the seal carrier each have two identical or symmetrical ring parts and two identical or symmetrical support parts, which allows a comfortable production and a particularly simple assembly.
  • the two ring parts each enclose an angle of 180 °, wherein the carrier parts span different angles to form the offset parting planes.
  • the one carrier parts has an angle which is reduced by a certain angle change, and the other carrier parts has an angle which is increased by this change in angle.
  • the ring parts are thus symmetrical in this embodiment, allowing a comfortable production of these parts.
  • the carrier parts are however asymmetrical.
  • the carrier parts are symmetrical and the ring parts each span different angles.
  • the two support parts each enclose an angle of 180 ° and the one ring parts has an angle which is reduced by a certain angle change, and the other ring parts has an angle which is increased by this angle change.
  • the carrier parts can be produced conventionally.
  • the two ring parts and the two support parts are each formed asymmetrically.
  • the one ring parts and the one support parts enclose an angle which is reduced by a certain angle change, and the other ring parts and the other support parts each span an angle which is increased by this change in angle.
  • the angular changes of the ring parts and the carrier parts are identical. This allows for easy production and easy twisted positioning of the parts to each other.
  • the angular changes of the ring parts and the support parts are different.
  • a greatest possible flexibility with regard to the ring and support part angles is created.
  • a turbomachine according to the invention has an adjustable vane grille having an inner ring seal carrier assembly according to the invention. Due to the twisted arrangement of the parting planes of the inner ring and the seal carrier leakage currents are through Butt joints of the inner ring at least greatly reduced. In addition, the ring parts of the inner ring are fixed, whereby a precise running gap can be set to rotor tip points. This leads to reduced leakage flows through the running gap.
  • Such a turbomachine thus has a higher efficiency and in particular a higher compressor efficiency compared to a turbomachine with a conventional guide vane grille.
  • FIG. 1 is a view of an embodiment of an inventive inner ring seal carrier assembly 1 shown in the flow direction of a hot gas stream.
  • the inner ring seal carrier assembly 1 is part of an adjustable vane grille of a turbomachine such as an aircraft engine or a stationary gas turbine.
  • the vane grille is arranged on the stator side in the compressor of the turbomachine and surrounds a rotor drum of a rotor which rotates about a rotor axis m. It has a multitude of uniformly distributed over its circumference and in FIG. 1 not illustrated vanes, which are each adjustable about their radially to the rotor axis m extending vertical axis.
  • the inner ring seal carrier assembly 1 has an inner ring 2 and a seal carrier 4, which is pushed onto the inner ring 2 in the circumferential direction or axial direction of the arrangement 1 and thus the guide vane grille and is arranged radially inwardly thereto.
  • the ring members 10a, 10b for receiving the seal carrier 4 in the flow direction of the hot gas flow have front and rear guide members 14, 16 formed as a front guide groove 14 and a rear guide projection 16 in the embodiment shown here.
  • the seal carrier 4 is used to seal a radial gap to the rotor and in particular for sealing a running gap to opposite circumferential rotor seal tips.
  • the seal carrier 4 has an inner peripheral surface 18 for receiving corresponding sealing elements, not shown, such as honeycomb sheets or for applying a coating system.
  • the seal carrier 4 consists of two separate in a second parting plane 20 support members 22a, 22b.
  • the carrier parts 22a, 22b For sliding on the ring parts 10a, 10b, the carrier parts 22a, 22b with the guide elements 14, 16 corresponding counter-elements 26, 28.
  • the front mating member 26 is formed as a hook-like projection for engaging the guide groove 14 and the rear mating member 28 as a rear circumferential groove for receiving the rear guide projection 16.
  • the ring parts 10a, 10b and the carrier parts 22a, 22b are oriented relative to one another such that the ring separating plane 8 is arranged offset in the circumferential direction to the carrier separating plane 20.
  • the two abutting areas 30, 32 of the inner ring seal carrier arrangement 1 are designed as overlap joints, in which, as in FIG. 2 shown, in each case an end-side support portion portion 34, an end-side ring portion portion 36 overlaps in the circumferential direction.
  • the two ring parts 10a, 10b symmetrically and the two support parts 22a, 22b formed symmetrically.
  • the ring parts 10a, 10 terminate flush with a housing parting plane 38 of the turbomachine, whereas the support parts 22a, 22b respectively protrude beyond the housing parting plane 38 with their support part section 34.
  • the ring separation plane 8 is thus in this embodiment in the housing separation plane 38 and the carrier separation plane 20 is also rotated to the housing separation plane 38 in the circumferential direction.
  • the carrier separation plane 20 positioned in the housing separation plane 38 and the ring separation plane 8 to the housing separation plane 36 staggered.
  • both the inner ring 8 and the seal carrier 4 can be rotated with its parting plane 8, 20 to the housing separation plane 34.
  • FIG. 3 an alternative embodiment of the inner ring seal carrier assembly 1 is shown.
  • the ring parts 10a, 10b are symmetrical and the support parts 22a, 22b are asymmetrical.
  • the one support part 22a spans an angle ⁇ ' ⁇ 180 ° and the other support part 22b an angle ⁇ "> 180 ° .
  • ⁇ ⁇ with respect to 180 ° is constant, so that the seal carrier 4 is closed over 360 ° in the installed state.
  • the carrier parts 22a, 22b are thus formed by separating the seal carrier 4 along two parting planes 20 ', 20 "which are set apart by the angle change ⁇ .
  • one carrier parting plane 20' lies in the housing parting plane 38, whereas the other carrier parting plane 20" is made by the angle change ⁇ to the housing separation plane 38.
  • the ring parts 10a, 10b are arranged such that the ring separation plane 8 is offset to the housing separation plane 38.
  • FIG. 4 another embodiment of the inner ring seal carrier assembly 1 is shown.
  • the support parts 22a, 22b are symmetrical and the ring parts 10a, 10b are asymmetrical.
  • the one ring part 10a spans an angle ⁇ ' ⁇ 180 ° and the other ring part 10b an angle ⁇ "> 180 ° .
  • ⁇ ⁇ with respect to 180 ° is constant, so that the inner support 2 is closed over 360 ° in the mounted state.
  • the ring parts 10a, 10b are thus formed by separating the inner support 2 along two parting planes 8 ', 8 "set apart by the angle change ⁇ .
  • one ring separation plane 8' lies in the housing separation plane 38
  • the other ring separation plane 8" is made by the angle change ⁇ to the housing separation plane 38.
  • the carrier parts 22a, 22b arranged such that the carrier separation plane 20 is offset to the housing separation plane 38.
  • FIG. 5 another embodiment of the inner ring seal carrier assembly 1 is shown.
  • the ring parts 10a, 10b are asymmetrical and the support parts 22a, 22b are asymmetrical.
  • Both the inner ring 2 and the seal carrier 4 is divided along two mutually employed parting lines 8 ', 8 ", 20', 20" in two ring parts 10a, 10b and in two support parts 22a, 22b, each spanning an angle not equal to 180 ° ,
  • an angle change ⁇ r of the ring parts 10a, 10b is equal to an angle change ⁇ t of the carrier parts 22a, 22b.
  • the ring parts 10a, 10b and the carrier parts 22a, 22b may also have different angle changes ⁇ r, ⁇ t.
  • the orientation of the ring parts 10a, 10b and the support parts 22a, 22b is in the embodiment shown such that in each case one of the ring separation planes 8 'and one of the support separation planes 20' lie in a housing separation plane 38 and the other ring separation plane 8 "and the other carrier separation plane 20 "offset to housing separation plane 38 are located.
  • both parting planes 8 ', 8 ", 20', 20" of the inner ring 2 and the seal carrier 4 may be offset to the housing separation plane 38.
  • an inner ring seal carrier assembly of an adjustable guide vane grille of a turbomachine whose divided into two ring parts inner ring and its divided into two carrier parts seal carrier in the circumferential direction of the arrangement are arranged rotated to each other, and a turbomachine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP12189946.2A 2012-10-25 2012-10-25 Agencement de support d'étanchéité d'anneau intérieur pour assemblage des aubes statoriques variables d'une turbomachine Withdrawn EP2725202A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12189946.2A EP2725202A1 (fr) 2012-10-25 2012-10-25 Agencement de support d'étanchéité d'anneau intérieur pour assemblage des aubes statoriques variables d'une turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12189946.2A EP2725202A1 (fr) 2012-10-25 2012-10-25 Agencement de support d'étanchéité d'anneau intérieur pour assemblage des aubes statoriques variables d'une turbomachine

Publications (1)

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EP2725202A1 true EP2725202A1 (fr) 2014-04-30

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Family Applications (1)

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EP12189946.2A Withdrawn EP2725202A1 (fr) 2012-10-25 2012-10-25 Agencement de support d'étanchéité d'anneau intérieur pour assemblage des aubes statoriques variables d'une turbomachine

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111098245A (zh) * 2019-12-11 2020-05-05 北京龙威发电技术有限公司 一种汽轮机持环预扭叶片的配准装置及方法
CN112065777A (zh) * 2020-11-10 2020-12-11 中国航发上海商用航空发动机制造有限责任公司 压气机进口导流叶片的调节精度保持结构

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT113565B (de) * 1926-08-28 1929-06-25 Franz Ing Hauber Metallpackung.
DE618115C (de) * 1932-04-21 1935-09-02 Bruno Malcher Abdichtung einer Welle mit zwei Reihen starrer Ringsegmente und einem eigenelastischen Dichtungsring
DE1914893U (de) * 1964-12-24 1965-04-29 Bbc Brown Boveri & Cie Wellendichtring fuer die abdichtung der wellendurchfuehrung.
US5639212A (en) * 1996-03-29 1997-06-17 General Electric Company Cavity sealed compressor
US6129512A (en) * 1998-03-05 2000-10-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Circular stage of vanes connected at internal ends thereof by a connecting ring
DE102006024085A1 (de) 2006-05-23 2007-11-29 Mtu Aero Engines Gmbh Turboverdichter in Axialbauweise
WO2010081468A1 (fr) 2009-01-16 2010-07-22 Mtu Aero Engines Gmbh Procédé de montage d'une bague intérieure intégrée d'un stator de turbocompresseur
DE202011104825U1 (de) * 2011-08-20 2011-11-23 Gapi Technische Produkte Gmbh Dichtungsanordnung
DE102012001322A1 (de) * 2011-01-25 2012-07-26 Rolls-Royce Corp. Schaufelkranzaggregat

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT113565B (de) * 1926-08-28 1929-06-25 Franz Ing Hauber Metallpackung.
DE618115C (de) * 1932-04-21 1935-09-02 Bruno Malcher Abdichtung einer Welle mit zwei Reihen starrer Ringsegmente und einem eigenelastischen Dichtungsring
DE1914893U (de) * 1964-12-24 1965-04-29 Bbc Brown Boveri & Cie Wellendichtring fuer die abdichtung der wellendurchfuehrung.
US5639212A (en) * 1996-03-29 1997-06-17 General Electric Company Cavity sealed compressor
US6129512A (en) * 1998-03-05 2000-10-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Circular stage of vanes connected at internal ends thereof by a connecting ring
DE102006024085A1 (de) 2006-05-23 2007-11-29 Mtu Aero Engines Gmbh Turboverdichter in Axialbauweise
WO2010081468A1 (fr) 2009-01-16 2010-07-22 Mtu Aero Engines Gmbh Procédé de montage d'une bague intérieure intégrée d'un stator de turbocompresseur
DE102012001322A1 (de) * 2011-01-25 2012-07-26 Rolls-Royce Corp. Schaufelkranzaggregat
DE202011104825U1 (de) * 2011-08-20 2011-11-23 Gapi Technische Produkte Gmbh Dichtungsanordnung

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111098245A (zh) * 2019-12-11 2020-05-05 北京龙威发电技术有限公司 一种汽轮机持环预扭叶片的配准装置及方法
CN111098245B (zh) * 2019-12-11 2021-06-15 北京龙威发电技术有限公司 一种汽轮机持环预扭叶片的配准装置及方法
CN112065777A (zh) * 2020-11-10 2020-12-11 中国航发上海商用航空发动机制造有限责任公司 压气机进口导流叶片的调节精度保持结构
CN112065777B (zh) * 2020-11-10 2021-01-19 中国航发上海商用航空发动机制造有限责任公司 压气机进口导流叶片的调节精度保持结构

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