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EP1673519B1 - Dispositif d'etancheite pour une turbine a gaz - Google Patents

Dispositif d'etancheite pour une turbine a gaz Download PDF

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Publication number
EP1673519B1
EP1673519B1 EP04786886A EP04786886A EP1673519B1 EP 1673519 B1 EP1673519 B1 EP 1673519B1 EP 04786886 A EP04786886 A EP 04786886A EP 04786886 A EP04786886 A EP 04786886A EP 1673519 B1 EP1673519 B1 EP 1673519B1
Authority
EP
European Patent Office
Prior art keywords
sealing
projections
rotor
sealing arrangement
compressor
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
EP04786886A
Other languages
German (de)
English (en)
Other versions
EP1673519A1 (fr
Inventor
Marcello De Martino
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 GmbH
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 GmbH, MTU Aero Engines AG filed Critical MTU Aero Engines GmbH
Publication of EP1673519A1 publication Critical patent/EP1673519A1/fr
Application granted granted Critical
Publication of EP1673519B1 publication Critical patent/EP1673519B1/fr
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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • 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
    • F05D2240/55—Seals
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb

Definitions

  • the invention relates to a sealing arrangement for a gas turbine according to the preamble of patent claim 1.
  • Gas turbines consist of several modules, such as, inter alia, a fan (fan), a combustion chamber, preferably a plurality of compressors and a plurality of turbines.
  • the preferably several turbines are, in particular, a high-pressure turbine and a low-pressure turbine, with the plurality of compressors in particular a high-pressure compressor and low-pressure compressor.
  • a plurality of guide vane rings are positioned behind one another in the axial direction or in the direction of flow through the gas turbine, each guide vane ring having a plurality of guide vanes distributed over the circumference.
  • each a rotor blade ring is positioned, which has a plurality of blades. The blades are associated with a rotor and rotate together with the rotor relative to a fixed housing and the also stationary formed vanes of the vane rings.
  • sealing arrangements are known from the prior art, which serve to seal a gap between the radially inner ends of the fixed guide vanes and the rotor of the gas turbine, said sealing arrangements configured in such a way in that the rotor has at least two circumferentially spaced apart axially spaced sealing projections cooperating with inlet linings associated with the radially inward ends of the stationary vanes.
  • a seal assembly according to the prior art is from the document EP 1347152 A known.
  • the present invention relates to a seal assembly for sealing the gap between radially inner ends of the vanes of a vane ring and a rotor of the gas turbine.
  • the present invention is based on the problem to provide a novel seal assembly for a gas turbine.
  • the sealing projections are inclined in the axial direction to a side of higher pressure, wherein at least one recirculation structure is arranged in a space defined by the at least two sealing projections and the corresponding inlet linings, and wherein the or each recirculation structure points towards the higher pressure side is aligned.
  • inlet coverings are formed as honeycomb structures.
  • the sealing projections are formed as sealing fins.
  • the sealing projections cooperating with a vane ring and the corresponding vane ring inlet linings have different radii, wherein outer radii of the sealing projections and inner radii of the inlet linings increase or increase towards the higher pressure side.
  • FIG Fig. 1 described in more detail.
  • Fig. 1 shows a schematic cross section through a compressor 10 of a gas turbine with a fixed housing 11 and a relative to the stationary housing 11 rotating rotor 12, wherein the fixed housing 11 and the rotor 12 define a main flow channel 13.
  • the flow direction of the main flow passage 13 is in Fig. 1 visualized by an arrow 14.
  • a plurality of fixed vane rings 15 are arranged in the axial direction or in the flow direction behind each other, wherein Fig. 1 only shows such a vane ring 15.
  • Each vane ring 15 is formed by a plurality of vanes 16 disposed at an axial position of the compressor 10 in the circumferential direction thereof around the rotor 12.
  • the stationary vanes 16 are integrated with a radially outer end 17 in the housing 11. Between a radial outer end 17 opposite the radially inner end 18 of the guide vanes 16 and the rotor 12, a gap 19 is formed.
  • FIG. 1 shows such a blade ring 20, which is formed of a plurality of blades 21 which are fixed with a radially inner end 22 on the rotor 12. Between a radially outer end 23 of the blades 21 and the housing 11 of the compressor 10, in turn, a gap is formed. To seal this radial gap between the radially outer ends 23 of the rotating blades 20 and the fixed housing 11, a so-called inlet lining 24 is associated with the housing 11, which enables a wear-resistant rubbing of the radially outer ends 23 of the rotor blades 21 into the housing 11 of the compressor 10.
  • the present invention relates to a sealing arrangement for sealing the gap 19 between the radially inner ends 18 of the stationary vanes 16 of a vane ring 15 and the rotor 12 of the compressor 10.
  • this seal arrangement comprises two sealing projections 25 and 26 associated with the rotor 12.
  • the sealing projections 25 and 26 are formed as so-called sealing fins and spaced apart in the axial direction of the compressor 10.
  • the sealing projections 25 and 26 ⁇ extend over the entire circumference of the rotor 12, so are closed in the circumferential direction.
  • the sealing projections 25 and 26 cooperate with inlet linings 27 and 28.
  • the inlet linings 27 and 28 are associated with the radially inner ends 18 of the fixed guide vanes 16, namely, integrated into the platform-shaped, radially inward ends 18 of the guide vanes 16.
  • the inlet pads 27 and 28 are therefore fixed and the sealing projections 25 and 26 rotate together with the rotor 12 with respect to the fixed inlet linings 27 and 28.
  • the inlet linings 27 and 28 are preferably designed as honeycomb seals, wherein honeycomb of these honeycomb structures in the direction of the sealing projections 25th and 26 are open.
  • Fig. 1 shows compressor 10 of a gas turbine increases in the flow direction (arrow 14), the gas pressure within the compressor.
  • the sealing projections 25 and 26, which are - as already mentioned - are designed as sealing fins, inclined or inclined in the axial direction to a side of higher gas pressure.
  • the sealing projections 25 and 26 are with their tips to the right side, so to the side higher gas pressure, inclined. As a result, the sealing effect of the sealing projections 25 and 26 is optimized.
  • a recirculation structure 30 is arranged according to the invention in one of the sealing projections 25 and 26 and the corresponding inlet coverings 27 and 28 limited space 29.
  • the recirculation structure 30 is integrated in the radially inner end 18 of the guide vanes 16 of the Leitschaufelkränzes 15, wherein the radially inner ends 18 are designed as a platform of the vanes 16.
  • the inlet pads 27 and 28, which are also associated with the radially inner end 18 of the vanes 16, are according to Fig. 1 arranged on both sides of the recirculation structure 30. It is within the meaning of the present invention that the recirculation structure 30 as well as the sealing projections 25 and 26 is aligned with the side of higher gas pressure.
  • the two sealing projections 25 and 26 and the two cooperating with the sealing projections 25 and 26 inlet linings 27 and 28 have graduated radii.
  • the inlet lining 28 cooperating with the downstream sealing projection 26 also has a larger inner diameter than the inlet lining 27 cooperating with the upstream sealing projection 25.
  • the recirculation structure 30 projects radially beyond the inlet lining 28 arranged downstream.
  • each vane ring 15 can be arranged as described above sealing arrangement for sealing the radial gap 19 between the radially inner ends 18 of the stationary vanes and the rotor 12.
  • the present invention preferably finds use for reducing the leakage in the so-called Statorwell cavities of high pressure compressors of an aircraft engine.
  • the seal assembly according to the invention can also be used in the turbines of aircraft engines or in stationary gas turbines.

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 (8)

  1. Dispositif d'étanchéité pour une turbine à gaz, en particulier pour un compresseur d'un turboréacteur, permettant d'assurer l'étanchéité d'un interstice (19) entre des extrémités (18) radialement intérieures d'aubes directrices (16) d'une couronne d'aubes directrices (15) et un rotor (12), dans lequel le rotor (12) présente au moins deux saillies d'étanchéité (25, 26) s'étendant dans le sens périphérique du rotor (12), positionnées à une distance axiale l'une de l'autre qui entraînent, en combinaison avec les revêtements d'entrée (27, 28) réalisés sous forme de structures en nid d'abeille affectés aux extrémités (18) radialement intérieures des aubes directrices (16), une étanchéification de l'interstice (19), et dans lequel les saillies d'étanchéité (25, 26) sont inclinées ou disposées en oblique dans le sens axial vers un côté de pression supérieure, dans lequel le dispositif d'étanchéité comporte les au moins deux saillies d'étanchéité, les revêtements d'entrée ainsi qu'un espace qui en est délimité, caractérisé en ce qu'au moins une structure de recirculation (30) est disposée dans l'espace (29) délimité par les au moins deux saillies d'étanchéité (25, 26) et les revêtements d'entrée (27, 28) réalisés sous forme de structures en nid d'abeille, et dirigée vers le côté de pression supérieure.
  2. Dispositif d'étanchéité selon la revendication 1, caractérisé en ce que la ou chaque structure de recirculation (30) est intégrée dans un plateau radialement intérieur des aubes directrices (16) de la couronne d'aubes directrices (15).
  3. Dispositif d'étanchéité selon la revendication 1 ou 2, caractérisé en ce que les saillies d'étanchéité (25, 26) sont réalisées sous forme d'ailettes d'étanchéité.
  4. Dispositif d'étanchéité selon l'une quelconque des revendications 1 à 3, caractérisé en ce que les nids d'abeille des structures en nid d'abeille sont ouverts en direction des saillies d'étanchéité (25, 26).
  5. Dispositif d'étanchéité selon l'une quelconque des revendications 1 à 4, caractérisé en ce que les saillies d'étanchéité (25, 26) coopérant avec une couronne d'ailes directrices et les revêtements d'entrée (27, 28) correspondants de la couronne d'ailes directrices (15) sont de rayons différents, dans lequel les rayons extérieurs des saillies d'étanchéité (25, 26) ainsi que les rayons intérieurs des revêtements d'entrée (27, 28) augmentent ou sont croissants en direction du côté de pression supérieure.
  6. Turbocompresseur de type axial et/ou de type diagonal et/ou de type radial, avec un dispositif d'étanchéité selon l'une quelconque des revendications 1 à 5.
  7. Turboréacteur, avec un turbocompresseur selon la revendication 6.
  8. Turbine à gaz stationnaire, avec un turbocompresseur selon la revendication 6.
EP04786886A 2003-10-17 2004-09-30 Dispositif d'etancheite pour une turbine a gaz Expired - Lifetime EP1673519B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE2003148290 DE10348290A1 (de) 2003-10-17 2003-10-17 Dichtungsanordnung für eine Gasturbine
PCT/DE2004/002174 WO2005040561A1 (fr) 2003-10-17 2004-09-30 Dispositif d'etancheite conçu pour une turbine a gaz

Publications (2)

Publication Number Publication Date
EP1673519A1 EP1673519A1 (fr) 2006-06-28
EP1673519B1 true EP1673519B1 (fr) 2012-08-29

Family

ID=34428460

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04786886A Expired - Lifetime EP1673519B1 (fr) 2003-10-17 2004-09-30 Dispositif d'etancheite pour une turbine a gaz

Country Status (4)

Country Link
US (1) US9011083B2 (fr)
EP (1) EP1673519B1 (fr)
DE (1) DE10348290A1 (fr)
WO (1) WO2005040561A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2014020509A (ja) * 2012-07-20 2014-02-03 Toshiba Corp シール装置、軸流タービン、および発電プラント
US10066750B2 (en) * 2012-11-13 2018-09-04 Mitsubishi Heavy Industries Compressor Corporation Rotary machine
DE102013224199A1 (de) * 2013-11-27 2015-05-28 MTU Aero Engines AG Gasturbinen-Laufschaufel
EP3172410B1 (fr) * 2014-07-24 2018-05-16 Siemens Aktiengesellschaft Ensemble d'aubes statoriques dans une turbine à gaz
DE102017204243A1 (de) * 2017-03-14 2018-09-20 MTU Aero Engines AG Dichtfin mit zumindest einer gewölbten Seitenflanke
FR3099788B1 (fr) * 2019-08-06 2021-09-03 Safran Aircraft Engines Abradable de turbine de turbomachine comprenant une face d’usure pourvue de redresseurs de flux

Family Cites Families (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1689735A (en) * 1923-10-05 1928-10-30 Losel Franz Labyrinth gland construction
US1857961A (en) * 1927-12-15 1932-05-10 Westinghouse Electric & Mfg Co Bi-metal packing
US1756958A (en) * 1928-10-03 1930-05-06 Westinghouse Electric & Mfg Co Elastic-fluid turbine
US4351532A (en) * 1975-10-01 1982-09-28 United Technologies Corporation Labyrinth seal
US4513975A (en) * 1984-04-27 1985-04-30 General Electric Company Thermally responsive labyrinth seal
US5244216A (en) * 1988-01-04 1993-09-14 The Texas A & M University System Labyrinth seal
US5029876A (en) * 1988-12-14 1991-07-09 General Electric Company Labyrinth seal system
US5281090A (en) * 1990-04-03 1994-01-25 General Electric Co. Thermally-tuned rotary labyrinth seal with active seal clearance control
US5127797A (en) * 1990-09-12 1992-07-07 United Technologies Corporation Compressor case attachment means
US5118253A (en) * 1990-09-12 1992-06-02 United Technologies Corporation Compressor case construction with backbone
US5354174A (en) * 1990-09-12 1994-10-11 United Technologies Corporation Backbone support structure for compressor
US5236302A (en) * 1991-10-30 1993-08-17 General Electric Company Turbine disk interstage seal system
US5218816A (en) * 1992-01-28 1993-06-15 General Electric Company Seal exit flow discourager
US5320488A (en) * 1993-01-21 1994-06-14 General Electric Company Turbine disk interstage seal anti-rotation system
US5333993A (en) * 1993-03-01 1994-08-02 General Electric Company Stator seal assembly providing improved clearance control
US5380155A (en) * 1994-03-01 1995-01-10 United Technologies Corporation Compressor stator assembly
GB2307520B (en) * 1995-11-14 1999-07-07 Rolls Royce Plc A gas turbine engine
US5749701A (en) * 1996-10-28 1998-05-12 General Electric Company Interstage seal assembly for a turbine
US5984630A (en) * 1997-12-24 1999-11-16 General Electric Company Reduced windage high pressure turbine forward outer seal
DE19931765A1 (de) * 1999-07-08 2001-01-11 Rolls Royce Deutschland Zweistufige oder mehrstufige Axialturbine einer Gasturbine
US6610416B2 (en) 2001-04-26 2003-08-26 General Electric Company Material treatment for reduced cutting energy and improved temperature capability of honeycomb seals
US6769865B2 (en) 2002-03-22 2004-08-03 General Electric Company Band cooled turbine nozzle
GB0218060D0 (en) * 2002-08-03 2002-09-11 Alstom Switzerland Ltd Sealing arrangements
US6969239B2 (en) * 2002-09-30 2005-11-29 General Electric Company Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine
FR2867223B1 (fr) * 2004-03-03 2006-07-28 Snecma Moteurs Turbomachine comme par exemple un turboreacteur pour avion
GB0412476D0 (en) * 2004-06-04 2004-07-07 Rolls Royce Plc Seal system
GB0424883D0 (en) * 2004-11-11 2004-12-15 Rolls Royce Plc Seal structure
US7287956B2 (en) * 2004-12-22 2007-10-30 General Electric Company Removable abradable seal carriers for sealing between rotary and stationary turbine components
GB0613715D0 (en) * 2006-07-11 2006-08-23 Rolls Royce Plc A seal between relatively moveable members
GB0722511D0 (en) * 2007-11-19 2007-12-27 Rolls Royce Plc Turbine arrangement

Also Published As

Publication number Publication date
EP1673519A1 (fr) 2006-06-28
US20070274825A1 (en) 2007-11-29
DE10348290A1 (de) 2005-05-12
US9011083B2 (en) 2015-04-21
WO2005040561A1 (fr) 2005-05-06

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