EP1577501A1 - Hochdruckturbinenstator einer Strömungsmaschine und deren Zusammenbauverfahren - Google Patents

Hochdruckturbinenstator einer Strömungsmaschine und deren Zusammenbauverfahren Download PDF

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Publication number
EP1577501A1
EP1577501A1 EP05290319A EP05290319A EP1577501A1 EP 1577501 A1 EP1577501 A1 EP 1577501A1 EP 05290319 A EP05290319 A EP 05290319A EP 05290319 A EP05290319 A EP 05290319A EP 1577501 A1 EP1577501 A1 EP 1577501A1
Authority
EP
European Patent Office
Prior art keywords
stator
housing
pressure turbine
sectors
air
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.)
Granted
Application number
EP05290319A
Other languages
English (en)
French (fr)
Other versions
EP1577501B1 (de
Inventor
Anne-Marie Arraitz
Thierry Fachat
Jérôme Friedel
Alain Gendraud
Delphine Roussin
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 EP1577501A1 publication Critical patent/EP1577501A1/de
Application granted granted Critical
Publication of EP1577501B1 publication Critical patent/EP1577501B1/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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/209—Heat transfer, e.g. cooling using vortex tubes

Definitions

  • the present invention relates to the general field of driving game at the top of the moving blades of a high-pressure turbine turbomachine. It is more particularly a method of the sectorized elements composing the stator of a turbine high-pressure turbomachine.
  • the stator of a turbomachine high-pressure turbine is consists mainly of an annular housing arranged around an axis longitudinal axis of the turbine, a plurality of sectorized spacers mounted on the housing and a plurality of ring segments attached to the spacers and which form a circular surface surrounding blades movable rotor of the turbine.
  • the present invention therefore aims to overcome such drawbacks by proposing a method of assembling the sectorized elements of a annular stator of a high-pressure turbine which makes it possible to obtain a gameplay at the top of the blades leading to distortions as low as possible and in all repetitive cases.
  • the invention relates to a method of assembly of sectorized elements of an annular stator of a high-pressure turbine turbomachine about a longitudinal axis of said turbine, characterized in that it consists in defining an angular distribution pattern of the elements of the stator for a predetermined angular sector, the distribution pattern being defined to avoid radial alignment between inter-sector areas stator elements defined between two adjacent sectors the same stator element, and to repeat the distribution pattern over any the circumference of the stator.
  • the angular distribution pattern is repeated from symmetrical way in rotation with respect to the angular sector predetermined.
  • the stator elements consist of a housing annular, of a plurality of sectorized spacers on which are fixed a plurality of ring sectors forming a circular surface continuous flow around turbine blades of a turbine rotor, and a plurality of angular sectors of air flow boxes intended to unload air on the housing to allow the control of the game in top of the rotor blades of the high-pressure turbine
  • the motive angular distribution of the stator elements is advantageously defined to avoid radial alignment between inter-spacing zones defined between two adjacent spacers and inter-sector areas housing defined between two adjacent housing sectors.
  • the method further consists in radially aligning each feed mouth with air with an inter-sector box area.
  • the predetermined angular sector corresponds to an angular sector of air circulation housing.
  • each angular sector of air circulation box is associated advantageously three spacers and an air supply mouth.
  • the invention also relates to a high-pressure turbine stator whose angular distribution of the sectored elements leads to low and repetitive thermal distortions.
  • the high-pressure turbine stator is characterized in that the stator elements are angularly distributed around the longitudinal axis of the high-pressure turbine so as to avoid radial alignment between inter-spacer zones defined between two adjacent spacers and inter-sector box areas defined between two housing sectors adjacent.
  • stator elements are distributed angularly around the longitudinal axis of the high-pressure turbine in in addition to radially align each air supply mouth with an inter-sector box area.
  • the stator comprises N angular sectors air flow boxes, 3N spacers, N power outlets in air and 6N ring sectors.
  • the stator 10 of a high-pressure turbine comprises a housing annular 12 disposed around a longitudinal axis X-X of the high-pressure turbine.
  • annular housing 12 On the inner surface of the annular housing 12 are mounted a plurality of sectorized spacers 14 and arranged circumferentially around the longitudinal axis X-X of the turbine.
  • sectored elements for the rest of the description, it is understood that the designated elements are present in the form of angular sectors which, when placed end to end, form an annular assembly.
  • Ring sectors 16 are fixed on the inner surface of the spacers 14.
  • the ring sectors 16 are arranged circumferentially around the longitudinal axis X-X of the turbine and form a continuous circular surface surrounding moving blades (no shown in the figures) of a rotor (not shown) of the turbine high pressure.
  • the inner surface of the ring sectors 16 partially defines the flow of gases from the combustion chamber (no represented) of the turbomachine and passing through the high-pressure turbine.
  • a game (not shown) is left between the inner surface of the ring sectors 16 and the top of the rotor blades of the rotor of the turbine to allow rotation of the latter.
  • a device is 18.
  • This device consists in particular of a tube air collector 20 disposed around the housing 12 and supplied with air by the least one supply line 22 (only one is shown on the figure 1).
  • the air collection tube 20 supplies an air with a plurality of angular sectors of air circulation boxes 24 which are fixed circumferentially on the casing 12 via rules of Fixing 26.
  • the supply of air circulation housing sectors 24 is carried out by means of waterproof V-clamps 28 connected to the collecting tube 20.
  • each housing sector 24 consists of three air circulation ramps spaced axially and substantially parallel to each other. Each of these ramps is pierced with a plurality of holes (not shown) that discharge air on the housing 14 to change the temperature.
  • a plurality of air supply vents 30 are disposed through the housing 12. These mouths 30 are intended for supplying air to a stage of a low-pressure distributor (not shown in the figures) of the turbomachine arranged downstream of the high-pressure turbine.
  • the invention provides a method of assembling these different stator elements of the turbine about its longitudinal axis X-X.
  • this method consists in defining an angular distribution pattern of the stator elements 10 for a predetermined angular sector ⁇ , and in repeating the pattern over the entire circumference of the stator.
  • the pattern of distribution of the elements of the stator 10 over a predetermined angular sector ⁇ is defined so as to avoid radial alignment between inter-sector areas of stator elements.
  • the inter-sector zones are defined as zones located between two adjacent sectors of the same element of the stator.
  • the predetermined angular sector ⁇ is advantageously chosen so as to correspond to an angular sector of housing 24.
  • FIG. 2 illustrates an example of application of the method according to the invention.
  • the predetermined angular sector ⁇ a has a sector of 60 °.
  • stator elements 10 are arranged so as to avoid radial alignment between inter-sector areas of stator elements. More particularly, the angular distribution is chosen so as to avoid radial alignment between the inter-spacing zones 14a defined between two adjacent struts 14 and the inter-sector areas 24a of housing defined between two housing sectors 24 adjacent.
  • Such a distribution of the spacers 14 with respect to the sectors housing 24 avoids radially aligning between areas of the 12 on which air is not discharged by the device of game control 18 (that is to say at the level of inter-sector zones 24a of housing) and inter-spacing zones 14a.
  • the distribution pattern thus defined on the angular sector ⁇ a is then repeated over the entire circumference of the stator 10.
  • the distribution pattern is repeated five times to cover the entire circumference of the stator.
  • the distribution pattern is repeated over the entire circumference of the stator symmetrically in rotation with respect to the predetermined angular sector ⁇ a .
  • the temperature distribution of the housing 12 is done so symmetrical around the entire circumference of the housing.
  • thermal distortions of the housing 12 are substantially repetitive, which facilitates control.
  • the angular distribution pattern of the stator elements 10 for the sector predetermined angle is also defined to align radially each air supply mouth 30 with an inter-sectoral area housing 24a.
  • This particular arrangement of mouths air supply 30 also contributes to improving the homogeneity of crankcase temperature 12.
  • the mouths 30 intended to to supply air a stage of a low-pressure distributor are each disposed between two housing sectors 24 adjacent.
  • FIG. 3 illustrates another example of application of the method according to the invention.
  • the selected angular sector ⁇ b has a sector of 90 °.
  • This angular sector ⁇ b corresponds to an angular sector of housing 24.
  • the elements of the stator 10 are arranged, on the one hand so as to avoid radial alignment between inter-sector areas of stator elements, and on the other hand so as to radially align each mouth of the stator. air supply 30 with an inter-sector housing area 24a.
  • FIG. 4 illustrates another example of application of the method according to the invention.
  • ⁇ c a sector of 30 ° corresponding to an angular sector of housing 24.
  • each angular sector of housing of air circulation 24 is associated three spacers 14 and a mouth 30.
  • the high-pressure turbine stator 10 comprises N angular sectors of air flow boxes 24, 3N spacers 14, N air supply vents 30, and 6N sectors of ring 16.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05290319A 2004-03-18 2005-02-14 Hochdruckturbinenstator einer Strömungsmaschine und deren Zusammenbauverfahren Expired - Lifetime EP1577501B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0402825A FR2867805A1 (fr) 2004-03-18 2004-03-18 Stator de turbine haute-pression de turbomachine et procede d'assemblage
FR0402825 2004-03-18

Publications (2)

Publication Number Publication Date
EP1577501A1 true EP1577501A1 (de) 2005-09-21
EP1577501B1 EP1577501B1 (de) 2006-11-29

Family

ID=34834195

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05290319A Expired - Lifetime EP1577501B1 (de) 2004-03-18 2005-02-14 Hochdruckturbinenstator einer Strömungsmaschine und deren Zusammenbauverfahren

Country Status (9)

Country Link
US (1) US7360987B2 (de)
EP (1) EP1577501B1 (de)
JP (1) JP4526420B2 (de)
CA (1) CA2500493C (de)
DE (1) DE602005000290T2 (de)
ES (1) ES2273318T3 (de)
FR (1) FR2867805A1 (de)
RU (1) RU2374459C2 (de)
UA (1) UA87968C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2182175A3 (de) * 2008-10-30 2013-10-09 General Electric Company Gehäusestruktur und Verfahren zur Verbesserung des thermischen Verhaltens der Turbine während transienter und stationärer Betriebsbedingungen

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009031009A1 (de) * 2009-06-29 2010-12-30 Osram Opto Semiconductors Gmbh Strahlungsemittierendes Bauelement
DE102015215144B4 (de) 2015-08-07 2017-11-09 MTU Aero Engines AG Vorrichtung und Verfahren zum Beeinflussen der Temperaturen in Innenringsegmenten einer Gasturbine
US10443616B2 (en) * 2016-03-16 2019-10-15 United Technologies Corporation Blade outer air seal with centrally mounted seal arc segments

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
EP0892153A1 (de) * 1997-07-18 1999-01-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt
EP0892152A1 (de) * 1997-07-18 1999-01-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt
EP1205637A1 (de) * 2000-11-09 2002-05-15 Snecma Moteurs Kühlungsvorrichtung für einen Statorring
EP1258599A2 (de) * 2001-03-23 2002-11-20 General Electric Company Montageverfahren und Vorrichtung zur Aufrechterhaltung des Schaufelspitzenspiels einer Rotoranordnung
US20040018084A1 (en) * 2002-05-10 2004-01-29 Halliwell Mark A. Gas turbine blade tip clearance control structure

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5100291A (en) * 1990-03-28 1992-03-31 General Electric Company Impingement manifold
US5281085A (en) * 1990-12-21 1994-01-25 General Electric Company Clearance control system for separately expanding or contracting individual portions of an annular shroud
US5205115A (en) * 1991-11-04 1993-04-27 General Electric Company Gas turbine engine case counterflow thermal control
US5219268A (en) * 1992-03-06 1993-06-15 General Electric Company Gas turbine engine case thermal control flange

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
EP0892153A1 (de) * 1997-07-18 1999-01-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt
EP0892152A1 (de) * 1997-07-18 1999-01-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt
EP1205637A1 (de) * 2000-11-09 2002-05-15 Snecma Moteurs Kühlungsvorrichtung für einen Statorring
EP1258599A2 (de) * 2001-03-23 2002-11-20 General Electric Company Montageverfahren und Vorrichtung zur Aufrechterhaltung des Schaufelspitzenspiels einer Rotoranordnung
US20040018084A1 (en) * 2002-05-10 2004-01-29 Halliwell Mark A. Gas turbine blade tip clearance control structure

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2182175A3 (de) * 2008-10-30 2013-10-09 General Electric Company Gehäusestruktur und Verfahren zur Verbesserung des thermischen Verhaltens der Turbine während transienter und stationärer Betriebsbedingungen

Also Published As

Publication number Publication date
DE602005000290D1 (de) 2007-01-11
US7360987B2 (en) 2008-04-22
US20050238477A1 (en) 2005-10-27
CA2500493A1 (fr) 2005-09-18
ES2273318T3 (es) 2007-05-01
FR2867805A1 (fr) 2005-09-23
UA87968C2 (ru) 2009-09-10
JP4526420B2 (ja) 2010-08-18
JP2005264935A (ja) 2005-09-29
EP1577501B1 (de) 2006-11-29
CA2500493C (fr) 2012-01-10
RU2005106888A (ru) 2006-08-20
RU2374459C2 (ru) 2009-11-27
DE602005000290T2 (de) 2007-06-21

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