EP1059420B1 - Gehäuse für einen Hochdruckkompressor - Google Patents

Gehäuse für einen Hochdruckkompressor Download PDF

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Publication number
EP1059420B1
EP1059420B1 EP00401609A EP00401609A EP1059420B1 EP 1059420 B1 EP1059420 B1 EP 1059420B1 EP 00401609 A EP00401609 A EP 00401609A EP 00401609 A EP00401609 A EP 00401609A EP 1059420 B1 EP1059420 B1 EP 1059420B1
Authority
EP
European Patent Office
Prior art keywords
shroud
rings
casing
sectors
ventilation
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
EP00401609A
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English (en)
French (fr)
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EP1059420A1 (de
Inventor
Pascal Gérard Gervais
Pascal Michel Daniel Lejeune
Carmen Miraucourt
Jacky Serge Naudet
Patrice Suet
Monique Andrée Thore
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 Moteurs SA
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Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1059420A1 publication Critical patent/EP1059420A1/de
Application granted granted Critical
Publication of EP1059420B1 publication Critical patent/EP1059420B1/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
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/545—Ducts

Definitions

  • the subject of this invention is a stator at heterogeneous structure that could be applied in particular to high pressure compressors of gas turbines.
  • the rotor and stator structure of gas turbines is often cooled or broken down by the air taken from the flow that runs through the machine.
  • the air taken for ventilation in downstream originates from a part of the machine where he has already been compressed, which made it much more heated as the air from the ventilation upstream.
  • the invention consists of a compressor stator provided with a upstream ventilation of cooling air and downstream ventilation of air warmer than at the upstream, upstream and downstream ventilation being defined with respect to the normal direction of circulation of the main air flow and comprising a ferrule delimiting a stream of gas flow, characterized in that it comprises a first portion ferrule, subject to upstream ventilation, continuous annular structure on a circumference and in a first material, and a second portion of ferrule, subject to downstream ventilation, with structure formed of angular sectors juxtaposed and in one second material having a coefficient of expansion larger than the first material.
  • the first and second materials may be chosen respectively from lower coefficient of expansion materials such as TA6V and titanium alloys INC0909, TiAl type intermetallic, having an average coefficient of linear expansion less than 10 ⁇ 10 -6 m per degree; and among materials with a larger coefficient of expansion, such as nickel-based alloys of the INC0718, RENE77 and derivative type, having an average coefficient of linear expansion close to 15 ⁇ 10 -6 m per degree.
  • lower coefficient of expansion materials such as TA6V and titanium alloys INC0909, TiAl type intermetallic, having an average coefficient of linear expansion less than 10 ⁇ 10 -6 m per degree
  • materials with a larger coefficient of expansion such as nickel-based alloys of the INC0718, RENE77 and derivative type, having an average coefficient of linear expansion close to 15 ⁇ 10 -6 m per degree.
  • Figure 1 is an overview of a high-pressure compressor a gas turbine
  • Figure 2 is an enlarged view the downstream portion of the stator of this compressor
  • the FIG. 2A a similar view of another embodiment possible of the invention
  • Figures 3 and 4 are two cuts of the upstream and downstream parts of the compressor
  • Figure 5 is an enlarged view of the upstream part of the compressor.
  • a stator 7 surrounds the rotor 1 and comprises, in internal lining of a carcass 8, a portion 9 to which the invention relates and which consists of a support casing 10 and a ferrule 11 supported by the housing 10, turned towards the rotor 1 and which serves to delimit a ring vein 12 of gas flow in which the moving blade stages 6 and blade stages stationary 13 flow rectification, which are attached to the shell 11 and alternate with the floors previously mentioned.
  • abradable 15 formed of a honeycomb structure or more generally of easy erosion, which is dug by ribs 16 opposite erected on the envelope 3 and which form with it a seal at labyrinth.
  • the tips of the moving blades 6 are free of any equipment and end up close of the ferrule 11.
  • the internal portion 9 of the stator 7 presents discontinuities, which are openings of air sampling from vein 12, noted by references 17, 18 and which give in rooms 19 and 20 established between the portion 9 and the carcass 8 and through which the air taken from the vein 12 to ventilate in particular the housing 10 and subject it to temperature and dilation thermal determined.
  • the inside of the rotor 1 is it also ventilated, firstly through a piercing 21 of the casing 3 located upstream of the rotor 1 and by which fresh air, at approximately the same temperature as the one who enters the room 19, is sucked, then by another bore 22 of the casing 3, substantially to the right of the second opening 18.
  • Sectors 23 and 23 'adjacent are united by flexible tongues 24 sealing, extending into grooves longitudinal edges of the sectors and joining by their ends 25, between circles of sectors 23 and 23 'consecutive; and by other tabs 26 flexible established in grooves purely or obliquely radial edges of sectors 23 and 23 ', and extending from the first tongues 24 to the housing 10.
  • This arrangement effectively prevents the gases, very hot there, from vein 12 to flee between sectors 23 and 23 'to reach the housing 10 and risk of damaging it.
  • the tabs 24 and 26 isolate empty volumes 27 (which can also be filled with insulation at the heat) that appear between each of the circles of sectors 23 and 23 'and associated rings 28 of the housing 10.
  • each of them comprises a rear lip 31 protruding towards inside and back, and that is enclosed between a lip 32 of one of the rings 28, located radially outward, and a lip 33 or 33 ' pointing forward and established either in front of sectors 23, that is to the front of ring 28 located on further downstream; and sectors 23 and 23 'include still an outer lip 34 at the front, which cooperates with lips 33 to enclose lips 31 and 32 directed to the rear.
  • Sectors 23 ' differ in that they only include one lip unique at the front, bearing the reference 35 and oriented towards the rear, and which is housed in a groove 36 of the ring 28 located furthest forward.
  • This mode assembly is simpler than a mode inspired by more traditional ring fastening designs of ferrule, illustrated in Figure 2A, where the lips 31 and 32 are united by separate seals 37 with a cross-section staple and where the ferrule elements comprise a rib 38 relatively high ending in a lip 39 forward facing and housed in a groove of the adjacent ring; however, it is possible to adopt this less favorable design if desired.
  • the 50 tenon nesting systems allow in all cases of linking sectors 23 and 23 'to rings 28 in the angular direction; many achievements are within the reach of the skilled person.
  • the mode of linking sectors 23 and 23 'to Rings 28 is quite flexible and absorbs deformations without receiving strong constraints.
  • the rings 28 are preferably continuous on the circumference for give a simpler structure and a better mechanical resistance.
  • a nickel-based alloy, type INCO718, high coefficient of expansion can be used for this downstream part of the compressor.
  • the housing 10 is at this place composed of rings 40, joined together by bolts 42 enclosing flanges 41 which the end, as well as the carcass 8, in the manner of rings 28; but these rings 40 still include protuberances 43 and 43 'radially on the inside, which open out on the 12th vein of airflow and are therefore exposed to its temperature. Two of these protuberances 43 are wide enough to extend in front of a stage of moving blades 6 respective.
  • the ferrule 11 is here formed at a time by the protuberances 43 and 43 'and by rings 44 support of the stationary vanes 13; the rings 44 finish at the front and back by lips 45 who enter grooves of the growths 43 and 43 '.
  • mechanical systems 46 with interlocking tenon join the rings 40 to the rings 44 concentric against mutual rotations.
  • the major difference with downstream design is that the rings 44 are continuous on a circumference while as the rings 40. It is estimated that, as heating up are less important upstream, and that the temperature differences between the housing 10 and the ferrule 11 are less important also it is more simple and more advantageous to have a structure similar for both, the risks of deformation and excessive stress being reduced.
  • the material used has a coefficient of dilation less than that used for build the downstream of the crankcase, because we observe that Slower dilations than these materials undergo regulate a little the evolution of the dilatation during transient phases and allow finally better control games at the end of the blade blades 6.
  • An alloy of the Inconel 909 type may be recommended or an intermetallic type TiAl.
  • the rotor 1 can be built in a material whose coefficient of expansion is close of that used for the stator rings 40 in look, for example a titanium alloy.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (8)

  1. Verdichter-Stator, der mit einer vorderen Belüftung (17, 19) mit Kühlungsluft und mit einer hinteren Belüftung (18, 20) mit wärmerer Luft als bei der vorderen Belüftung ausgestattet ist, wobei vordere und hintere bezogen auf die normale Zirkulationsrichtung des Hauptluftstroms definiert sind, und der einen Ring (11) umfasst, welcher eine Gasströmungsbahn (12) umgrenzt,
       dadurch gekennzeichnet,    dass er einen ersten Ringabschnitt aufweist, der der vorderen Belüftung (17) ausgesetzt ist, einen ringförmigen Aufbau (44) mit durchgehender Umfangslinie aufweist und aus einem ersten Werkstoff besteht, sowie einen zweiten Ringabschnitt aufweist, der der hinteren Belüftung ausgesetzt ist, einen Aufbau aufweist, der aus aneinandergrenzenden Winkelsegmenten (23) gebildet ist, und aus einem zweiten Werkstoff besteht, dessen Ausdehnungskoeffizient größer ist als der des ersten Werkstoffs.
  2. Stator nach Anspruch 1,
       dadurch gekennzeichnet,    dass der erste und der zweite Werkstoff aus einer Gruppe von Werkstoffen mit niedrigerem Ausdehnungskoeffizient wie z. B. TA6V und Titanlegierungen, INC0909, intermetallischen Werkstoffen des Typs TiAl, die einen durchschnittlichen linearen Ausdehnungskoeffizient von unter 10 x 10-6 m pro Grad haben, bzw. aus einer Gruppe von Werkstoffen mit höherem Ausdehnungskoeffizient wie z. B. Legierungen aufNickelbasis des Typs INC0718, RENE77 und Derivaten, die einen durchschnittlichen linearen Ausdehnungskoeffizient von an die 15 x 10-6 m pro Grad haben, gewählt werden.
  3. Stator nach einem der Ansprüche 1 oder 2,
       dadurch gekennzeichnet,    dass er ein Gehäuse (10) umfasst, an dem der Ring (11) sitzt, wobei das Gehäuse (10) eine Kammer (19), die zur vorderen Belüftung gehört, und eine Kammer (20), die zur hinteren Belüftung gehört, umgrenzt, und dass das Gehäuse als ein ringförmiger Aufbau (28, 40) mit durchgehender Umfangslinie vor den beiden Kammern geformt ist.
  4. Stator nach Anspruch 3,
       dadurch gekennzeichnet,    dass das Gehäuse (10) aus in Verlängerung angeordneten Ringen (28, 40) besteht, die ein durchgehendes Ganzes vor dem ersten Ringabschnitt und vor dem zweiten Ringabschnitt bilden.
  5. Stator nach Anspruch 4,
       dadurch gekennzeichnet,    dass die Ringe des Gehäuses vor dem zweiten Ringabschnitt jeweils mit ringförmigen Gesamtanordnungen von aneinandergrenzenden Segmenten (23, 23') des Rings verbunden sind, und die meisten Segmente (23) an einem Ende ein Paar von konzentrischen Lippen (33, 34) aufweisen, die eine Lippe (31) am entgegengesetzten Ende der Segmente (23, 23') einer Gesamtanordnung benachbarter Ringe festklemmen, sowie eine Lippe (32) eines Gehäuserings, der mit dieser Gesamtanordnung benachbarter Ringe verbunden ist.
  6. Stator nach Anspruch 3,
       dadurch gekennzeichnet,    dass die Ringe des Gehäuses vor dem ersten Ringabschnitt Ausstülpungen (43, 43') aufweisen, die sich zwischen den Ringen erstrecken und so die Strömungsbahn (12) abgrenzen, wobei die Ringe zwischen den Ausstülpungen verzahnt angeordnet sind.
  7. Stator nach einem der Ansprüche 1 bis 6,
       dadurch gekennzeichnet,    dass die Segmente (23, 23') durch biegsame Zungen (24, 26) verbunden sind.
  8. Stator nach einem der Ansprüche 1 bis 7,
       dadurch gekennzeichnet,    dass der erste und der zweite Ringabschnitt sich vor Abschnitten eines Rotors (1) befinden, die aus dem ersten Werkstoff bzw. aus dem zweiten Werkstoff hergestellt sind.
EP00401609A 1999-06-10 2000-06-08 Gehäuse für einen Hochdruckkompressor Expired - Lifetime EP1059420B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9907315A FR2794816B1 (fr) 1999-06-10 1999-06-10 Stator de compresseur a haute pression
FR9907315 1999-06-10

Publications (2)

Publication Number Publication Date
EP1059420A1 EP1059420A1 (de) 2000-12-13
EP1059420B1 true EP1059420B1 (de) 2004-12-08

Family

ID=9546602

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00401609A Expired - Lifetime EP1059420B1 (de) 1999-06-10 2000-06-08 Gehäuse für einen Hochdruckkompressor

Country Status (5)

Country Link
US (1) US6390771B1 (de)
EP (1) EP1059420B1 (de)
JP (1) JP4124552B2 (de)
DE (1) DE60016505T2 (de)
FR (1) FR2794816B1 (de)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1118806A1 (de) * 2000-01-20 2001-07-25 Siemens Aktiengesellschaft Thermisch belastbare Wand und Verfahren zur Abdichtung eines Spaltes in einer thermisch belasteten Wand
FR2866079B1 (fr) 2004-02-05 2006-03-17 Snecma Moteurs Diffuseur pour turboreacteur
DE102004016222A1 (de) * 2004-03-26 2005-10-06 Rolls-Royce Deutschland Ltd & Co Kg Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine
FR2887939B1 (fr) * 2005-06-29 2016-09-30 Soc Nat D'etude Et De Construction De Moteurs D'aviation Snecma Compresseur multi-etages de turbomachine
US7604455B2 (en) * 2006-08-15 2009-10-20 Siemens Energy, Inc. Rotor disc assembly with abrasive insert
US7704038B2 (en) * 2006-11-28 2010-04-27 General Electric Company Method and apparatus to facilitate reducing losses in turbine engines
FR2913051B1 (fr) 2007-02-28 2011-06-10 Snecma Etage de turbine dans une turbomachine
FR2925109B1 (fr) * 2007-12-14 2015-05-15 Snecma Module de turbomachine muni d'un dispositif d'amelioration des jeux radiaux
FR2925108B1 (fr) * 2007-12-14 2013-05-03 Snecma Module de turbomachine muni d'un dispositif d'amelioration des jeux radiaux
US20100260599A1 (en) * 2008-03-31 2010-10-14 Mitsubishi Heavy Industries, Ltd. Rotary machine
FR2935625B1 (fr) * 2008-09-05 2011-09-09 Snecma Procede de fabrication d'une piece thermamecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane
FR2935623B1 (fr) * 2008-09-05 2011-12-09 Snecma Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane
FR2935624B1 (fr) * 2008-09-05 2011-06-10 Snecma Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane
US8613593B2 (en) * 2008-12-30 2013-12-24 Rolls-Royce North American Technologies Inc. Engine case system for a gas turbine engine
JP4856257B2 (ja) * 2010-03-24 2012-01-18 川崎重工業株式会社 タービンロータのシール構造
US8714908B2 (en) * 2010-11-05 2014-05-06 General Electric Company Shroud leakage cover
US9091172B2 (en) 2010-12-28 2015-07-28 Rolls-Royce Corporation Rotor with cooling passage
US9115600B2 (en) * 2011-08-30 2015-08-25 Siemens Energy, Inc. Insulated wall section
US9234463B2 (en) * 2012-04-24 2016-01-12 United Technologies Corporation Thermal management system for a gas turbine engine
US20140286766A1 (en) * 2012-09-11 2014-09-25 General Electric Company Compressor Casing Assembly Providing Access To Compressor Blade Sealing Assembly
US10539153B2 (en) * 2017-03-14 2020-01-21 General Electric Company Clipped heat shield assembly
US10767485B2 (en) * 2018-01-08 2020-09-08 Raytheon Technologies Corporation Radial cooling system for gas turbine engine compressors
US20200072070A1 (en) * 2018-09-05 2020-03-05 United Technologies Corporation Unified boas support and vane platform
FR3086323B1 (fr) 2018-09-24 2020-12-11 Safran Aircraft Engines Carter interne de turmomachine a isolation thermique amelioree
US11174742B2 (en) 2019-07-19 2021-11-16 Rolls-Royce Plc Turbine section of a gas turbine engine with ceramic matrix composite vanes

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1285255B (de) * 1964-10-28 1968-12-12 Bergmann Borsig Veb Waermebeweglich aufgehaengte Leitgittersegmente von Axialgasturbinen
BE792224A (fr) * 1971-12-01 1973-03-30 Penny Robert N Element composite long ayant un coefficient de dilatation lineaire effectif predetermine
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines
DE3315914A1 (de) * 1983-05-02 1984-11-08 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Gasturbinentriebwerk mit einrichtungen zur schaufelspaltminimierung
FR2604750B1 (fr) * 1986-10-01 1988-12-02 Snecma Turbomachine munie d'un dispositif de commande automatique des debits de ventilation de turbine
US5127794A (en) * 1990-09-12 1992-07-07 United Technologies Corporation Compressor case with controlled thermal environment
US5160241A (en) * 1991-09-09 1992-11-03 General Electric Company Multi-port air channeling assembly
FR2685936A1 (fr) * 1992-01-08 1993-07-09 Snecma Dispositif de controle des jeux d'un carter de compresseur de turbomachine.
US5351478A (en) * 1992-05-29 1994-10-04 General Electric Company Compressor casing assembly
FR2695164B1 (fr) * 1992-08-26 1994-11-04 Snecma Turbomachine munie d'un dispositif empêchant une circulation longitudinale de gaz autour des étages d'aubes de redressement.
US5653581A (en) * 1994-11-29 1997-08-05 United Technologies Corporation Case-tied joint for compressor stators
US5553999A (en) * 1995-06-06 1996-09-10 General Electric Company Sealable turbine shroud hanger
US6109868A (en) * 1998-12-07 2000-08-29 General Electric Company Reduced-length high flow interstage air extraction

Also Published As

Publication number Publication date
DE60016505T2 (de) 2005-11-03
JP4124552B2 (ja) 2008-07-23
DE60016505D1 (de) 2005-01-13
FR2794816B1 (fr) 2001-07-06
US6390771B1 (en) 2002-05-21
JP2001012396A (ja) 2001-01-16
EP1059420A1 (de) 2000-12-13
FR2794816A1 (fr) 2000-12-15

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