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EP0967364B1 - Statorring für die Hochdruckturbine einer Turbomachine - Google Patents

Statorring für die Hochdruckturbine einer Turbomachine Download PDF

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Publication number
EP0967364B1
EP0967364B1 EP99401567A EP99401567A EP0967364B1 EP 0967364 B1 EP0967364 B1 EP 0967364B1 EP 99401567 A EP99401567 A EP 99401567A EP 99401567 A EP99401567 A EP 99401567A EP 0967364 B1 EP0967364 B1 EP 0967364B1
Authority
EP
European Patent Office
Prior art keywords
downstream
sectors
ring
spacer
foot
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
EP99401567A
Other languages
English (en)
French (fr)
Other versions
EP0967364A1 (de
Inventor
Alain Marc Lucien Broman
Léopold Jean Marie De Verduzan
Daniel Jean Marey
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
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 Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP0967364A1 publication Critical patent/EP0967364A1/de
Application granted granted Critical
Publication of EP0967364B1 publication Critical patent/EP0967364B1/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
    • 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
    • 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
    • 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the invention relates to the stator of the high pressure turbine of a turbomachine. It concerns, in particular, the parts of the stator which face the blades of the rotor, especially at the level of the first stage of the high pressure turbine.
  • the turbine casing 1 of the stator comprises parts 2 which face the blades 3 of the rotor 4, at the level of the inlet of the high pressure turbine, downstream of the combustion chamber 5.
  • These annular parts 2 of the turbine casing 1 therefore define a game with the top of the blades 3 of the stator 4, thereby conditioning the efficiency of the turbine engine.
  • these annular parts 2 are supplied with gas to temperatures that allow them to be dilated or contracted to reduce to a minimum value the clearance between these blades 3 and these annular parts 2, in order to increase the performance of the turbine engine.
  • the gas is usually withdrawn from another part of the turbomachine, depending on the temperature of the gases or the speed of the rotor.
  • the annular portion of the stator is composed of an inner crown that can be continuous but which is generally formed of a series of ring sectors 6 facing the end of the blades 3 of the rotor. They are worn by a sector spacer 10 attached to the turbine casing 1 and in which is formed least one cavity 11 in contact with the ring sectors 6, with a view to proceed with the thermal adjustment of these.
  • the fixing of these sectors of ring 6 to the spacer sectors 10 of the stator is by via clips 7 placed on respective downstream flanges 8 and 9 ring sectors 6 and spacer sectors 10, these two flanges 8 and 9 being joined.
  • fixing is done by an upstream collar 12 of each spacer sector 10 engaging in a groove 13 upstream of each of the ring sectors 6.
  • such a high pressure turbine turbomachine may comprise several stages of this type, and consequently several stages of ring sectors and spacer parts.
  • the Ring sectors 6 are located at the inlet of the high pressure turbine, in an area where the temperature can reach 1500 ° C. In therefore, they must be cooled.
  • the tightness between these ring sectors 6 and the spacer sectors 10 must be realized at better, in order to avoid the loss of a part of the air flow of the turbomachine.
  • the securing clips 7 help to partially ensure this seal.
  • air leaks take place and the air flow taken from the engine to cool the ring sectors 6 can be relatively consistent.
  • the object of the invention is to remedy this drawback by minimizing these leaks and the airflow taken from the engine, for the purpose to keep the performance of the turbomachine good value.
  • US-A-5 593 276 shows a sectorized ring of turbine stator, the side upstream of each sector being fixed by an axial upstream collar inserting in a groove of the upstream leg of a support ring fixed on the housing of turbine. Downstream side, a collar downstream of the ring sectors has an edge radial curved downstream cooperating with a downstream leg of the support ring and held by a C-clamp.
  • downstream foot of the spacer and the downstream flange of the ring sectors are curved thin and joined together by radial joining surfaces which respectively extend the surface external of the downstream foot of the spacer sectors and the inner surface of the collar for fixing the downstream leg of the ring sectors, this makes it possible to form a radial flange at 90 ° constituting an additional element operational vis-à-vis the sealing.
  • the fixing clamps being placed around the downstream part of the assembly thus formed by the foot and downstream flange curved of spacer sectors and sectors ring.
  • the ring areas comprise an upstream collar intended to be engaged in a corresponding groove of a foot upstream of the spacer sectors, in the purpose of achieving the fixing, on the upstream side, of the ring sectors on the spacer sectors.
  • FIG 3 shows in detail the first embodiment of the high pressure turbine stator ring according to the invention.
  • the end of a blade 3 of the rotor which rotates of the inner surface 21 of a ring sector 20 fixed to the stator by through the turbine casing 1.
  • This fixation is carried out by intermediate spacer sectors 30 themselves each attached to the turbine casing 1.
  • the spacer sectors 30 therefore constitute a crown fixed fixing.
  • Figure 4 allows to see this crown of spacer sectors 30 attached to the turbine casing 1.
  • the number of sectors is relatively important.
  • This crown of sectors spacer 30 makes it possible to constitute an annular channel allowing a gas withdrawn from another part of the turbomachine to be in contact with ring sectors 20 and affect their temperature.
  • this gas flow can penetrate the spacer sectors via of a first orifice 33 to enter a first cavity 31 and in a second cavity 32 by a second orifice 34.
  • the flow of gas taken upstream in the turbomachine can be in direct contact with ring sectors 20 and affect their temperature.
  • This spacer sector 30 is attached to the turbine casing 1 through an upstream mounting head 37M fitting into annular grooves 15M and a downstream fixing head 37V inserting in a downstream groove 15V of the turbine casing 1.
  • each ring sector 20 is fixed relative to the spacer sector 30 via a 23M upstream collar fitting into an annular groove 38 of the foot upstream 35M of each spacer sector 30.
  • Fixing the downstream side of the ring sectors is done by a downstream flange 23V of each ring sector 20 which is plated, by its downstream internal surface 24V against the downstream outer surface 37V downstream leg 35V of each spacer sector 30.
  • a characteristic important of the fixation according to the invention is that these two surfaces pressed against each other are curved upwards, ie towards the outside of the axis of rotation of the turbomachine. In the embodiment described in Figure 3, these two surfaces are perpendicular this axis, that is to say that they constitute radial surfaces of junction. Maintaining in this position glued or plated one against the other of these two radial joining surfaces is realized by means of several clamps 40 placed on the entire circumference of all.
  • a first clamp leg 41 is housed in the hollow formed by the downstream outer surface 36V of each spacer sector 30, while a second clamp tab 42 presses against the 25V downstream external surface of the downstream flange 23V.
  • the downstream internal surface 24V of each ring sector 20 is extended by curved way perpendicularly to the axis of the turbomachine. He is leaving likewise for the downstream external surface 37V of the downstream leg 35V, the end the downstream foot of each spacer sector 30 and the downstream flange 23V each ring sector 20 being thin.
  • a second embodiment of the fixing 75V downstream foot of spacer sectors 70 and sectors ring 20 can be made with a second kind of clamp of fixing 60.
  • fixation 60 may have a first gripper leg 61 to take support on the downstream external surface 76V of the spacer sector 70.
  • its second clamping lug 62 comes to bear against the downstream outer surface 55V of the downstream flange 53V, at a location where this Downstream external surface 55V is coaxial with the axis of the turbomachine.
  • the clamp 60 comes to bear by its second clamp 62 on the downstream flange 53V, before its curved portion.
  • a recess 63 inside the clamp 60, placed opposite the part curved downstream flange 53V, allows a better tightening of the fixing clamp 60 on the assembly and, in particular, on the downstream leg of each ring sector 20.
  • the main advantage of the invention is to obtain the better sealing possible at this high turbine ring pressure, in order to reduce the air flow taken from the turbomachine for cooling the ring sectors and thus keeping a good value of the performance of this turbomachine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gasket Seals (AREA)

Claims (4)

  1. Statorring für die Hochdruckturbine einer Turbomaschine, wobei der Stator ein Turbinengehäuse (1) umfaßt, das pro Stufe aufweist:
    kreisbogenförmige Stegsektoren (30, 70), die zusammen einen über 360° geschlossenen und an der Innenwand des Turbinengehäuses (1) befestigten Ringsteg bilden und einen stromaufwärtigen Fuß (35M) und einen stromabwärtigen Fuß (35V, 75V) besitzen, und
    kreisbogenförmige Ringsektoren (20), die zusammen einen über 360° geschlossenen Ring bilden, so daß sie mit ihrer Innenfläche (21) an die von den Enden der Schaufeln (3) der Räder der Turbine bestimmte Hüllkurve angepaßt sind, wobei die Ringsektoren (20) an dem stromabwärtigen Fuß (35V, 75V) der Stegsektoren (30, 70) durch einen stromabwärtigen Kragen (23V, 53V) befestigt sind, der an dem stromabwärtigen Fuß der Stegsektoren (30, 70) mit Hilfe von Befestigungsklammern (40, 60) befestigt sind, die diese beiden Sektorentypen (20, 30, 70) mit ihrem stromabwärtigen Fuß und ihrem stromabwärtigen Kragen (23V, 53V) gegeneinander verspannen,
       wobei der stromabwärtige Fuß (35V, 75V) der Stegsektoren (30, 70) und die stromabwärtigen Kragen (23V, 53V) der Ringsektoren (20) abgewinkelt und durch radiale Verbindungsflächen miteinander verbunden sind, die die Außenfläche (37V) des stromabwärtigen Fußes (35V, 75V) der Stegsektoren (30, 70) und die Innenfläche des stromabwärtigen Kragens (23V, 53V) der Ringsektoren (20) verlängern,
       wobei die abgewinkelten radialen Ende des stromabwärtigen Fußes jedes Stegsektors (30, 70) und der stromabwärtige Kragen (23V, 53V) jedes Ringsektors (20) geringe Dicke haben und so eine radiale 90°-Randleiste bilden, die ein zusätzliches Funktionselement in Bezug auf die Dichtigkeit darstellt, wobei die Befestigungsklammern (40, 60) um den stromabwärtigen Teil der in dieser Weise von den abgewinkelten stromabwärtigen Fuß (35, 75V) und den abgewinkelten stromabwärtigen Kragen (23V, 53V) der Stegsektoren (30, 70) und der Ringsektoren (20, 50) gebildeten Baugruppe herum angeordnet sind.
  2. Statorring nach Anspruch 1, bei dem der stromabwärtige Kragen (23M) der Ringsektoren (20) für den Eingriff in eine entsprechende Nut (38) eines stromabwärtigen Fußes (35M) der Stegsektoren (30) bestimmt ist.
  3. Statorring nach Anspruch 1, dadurch gekennzeichnet, daß die Klemmflächen der Befestigungsklammern (40) sich an einem abgewinkelten Teil der Außenfläche (36V) des stromabwärtigen Fußes (35V) der Stegsektoren (30) und an dem abgewinkelten Teil der Außenfläche (25V) der Ringsektoren (20) abstützen.
  4. Statorring nach Anspruch 1, dadurch gekennzeichnet, daß die Klemmflächen der Befestigungsklammern (60) sich an dem abgewinkelten Teil der Außenfläche (76V) des stromabwärtigen Fußes (75V) der Stegsektoren (70) und an dem abgewinkelten Teil und dem nicht abgewinkelten Teil der Außenfläche (55V) stromabwärtigen Kragens (53V) der Ringsektoren (50) abstützen.
EP99401567A 1998-06-25 1999-06-24 Statorring für die Hochdruckturbine einer Turbomachine Expired - Lifetime EP0967364B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9808053 1998-06-25
FR9808053A FR2780443B1 (fr) 1998-06-25 1998-06-25 Anneau de stator de turbine haute pression d'une turbomachine

Publications (2)

Publication Number Publication Date
EP0967364A1 EP0967364A1 (de) 1999-12-29
EP0967364B1 true EP0967364B1 (de) 2004-10-06

Family

ID=9527846

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99401567A Expired - Lifetime EP0967364B1 (de) 1998-06-25 1999-06-24 Statorring für die Hochdruckturbine einer Turbomachine

Country Status (6)

Country Link
US (1) US6200091B1 (de)
EP (1) EP0967364B1 (de)
JP (1) JP3912935B2 (de)
CA (1) CA2276238C (de)
DE (1) DE69920812T2 (de)
FR (1) FR2780443B1 (de)

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EP2846001B1 (de) * 2013-09-06 2023-01-11 MTU Aero Engines AG Montage- und Demontageverfahren eines Gasturbinenrotors und zugehörige Werkzeug
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US10119403B2 (en) 2014-02-13 2018-11-06 United Technologies Corporation Mistuned concentric airfoil assembly and method of mistuning same
US20160047549A1 (en) * 2014-08-15 2016-02-18 Rolls-Royce Corporation Ceramic matrix composite components with inserts
US10215099B2 (en) * 2015-02-06 2019-02-26 United Technologies Corporation System and method for limiting movement of a retainer ring of a gas turbine engine
US9932901B2 (en) 2015-05-11 2018-04-03 General Electric Company Shroud retention system with retention springs
US9828879B2 (en) * 2015-05-11 2017-11-28 General Electric Company Shroud retention system with keyed retention clips
FR3046410B1 (fr) * 2016-01-05 2017-12-29 Snecma Assemblage pour turbomachine d'aeronef a helices contrarotatives non carenees, comprenant un fourreau de passage de servitudes a encombrement reduit
US10753232B2 (en) * 2017-06-16 2020-08-25 General Electric Company Assemblies and methods for cooling flowpath support structure and flowpath components
FR3076578B1 (fr) * 2018-01-09 2020-01-31 Safran Aircraft Engines Ensemble d'anneau de turbine
US10934876B2 (en) * 2018-07-18 2021-03-02 Raytheon Technologies Corporation Blade outer air seal AFT hook retainer
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CN109252902B (zh) * 2018-09-14 2021-09-07 中国航发湖南动力机械研究所 轴向限位结构和涡轮发动机
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Also Published As

Publication number Publication date
US6200091B1 (en) 2001-03-13
FR2780443B1 (fr) 2000-08-04
JP2000045707A (ja) 2000-02-15
DE69920812D1 (de) 2004-11-11
FR2780443A1 (fr) 1999-12-31
EP0967364A1 (de) 1999-12-29
CA2276238C (en) 2008-10-14
DE69920812T2 (de) 2005-10-13
CA2276238A1 (en) 1999-12-25
JP3912935B2 (ja) 2007-05-09

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