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EP2052133B1 - Ensemble destiné à optimiser le jeu fonctionnel pour des turbomachines - Google Patents

Ensemble destiné à optimiser le jeu fonctionnel pour des turbomachines Download PDF

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Publication number
EP2052133B1
EP2052133B1 EP07817418.2A EP07817418A EP2052133B1 EP 2052133 B1 EP2052133 B1 EP 2052133B1 EP 07817418 A EP07817418 A EP 07817418A EP 2052133 B1 EP2052133 B1 EP 2052133B1
Authority
EP
European Patent Office
Prior art keywords
inner ring
outer ring
arrangement according
ring
arrangement
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 - Fee Related
Application number
EP07817418.2A
Other languages
German (de)
English (en)
Other versions
EP2052133A2 (fr
Inventor
Alexander Böck
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
Publication of EP2052133A2 publication Critical patent/EP2052133A2/fr
Application granted granted Critical
Publication of EP2052133B1 publication Critical patent/EP2052133B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to an arrangement for optimizing the running gap for at least sections of axial-type turbomachinery by controlling or regulating the run-gap-relevant inner diameter of at least one stator blade surrounding a rotor blade ring.
  • the document GB 2 108 591 A relates to an arrangement for running gap optimization, in which over the circumference a plurality of interrupted, ie segmented, inner ring via lever mechanisms with actuators in the diameter is variable. At any deviation from the design diameter of the inner ring deviates from the ideal circular shape, ie polygonized.
  • the object of the invention is to propose an arrangement for running-gap optimization for at least sections of axial-type turbomachinery, which is fast-reacting as well as powerful and reliable.
  • the arrangement comprises a stator structure having an inner ring, an outer ring concentric with the latter and radially spaced and a plurality of webs integrally connecting the rings in a novel manner on. All webs are inclined relative to the radial direction by the same angle in the circumferential direction. Furthermore, the arrangement comprises an adjusting device for rotating the inner ring relative to the outer ring under elastic change of the running gap-relevant inner diameter.
  • it is a mechanical arrangement, which, starting from a zero adjustment "center position" depending on the direction of rotation allows both a compression and expansion of the inner ring under elastic, reversible deformation.
  • the reaction rate of the arrangement depends primarily on the speed of the selected adjustment. Since the invention is not dependent on thermally induced deformations, speed improvements can be achieved, for. B. by hydraulic, pneumatic or piezoelectric force generator. This also has the advantage that no or at least no relevant process gas flow has to be taken from the engine for the adjustment.
  • the arrangement 1 for running gap optimization comprises two essential functional units, firstly an integral, elastically deformable stator structure 3 and secondly an adjusting device with at least one lever 10, at least one actuator 16 and at least one sensor 18 for running splitter detection.
  • the stator structure 3 consists essentially of a circular, self-contained inner ring 5, of a concentric to this radially spaced circular outer ring 7 and a plurality of distributed over the circumference of the stator 3, the inner ring 5 and the outer ring 7 integral
  • the webs 8 are inclined at a defined angle ⁇ relative to the radial direction in the circumferential direction, so that a relative rotation of the inner ring 5 and the outer ring 7 a reversible compression or widening of the inner ring 5 and thus a change of the running clearance relevant inner diameter D entails.
  • the inner ring 5 has in relation to the outer ring 7 has a thinner cross-section, is thus much more flexible. This ensures that the desired change in diameter essentially results from the deformation of the inner ring 5.
  • the radially inner and radially outer ends of the webs 8 are integrally connected to the inner ring 5 and the outer ring 7 and designed as elastic solid joints. It can be seen that the webs 8 are contoured over their radial length, wherein the radially central region 9 is thickened relative to the ends and thus stiffened. Thus, the webs 8 behave over the majority of their radial length rigid body-like, which amplifies the change in diameter of the inner ring 5 at a given relative rotation.
  • the webs 8 may also be contoured with respect to their axial extent.
  • the outer ring 7 is rotationally held in a housing-like support 29, so that it forms the truly static element of the stator structure 3.
  • the possibly with - in FIG. 1 not shown - Rotor blade coming into contact inner ring 5 is provided radially inside with a friction-tolerant Anstreifbelag 17, the inside of the running gap-relevant inner diameter D predetermines.
  • the Anstreifbelag 17 follows the elastic deformation (compression, expansion) of the inner ring. 5
  • FIG. 1 still essential elements of the adjustment.
  • the relative rotation causing force transmission between the inner ring 5 and the outer ring 7 takes place mechanically.
  • a pivoting movements about an axis parallel to the axis of rotation of the turbomachine axis permitting storage 13 for a lever 10 is disposed on the outer ring 7 at least one point of its circumference.
  • the inner ring 5 is a corresponding recess, which together with a nose-like end of the lever 10 is a positive, play-free and low-friction Joint 15 forms.
  • the connecting line from the hinge 15 to the bearing 13 (center to center) extends at an angle ⁇ to the radial direction.
  • the adjusting kinematics including the angle ⁇ , are designed so that the local run-gap-relevant deformation of the inner ring 5 corresponds optimally to the deformation in the region of a web 8.
  • the angle ⁇ is generally different from the angle ⁇ .
  • angles ⁇ and ⁇ are here - arbitrarily - set in such a way that the longitudinal center line of a web 8 and the connecting line from the bearing 13 to the joint 15 (center to center) are each strung with the running gap relevant inside diameter D, respectively a connecting line of the Rotary axis of the turbomachine to the intersection S1, S2 is placed, and then the acute angle between the respective connecting line "rotation axis intersection” and the longitudinal center line "web” and the connecting line "bearing joint” are determined.
  • the angles are comparable only if the relevant intersection points S1, S2 lie on the same diameter, but which does not necessarily have to be the inner diameter D.
  • the lever 10 is angled to save space, with its long lever arm 12 is adapted to the circular cylindrical outer contour of the outer ring 7 and its support 29 and still extends within the housing 27 of the turbomachine.
  • the passage of the lever 10 through the outer ring 7 in the region of the bearing 13 is provided with a lip-like or seal 14, whereby the interior of the stator 3 is separated from the radially outer environment, unless there is a connection over at least one Front side of the stator structure 3.
  • an actuator 16 engages, which is largely arranged on the outside of the housing 27 of the turbomachine.
  • the actuator 16 is preferably designed as a double-acting, ie pressure and tensile forces generating, power cylinder whose power supply can be pneumatic, hydraulic or electrical / electronic. Due to the arrangement on the long lever arm 12, the Aktuator element and thus also its weight, etc. are reduced. Only the required Aktuatorhub thereby increases. In FIG. 1 Bottom right another gap without bridge 8 with a bearing and a yoke for another lever 10 (not shown) recognizable. With even distribution over the circumference so here four actuator / lever kinematics would be provided. Theoretically, a kinematics for the stator structure would suffice. With a view to the most uniform possible deformation of the inner ring 5 and on a redundant system you will probably install two or more kinematics.
  • FIG. 2 shows as a concrete application example a multi-stage compressor 26 in axial construction with two arrangements 1, 2 according to the invention for Laufspaltoptimtechnik in partial longitudinal section. Above you can see the multi-part housing 27 of the compressor 26 with flange. Down in FIG. 2 the flow channel of the compressor with a plurality of rotor and vane rings and a part of the rotor 34 is shown. The - not reproduced - rotation axis would run horizontally below the representation. The flow through the compressor 26 is from left to right, see the white arrows.
  • the arrangements 1, 2 are in the radial planes of the blade rings 30, 31, wherein the axial distance is such that even a vane ring with vane ring segments 33 between the assemblies 1, 2 place fits.
  • a common carrier 29 for the two stator structures 3, 4 is present within the housing 27 and fastened to the housing 27 via a flange connection.
  • the lever 10, 11 passing through the carrier 29 and the two pedestals for the actuators not shown here can be seen on the outside, here above, on the housing 27.
  • the inner ring 5 of the left, upstream stator structure 3 is kinematically coupled on both sides with guide vane segments 32, 33.
  • the inner ring 6 of the right stator structure 4 is kinematically coupled on one side with the vane ring segments 33.
  • the assemblies 1, 2 affect not only the running gaps of the blade rings 30, 31, ie the outer airseal, but also the gaps between the rotor 34 and the vane ring segments 32, 33, ie the Inner Airseal. Due to the two-sided coupling with the inner rings 5 and 6, the vane ring segments 33 are optimally moved. The vane ring segments 32 coupled only on one side to the inner ring 5 are not moved to the same extent, but still advantageously.
  • FIG. 3 shows in the partial cross section the range of such a sensor 18 within an arrangement for running gap optimization.
  • the sensor 18 is fixed relative to the inner ring 5 immediately surrounding a blade ring.
  • a sleeve-like holder 20 is integrated into the inner ring 5, in which the sensor 18 is radially inserted from the outside against the stop and again pulled out.
  • the authoritative radially inner sensor end is approximately flush with the inner surface of the squealer pad 17.
  • the Anstreifbelag must have a "window", ie a breakthrough in the region of the sensor 18.
  • at least one web 8 may be omitted in order to make space for the sensor 18 together with the holder 20.
  • a passage 21 is provided with sufficient clearance in the circumferential direction to the sensor shaft.
  • a slidable on the outer diameter of the outer ring 7, sliding sealing ring 22 is arranged, which is loaded via a spring washer 23 radially from the outside.
  • a bellows 24 extends radially, which forms an elastic, open channel for a flexible connecting line 19 of the sensor 18. The bellows 24 is also used to hold the sensor 18 in its operating position by exerting a defined radial force.
  • the bellows 24 is in turn connected to a cover 25 which is attached to a flange 28 of the housing 27 releasably and sealed, preferably screwed.
  • the connection line 19 leads to electrical or electronic components, which are attributable to the control or regulation system of the gap optimization ultimately exporting, at least one actuator 16.

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  • 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 (13)

  1. Ensemble (1, 2) servant à optimiser le jeu fonctionnel pour des turbomachines présentant au moins par endroits une structure axiale, telles que des turbocompresseurs, des turbines à gaz et des turbines à vapeur, en particulier pour des compresseurs de turbines à gaz stationnaires, par commande ou, par extension, par réglage du diamètre intérieur (D), concernant le jeu fonctionnel, d'au moins une structure de stator (3, 4) entourant une couronne d'aubes directrices (30, 31), l'ensemble (1, 2) comprenant la structure de stator (3, 4), la structure de stator (3, 4) présentant une bague intérieure (5, 6) fermée de forme circulaire, une bague extérieure (7) de forme circulaire, concentrique et espacée radialement par rapport à la bague intérieure (5, 6), ainsi que plusieurs entretoises (8) reliant la bague intérieure (5, 6) à la bague extérieure (7), inclinées dans la direction périphérique selon un angle (α) défini par rapport à la direction radiale et réparties sur la périphérie de la structure de stator (3, 4),
    caractérisé en ce
    que les entretoises (8) relient intégralement la bague intérieure (5, 6) à la bague extérieure (7), et en ce que l'ensemble (1, 2) comprend un système d'ajustage servant à faire tourner la bague intérieure (5, 6) par rapport à la bague extérieure (7) en modifiant de manière élastique le diamètre intérieur (D) concernant le jeu fonctionnel, de la bague intérieure (5, 6).
  2. Ensemble selon la revendication 1,
    caractérisé en ce
    que le système d'ajustage comprend au moins un levier (10, 11) logé de manière à pouvoir pivoter au niveau de la bague extérieure (7) et relié par complémentarité de forme et de manière articulée à la bague intérieure (5, 6) et au moins un actionneur (16) déplaçant le levier (10, 11).
  3. Ensemble selon la revendication 2,
    caractérisé en ce
    que l'au moins un levier (10, 11) est coudé, est adapté, sur la majeure partie de sa longueur, au diamètre extérieur de la bague extérieure (7) et est étanchéifié dans la zone de son logement (13) au niveau de la bague extérieure (7).
  4. Ensemble selon la revendication 2 ou 3,
    caractérisé en ce
    que l'au moins un actionneur (16) est réalisé sous la forme d'un cylindre de force et vient en prise au niveau de l'extrémité du long bras de levier (12) du levier (10, 11) en dehors de la bague extérieure (7).
  5. Ensemble selon l'une quelconque des revendications 1 à 4,
    caractérisé en ce
    qu'au moins un capteur (18) détectant le jeu fonctionnel est fixé au niveau de la bague intérieure (5, 6).
  6. Ensemble selon la revendication 5,
    caractérisé en ce
    que la bague extérieure (7) présente au moins un passage étanchéifié (21) pour la ligne de raccordement (19) de l'au moins un capteur (18) ainsi que pour le montage et le démontage de l'au moins un capteur (18) en passant par la bague extérieure (7).
  7. Ensemble selon la revendication 5 ou 6,
    caractérisé en ce
    que l'au moins un capteur (18) est intégré dans un circuit de réglage pour actionner l'au moins un actionneur (16).
  8. Ensemble selon l'une quelconque des revendications 1 à 7,
    caractérisé en ce
    que la bague intérieure (5, 6) est plus mince dans la section transversale et donc est réalisée de manière à pouvoir être plus facilement déformée que la bague extérieure (7).
  9. Ensemble selon l'une quelconque des revendications 1 à 8,
    caractérisé en ce que les entretoises (8) sont contourées et sont dans ce cadre plus épaisses dans la zone radialement médiane (9) entre la bague intérieure (5, 6) et la bague extérieure (7).
  10. Ensemble selon l'une quelconque des revendications 2 à 9,
    caractérisé en ce
    que l'inclinaison de l'au moins un levier (10, 11) entre son logement (13) au niveau de la bague extérieure (7) et sa liaison avec la bague intérieure (5, 6) selon un angle (ß) défini par rapport à la direction radiale est choisie par l'intermédiaire du déplacement d'ajustage pour une rondeur optimale de la bague intérieure (5, 6) et est différente de l'inclinaison des entretoises (α) par rapport à la direction radiale.
  11. Ensemble selon l'une quelconque des revendications 1 à 10,
    caractérisé en ce
    que la bague intérieure (5, 6) de l'au moins une structure de stator (3, 4) est couplée de manière cinématique sur au moins un côté à des segments de couronnes d'aubes directrices (32, 33) et influence ce faisant également le jeu fonctionnel de ces dernières par rapport au rotor.
  12. Ensemble selon l'une quelconque des revendications 1 à 11,
    caractérisé en ce
    que l'au moins une structure de stator (3, 4) est configurée pour réduire le diamètre intérieur (D) concernant le jeu fonctionnel d'environ - 0,2 % en écrasant la bague intérieure (5, 6) et pour agrandir le diamètre intérieur (D) concernant le jeu fonctionnel d'environ + 0,2 % en élargissant la bague intérieure (5, 6).
  13. Ensemble selon l'une quelconque des revendications 1 à 12,
    caractérisé en ce
    que les entretoises (8) au niveau de la bague extérieure (7) présentent, dans la direction axiale, une profondeur plus grande que sur la bague intérieure (5, 6) et se rétrécissent de manière conique en partant de la bague extérieure (7) vers la bague intérieure (5, 6).
EP07817418.2A 2006-08-17 2007-08-08 Ensemble destiné à optimiser le jeu fonctionnel pour des turbomachines Expired - Fee Related EP2052133B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006038753A DE102006038753A1 (de) 2006-08-17 2006-08-17 Anordnung zur Laufspaltoptimierung für Turbomaschinen
PCT/DE2007/001416 WO2008019657A2 (fr) 2006-08-17 2007-08-08 Ensemble destiné à optimiser le jeu fonctionnel pour des turbomachines

Publications (2)

Publication Number Publication Date
EP2052133A2 EP2052133A2 (fr) 2009-04-29
EP2052133B1 true EP2052133B1 (fr) 2014-01-15

Family

ID=39044234

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07817418.2A Expired - Fee Related EP2052133B1 (fr) 2006-08-17 2007-08-08 Ensemble destiné à optimiser le jeu fonctionnel pour des turbomachines

Country Status (5)

Country Link
US (1) US8608427B2 (fr)
EP (1) EP2052133B1 (fr)
CA (1) CA2660368A1 (fr)
DE (1) DE102006038753A1 (fr)
WO (1) WO2008019657A2 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009006029A1 (de) * 2009-01-24 2010-07-29 Mtu Aero Engines Gmbh Turbomaschine
US9228447B2 (en) * 2012-02-14 2016-01-05 United Technologies Corporation Adjustable blade outer air seal apparatus
US9683453B2 (en) * 2013-09-11 2017-06-20 General Electric Company Turbine casing clearance management system
US9695705B2 (en) 2014-10-29 2017-07-04 General Electric Company Systems and methods for controlling rotor to stator clearances in a steam turbine
US10458429B2 (en) 2016-05-26 2019-10-29 Rolls-Royce Corporation Impeller shroud with slidable coupling for clearance control in a centrifugal compressor
US10851712B2 (en) 2017-06-27 2020-12-01 General Electric Company Clearance control device
IT201900005266A1 (it) * 2019-04-05 2020-10-05 Nuovo Pignone Tecnologie Srl Turbina a vapore con pale statoriche girevoli
CN110725722B (zh) * 2019-08-27 2022-04-19 中国科学院工程热物理研究所 一种适用于叶轮机械的动叶叶顶间隙动态连续可调结构
CN113107615B (zh) * 2021-04-08 2022-08-26 沈阳航空航天大学 基于偏心阻尼作用的主动间隙控制篦齿密封结构
US12006829B1 (en) 2023-02-16 2024-06-11 General Electric Company Seal member support system for a gas turbine engine
US12116896B1 (en) 2023-03-24 2024-10-15 General Electric Company Seal support assembly for a turbine engine

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US3227418A (en) * 1963-11-04 1966-01-04 Gen Electric Variable clearance seal
DE2922835C2 (de) * 1979-06-06 1985-06-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Umfangsspaltdichtung an Axialströmungsmaschinen
GB2108591A (en) * 1981-11-03 1983-05-18 Rolls Royce Casing of a gas turbine engine rotor
DE3509192A1 (de) * 1985-03-14 1986-09-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Stroemungsmaschine mit mitteln zur kontrolle des radialspaltes
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US6454529B1 (en) 2001-03-23 2002-09-24 General Electric Company Methods and apparatus for maintaining rotor assembly tip clearances
DE10233881B4 (de) * 2002-07-25 2010-02-18 Rolls-Royce Deutschland Ltd & Co Kg Durch thermische Effekte radial veränderbares Ringelement
US7686569B2 (en) * 2006-12-04 2010-03-30 Siemens Energy, Inc. Blade clearance system for a turbine engine

Also Published As

Publication number Publication date
EP2052133A2 (fr) 2009-04-29
US8608427B2 (en) 2013-12-17
WO2008019657A2 (fr) 2008-02-21
CA2660368A1 (fr) 2008-02-21
DE102006038753A1 (de) 2008-03-13
WO2008019657A3 (fr) 2008-04-17
US20100232942A1 (en) 2010-09-16

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