EP2024608B1 - Turbocompresseur en montage axial - Google Patents

Turbocompresseur en montage axial Download PDF

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Publication number
EP2024608B1
EP2024608B1 EP07785513.8A EP07785513A EP2024608B1 EP 2024608 B1 EP2024608 B1 EP 2024608B1 EP 07785513 A EP07785513 A EP 07785513A EP 2024608 B1 EP2024608 B1 EP 2024608B1
Authority
EP
European Patent Office
Prior art keywords
inner ring
turbocompressor
radially
set forth
compressor housing
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.)
Active
Application number
EP07785513.8A
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German (de)
English (en)
Other versions
EP2024608A1 (fr
Inventor
Frank Stiehler
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
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MTU Aero Engines AG
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Publication date
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Publication of EP2024608A1 publication Critical patent/EP2024608A1/fr
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Classifications

    • 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
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • 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
    • F05D2240/50—Bearings

Definitions

  • the invention relates to a turbocompressor in axial construction for a gas turbine, with a bladed stator and a bladed rotor, wherein the stator comprises a compressor housing longitudinally divided on diametrically opposite sides and at least one vane ring with adjustable guide vanes, according to the preamble of patent claim 1.
  • turbocompressors in axial design for gas turbines can be different in terms of housing design in principle, two types.
  • housing design in principle, two types.
  • transversely divided compressor housing which are composed of a plurality of concentric, axially juxtaposed housing rings. The housing rings are usually bolted together via radially outwardly facing flanges. Both types have specific advantages and disadvantages and can also be combined with multi-stage compressors with considerable axial extension.
  • a compressor which have at least one vane ring with adjustable guide vanes.
  • Such compressors can be better adapted to changing operating conditions, this with low number of stages, small size and low weight. It is customary to mount adjustable vanes radially outside the airfoil on or in the compressor housing, radially inside the airfoil, on or in a stator-associated inner ring.
  • the guide vanes starting from the blade on a - usually longer - outer pin and a - usually shorter - inner pin.
  • Each at the transition blade / pin is often arranged a plate-like plate, which has fluidic and mechanical functions.
  • the static inner ring has a complementary recess for each inner vane for the inner plate-like plate on the vane and a bearing for the inner pin.
  • the bearing is usually designed as a plain bearing with radially oriented longitudinal central axis.
  • the inner ring is transversely divided, wherein the parting line runs through the longitudinal center of the bearing. additionally the inner ring is split longitudinally on two diametrically opposite sides, so that it basically consists of four half-rings, two of which are axially adjacent to one another and are usually screwed together.
  • the radial and axial dimensions are usually larger, which has an effect on rotor sizing.
  • the local rotor diameter must be reduced, in addition may increase the rotor length. Both are unfavorable for the dynamic rotor behavior (rigidity, vibration behavior, weight, etc.)
  • parts of the gland can become loose and cause serious damage.
  • the parting line due to the transverse distribution affects the position and extent of the inlet lining, since the joint extends over the entire inner ring circumference. Due to its complexity, this construction is also expensive.
  • a turbo-machine stage with blades which have inner pivots which are mounted in inner pivot bearings of a connecting ring.
  • These inner pivot bearings are formed by bushings which have an external thread and are screwed into bores of the ring.
  • Bushings are taken in blind holes in the bearing ring and store the blade feet.
  • the blade feet are stored directly in blind holes of the bearing ring.
  • the object of the invention is in a turbocompressor of the type mentioned with adjustable vanes the latter in the area of the Inner Airseal and the rotor supporting and supporting inner ring in terms of its To optimize mechanical properties, its volume, its weight and ease of assembly, in order to ultimately improve the rotor dynamics.
  • the inner ring is also divided at least two points in its circumference, i. segmented. Each of its at least two segments is integral, i. monolithic.
  • the inner ring has in its segments for each of the adjustable guide vanes at least one radially insertable from the inside into an opening bearing bush. Starting from a state in which the adjustable vanes are already inserted into the disassembled compressor housing halves, and the inner bearing of the inner bearing projecting from the blades free inwardly, the segments can still without bushes radially from the inside with their openings for the bushings on a Segment end starting to be moved over the inner pin.
  • the bearing bushes can then be inserted radially from the inside into the segment located in the desired position, one or more bushings per bearing, i. per inner pin and opening, can be provided.
  • the monolithic segments are optimal in terms of strength, space and weight and do not require additional elements such as screws, nuts, pins, etc., which can come loose.
  • the bushings as wear parts can be replaced without having to dismantle the segments of the inner ring or the guide vanes.
  • a seal carrier with a squish or inlet lining should be releasably secured to the inner ring.
  • the seal carrier should, like the inner ring itself, segmented and radially positive fit, be held on the inner ring as a sheet metal profile.
  • FIG. 1 gives one. Part of a vane ring 1 with adjustable vanes 2 again.
  • Such vane rings are preferably used in turbocompressors in order to be able to change or adapt their fluidic properties.
  • the compressor housing including blade storage and adjustment mechanism is not shown.
  • each vane 2 has an aerodynamically effective airfoil 3, a radially inner and a radially outer, each plate-like plate 4, 5 and a radially inner inner pin 7 and a radially outer outer pin 8.
  • the latter is used for storage in or on the compressor housing and the connection with the adjusting mechanism.
  • the stator-associated inner ring 9 which as a rule comprises two segments 10 adjoining in the circumferential direction.
  • the inner ring 9 or its segment 10 is shown cut, so that the openings 11 can be seen for the bearing bushes.
  • the openings 11 may be made for example by drilling, lowering or turning. It is important that they allow a subsequent mounting of the bearing bushes radially from the inside.
  • the monolithic segments 10 can be biased for mounting to a defined smaller radius and radially from inside - in FIG. 1 be moved from the bottom over the inner pin 7.
  • the inner pin 7 and the openings 11 are largely only approximately aligned, this type of assembly due to the difference in diameter between the inner pin 7 and the openings 11 is possible.
  • the plates 4 dipping into the inner ring 9 have, for example, a conical or spherical taper 6.
  • FIG. 1 indicates that the segment 10 is not moved synchronously over all inner pins 7, but at one point on the circumference - here left - starting and then on the circumference - here to the right - progressing.
  • the radius of the segment 10 by gradual reduction of the bias continuously or by stepped reduction gradually increased to the relaxed state.
  • inner pin 7 and openings 11 should be positioned flush with each other in the desired position.
  • the described assembly process additionally facilitates can be by the housing-side mounting of the outer pin is completed only thereafter, by inserting the bushings, in analogy to the storage on the inner ring 9. Ggf. can be completely dispensed with a bias of the segment, ie a threading done without deformation.
  • FIG. 2 shows the state with located in desired position inner ring 9 and segment 10, wherein the bearing bushes 12 are inserted into the openings 11 and enclose the inner pin 7 with a defined, small bearing clearance.
  • FIG. 3 shows the subsequent assembly of the seal carrier 13.
  • This is like the inner ring 9 segmented and complementary to the segment 10 as a segment 14 in the form of a radially form-fitting sheet metal profile.
  • the segment 14 carries an inlet lining 15, for example in the form of a Honigwabendichtung.
  • the seal carrier 13 additionally prevents loosening and falling out of the bearing bushes 12.
  • the bearing bushes 12 wear, first the seal carrier 13, ie the segment 14, is dismantled. The bushings then read exchange without having to dismantle the inner ring 9.

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

Claims (9)

  1. Turbocompresseur en montage axial pour une turbine à gaz, en particulier pour un moteur d'aéronef, avec un stator aubagé et un rotor aubagé, dans lequel le stator comprend un carter de compresseur et au moins une couronne d'aubes directrices avec des aubes directrices réglables, dont les aubes directrices sont logées de manière pivotante radialement à l'extérieur de leur pale d'aube au niveau de et/ou dans le carter de compresseur ainsi que radialement à l'intérieur de leur pale d'aube au niveau de et/ou dans une bague intérieure appartenant au stator autour d'axes radiaux ou principalement radiaux, dans lequel la bague intérieure (9) est divisée à au moins deux endroits de sa périphérie, autrement dit, segmentée et présente pour chaque aube directrice (2) au moins une douille de palier (12) insérable radialement de l'intérieur dans une ouverture (11), caractérisé en ce que le carter de compresseur est divisé longitudinalement au niveau de côtés diamétralement opposés, et en ce qu'un porte-joint (13) est fixé de manière amovible au niveau de la bague intérieure (9) avec un revêtement d'effleurement ou de rodage (15) et bloque les douilles de palier (12) contre leur sortie des ouvertures (11).
  2. Turbocompresseur selon la revendication 1, caractérisé en ce que chaque segment (10) de la bague intérieure (9) est réalisée de manière déformable par cintrage - d'un premier rayon dans un état non chargé à un deuxième rayon défini plus petit.
  3. Turbocompresseur selon la revendication 1 ou 2, caractérisé en ce que la bague intérieure (9) est divisée en deux, autrement dit est divisée en deux segments (10) s'étendant respectivement sur un angle d'environ 180°.
  4. Turbocompresseur selon l'une quelconque des revendications 1 à 3, caractérisé en ce que chaque segment (10) de la bague intérieure (9) présente au moins un élément de blocage en tôle et/ou fil, lequel bloque au moins une douille de palier (12) contre une sortie d'une ouverture (11) radialement vers l'intérieur,
  5. Turbocompresseur selon la revendication 1, caractérisé en ce que le porte-joint (13) est divisé à au moins deux endroits de sa périphérie, autrement dit segmenté et maintenu par correspondance de forme radiale au niveau des segments (10) de la bague intérieure (9).
  6. Turbocompresseur selon la revendication 5, caractérisé en ce que le porte-joint (13) est divisé en deux, et en ce que chacun de ses deux segments (14) comporte un profil de tôle à correspondance de forme radiale, complémentaire à la bague intérieure (9), ainsi que par exemple une structure alvéolée comme revêtement d'effleurement ou de rodage (15).
  7. Turbocompresseur selon l'une quelconque des revendications 1 à 6, caractérisé en ce que le carter de compresseur présente pour chaque aube directrice (2) au moins une douille de palier insérable radialement de l'extérieur dans une ouverture.
  8. Turbocompresseur selon l'une quelconque des revendications 1 à 7, caractérisé en ce que les ouvertures (11) pour les douilles de palier (12) dans la bague intérieure (9) et/ou les ouvertures pour les douilles de palier dans le carter de compresseur sont réalisées sous forme d'alésages, d'enfoncements et/ou d'évidements au tour.
  9. Turbocompresseur selon l'une quelconque des revendications 1 à 8, caractérisé en ce que chaque aube directrice réglable (2) présente respectivement une plaque en forme d'assiette (4,5) au niveau de l'extrémité radialement intérieure et radialement extérieure de sa pale d'aube (3), dans lequel au moins la plaque radialement intérieure (4) présente un rétrécissement (6) conique ou bombé vers la douille de palier (12).
EP07785513.8A 2006-05-23 2007-05-18 Turbocompresseur en montage axial Active EP2024608B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006024085.5A DE102006024085B4 (de) 2006-05-23 2006-05-23 Turboverdichter in Axialbauweise
PCT/DE2007/000916 WO2007134585A1 (fr) 2006-05-23 2007-05-18 Turbocompresseur en montage axial

Publications (2)

Publication Number Publication Date
EP2024608A1 EP2024608A1 (fr) 2009-02-18
EP2024608B1 true EP2024608B1 (fr) 2017-03-29

Family

ID=38610840

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07785513.8A Active EP2024608B1 (fr) 2006-05-23 2007-05-18 Turbocompresseur en montage axial

Country Status (5)

Country Link
US (1) US8376692B2 (fr)
EP (1) EP2024608B1 (fr)
CA (1) CA2652272C (fr)
DE (1) DE102006024085B4 (fr)
WO (1) WO2007134585A1 (fr)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009004934B4 (de) 2009-01-16 2021-08-26 MTU Aero Engines AG Verfahren zur Montage eines integralen Innenrings eines Turboverdichterstators
DE102009004933A1 (de) 2009-01-16 2010-07-29 Mtu Aero Engines Gmbh Leitschaufel für einen Stator eines Turboverdichters
EP2520769A1 (fr) 2011-05-02 2012-11-07 MTU Aero Engines GmbH Anneau intérieur pour la formation d'une couronne d'aube directrice, couronne d'aube directrice et turbomachine
EP2636849B1 (fr) 2012-03-05 2017-11-01 MTU Aero Engines GmbH Compresseur
EP2696041B1 (fr) 2012-08-07 2020-01-22 MTU Aero Engines AG Assemblage de stator d'une turbine à gaz et procédé de montage
EP2725200B1 (fr) 2012-10-25 2018-06-06 MTU Aero Engines AG Stator et turbomachine
EP2725202A1 (fr) 2012-10-25 2014-04-30 MTU Aero Engines GmbH Agencement de support d'étanchéité d'anneau intérieur pour assemblage des aubes statoriques variables d'une turbomachine
EP2787177B1 (fr) 2013-04-02 2017-01-18 MTU Aero Engines AG Turbomachine axiale et procédé de montage
EP2806107B1 (fr) 2013-05-22 2017-08-09 MTU Aero Engines AG Bague intérieure séparée
DE102013217502A1 (de) 2013-09-03 2015-03-05 MTU Aero Engines AG Leitschaufelkranz für eine Gasturbine
FR3014152B1 (fr) * 2013-11-29 2015-12-25 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine et procede d'assemblage d'un tel dispositif
DE102014205986B4 (de) 2014-03-31 2021-03-18 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
DE102014223975A1 (de) * 2014-11-25 2016-05-25 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
EP3109520B1 (fr) 2015-06-24 2020-05-06 MTU Aero Engines GmbH Support d'étanchéité, stator et turbomachine
DE102015220371A1 (de) 2015-10-20 2017-04-20 MTU Aero Engines AG Innenringsystem, Leitschaufelkranz und Strömungsmaschine
BE1024524B1 (fr) * 2016-08-30 2018-03-26 Safran Aero Boosters S.A. Virole interne et aube orientable de compresseur de turbomachine axiale
US11879480B1 (en) 2023-04-07 2024-01-23 Rolls-Royce North American Technologies Inc. Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines

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Also Published As

Publication number Publication date
DE102006024085A1 (de) 2007-11-29
US8376692B2 (en) 2013-02-19
CA2652272A1 (fr) 2007-11-29
DE102006024085B4 (de) 2020-04-16
WO2007134585A1 (fr) 2007-11-29
EP2024608A1 (fr) 2009-02-18
US20100232952A1 (en) 2010-09-16
CA2652272C (fr) 2014-11-25

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