EP2722485B1 - Anneau intérieur pour un stator avec aubes directrices réglables - Google Patents

Anneau intérieur pour un stator avec aubes directrices réglables Download PDF

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Publication number
EP2722485B1
EP2722485B1 EP12189450.5A EP12189450A EP2722485B1 EP 2722485 B1 EP2722485 B1 EP 2722485B1 EP 12189450 A EP12189450 A EP 12189450A EP 2722485 B1 EP2722485 B1 EP 2722485B1
Authority
EP
European Patent Office
Prior art keywords
inner ring
lateral surface
guide vanes
groove
vanes
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
EP12189450.5A
Other languages
German (de)
English (en)
Other versions
EP2722485A1 (fr
Inventor
Georg Zotz
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
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Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP12189450.5A priority Critical patent/EP2722485B1/fr
Publication of EP2722485A1 publication Critical patent/EP2722485A1/fr
Application granted granted Critical
Publication of EP2722485B1 publication Critical patent/EP2722485B1/fr
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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
    • 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
    • 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
    • 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
    • F05D2300/502—Thermal properties

Definitions

  • the present invention relates to an inner ring for a vane ring with adjustable guide vanes of a turbomachine, in particular a gas turbine, preferably a gas turbine engine, a vane ring and such a turbomachine with such an inner ring.
  • a turbomachine in particular a gas turbine, preferably a gas turbine engine, a vane ring and such a turbomachine with such an inner ring.
  • Such inner rings can, in particular in transient operation, be exposed to partially changing and / or high temperature gradients, in particular by the working vane flowing through the vane ring and / or a sliding seal between the vane ring and the rotor rotating relative thereto.
  • temperature gradients temperature distributions can be formed in a cross-section, in particular a meridian section, of the guide vane ring, which influence its diameter and / or shape, in particular roundness - the inner ring can, so to speak, move thermally.
  • a seal between the vane ring and the rotor is adversely affected, in particular a gap between the vane ring and the rotor can be increased and / or an inlet can be increased.
  • An object of the present invention is to improve the performance of a turbomachine. This object is achieved by an inner ring for a vane ring with adjustable guide vanes of a turbomachine with the features of claim 1.
  • Claim 8 illustrates a vane ring with an inner ring according to the invention and claim 9 a turbomachine with such a vane ring
  • a turbomachine includes one or more compressor stages and / or one or more turbine stages.
  • One or more of these compressor and / or turbine stages each include a runner and a guide grid, one or more of these guide grilles having a variable nozzle vane ring according to one aspect of the present invention.
  • the invention is used in gas turbines, in particular in gas turbine engines, preferably in a low-pressure and / or high-pressure compressor. Accordingly, one aspect of the present disclosure relates to a low or high pressure compressor having an inner ring according to one aspect of the present invention.
  • a vane ring according to one aspect of the present invention comprises a plurality of guide vanes, which are adjustably, in particular rotatably, mounted on an inner ring according to the present invention.
  • the guide vanes can be supported radially on the inner ring.
  • the guide vanes may be partially arranged, in particular rotatably supported, in continuous or blind-hole-like recesses on a lateral surface of the inner ring facing the guide vanes, in which case separate bearing elements are arranged in the recesses could be.
  • a guide blade receptacles according to the present invention in particular continuous or blind hole-like recesses are referred to, in which guide vanes are rotatably mounted and / or radially supported.
  • An inner ring according to the present invention comprises a number of a plurality of vane seats and one or more grooves.
  • the grooves are arranged on a side facing away from the vanes lateral surface of the inner ring.
  • At least one groove is, as seen in the circumferential direction, arranged between two adjacent guide vanes or Leitschaufelfactn.
  • the groove is either material-free in order to locally reduce the cross-sectional area of the inner ring, or it is at least partially filled with a highly heat-conducting material.
  • a groove in the sense of the present invention is understood in particular to mean a local, preferably channel-like, radial recess in the lateral surface. Such grooves reduce the cross-sectional area of the inner ring locally. As a result, in one embodiment, a better temperature distribution, preferably an approximately or at least substantially constant temperature, can advantageously be represented in the remaining cross section. Additionally or alternatively, through such grooves in one embodiment, a heat conduction in the circumferential direction of the inner ring can be influenced, in particular limited and / or reduced.
  • a seal between the vane ring and the rotor can advantageously be improved, in particular a gap between the vane ring and the rotor and / or an inlet can be reduced and thus the operating behavior, in particular an efficiency, of a turbomachine can be improved.
  • An arrangement of one or more grooves between the guide blade receptacles can advantageously reduce the cross section at this point, at which point it would initially have a greater wall thickness compared with recesses for receiving the guide vanes.
  • one or more grooves arranged on the lateral surface of the inner ring facing away from the guide vanes extend, at least substantially, in the axial direction.
  • the grooves may be inclined in the circumferential and / or radial direction against the axial direction.
  • the grooves are straight or have a straight center line.
  • one or more grooves arranged on the lateral surface facing away from the guide vanes of the inner ring are open on one or both end faces or in the axial direction. Such unilaterally or bilaterally open grooves can be advantageously produced easily.
  • one or more arranged on the side facing away from the vanes lateral surface of the inner ring grooves are closed on one or both end faces or in the axial direction. As a result, a leakage of working fluid through the groove can advantageously be prevented or reduced.
  • a leakage of working fluid through the groove (s) can be prevented or reduced by, in one embodiment of the present invention, a seal carrier the groove (s), in particular frontally or in the axial direction seen, covering.
  • the seal carrier may rest against the inner ring, in particular at least in the edge region of open grooves on one or both end faces of the inner ring, in a development of the seal carrier, in particular the front side and / or radially from the inside, engage in the groove (s).
  • a arranged on the side facing away from the vanes lateral surface of the inner ring groove is free of material, in particular to reduce the cross section and so to improve the temperature distribution in the inner ring.
  • the groove is at least partially filled with a highly heat-conductive material, in particular to represent a better strength at improved temperature distribution nonetheless.
  • the inner ring is formed in one piece. In another embodiment, it has two or more segments. In one development, an abutting edge between circumferentially adjacent segments of the inner ring may be groove-free, in particular in order not to impress any cross-sectional weakening there. Likewise, a groove may be arranged on an abutting edge between circumferentially adjacent segments of the inner ring on the lateral surface facing away from the guide vanes, in particular in order to facilitate their manufacture.
  • FIG. 1 1 shows a meridian section of a part of a gas turbine engine compressor with a vane ring with an inner ring 9 according to an embodiment of the present invention, which is shown in FIG Fig. 2 is shown enlarged in a circumferentially offset by half a blade pitch meridian section.
  • the gas turbine engine compressor has in known manner a rotor 1 with blades 1.1, which in the axial direction (from left to right in Fig. 1 ) are arranged alternately with vanes 2.
  • the guide vanes 2 are mounted on the inner ring 9 in a manner known per se on the lateral surface 9.1 facing the guide vanes, which defines the annular space contour.
  • the guide vanes 2 can have axle journals which are rotatably mounted in recesses in the inner ring 9, as shown in FIG Fig. 3 is indicated. As can be seen there, the guide vanes 2 can have radially outer outer pins 8, with which they are mounted radially outward on the guide vane ring or housing and by means of which they can be adjusted.
  • a groove 9.3 arranged, which, in particular in the meridian section of Fig. 2 recognizable, essentially in the axial direction (from left to right in Fig. 2 ).
  • the grooves 9.3 have in a cross section perpendicular to the axial direction or plane of the drawing Fig. 2 one, at least substantially, U-shaped or V-shaped cross-section and are material-free according to an alternative of the invention.
  • the grooves 9.3 are, as in Fig. 2 recognizable, on both front sides (left, right in Fig. 2 ) open.
  • Fig. 3 shows a perspective view of a vane ring with an inner ring according to another embodiment of the present invention.
  • a seal carrier 13 which is also divided into segments 14 which abut one another in the circumferential direction and radially inwardly have an inlet lining 15.

Landscapes

  • 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 (9)

  1. Bague intérieure (9), destinée à une couronne d'aubes directrices pourvue d'aubes directrices réglables (2) d'une turbomachine, comprenant un certain nombre de logements d'aube directrice, au moins une rainure (9.3) ménagée sur une surface d'enveloppe (9.2), opposée aux aubes directrices, de la bague intérieure,
    caractérisée en ce que
    l'au moins une rainure est ménagée entre deux logements d'aube directrice, et en ce que, pendant le fonctionnement de la turbomachine, la rainure est soit exempte localement de matériau pour réduire la surface en coupe transversale de la bague intérieure (9) soit est remplie au moins partiellement d'un matériau fortement conducteur de chaleur.
  2. Bague intérieure selon la revendication 1, caractérisée en ce qu'au moins une rainure ménagée sur la surface d'enveloppe, opposée aux aubes directrices, de la bague intérieure s'étend, au moins sensiblement, dans la direction axiale.
  3. Bague intérieure selon l'une des revendications précédentes, caractérisée en ce qu'au moins une rainure ménagée sur la surface d'enveloppe, opposée aux aubes directrices, de la bague intérieure est ouverte ou fermée sur une face d'extrémité ou les deux faces d'extrémité.
  4. Bague intérieure selon l'une des revendications précédentes, caractérisée en ce qu'au moins une rainure ménagée sur la surface d'enveloppe, opposée aux aubes directrices, de la bague intérieure a, dans une vue en coupe transversale perpendiculaire à la direction axiale, une section transversale, au moins sensiblement, en forme de U ou en forme de V.
  5. Bague intérieure selon l'une des revendications précédentes, caractérisée en ce qu'une pluralité de rainures ménagées sur la surface d'enveloppe, opposée aux aubes directrices, de la bague intérieure sont ménagées de manière répartie, en particulier au moins sensiblement à équidistance, sur la circonférence de la bague intérieure.
  6. Bague intérieure selon la revendication précédente, caractérisée en ce qu'au moins une rainure est ménagée sur la surface d'enveloppe, opposée aux aubes directrices, de la bague intérieure à chaque fois entre deux logements d'aube directrice adjacents, deux paires de logements d'aube directrice adjacentes ou deux triplets de logements d'aube directrice adjacents.
  7. Bague intérieure selon l'une des revendications précédentes, caractérisée en ce que la bague intérieure est réalisée en une partie ou en plusieurs parties.
  8. Couronne d'aubes directrices pourvue d'aubes directrices réglables destiné à une turbomachine, comprenant une bague intérieure selon l'une des revendications précédentes, caractérisée par un support de garniture d'étanchéité (13), qui recouvre, en particulier le côté avant, au moins un rainure ménagée sur la surface d'enveloppe, opposée aux aubes directrices, de la bague intérieure.
  9. Turbomachine, en particulier turbine à gaz, en particulier moteur à turbine à gaz, comprenant au moins une couronne d'aubes directrices selon la revendication précédente ou une bague intérieure selon la revendication 1 ou l'une des revendications dépendantes de celle-ci.
EP12189450.5A 2012-10-22 2012-10-22 Anneau intérieur pour un stator avec aubes directrices réglables Active EP2722485B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12189450.5A EP2722485B1 (fr) 2012-10-22 2012-10-22 Anneau intérieur pour un stator avec aubes directrices réglables

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12189450.5A EP2722485B1 (fr) 2012-10-22 2012-10-22 Anneau intérieur pour un stator avec aubes directrices réglables

Publications (2)

Publication Number Publication Date
EP2722485A1 EP2722485A1 (fr) 2014-04-23
EP2722485B1 true EP2722485B1 (fr) 2018-07-25

Family

ID=47080358

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12189450.5A Active EP2722485B1 (fr) 2012-10-22 2012-10-22 Anneau intérieur pour un stator avec aubes directrices réglables

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Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018213983A1 (de) * 2018-08-20 2020-02-20 MTU Aero Engines AG Verstellbare Leitschaufelanordnung, Leitschaufel, Dichtungsträger und Turbomaschine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE496713A (fr) * 1949-07-01
DE3018621C2 (de) * 1980-05-16 1982-06-03 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Außengehäuse für Axialverdichter oder -turbinen von Strömungsmaschinen, insbesondere Gasturbinentriebwerken
FR2875270B1 (fr) * 2004-09-10 2006-12-01 Snecma Moteurs Sa Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
US7713022B2 (en) * 2007-03-06 2010-05-11 United Technologies Operations Small radial profile shroud for variable vane structure in a gas turbine engine
DE102009038623B4 (de) * 2009-08-26 2012-01-19 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelkranz für den Verdichter einer Fluggasturbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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