EP2722485A1 - 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
EP2722485A1
EP2722485A1 EP12189450.5A EP12189450A EP2722485A1 EP 2722485 A1 EP2722485 A1 EP 2722485A1 EP 12189450 A EP12189450 A EP 12189450A EP 2722485 A1 EP2722485 A1 EP 2722485A1
Authority
EP
European Patent Office
Prior art keywords
inner ring
vanes
lateral surface
facing away
groove
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.)
Granted
Application number
EP12189450.5A
Other languages
German (de)
English (en)
Other versions
EP2722485B1 (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
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
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
Active 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
    • 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 and a method for producing 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 and a method for producing 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.
  • Claim 10 illustrates a vane ring with an inner ring according to the invention, claim 11 a turbomachine with such a vane ring and claim 12 a method for producing an inner ring according to the invention under protection.
  • the subclaims relate to advantageous developments.
  • 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 have a rotor and a guide grid, wherein one or more of these guide grilles comprise a stator vane ring with adjustable vanes 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 invention 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 an aspect of 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 one aspect of the present invention has one or more grooves which are arranged on a lateral surface of the inner ring facing away from the guide vanes.
  • 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.
  • a better temperature distribution preferably an approximately or at least substantially constant temperature, can advantageously be represented in the remaining cross section.
  • a heat conduction in the circumferential direction of the inner ring can be influenced, in particular limited and / or reduced.
  • the groove or grooves can be influenced by the groove or grooves a thermal movement of the inner ring, in particular during operation, in particular reduced, and so a change in its diameter and / or its shape, in particular roundness, influenced, in particular 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 between guide blade receptacles can advantageously reduce the cross section at this point, at which point it would initially have a greater wall thickness compared to recesses for receiving the guide blades.
  • one or more grooves arranged on the lateral surface of the inner ring remote 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 on the front side 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 groove in one embodiment of the present invention is, at least substantially, free of material to reduce the cross-section and thus improve the temperature distribution in the inner ring.
  • the grooves can also be completely or partially filled with a highly heat-conductive material.
  • two or more grooves arranged on the lateral surface of the inner ring facing away from the guide vanes are distributed over the circumference of the inner ring, in particular at least substantially equidistantly.
  • an advantageous temperature distribution can be represented.
  • an arrangement of one or more grooves between each two adjacent vane seats i. one or more grooves seen in the circumferential direction after all vane receptacles or vanes, thermodynamically may be advantageous.
  • an arrangement of one or more grooves between each two adjacent vane receiving pairs or vane receiving nipples i. one or more grooves seen in the circumferential direction after each second or third vane receiving or guide vane, can represent an optimal combination of thermodynamic and structural aspects.
  • the inner ring is formed in one piece. In another embodiment, it has two or more segments.
  • 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.
  • 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.
  • the grooves can be formed according to an embodiment of the present invention on the side facing away from the vanes lateral surface of the inner ring in particular by machining. Likewise, they may be uroformed with the inner ring, for example cast, or thermally or optically removed, in particular eroded or formed by means of a laser.
  • 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.
  • the guide vanes 2 can have radially outer outer pins 8, with which they can be mounted radially on the outside of 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 meridian cross section of the inner ring is reduced at these points, so that adjusts an advantageous temperature distribution in the remaining reduced residual cross section 9.4, which reduces thermal movement of the inner ring 9 and thus a change in the sealing gap or inlet between the vane ring and rotor 1.
  • 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 free of material.
  • 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)
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 true EP2722485A1 (fr) 2014-04-23
EP2722485B1 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

Country Status (1)

Country Link
EP (1) EP2722485B1 (fr)

Cited By (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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH288242A (de) * 1949-07-01 1953-01-15 Rolls Royce Axialströmungsmaschine.
DE3018621A1 (de) * 1980-05-16 1981-12-03 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Aussengehaeuse fuer axialverdichter oder -turbinen von stroemungsmaschinen
US20060056963A1 (en) * 2004-09-10 2006-03-16 Snecma Retaining of centring keys for rings under variable angle stator vanes in a gas turbine engine
EP1967718A2 (fr) * 2007-03-06 2008-09-10 United Technologies Corporation Virole pour turbine à gaz ayant des aubes de guidage à calage variable
DE102009038623A1 (de) * 2009-08-26 2011-03-10 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelkranz für den Verdichter einer Fluggasturbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH288242A (de) * 1949-07-01 1953-01-15 Rolls Royce Axialströmungsmaschine.
DE3018621A1 (de) * 1980-05-16 1981-12-03 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Aussengehaeuse fuer axialverdichter oder -turbinen von stroemungsmaschinen
US20060056963A1 (en) * 2004-09-10 2006-03-16 Snecma Retaining of centring keys for rings under variable angle stator vanes in a gas turbine engine
EP1967718A2 (fr) * 2007-03-06 2008-09-10 United Technologies Corporation Virole pour turbine à gaz ayant des aubes de guidage à calage variable
DE102009038623A1 (de) * 2009-08-26 2011-03-10 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelkranz für den Verdichter einer Fluggasturbine

Cited By (3)

* 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
EP3613952A1 (fr) 2018-08-20 2020-02-26 MTU Aero Engines GmbH Dispositif d'aube directrice réglable, aube directrice, porte-joint et turbomachine
US11300004B2 (en) 2018-08-20 2022-04-12 MTU Aero Engines AG Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine

Also Published As

Publication number Publication date
EP2722485B1 (fr) 2018-07-25

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