EP2591213A2 - Compresseur et turbine à gaz associée - Google Patents

Compresseur et turbine à gaz associée

Info

Publication number
EP2591213A2
EP2591213A2 EP11732418.6A EP11732418A EP2591213A2 EP 2591213 A2 EP2591213 A2 EP 2591213A2 EP 11732418 A EP11732418 A EP 11732418A EP 2591213 A2 EP2591213 A2 EP 2591213A2
Authority
EP
European Patent Office
Prior art keywords
compressor
inner ring
ring
pin
spring element
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
EP11732418.6A
Other languages
German (de)
English (en)
Other versions
EP2591213B1 (fr
Inventor
Thomas Brandenburg
Daniel Ecke
Markus Hofmann
Torsten Matthias
Bernward Mertens
Frank Mildner
Markus Paus
Achim Schirrmacher
Vadim Shevchenko
Uwe Sieber
Hubertus Michael Wigger
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP11732418.6A priority Critical patent/EP2591213B1/fr
Publication of EP2591213A2 publication Critical patent/EP2591213A2/fr
Application granted granted Critical
Publication of EP2591213B1 publication Critical patent/EP2591213B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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

Definitions

  • the invention relates to a compressor with an annular flow channel radially outwardly delimiting housing in which are radially supported by the flow channel Leit ⁇ blades of a vane ring rotatably supported, wherein each vane on the housing side extending through the housing first pin and rotor side into a Inner ring has protruding second pin.
  • Known compressors of modern gas turbines have one or more compressor stages whose Leitgeschaufelung is adjustable.
  • the corresponding vanes associated vanes are adjustable about its longitudinal axis to control the mass flow. By regulating the mass flow, the compressor has an enlarged working range.
  • pins are provided at the two blade end of the vanes.
  • the outer pin in the annular housing and the inner pin are mounted in a so-called inner ring.
  • the inner ring is held by all vanes.
  • the centric positioning of the inner ring to the rotor axis via the radial positioning of the outer pin in the housing.
  • the gaps between the blades ⁇ blades of the adjustable vane and the outer housing or the inner ring are adjusted so that during the adjustment of the blade this is not on the flow channel boundary wall strikes.
  • the object of the invention is therefore to provide a compressor with a fastening arrangement for guide vanes which are pivotable about their longitudinal axis and whose inner ring support is comparatively low in wear and at the same time permits a simple positioning of the inner ring relative to the rotor.
  • the object underlying the invention is achieved with a compressor according to the preamble of claim 1, wherein the inner ring is formed as a split ring with two opposite ends and provided with a spring element for spreading the annular gap.
  • pre schla ⁇ gen incorporate a preferably encapsulated spring element in the area of the annular gap.
  • a radial bias of the inner ring is achieved in the assembled state of the upper housing part and lower housing part. Due to the radial bias the inner ring is pressed against the second pin of the guide vanes. This eliminates the radial fixation of the inner ring on all vanes.
  • the guide vanes can be equipped with a radially inwardly disposed, second pin, which is formed purely cylindrically.
  • the pin receiving holes in the inner ring which according to the invention now no endless circumferential collar for the positive locking more.
  • poten ⁇ tial tension of the inner ring are avoided due to the now error-lumbar radial interlocking.
  • the simplified design of the inner bearing of the vanes also reduces the assembly time.
  • the calculations are diedeh- the inner ring and vanes of all Federele ⁇ ment compensated, which reduces the voltages between the inner ring and the inner bearing points of the vanes and reduces wear on the bearings.
  • Inner ring are designed as a self-supporting and self-centering system, in which case only the arranged in the lower half of the vane ring adjustable vanes, so to speak, floating the inner ring wear.
  • Another advantage of the invention is that due to the self-centering bearing of the inner ring, the adjusting device for radial positioning of the guide vanes in the housing may possibly even be omitted. This simplifies the compressor and reduces the failure probability of the compressor due to the smaller number of components used.
  • the two ends of the split ring facing each other ing first recordings which are blind hole-like and in which the spring element sits.
  • the spring element is designed as a helical spring. Slippage of the coil spring is excluded due to their seat in the recordings.
  • Relative movements of the two ends of the inner ring in the axial direction can be prevented if they are axially locked. This can be done, for example, with feather keys which predetermine the axial positioning of the two opposite ends of the split ring.
  • example ⁇ also, the springs pass into appropriate receptacles at both ends in the gap of the inner ring disposed.
  • the inner ring comprises at least two segments.
  • the segments preferably extend over an arc length of 180 °.
  • a wear-lubricating lubricant can be provided between the second pin and the pin receiving holes of the inner ring in each case a collar.
  • an endlessly encircling groove is provided on the second pin, in which a seated therein sealing ring, for example an O-ring is arranged. This reduces wear on the radially inner storage provided.
  • Segment can be specified if they are axially divisible.
  • the portions of the segment or the inner ring can ⁇ example, screwed together or even comparable with each other be welded.
  • the segment or the inner ring is axially undivided.
  • a stationary gas turbine provided for generating energy is equipped with a half-split housing with a compressor according to the invention in accordance with the aforementioned embodiments.
  • FIG. 1 shows a cross section through a section of Ver ⁇ poet with both ends rotatably mounted about its longitudinal axis pivotable compressor guide vanes;
  • FIG 2 schematically a trained as a split ring
  • Inner ring and FIG 3 an example of a arranged in the gap between the two opposite ends of the split ring spring element.
  • FIG. 1 shows a cross-section through a compressor 10 of axial design in the axial section of guide vanes 14 pivotable about its longitudinal axis 12.
  • the guide vanes 14 may, for example, be the inlet guide vanes of the compressor 10. However, they can also be associated with downstream compressor circuits of subordinate compressor stages.
  • the guide vanes 14 have an only partially shown aerodynamically curved blade 16, at its radially inner end 18 has a circular platform 20 is angeord ⁇ net.
  • the platform 20 merges into a first cylindrical portion 22 in which a circumferential groove 24 for receiving a sealing O-ring is disposed.
  • a concentric second section 23 connects with a smaller diameter.
  • Both sections 22, 23 are part of a pin 26 and each cylindrical latestbil ⁇ det.
  • a flanged bushing 28 is arranged around the second portion 23 around a flanged bushing 28 .
  • the first portion 22 and the collar bushing 28 are seated in a corresponding to the contour of the receptacle 30, which is formed as a stepped bore.
  • the bore is arranged in the so-called inner ring 32.
  • the outer circumferential surface 34 of the inner ring 32 defines an annular flow channel 36 of the compressor 10 radially inward. In this case, ⁇ the inner ring 32 engages a rotor 35 of the compressor 10.
  • radially outer ends of the vanes 14 are in an analogous manner to the inner end 18 pins in a flow channel 36 outside limiting housing pre ⁇ see. Due to the chosen construction, in principle, the guide vanes 14 are radially inserted only from the outside into the receptacles 30. The radial direction refers to the machine axis 38 of the compressor 10, along which it extends.
  • the composed of two segments 40 inner ring 32 is shown schematically in FIG.
  • the two segments 40 each have an arc length of 180 °.
  • the two segments 40 are bolted end-to-end without gaps.
  • the second connection region 46 is shown in detail in FIG.
  • a first receptacle 50 is provided in each case, each formed by a blind hole.
  • the two first receptacles 50 are opposite each other, so that in these an encapsulated spring element 52 is seated.
  • the spring ⁇ element 52 is configured in the illustrated embodiment as a screw with a capsule benfeder 53rd.
  • second receptacles 54 are provided in the two ends 44, which also face each other in an aligned manner.
  • a centering element 56 which may be configured, for example, as a feather key. This arrangement can prevent a relative displacement of the two ends 44 in the axial direction, whereby the two ends 44 are locked. A shear stress of the spring element 52 is thereby avoided ⁇ the.
  • the invention thus relates to an axial compressor 10 with an annular flow channel 36 by rotatably supported by the flow channel 36 adjustable guide vanes 14 of a vane ring, where ⁇ each guide vanes 14 for supporting an inner ring 32 on its blade 16 on the rotor side a pin 26 - points.
  • ⁇ each guide vanes 14 for supporting an inner ring 32 on its blade 16 on the rotor side a pin 26 - points is designed as a split ring with two opposite ends 44 and provided with a spring element 52 for spreading the split ring.

Landscapes

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

Abstract

L'invention concerne un compresseur axial (10) comportant un canal d'écoulement (36) annulaire dans lequel s'étendent des aubes fixes (14) d'une couronne d'aubes fixes, réglables et montées pivotantes, chaque aube fixe (14) présentant un axe (26) sur son ailette (16) côté rotor pour la fixation d'une bague intérieure (32). L'invention vise à créer une bague intérieure (32) à centrage automatique de faible usure. A cet effet, cette bague est une bague ouverte pourvue de deux extrémités (44) opposées et d'un élément ressort (52) pour son extension.
EP11732418.6A 2010-07-08 2011-07-07 Compresseur et turbine à gaz associée Not-in-force EP2591213B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11732418.6A EP2591213B1 (fr) 2010-07-08 2011-07-07 Compresseur et turbine à gaz associée

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10007062A EP2405104A1 (fr) 2010-07-08 2010-07-08 Compresseur et moteur à turbine à gaz associé
EP11732418.6A EP2591213B1 (fr) 2010-07-08 2011-07-07 Compresseur et turbine à gaz associée
PCT/EP2011/061486 WO2012004336A2 (fr) 2010-07-08 2011-07-07 Compresseur

Publications (2)

Publication Number Publication Date
EP2591213A2 true EP2591213A2 (fr) 2013-05-15
EP2591213B1 EP2591213B1 (fr) 2014-04-02

Family

ID=43221935

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10007062A Withdrawn EP2405104A1 (fr) 2010-07-08 2010-07-08 Compresseur et moteur à turbine à gaz associé
EP11732418.6A Not-in-force EP2591213B1 (fr) 2010-07-08 2011-07-07 Compresseur et turbine à gaz associée

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10007062A Withdrawn EP2405104A1 (fr) 2010-07-08 2010-07-08 Compresseur et moteur à turbine à gaz associé

Country Status (6)

Country Link
US (1) US20130216359A1 (fr)
EP (2) EP2405104A1 (fr)
JP (1) JP5638696B2 (fr)
CN (1) CN102985640B (fr)
RU (1) RU2575956C2 (fr)
WO (1) WO2012004336A2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10677076B2 (en) 2016-04-28 2020-06-09 MTU Aero Engines AG Guide vane ring for a turbomachine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9951639B2 (en) * 2012-02-10 2018-04-24 Pratt & Whitney Canada Corp. Vane assemblies for gas turbine engines
US9341194B2 (en) 2012-11-01 2016-05-17 Solar Turbines Incorporated Gas turbine engine compressor with a biased inner ring
JP7349274B2 (ja) * 2019-06-27 2023-09-22 三菱重工業株式会社 静翼支持リング及びタービン
CN112065777B (zh) * 2020-11-10 2021-01-19 中国航发上海商用航空发动机制造有限责任公司 压气机进口导流叶片的调节精度保持结构
JP7439315B1 (ja) 2023-03-16 2024-02-27 株式会社神鋼環境ソリューション 筒状構造体

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BE496713A (fr) * 1949-07-01
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor
FR2685033B1 (fr) * 1991-12-11 1994-02-11 Snecma Stator dirigeant l'entree de l'air a l'interieur d'une turbomachine et procede de montage d'une aube de ce stator.
US5395124A (en) * 1993-01-04 1995-03-07 Imo Industries, Inc. Retractible segmented packing ring for fluid turbines having gravity springs to neutralize packing segment weight forces
FR2723614B1 (fr) * 1994-08-10 1996-09-13 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.
FR2775731B1 (fr) * 1998-03-05 2000-04-07 Snecma Etage circulaire d'aubes aux extremites interieures unies par un anneau de liaison
ITMI991208A1 (it) * 1999-05-31 2000-12-01 Nuovo Pignone Spa Dispositivo per il posizionamento di ugelli di uno stadio statorico eper il raffreddamento di dischi rotorici in turbine a gas
EP1205639A1 (fr) * 2000-11-09 2002-05-15 General Electric Company Système de fixation des aubes statoriques variables dans une virole interieure de turbines
US6682299B2 (en) * 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement
US6651986B2 (en) * 2002-01-29 2003-11-25 General Electric Company Retractable packing ring lower half segment retaining key and method for retaining retractable packing ring lower half segment
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DE10225679A1 (de) * 2002-06-10 2003-12-18 Rolls Royce Deutschland Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
US7125222B2 (en) * 2004-04-14 2006-10-24 General Electric Company Gas turbine engine variable vane assembly
US7101150B2 (en) * 2004-05-11 2006-09-05 Power Systems Mfg, Llc Fastened vane assembly
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FR2896012B1 (fr) * 2006-01-06 2008-04-04 Snecma Sa Dispositif anti-usure pour pivot de guidage d'aube a angle de calage variable de compresseur de turbomachine
FR2902843A1 (fr) * 2006-06-23 2007-12-28 Snecma Sa Secteur de redresseur de compresseur ou secteur de distributeur de turbomachine
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10677076B2 (en) 2016-04-28 2020-06-09 MTU Aero Engines AG Guide vane ring for a turbomachine

Also Published As

Publication number Publication date
WO2012004336A3 (fr) 2012-06-07
JP5638696B2 (ja) 2014-12-10
WO2012004336A2 (fr) 2012-01-12
JP2013529755A (ja) 2013-07-22
CN102985640A (zh) 2013-03-20
US20130216359A1 (en) 2013-08-22
CN102985640B (zh) 2015-10-21
EP2591213B1 (fr) 2014-04-02
RU2575956C2 (ru) 2016-02-27
RU2013105342A (ru) 2014-08-20
EP2405104A1 (fr) 2012-01-11

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