EP2405104A1 - Compresseur et moteur à turbine à gaz associé - Google Patents

Compresseur et moteur à turbine à gaz associé Download PDF

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Publication number
EP2405104A1
EP2405104A1 EP10007062A EP10007062A EP2405104A1 EP 2405104 A1 EP2405104 A1 EP 2405104A1 EP 10007062 A EP10007062 A EP 10007062A EP 10007062 A EP10007062 A EP 10007062A EP 2405104 A1 EP2405104 A1 EP 2405104A1
Authority
EP
European Patent Office
Prior art keywords
compressor
inner ring
ring
housing
pin
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.)
Withdrawn
Application number
EP10007062A
Other languages
German (de)
English (en)
Inventor
Thomas Brandenburg
Daniel Ecke
Markus Hofmann
Torsten Matthias
Bernward Dr. Mertens
Frank Dr. Mildner
Markus Paus
Achim Schirrmacher
Vadim Shevchenko
Uwe Sieber
Hubertus Michael Dr. 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 EP10007062A priority Critical patent/EP2405104A1/fr
Priority to PCT/EP2011/061486 priority patent/WO2012004336A2/fr
Priority to EP11732418.6A priority patent/EP2591213B1/fr
Priority to US13/808,117 priority patent/US20130216359A1/en
Priority to RU2013105342/06A priority patent/RU2575956C2/ru
Priority to CN201180033946.2A priority patent/CN102985640B/zh
Priority to JP2013517385A priority patent/JP5638696B2/ja
Publication of EP2405104A1 publication Critical patent/EP2405104A1/fr
Withdrawn legal-status Critical Current

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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
    • 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 bounding housing in which are radially mounted rotatably supported by the flow channel extending vanes of a vane ring, wherein each vane on the housing side extending through the housing first pin and the rotor side projecting into an inner ring having 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.
  • Inner ring provides, it can lead to increased mechanical stresses within the respective inner ring bearing, which can cause considerable wear on the bearing shells used there. The mechanical stresses during operation can still be enhanced by thermal stresses.
  • the object of the invention is therefore to provide a compressor with a mounting arrangement for about its longitudinal axis pivotable vanes, the inner ring support is comparatively low wear and at the same time allows easy 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.
  • the inner ring is formed as a split ring with two opposite ends and provided with a spring element for spreading 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 of the inner ring is pressed against the second pin of the vanes. This eliminates the radial fixation of the inner ring on all vanes.
  • the vanes can be equipped with a radially inwardly disposed second pin, which is purely cylindrical.
  • the pin receiving holes in the inner ring which according to the invention now no endless circumferential collar for the positive locking more. It is particularly advantageous that potential stresses of the inner ring due to the now missing radial entanglement are avoided.
  • the internal bearing of the vanes reduces the assembly time.
  • the thermal expansions of the inner ring and all the vanes are compensated by the spring element, which reduces the stresses between the inner ring and the inner bearing points of the vanes and reduces wear on the bearings.
  • the inner ring can be designed as a self-supporting and self-centering system, in which case only the adjustable guide vanes arranged in the lower half of the vane ring carry, so to speak, floating the inner ring.
  • Another advantage of the invention is that due to the self-centering bearing of the inner ring, the adjustment 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 on each other opposite first receptacles which are blind hole-like and in which the spring element is seated.
  • the spring element is designed as a helical spring. Slippage of the coil spring is excluded due to their seat in the recordings.
  • this is formed encapsulated. 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 feathers, which dictate the axial positioning of the two opposite ends of the split ring.
  • the feather keys are arranged in the receptacles provided for this purpose at both ends in the gap of the inner ring.
  • the inner ring comprises at least two segments.
  • the segments preferably extend over an arc length of 180 °. This allows a comparatively simple assembly of vanes in a compressor.
  • 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 endless circumferential 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.
  • a comparatively easy to manufacture inner ring or segment can be specified if they are axially divisible.
  • the parts of the segment or of the inner ring can for example be screwed together or also welded together.
  • 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 1 shows a cross-section through an axial type compressor 10 in the axial section of vanes 14 pivotable about its longitudinal axis 12.
  • the vanes 14 may, for example, be the inlet guide vanes of the compressor 10. However, they can also be associated with downstream compressor blade rings of downstream compressor stages.
  • the vanes 14 have an aerodynamically curved airfoil 16, only partially shown, at the radially inner end 18 of which a circular platform 20 is arranged.
  • the platform 20 merges into a first cylindrical portion 22 in which a circumferential groove 24 for receiving a sealing O-ring is disposed.
  • the first section 22 is followed by a concentric second section 23 of smaller diameter. Both sections 22, 23 are part of a pin 26 and each cylindrical.
  • the second portion 23 around a flanged bushing 28 is arranged.
  • 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. It encompasses the inner ring 32 a rotor 35 of the compressor 10.
  • radially outer ends of the guide vanes 14 are provided in a manner analogous to the inner end 18 pins in a flow channel 36 outside limiting housing.
  • 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 in FIG. 2 shown schematically.
  • the two segments 40 each have an arc length of 180 °.
  • a first connection region 42 the two segments 40 are bolted end-to-end without gaps.
  • the two other ends 44 of the segments 40 lie in a second connection region 46 facing one another to form an annular gap.
  • the annular gap is hereinafter referred to briefly as gap 48.
  • the second connection region 46 is in FIG. 3 shown in detail.
  • 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 embodiment shown as a helical spring with a capsule 53.
  • the spring element 52 is biased in the gap 48, so that the two ends 44 are pressed apart.
  • the inner ring 32 is thereby pressed against the pins 26 of the guide vanes 14. As a result, a self-centering of the inner ring 32 can be achieved.
  • second receptacles 54 are provided in the two ends 44, which are also opposite one another in alignment.
  • a centering element 56 which may be configured, for example, as a feather key. This arrangement can be a Prevent 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 invention thus relates to an axial compressor 10 having an annular flow channel 36 by rotatably supported by the flow channel 36 extending variable guide vanes 14 of a vane ring, each guide vanes 14 for supporting an inner ring 32 on its blade 16 on the rotor side a pin 26 has.
  • a low-wear self-centering inner ring 32 this 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)
EP10007062A 2010-07-08 2010-07-08 Compresseur et moteur à turbine à gaz associé Withdrawn EP2405104A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP10007062A EP2405104A1 (fr) 2010-07-08 2010-07-08 Compresseur et moteur à turbine à gaz associé
PCT/EP2011/061486 WO2012004336A2 (fr) 2010-07-08 2011-07-07 Compresseur
EP11732418.6A EP2591213B1 (fr) 2010-07-08 2011-07-07 Compresseur et turbine à gaz associée
US13/808,117 US20130216359A1 (en) 2010-07-08 2011-07-07 Compressor
RU2013105342/06A RU2575956C2 (ru) 2010-07-08 2011-07-07 Компрессор и соответствующая газовая турбина
CN201180033946.2A CN102985640B (zh) 2010-07-08 2011-07-07 压缩机和相关联的燃气轮机
JP2013517385A JP5638696B2 (ja) 2010-07-08 2011-07-07 コンプレッサおよびこれに関連したガスタービン

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP2405104A1 true EP2405104A1 (fr) 2012-01-11

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 After (1)

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

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)

Families Citing this family (6)

* 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
DE102016207212A1 (de) * 2016-04-28 2017-11-02 MTU Aero Engines AG Leitschaufelkranz für eine Strömungsmaschine
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

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2671634A (en) * 1949-07-01 1954-03-09 Rolls Royce Adjustable stator blade and shroud ring arrangement for axial flow turbines and compressors
DE10225679A1 (de) * 2002-06-10 2003-12-18 Rolls Royce Deutschland Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
EP1586744A2 (fr) * 2004-04-14 2005-10-19 General Electric Company Aubes de guidage variables pour turbine à gaz

Family Cites Families (17)

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Publication number Priority date Publication date Assignee Title
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
US7651319B2 (en) * 2002-02-22 2010-01-26 Drs Power Technology Inc. Compressor stator vane
US7101150B2 (en) * 2004-05-11 2006-09-05 Power Systems Mfg, Llc Fastened vane assembly
DE102005040574A1 (de) * 2005-08-26 2007-03-15 Rolls-Royce Deutschland Ltd & Co Kg Spaltkontrollvorrichtung für eine Gasturbine
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
US7572098B1 (en) * 2006-10-10 2009-08-11 Johnson Gabriel L Vane ring with a damper
US7824152B2 (en) * 2007-05-09 2010-11-02 Siemens Energy, Inc. Multivane segment mounting arrangement for a gas turbine
US8632300B2 (en) * 2010-07-22 2014-01-21 Siemens Energy, Inc. Energy absorbing apparatus in a gas turbine engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2671634A (en) * 1949-07-01 1954-03-09 Rolls Royce Adjustable stator blade and shroud ring arrangement for axial flow turbines and compressors
DE10225679A1 (de) * 2002-06-10 2003-12-18 Rolls Royce Deutschland Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
EP1586744A2 (fr) * 2004-04-14 2005-10-19 General Electric Company Aubes de guidage variables pour turbine à gaz

Also Published As

Publication number Publication date
EP2591213A2 (fr) 2013-05-15
JP5638696B2 (ja) 2014-12-10
US20130216359A1 (en) 2013-08-22
WO2012004336A2 (fr) 2012-01-12
RU2575956C2 (ru) 2016-02-27
CN102985640B (zh) 2015-10-21
CN102985640A (zh) 2013-03-20
JP2013529755A (ja) 2013-07-22
WO2012004336A3 (fr) 2012-06-07
EP2591213B1 (fr) 2014-04-02
RU2013105342A (ru) 2014-08-20

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