EP2591213B1 - Compresseur et turbine à gaz associée - Google Patents

Compresseur et turbine à gaz associée Download PDF

Info

Publication number
EP2591213B1
EP2591213B1 EP11732418.6A EP11732418A EP2591213B1 EP 2591213 B1 EP2591213 B1 EP 2591213B1 EP 11732418 A EP11732418 A EP 11732418A EP 2591213 B1 EP2591213 B1 EP 2591213B1
Authority
EP
European Patent Office
Prior art keywords
compressor
inner ring
ring
spring element
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.)
Not-in-force
Application number
EP11732418.6A
Other languages
German (de)
English (en)
Other versions
EP2591213A2 (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

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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 delimiting housing in which radially extending through the flow channel extending vanes of a vane ring are mounted, 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.
  • An alternative variant of the storage of adjustable vanes is from the US 2,671,634 known.
  • the arrangement shown therein comprises a divided into two segments half inner ring. The ends of the segments are in a tongue and groove connection loosely together, the inner pins of the adjustable vanes are mounted directly in radial bores of the inner ring. As a result, each segment is carried by those in the guide vanes to be assigned, which can also lead to increased wear.
  • 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.
  • 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.
  • 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 become.
  • the segment or the inner ring is axially undivided.
  • 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.
  • the inner ring 32 surrounds 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.

Landscapes

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

Claims (9)

  1. Compresseur (10)
    comprenant une enveloppe, qui délimite à l'extérieur radialement un canal (36) annulaire d'écoulement et dans lequel sont maintenues, en étant montées tournantes, des aubes (14) directrices, s'étendant radialement dans le canal (36) d'écoulement, d'une couronne d'aubes directrices,
    chaque aube (14) directrice a, du côté de l'enveloppe, un premier tenon (26) traversant l'enveloppe et, du côté du rotor, un deuxième tenon (26) pénétrant dans un anneau (32) intérieur,
    caractérisé en ce que
    l'anneau (32) intérieur est constitué sous la forme d'un anneau fendu ayant deux extrémités (44) opposées l'une à l'autre et est pourvu d'un élément (52) de ressort pour l'écartement de l'anneau fendu.
  2. Compresseur (10) suivant la revendication 1,
    dans lequel les deux extrémités (44) de l'anneau fendu ont des premiers logements (50), qui sont opposés l'un à l'autre et dans lesquels vient l'élément (52) de ressort.
  3. Compresseur (10) suivant la revendication 1 ou 2,
    dans lequel l'élément (52) de ressort est enfermé.
  4. Compresseur (10) suivant la revendication 1, 2 ou 3,
    dans lequel les extrémités (44) sont bloquées axialement.
  5. Compresseur (10) suivant l'une des revendications précédentes,
    dans lequel l'anneau (32) intérieur comprend au moins deux segments (40).
  6. Compresseur (10) suivant l'une des revendications précédentes,
    dans lequel, respectivement, une douille (28) à collet est montée sur le deuxième tenon (26).
  7. Compresseur (10) suivant l'une des revendications précédentes,
    dans lequel le deuxième tenon (26) a une rainure (24) faisant le tour sans fin, dans laquelle se trouve un joint torique.
  8. Compresseur (10) suivant l'une des revendications précédentes,
    dans lequel l'anneau (32) intérieur ou les segments (40) peuvent être subdivisés axialement.
  9. Turbine à gaz ayant un compresseur (10) suivant l'une des revendications précédentes.
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
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

Publications (2)

Publication Number Publication Date
EP2591213A2 EP2591213A2 (fr) 2013-05-15
EP2591213B1 true 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
DE102016207212A1 (de) * 2016-04-28 2017-11-02 MTU Aero Engines AG Leitschaufelkranz für eine Strömungsmaschine

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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Publication number Priority date Publication date Assignee Title
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
US7651319B2 (en) * 2002-02-22 2010-01-26 Drs Power Technology Inc. Compressor stator vane
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
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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016207212A1 (de) * 2016-04-28 2017-11-02 MTU Aero Engines AG Leitschaufelkranz für eine Strömungsmaschine

Also Published As

Publication number Publication date
JP5638696B2 (ja) 2014-12-10
EP2405104A1 (fr) 2012-01-11
US20130216359A1 (en) 2013-08-22
RU2575956C2 (ru) 2016-02-27
CN102985640B (zh) 2015-10-21
CN102985640A (zh) 2013-03-20
WO2012004336A2 (fr) 2012-01-12
EP2591213A2 (fr) 2013-05-15
JP2013529755A (ja) 2013-07-22
WO2012004336A3 (fr) 2012-06-07
RU2013105342A (ru) 2014-08-20

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