US20130216359A1 - Compressor - Google Patents

Compressor Download PDF

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Publication number
US20130216359A1
US20130216359A1 US13/808,117 US201113808117A US2013216359A1 US 20130216359 A1 US20130216359 A1 US 20130216359A1 US 201113808117 A US201113808117 A US 201113808117A US 2013216359 A1 US2013216359 A1 US 2013216359A1
Authority
US
United States
Prior art keywords
compressor
inner ring
ring
guide vanes
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.)
Abandoned
Application number
US13/808,117
Other languages
English (en)
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
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Brandenburg, Thomas, HOFMANN, MARKUS, MILDNER, FRANK, Paus, Markus, Ecke, Daniel, MATTHIAS, TORSTEN, MERTENS, BERNWARD, SCHIRRMACHER, ACHIM, SHEVCHENKO, VADIM, SIEBER, UWE, Wigger, Hubertus Michael
Publication of US20130216359A1 publication Critical patent/US20130216359A1/en
Abandoned 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 having a housing, which defines the radially outer limit of an annular flow duct and in which guide vanes of a vane ring extending radially through the flow duct are pivotally mounted, wherein each guide vane on the housing side comprises a first pivot extending through the housing and on the rotor side comprises a second pivot extending into an inner ring.
  • Known compressors of modern gas turbines comprise one or more compressor stages, the guide vanes of which are adjustable.
  • the guide vanes assigned to a corresponding ring are adjustable about their longitudinal axis, in order to regulate the mass flow.
  • the capacity for regulating the mass flow gives the compressor a larger working range.
  • pivots are provided at each of the two blade ends of the guide vanes.
  • the outer pivot is supported in the annular housing and the inner pivot in a so-called inner ring.
  • the inner ring is held by all the guide vanes.
  • the inner ring is positioned centrally in relation to the rotor axis via the radial positioning of the outer pivots in the housing.
  • the radial adjustment of the vanes serves not only to position the inner ring in relation to the rotor but at the same time also to set the gaps between the blades of the adjustable guide vanes and the external housing and the inner ring, so that in the process of adjusting the blade this does not touch the boundary wall of the flow duct.
  • U.S. Pat. No. 2,671,634 discloses an alternative variant of the bearing of adjustable guide vanes.
  • the arrangement shown therein comprises an inner ring divided into two equal segments. The ends of the segments here rest loosely against one another in a tongue-and-groove connection, the inner pivots of the adjustable guide vanes being supported directly in radial bores of the inner ring. Each segment is thereby supported by those in the associated guide vanes, which can also lead to increased wear.
  • the object of the invention in therefore to provide a compressor having a fastening arrangement for guide vanes which are capable of pivoting about their longitudinal axis and an inner ring support of which is relatively free from wear and at the same time allows easy positioning of the inner ring in relation to the rotor.
  • the object of the invention is achieved by a compressor, in which the inner ring is embodied as a split ring having two opposing ends and is provided with a spring element for spreading the ring gap.
  • the inner ring is embodied as a split ring having two opposing ends and is provided with a spring element for spreading the ring gap.
  • a spring element for spreading the ring gap.
  • the guide vanes can be equipped with a second pivot which is disposed radially inside and is of a purely cylindrical design.
  • the bores in the inner ring which receive the pivots and which according to the invention no longer comprise a continuous circumferential flange for the positive interlock. It is of particular advantage here that potential distortions of the inner ring are now avoided due to the absence of radial latching.
  • the simplified design of the inner bearing of the guide vanes reduces the assembly time.
  • the inner ring consequently allows the inner ring to be designed as a self-supporting and self-centering system, in which only the adjustable guide vanes arranged in the lower half of the vane ring then support the so-to-speak floating inner ring.
  • a further advantage of the invention is that owing to the self-centering support of the inner ring the adjusting device for the radial positioning of the guide vanes in the housing can even be dispensed with. This simplifies the compressor and owing to the smaller number of components used reduces the likelihood of the compressor failing.
  • the two ends of the split ring comprise opposing first sockets, which are in the nature of blind holes and in which the spring element is seated.
  • a relatively simple design for spreading the split ring can thereby be specified, in which the spring element is embodied as a coil spring, for example.
  • the coil spring is prevented from slipping, since it is seated in the sockets.
  • Relative movements of the two ends of the inner ring in an axial direction can be prevented if these ends are axially locked.
  • This can be done with parallel keys, for example, which predefine the axial positioning of the two opposing ends of the split ring.
  • the parallel keys are likewise arranged in sockets provided for this purpose in both end faces of the gap in the inner ring.
  • the inner ring comprises at least two segments.
  • the segments here preferably extend over an arc length of 180°. This allows a relatively easy assembly of the guide vanes in a compressor.
  • a collared bushing may be provided as a wearing lubricant between the second pivots and each of the bores of the inner ring receiving the pivots.
  • a continuous circumferential groove be provided on the second pivot, in which groove a sealing ring, for example an O-ring seating therein, is arranged. This reduces the wear to the radially inner bearing.
  • An inner ring or segment that is relatively easy to produce can be specified if these are axially dividable.
  • the parts of the segment or the inner ring can be screwed together, for example, or also welded together.
  • the segment or the inner ring is preferably undivided axially.
  • a stationary gas turbine having a housing dividable into equal parts and intended for generating power is in particular equipped with an inventive compressor according to the aforementioned developments.
  • FIG. 1 shows a cross section through a detail of the compressor having compressor guide vanes rotatably supported at both ends and capable of pivoting about their longitudinal axis;
  • FIG. 2 schematically shows an inner ring embodied as a split ring
  • FIG. 3 shows, by way of example, a spring element arranged in the gap between the two opposing ends of the split ring.
  • FIG. 1 shows a cross section through a compressor 10 of axial-flow type in the axial portion of guide vanes 14 capable of pivoting about their longitudinal axis 12 .
  • the guide vanes 14 may be inlet guide vanes of the compressor 10 , for example. However, they may also form part of vane rings of subordinate compressor stages situated downstream thereof.
  • the guide vanes 14 comprise an aerodynamically curved blade 16 (represented only in part), 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 is arranged for receiving a sealing O-ring. Adjoining the first portion 22 is a concentric second portion 23 of smaller diameter.
  • Both portions 22 , 23 are part of a pivot 26 and are each of cylindrical design.
  • a collared bushing 28 is arranged around the second portion 23 .
  • the first portion 22 and the collared bushing 28 are seated in a socket 30 corresponding to their contour, which is embodied 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 the radially inner limit of an annular flow duct 36 of the compressor 10 .
  • the inner ring 32 encompasses a rotor 35 of the compressor 10 .
  • pivots are provided in a housing defining the outer limit of the flow duct 36 .
  • the design chosen means that in principle the guide vanes 14 are merely inserted into the sockets 30 radially from outside.
  • the radial direction here relates to the machine axis 38 of the compressor 10 , along which this extends.
  • the inner ring 32 assembled from two segments 40 is represented schematically in FIG. 2 .
  • the two segments 40 each have an arc length of 180°.
  • a first connecting area 42 the two segments 40 are screwed together at the end face without leaving a gap.
  • the other two ends 44 of the segments 40 are situated opposite one another in a second connecting area 46 forming a ring gap.
  • the term ring gap is hereinafter abbreviated to gap 48 .
  • the second connecting area 46 is shown in detail in FIG. 3 .
  • a first socket 50 which in each case is formed by a blind hole, is provided in each of the two ends 44 .
  • the two first sockets 50 are situated opposite one another, so that an encapsulated spring element 52 is seated in these sockets.
  • the spring element 52 is designed as a coil spring having a capsule 53 .
  • the spring element 52 is seated prestressed in the gap 48 , so that the two ends 44 are forced apart.
  • the inner ring 32 is thereby pressed against the pivots 26 of the guide vanes 14 .
  • a self-centering of the inner ring 32 is thereby achieved.
  • sockets 54 which are likewise situated in opposing alignment with one another, are provided in the two ends 44 .
  • a centering element 56 which may be designed as a parallel key, for example, is seated in the second sockets 54 .
  • This arrangement is capable of preventing a relative displacement of the two ends 44 in an axial direction, thereby locking the two ends 44 . This prevents a shear stress load acting on the spring element 52 .
  • the invention therefore relates overall to an axial-flow compressor 10 having an annular flow duct 36 , in which adjustable guide vanes 14 of a vane ring extending through the flow duct 36 are pivotally mounted, wherein each guide vane 14 on the rotor side comprises a pivot 26 for mounting an inner ring 32 on its blade 16 .
  • the inner ring is embodied as a split ring having two opposing ends 44 and is 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)
US13/808,117 2010-07-08 2011-07-07 Compressor Abandoned US20130216359A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10007062.2 2010-07-08
EP10007062A EP2405104A1 (de) 2010-07-08 2010-07-08 Verdichter und zugehöriges Gasturbinenkraftwerk
PCT/EP2011/061486 WO2012004336A2 (de) 2010-07-08 2011-07-07 Verdichter

Publications (1)

Publication Number Publication Date
US20130216359A1 true US20130216359A1 (en) 2013-08-22

Family

ID=43221935

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/808,117 Abandoned US20130216359A1 (en) 2010-07-08 2011-07-07 Compressor

Country Status (6)

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

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130205800A1 (en) * 2012-02-10 2013-08-15 Richard Ivakitch 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
US10677076B2 (en) 2016-04-28 2020-06-09 MTU Aero Engines AG Guide vane ring for a turbomachine
CN112065777A (zh) * 2020-11-10 2020-12-11 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

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
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 (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor
US20050254944A1 (en) * 2004-05-11 2005-11-17 Gary Bash Fastened vane assembly
US7572098B1 (en) * 2006-10-10 2009-08-11 Johnson Gabriel L Vane ring with a damper
US7651319B2 (en) * 2002-02-22 2010-01-26 Drs Power Technology Inc. Compressor stator vane
US7824152B2 (en) * 2007-05-09 2010-11-02 Siemens Energy, Inc. Multivane segment mounting arrangement for a gas turbine
US20120020770A1 (en) * 2010-07-22 2012-01-26 Friedrich Rogers Energy absorbing apparatus in a gas turbine engine

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE496713A (ru) * 1949-07-01
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 (en) * 2000-11-09 2002-05-15 General Electric Company Inner shroud retaining system for variable stator vanes
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
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
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

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor
US7651319B2 (en) * 2002-02-22 2010-01-26 Drs Power Technology Inc. Compressor stator vane
US20050254944A1 (en) * 2004-05-11 2005-11-17 Gary Bash Fastened vane assembly
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
US20120020770A1 (en) * 2010-07-22 2012-01-26 Friedrich Rogers Energy absorbing apparatus in a gas turbine engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130205800A1 (en) * 2012-02-10 2013-08-15 Richard Ivakitch Vane assemblies for gas turbine engines
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
US10677076B2 (en) 2016-04-28 2020-06-09 MTU Aero Engines AG Guide vane ring for a turbomachine
CN112065777A (zh) * 2020-11-10 2020-12-11 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

Also Published As

Publication number Publication date
EP2591213B1 (de) 2014-04-02
RU2013105342A (ru) 2014-08-20
JP2013529755A (ja) 2013-07-22
RU2575956C2 (ru) 2016-02-27
EP2591213A2 (de) 2013-05-15
WO2012004336A2 (de) 2012-01-12
EP2405104A1 (de) 2012-01-11
CN102985640A (zh) 2013-03-20
CN102985640B (zh) 2015-10-21
WO2012004336A3 (de) 2012-06-07
JP5638696B2 (ja) 2014-12-10

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Legal Events

Date Code Title Description
AS Assignment

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BRANDENBURG, THOMAS;ECKE, DANIEL;HOFMANN, MARKUS;AND OTHERS;SIGNING DATES FROM 20121218 TO 20130314;REEL/FRAME:030012/0858

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION