EP0707150A2 - Compression - Google Patents

Compression Download PDF

Info

Publication number
EP0707150A2
EP0707150A2 EP95810613A EP95810613A EP0707150A2 EP 0707150 A2 EP0707150 A2 EP 0707150A2 EP 95810613 A EP95810613 A EP 95810613A EP 95810613 A EP95810613 A EP 95810613A EP 0707150 A2 EP0707150 A2 EP 0707150A2
Authority
EP
European Patent Office
Prior art keywords
bolts
housing
groups
guide vanes
guide
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
EP95810613A
Other languages
German (de)
English (en)
Other versions
EP0707150A3 (fr
EP0707150B1 (fr
Inventor
Ivan Luketic
Alfred Krähenbühl
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.)
General Electric Switzerland GmbH
Original Assignee
ABB Management 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 ABB Management AG filed Critical ABB Management AG
Publication of EP0707150A2 publication Critical patent/EP0707150A2/fr
Publication of EP0707150A3 publication Critical patent/EP0707150A3/fr
Application granted granted Critical
Publication of EP0707150B1 publication Critical patent/EP0707150B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the invention relates to a compressor with an axially divided housing, consisting of several housing halves, in which the guide vanes are fastened with their feet in circumferential grooves.
  • Such compressors are known. Intermediate pieces are usually arranged between the guide vane feet. When the compressor is operating, the air is heated by the compression. The compressed air gives off heat to the spacers and blade material, causing them to expand. In order to avoid the stress in the blade root area resulting from thermal expansion, which can lead to material defects, the guide blades and the spacers are inserted with play in the housing. When installing the blades in the housing, paper intermediate layers are placed between the blade feet in order to distribute the play evenly over the circumference. Some intermediate pieces are fixed by documents placed under the intermediate pieces. The paper liners burn when the compressor is operating. If the gas turbine group is switched off and started again, the fixation of the spacers loosen due to vibrations. As a result, the guide vanes can slide together when cooled.
  • the blades are installed in the axially split housing at the installation site of the compressor. Due to the inaccuracy that results from the summation of the manufacturing tolerances of the individual elements, as well as the play distribution with paper intermediate layers, the elements that are at the parting plane of the housing can only be machined exactly at the place of installation.
  • the guide vanes with paper intermediate layers are installed in the housing, the protruding, final elements lying on the parting plane are milled over and holes are drilled for fastening the final elements. In order to remove chips and dirt, all elements must be removed again. After cleaning, the elements are reinstalled exactly as in the first installation step. This means a lot of work and therefore high costs.
  • the invention has for its object to simplify the installation of the guide vanes in the compressor housing in a compressor of the type mentioned.
  • this is achieved in that bolts anchored over the circumference in the groove base of the circumferential groove are inserted, which preferably protrude radially into the circumferential groove and which subdivide the guide vanes into groups and end groups located on the parting plane of the housing.
  • the advantages of the invention can be seen, inter alia, in the fact that the position of the bolts is precisely known and that the individual sums of the manufacturing tolerances of the groups can be determined with sufficient accuracy.
  • the bolts also distribute the play evenly over the circumference of the housing.
  • the play of the individual groups is easily adjustable. Post-processing is no longer necessary when installing the groups in the housing, which considerably reduces the workload.
  • the compressor housing 21 consists of a lower housing half 21a and an upper housing half 21b, with an axial parting plane 20.
  • the guide vanes are each spacers 4.
  • the intermediate pieces 4 can be differentiated into intermediate pieces 4a without cutouts and intermediate pieces 4b with cutouts 11. These cutouts 11 serve to receive bolts 8.
  • the groups A2-A5 are identical in terms of the number of intermediate pieces 4 and guide vanes 1. With regard to the design and arrangement of the intermediate pieces 4, the groups A2 and A4 and the groups A3 and A5 are identical.
  • the end groups A6 and A7 adjoining the parting plane 20 are designed with divided intermediate pieces 6 and 7. In order to be able to fasten these divided intermediate pieces 6 and 7 in the circumferential groove 10, they are connected to the subsequent guide vane 1 and the intermediate piece 4b with screws 12 and pins, not shown.
  • the final groups A6 and A7 are then processed in the factory in such a way that no further processing steps are necessary during assembly on site.
  • the blade root 3a of the guide blade 1 is also modified.
  • the end groups A6 and A7 are fixed in the housing 21 by means of the head of anchoring screws 9.
  • the housing In order to install the guide vanes 1 in the housing 21, the housing is opened along the parting plane 20 via flanges, not shown.
  • the upper housing half 21b is in the axial direction rotated by one hundred and eighty degrees and arranged next to the lower housing half 21a. Due to the rotational symmetry of the housing 21, the installation of groups A1-A7 is identical for both housing halves 21a and 21b. Therefore, only the lower housing half 21a is described below.
  • the guide vanes 1 and intermediate pieces 4 of group A1 are inserted into the circumferential groove 10 in accordance with the position in FIG. 1.
  • a bolt 8 is pressed into the predrilled blind holes 5 on both sides.
  • an intermediate piece 4b with a recess 8 is inserted into the circumferential groove 10 on both sides of group A1, as well as the guide vanes 1 and intermediate pieces 4 belonging to groups A2 and A3.
  • a bolt 8 is anchored and then groups A4 and A5 inserted into the circumferential groove.
  • the end groups A6 and A7 are pushed in as a unit and fixed with the anchoring screws 9 in the lower housing half 21a.
  • the end groups A6 and A7 are manufactured with a negative tolerance so that they do not protrude beyond the parting plane 20.
  • possibly further rows of guide vanes are installed, in which case the number of guide vanes can vary.
  • the rotor (not shown) with the rotor blades is inserted into the lower housing half 21a.
  • the upper housing half 21b is rotated back into its original position and connected to the lower housing half 21a.
  • the guide vanes can also be installed without intermediate pieces, in which case recesses for receiving the bolts must then be provided in the correspondingly larger blade roots.
  • the number of bolts, and therefore the groups of Guide blades takes place according to the desired division of play and based on the manufacturing tolerances.
  • the design of the bolts is arbitrary.
  • the groups can also have a different number of guide vanes among one another. Of course, a multiple division of the housing is also possible, the number of termination groups then increasing.
  • the end group can also be connected by methods other than screwing and pinning.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP95810613A 1994-10-14 1995-10-03 Compresseur Expired - Lifetime EP0707150B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4436731A DE4436731A1 (de) 1994-10-14 1994-10-14 Verdichter
DE4436731 1994-10-14

Publications (3)

Publication Number Publication Date
EP0707150A2 true EP0707150A2 (fr) 1996-04-17
EP0707150A3 EP0707150A3 (fr) 1998-01-07
EP0707150B1 EP0707150B1 (fr) 2002-08-28

Family

ID=6530758

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810613A Expired - Lifetime EP0707150B1 (fr) 1994-10-14 1995-10-03 Compresseur

Country Status (5)

Country Link
US (1) US5575621A (fr)
EP (1) EP0707150B1 (fr)
JP (1) JP4043537B2 (fr)
CN (1) CN1057820C (fr)
DE (2) DE4436731A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1674734A1 (fr) * 2004-12-21 2006-06-28 ALSTOM Technology Ltd Méthode d' amélioration de la stabilité de courant d' une turbomachine
WO2008101473A1 (fr) * 2007-02-24 2008-08-28 Mtu Aero Engines Gmbh Compresseur et turbine à gaz
EP2163728A2 (fr) * 2008-09-11 2010-03-17 General Electric Company Tige de charge pour un stator à base carrée de compresseur et procédé d'utilisation
EP1965028A3 (fr) * 2007-02-27 2010-11-24 General Electric Company Appareil pour assembler des cales d' aubes
FR2948736A1 (fr) * 2009-07-31 2011-02-04 Snecma Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19643716A1 (de) * 1996-10-23 1998-04-30 Asea Brown Boveri Schaufelträger für einen Verdichter
DE59906856D1 (de) 1999-02-12 2003-10-09 Alstom Switzerland Ltd Befestigung von Laufschaufeln einer Strömungsmachine
EP1548232A1 (fr) * 2003-12-23 2005-06-29 Siemens Aktiengesellschaft Turbomachine avec un stator et procédé de fixation d'aubes statoriques dans le stator
JP5980405B1 (ja) * 2015-12-24 2016-08-31 三菱日立パワーシステムズ株式会社 翼の取外方法、この方法を実行するための装置及び治具、この装置を備える翼セット

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190326455A (en) * 1903-12-03 1904-12-01 Warwick Machinery Co Ltd Improvements in and relating to Elastic Fluid Turbines.
US2247387A (en) * 1940-01-25 1941-07-01 Gen Electric Elastic fluid turbine diaphragm supporting and centering arrangement
US2247423A (en) * 1940-01-25 1941-07-01 Gen Electric Elastic fluid turbine diaphragm supporting and centering arrangement
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
GB777955A (en) * 1954-07-06 1957-07-03 Ruston & Hornsby Ltd Improvements in or relating to fluid flow machines such as hydraulic, steam or gas turbines or axial-flow compressors
GB779060A (en) * 1954-08-26 1957-07-17 Rolls Royce Improvements in or relating to axial-flow compressors and turbines
US3300180A (en) * 1964-11-17 1967-01-24 Worthington Corp Segmented diaphragm assembly
DE2165529A1 (de) * 1971-12-30 1973-07-05 Kloeckner Humboldt Deutz Ag Einrichtung zum zentrieren und fixieren eines koerpers
US3817655A (en) * 1972-11-22 1974-06-18 Carrier Corp Stator blade mounting structure for turbomachines
DE3341871A1 (de) * 1983-11-19 1985-05-30 Brown, Boveri & Cie Ag, 6800 Mannheim Axialverdichter
US5022818A (en) * 1989-02-21 1991-06-11 Westinghouse Electric Corp. Compressor diaphragm assembly
CZ406592A3 (en) * 1992-01-08 1993-08-11 Alsthom Gec Drum rotor for steam action turbine and steam action turbine comprising such rotor
DE59205187D1 (de) * 1992-10-05 1996-03-07 Asea Brown Boveri Leitschaufeleinhängung für axialdurchströmte Turbomaschine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1674734A1 (fr) * 2004-12-21 2006-06-28 ALSTOM Technology Ltd Méthode d' amélioration de la stabilité de courant d' une turbomachine
WO2006067025A1 (fr) * 2004-12-21 2006-06-29 Alstom Technology Ltd Procede de modification d'un turbocompresseur
WO2008101473A1 (fr) * 2007-02-24 2008-08-28 Mtu Aero Engines Gmbh Compresseur et turbine à gaz
US8333553B2 (en) 2007-02-24 2012-12-18 Mtu Aero Engines Gmbh Compressor of a gas turbine
EP1965028A3 (fr) * 2007-02-27 2010-11-24 General Electric Company Appareil pour assembler des cales d' aubes
EP2163728A2 (fr) * 2008-09-11 2010-03-17 General Electric Company Tige de charge pour un stator à base carrée de compresseur et procédé d'utilisation
EP2163728A3 (fr) * 2008-09-11 2012-04-25 General Electric Company Tige de charge pour un stator à base carrée de compresseur et procédé d'utilisation
FR2948736A1 (fr) * 2009-07-31 2011-02-04 Snecma Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations
WO2011012679A3 (fr) * 2009-07-31 2011-04-21 Snecma Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations

Also Published As

Publication number Publication date
DE59510342D1 (de) 2002-10-02
EP0707150A3 (fr) 1998-01-07
JP4043537B2 (ja) 2008-02-06
EP0707150B1 (fr) 2002-08-28
JPH08177798A (ja) 1996-07-12
CN1129290A (zh) 1996-08-21
DE4436731A1 (de) 1996-04-18
CN1057820C (zh) 2000-10-25
US5575621A (en) 1996-11-19

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