EP1836401B1 - Méthode pour modifier un compresseur multi-étages - Google Patents

Méthode pour modifier un compresseur multi-étages Download PDF

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Publication number
EP1836401B1
EP1836401B1 EP06707706.5A EP06707706A EP1836401B1 EP 1836401 B1 EP1836401 B1 EP 1836401B1 EP 06707706 A EP06707706 A EP 06707706A EP 1836401 B1 EP1836401 B1 EP 1836401B1
Authority
EP
European Patent Office
Prior art keywords
blade
blades
compressor
row
moving
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
EP06707706.5A
Other languages
German (de)
English (en)
Other versions
EP1836401A1 (fr
Inventor
Marco Micheli
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 Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP06707706.5A priority Critical patent/EP1836401B1/fr
Publication of EP1836401A1 publication Critical patent/EP1836401A1/fr
Application granted granted Critical
Publication of EP1836401B1 publication Critical patent/EP1836401B1/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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/601—Assembly methods using limited numbers of standard modules which can be adapted by machining
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49236—Fluid pump or compressor making
    • Y10T29/49238—Repairing, converting, servicing or salvaging

Definitions

  • the invention relates to a method for modifying a multi-stage compressor according to claim 1. Furthermore, it relates to a modified according to the specified method compressor and a gas turbine group, which comprises a so modified compressor.
  • a modification of turbocompressors can be done by changing the blade angle of blade rows with a constant profile of the blades.
  • the blade angle is usually defined as the angle that encloses the chord of the profile with the circumferential direction of the compressor.
  • the method described in claim 1 is capable, among other advantageous effects, of meeting the requirements set forth above.
  • the method comprises exchanging the blades of the first compressor barrel row for changed blades, which have an identical blade profile and a blade angle that is different compared to the originally installed blades.
  • the absorption capacity of the first compressor run series can be increased and, in particular, the compressor mass flow can be increased in conjunction with an adjustable preliminary guide row.
  • a potentially deteriorated flow stability associated with the changed geometry of the blade lattice is counteracted by further varying the blade angle of at least one row of blades further downstream and more particularly downstream of the second compressor stage.
  • the blades of the at least one further row of blades are replaced by modified blades which have an identical airfoil profile as the original blades, and whose blade angle is different from that of the original blades.
  • the change of the blade angle in the further blade row is in the same direction as the change of the blade angle in the first compressor barrel row, that is, if the blade angle of the first compressor barrel row is increased, also the blade angle of the further blade row is increased, and if the Shovel angle of the first compressor run series is reduced, also the blade angle of the other blade row is reduced.
  • An embodiment of the The invention is characterized in that the blade geometry of the guide row of the first compressor stage is maintained unchanged, so that neither the blade airfoil nor the blade angle are changed.
  • a compressor stage is to understand the arrangement of a compressor run series and a downstream Ver Whyrleit plin. This is to be understood in contrast to a turbine stage which comprises a guide row with a row of nozzles arranged downstream thereof.
  • a row of flights comprises a blade ring or a blade grid, which comprises a plurality of rotor blades. These are also referred to as rotor components, for example rotor blading, rotor blade ring, or rotor blade grille and the like.
  • a guide row comprises a blade ring or a blade grid, which comprises a plurality of guide vanes. These are also referred to as stator components, such as stator blading, stator blade ring, or stator blade grid, and the like.
  • a further development of the method specified here comprises exchanging the blades of the second compressor barrel row for changed blades, which have an identical airfoil profile as the original rotor blades, and whose blade angle is different from that of the original rotor blades.
  • An embodiment of this development comprises maintaining the blade geometry of the guide row of the second compressor stage unchanged.
  • Developments of the method described here include, in at least one compressor stage arranged downstream of the second compressor stage, exchanging both the blades of the rotor row and the blades of the guide row for changed blades which have an identical airfoil profile as the original blades and whose blade angle is that of the original one Shovels is different, and / or the blades of at least one row of blades each downstream of the second compressor stage arranged compressor stage to replace changed blades having an identical airfoil profile as the original blades, and their blade angle is different from that of the original blades.
  • the blade angles in the rows of blades whose blades are replaced by changed blades are adapted to each other such that the relative enthalpy buildup relative to the total enthalpy buildup in the compressor, in the individual compressor stages and / or in the individual blade rows, is different from that in FIG unmodified compressor is kept substantially constant.
  • An increase in the blade angle which is defined as the angle that the chord of the airfoil profile encloses with the circumferential direction of the compressor, generally results in an increase in the mass flow.
  • an increase in the compressor mass flow can be achieved by up to six percent without substantially changing the stability reserve of the compressor.
  • a gas turbine group 100 is illustrated. This includes a multi-stage axial turbocompressor 101, a combustor 102, and a turbine 103.
  • the gas turbine group shaft 111 is drive-connected to a generator 104.
  • the compressor 101 includes a Housing in which the static components of the compressor are arranged, and the shaft 111 on which the rotor components are arranged.
  • the compressor shown as an example and simplified comprises a Vorleit Herbert IGV, which may be equipped with adjustable vanes, and ten compressor stages 1 to 10.
  • the number of compressor stages here is not limiting;
  • the turbocompressors of modern gas turbine groups usually have a higher number of stages, for example 10 to 22. For an illustration of the invention, however, the representation with ten compressor stages is sufficient and clearer.
  • the flow direction of the compressor is in the drawing from left to right.
  • the first compressor stage comprises a blade row LA1 arranged on the shaft and a stator blade row LE1 arranged downstream thereof in the housing. All other compressor stages also each comprise a blade row with a Leitschaüfelsch arranged downstream thereof.
  • each row of blades comprises a plurality of blades, each of which has a blade root and an airfoil in a manner also known per se.
  • FIG. 2 shows details of an exemplary compressor, such as in the gas turbine group FIG. 1 Use, in its original state, that is before a modification with the specified method. Shown are the first two compressor stages, comprising the row LA1 and the guide row LE1, and the row LA2 and the row LE2. Furthermore, an arbitrary compressor stage N arranged downstream of the second compressor stage is shown with the row LAN and the row LEN.
  • the blades are labeled 121, 122, 123, 124, 125, and 126. In a view from radially outward, the blade shed profiles are discernible, as well as the blade angle, which is defined as the angle which encloses the chord of the airfoil profile with the circumferential direction of the compressor.
  • the blade angle of the blades 121 of the first Blade row LA1 is designated B '10th
  • the blade angle of the blades 122 of the first stator row LE1 is "means the 10th of the blade angle of the blades 123 of the second blade row LA2 is designated B '20th of the blade angle of the blades 124 of the second stator row LE2 is connected to B" denoted by B twentieth
  • the blade angle of the vanes 125 of the row LAN is denoted by B ' N0 .
  • the blade angle of the blades 126 of the guide row LEN is denoted by B " N0 .
  • FIG. 3 is the compressor off FIG. 2 which was modified by the method described.
  • the airfoil profiles of the blades in the illustrated blade rows are identical.
  • the blade angle has been retained in the guide rows LE1 of the first and LE2 of the second compressor stage.
  • the bucket angle in the first LA1 series has been increased from B '10 to B' 11 .
  • the bucket angle of the second row LA2 has been increased from B '20 to B' 21 .
  • the chords are now oriented more strongly in the direction of the axis of the compressor in these two rows of runs.
  • the degree of locking of the respective blade grid is reduced, resulting in an increase of the compressor mass flow.
  • the blade angles are also increased from B ' N0 and B " N0 to B' N1 and B" N1 ; the airfoil profiles are each kept identical.
  • This modification can also be made in other, not shown blade rows of the compressor. It is not necessary to always change the blade angles of the row and the guide row of a stage; Similarly, in one stage, only the blade angle of either the row of rows or the row of leaders may be changed.

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

Claims (11)

  1. Procédé pour l'augmentation de la capacité d'absorption d'un compresseur à plusieurs étages (101), le compresseur comprenant des aubes mobiles d'une première rangée mobile de compresseur (LA1) présentant un profil de pale d'aube déterminé (121), et ces aubes mobiles présentant un angle d'aube prédéfini (B'10) dans la direction d'arrivée d'écoulement, et les aubes d'au moins une rangée d'aubes supplémentaire (LAN, LEN) disposée en aval du deuxième étage de compresseur présentant un profil de pale d'aube déterminé (125, 126) et présentant un angle d'aube prédéfini (B'NO, B"NO) dans la direction d'arrivée d'écoulement, caractérisé en ce que la rangée mobile de compresseur (LA1) et au moins l'une des rangées d'aubes supplémentaires (LAN, LEN) disposée en aval du deuxième étage de compresseur sont réalisées de manière à présenter un angle d'aube différent (B'11, B'N1, B"N1) par rapport aux angles d'aube prédéfinis (B'10, B'NO, B"NO) en cas de profils de pale d'aube inchangés (121, 125, 126), et en ce que les angles d'aube (B'N1, B"N1) des rangées d'aubes supplémentaires (LAN, LEN) sont ajustés en fonction de l'angle d'aube (B'11), modifié pour obtenir une plus grande capacité d'absorption, de la première rangée mobile (LA1).
  2. Procédé selon la revendication 1, caractérisé par le fait de maintenir inchangée la géométrie d'aube de la rangée directrice (LE1) du premier étage de compresseur.
  3. Procédé selon la revendication 1 ou 2, caractérisé par le remplacement des aubes mobiles de la deuxième rangée mobile de compresseur (LA2) par des aubes mobiles modifiées, lesquelles présentent un profil de pale d'aube identique (122) à celui des aubes mobiles d'origine, et dont l'angle d'aube (B'21) est différent de l'angle d'aube (B'20) des aubes mobiles d'origine.
  4. Procédé selon la revendication 3, caractérisé par le fait de maintenir inchangée la géométrie d'aube de la rangée directrice (LE2) du deuxième étage de compresseur.
  5. Procédé selon l'une quelconque des revendications précédentes, dans lequel la rangée d'aubes supplémentaire est une rangée d'aubes mobiles (LAN).
  6. Procédé selon l'une quelconque des revendications précédentes, dans lequel la rangée d'aubes supplémentaire est une rangée d'aubes directrices (LEN).
  7. Procédé selon l'une quelconque des revendications précédentes, caractérisé par le remplacement, dans au moins un étage de compresseur disposé en aval du deuxième étage de compresseur, à la fois des aubes de la rangée mobile et des aubes de la rangée directrice par des aubes modifiées, lesquelles présentent un profil de pale d'aube identique à celui des aubes d'origine, et dont l'angle d'aube est différent de celui des aubes d'origine.
  8. Procédé selon l'une quelconque des revendications précédentes, caractérisé par le remplacement des aubes d'au moins une rangée d'aubes de chaque étage de compresseur disposé en aval du deuxième étage de compresseur par des aubes modifiées, lesquelles présentent un profil de pale d'aube identique à celui des aubes d'origine, et dont l'angle d'aube est différent de celui des aubes d'origine.
  9. Procédé selon l'une quelconque des revendications précédentes, caractérisé par l'adaptation les uns aux autres des angles d'aube dans les rangées d'aubes dont les aubes sont remplacées par des aubes modifiées, de telle sorte que l'augmentation d'enthalpie relative dans les étages de compresseur individuels soit maintenue essentiellement constante.
  10. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que l'angle d'aube des aubes modifiées est supérieur à l'angle d'aube des aubes d'origine, de telle sorte que les cordes des profils de pale d'aube des aubes modifiées soient orientées plus fortement en direction de l'axe de compresseur en fonction du débit massique accru.
  11. Procédé selon l'une quelconque des revendications précédentes pour l'augmentation du débit massique de compresseur.
EP06707706.5A 2005-01-14 2006-01-12 Méthode pour modifier un compresseur multi-étages Not-in-force EP1836401B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06707706.5A EP1836401B1 (fr) 2005-01-14 2006-01-12 Méthode pour modifier un compresseur multi-étages

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP05100201A EP1681472A1 (fr) 2005-01-14 2005-01-14 Méthode pour modifier un compresseur multi-étages
EP06707706.5A EP1836401B1 (fr) 2005-01-14 2006-01-12 Méthode pour modifier un compresseur multi-étages
PCT/EP2006/050172 WO2006075014A1 (fr) 2005-01-14 2006-01-12 Procede de modification d'un compresseur a plusieurs etages

Publications (2)

Publication Number Publication Date
EP1836401A1 EP1836401A1 (fr) 2007-09-26
EP1836401B1 true EP1836401B1 (fr) 2014-09-24

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ID=34938514

Family Applications (2)

Application Number Title Priority Date Filing Date
EP05100201A Withdrawn EP1681472A1 (fr) 2005-01-14 2005-01-14 Méthode pour modifier un compresseur multi-étages
EP06707706.5A Not-in-force EP1836401B1 (fr) 2005-01-14 2006-01-12 Méthode pour modifier un compresseur multi-étages

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP05100201A Withdrawn EP1681472A1 (fr) 2005-01-14 2005-01-14 Méthode pour modifier un compresseur multi-étages

Country Status (4)

Country Link
US (1) US7753649B2 (fr)
EP (2) EP1681472A1 (fr)
TW (1) TWI364490B (fr)
WO (1) WO2006075014A1 (fr)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003027461A1 (fr) * 2001-09-24 2003-04-03 Alstom Technology Ltd Systeme de turbine a gaz destine a un fluide de travail se presentant sous la forme d'un melange dioxyde de carbone/eau
TWI397634B (zh) * 2010-12-06 2013-06-01 China Steel Corp 多級壓縮機之線上監控方法
CN104763475B (zh) * 2015-03-28 2016-09-14 中国船舶重工集团公司第七�三研究所 三转子燃气轮机
US9777744B2 (en) 2015-09-04 2017-10-03 General Electric Company Airfoil shape for a compressor
US9957964B2 (en) 2015-09-04 2018-05-01 General Electric Company Airfoil shape for a compressor
US9759076B2 (en) 2015-09-04 2017-09-12 General Electric Company Airfoil shape for a compressor
US9746000B2 (en) 2015-09-04 2017-08-29 General Electric Company Airfoil shape for a compressor
US10041370B2 (en) 2015-09-04 2018-08-07 General Electric Company Airfoil shape for a compressor
US9732761B2 (en) 2015-09-04 2017-08-15 General Electric Company Airfoil shape for a compressor
US9951790B2 (en) 2015-09-04 2018-04-24 General Electric Company Airfoil shape for a compressor
US9938985B2 (en) 2015-09-04 2018-04-10 General Electric Company Airfoil shape for a compressor
US9759227B2 (en) 2015-09-04 2017-09-12 General Electric Company Airfoil shape for a compressor
US9771948B2 (en) 2015-09-04 2017-09-26 General Electric Company Airfoil shape for a compressor
US9745994B2 (en) 2015-09-04 2017-08-29 General Electric Company Airfoil shape for a compressor

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2705590A (en) * 1949-10-28 1955-04-05 Rolls Royce Multi-stage axial-flow compressors with adjustable pitch stator blades
US2990106A (en) * 1956-10-12 1961-06-27 English Electric Co Ltd Axial flow multi-stage compressors
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade
NL123379C (fr) * 1963-11-01
DE1503628B2 (de) * 1965-10-22 1974-06-27 Turbon Ventilatoren- Und Apparatebau Gmbh, 1000 Berlin Flügelrad
US4252498A (en) * 1978-03-14 1981-02-24 Rolls-Royce Limited Control systems for multi-stage axial flow compressors

Also Published As

Publication number Publication date
WO2006075014A1 (fr) 2006-07-20
TW200637965A (en) 2006-11-01
EP1681472A1 (fr) 2006-07-19
US20080260516A1 (en) 2008-10-23
TWI364490B (en) 2012-05-21
EP1836401A1 (fr) 2007-09-26
US7753649B2 (en) 2010-07-13

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