EP1836401B1 - Method for retrofitting a compressor - Google Patents

Method for retrofitting a compressor 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
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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
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German (de)
French (fr)
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EP1836401A1 (en
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
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Alstom Technology AG
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Priority to EP06707706.5A priority Critical patent/EP1836401B1/en
Publication of EP1836401A1 publication Critical patent/EP1836401A1/en
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    • 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)

Description

Technisches GebietTechnical area

Die Erfindung betrifft ein Verfahren zur Modifikation eines mehrstufigen Verdichters gemäss dem Patentanspruch 1. Weiterhin betrifft sie einen gemäss dem angegebenen Verfahren modifizierten Verdichter sowie eine Gasturbogruppe, welche einen so modifizierten Verdichter umfasst.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.

Stand der TechnikState of the art

Eine Modifikation von Turboverdichtern kann erfolgen, indem der Schaufelwinkel von Schaufelreihen bei konstantem Profil der Schaufelblätter verändert wird. Der Schaufelwinkel wird dabei üblicherweise als der Winkel definiert, den die Sehne des Profils mit der Umfangsrichtung des Verdichters einschliesst. Durch diese Möglichkeit der Veränderung der Geometrie eines Schaufelgitters kann beispielsweise der Massenstrom erhöht werden, ohne eine Neukonstruktion des Schaufelblattes zu erfordern. Dies wird beispielsweise bei verstellbaren Verdichterleitreihen und insbesondere bei einer verstellbaren Vorleitreihe eines Verdichters realisiert. Die Implementation einer Mehrzahl verstellbar Verdichterleitreihen ist jedoch vergleichsweise aufwendig.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. By this possibility of changing the geometry of a blade grid, for example, the mass flow can be increased without requiring a redesign of the airfoil. This is realized, for example, with adjustable Verdichterleitreihen and in particular with an adjustable Vorleitreihe a compressor. However, the implementation of a plurality of adjustable Verdichterleitreihen is relatively expensive.

Darstellung der ErfindungPresentation of the invention

Gemäss einem Aspekt der Erfindung soll nunmehr ein Verfahren zur Modifikation eines mehrstufigen Verdichters durch Umstaffelung von Schaufeln, also der Veränderung des Schaufelwinkels, angegebenen werden. Das Profil des Schaufelblattes bleibt erhalten. Gemäss einem spezifischeren Aspekt der Erfindung soll diese Möglichkeit angegeben werden, ohne verstellbare Schaufelreihen zu verwenden. Ein anderer Aspekt der Erfindung besteht darin, den Massenstrom des Verdichters zu erhöhen, in einer beispielhaften Ausführungsform um bis zu sechs Prozent gegenüber dem Verdichter vor der Modifikation. In einer spezielleren Ausführungsform soll die Erhöhung des Massenstroms erzielt werden, ohne die Strömungsstabilität im Verdichter zu vermindern oder aufgrund des erhöhten Massenstroms Strömungsblockierungen in Schaufelkanälen zu provozieren.According to one aspect of the invention, a method for modifying a multi-stage compressor by re-scaling blades, that is to say the change of the blade angle, will now be given. The profile of the airfoil is retained. According to a more specific aspect of the invention, this possibility should be given without using adjustable blade rows. Another aspect of the invention is to increase the mass flow of the compressor increase, in an exemplary embodiment, by up to six percent over the compressor prior to modification. In a more specific embodiment, the increase in the mass flow should be achieved without reducing the flow stability in the compressor or due to the increased mass flow to provoke flow blockages in the blade channels.

Das in Anspruch 1 beschriebene Verfahren vermag, neben anderen vorteilhaften Wirkungen, die oben aufgestellten Forderungen zu erfüllen.The method described in claim 1 is capable, among other advantageous effects, of meeting the requirements set forth above.

Das Verfahren umfasst, die Laufschaufeln der ersten Verdichterlaufreihe gegen veränderte Laufschaufeln auszutauschen, welche gegenüber den ursprünglich eingebauten Laufschaufeln ein identisches Schaufelblattprofil und einen demgegenüber verschiedenen Schaufelwinkel aufweisen. Derart kann das Schluckvermögen der ersten Verdichterlaufreihe vergrössert und insbesondere in Verbindung mit einer verstellbaren Vorleitreihe der Verdichtermassenstrom erhöht werden. Einer mit der veränderten Geometrie des Schaufelgitters einhergehenden potenziell verschlechterten Strömungsstabilität wird entgegengewirkt, indem weiterhin der Schaufelwinkel wenigstens einer weiter stromab und insbesondere stromab der zweiten Verdichterstufe angeordneten Schaufelreihe verändert wird. Dazu werden die Schaufeln der wenigstens einen weiteren Schaufelreihe gegen veränderte Schaufeln ausgetauscht, welche ein identisches Schaufelblattprofil aufweisen wie die ursprünglichen Schaufeln, und deren Schaufelwinkel von dem der ursprünglichen Schaufeln verschieden ist. In einer Ausführungsform der Erfindung ist die Veränderung des Schaufelwinkels in der weiteren Schaufelreihe gleichsinnig wie die Veränderung des Schaufelwinkels in der ersten Verdichterlaufreihe, das heisst, wenn der Schaufelwinkel der ersten Verdichterlaufreihe vergrössert wird, wird auch der Schaufelwinkel der weiteren Schaufelreihe vergrössert, und, wenn der Schaufelwinkel der ersten Verdichterlaufreihe verkleinert wird, wird auch der Schaufelwinkel der weiteren Schaufelreihe verkleinert. Eine Ausführungsform der Erfindung zeichnet sich dadurch aus, dass die Schaufelgeometrie der Leitreihe der ersten Verdichterstufe unverändert beibehalten wird, dass also weder das Schaufelblattprofil noch der Schaufelwinkel verändert werden.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. In this way, 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. For this purpose, 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. In one embodiment of the invention, 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.

Unter einer Verdichterstufe ist dabei die Anordnung einer Verdichterlaufreihe und einer stromab folgenden Verdichterleitreihe zu verstehen. Dies ist im Gegensatz zu einer Turbinenstufe zu verstehen, welche eine Leitreihe mit einer stromab davon angeordneten Laufreihe umfasst. Eine Laufreihe umfasst einen Schaufelkranz oder ein Schaufelgitter, welches eine Mehrzahl von Laufschaufeln umfasst. Diese werden auch als Rotorkomponenten, beispielsweise Rotorbeschaufelung, Rotorschaufelkranz, oder Rotorschaufelgitter und dergleichen bezeichnet. Eine Leitreihe umfasst einen Schaufelkranz oder ein Schaufelgitter, welches eine Mehrzahl von Leitschaufeln umfasst. Diese werden auch als Statorkomponenten, beispielsweise Statorbeschaufelung, Statorschaufelkranz, oder Statorschaufelgitter und dergleichen bezeichnet.Under a compressor stage is to understand the arrangement of a compressor run series and a downstream Verdichterleitreihe. 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.

Eine Weiterbildung des hier angegebenen Verfahrens umfasst, die Laufschaufeln der zweiten Verdichterlaufreihe gegen veränderte Laufschaufeln auszutauschen, welche ein identisches Schaufelblattprofil aufweisen wie die ursprünglichen Laufschaufeln, und deren Schaufelwinkel von dem der ursprünglichen Laufschaufeln verschieden ist. Eine Ausführungsform dieser Weiterbildung umfasst, die Schaufelgeometrie der Leitreihe der zweiten Verdichterstufe unverändert beizubehalten.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.

Weiterbildungen des hier beschriebenen Verfahrens umfassen, in wenigstens einer stromab der zweiten Verdichterstufe angeordneten Verdichterstufe sowohl die Schaufeln der Laufreihe als auch die Schaufeln der Leitreihe gegen veränderte Schaufeln auszutauschen, welche ein identisches Schaufelblattprofil aufweisen wie die ursprünglichen Schaufeln, und deren Schaufelwinkel von dem der ursprünglichen Schaufeln verschieden ist, und/oder die Schaufeln wenigstens einer Schaufelreihe jeder stromab der zweiten Verdichterstufe angeordneten Verdichterstufe gegen veränderte Schaufeln auszutauschen, welche ein identisches Schaufelblattprofil aufweisen wie die ursprünglichen Schaufeln, und deren Schaufelwinkel von dem der ursprünglichen Schaufeln verschieden ist.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.

In einer Ausführungsform des Verfahrens werden die Schaufelwinkel in den Schaufelreihen, deren Schaufeln gegen veränderte Schaufeln ausgetauscht werden, derart aufeinander angepasst, dass der relative Enthalpieaufbau, bezogen auf den gesamten Enthalpieaufbau im Verdichter, in den einzelnen Verdichterstufen und/oder in den einzelnen Schaufelreihen gegenüber dem nicht modifizierten Verdichter im Wesentlichen konstant gehalten wird. Damit ist es möglich, den Massenstrom des Verdichters zu verändern, und dabei die Stabilitätsreserve gegen einen Strömungsabriss im Wesentlichen unverändert beizubehalten.In one embodiment of the method, 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. Thus, it is possible to change the mass flow of the compressor, while maintaining the stability reserve against stall substantially unchanged.

Eine Vergrösserung des Schaufelwinkels, der als der Winkel definiert ist, den die Sehne des Schaufelblattprofils mit der Umfangsrichtung des Verdichters einschliesst, resultiert im Allgemeinen in einer Vergrösserung des Massenstroms. Eine Anwendung des hier beschriebenen Verfahrens, bei dem ursprünglich eingebaute Schaufeln gegen veränderte Schaufeln ausgetauscht werden, bei denen die Sehnen der Schaufelblattprofile stärker in Richtung der Verdichterachse orientiert sind als bei den ursprünglich eingebauten Schaufeln, resultiert demnach in einer Anwendung des Verfahrens zur Erhöhung des Verdichtermassenstroms. Mit einer beispielhaften Ausführungsform des Verfahrens lässt sich eine Erhöhung des Verdichtermassenstroms um bis zu sechs Prozent erreichen, ohne dass die Stabilitätsreserve des Verdichters wesentlich verändert wird.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 application of the method described herein, in which originally installed blades are replaced by modified blades, in which the chords of the airfoils are oriented more towards the compressor axis than the originally installed blades, thus resulting in an application of the method for increasing the compressor mass flow. With an exemplary embodiment of the method, an increase in the compressor mass flow can be achieved by up to six percent without substantially changing the stability reserve of the compressor.

Die oben beschriebenen Ausgestaltungen des Verfahrens können selbstverständlich untereinander kombiniert werden.The above-described embodiments of the method can of course be combined with each other.

Die Erfindung umfasst weiterhin einen Verdichter, welcher mittels dem oben beschriebenen Verfahren modifiziert ist. Ein solcher Verdichter umfasst insbesondere wenigstens zwei axiale Verdichterstufen, und in einer spezifischeren Ausführungsform handelt es sich um einen rein axialen mehrstufigen Verdichter. Mehrstufige rein axiale Turboverdichter finden beispielsweise als Verdichter von Gasturbogruppen Verwendung; insofern umfasst die Erfindung auch eine Gasturbogruppe, welche einen mit einem oben beschriebenen Verfahren modifizierten Verdichter aufweist.The invention further comprises a compressor modified by the method described above. In particular, such a compressor comprises at least two axial compressor stages, and in a more specific embodiment it is a purely axial multi-stage compressor. Multi-stage purely axial turbocompressors are used, for example, as compressors of gas turbine groups; In this respect, the invention also includes a gas turbine group having a compressor modified by a method as described above.

Weitere vorteilhafte und zweckmässige Weiterbildungen der Erfindung erschliessen sich dem Fachmann im Lichte der Unteransprüche und des nachfolgend dargestellten Ausführungsbeispiels.Further advantageous and expedient developments of the invention will be apparent to those skilled in the light of the dependent claims and the embodiment illustrated below.

Kurze Beschreibung der ZeichnungShort description of the drawing

Das oben angegebene Verfahren wird nachfolgend anhand eines in der Zeichnung illustrierten Ausführungsbeispiels näher erläutert. Im Einzelnen zeigen

  • Figur 1 eine Gasturbogruppe;
  • Figur 2 Details eines mehrstufigen Axialverdichters; und
  • Figur 3 Details eines modifizierten mehrstufigen Axialverdichters.
The above-mentioned method is explained in more detail below with reference to an exemplary embodiment illustrated in the drawing. Show in detail
  • FIG. 1 a gas turbine group;
  • FIG. 2 Details of a multi-stage axial compressor; and
  • FIG. 3 Details of a modified multi-stage axial compressor.

Für das Verständnis der Erfindung nicht wesentliche Einzelheiten sind weggelassen worden. Das Ausführungsbeispiel und die Zeichnung sollen dem besseren Verständnis des oben beschriebenen Verfahrens dienen, und sollen nicht zur Einschränkung der in den Ansprüchen gekennzeichneten Erfindung herangezogen werden.Details that are not essential to understanding the invention have been omitted. The embodiment and the drawing are intended to better understand the method described above, and are not to be used to limit the invention characterized in the claims.

Wege zur Ausführung der ErfindungWays to carry out the invention

In der Figur 1 ist eine Gasturbogruppe 100 dargestellt Diese umfasst einen mehrstufigen axialen Turboverdichter 101, eine Brennkammer 102 und eine Turbine 103. Die Welle 111 der Gasturbogruppe ist mit einem Generator 104 antriebsverbunden. Der Verdichter 101 umfasst ein Gehäuse, in welchem die statischen Bauteile des Verdichters angeordnet sind, sowie die Welle 111, auf welcher die Rotorkomponenten angeordnet sind. Der beispielhaft und vereinfacht dargestellte Verdichter umfasst eine Vorleitreihe IGV, welche mit verstellbaren Leitschaufeln ausgestattet sein kann, sowie zehn Verdichterstufen 1 bis 10. Die Anzahl der Verdichterstufen stellt hierbei keine Einschränkung dar; die Turboverdichter moderner Gasturbogruppen weisen üblicherweise eine höhere Stufenzahl von beispielsweise 10 bis 22 auf. Für eine Illustration der Erfindung ist die Darstellung mit zehn Verdichterstufen jedoch ausreichend und übersichtlicher. Die Durchströmungsrichtung des Verdichters ist in der Zeichnung von links nach rechts. Die erste Verdichterstufe umfasst eine auf der Welle angeordnete Laufschaufelreihe LA1 und eine stromab davon im Gehäuse angeordnete Leitschaufelreihe LE1. Alle weiteren Verdichterstufen umfassen ebenfalls jeweils eine Laufschaufelreihe mit einer stromab davon angeordneten Leitschaüfelreihe. Auf an sich bekannte Weise umfasst jede Schaufelreihe eine Mehrzahl von Schaufeln, von denen jede auf ebenfalls an sich bekannte Weise einen Schaufelfuss und ein Schaufelblatt aufweist.In the FIG. 1 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 Vorleitreihe 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 Leitschaüfelreihe arranged downstream thereof. In a manner known per se, 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.

Die Figur 2 zeigt Details eines beispielhaften Verdichters, wie er beispielsweise in der Gasturbogruppe aus Figur 1 Verwendung findet, im ursprünglichen Zustand, das heisst vor einer Modifikation mit dem angegebenen Verfahren. Dargestellt sind die ersten beiden Verdichterstufen, umfassend die Laufreihe LA1 und die Leitreihe LE1 sowie die Laufreihe LA2 und die Leitreihe LE2. Weiterhin dargestellt ist eine beliebige stromab der zweiten Verdichterstufe angeordnete Verdichterstufe N mit der Laufreihe LAN und der Leitreihe LEN. Die Schaufelblätter sind mit 121, 122, 123, 124, 125, und 126 bezeichnet. In einer Ansicht von radial aussen sind die Schaufelbtattprofile zu erkennen, sowie der Schaufelwinkel, welcher als der Winkel definiert ist, welche die Sehne des Schaufelblattprofils mit der Umfangsrichtung des Verdichters einschliesst. Der Schaufelwinkel der Schaufeln 121 der ersten Laufreihe LA1 ist mit B'10 bezeichnet. Der Schaufelwinkel der Schaufeln 122 der ersten Leitreihe LE1 ist mit B"10 bezeichnet. Der Schaufelwinkel der Schaufeln 123 der zweiten Laufreihe LA2 ist mit B'20 bezeichnet. Der Schaufelwinkel der Schaufeln 124 der zweiten Leitreihe LE2 ist mit B"20 bezeichnet. Der Schaufelwinkel der Schaufeln 125 der Laufreihe LAN ist mit B'N0 bezeichnet. Der Schaufelwinkel der Schaufeln 126 der Leitreihe LEN ist mit B"N0 bezeichnet.The 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 .

In der Figur 3 ist der Verdichter aus Figur 2 dargestellt, welcher mit dem beschriebenen Verfahren modifiziert wurde. Die Schaufelblattprofile der Schaufeln in den dargestellten Schaufelreihen sind identisch. Ebenso ist der Schaufelwinkel in den Leitreihen LE1 der ersten und LE2 der zweiten Verdichterstufe beibehalten worden. Hingegen wurde der Schaufelwinkel in der ersten Laufreihe LA1 von B'10 auf B'11 vergrössert. Der Schaufelwinkel der zweiten Laufreihe LA2 wurde von B'20 auf B'21 vergrössert. Die Profilsehnen sind in diesen beiden Laufreihen nunmehr stärker in Richtung der Achse des Verdichters orientiert. Damit wird der Versperrungsgrad der jeweiligen Schaufelgitter vermindert, woraus eine Erhöhung des Verdichtermassenstroms resultiert. In der Laufreihe LAN und der Leitreihe LEN sind die Schaufelwinkel ebenfalls von B'N0 und B"N0 auf B'N1 und B"N1 vergrössert; die Schaufelblattprofile sind jeweils identisch beibehalten. Diese Modifikation kann auch in anderen, nicht dargestellten Schaufelreihen des Verdichters vorgenommen sein. Es ist dabei nicht notwendig, immer die Schaufelwinkel der Laufreihe und der Leitreihe einer Stufe zu verändern; ebenso kann in einer Stufe nur der Schaufelwinkel entweder der Laufreihe oder der Leitreihe verändert sein. Die Modifikation von stromab der zweiten Verdichterstufe angeordneten Schaufelreihen bewirkt, dass einerseits keine Strömungsblockierung in diesen Schaufelreihen aufgrund des vergrösserten Massenstroms auftritt, und andererseits, dass der Enthalpieaufbau des Verdichters nicht überproportional in die erste und zweite Laufreihe verschoben wird, was andernfalls die Stabilitätsreserve gegen einen Strömungsabriss in den Schaufelgittern der ersten und der zweiten Laufreihe vermindern würde.In the 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. Likewise, the blade angle has been retained in the guide rows LE1 of the first and LE2 of the second compressor stage. On the other hand, 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. Thus, the degree of locking of the respective blade grid is reduced, resulting in an increase of the compressor mass flow. In the LAN and LEN series, 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. The modification of rows of blades arranged downstream of the second compressor stage causes, on the one hand, no flow blocking in these rows of blades due to the increased mass flow, and on the other hand, that the Enthalpieaufbau of the compressor is not disproportionately moved in the first and second rows, what otherwise, the stability reserve against stalling in the airfoils of the first and second rows of flights would be reduced.

Obschon nicht explizit erwähnt, ist für den Fachmann offensichtlich, dass die oben gemachten Darstellungen analog für Verdichterbeschaufelungen anwendbar sind, bei denen die Schaufelblattprofile über der Schaufelhöhe veränderlich sind und insbesondere auch für den Fachmann geläufige verwundene Schaufeln; die Darstellungen in den Figuren 2 und 3 beziehen sich dann auf einen Umfangsschnitt.Although not explicitly mentioned, it will be apparent to those skilled in the art that the above illustrations are analogously applicable to compressor blades in which the airfoils are variable over the blade height and in particular also twisted blades familiar to those skilled in the art; the representations in the FIGS. 2 and 3 then refer to a circumferential section.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

00
Vorleitreiheguide row
11
erste Verdichterstufefirst compressor stage
22
zweite Verdichterstufesecond compressor stage
33
dritte Verdichterstufethird compressor stage
44
vierte Verdichterstufefourth compressor stage
55
fünfte Verdichterstufefifth compressor stage
66
sechste Verdichterstufesixth compressor stage
77
siebte Verdichterstufeseventh compressor stage
88th
achte Verdichterstufeeighth compressor stage
99
neunte Verdichterstufeninth compressor stage
1010
zehnte Verdichterstufetenth compressor stage
100100
GasturbogruppeGas turbine group
101101
Verdichtercompressor
102102
Brennkammercombustion chamber
103103
Turbineturbine
104104
Generatorgenerator
111111
Wellewave
112112
Gehäusecasing
121121
Schaufelblatt der ersten LaufreiheBlade of the first row
122122
Schaufelblatt der ersten LeitreiheBlade of the first guide row
123123
Schaufelblatt der zweiten LaufreiheAirfoil of the second series
124124
Schaufelblatt der zweiten LeitreiheAirfoil of the second guide row
125125
Schaufelblatt der Laufreihe NBlade of the row N
126126
Schaufelblatt der Leitreihe NAirfoil of the Leitreihe N
IGVIGV
Vorleitreiheguide row
LA1LA1
Laufreihe der ersten VerdichterstufeRunning row of the first compressor stage
LE1LE1
Leitreihe der ersten VerdichterstufeGuide row of the first compressor stage
LA2LA2
Laufreihe der zweiten VerdichterstufeRun row of the second compressor stage
LE2LE2
Leitreihe der zweiten VerdichterstufeGuide row of the second compressor stage
LA3LA3
Laufreihe der dritten VerdichterstufeRun row of the third compressor stage
LE3LE3
Leitreihe der dritten VerdichterstufeGuide row of the third compressor stage
LA4LA4
Laufreihe der vierten VerdichterstufeRun row of the fourth compressor stage
LE4LE4
Leitreihe der vierten VerdichterstufeLeitreihe the fourth compressor stage
LA5LA5
Laufreihe der fünften VerdichterstufeRun row of the fifth compressor stage
LE5LE5
Leitreihe der fünften VerdichterstufeGuide row of the fifth compressor stage
LA6LA6
Laufreihe der sechsten VerdichterstufeRun series of the sixth compressor stage
LE6LE6
Leitreihe der sechsten VerdichterstufeGuide row of the sixth compressor stage
LA7LA7
Laufreihe der siebten VerdichterstufeRun series of the seventh compressor stage
LE7LE7
Leitreihe der siebten VerdichterstufeLeitreihe of the seventh compressor stage
LA8LA8
Laufreihe der achten VerdichterstufeRun series of the eighth compressor stage
LE8LE8
Leitreihe der achten VerdichterstufeGuide row of the eighth compressor stage
LA9LA9
Laufreihe der neunten VerdichterstufeSeries of the ninth compressor stage
LE9LE9
Leitreihe der neunten VerdichterstufeGuide to the ninth compressor stage
LA10LA10
Laufreihe der zehnten VerdichterstufeRun row of the tenth compressor stage
LE10LE10
Leitreihe der zehnten VerdichterstufeLeitreihe of the tenth compressor stage
LANLAN
Laufreihe der Verdichterstufe NSeries of the compressor stage N
LENLEN
Leitreihe der Verdichterstufe NGuide row of the compressor stage N
B'10 B '10
ursprünglicher Schaufelwinkel in der ersten Laufreiheoriginal bucket angle in the first run row
B'11 B '11
geänderter Schaufelwinkel in der ersten Laüfreihechanged bucket angle in the first Laüfreihe
B"10 B " 10
ursprünglicher Schaufelwinkel in der ersten Leitreiheoriginal bucket angle in the first guide row
B'20 B '20
ursprünglicher Schaufelwinkel in der zweiten Laufreiheoriginal bucket angle in the second run row
B'21 B '21
geänderter Schaufelwinkel in der zweiten Laufreihechanged bucket angle in the second run row
B"20 B " 20
ursprünglicher Schaufelwinkel in der zweiten Leitreiheoriginal bucket angle in the second guide row
B'N0 B ' N0
ursprünglicher Schaufelwinkel in der Laufreihe der Stufe Noriginal bucket angle in the N series course
B'N1 B ' N1
geänderter Schaufelwinkel in der Laufreihe der Stufe Nchanged blade angle in the row of stages N level
B"N0 B " N0
ursprünglicher Schaufelwinkel in der Leitreihe der Stufe Noriginal bucket angle in the N series guide row
B"N1 B " N1
geänderter Schaufelwinkel in der Leitreihe der Stufe Nchanged bucket angle in the guide row of the stage N

Claims (11)

  1. Method for increasing the absorption capacity in a multistage compressor (101), the compressor comprising moving blades of a first compressor moving blade row (LA1) with a defined blade leaf profile (121), and these moving blades having a predetermined blade angle (B'10) in the flow-on direction, and the blades of at least one further blade row (LAN, LEN) arranged downstream of the second compressor stage having a defined blade leaf profile (125, 126) and, in the flow-on direction, a predetermined blade angle (B'NO, B"NO), characterized in that the compressor moving blade row (LA1) and at least one of the further blade rows (LAN, LEN) arranged downstream of the second compressor stage are realized, in the case of unchanged blade leaf profiles (121, 125, 126), with a different blade angle (B'11, B'N1. B"N11), as compared with the predetermined blade angles (B'10, B'NO, B"NO), and in that the blade angles (B'N1, B"N1) of the further blade rows (LAN, LEN) are adapted as a function of the blade angle (B'11), modified for a greater absorption capacity, of the first compressor moving blade row (LA1).
  2. Method according to Claim 1, characterized in that the blade geometry of the guide blade row (LE1) of the first compressor stage is maintained unchanged.
  3. Method according to either one of Claims 1 or 2, characterized in that the moving blades of the second compressor moving blade row (LA2) are exchanged for modified moving blades which have an identical blade leaf profile (122) to the original moving blades and the blade angle (B'21) of which is different from the blade angle (B'20) of the original moving blades.
  4. Method according to Claim 3, characterized in that the blade geometry of the guide blade row (LE2) of the second compressor stage is maintained unchanged.
  5. Method according to one of the preceding claims, the further blade row being a moving blade row (LAN).
  6. Method according to one of the preceding claims, the further blade row being a guide blade row (LEN).
  7. Method according to one of the preceding claims, characterized in that, in at least one compressor stage arranged downstream of the second compressor stage, both the blades of the moving blade row and the blades of the guide blade row are exchanged for modified blades which have an identical blade leaf profile to the original blades and the blade angle of which is different from that of the original blades.
  8. Method according to one of the preceding claims, characterized in that the blades of at least one blade row of each compressor stage arranged downstream of the second compressor stage are exchanged for modified blades which have an identical blade leaf profile to the original blades and the blade angle of which is different from that of the original blades.
  9. Method according to one of the preceding claims, characterized in that the blade angles in the blade rows, the blades of which are exchanged for modified blades, are coordinated with one another in such a way that the relative enthalpy build-up in the individual compressor stages is kept essentially constant.
  10. Method according to one of the preceding claims, characterized in that the blade angle of the modified blades is greater than the blade angle of the original blades, in such a way that the chords of the blade leaf profiles of the modified blades are oriented to a greater extent in the direction of the compressor axis as a function of the increased mass flow.
  11. Method according to one of the preceding claims for increasing the compressor mass flow.
EP06707706.5A 2005-01-14 2006-01-12 Method for retrofitting a compressor Not-in-force EP1836401B1 (en)

Priority Applications (1)

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EP05100201A EP1681472A1 (en) 2005-01-14 2005-01-14 Method for retrofitting a compressor
PCT/EP2006/050172 WO2006075014A1 (en) 2005-01-14 2006-01-12 Method for modifying a multistage compressor
EP06707706.5A EP1836401B1 (en) 2005-01-14 2006-01-12 Method for retrofitting a compressor

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WO2003027461A1 (en) * 2001-09-24 2003-04-03 Alstom Technology Ltd Gas turbine system for working fluid in the form of a carbon dioxide/water mixture
TWI397634B (en) * 2010-12-06 2013-06-01 China Steel Corp On-line monitor method of multi-stage compressor
CN104763475B (en) * 2015-03-28 2016-09-14 中国船舶重工集团公司第七�三研究所 Three spool turbine
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
US9759227B2 (en) 2015-09-04 2017-09-12 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
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
US10041370B2 (en) 2015-09-04 2018-08-07 General Electric Company Airfoil shape for a compressor
US9745994B2 (en) 2015-09-04 2017-08-29 General Electric Company Airfoil shape for a compressor
US9732761B2 (en) 2015-09-04 2017-08-15 General Electric Company Airfoil shape for a compressor
US9771948B2 (en) 2015-09-04 2017-09-26 General Electric Company Airfoil shape for a compressor

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TWI364490B (en) 2012-05-21
TW200637965A (en) 2006-11-01
WO2006075014A1 (en) 2006-07-20
US20080260516A1 (en) 2008-10-23
US7753649B2 (en) 2010-07-13
EP1681472A1 (en) 2006-07-19

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