EP1689979A1 - Compressor rotor - Google Patents

Compressor rotor

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Publication number
EP1689979A1
EP1689979A1 EP04819680A EP04819680A EP1689979A1 EP 1689979 A1 EP1689979 A1 EP 1689979A1 EP 04819680 A EP04819680 A EP 04819680A EP 04819680 A EP04819680 A EP 04819680A EP 1689979 A1 EP1689979 A1 EP 1689979A1
Authority
EP
European Patent Office
Prior art keywords
rotor
heat accumulation
segments
heat
segment
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.)
Withdrawn
Application number
EP04819680A
Other languages
German (de)
French (fr)
Inventor
René Bachofner
Wolfgang Kappis
Kurt Rubischon
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
Publication of EP1689979A1 publication Critical patent/EP1689979A1/en
Withdrawn legal-status Critical Current

Links

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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins

Definitions

  • the present invention relates to the field of turbomachinery. It relates to a compressor with a rotor according to the preamble of the claim
  • High-pressure compressors as are used in particular in gas turbines for compressing the combustion air, comprise a multi-stage blading which consists of rotor blades and guide vanes arranged alternately in the axial direction.
  • the blades are attached to the rotatably mounted rotor.
  • the guide vanes are arranged between adjacent rotor blade rings on the inner housing of the compressor. The air that flows through the annular channel of the compressor, which is formed between the rotor and the inner housing, and is compressed in the process, heats up due to the compression.
  • heat accumulation elements are often arranged between adjacent rotor blade and guide blade rings, which form a circumferential protective ring (see, for example, DE-A1-198 08740). Since the heat accumulation segments each lie opposite the blade tips of the moving blades or guide blades and abut against them, they are significantly involved in the adjustment of the blade clearance. So that direct contact between the blade tips and the heat accumulation segments is prevented, cutting tools are arranged between the heat accumulation segments, which protrude above the heat accumulation segments and at the same time prevent displacement of the heat accumulation segments in the circumferential direction.
  • a rotor structure is very complex to manufacture and assemble.
  • the known heat accumulation segments 10 are designed as cup-shaped circular ring segments, which have a smooth outer surface 11 and on the underside of which two segment feet 12 with a hook-shaped cross section extending in the circumferential direction are formed.
  • a circumferential groove with two hooks extending over the entire circumference is provided between adjacent rotor blade rings in the rotor, behind which the heat accumulation segments are hooked with their segment feet.
  • Each of the heat accumulation segments is secured against shifting in the circumferential direction by a fastening pin (Fig. 3 and claim 4 of DE-A-1-196 15 549). In this case too, the backup provides everyone
  • Heat accumulation segments in the circumferential direction represent a considerable effort because the corresponding bores in the rotor and the heat accumulation segments inserted and the mounting pins must be installed. In addition, no provision is made in this case to set a predetermined play between the heat accumulation segments and the blade tips.
  • the object is achieved by the entirety of the features of claim 1.
  • the essence of the invention is not to secure each heat accumulation segment against displacement in the circumferential direction, but rather to equip only a subset of selected segments with appropriate securing means. As a result, a considerable reduction in the effort is achieved both in the manufacture and in the assembly.
  • the heat accumulation segments not equipped with securing means are also secured by the heat accumulation segments equipped with securing means.
  • the heat accumulation segments have segmented feet with a hook-shaped cross section, with which they are hooked in behind rotating rotor hooks formed on the rotor, and the securing means comprise a securing pin which extends in the axial direction through the segmented feet and rotor hooks, in particular the securing pin in the circumferential direction seen is arranged in the middle of the heat accumulation segment.
  • guide vanes are arranged in the area of the heat accumulation segments, which end with their blade tip on an outer surface of the heat accumulation segments, it is particularly advantageous with this type of securing if the outer surface of the heat accumulation segments is provided with an abrasion layer, which is applied when the blade tips of the guide vanes are ground the outer surfaces of the heat accumulation segments causes material removal at the blade tips.
  • FIG. 1 shows a perspective side view of a heat accumulation segment known per se, as is used in the context of the invention
  • Figure 2 is a partially sectioned view of the arrangement of the heat segments between adjacent rows of blades with securing means according to an embodiment of the invention.
  • Fig. 3 shows the section along the plane A-A of Fig. 2 and
  • FIG. 4 in a view comparable to FIG. 2 shows a heat accumulation segment according to the invention provided with an abrasion layer.
  • a preferred exemplary embodiment of the invention is based on a heat accumulation segment 10 of the type shown in FIG. 1, which is attached to the rotor between two rows of rotor blades by means of the segment feet 12 and with an outer surface 11 of the blade tips of the guide blades (16 in FIG. 4) arranged between the rows of rotor blades ) is opposite.
  • 2 shows the arrangement of the heat accumulation segments 10 on the rotor 13 between the rotor blades 14, 14 'of adjacent rotor blade rows.
  • a circumferential groove 21 is embedded in the rotor 13, in which two rotor hooks 19 run parallel in the circumferential direction (see also FIG. 4).
  • the heat accumulation segments 10 are hooked into these rotor hooks 19 with the segment feet 12, so that the outer surface 11 of the heat accumulation segments adjoins the platforms of the moving blades 14, 14 ′.
  • an axially oriented locking pin 15 in the form of a circular cylindrical bolt is provided, which is inserted through corresponding bores in the segment feet 12 and one of the rotor hooks 19.
  • the securing pin 15 is preferably arranged in the middle of the heat accumulation segment 10, as seen in the circumferential direction.
  • FIG. 3 shows that in the case of two adjacent heat accumulation segments, only the one (in FIG. 3 the right) heat accumulation segment is secured with a locking pin 15. All of the heat accumulation segments arranged between the two rows of blades 14 and 14 'together form a segmented heat accumulation ring, in which every second segment is secured with a locking pin 15 against "wandering" over the circumference.
  • the outer surface is fraught with an abrasion layer 18.
  • the abrasion layer 18 is made of a material that is harder than the material of the adjoining guide vanes 16. This ensures that the guide vanes 16 running over the abrasion layer 18 wear during the streaking on the heat accumulation segment 10, in which material is removed from the blade tip 20 in a removal area 17 , This prevents the surface on the heat accumulation segment 10 from being permanently heated by friction.

Abstract

A compressor comprises a rotor (13) which has several rotor blades (14, 14') which are arranged successively at a distance from each other in an axial direction. A plurality of heat-accumulating segments (10), which are detachably fixed to the rotor (13) in a successive manner in the direction of the periphery and which can be displaceably mounted in the direction of the periphery, are arranged between adjacent rows of rotor blades (14, 14') on the periphery of the rotor (13). Security means (15) are provided on the heat-accumulating segments (10). Said security means are used to secure the heat-exchanging segments against displacement in the direction of the periphery. Production and mounting of the inventive rotor are simplified by virtue of the fact that only one part of the heat-accumulating segments (10) is provided with said security means (15).

Description

BESCHREIBUNG DESCRIPTION
VERDICHTERROTORCOMPRESSOR ROTOR
TECHNISCHES GEBIETTECHNICAL AREA
Die vorliegende Erfindung bezieht sich auf das Gebiet der Turbomaschinen. Sie betrifft einen Verdichter mit einem Rotor gemäss dem Oberbegriff des AnspruchsThe present invention relates to the field of turbomachinery. It relates to a compressor with a rotor according to the preamble of the claim
1.1.
STAND DER TECHNIKSTATE OF THE ART
Hochdruckverdichter, wie sie insbesondere in Gasturbinen zur Verdichtung der Verbrennungsluft eingesetzt werden, umfassen eine mehrstufige Beschaufelung, die aus in axialer Richtung alternierend angeordneten Laufschaufeln und Leitschaufeln besteht. Die Laufschaufeln sind auf dem drehbar gelagerten Rotor befestigt. Die Leitschaufeln sind zwischen benachbarten Laufschaufelkränzen am inneren Gehäuse des Verdichters angeordnet Die Luft, die durch den zwischen Rotor und innerem Gehäuse gebildeten Ringkanal des Verdichters strömt und dabei komprimiert wird, erhitzt sich aufgrund der Kompression. Um den Rotor und das innere Gehäuse vor einer übermässigen thermischen Belastung durch die erhitzte Luft zu schützen, werden zwischen benachbarten Laufschaufel- und Leitschaufelkränzen häufig Wärmestauelemente angeordnet, die einen umlaufenden Schutzring bilden (siehe z. B. die DE-A1-198 08740). Da die Wärmestausegmente jeweils den Schaufelspitzen der Laufschaufeln bzw. Leitschaufeln gegenüberliegen und an diese anstossen, sind sie massgeblich an der Einstellung des Schaufelspiels beteiligt. Damit ein direkter Kontakt zwischen den Schaufelspitzen und den Wärmestausegmenten verhindert wird, sind zwischen den Wärmestausegmenten Schneidwerkzeuge angeordnet, welche die Wärmestausegmente um einen vorbestimmten Betrag überragen und gleichzeitig eine Verschiebung der Wärmestausegmente in Umfangsrichtung verhindern. Ein solcher Rotoraufbau ist jedoch sehr aufwendig in der Herstellung und Montage.High-pressure compressors, as are used in particular in gas turbines for compressing the combustion air, comprise a multi-stage blading which consists of rotor blades and guide vanes arranged alternately in the axial direction. The blades are attached to the rotatably mounted rotor. The guide vanes are arranged between adjacent rotor blade rings on the inner housing of the compressor The air that flows through the annular channel of the compressor, which is formed between the rotor and the inner housing, and is compressed in the process, heats up due to the compression. In order to protect the rotor and the inner housing against excessive thermal stress from the heated air, heat accumulation elements are often arranged between adjacent rotor blade and guide blade rings, which form a circumferential protective ring (see, for example, DE-A1-198 08740). Since the heat accumulation segments each lie opposite the blade tips of the moving blades or guide blades and abut against them, they are significantly involved in the adjustment of the blade clearance. So that direct contact between the blade tips and the heat accumulation segments is prevented, cutting tools are arranged between the heat accumulation segments, which protrude above the heat accumulation segments and at the same time prevent displacement of the heat accumulation segments in the circumferential direction. However, such a rotor structure is very complex to manufacture and assemble.
Eine bekannte Ausführungsform der rotorseitigen, d.h., den Leitschaufeln gegenüberliegenden Wärmestausegmente ist in der DE-A-1-196 15549 wiedergegeben und auch in Fig. 1 der vorliegenden Anmeldung dargestellt. Die bekannten Wärmestausegmente 10 sind als schalenförmige Kreisringsegmente ausgebildet, die eine glatte Aussenfläche 11 aufweisen und auf deren Unterseite zwei sich parallel in Umfangsrichtung erstreckende Segmentfüsse 12 mit hakenförmigem Querschnitt angeformt sind. Zur Befestigung der Wärmestausegmente 10 ist zwischen benachbarten Laufschaufelkranzen im Rotor eine Umfangsnut mit zwei sich über den gesamten Umfang erstreckenden Haken vorgesehen, hinter welchen die Wärmestausegmente mit ihren Segmentfüssen eingehakt werden. Jedes der Wärmestausegmente ist gegen eine Verschiebung in Umfangsrichtung durch einen Befestigungsstift gesichert (Fig. 3 und Anspruch 4 der DE-A-1-196 15 549). Auch in diesem Falle stellt die Sicherung jedesA known embodiment of the heat accumulator segments on the rotor side, i.e. opposite the guide vanes, is shown in DE-A-1-196 15549 and is also shown in FIG. 1 of the present application. The known heat accumulation segments 10 are designed as cup-shaped circular ring segments, which have a smooth outer surface 11 and on the underside of which two segment feet 12 with a hook-shaped cross section extending in the circumferential direction are formed. To attach the heat accumulation segments 10, a circumferential groove with two hooks extending over the entire circumference is provided between adjacent rotor blade rings in the rotor, behind which the heat accumulation segments are hooked with their segment feet. Each of the heat accumulation segments is secured against shifting in the circumferential direction by a fastening pin (Fig. 3 and claim 4 of DE-A-1-196 15 549). In this case too, the backup provides everyone
Wärmestausegments in Umfangsrichtung einen erheblichen Aufwand dar, weil die entsprechenden Bohrungen in den Rotor und die Wärmestausegmente eingebracht und die Befestigungsstifte montiert werden müssen. Darüber hinaus ist in diesem Fall keine Vorkehrung getroffen, ein vorbestimmtes Spiel zwischen Wärmestausegmenten und Schaufelspitzen einzustellen.Heat accumulation segments in the circumferential direction represent a considerable effort because the corresponding bores in the rotor and the heat accumulation segments inserted and the mounting pins must be installed. In addition, no provision is made in this case to set a predetermined play between the heat accumulation segments and the blade tips.
DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION
Es ist Aufgabe der Erfindung, einen Verdichter mit einem Rotor zu schaffen, welcher die Nachteile bekannter Lösungen vermeidet und sich durch eine vereinfachte Herstellung und Montage auszeichnet.It is an object of the invention to provide a compressor with a rotor which avoids the disadvantages of known solutions and is characterized by simplified manufacture and assembly.
Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Der Kern der Erfindung besteht darin, nicht jedes Wärmestausegment gegen eine Verschiebung in Umfangsrichtung zu sichern, sondern nur eine Teilmenge von ausgewählten Segmenten mit entsprechenden Sicherungsmitteln auszustatten. Hierdurch wird eine erhebliche Reduktion des Aufwandes sowohl bei der Herstellung als auch bei der Montage erreicht. Die nicht mit Sicherungsmitteln ausgerüsteten Wärmestausegmente werden dabei durch die mit Sicherungsmitteln ausgestatteten Wärmestaussegmente mit gesichert.The object is achieved by the entirety of the features of claim 1. The essence of the invention is not to secure each heat accumulation segment against displacement in the circumferential direction, but rather to equip only a subset of selected segments with appropriate securing means. As a result, a considerable reduction in the effort is achieved both in the manufacture and in the assembly. The heat accumulation segments not equipped with securing means are also secured by the heat accumulation segments equipped with securing means.
Besonders vorteilhaft ist diese Art der Sicherung, wenn gemäss einer bevorzugten Ausgestaltung der Erfindung in Umfangsrichtung gesehen jedes zweite Wärmestausegment mit den Sicherungsmitteln ausgestattet ist, weil dadurch eine maximale Sicherung mit einem minimalen Aufwand erzielt werden kann.This type of securing is particularly advantageous if, according to a preferred embodiment of the invention, viewed in the circumferential direction, every second heat accumulation segment is equipped with the securing means, because maximum securing can thereby be achieved with minimal effort.
Insbesondere weisen die Wärmestausegmente Segmentfüsse mit einem hakenförmigen Querschnitt auf, mit welchen sie hinter am Rotor angeformten, umlaufenden Rotorhaken eingehakt werden, und umfassen die Sicherungsmittel einen Sicherungsstift, welcher sich in axialer Richtung durch die Segmentfüsse und Rotorhaken hindurch erstreckt, wobei insbesondere der Sicherungsstift in Umfangsrichtung gesehen jeweils in der Mitte des Wärmestausegmentes angeordnet ist. Wenn im Bereich der Wärmestausegmente Leitschaufeln angeordnet sind, welche mit ihrer Schaufelspitze an einer Aussenfläche der Wärmestausegmente enden, ist es bei dieser Art der Sicherung besonders vorteilhaft, wenn die Aussenfläche der Wärmestausegmente mit einer Abreibschicht versehen ist, welche bei einem Schleifen der Schaufelspitzen der Leitschaufeln an den Aussenflächen der Wärmestausegmente einen Materialabtrag an den Schaufelspitzen bewirkt.In particular, the heat accumulation segments have segmented feet with a hook-shaped cross section, with which they are hooked in behind rotating rotor hooks formed on the rotor, and the securing means comprise a securing pin which extends in the axial direction through the segmented feet and rotor hooks, in particular the securing pin in the circumferential direction seen is arranged in the middle of the heat accumulation segment. If guide vanes are arranged in the area of the heat accumulation segments, which end with their blade tip on an outer surface of the heat accumulation segments, it is particularly advantageous with this type of securing if the outer surface of the heat accumulation segments is provided with an abrasion layer, which is applied when the blade tips of the guide vanes are ground the outer surfaces of the heat accumulation segments causes material removal at the blade tips.
KURZE ERLÄUTERUNG DER FIGURENBRIEF EXPLANATION OF THE FIGURES
Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Es zeigenThe invention will be explained in more detail below on the basis of exemplary embodiments in connection with the drawing. Show it
Fig. 1 in einer perspektivischen Seiteansicht ein an sich bekanntes Wärmestausegment, wie es im Rahmen der Erfindung zum Einsatz kommt;1 shows a perspective side view of a heat accumulation segment known per se, as is used in the context of the invention;
Fig. 2 in einer teilweise geschnittenen Ansicht die Anordnung der Wärmesegmente zwischen benachbarten Reihen von Laufschaufeln mit Sicherungsmitteln gemäss einem Ausführungsbeispiel der Erfindung;Figure 2 is a partially sectioned view of the arrangement of the heat segments between adjacent rows of blades with securing means according to an embodiment of the invention.
Fig. 3 den Schnitt entlang der Ebene A-A aus Fig. 2 undFig. 3 shows the section along the plane A-A of Fig. 2 and
Fig. 4 in einer zu Fig. 2 vergleichbaren Ansicht ein mit einer Abreibschicht versehenes Wärmestausegment nach der Erfindung. WEGE ZUR AUSFÜHRUNG DER ERFINDUNGFig. 4 in a view comparable to FIG. 2 shows a heat accumulation segment according to the invention provided with an abrasion layer. WAYS OF CARRYING OUT THE INVENTION
Ein bevorzugtes Ausführungsbeispiel der Erfindung geht aus von einem Wärmestausegment 10 der in Fig. 1 dargestellten Art, das mittels der Segmentfüsse 12 am Rotor zwischen zwei Laufschaufelreihen befestigt wird und mit einer Aussenfläche 11 den Schaufelspitzen der zwischen den Laufschaufelreihen angeordneten Leitschaufeln (16 in Fig. 4) gegenüberliegt. Aus Fig. 2 ist die Anordnung der Wärmestausegmente 10 am Rotor 13 zwischen den Laufschaufeln 14, 14' benachbarter Laufschaufelreihen ersichtlich. Dazu ist im Rotor 13 eine Umfangsnut 21 eingelassen, in der in Umfangsrichtung parallel zwei Rotorhaken 19 verlaufen (siehe auch Fig. 4). In diese Rotorhaken 19 sind die Wärmestausegmente 10 mit den Segmentfüssen 12 eingehakt, so dass die Aussenfläche 11 der Wärmestausegmente an die Plattformen der Laufschaufeln 14, 14' anschliesst. Zur Sicherung des in Fig. 2 gezeigten Wärmestausegments 10 ist ein axial orientierter Sicherungsstift 15 in Form eines kreiszylindrischen Bolzens vorgesehen, der durch entsprechende Bohrungen in den Segmentfüssen 12 und einem der Rotorhaken 19 gesteckt ist. Der Sicherungsstift 15 ist dabei vorzugsweise in Umfangsrichtung gesehen in der Mitte des Wärmestausegments 10 angeordnet.A preferred exemplary embodiment of the invention is based on a heat accumulation segment 10 of the type shown in FIG. 1, which is attached to the rotor between two rows of rotor blades by means of the segment feet 12 and with an outer surface 11 of the blade tips of the guide blades (16 in FIG. 4) arranged between the rows of rotor blades ) is opposite. 2 shows the arrangement of the heat accumulation segments 10 on the rotor 13 between the rotor blades 14, 14 'of adjacent rotor blade rows. For this purpose, a circumferential groove 21 is embedded in the rotor 13, in which two rotor hooks 19 run parallel in the circumferential direction (see also FIG. 4). The heat accumulation segments 10 are hooked into these rotor hooks 19 with the segment feet 12, so that the outer surface 11 of the heat accumulation segments adjoins the platforms of the moving blades 14, 14 ′. To secure the heat accumulation segment 10 shown in FIG. 2, an axially oriented locking pin 15 in the form of a circular cylindrical bolt is provided, which is inserted through corresponding bores in the segment feet 12 and one of the rotor hooks 19. The securing pin 15 is preferably arranged in the middle of the heat accumulation segment 10, as seen in the circumferential direction.
Der in Fig. 3 dargestellte Schnitt in der Ebene A-A der Fig. 2 zeigt, dass bei zwei benachbarten Wärmestausegmenten nur das eine (in Fig. 3 das rechte) Wärmestausegment mit einem Sicherungsstift 15 gesichert ist. Alle zwischen den beiden Laufschaufelreihen 14 und 14' angeordneten Wärmestausegmente zusammen bilden einen segmentierten Wärmestauring, bei dem jedes zweite Segment mit einem Sicherungsstift 15 gegen ein „Wandern" über den Umfang gesichert ist.The section shown in FIG. 3 in plane A-A of FIG. 2 shows that in the case of two adjacent heat accumulation segments, only the one (in FIG. 3 the right) heat accumulation segment is secured with a locking pin 15. All of the heat accumulation segments arranged between the two rows of blades 14 and 14 'together form a segmented heat accumulation ring, in which every second segment is secured with a locking pin 15 against "wandering" over the circumference.
Damit sich bei den derart gesicherten Wärmestausegmenten das gewünschte optimale Spiel zwischen der Aussenfläche 11 der Wärmestausegmente 10 und den Schaufelspitzen der anstossenden Leitschaufeln einstellen kann, ist gemäss Fig. 4 die Aussenfläche mit einer Abreibschicht 18 behaftet. Die Abreibschicht 18 ist aus einem Material, das härter ist als das Material der anstossenden Leitschaufeln 16. Dadurch wird erreicht, dass sich die über die Abreibschicht 18 laufenden Leitschaufeln 16 beim Streifen am Wärmestausegment 10 abnützen, in dem an der Schaufelspitze 20 in einem Abtragsbereich 17 Material abgetragen wird. Auf diese Weise wird verhindert, dass sich die Oberfläche am Wärmestausegment 10 dauerhaft durch Reibung erhitzt wird.4 so that the desired optimal play between the outer surface 11 of the heat accumulation segments 10 and the blade tips of the abutting guide vanes can occur in the heat accumulation segments secured in this way, the outer surface is fraught with an abrasion layer 18. The abrasion layer 18 is made of a material that is harder than the material of the adjoining guide vanes 16. This ensures that the guide vanes 16 running over the abrasion layer 18 wear during the streaking on the heat accumulation segment 10, in which material is removed from the blade tip 20 in a removal area 17 , This prevents the surface on the heat accumulation segment 10 from being permanently heated by friction.
BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS
10 Wärmestausegment10 heat accumulation segment
11 Aussenfläche (Wärmestausegment)11 outer surface (heat accumulation segment)
12 Segmentfuss12 segment foot
13 Rotor13 rotor
14 Laufschaufel 15 Sicherungsstift14 rotor blade 15 locking pin
16 Leitschaufel16 guide vane
17 Abtragsbereich17 removal area
18 Abreibschicht18 rubbing layer
19 Rotorhaken 20 Schaufelspitze (Leitschaufel)19 rotor hooks 20 blade tip (guide blade)
21 Umfangsnut 21 circumferential groove

Claims

PATENTANSPRÜCHE
1. Verdichter mit einem Rotor (13), welcher Rotor (13) in axialer Richtung hintereinander mehrere voneinander beabstandete Reihen von Laufschaufeln (14, 14') aufweist, wobei zwischen benachbarten Reihen von Laufschaufeln (14, 14') am Umfang des Rotors (13) in Umfangsrichtung hintereinander eine Mehrzahl von lösbar am Rotor (13) befestigten, in Umfangsrichtung verschiebbar gelagerten Wärmestausegmenten (10) angeordnet ist, und wobei an den Wärmestausegmenten (10) Sicherungsmittel (15) vorgesehen sind, welche die Wärmestausegmente (10) gegen eine Verschiebung in Umfangsrichtung sichern, dadurch gekennzeichnet, dass nur ein Teil der Wärmestausegmente (10) mit den Sicherungsmitteln (15) ausgestattet ist. 1. Compressor with a rotor (13), the rotor (13) in the axial direction one behind the other has a plurality of spaced rows of blades (14, 14 '), with adjacent rows of blades (14, 14') on the circumference of the rotor ( 13) a plurality of heat accumulator segments (10) which are detachably fastened to the rotor (13) and are displaceably mounted in the circumferential direction are arranged in the circumferential direction, and securing means (15) are provided on the heat accumulator segments (10) which prevent the heat accumulator segments (10) against one Secure displacement in the circumferential direction, characterized in that only part of the heat accumulation segments (10) is equipped with the securing means (15).
2. Verdichter nach Anspruch 1 , dadurch gekennzeichnet, dass in2. Compressor according to claim 1, characterized in that in
Umfangsrichtung gesehen jedes zweite Wärmestausegment (10) mit den Sicherungsmitteln (15) ausgestattet ist.Viewed in the circumferential direction, every second heat accumulation segment (10) is equipped with the securing means (15).
3. Verdichter nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Wärmestausegmente (10) Segmentfüsse (12) mit einem hakenförmigen3. Compressor according to claim 1 or 2, characterized in that the heat accumulation segments (10) segment feet (12) with a hook-shaped
Querschnitt aufweisen, mit welchen sie hinter am Rotor (13) angeformten, umlaufenden Rotorhaken (19) eingehakt werden, und dass die Sicherungsmittel einen Sicherungsstift (15) umfassen, welcher sich in axialer Richtung durch die Segmentfüsse (12) und Rotorhaken (19) hindurch erstreckt.Have a cross section with which they are hooked behind the rotating rotor hooks (19) formed on the rotor (13), and that the securing means comprise a locking pin (15) which extends in the axial direction through the segment feet (12) and rotor hooks (19) extends.
4. Verdichter nach Anspruch 3, dadurch gekennzeichnet, dass der Sicherungsstift (15) in Umfangsrichtung gesehen jeweils in der Mitte des Wärmestausegmentes (10) angeordnet ist. 4. Compressor according to claim 3, characterized in that the securing pin (15) is arranged in the circumferential direction in each case in the middle of the heat accumulation segment (10).
5. Verdichter nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass im Bereich der Wärmestausegmente (10) Leitschaufeln (16) angeordnet sind, welche mit ihrer Schaufelspitze (20) an einer Aussenfläche (11) der Wärmestausegmente (10) enden, und dass die Aussenfläche (11) der Wärmestausegmente (10) mit einer Abreibschicht (18) versehen ist, welche bei einem Schleifen der Schaufelspitzen (20) der Leitschaufeln (16) an den Aussenflächen der Wärmestausegmente (10) einen Materialabtrag an den Schaufelspitzen (20) bewirkt. 5. Compressor according to one of claims 1 to 4, characterized in that in the area of the heat accumulation segments (10) guide vanes (16) are arranged, which with their blade tip (20) on an outer surface (11) of the Heat accumulation segments (10) end, and that the outer surface (11) of the heat accumulation segments (10) is provided with an abrasion layer (18) which, when the blade tips (20) of the guide vanes (16) are ground, on the outer surfaces of the heat accumulation segments (10) Material removal on the blade tips (20) causes.
EP04819680A 2003-12-04 2004-11-17 Compressor rotor Withdrawn EP1689979A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10356586A DE10356586A1 (en) 2003-12-04 2003-12-04 compressor rotor
PCT/EP2004/052993 WO2005054634A1 (en) 2003-12-04 2004-11-17 Compressor rotor

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EP1689979A1 true EP1689979A1 (en) 2006-08-16

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US (1) US8033784B2 (en)
EP (1) EP1689979A1 (en)
CA (1) CA2549136A1 (en)
DE (1) DE10356586A1 (en)
TW (1) TWI350877B (en)
WO (1) WO2005054634A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10356586A1 (en) 2003-12-04 2005-07-07 Alstom Technology Ltd compressor rotor
CH700001A1 (en) 2008-11-20 2010-05-31 Alstom Technology Ltd Moving blade arrangement, especially for a gas turbine.
US20110280716A1 (en) * 2010-05-17 2011-11-17 Douglas Gerard Konitzer Gas turbine engine compressor components comprising thermal barriers, thermal barrier systems, and methods of using the same
US9528376B2 (en) * 2012-09-13 2016-12-27 General Electric Company Compressor fairing segment
US9771802B2 (en) 2014-02-25 2017-09-26 Siemens Energy, Inc. Thermal shields for gas turbine rotor

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1033197A (en) * 1951-02-27 1953-07-08 Rateau Soc Vibration dampers for mobile turbo-machine blades
US3143383A (en) * 1961-07-21 1964-08-04 Gen Electric Means for preventing fretting erosion
US3088708A (en) * 1961-12-29 1963-05-07 Seymour J Feinberg Compressor blade locking device
US4867639A (en) * 1987-09-22 1989-09-19 Allied-Signal Inc. Abradable shroud coating
DE59200115D1 (en) * 1991-06-28 1994-05-19 Asea Brown Boveri Drum rotor for axially flow-through turbomachine.
CZ406592A3 (en) * 1992-01-08 1993-08-11 Alsthom Gec Drum rotor for steam action turbine and steam action turbine comprising such rotor
GB2293628B (en) * 1994-09-27 1998-04-01 Europ Gas Turbines Ltd Turbines
DE4442157A1 (en) * 1994-11-26 1996-05-30 Abb Management Ag Method and device for influencing the radial clearance of the blades in compressors with axial flow
DE19615549B8 (en) * 1996-04-19 2005-07-07 Alstom Device for thermal protection of a rotor of a high-pressure compressor
DE19619438B4 (en) * 1996-05-14 2005-04-21 Alstom Heat release segment for a turbomachine
DE19808740B4 (en) * 1998-03-02 2007-03-08 Alstom Apparatus for ensuring minimal radial blade clearance in thermal turbomachinery
DE19937577A1 (en) * 1999-08-09 2001-02-15 Abb Alstom Power Ch Ag Frictional gas turbine component
DE19938274A1 (en) * 1999-08-12 2001-02-15 Asea Brown Boveri Device and method for drawing the gap between the stator and rotor arrangement of a turbomachine
US6558118B1 (en) * 2001-11-01 2003-05-06 General Electric Company Bucket dovetail bridge member and method for eliminating thermal bowing of steam turbine rotors
DE10356586A1 (en) 2003-12-04 2005-07-07 Alstom Technology Ltd compressor rotor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2005054634A1 *

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DE10356586A1 (en) 2005-07-07
TW200525077A (en) 2005-08-01
TWI350877B (en) 2011-10-21
CA2549136A1 (en) 2005-06-16
US20060228210A1 (en) 2006-10-12
US8033784B2 (en) 2011-10-11
WO2005054634A1 (en) 2005-06-16

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