EP1006264A2 - Coolable shroud for a turbomachine - Google Patents

Coolable shroud for a turbomachine Download PDF

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Publication number
EP1006264A2
EP1006264A2 EP99811095A EP99811095A EP1006264A2 EP 1006264 A2 EP1006264 A2 EP 1006264A2 EP 99811095 A EP99811095 A EP 99811095A EP 99811095 A EP99811095 A EP 99811095A EP 1006264 A2 EP1006264 A2 EP 1006264A2
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EP
European Patent Office
Prior art keywords
segments
guide
jacket
segment
guide segments
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP99811095A
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German (de)
French (fr)
Other versions
EP1006264A3 (en
EP1006264B1 (en
Inventor
Christoph Pfeiffer
Ulrich Wellenkamp
Christoph Nagler
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
ABB Alstom Power Switzerland Ltd
Alstom Technology AG
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Publication date
Application filed by ABB Alstom Power Switzerland Ltd, Alstom Technology AG filed Critical ABB Alstom Power Switzerland Ltd
Publication of EP1006264A2 publication Critical patent/EP1006264A2/en
Publication of EP1006264A3 publication Critical patent/EP1006264A3/en
Application granted granted Critical
Publication of EP1006264B1 publication Critical patent/EP1006264B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20Actively adjusting tip-clearance
    • F01D11/24Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246Fastening of diaphragms or stator-rings
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/20Heat transfer, e.g. cooling
    • F05D2260/201Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the invention relates to a coolable jacket of a gas turbine or the like according to the preamble of claim 1.
  • EP 0 516 322 B1 is a coolable jacket known for a gas turbine.
  • the jacket is made up of several arcuate jacket segments formed that adjoining one another in the circumferential direction is a jacket ring form, which surrounds an impeller of a high-pressure turbine stage.
  • An annular jacket cooling chamber is located on the side of the jacket segments facing away from the impeller provided, which is located in the radial direction between the shell segments and arcuate guide segments extends.
  • the leading segments are out Shaped sheet metal sections, which are provided with a plurality of through openings are.
  • the carrier also has an air supply duct which opens into the air duct chamber.
  • Cooling air is fed into the air supply duct to cool the jacket. From there it passes through the through holes, creating high-speed air jets train that is substantially perpendicular to the Impact the back of the jacket segments. After the impact, they are redirected and there is a cross flow in the jacket cooling chamber.
  • the high cooling effect that can be achieved with this device is based in particular on the combination of impingement and convection cooling.
  • To the particularly cheap To make optimal use of the heat transfer of the impingement cooling it is particularly important to achieve the highest possible speed of the cooling air jets emerging through the through openings.
  • the basic prerequisite for this is the setting of the highest possible pressure difference between the air duct chamber and the jacket cooling chamber.
  • the invention tries to avoid the disadvantages described. You are the Based on the task of specifying a coolable jacket of the type mentioned at the outset, which is constructed in a structurally simple manner without a serious loss in cooling effectiveness is, which both the manufacturing and the repair and Have maintenance costs reduced. In addition, the mechanical loads reduced and thus in the described transient processes an increased lifespan can be achieved.
  • this is achieved in that with a coolable jacket according to the preamble of claim 1, the guide segments loose and with a radial Play are stored.
  • This type of storage means that there are relative movements between the carrier or carrier segment and the jacket segments possible.
  • the radial play is dimensioned so that a largely unimpeded relative movement is also possible for the most unfavorable transient operating state. This occurs during the run-up phase, when the leading segments are exposed to cooling air be, which has a comparatively high temperature, whereby the carrier is still comparatively cold.
  • a particularly simple structural design can be realized if the guide segments are loosely guided between the carrier and spacers, the spacers protruding in the radial direction on the back of the Sheath segments are attached.
  • the cooling air flow hitting the leading segments presses them against the spacers, creating a fixed predetermined distance observed between the guide segments and the back of the jacket segments becomes.
  • the jacket cooling chamber is thus fixed in the radial direction, whose radial extension corresponds to the height of the spacers.
  • the comparative high pressure, under which the cooling air is supplied ensures that the Guiding segments against cool air during the duration of the exposure the spacers are held down.
  • Ribs which are continuous, have proven particularly useful as spacers Allow support of the leading segments along a continuous line.
  • point support elements such as pins or bumps are suitable in a cylindrical or conical configuration, their arrangement is in principle arbitrary and thereby an even better equalization of the Allow cooling effect.
  • a particularly secure storage of the guide segments can then be achieved if these are provided with at least two radial webs that have a small engage axial play in corresponding guide grooves of the carrier.
  • the on the one hand, slight play allows the guide segments to move radially, on the other hand, minimizes the leakage losses due to the flow around the guide segments even with a comparatively high overpressure of the cooling air supply.
  • the design of the guide segments with a U-shaped is particularly favorable Cross-sectional profile that is particularly easy to manufacture.
  • a chipless Forming process can be formed laterally legs, which as in Crosspieces running through the circumferential direction ensure the exact guidance of the respective guide segment to ensure.
  • the guide segments are preferably arranged to overlap in the circumferential direction. This creates a continuous, uninterrupted separating surface in the circumferential direction between the jacket cooling chamber and the air supply duct, so that Leakage losses at the transition points of two adjacent ones Leading segments are further minimized.
  • An increased number of through holes can be provided in the overlap area be to the formation of cooling air jets in this area too to provide sufficient quantity. This takes the effect into account that the relative assignment is borne by the loose storage of the individual leading segments can vary in the circumferential direction, associated with the risk that in Overlap area too few through holes of two overlapping guide segments to be brought to cover.
  • flange sections In the contact area between the jacket segment and the carrier are in the circumferential direction extending flange sections are provided, so that jacket segment and Carrier by means of brackets, which are the adjacent flange sections reach around, are releasably connected.
  • the retaining clips press the jacket segments and carrier firmly against one another so that Leakage losses due to cooling air escaping between the two components largely is prevented.
  • the retaining clips allow a simple one Disconnect and restore the connection, so that not only the assembly of the Coat, but also to a special extent the repair by exchanging individual Elements is greatly simplified.
  • an embodiment of the invention is based on a coolable Sheath of the first impeller of a high-pressure turbine stage shown.
  • FIG. 1 It is a section of the first high-pressure turbine stage a gas turbine consisting of an impeller 110 and a stator 120 shown.
  • the impeller 110 is in the radial direction from a jacket ring surrounded by several, in the circumferential direction strung together jacket segments 10 is constructed.
  • Each jacket segment 10 is assigned to a carrier segment 20, which in is not shown in detail on a housing 100 is fixed.
  • the support segment 20 is in a substantially radial direction from an air supply duct 26 penetrates through the cooling air from a not shown Cooling air supply is supplied.
  • Cooling air supply is supplied.
  • the air supply duct 26 opens into a continuous recess 24 in the circumferential direction, which is part of an air duct chamber 25.
  • the air guide chamber 25 becomes radial limited on the inside by a guide segment 30.
  • the leading segment 30 has a U-shaped basic shape with two webs 32, which designed in corresponding Engage guide grooves 22 of the carrier segment 20.
  • the guide segment 30 is supported on two ribs Spacers 12, which run in the circumferential direction and in the radial Direction protruding on the back of the shell segment 10 are attached.
  • a jacket cooling chamber 15 arises in the radial direction between the shell segment 10 and the Guide segment 30 a jacket cooling chamber 15.
  • the guide segments 30 have a large number through openings 34 which provide a fluid connection between represent the air guide chamber 25 and the jacket cooling chamber 15 and the Training of cooling air jets serve.
  • the carrier segment 20 and the jacket segment 10 have flange sections 28 or 18, which are surrounded by retaining clips 80 and thus that Connect the carrier segment 20 and the jacket segment 10 to one another.
  • the retaining clips 80 have an approximately U-shaped cross-sectional profile with two axial webs 89, which in corresponding axial grooves 29, 19 of the support segment 20th or the shell segment 10 engage. This creates an axial aligned transition from the carrier segment 20 to the jacket segment 10.
  • Sealing elements 90 are in corner areas between the retaining clips 80 on the one hand and the flange portions 28 of the support segment 20 and Flange sections 18 of the shell segment 10, on the other hand, used to form a largely pressure-tight seal between the air-guiding areas, in particular the jacket cooling chamber 15 and the air duct chamber 25 and the surrounding area.
  • the guide segments 30 are for forming in the circumferential direction continuous air-guiding channels overlapping.
  • two abutting guide segments 30 are arranged such that there is an overlap area 38.
  • the leading segments are 30 each shaped at one end so that it fits into the adjacent one Guide segment 30 can be inserted.
  • the outer contour gives way slightly backwards, so that a kind Leadership results.
  • the cooling air supplied via the air duct 26 acts on the guide segment 30 and presses it radially inward against the ribs 12 of the Sheath segment 10.
  • a permanent pressure supply creates a pressure difference maintained between the air guide chamber 25 and the jacket cooling chamber 15, so that the guide segment 30 is securely fixed during operation.
  • the maintenance of the pressure difference is required in order to to achieve the desired impingement cooling by cooling air jets, which are caused by the Through openings 34 are generated.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The ring-shaped jacket has an air guide chamber formed between curved jacket segments and guide segments. The guide segments (30) are positioned loose with radial play. They are guided between a carrier segment (20) and distance pieces (12). These are fastened to the back of the jacket segments to project in radial direction. The guide segments have U-shaped radial webs (32) held with small axial play in guide grooves (22) of the carrier segment.

Description

Technisches GebietTechnical field

Die Erfindung betrifft einen kühlbaren Mantel einer Gasturbine oder dergleichen gemäß dem Oberbegriff des Anspruchs 1.The invention relates to a coolable jacket of a gas turbine or the like according to the preamble of claim 1.

Stand der TechnikState of the art

Aus der EP 0 516 322 B1, von der die Erfindung ausgeht, ist ein kühlbarer Mantel für eine Gasturbine bekannt. Der Mantel wird durch mehrere bogenförmige Mantelsegmente gebildet, die in Umfangsrichtung aneinandergrenzend einen Mantelring bilden, der ein Laufrad einer Hochdruckturbinenstufe umgibt. Zur Kühlung der dem Laufrad abgewandten Seite der Mantelsegmente ist eine ringförmige Mantelkühlkammer vorgesehen, die sich in radialer Richtung zwischen den Mantelsegmenten und bogenförmigen Leitsegmenten erstreckt. Die Leitsegmente sind aus Blechabschnitten geformt, die mit einer Vielzahl von Durchgangsöffnungen versehen sind. Ferner ist eine Luftführungskammer vorhanden, die sich in radialer Richtung zwischen den Leitsegmenten und einem gehäuseseitigen Träger bzw. Trägersegment erstreckt. Der Träger weist ferner einen Luftzuführungskanal auf, der in die Luftführungskammer mündet.EP 0 516 322 B1, from which the invention is based, is a coolable jacket known for a gas turbine. The jacket is made up of several arcuate jacket segments formed that adjoining one another in the circumferential direction is a jacket ring form, which surrounds an impeller of a high-pressure turbine stage. To cool the An annular jacket cooling chamber is located on the side of the jacket segments facing away from the impeller provided, which is located in the radial direction between the shell segments and arcuate guide segments extends. The leading segments are out Shaped sheet metal sections, which are provided with a plurality of through openings are. There is also an air guide chamber that extends in the radial direction between the guide segments and a housing-side carrier or carrier segment extends. The carrier also has an air supply duct which opens into the air duct chamber.

Zur Kühlung des Mantels wird Kühlluft in den Luftzuführungskanal eingespeist. Von dort tritt sie durch die Durchgangsöffnungen hindurch, wobei sich Hochgeschwindigkeits-Luftstrahlen ausbilden, die im Wesentlichen senkrecht auf die Rückseite der Mantelsegmente aufprallen. Nach dem Aufprall werden sie umgelenkt und es stellt sich eine Querströmung in der Mantelkühlkammer ein.Cooling air is fed into the air supply duct to cool the jacket. From there it passes through the through holes, creating high-speed air jets train that is substantially perpendicular to the Impact the back of the jacket segments. After the impact, they are redirected and there is a cross flow in the jacket cooling chamber.

Die mit dieser Einrichtung erzielbare hohe Kühlwirkung beruht insbesondere auf der Kombination von Prall- und Konvektionskühlung. Um den besonders günstigen Wärmeübergang der sich einstellenden Prallkühlung optimal zu nutzen, kommt es im besonderen Maße darauf an, eine möglichst hohe Geschwindigkeit der durch die Durchgangsöffnungen austretenden Kühlluftstrahlen zu realisieren. Grundvoraussetzung hierfür ist die Einstellung einer möglichst hohen Druckdifferenz zwischen der Luftführungskammer und der Mantelkühlkammer. The high cooling effect that can be achieved with this device is based in particular on the combination of impingement and convection cooling. To the particularly cheap To make optimal use of the heat transfer of the impingement cooling it is particularly important to achieve the highest possible speed of the cooling air jets emerging through the through openings. The basic prerequisite for this is the setting of the highest possible pressure difference between the air duct chamber and the jacket cooling chamber.

Problematisch ist in diesem Zusammenhang der Leckverlust, der sich durch Seitenumströmungen der Leitsegmente ergibt. Zur Vermeidung solcher Leckagen sind deshalb die einzelnen Leitsegmente mit dem Träger vollständig und umlaufend verlötet. Der hierfür erforderliche Aufwand ist enorm und führt deshalb zu hohen Herstellkosten. Darüberhinaus ist diese Konzeption auch deshalb problematisch, weil derartige Mantelsegmente speziell bei modernen Gasturbinen mit extrem hohen Turbineneintrittstemperaturen stark beschädigungsgefährdet sind. Im Falle eines notwendigen Austausches oder einer Reparatur der Leitsegmente fallen überproportional hohe Kosten an, die unter anderem auf die damit verbundenen Lötarbeiten zurückzuführen sind.The problem in this context is the leakage loss caused by the flow around the sides of the leading segments. To avoid such leaks the individual leading segments with the carrier are therefore complete and encircling soldered. The effort required for this is enormous and therefore leads to high costs Manufacturing costs. Furthermore, this concept is also problematic because such jacket segments, especially in modern gas turbines with extreme high turbine inlet temperatures are at risk of damage. in the In the event of a necessary exchange or repair of the leading segments disproportionately high costs, among other things on the associated Soldering work.

Auch ist diese Art der Anbindung der Leitsegmente an den Träger bei instationären Vorgängen, wie beispielsweise beim Hochfahren der Gasturbine oder bei Lastwechseln, problematisch, da bei diesen Betriebszuständen hohe Temparaturgradienten innerhalb der Bauteile und Baugruppen auftreten und zu hohen mechanischen Spannungen führen können. Besonders gefährdet ist hierbei die Lötverbindung zwischen den Leitsegmenten und dem Träger.This type of connection of the leading segments to the carrier is also with transient ones Operations, such as when starting up the gas turbine or at Load changes, problematic because of the high temperature gradients in these operating conditions occur within the components and assemblies and too high mechanical Can cause tension. The solder connection is particularly at risk between the lead segments and the beam.

Darstellung der ErfindungPresentation of the invention

Die Erfindung versucht, die beschriebenen Nachteile zu vermeiden. Ihr liegt die Aufgabe zugrunde, einen kühlbaren Mantel der eingangs genannten Art anzugeben, der ohne gravierende Einbuße an Kühleffektivität konstruktiv einfach aufgebaut ist, wodurch sich sowohl die Herstellungs- als auch die Reparatur- und Wartungskosten reduzieren lassen. Darüber hinaus sollen die mechanischen Belastungen bei den beschriebenen instationären Vorgängen verringert und somit eine erhöhte Lebensdauer erzielt werden.The invention tries to avoid the disadvantages described. You are the Based on the task of specifying a coolable jacket of the type mentioned at the outset, which is constructed in a structurally simple manner without a serious loss in cooling effectiveness is, which both the manufacturing and the repair and Have maintenance costs reduced. In addition, the mechanical loads reduced and thus in the described transient processes an increased lifespan can be achieved.

Erfindungsgemäß wird dies dadurch erreicht, dass bei einem kühlbaren Mantel gemäß dem Oberbegriff des Anspruchs 1 die Leitsegmente lose und mit radialem Spiel gelagert sind. Durch diese Art der Lagerung sind Relativbewegungen zwischen dem Träger bzw. Trägersegment und den Mantelsegmenten möglich. Das radiale Spiel ist so bemessen, dass eine weitgehend ungehinderte Relativbewegung auch für den ungünstigsten instationären Betriebszustand möglich ist. Dieser tritt während der Hochlaufphase auf, bei der die Leitsegmente mit Kühlluft beaufschlagt werden, die eine vergleichsweise hohe Temperatur besitzt, wodurch hingegen der Träger noch vergleichsweise kalt ist.According to the invention this is achieved in that with a coolable jacket according to the preamble of claim 1, the guide segments loose and with a radial Play are stored. This type of storage means that there are relative movements between the carrier or carrier segment and the jacket segments possible. The radial play is dimensioned so that a largely unimpeded relative movement is also possible for the most unfavorable transient operating state. This occurs during the run-up phase, when the leading segments are exposed to cooling air be, which has a comparatively high temperature, whereby the carrier is still comparatively cold.

Ein besonders einfacher konstruktiver Aufbau lässt sich dann realisieren, wenn die Leitsegmente lose zwischen dem Träger und Abstandshaltern geführt sind, wobei die Abstandshalter in radialer Richtung abstehend an der Rückseite der Mantelsegmente angebracht sind. Der auf die Leitsegmente auftreffende Kühlluftstrom drückt diese gegen die Abstandshalter, wodurch ein fest vorgegebener Abstand zwischen den Leitsegmenten und der Rückseite der Mantelsegmente eingehalten wird. Damit ist in radialer Richtung die Mantelkühlkammer festgelegt, deren radiale Erstreckung der Höhe der Abstandshalter entspricht. Der vergleichsweise hohe Druck, unter dem die Kühlluft zugeführt wird, sorgt dafür, dass die Leitsegmente während der Dauer der Beaufschlagung mit Kühlluft sicher gegen die Abstandshalter gedrückt gehalten sind.A particularly simple structural design can be realized if the guide segments are loosely guided between the carrier and spacers, the spacers protruding in the radial direction on the back of the Sheath segments are attached. The cooling air flow hitting the leading segments presses them against the spacers, creating a fixed predetermined distance observed between the guide segments and the back of the jacket segments becomes. The jacket cooling chamber is thus fixed in the radial direction, whose radial extension corresponds to the height of the spacers. The comparative high pressure, under which the cooling air is supplied, ensures that the Guiding segments against cool air during the duration of the exposure the spacers are held down.

Als Abstandshalter haben sich besonders Rippen bewährt, die eine durchgehende Unterstützung der Leitsegmente längs einer durchgehenden Linie erlauben. Ebenso eignen sich punktuelle Stützelemente, wie beispielsweise Pins oder Erhebungen in zylindrischer beziehungsweise kegeliger Ausgestaltung, deren Anordnung prinzipiell beliebig ist und dadurch eine noch bessere Vergleichmäßigung der Kühlwirkung zulassen.Ribs, which are continuous, have proven particularly useful as spacers Allow support of the leading segments along a continuous line. As well point support elements such as pins or bumps are suitable in a cylindrical or conical configuration, their arrangement is in principle arbitrary and thereby an even better equalization of the Allow cooling effect.

Eine besonders sichere Lagerung der Leitsegmente lässt sich dann erreichen, wenn diese mit zumindest zwei radialen Stegen versehen sind, die mit geringem axialem Spiel in korrespondierende Führungsnuten des Trägers eingreifen. Das geringe Spiel erlaubt einerseits die radiale Verschiebebewegung der Leitsegmente, minimiert andererseits die Leckverluste infolge seitlichen Umströmens der Leitsegmente auch bei vergleichsweise hohem Überdruck der Kühlluftzufuhr.A particularly secure storage of the guide segments can then be achieved if these are provided with at least two radial webs that have a small engage axial play in corresponding guide grooves of the carrier. The on the one hand, slight play allows the guide segments to move radially, on the other hand, minimizes the leakage losses due to the flow around the guide segments even with a comparatively high overpressure of the cooling air supply.

Besonders günstig ist die Ausgestaltung der Leitsegmente mit einem U-förmigen Querschnittsprofil, das sich besonders einfach herstellen lässt. Durch einen spanlosen Umformvorgang können jeweils seitlich Schenkel gebildet werden, die als in Umfangsrichtung durchlaufende Stege die exakte Führung des jeweiligen Leitsegmentes sicherstellen. The design of the guide segments with a U-shaped is particularly favorable Cross-sectional profile that is particularly easy to manufacture. By a chipless Forming process can be formed laterally legs, which as in Crosspieces running through the circumferential direction ensure the exact guidance of the respective guide segment to ensure.

Bevorzugt sind die Leitsegmente in Umfangsrichtung überlappend angeordnet. Damit entsteht in Umfangsrichtung eine durchgängige, nicht unterbrochene Trennfläche zwischen der Mantelkühlkammer und dem Luftzuführungskanal, so dass Leckverluste an den Übergangsstellen von jeweils zwei benachbart angeordneten Leitsegmenten weiter minimiert werden.The guide segments are preferably arranged to overlap in the circumferential direction. This creates a continuous, uninterrupted separating surface in the circumferential direction between the jacket cooling chamber and the air supply duct, so that Leakage losses at the transition points of two adjacent ones Leading segments are further minimized.

Im Überlappungsbereich kann eine erhöhte Zahl von Durchgangsbohrungen vorgesehen sein, um auch in diesem Bereich die Ausbildung von Kühlluftstrahlen in ausreichender Menge zur Verfügung zu stellen. Damit wird dem Effekt Rechnung getragen, dass durch das lose Lagern der einzelnen Leitsegmente die relative Zuordnung in Umfangsrichtung variieren kann, verbunden mit der Gefahr, dass im Überlappungsbereich zu wenig Durchgangsbohrungen zweier überlappender Leitsegmente zur Deckung gebracht werden.An increased number of through holes can be provided in the overlap area be to the formation of cooling air jets in this area too to provide sufficient quantity. This takes the effect into account that the relative assignment is borne by the loose storage of the individual leading segments can vary in the circumferential direction, associated with the risk that in Overlap area too few through holes of two overlapping guide segments to be brought to cover.

Selbstverständlich ist es auch möglich, anstelle einer erhöhten Zahl von Durchgangsbohrungen im Überlappungsbereich bei jeweils einem der beiden Leitsegmente Durchgangsöffnungen mit vergrößertem Querschnitt in Umfangsrichtung vorzusehen, so dass unabhängig von der augenblicklich eingenommenen Rela tivlage zweier benachbarter Leitsegmente die Durchgangsbohrungen freibleiben.Of course, it is also possible instead of an increased number of through holes in the overlap area for each of the two leading segments Through openings with an enlarged cross-section in the circumferential direction to be provided so that regardless of the currently taken Rela tivlage of two adjacent guide segments, the through holes remain free.

Im Kontaktbereich jeweils zwischen Mantelsegment und Träger sind in Umfangsrichtung verlaufende Flanschabschnitte vorgesehen, so dass Mantelsegment und Träger mittels Halteklammern, die die jeweils aneinandergrenzenden Flanschabschnitte umgreifen, miteinander lösbar verbunden sind. Die Halteklammern pressen einerseits die Mantelsegmente und Träger fest aneinander, so dass Leckverluste durch zwischen den beiden Bauteilen austretende Kühlluft weitgehend unterbunden wird. Andererseits gestatten die Halteklammern ein einfaches Lösen und Wiederherstellen der Verbindung, so dass nicht nur die Montage des Mantels, sondern im besonderen Maße auch die Reparatur durch Austausch einzelner Elemente stark vereinfacht ist.In the contact area between the jacket segment and the carrier are in the circumferential direction extending flange sections are provided, so that jacket segment and Carrier by means of brackets, which are the adjacent flange sections reach around, are releasably connected. The retaining clips press the jacket segments and carrier firmly against one another so that Leakage losses due to cooling air escaping between the two components largely is prevented. On the other hand, the retaining clips allow a simple one Disconnect and restore the connection, so that not only the assembly of the Coat, but also to a special extent the repair by exchanging individual Elements is greatly simplified.

Zusätzliche Dichtelemente zwischen den Halteklammern einerseits und den Flanschabschnitten andererseits gewährleisten eine praktisch vollständige Abdichtung im Kontaktbereich zwischen Mantelsegment und Träger. Damit lässt sich der Kühlluftbedarf auf niedrigem Niveau halten. Additional sealing elements between the retaining clips on the one hand and the Flange sections, on the other hand, ensure practically complete sealing in the contact area between the jacket segment and the carrier. With that, the Keep cooling air requirement at a low level.

Kurze Beschreibung der ZeichnungBrief description of the drawing

In der Zeichnung ist ein Ausführungsbeispiel der Erfindung anhand eines kühlbaren Mantels des ersten Laufrades einer Hochdruck-Turbinenstufe dargestellt.In the drawing, an embodiment of the invention is based on a coolable Sheath of the first impeller of a high-pressure turbine stage shown.

Es zeigen:

Fig. 1
Kühlbarer Mantel im Axialschnitt (Teilansicht);
Fig. 2
Überlappungsbereich zweier aneinandergrenzender Leitsegmente in perspektivischer Ansicht.
Show it:
Fig. 1
Coolable jacket in axial section (partial view);
Fig. 2
Overlapping area of two adjacent leading segments in a perspective view.

Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt.Only the elements essential for understanding the invention are shown.

Weg zur Ausführung der ErfindungWay of carrying out the invention

Das der Erfindung zugrundeliegende Konzept eines kühlbaren Mantels ergibt sich insbesondere aus Fig. 1. Es ist ein Ausschnitt aus der ersten Hochdruck-Turbinenstufe einer Gasturbine, bestehend aus einem Laufrad 110 und einem Leitrad 120 dargestellt. Das Laufrad 110 ist in radialer Richtung von einem Mantelring umgeben, der aus mehreren, in Umfangsrichtung aneinandergereihten Mantelsegmenten 10 aufgebaut ist.The concept of a coolable jacket on which the invention is based arises in particular from FIG. 1. It is a section of the first high-pressure turbine stage a gas turbine consisting of an impeller 110 and a stator 120 shown. The impeller 110 is in the radial direction from a jacket ring surrounded by several, in the circumferential direction strung together jacket segments 10 is constructed.

Jedes Mantelsegment 10 ist einem Trägersegment 20 zugeordnet, welches in nicht näher dargestellter Art und Weise an einem Gehäuse 100 fixiert ist. Das Trägersegment 20 wird in im Wesentlichen radialer Richtung von einem Luftzuführungskanal 26 durchsetzt, durch den Kühlluft aus einer nicht näher dargestellten Kühlluftversorgung zugeführt wird. Als Kühlluft wird beispielsweise ein Teilluftstrom aus einer der vorangeschalteten Verdichterstufen verwendet. Der Luftzuführungskanal 26 mündet in eine in Umfangsrichtung durchgehende Vertiefung 24, die Teil einer Luftführungskammer 25 ist. Die Luftführungskammer 25 wird radial innenliegend von einem Leitsegment 30 begrenzt. Das Leitsegment 30 besitzt eine U-förmige Grundform mit zwei Stegen 32, die in korrespondierend gestaltete Führungsnuten 22 des Trägersegmentes 20 eingreifen. Each jacket segment 10 is assigned to a carrier segment 20, which in is not shown in detail on a housing 100 is fixed. The support segment 20 is in a substantially radial direction from an air supply duct 26 penetrates through the cooling air from a not shown Cooling air supply is supplied. For example, a partial air flow is used as cooling air used from one of the upstream compressor stages. The air supply duct 26 opens into a continuous recess 24 in the circumferential direction, which is part of an air duct chamber 25. The air guide chamber 25 becomes radial limited on the inside by a guide segment 30. The leading segment 30 has a U-shaped basic shape with two webs 32, which designed in corresponding Engage guide grooves 22 of the carrier segment 20.

Gegenüberliegend stützt sich das Leitsegment 30 an zwei als Rippen ausgebildeten Abstandshaltern 12 ab, die in Umfangsrichtung verlaufend und in radialer Richtung abstehend an der Rückseite des Mantelsegmentes 10 angebracht sind. Somit entsteht in radialer Richtung zwischen dem Mantelsegment 10 und dem Leitsegment 30 eine Mantelkühlkammer 15.Opposite, the guide segment 30 is supported on two ribs Spacers 12, which run in the circumferential direction and in the radial Direction protruding on the back of the shell segment 10 are attached. Thus arises in the radial direction between the shell segment 10 and the Guide segment 30 a jacket cooling chamber 15.

Wie sich insbesondere aus Fig. 2 ergibt, sind die Leitsegmente 30 mit einer Vielzahl von Durchgangsöffnungen 34 versehen, die eine Fluidverbindung zwischen der Luftführungskammer 25 und der Mantelkühlkammer 15 darstellen und der Ausbildung von Kühlluftstrahlen dienen.As can be seen in particular from FIG. 2, the guide segments 30 have a large number through openings 34 which provide a fluid connection between represent the air guide chamber 25 and the jacket cooling chamber 15 and the Training of cooling air jets serve.

Das Trägersegment 20 und das Mantelsegment 10 weisen Flanschabschnitte 28 beziehungsweise 18 auf, die von Halteklammern 80 umfaßt werden und damit das Trägersegment 20 und das Mantelsegment 10 miteinander verbinden. Die Halteklammern 80 besitzen ein in etwa U-förmiges Querschnittsprofil mit zwei Axialstegen 89, die in korrespondierende Axialnuten 29, 19 des Trägersegments 20 beziehungsweise des Mantelsegmentes 10 eingreifen. Hierdurch entsteht ein axial fluchtender Übergang vom Trägersegment 20 zum Mantelsegment 10.The carrier segment 20 and the jacket segment 10 have flange sections 28 or 18, which are surrounded by retaining clips 80 and thus that Connect the carrier segment 20 and the jacket segment 10 to one another. The retaining clips 80 have an approximately U-shaped cross-sectional profile with two axial webs 89, which in corresponding axial grooves 29, 19 of the support segment 20th or the shell segment 10 engage. This creates an axial aligned transition from the carrier segment 20 to the jacket segment 10.

Dichtungselemente 90 sind in Eckbereichen zwischen den Halteklammern 80 einerseits und den Flanschabschnitten 28 des Trägersegments 20 und den Flanschabschnitten 18 des Mantelsegments 10 andererseits eingesetzt, um einen weitgehend druckdichten Abschluss zwischen den luftführenden Bereichen, insbesondere der Mantelkühlkammer 15 beziehungsweise der Luftführungskammer 25 und der Umgebung sicherzustellen.Sealing elements 90 are in corner areas between the retaining clips 80 on the one hand and the flange portions 28 of the support segment 20 and Flange sections 18 of the shell segment 10, on the other hand, used to form a largely pressure-tight seal between the air-guiding areas, in particular the jacket cooling chamber 15 and the air duct chamber 25 and the surrounding area.

In Umfangsrichtung sind die Leitsegmente 30 zur Bildung von in Umfangsrichtung durchgehenden luftführenden Kanälen überlappend angeordnet. Wie sich aus Fig. 2 ergibt, sind jeweils zwei aneinanderstoßende Leitsegmente 30 so angeordnet, dass sich ein Überlappungsbereich 38 ergibt. Zu diesem Zweck sind die Leitsegmente 30 jeweils an einem Ende so geformt, dass sie in das benachbarte Leitsegment 30 eingeschoben werden können. Hierzu weicht die Außenkontur geringfügig nach innen zurück, so dass sich im Übergangsbereich 38 eine Art Führung ergibt. In the circumferential direction, the guide segments 30 are for forming in the circumferential direction continuous air-guiding channels overlapping. As can be seen from Fig. 2 results, two abutting guide segments 30 are arranged such that there is an overlap area 38. For this purpose, the leading segments are 30 each shaped at one end so that it fits into the adjacent one Guide segment 30 can be inserted. For this, the outer contour gives way slightly backwards, so that a kind Leadership results.

Die Besonderheit der vorliegenden Konstruktion besteht nun darin, dass die Leitsegmente 30 lose mit etwas radialem Spiel gelagert sind und somit eine Relativbewegung zwischen dem Trägersegment 20 und dem Leitsegment 30 ermöglicht wird. Diese Relativbewegung gestattet insbesondere den spannungsfreien Ausgleich unterschiedlicher thermischer Expansion bei instationärem Betriebszuständen, wie beispielsweise beim Hochfahren der Gasturbine, bei denen die Bauteile unterschiedliche Temperaturen aufweisen. Im Falle einer Startphase ist das Trägersegment 20 noch kalt (beispielsweise Umgebungstemperatur), wohingegen das Leitsegment 30 bereits durch Kühlluft höherer Temperatur aus einer der Verdichterstufen stark erwärmt wird.The peculiarity of the present construction is now that the leading segments 30 are loosely stored with some radial play and thus a relative movement between the support segment 20 and the guide segment 30 allows becomes. This relative movement allows tension-free compensation in particular different thermal expansion in transient operating states, such as when starting up the gas turbine, in which the components have different temperatures. In the case of a start phase, the carrier segment 20 still cold (e.g. ambient temperature), whereas the guide segment 30 already by cooling air of higher temperature from one of the compressor stages is strongly heated.

Die über den Luftführungskanal 26 zugeführte Kühlluft beaufschlagt das Leitsegment 30 und drückt dieses radial einwärts gerichtet gegen die Rippen 12 des Mantelsegmentes 10. Durch permanente Kühlluftzufuhr wird eine Druckdifferenz zwischen der Luftführungskammer 25 und der Mantelkühlkammer 15 aufrechterhalten, so dass das Leitsegment 30 während des Betriebes sicher fixiert ist. Darüber hinaus ist die Aufrechterhaltung der Druckdifferenz erforderlich, um die angestrebte Prallkühlung durch Kühlluftstrahlen zu realisieren, welche durch die Durchgangsöffnungen 34 erzeugt werden.The cooling air supplied via the air duct 26 acts on the guide segment 30 and presses it radially inward against the ribs 12 of the Sheath segment 10. A permanent pressure supply creates a pressure difference maintained between the air guide chamber 25 and the jacket cooling chamber 15, so that the guide segment 30 is securely fixed during operation. In addition, the maintenance of the pressure difference is required in order to to achieve the desired impingement cooling by cooling air jets, which are caused by the Through openings 34 are generated.

Zur Vermeidung von Leckverlusten infolge Seitenumströmung der Leitsegmente 30 im Bereich der Stege 32 ist es erforderlich, das axiale Spiel der Stege 32 in den korrespondierenden Führungsnuten 22 möglichst eng zu bemessen.To avoid leakage losses due to the flow around the guide segments 30 in the area of the webs 32, it is necessary to adjust the axial play of the webs 32 in to dimension the corresponding guide grooves 22 as narrowly as possible.

Darüber hinaus wird deutlich, dass infolge der losen Lagerung der einzelnen Leitsegmente 30 auch eine Relativbewegung in Umfangsrichtung zwischen den einzelnen Leitsegmenten 30 auftreten kann. Der Überlappungsbereich 38 muss deshalb so dimensioniert sein, dass gewisse Relativbewegungen ermöglicht werden. Zweckmäßigerweise sind deshalb im Überlappungsbereich 38 zusätzliche Durchgangsöffnungen vorgesehen (in Fig. 2 nicht dargestellt), um die Ausbildung von Kühlluftstrahlen auch in diesem Bereich sicherzustellen. In addition, it becomes clear that due to the loose storage of the individual leading segments 30 also a relative movement in the circumferential direction between the individual Guide segments 30 can occur. The overlap area 38 must therefore be dimensioned so that certain relative movements are made possible. Therefore, additional through openings 38 are expedient in the overlap area provided (not shown in Fig. 2) to the formation of Ensure cooling air jets also in this area.

BezugszeichenlisteReference list

1010th
MantelsegmentSheath segment
1212th
Abstandshalter, RippeSpacer, rib
1515
MantelkühlkammerJacket cooling chamber
1818th
FlanschabschnittFlange section
1919th
AxialnutAxial groove
2020th
TrägersegmentCarrier segment
2222
FührungsnutGuide groove
2424th
Vertiefungdeepening
2525th
LuftführungskammerAir duct chamber
2626
LuftzuführungskanalAir supply duct
2828
FlanschabschnittFlange section
2929
AxialnutAxial groove
3030th
LeitsegmentLead segment
3232
Stegweb
3434
DurchgangsöffnungThrough opening
3838
ÜberlappungsbereichOverlap area
8080
HalteklammerBracket
8989
AxialstegAxial web
9090
DichtungselementSealing element
100100
Gehäusecasing
110110
LaufradWheel
120120
LeitradDiffuser

Claims (10)

Kühlbarer Mantel einer Gasturbine oder dergleichen, mit mehreren bogenförmigen Mantelsegmenten, die in Umfangsrichtung aneinandergrenzend zu einem im Wesentlichen geschlossenen, ein Laufrad, insbesondere einer Hochdruckturbine, umgebenden Mantelring angeordnet sind, wenigstens einer ringförmigen Mantelkühlkammer, die in radialer Richtung zwischen den Mantelsegmenten und bogenförmigen, mit einer Vielzahl von Durchgangsöffnungen versehenen Leitsegmenten gebildet ist, wenigstens einer Luftführungskammer, die in radialer Richtung zwischen den Leitsegmenten und wenigstens einem Trägersegment gebildet ist, sowie wenigstens einem, an dem Trägersegment angebrachten Luftzuführungskanal, der in die Luftführungskammer mündet, dadurch gekennzeichnet, dass die Leitsegmente (30) lose mit radialem Spiel gelagert sind.Coolable jacket of a gas turbine or the like, with a plurality of arc-shaped jacket segments which are arranged adjacent to one another in the circumferential direction to form a substantially closed jacket ring surrounding an impeller, in particular a high-pressure turbine, at least one annular jacket cooling chamber, which is formed in the radial direction between the jacket segments and arcuate guide segments provided with a plurality of through openings, at least one air guide chamber, which is formed in the radial direction between the guide segments and at least one carrier segment, and at least one air supply duct, which is attached to the carrier segment and opens into the air guide chamber, characterized in that the guide segments (30) are loosely supported with radial play. Mantel nach Anspruch 1,
dadurch gekennzeichnet, dass die Leitsegmente (30) lose zwischen dem Trägersegment (20) und Abstandshaltern (12) geführt sind, welche in radialer Richtung abstehend an der Rückseite der Mantelsegmente (10) angebracht sind.
Coat according to claim 1,
characterized in that the guide segments (30) are loosely guided between the carrier segment (20) and spacers (12) which are attached in a radial direction to the rear of the jacket segments (10).
Mantel nach Anspruch 2,
gekennzeichnet durch Abstandshalter (12) in Form von Stegen, Rippen, Pins oder Auflageerhebungen.
Coat according to claim 2,
characterized by spacers (12) in the form of webs, ribs, pins or elevations.
Mantel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die Leitsegmente (30) radiale Stege (32) aufweisen, die mit geringem axialem Spiel in Führungsnuten (22) des Trägersegments (20) geführt sind.
Sheath according to one of the preceding claims,
characterized in that the guide segments (30) have radial webs (32) which are guided in guide grooves (22) of the carrier segment (20) with little axial play.
Mantel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die Leitsegmente (30) ein U-förmiges Querschnittsprofil aufweisen.
Sheath according to one of the preceding claims,
characterized in that the guide segments (30) have a U-shaped cross-sectional profile.
Mantel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die Leitsegmente (30) in Umfangsrichtung überlappend angeordnet sind.
Sheath according to one of the preceding claims,
characterized in that the guide segments (30) are arranged to overlap in the circumferential direction.
Mantel nach Anspruch 6,
dadurch gekennzeichnet, dass die Leitsegmente (30) im Überlappungsbereich (38) eine erhöhte Anzahl von Durchgangsöffnungen (34) aufweisen.
Coat according to claim 6,
characterized in that the guide segments (30) have an increased number of through openings (34) in the overlap region (38).
Mantel nach Anspruch 6,
dadurch gekennzeichnet, dass die Leitsegmente (30) im Überlappungsbereich (38) Durchgangsöffnungen mit vergrößerter Fläche aufweisen.
Coat according to claim 6,
characterized in that the guide segments (30) have through openings with an enlarged area in the overlap region (38).
Mantel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass die Mantelsegmente (10) und die Trägersegmente (20) in Axialrichtung weisende Flanschabschnitte (18; 28) aufweisen und mittels die Flanschabschnitte (18; 28) umgreifender Halteklammern (80) miteinander lösbar verbunden sind.
Sheath according to one of the preceding claims,
characterized in that the jacket segments (10) and the carrier segments (20) have flange sections (18; 28) pointing in the axial direction and detachably connected to one another by means of retaining clips (80) encompassing the flange sections (18; 28).
Mantel nach Anspruch 9,
gekennzeichnet durch Dichtungselemente (90) zwischen den Halteklammern (80) einerseits und den Flanschabschnitten (18; 28) andererseits.
Coat according to claim 9,
characterized by sealing elements (90) between the retaining clips (80) on the one hand and the flange sections (18; 28) on the other.
EP99811095A 1998-11-30 1999-11-26 Coolable shroud for a turbomachine Expired - Lifetime EP1006264B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19855130 1998-11-30
DE19855130A DE19855130A1 (en) 1998-11-30 1998-11-30 Coolable jacket of a gas turbine or the like
US09/450,728 US6322320B1 (en) 1998-11-30 1999-11-30 Coolable casing of a gas turbine or the like

Publications (3)

Publication Number Publication Date
EP1006264A2 true EP1006264A2 (en) 2000-06-07
EP1006264A3 EP1006264A3 (en) 2003-10-22
EP1006264B1 EP1006264B1 (en) 2005-01-05

Family

ID=26050451

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99811095A Expired - Lifetime EP1006264B1 (en) 1998-11-30 1999-11-26 Coolable shroud for a turbomachine

Country Status (4)

Country Link
US (1) US6322320B1 (en)
EP (1) EP1006264B1 (en)
JP (1) JP4489882B2 (en)
DE (1) DE19855130A1 (en)

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Also Published As

Publication number Publication date
EP1006264A3 (en) 2003-10-22
JP4489882B2 (en) 2010-06-23
US6322320B1 (en) 2001-11-27
EP1006264B1 (en) 2005-01-05
JP2000192802A (en) 2000-07-11
DE19855130A1 (en) 2000-05-31

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