EP2347101A1 - Gas turbine - Google Patents

Gas turbine

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Publication number
EP2347101A1
EP2347101A1 EP09827201A EP09827201A EP2347101A1 EP 2347101 A1 EP2347101 A1 EP 2347101A1 EP 09827201 A EP09827201 A EP 09827201A EP 09827201 A EP09827201 A EP 09827201A EP 2347101 A1 EP2347101 A1 EP 2347101A1
Authority
EP
European Patent Office
Prior art keywords
turbine
gas turbine
ring segments
wall
gas
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
EP09827201A
Other languages
German (de)
French (fr)
Other versions
EP2347101B1 (en
Inventor
Francois Benkler
Tobias Buchal
Andreas Böttcher
Martin Hartmann
Patricia Hülsmeier
Uwe Kahlstorf
Ekkehard Maldfeld
Dieter Minninger
Michael Neubauer
Peter Schröder
Rostislav Teteruk
Vyacheslav Veitsman
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP09827201.6A priority Critical patent/EP2347101B1/en
Priority to PL09827201T priority patent/PL2347101T3/en
Publication of EP2347101A1 publication Critical patent/EP2347101A1/en
Application granted granted Critical
Publication of EP2347101B1 publication Critical patent/EP2347101B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings

Definitions

  • the invention relates to a gas turbine having a substantially hollow conical or hollow cylindrical, extending along a machine axis vane carrier and a segmented in the circumferential and / or axial direction in ring segments, substantially hollow cone-shaped or hollow cylindrical outer wall of an annular hot gas path, the ring segments by means of a number are fastened by hooking elements on the inside of the guide blade carrier.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel which is under high pressure and at high temperature, is guided via a turbine unit connected downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
  • guide vanes are also usually arranged between adjacent rotor blade rows and connected to the turbine housing, which are combined into rows of guide blades. These are attached to a usually hollow cylindrical or hollow cone-shaped vane carrier.
  • a particularly high efficiency is a design target.
  • an increase in the degree of efficiency can basically be achieved by increasing the outlet temperature at which the working medium flows from the combustion chamber into and into the turbine unit. Temperatures of about 1200 0 C to 1500 0 C are sought for such gas turbines and also achieved.
  • the hot gas channel is usually lined by so-called ring segments, which form axial sections of the outer wall of the hot gas channel. These are usually fastened via hooking elements on the guide blade carrier, so that the entirety of the ring segments in the circumferential direction as well as the guide blade carrier form a hollow conical or hollow cylindrical structure.
  • the components of the gas turbine can be deformed by different thermal expansion in different operating conditions, which has a direct influence on the size of the radial gap between the blades and the outer wall of the
  • JP 2005-042612 proposes to configure the guide vane carrier to be coolable, whereby the thermally induced deformation should be avoided. According to JP 54-081409 this problem is to be solved with several gas sampling chambers, which leads to a uniform stiffness of the upper and lower housing part.
  • the invention is therefore based on the object to provide a gas turbine, which allows a particularly high efficiency while maintaining the greatest possible operational safety and life.
  • the catching elements of at least one of the ring segments of the input gas turbine are geometrically adjusted in such a way that in the non-operating state the outer wall delimiting the hot gas path has a substantially elliptical cross-sectional contour in a section perpendicular to the machine axis.
  • the invention is based on the consideration that a particularly high efficiency by reducing the radial column in regular operation, ie, for example, full load operation of the gas turbine would be possible.
  • a comparatively large dimension of the radial gaps was required in particular because the turbine deforms differently in different operating states.
  • an ovalization of the cylindrical or conically shaped components of the gas turbine occurs, which must be taken into account in the design of the radial gaps.
  • the ovalization in the operation of the gas turbine should be kept as low as possible.
  • This cross-sectional contour should be designed in such a way that the cross-sectional contour present at room temperature after installation of the gas turbine is then circular due to thermal deformations occurring in the operating state
  • Cross-sectional contour leads This can be achieved by geometrically adjusting the hooking elements of at least one of the ring segments in such a way that, in the non-operating state, the outer wall delimiting the hot gas path is essentially elliptical in a section perpendicular to the machine axis
  • Ring segments with which the hot gas path is lined outside the blades, to manufacture accordingly.
  • the annular segments form in the axial portion of the blades in the circumferential direction of the outer wall of the hot gas path, which thus together form the rotor blades closest to the hollow cone-shaped or hollow cylindrical component of the gas turbine. Therefore, the vertical cross-section of the machine segment to the axis of the outer wall of the hot gas path forming ring segments, the described elliptical cross-sectional contour in the inoperative state.
  • the ring segments forming the outer wall of the hot gas path in the axial section of the rotor blades are usually hooked in the guide blade carrier via hooking elements. Since the vane support is a relatively solid component which has a comparatively large deformation during operation, the cross-sectional contour formed by all ring segments in the operating state is often determined by the attachment or clamping of the ring segments in the vane support and its deformation during operation. It is therefore not absolutely necessary to manufacture the cold contour of the external wall consisting of ring segments in elliptical form, since the deformation induced by the contact points on the interlocking elements is established anyway.
  • the compensation of the ovalization of the guide vane carrier can therefore be achieved by advantageously only the individual hooking elements of the ring segments are adapted so that the outer wall of a substantially elliptical Has cross-sectional contour. Since these ring segments are exchangeable service parts, this makes it possible on the one hand to retrofit existing gas turbines, on the other hand to compensate for manufacturing errors in guide vanes and also a particularly simple adaptation to changing driving styles including other modified measures to reduce the radial gap.
  • the length of the main and minor axes of the elliptical cross-sectional contour is in each case selected such that the respective component has a substantially circular cross-sectional contour by its thermal deformation in the operating state during the production of the hollow cone-shaped or hollow cylindrical components of the gas turbine.
  • This can be done, for example, by introducing an expected in operation by 90 degrees offset ovalization.
  • the elliptical shape of these components is thus chosen so that the deformations are compensated in the operating state just so that the operation produces a circular cross-section and thus over the entire circumference of the gas turbine same radial gaps are present, d. h.,
  • the radial gaps have no variance over the circumference. As a result, even in the construction of the radial gaps can be sized accordingly narrow, which has a higher efficiency of the gas turbine result.
  • the interlocking elements are adapted in their radial length and / or arranged to change the radial position of the interlocking elements in a corresponding retaining groove of the guide blade carrier inserts. These then lie between the hooks of the hooking elements and the retaining groove and thus lead along the circumference to different radial positions of ring segments.
  • De Facto can thus be provided either distributed along the circumference ring segments with different lengths radial entanglements in the vane support, or the Verhakungsetti the ring segments along a circumference are identical, in which case to change the radial Position of the ring segments along the circumference of different thickness supplements are used for the corresponding entanglements.
  • the turbine shaft in the cold operating state, can be displaced in the direction of the hot gas flow, so that an enlargement of the radial gap occurs in the case of a hollow conical shape of the outer wall with enlargement of the radius in the direction of the hot gas flow in the cold inoperative state, and thus in the cold state (eg when starting the combustion process) Gas turbine), the remaining counter-ovalization represents no restriction for the achievable radial gap in the warm state. As a result, an even greater efficiency of the gas turbine can be achieved.
  • such a gas turbine is used in a gas and steam turbine plant.
  • the advantages achieved by the invention are, in particular, that a particularly high efficiency of the gas turbine is achieved by a reduction of the radial gaps by a targeted design of the hollow cone-shaped or hollow cylindrical components of a gas turbine such that they have a substantially elliptical cross-sectional contour in the inoperative state.
  • a particularly high efficiency of the gas turbine is achieved by a reduction of the radial gaps by a targeted design of the hollow cone-shaped or hollow cylindrical components of a gas turbine such that they have a substantially elliptical cross-sectional contour in the inoperative state.
  • FIG. 3 shows a cross section through the guide vane carrier of a gas turbine with incorporated elliptical shape in FIG
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine unit 6 for driving the compressor 2 and a generator or a working machine (not shown).
  • the turbine unit 6 and the compressor 2 are arranged on a common, also referred to as a turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its turbine axis 9.
  • the running in the manner of an annular combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
  • the turbine unit 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the rotor blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rotor blade rows.
  • the turbine unit 6 comprises a number of stationary vanes 14, which are also attached in a donut-like manner to a vane support 16 of the turbine unit 6 to form rows of vanes.
  • the guide vanes 14 serve to guide the flow of the working medium M between two respective rows of rotor blades or rotor blade rings seen in the direction of flow of the working medium M.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of blades 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18 which is arranged to fix the respective vane 14 to a vane support 16 of the turbine unit 6 as a wall element.
  • the platform 18 is a thermally comparatively heavily loaded component which forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine unit 6.
  • Each rotor blade 12 is fastened to the turbine shaft 8 in an analogous manner via a platform 19, also referred to as a blade root.
  • each ring segment 21 is arranged on a guide blade carrier 16 of the turbine unit 6 respectively.
  • the inner surface of each ring segment 21 is also the hot, the
  • In the radial direction is the outer wall from the outer end of the opposite blades 12 spaced by a radial gap.
  • the ring segments 21 arranged between adjacent guide blade rows serve in particular as cover elements which protect the guide blade carrier 16 or other housing built-in components from thermal overload by the hot working medium M flowing through the turbine 6.
  • the combustion chamber 4 is designed in the embodiment as a so-called annular combustion chamber, in which a plurality of circumferentially around the turbine shaft 8 arranged around burners 10 open into a common combustion chamber space.
  • the combustion chamber 4 in its entirety is designed as an annular structure which is positioned around the turbine shaft 8.
  • FIG 2 and FIG 3 show now schematically the guide vane 16 of the gas turbine 1 in a cross section perpendicular to the turbine axis 9 once left in the inoperative state, ie at cold gas turbine 1, and right in the operating state, ie at operating temperature.
  • the guide vane carrier 16 has a material temperature corresponding to the ambient temperature of the gas turbine.
  • the operating temperature is much higher; beyond 100 0 C.
  • the guide blade carrier 16 is composed of an upper segment 24 and a lower segment 26.
  • the two segments 24, 26 are connected to one another via flanges 28 and each form a connecting joint 30 at their connection point.
  • the distance between the apexes 32 of the upper and lower segments 24, 26 is shortened, so that the cross section in the inoperative state nachformt a horizontal ellipse, which is shown on the left in FIG. Due to the thermally induced expansion and enlargement of the distance between the peaks 32 in the operating state, as shown on the right, then results in a substantially circular shape of the vane support 16, as shown in Figure 3 right.
  • the turbine shaft 8 is displaceable along the turbine axis 9.
  • the turbine shaft 8 In the cold state, that is, if there is an elliptical shape of the hot gas channel, then the turbine shaft 8 can be moved in the direction of the hot gas flow direction. As a result of the conical shape of the hot gas channel, this causes an enlargement of the radial gaps. Then, when in operation, a circular cross-section sets by thermal deformation, the turbine shaft 8 is displaced in the reverse direction to optimize the radial gap.
  • the ring segments 21 may be configured by a correspondingly introduced ovalization so that the hot gas channel receives a circular cross-section during operation.
  • the hooking elements for fastening the ring segments 21 on the guide blade carrier 16 can be of different lengths, ie different lengths for different circumferential positions, or inserts between the hook and holding groove on the guide blade carrier 16 are introduced, which influence the radial position of the ring segments 21 with equally long hooking elements .
  • the perpendicular to the machine axis cross-sectional contour of the Ring segments 21 formed radially outer outer wall of the annular hot gas channel is namely largely determined by the passed through the Verhakungs institute the ring segments deformation of the vane support 16. Accordingly, in FIG. 2 and FIG. 3, instead of the guide blade carriers 16, it is also understood that a flange flange outer wall of the hot gas path of a gas turbine is then understood.
  • Ovalization in the operating state can be avoided by such an ellipse-like shape of the guide vane carrier 16 or the outer wall of the hot gas channel of the gas turbine 1 consisting of ring segments.
  • the radial gaps can be designed correspondingly smaller, resulting in a significantly higher overall efficiency of the gas turbine 1 without sacrificing operational safety.

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

Abstract

A gas turbine (1) comprising a plurality of coaxial components disposed one inside the other and designed substantially in the form of hollow cones or hollow cylinders, and comprising a guide vane support (16), is intended to enable an especially high efficiency while maintaining the greatest possible operating safety and operating life. To this end, at least one of the components or the guide vane support has a substantially elliptical cross-sectional contour.

Description

Beschreibungdescription
Gasturbinegas turbine
Die Erfindung betrifft eine Gasturbine mit einem im Wesentlichen hohlkegelförmig oder hohlzylindrisch ausgebildeten, sich entlang einer Maschinenachse erstreckenden Leitschaufelträger und einer in Umfangs- und/oder axialer Richtung in Ringsegmente segmentierten, im Wesentlichen hohlkegelförmig oder hohlzylindrisch ausgebildeten Außenwand eines ringförmigen Heißgaspfades, deren Ringsegmente mittels einer Anzahl von Verhakungselementen an der Innenseite des Leitschaufelträgers befestigt sind.The invention relates to a gas turbine having a substantially hollow conical or hollow cylindrical, extending along a machine axis vane carrier and a segmented in the circumferential and / or axial direction in ring segments, substantially hollow cone-shaped or hollow cylindrical outer wall of an annular hot gas path, the ring segments by means of a number are fastened by hooking elements on the inside of the guide blade carrier.
Gasturbinen werden in vielen Bereichen zum Antrieb von Generatoren oder von Arbeitsmaschinen eingesetzt. Dabei wird der Energieinhalt eines Brennstoffes zur Erzeugung einer Rotationsbewegung einer Turbinenwelle genutzt. Der Brennstoff wird dazu in einer Brennkammer verbrannt, wobei von einem Luftverdichter verdichtete Luft zugeführt wird. Das in der Brennkammer durch die Verbrennung des Brennstoffs erzeugte, unter hohem Druck und unter hoher Temperatur stehende Arbeitsmedium wird dabei über eine der Brennkammer nachgeschaltete Turbi- neneinheit geführt, wo es sich arbeitsleistend entspannt.Gas turbines are used in many areas to drive generators or work machines. In this case, the energy content of a fuel is used to generate a rotational movement of a turbine shaft. For this purpose, the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor. The working medium produced in the combustion chamber by the combustion of the fuel, which is under high pressure and at high temperature, is guided via a turbine unit connected downstream of the combustion chamber, where it relaxes to perform work.
Zur Erzeugung der Rotationsbewegung der Turbinenwelle sind dabei an dieser eine Anzahl von üblicherweise in Schaufelgruppen oder Schaufelreihen zusammengefassten Laufschaufeln angeordnet, die über einen Impulsübertrag aus dem Arbeitsmedium die Turbinenwelle antreiben. Zur Strömungsführung des Arbeitsmediums sind zudem üblicherweise zwischen benachbarten Laufschaufelreihen mit dem Turbinengehäuse verbundene, zu Leitschaufelreihen zusammengefasste Leitschaufeln angeordnet. Diese sind an einem üblicherweise hohlzylinder- oder hohlkegelförmigen Leitschaufelträger befestigt. Bei der Auslegung derartiger Gasturbinen ist zusätzlich zur erreichbaren Leistung üblicherweise ein besonders hoher Wirkungsgrad ein Auslegungsziel. Eine Erhöhung des Wirkungsgrades lässt sich dabei aus thermodynamischen Gründen grundsätz- lieh durch eine Erhöhung der Austrittstemperatur erreichen, mit der das Arbeitsmedium aus der Brennkammer ab und in die Turbineneinheit einströmt. Dabei werden Temperaturen von etwa 12000C bis 15000C für derartige Gasturbinen angestrebt und auch erreicht.To generate the rotational movement of the turbine shaft, a number of rotor blades, which are usually combined into blade groups or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium. For guiding the flow of the working medium, guide vanes are also usually arranged between adjacent rotor blade rows and connected to the turbine housing, which are combined into rows of guide blades. These are attached to a usually hollow cylindrical or hollow cone-shaped vane carrier. In the design of such gas turbines in addition to the achievable power usually a particularly high efficiency is a design target. For reasons of thermodynamics, an increase in the degree of efficiency can basically be achieved by increasing the outlet temperature at which the working medium flows from the combustion chamber into and into the turbine unit. Temperatures of about 1200 0 C to 1500 0 C are sought for such gas turbines and also achieved.
Bei derartig hohen Temperaturen des Arbeitsmediums sind jedoch die diesem ausgesetzten Komponenten und Bauteile hohen thermischen Belastungen ausgesetzt. Daher ist der Heißgaskanal üblicherweise durch so genannte Ringsegmente ausgeklei- det, die axiale Abschnitte der Außenwand des Heißgaskanals bilden. Diese sind üblicherweise über Verhakungselemente am Leitschaufelträger befestigt, so dass die Gesamtheit der Ringsegmente in Umfangsrichtung ebenso wie der Leitschaufelträger eine hohlkegelförmige oder hohlzylindrische Struktur bilden.At such high temperatures of the working medium, however, exposed to this components and components are exposed to high thermal loads. Therefore, the hot gas channel is usually lined by so-called ring segments, which form axial sections of the outer wall of the hot gas channel. These are usually fastened via hooking elements on the guide blade carrier, so that the entirety of the ring segments in the circumferential direction as well as the guide blade carrier form a hollow conical or hollow cylindrical structure.
Die Bauteile der Gasturbine können sich durch unterschiedliche thermische Ausdehnung in unterschiedlichen Betriebszu- ständen verformen, was einen direkten Einfluss auf die Größe der Radialspalte zwischen Laufschaufeln und Außenwand desThe components of the gas turbine can be deformed by different thermal expansion in different operating conditions, which has a direct influence on the size of the radial gap between the blades and the outer wall of the
Heißgaskanals hat. Diese Radialspalte sind beim An- und Abfahren der Turbine anders dimensioniert als im regulären Betrieb. Bei der Konstruktion der Gasturbine sind Bauteile wie Leitschaufelträger oder Außenwand stets so zu dimensionieren, dass die Radialspalte ausreichend groß gehalten sind, um in keinem Betriebszustand Beschädigungen der Gasturbine entstehen zu lassen. Eine entsprechend vergleichsweise großzügige Auslegung der Radialspalte führt jedoch zu erheblichen Einbußen im Wirkungsgrad.Has hot gas channels. These radial gaps are differently dimensioned when starting and stopping the turbine than in regular operation. In the construction of the gas turbine components such as guide vane or outer wall are always to be dimensioned so that the radial gaps are kept sufficiently large to cause any damage to the gas turbine in any operating condition. However, a correspondingly comparatively generous design of the radial gaps leads to considerable losses in the efficiency.
Um diesem Problem zu begegnen, schlägt die JP 2005-042612 vor, den Leitschaufelträger kühlbar auszugestalten, auszugestalten, wodurch die thermisch bedingte Deformation vermieden werden soll. Nach der JP 54-081409 soll dieses Problem mit mehreren Gasentnahmekammern gelöst werden, was zu einer vergleichmäßigten Steifigkeit von oberem und unterem Gehäuseteil führt.In order to counteract this problem, JP 2005-042612 proposes to configure the guide vane carrier to be coolable, whereby the thermally induced deformation should be avoided. According to JP 54-081409 this problem is to be solved with several gas sampling chambers, which leads to a uniform stiffness of the upper and lower housing part.
Der Erfindung liegt daher die Aufgabe zugrunde, eine Gasturbine anzugeben, welche bei Erhaltung der größtmöglichen betrieblichen Sicherheit und Lebensdauer einen besonders hohen Wirkungsgrad ermöglicht.The invention is therefore based on the object to provide a gas turbine, which allows a particularly high efficiency while maintaining the greatest possible operational safety and life.
Diese Aufgabe wird erfindungsgemäß gelöst, indem die Verha- kungselemente zumindest eines der Ringsegmente der Eingangs genannten Gasturbine geometrisch derart angepasst sind, dass im Außerbetriebszustand bei einem Schnitt senkrecht zur Maschinenachse die den Heißgaspfad begrenzende Außenwand eine im Wesentlichen ellipsenförmige Querschnittskontur aufweist.This object is achieved according to the invention in that the catching elements of at least one of the ring segments of the input gas turbine are geometrically adjusted in such a way that in the non-operating state the outer wall delimiting the hot gas path has a substantially elliptical cross-sectional contour in a section perpendicular to the machine axis.
Die Erfindung geht dabei von der Überlegung aus, dass ein besonders hoher Wirkungsgrad durch eine Reduzierung der Radial- spalte im regulären Betrieb, d. h. beispielsweise Volllastbetrieb der Gasturbine möglich wäre. Bisher war eine vergleichsweise große Auslegung der Radialspalte insbesondere deshalb erforderlich, weil sich die Turbine in unterschiedlichen Betriebszuständen unterschiedlich verformt. Insbesondere tritt dabei eine Ovalisierung der zylindrisch oder konisch geformten Bauteile der Gasturbine auf, der bei der Bemessung der Radialspalte Rechnung getragen werden muss. Um eine Reduzierung der Radialspalte bei der Konstruktion der Gasturbine zu ermöglichen, sollte daher die Ovalisierung im Betrieb der Gasturbine möglichst gering gehalten werden. Dies sollte durch eine entsprechend angepasste Querschnittskontur der hohlkegelförmig oder hohlzylindrisch ausgebildeten Bauteile der Gasturbine im Außerbetriebszustand, d. h. bei auf Raumtemperatur abgekühlter Gasturbine erzielt werden. Diese Querschnittskontur sollte derart gestaltet sein, dass die bei nach der Montage der Gasturbine, bei Raumtemperatur vorhandene Querschnittskontur durch im Betriebszustand auftretende thermische Verformungen zu einer dann kreisrunden Querschnittskontur führt. Dies ist erreichbar, indem die Ver- hakungselemente zumindest eines der Ringsegmente geometrisch derart angepasst sind, dass im Außerbetriebszustand bei einem Schnitt senkrecht zur Maschinenachse die den Heißgaspfad begrenzende Außenwand eine im Wesentlichen ellipsenförmigeThe invention is based on the consideration that a particularly high efficiency by reducing the radial column in regular operation, ie, for example, full load operation of the gas turbine would be possible. Until now, a comparatively large dimension of the radial gaps was required in particular because the turbine deforms differently in different operating states. In particular, an ovalization of the cylindrical or conically shaped components of the gas turbine occurs, which must be taken into account in the design of the radial gaps. In order to enable a reduction of the radial gaps in the design of the gas turbine, therefore, the ovalization in the operation of the gas turbine should be kept as low as possible. This should be achieved by a correspondingly adapted cross-sectional contour of the hollow cone-shaped or hollow cylindrical components of the gas turbine in the inoperative state, ie at cooled to room temperature gas turbine. This cross-sectional contour should be designed in such a way that the cross-sectional contour present at room temperature after installation of the gas turbine is then circular due to thermal deformations occurring in the operating state Cross-sectional contour leads. This can be achieved by geometrically adjusting the hooking elements of at least one of the ring segments in such a way that, in the non-operating state, the outer wall delimiting the hot gas path is essentially elliptical in a section perpendicular to the machine axis
Querschnittskontur aufweist. Die thermischen Dehnungen sollen demnach nicht, wie beim Stand der Technik JP 2005-042612 und JP 54-081409, unterdrückt werden.Has cross-sectional contour. Accordingly, the thermal strains should not be suppressed, as in the prior art JP 2005-042612 and JP 54-081409.
Es ist relativ einfach, die eingangs beschriebenenIt is relatively simple, as described above
Ringsegmente, mit denen der Heißgaspfad außerhalb der Laufschaufeln ausgekleidet ist, entsprechend zu fertigen. Die Ringsegmente bilden im axialen Abschnitt der Laufschaufeln in Umfangsrichtung die Außenwand des Heißgaspfades, welche gemeinsam somit das den Laufschaufeln am nächsten liegende hohlkegelförmige oder hohlzylindrische Bauteil der Gasturbine bilden. Daher weist der zur Maschinenachse senkrechte Querschnitt der die Außenwand des Heißgaspfades bildenden Ringsegmente die beschriebene ellipsenförmige Querschnitt- skontur im Außerbetriebszustand auf.Ring segments, with which the hot gas path is lined outside the blades, to manufacture accordingly. The annular segments form in the axial portion of the blades in the circumferential direction of the outer wall of the hot gas path, which thus together form the rotor blades closest to the hollow cone-shaped or hollow cylindrical component of the gas turbine. Therefore, the vertical cross-section of the machine segment to the axis of the outer wall of the hot gas path forming ring segments, the described elliptical cross-sectional contour in the inoperative state.
Die im axialen Abschnitt der Laufschaufeln die Außenwand des Heißgaspfades bildenden Ringsegmente sind dabei üblicherweise im Leitschaufelträger über Verhakungselemente eingehakt. Da der Leitschaufelträger ein relativ massives Bauteil ist, welches eine vergleichsweise starke Verformung im Betrieb aufweist, wird die von allen Ringsegmenten gebildete Querschnittskontur im Betriebszustand häufig durch die Befestigung oder Verspannung der Ringsegmente im Leitschaufelträger und dessen Verformung im Betrieb bestimmt. Es ist daher nicht unbedingt nötig, die kalte Kontur der aus Ringsegmenten bestehenden Außenwand selbst in Ellipsenform zu fertigen, da sich sowieso die von den Kontaktstellen an den Verhakungselementen erzwungene Verformung einstellt. Der Ausgleich der Ovalisierung des Leitschaufelträgers kann daher erreicht werden, indem vorteilhafterweise nur die einzelnen Verhakungselemente der Ringsegmente derart angepasst sind, dass die Außenwand eine im Wesentlichen ellipsenförmige Querschnittskontur aufweist. Da es sich bei diesen Ringsegmenten um austauschbare Serviceteile handelt, ermöglicht dies einerseits eine Nachrüstung bestehender Gasturbinen, andererseits einen Ausgleich von Fertigungsfehlern bei Leitschaufelträgern und weiterhin eine besonders einfache Anpassung an veränderte Fahrweisen inklusive veränderter anderer Maßnahmen zur Reduzierung der Radialspalte.The ring segments forming the outer wall of the hot gas path in the axial section of the rotor blades are usually hooked in the guide blade carrier via hooking elements. Since the vane support is a relatively solid component which has a comparatively large deformation during operation, the cross-sectional contour formed by all ring segments in the operating state is often determined by the attachment or clamping of the ring segments in the vane support and its deformation during operation. It is therefore not absolutely necessary to manufacture the cold contour of the external wall consisting of ring segments in elliptical form, since the deformation induced by the contact points on the interlocking elements is established anyway. The compensation of the ovalization of the guide vane carrier can therefore be achieved by advantageously only the individual hooking elements of the ring segments are adapted so that the outer wall of a substantially elliptical Has cross-sectional contour. Since these ring segments are exchangeable service parts, this makes it possible on the one hand to retrofit existing gas turbines, on the other hand to compensate for manufacturing errors in guide vanes and also a particularly simple adaptation to changing driving styles including other modified measures to reduce the radial gap.
In vorteilhafter Ausgestaltung ist die bei der Herstellung der hohlkegelförmig oder hohlzylindrisch ausgebildeten Bauteile der Gasturbine die Länge der Haupt- und Nebenachse der ellipsenförmigen Querschnittskontur jeweils derart gewählt, dass das jeweilige Bauteil durch seine thermische Verformung im Betriebszustand eine im Wesentlichen kreisförmige Quer- schnittskontur aufweist. Dies kann beispielsweise durch Einbringung einer zur im Betrieb erwarteten um 90 Grad versetzten Ovalisierung geschehen. Die elliptische Form dieser Bauteile ist somit derart gewählt, dass die Verformungen im Betriebszustand genau so ausgeglichen werden, dass im Betrieb ein kreisförmiger Querschnitt entsteht und somit über den gesamten Umfang der Gasturbine gleiche Radialspalte vorliegen, d. h., die Radialspalte über den Umfang keine Varianz mehr aufweisen. Dadurch können bereits bei der Konstruktion die Radialspalte entsprechend eng bemessen werden, was einen höheren Wirkungsgrad der Gasturbine zur Folge hat.In an advantageous embodiment, the length of the main and minor axes of the elliptical cross-sectional contour is in each case selected such that the respective component has a substantially circular cross-sectional contour by its thermal deformation in the operating state during the production of the hollow cone-shaped or hollow cylindrical components of the gas turbine. This can be done, for example, by introducing an expected in operation by 90 degrees offset ovalization. The elliptical shape of these components is thus chosen so that the deformations are compensated in the operating state just so that the operation produces a circular cross-section and thus over the entire circumference of the gas turbine same radial gaps are present, d. h., The radial gaps have no variance over the circumference. As a result, even in the construction of the radial gaps can be sized accordingly narrow, which has a higher efficiency of the gas turbine result.
Vorteilhafterweise sind die Verhakungselemente in ihrer radialen Länge angepasst und/oder zur Veränderung der radialen Lage der Verhakungselemente in einer entsprechenden Haltenut des Leitschaufelträgers Beilagen angeordnet. Diese liegen dann zwischen den Haken der Verhakungselemente und der Haltenut und führen somit entlang des Umfangs gesehen zu unterschiedlich radialen Lagen von Ringsegmenten. De Facto können somit entweder entlang des Umfangs verteilt Ringsegmente mit unterschiedlich langen radialen Verhakungen im Leitschaufelträger vorgesehen sein, oder die Verhakungselemente der Ringsegmente entlang eines Umfangs sind identisch, wobei dann zur Veränderung der radialen Position der Ringsegmente entlang des Umfangs unterschiedlich dicke Beilagen für die entsprechenden Verhakungen verwendet werden .Advantageously, the interlocking elements are adapted in their radial length and / or arranged to change the radial position of the interlocking elements in a corresponding retaining groove of the guide blade carrier inserts. These then lie between the hooks of the hooking elements and the retaining groove and thus lead along the circumference to different radial positions of ring segments. De Facto can thus be provided either distributed along the circumference ring segments with different lengths radial entanglements in the vane support, or the Verhakungselemente the ring segments along a circumference are identical, in which case to change the radial Position of the ring segments along the circumference of different thickness supplements are used for the corresponding entanglements.
Durch die erläuterte ellipsenförmige Ausgestaltung der hohlkegelförmigen oder hohlzylindrischen Bauteile der Gasturbine im Außerbetriebszustand kann für den Betriebszustand eine im Wesentlichen kreisförmige Form erreicht werden, zudem kann die jetzt im Außerbetriebszustand vorliegende elliptische Form bei der Auslegung der Radialspalte und Konstruktion der Gasturbine weiter berücksichtigt werden. Diesem Problem lässt sich begegnen, indem eine mit den beschriebenen gegenoval gefertigten Bauteilen ausgestattete Gasturbine vorteilhafterweise eine Lagereinrichtung der Turbinenwelle aufweist, wel- che derart ausgelegt ist, dass die Turbinenwelle entlang der Turbinenachse verschiebbar ist. Dadurch kann im kalten Betriebszustand die Turbinenwelle in Heißgasflussrichtung verschoben werden, so dass sich bei einer hohlkegelförmigen Form der Außenwand mit Vergrößerung des Radius in Richtung des Heißgasflusses im kalten Außerbetriebszustand eine Vergrößerung der Radialspalte einstellt und somit im kalten Zustand (z. B. beim Anfahren der Gasturbine) die noch vorhandene Gegenovalisierung keine Beschränkung für die im warmen Zustand erzielbaren Radialspalte darstellt. Dadurch ist ein noch größerer Wirkungsgrad der Gasturbine erreichbar.Due to the illustrated elliptical configuration of the hollow cone-shaped or hollow cylindrical components of the gas turbine in the inoperative state, a substantially circular shape can be achieved for the operating state, moreover, the present in the inoperative state elliptical shape can be considered in the design of the radial column and construction of the gas turbine on. This problem can be counteracted by a gas turbine equipped with the described counter-oval-made components advantageously having a bearing device of the turbine shaft, which is designed in such a way that the turbine shaft can be displaced along the turbine axis. As a result, in the cold operating state, the turbine shaft can be displaced in the direction of the hot gas flow, so that an enlargement of the radial gap occurs in the case of a hollow conical shape of the outer wall with enlargement of the radius in the direction of the hot gas flow in the cold inoperative state, and thus in the cold state (eg when starting the combustion process) Gas turbine), the remaining counter-ovalization represents no restriction for the achievable radial gap in the warm state. As a result, an even greater efficiency of the gas turbine can be achieved.
Vorteilhafterweise kommt eine derartige Gasturbine in einer Gas- und Dampfturbinenanlage zum Einsatz.Advantageously, such a gas turbine is used in a gas and steam turbine plant.
Die mit der Erfindung erzielten Vorteile bestehen insbesondere darin, dass durch eine gezielte Ausbildung der hohlkegelförmigen oder hohlzylindrischen Bauteile einer Gasturbine derart, dass diese im Außerbetriebszustand eine im Wesentlichen ellipsenförmige Querschnittkontur aufweisen, ein besonders hoher Wirkungsgrad der Gasturbine durch eine Reduzierung der Radialspalte erreicht wird. Durch eine ellipsenförmige Fertigung, bei der die im Kaltzustand eingebrachte Ovalisierung um 90° gegenüber der im Betrieb auftretenden Ovalisierung verdreht ist, wird die bisherige elliptische Verformung beispielsweise der Außenwand des ringförmigen Heißgaskanals oder die Innenwand des Leitschaufelträgers im Betriebszustand verringert oder vermieden. Durch die Vergleichmäßigung der Radialspalte am Umfang werdenThe advantages achieved by the invention are, in particular, that a particularly high efficiency of the gas turbine is achieved by a reduction of the radial gaps by a targeted design of the hollow cone-shaped or hollow cylindrical components of a gas turbine such that they have a substantially elliptical cross-sectional contour in the inoperative state. By an elliptical production, in which the introduced in the cold state ovalization by 90 ° relative to the occurring during operation Ovalization is twisted, the previous elliptical deformation, for example, the outer wall of the annular hot gas channel or the inner wall of the vane support is reduced or avoided in the operating state. By equalizing the radial gaps on the circumference
Strömungsverluste reduziert und damit der Wirkungsgrad der Maschine verbessert. Zusätzlich lassen sich die Kaltspalte im Neubau reduzieren, da der Betrag der Ovalisierung nicht mehr bei der Spaltgenerierung vorgehalten werden muss.Reduced flow losses and thus improves the efficiency of the machine. In addition, the cold gaps in the new building can be reduced, since the amount of ovalization no longer has to be kept in the gap generation.
Die Erfindung wird anhand einer Zeichnung näher erläutert. Darin zeigen:The invention will be explained in more detail with reference to a drawing. Show:
FIG 1 einen Halbschnitt durch eine Gasturbine,1 shows a half section through a gas turbine,
FIG 2 einen Querschnitt durch den Leitschaufelträger einer Gasturbine nach dem Stand der Technik, und2 shows a cross section through the guide vane carrier of a gas turbine according to the prior art, and
FIG 3 einen Querschnitt durch den Leitschaufelträger ei- ner Gasturbine mit eingebrachter Ellipsenform im3 shows a cross section through the guide vane carrier of a gas turbine with incorporated elliptical shape in FIG
Außerbetriebszustand.Inoperative condition.
Gleiche Teile sind in allen Figuren mit denselben Bezugszeichen versehen.Identical parts are provided with the same reference numerals in all figures.
Die Gasturbine 1 gemäß FIG 1 weist einen Verdichter 2 für Verbrennungsluft, eine Brennkammer 4 sowie eine Turbineneinheit 6 zum Antrieb des Verdichters 2 und eines nicht darge- stellten Generators oder einer Arbeitsmaschine auf. Dazu sind die Turbineneinheit 6 und der Verdichter 2 auf einer gemeinsamen, auch als Turbinenläufer bezeichneten Turbinenwelle 8 angeordnet, mit der auch der Generator bzw. die Arbeitsmaschine verbunden ist, und die um ihre Turbinenachse 9 drehbar gelagert ist. Die in der Art einer Ringbrennkammer ausgeführte Brennkammer 4 ist mit einer Anzahl von Brennern 10 zur Verbrennung eines flüssigen oder gasförmigen Brennstoffs bestückt . Die Turbineneinheit 6 weist eine Anzahl von mit der Turbinenwelle 8 verbundenen, rotierbaren Laufschaufeln 12 auf. Die Laufschaufeln 12 sind kranzförmig an der Turbinenwelle 8 an- geordnet und bilden somit eine Anzahl von Laufschaufelreihen . Weiterhin umfasst die Turbineneinheit 6 eine Anzahl von feststehenden Leitschaufeln 14, die ebenfalls kranzförmig unter der Bildung von Leitschaufelreihen an einem Leitschaufelträger 16 der Turbineneinheit 6 befestigt sind. Die Laufschau- fein 12 dienen dabei zum Antrieb der Turbinenwelle 8 durch Impulsübertrag vom die Turbineneinheit 6 durchströmenden Arbeitsmedium M. Die Leitschaufeln 14 dienen hingegen zur Strömungsführung des Arbeitsmediums M zwischen jeweils zwei in Strömungsrichtung des Arbeitsmediums M gesehen aufeinander folgenden Laufschaufelreihen oder Laufschaufelkränzen . Ein aufeinander folgendes Paar aus einem Kranz von Leitschaufeln 14 oder einer Leitschaufelreihe und aus einem Kranz von Laufschaufeln 12 oder einer Laufschaufelreihe wird dabei auch als Turbinenstufe bezeichnet.The gas turbine 1 according to FIG. 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine unit 6 for driving the compressor 2 and a generator or a working machine (not shown). For this purpose, the turbine unit 6 and the compressor 2 are arranged on a common, also referred to as a turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its turbine axis 9. The running in the manner of an annular combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel. The turbine unit 6 has a number of rotatable blades 12 connected to the turbine shaft 8. The rotor blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rotor blade rows. Furthermore, the turbine unit 6 comprises a number of stationary vanes 14, which are also attached in a donut-like manner to a vane support 16 of the turbine unit 6 to form rows of vanes. On the other hand, the guide vanes 14 serve to guide the flow of the working medium M between two respective rows of rotor blades or rotor blade rings seen in the direction of flow of the working medium M. A successive pair of a ring of vanes 14 or a row of vanes and a ring of blades 12 or a blade row is also referred to as a turbine stage.
Jede Leitschaufel 14 weist eine Plattform 18 auf, die zur Fixierung der jeweiligen Leitschaufel 14 an einem Leitschaufelträger 16 der Turbineneinheit 6 als Wandelement angeordnet ist. Die Plattform 18 ist dabei ein thermisch vergleichsweise stark belastetes Bauteil, das die äußere Begrenzung eines Heißgaskanals für das die Turbineneinheit 6 durchströmende Arbeitsmedium M bildet. Jede Laufschaufei 12 ist in analoger Weise über eine auch als Schaufelfuß bezeichnete Plattform 19 an der Turbinenwelle 8 befestigt.Each vane 14 has a platform 18 which is arranged to fix the respective vane 14 to a vane support 16 of the turbine unit 6 as a wall element. The platform 18 is a thermally comparatively heavily loaded component which forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine unit 6. Each rotor blade 12 is fastened to the turbine shaft 8 in an analogous manner via a platform 19, also referred to as a blade root.
Zwischen den beabstandet voneinander angeordneten Plattformen 18 der Leitschaufeln 14 zweier benachbarter Leitschaufelreihen sind jeweils Ringsegmente 21 an einem Leitschaufelträger 16 der Turbineneinheit 6 angeordnet. Die innere Oberfläche jedes Ringsegments 21 ist dabei ebenfalls dem heißen, dieBetween the spaced-apart platforms 18 of the guide vanes 14 of two adjacent rows of stator blades ring segments 21 are arranged on a guide blade carrier 16 of the turbine unit 6 respectively. The inner surface of each ring segment 21 is also the hot, the
Turbineneinheit 6 durchströmenden Arbeitsmedium M ausgesetzt und begrenzt demnach nach außen den ringförmigen Heißgaspfad als dessen Außenwand. In radialer Richtung ist die Außenwand vom äußeren Ende der ihr gegenüber liegenden Laufschaufeln 12 durch einen Radialspalt beabstandet. Die zwischen benachbarten Leitschaufelreihen angeordneten Ringsegmente 21 dienen dabei insbesondere als Abdeckelemente, die den Leitschaufelträger 16 oder andere Gehäuse-Einbauteile vor einer thermischen Überbeanspruchung durch das die Turbine 6 durchströmende heiße Arbeitsmedium M schützen.Turbine unit 6 flowing through working medium M exposed and therefore limited to the outside of the annular hot gas path as the outer wall. In the radial direction is the outer wall from the outer end of the opposite blades 12 spaced by a radial gap. The ring segments 21 arranged between adjacent guide blade rows serve in particular as cover elements which protect the guide blade carrier 16 or other housing built-in components from thermal overload by the hot working medium M flowing through the turbine 6.
Die Brennkammer 4 ist im Ausführungsbeispiel als so genannte Ringbrennkammer ausgestaltet, bei der eine Vielzahl von in Umfangsrichtung um die Turbinenwelle 8 herum angeordneten Brennern 10 in einen gemeinsamen Brennkammerraum münden. Dazu ist die Brennkammer 4 in ihrer Gesamtheit als ringförmige Struktur ausgestaltet, die um die Turbinenwelle 8 herum posi- tioniert ist.The combustion chamber 4 is designed in the embodiment as a so-called annular combustion chamber, in which a plurality of circumferentially around the turbine shaft 8 arranged around burners 10 open into a common combustion chamber space. For this purpose, the combustion chamber 4 in its entirety is designed as an annular structure which is positioned around the turbine shaft 8.
FIG 2 und FIG 3 zeigen nun schematisch den Leitschaufelträger 16 der Gasturbine 1 in einem Querschnitt senkrecht zur Turbinenachse 9 einmal links im Außerbetriebszustand, d. h. bei kalter Gasturbine 1, und rechts in Betriebszustand, d. h. auf Betriebstemperatur. Im Außerbetriebszustand hat demnach der Leitschaufelträger 16 eine Materialtemperatur entsprechend zur Umgebungstemperatur der Gasturbine. Die Betriebstemperatur dagegen liegt wesentlich höher; jenseits von 1000C. Der Leitschaufelträger 16 ist dabei zusammengesetzt aus einem oberen Segment 24 und einem unteren Segment 26. Die beiden Segmente 24, 26 sind über Flansche 28 miteinander verbunden und bilden an ihrer Verbindungsstelle jeweils eine Verbindungsfuge 30.FIG 2 and FIG 3 show now schematically the guide vane 16 of the gas turbine 1 in a cross section perpendicular to the turbine axis 9 once left in the inoperative state, ie at cold gas turbine 1, and right in the operating state, ie at operating temperature. In the inoperative state, therefore, the guide vane carrier 16 has a material temperature corresponding to the ambient temperature of the gas turbine. The operating temperature, however, is much higher; beyond 100 0 C. The guide blade carrier 16 is composed of an upper segment 24 and a lower segment 26. The two segments 24, 26 are connected to one another via flanges 28 and each form a connecting joint 30 at their connection point.
Durch die hohen Betriebstemperaturen der Gasturbine 1 stellt sich im Betriebszustand - wie rechts in der FIG 2 dargestellt - eine Verformung des Leitschaufelträgers 16 nach dem Stand der Technik dergestalt ein, dass sich der Abstand zwischen den Scheiteln 32 des jeweils oberen und unteren Teils 24, 26 vergrößert. Der Querschnitt des Leitschaufelträgers 16 verformt sich dabei zu einer stehenden Ellipse. Eine kreisrunde Kontur ist zum Vergleich in gestrichelter Linienart gezeigt. Diese Verformung kann nun durch eine gezielt eingebrachte ellipsenförmige Ausgestaltung des Querschnitts des Leitschaufelträgers 16 im kalten Außerbetriebszustand ausgeglichen werden, wie in FIG 3 dargestellt. Im Außerbetriebszustand ist der Abstand zwischen den Scheiteln 32 des oberen und unteren Segments 24, 26 verkürzt, so dass der Querschnitt im Außerbetriebszustand eine liegende Ellipse nachformt, was in FIG 3 links dargestellt ist. Durch die thermisch bedingte Ausdeh- nung und Vergrößerung des Abstandes zwischen den Scheiteln 32 im Betriebszustand, wie rechts dargestellt, ergibt sich dann eine im Wesentlichen kreisförmige Form des Leitschaufelträgers 16, wie in FIG 3 rechts dargestellt.Due to the high operating temperatures of the gas turbine 1, in the operating state-as shown on the right in FIG. 2 -a deformation of the guide blade carrier 16 according to the prior art takes place such that the distance between the peaks 32 of the respective upper and lower parts 24, 26 increased. The cross section of the guide blade carrier 16 thereby deforms into a vertical ellipse. A circular contour is shown for comparison in dashed line style. This deformation can now be compensated for by a deliberately introduced elliptical configuration of the cross section of the guide blade carrier 16 in the cold inoperative state, as shown in FIG. In the inoperative state, the distance between the apexes 32 of the upper and lower segments 24, 26 is shortened, so that the cross section in the inoperative state nachformt a horizontal ellipse, which is shown on the left in FIG. Due to the thermally induced expansion and enlargement of the distance between the peaks 32 in the operating state, as shown on the right, then results in a substantially circular shape of the vane support 16, as shown in Figure 3 right.
Um im Außerbetriebszustand keine Einschränkungen durch die eingebrachte Ovalisierung hinsichtlich der Radialspalte entstehen zu lassen, ist die Turbinenwelle 8 entlang der Turbinenachse 9 verschiebbar. Im kalten Zustand, wenn also eine elliptische Form des Heißgaskanals vorliegt, kann dann die Turbinenwelle 8 in Richtung der Heißgasflussrichtung verschoben werden. Durch die Kegelform des Heißgaskanals stellt sich dadurch eine Vergrößerung der Radialspalte ein. Wenn sich dann im Betriebszustand ein kreisförmiger Querschnitt durch thermische Verformung einstellt, wird die Turbinenwelle 8 in umgekehrter Richtung verschoben, um die Radialspalte zu optimieren .In order not to create any restrictions in the inoperative state due to the introduced ovalization with respect to the radial gaps, the turbine shaft 8 is displaceable along the turbine axis 9. In the cold state, that is, if there is an elliptical shape of the hot gas channel, then the turbine shaft 8 can be moved in the direction of the hot gas flow direction. As a result of the conical shape of the hot gas channel, this causes an enlargement of the radial gaps. Then, when in operation, a circular cross-section sets by thermal deformation, the turbine shaft 8 is displaced in the reverse direction to optimize the radial gap.
Alternativ können auch die Ringsegmente 21 durch eine entsprechend eingebrachte Ovalisierung so ausgestaltet sein, dass der Heißgaskanal im Betrieb einen kreisförmigen Querschnitt erhält. Dazu können die Verhakungselemente zur Befestigung der Ringsegmente 21 am Leitschaufelträger 16 unterschiedlich lang sein, d. h. für unterschiedliche Umfangsposi- tionen unterschiedlich lang sein, oder Beilagen zwischen Haken und Haltenut am Leitschaufelträger 16 eingebracht werden, die die radiale Lage der betreffenden Ringsegmente 21 mit gleichlangen Verhakungselementen beeinflussen. Die zur Maschinenachse senkrechte Querschnittskontur der aus den Ringsegmenten 21 gebildeten radial äußeren Außenwand des ringförmigen Heißgaskanals wird nämlich über die durch die Verhakungselemente der Ringsegmente weitergegebene Verformung des Leitschaufelträgers 16 weitgehend bestimmt. Demnach kann in FIG 2 und FIG 3 anstelle von Leitschaufelträgern 16 auch eine - dann flanschlose - Außenwand des Heißgaspfades einer Gasturbine verstanden sein.Alternatively, the ring segments 21 may be configured by a correspondingly introduced ovalization so that the hot gas channel receives a circular cross-section during operation. For this purpose, the hooking elements for fastening the ring segments 21 on the guide blade carrier 16 can be of different lengths, ie different lengths for different circumferential positions, or inserts between the hook and holding groove on the guide blade carrier 16 are introduced, which influence the radial position of the ring segments 21 with equally long hooking elements , The perpendicular to the machine axis cross-sectional contour of the Ring segments 21 formed radially outer outer wall of the annular hot gas channel is namely largely determined by the passed through the Verhakungselemente the ring segments deformation of the vane support 16. Accordingly, in FIG. 2 and FIG. 3, instead of the guide blade carriers 16, it is also understood that a flange flange outer wall of the hot gas path of a gas turbine is then understood.
Durch eine derartige ellipsenartige Ausformung des Leitschau- felträgers 16 oder der aus Ringsegmenten bestehenden Außenwand des Heißgaskanals der Gasturbine 1 kann die Ovalisierung im Betriebszustand vermieden werden. Dadurch lassen sich bei der Konstruktion der Gasturbine 1 die Radialspalte entsprechend kleiner auslegen, was insgesamt einen wesentlich höheren Wirkungsgrad der Gasturbine 1 ohne Einbußen hinsichtlich der betrieblichen Sicherheit zur Folge hat. Ovalization in the operating state can be avoided by such an ellipse-like shape of the guide vane carrier 16 or the outer wall of the hot gas channel of the gas turbine 1 consisting of ring segments. As a result, in the design of the gas turbine 1, the radial gaps can be designed correspondingly smaller, resulting in a significantly higher overall efficiency of the gas turbine 1 without sacrificing operational safety.

Claims

Patentansprüche claims
1. Gasturbine (1) mit einem im Wesentlichen hohlkegelförmig oder hohlzylindrisch ausgebildeten, sich entlang einer1. Gas turbine (1) with a substantially hollow cone-shaped or hollow cylindrical, along a
Maschinenachse erstreckenden Leitschaufelträger (16) und einer in Umfangs- und/oder axialer Richtung in Ringsegmente (21) segmentierten, im Wesentlichen hohlkegelförmig oder hohlzylindrisch ausgebildeten Außenwand eines ringförmigen Heißgaspfades, deren Ringsegmente (21) mittels einer Anzahl von Verhakungselementen an der Innenseite des Leitschaufelträgers (16) befestigt sind, dadurch gekennzeichnet, dass die Verhakungselemente zumindest eines der Ringsegmente (21) geometrisch derart angepasst sind, dass imMachine axis extending guide blade carrier (16) and a circumferentially and / or axially in ring segments (21) formed substantially hollow cone-shaped or hollow cylindrical outer wall of an annular hot gas path whose ring segments (21) by means of a number of interlocking elements on the inside of the guide vane carrier ( 16) are fastened, characterized in that the interlocking elements of at least one of the ring segments (21) are geometrically adjusted in such a way that in
Außerbetriebszustand bei einem Schnitt senkrecht zur Maschinenachse die den Heißgaspfad begrenzende Außenwand eine im Wesentlichen ellipsenförmige Querschnittskontur aufweist .Inoperative state in a section perpendicular to the machine axis which has the hot gas path limiting outer wall has a substantially elliptical cross-sectional contour.
2. Gasturbine (1) nach Anspruch 1, bei der die Länge der Haupt- und Nebenachse der ellipsen- förmigen Querschnittskontur jeweils derart gewählt sind, dass die Außenwand nach der im Betriebszustand auftretenden thermischen Verformung eine im Wesentlichen kreisförmige Querschnittskontur aufweist.2. Gas turbine (1) according to claim 1, wherein the length of the major and minor axes of the elliptical cross-sectional contour are each selected such that the outer wall has a substantially circular cross-sectional contour after the thermal deformation occurring in the operating state.
3. Gasturbine (1) nach Anspruch 1 oder 2, bei der die Verhakungselemente in ihrer radialen Länge an- gepasst sind und/oder für unterschiedliche radiale Positionen der Verhakungselemente in einer Haltenut des Leitschaufelträgers (16) Beilagen angeordnet sind.3. Gas turbine (1) according to claim 1 or 2, wherein the Verhakungselemente are adapted in their radial length and / or for different radial positions of the hooking elements in a retaining groove of the guide blade carrier (16) inserts are arranged.
4. Gasturbine (1) nach einem der Ansprüche 1 bis 3, die eine Turbinenwelle (8) mit einer Anzahl von zu Laufschaufelreihen gruppierten, umlaufend angeordneten Laufschaufeln (12) und eine Lagereinrichtung der Turbinenwelle (8) umfasst, welche derart ausgelegt ist, dass die Turbi- nenwelle (8) entlang der Turbinenachse (9) verschiebbar ist .4. A gas turbine (1) according to any one of claims 1 to 3, comprising a turbine shaft (8) with a number of circumferentially arranged arranged rotor blades (12) and a bearing device of the turbine shaft (8), which is designed such that the tur- nenwelle (8) along the turbine axis (9) is displaceable.
5. Gas- und Dampfturbinenanlage mit einer Gasturbine (1) nach einem der Ansprüche 1 bis 4. 5. Gas and steam turbine plant with a gas turbine (1) according to one of claims 1 to 4.
EP09827201.6A 2008-11-19 2009-09-15 Gas turbine and corresponding gas or steam turbine plant Not-in-force EP2347101B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP09827201.6A EP2347101B1 (en) 2008-11-19 2009-09-15 Gas turbine and corresponding gas or steam turbine plant
PL09827201T PL2347101T3 (en) 2008-11-19 2009-09-15 Gas turbine and corresponding gas or steam turbine plant

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08020190A EP2189630A1 (en) 2008-11-19 2008-11-19 Gas turbine, guide vane support for such a gas turbine and gas or steam turbine plant with such a gas turbine
EP09827201.6A EP2347101B1 (en) 2008-11-19 2009-09-15 Gas turbine and corresponding gas or steam turbine plant
PCT/EP2009/061936 WO2010057698A1 (en) 2008-11-19 2009-09-15 Gas turbine

Publications (2)

Publication Number Publication Date
EP2347101A1 true EP2347101A1 (en) 2011-07-27
EP2347101B1 EP2347101B1 (en) 2013-07-03

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EP08020190A Withdrawn EP2189630A1 (en) 2008-11-19 2008-11-19 Gas turbine, guide vane support for such a gas turbine and gas or steam turbine plant with such a gas turbine
EP09827201.6A Not-in-force EP2347101B1 (en) 2008-11-19 2009-09-15 Gas turbine and corresponding gas or steam turbine plant

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08020190A Withdrawn EP2189630A1 (en) 2008-11-19 2008-11-19 Gas turbine, guide vane support for such a gas turbine and gas or steam turbine plant with such a gas turbine

Country Status (7)

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US (1) US9074490B2 (en)
EP (2) EP2189630A1 (en)
JP (1) JP5281167B2 (en)
CN (1) CN102216570B (en)
ES (1) ES2426099T3 (en)
PL (1) PL2347101T3 (en)
WO (1) WO2010057698A1 (en)

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Also Published As

Publication number Publication date
US9074490B2 (en) 2015-07-07
CN102216570A (en) 2011-10-12
EP2189630A1 (en) 2010-05-26
EP2347101B1 (en) 2013-07-03
ES2426099T3 (en) 2013-10-21
PL2347101T3 (en) 2013-12-31
WO2010057698A1 (en) 2010-05-27
JP5281167B2 (en) 2013-09-04
US20110280721A1 (en) 2011-11-17
CN102216570B (en) 2014-03-05
JP2012508843A (en) 2012-04-12

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