EP2137382B1 - Stator heat shield - Google Patents

Stator heat shield Download PDF

Info

Publication number
EP2137382B1
EP2137382B1 EP08735874A EP08735874A EP2137382B1 EP 2137382 B1 EP2137382 B1 EP 2137382B1 EP 08735874 A EP08735874 A EP 08735874A EP 08735874 A EP08735874 A EP 08735874A EP 2137382 B1 EP2137382 B1 EP 2137382B1
Authority
EP
European Patent Office
Prior art keywords
heat shield
stator heat
gas turbine
stator
ribs
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.)
Active
Application number
EP08735874A
Other languages
German (de)
French (fr)
Other versions
EP2137382A1 (en
Inventor
Alexander Khanin
Edouard Sloutski
Sergey Vorontsov
Anton Sumin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Priority to SI200830743T priority Critical patent/SI2137382T1/en
Publication of EP2137382A1 publication Critical patent/EP2137382A1/en
Application granted granted Critical
Publication of EP2137382B1 publication Critical patent/EP2137382B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a stator heat shield for a gas turbine according to the preamble of claim 1 and a gas turbine equipped with such a stator heat shield.
  • Statorhitzeschilde are in the installed state of a stator or on a housing of a gas turbine. In this case, they are usually mounted on a guide blade carrier and form a radial boundary for a hot gas path of the gas turbine in the region of rotor blades of the gas turbine. In this case, a plurality of such Statorhitzeschilde is arranged adjacent to each other in the circumferential direction relative to a rotational axis of the rotor with respect to each other, whereby a closed ring of individual Statorhitzeschilden is formed.
  • the individual stator heat shields form ring segments. The stator heat shields protect the housing or the guide blade carrier from being exposed to the hot gas of the gas turbine.
  • the invention deals with the problem of providing an improved embodiment for a stator heat shield or for a gas turbine equipped therewith, which is characterized in particular by an increased service life of the stator heat shields.
  • the present invention is based on the general idea of combining a flapper cooling, a convection cooling and a sealing element cooling with each other in the stator heat shield, thereby providing a plurality of ribs formed on an inner side facing away from a hot gas path of the gas turbine in the installed state of the stator heat shield, which ribs are in the installed state with respect to an axis of rotation a rotor of the gas turbine extend axially and are spaced apart in the circumferential direction, so that can be formed on the inside of several channels. At the same time, these ribs serve to stiffen the respective stator heat shield. On the inside of a baffle plate is also arranged, which rests on the ribs.
  • the respective stator heat shield is provided with a groove, at least on a front side delimiting the stator heat shield in the circumferential direction, into which groove at least one sealing element can be inserted. Two circumferentially adjacent stator heat shields adjoin one another in the region of these end faces, wherein a relatively small gap is formed as a rule.
  • the respective sealing element now engages in the mutually aligned grooves of the two mutually opposite in the gap end faces and thereby closes the gap and thus the connection between the outside facing the hot gas path with a the inside facing cooling gas path.
  • the stator heat shield with a plurality of bores, which open at one end on the inside and the other end on the end face, in such a way that they open out from the groove in the direction of the outside.
  • the holes are arranged spaced apart in the axial direction. Through these holes, cooling gas can pass from the cooling gas path to the hot gas side in the gap between adjacent stator heat shields in the circumferential direction and can there apply cooling gas to the sealing elements.
  • film cooling of the sealing elements as well as the opposite end faces of the adjacent stator heat shields in the gap can be achieved in the region of the gap.
  • a targeted cooling of this area reduces the temperatures at the respective stator heat shield at the front ends, which reduces the heat load of the stator heat shield.
  • FIG. 1 has a gas turbine 1, of which only a small section is shown here, a stator 2 and a rotor 3, which are also shown only partially. From the stator 2 guide vanes 4 are partially visible and a portion of a vane carrier 5. On the guide vane 5 are on the one hand the vanes 4 attached to the other stator stator 5 are also attached to the stator vane 5, one of which is recognizable here. From the rotor 3, only one blade 7 can be seen here, which is arranged between the two guide vanes 4. A dot-dash line indicates a rotation axis 8 about which the rotor 3 rotates during operation of the gas turbine 1 and which defines the axial direction of the gas turbine 1.
  • Axial in the present context thus means parallel to the axis of rotation 8, while a radial direction is perpendicular to the axis of rotation 8 and a circumferential direction along a circular path about the axis of rotation 8 is oriented.
  • the blade 7 is arranged axially between the two guide vanes 4.
  • the stator heat shield 6 is disposed radially of the blade 7 and positioned axially between the two vanes 4.
  • the individual Statorhitzeschilde 6 form segments which are arranged adjacent to each other in the circumferential direction and form a closed circular ring which encloses a blade row, which is formed by circumferentially adjacent blades 7.
  • the respective stator heat shield 6 separates a hot gas path 9 of the gas turbine 1, indicated by an arrow, from a cooling gas path 10, likewise indicated by an arrow, which runs essentially in the stator 2.
  • the respective stator heat shield 6 has an outer side 11, which faces the hot gas path 9 in the installed state.
  • the stator heat shield 6 has an inner side 12, which faces the cooling gas path 10 and is remote from the hot gas path 9 and from the outer side 11.
  • the stator heat shield 6 has a plurality of ribs 13. These ribs 13 extend axially in the installed state and are preferably designed in a straight line. Furthermore, the ribs 13 are spaced from each other in the circumferential direction.
  • at least one baffle plate 14, which rests on the ribs 13, is arranged on the inner side 12. In the in Fig. 2 As shown, the baffle plate 14 extends only over one half of the inner side 12. A second baffle plate 14 covering the other half is omitted here for better recognition of the ribs 13. Likewise, a single baffle plate 14 may be provided which covers all the ribs 13.
  • the respective stator heat shield 6 also has, in the circumferential direction, two end faces 15, each delimiting the stator heat shield 6 in the circumferential direction. In at least one of these end faces 15, a groove 16 is incorporated. Preferably, in each case such a groove 16 is incorporated in both end faces 15.
  • two stator heat shields 6 which are adjacent to one another in the circumferential direction adjoin one another in the region of these end faces 15, each two such end faces 15 in an in Fig. 3 indicated axial gap 17 are opposite to each other.
  • the grooves 16 are arranged so that they are aligned with each other in the axial gap 17 opposite end faces 15 to each other.
  • the respective groove 16 serves to receive at least one sealing element 18, which is configured, for example, band-shaped or strip-shaped.
  • such a sealing element 18 engages in two mutually aligned grooves 16 at two in the gap 17 opposite end faces 15 at the same time. In this way, the respective sealing element 18 can seal off the axial gap 17, ie separate the hot gas path 9 facing the hot gas path from the cooling gas side facing the cooling gas path 10.
  • the stator heat shield 6 is also equipped with several holes 19.
  • Each of these holes 19 connects the inner side 12 of one of the end faces 15. Accordingly, the respective bore 19 opens at one end to the inner side 12 and the other end to the respective end face 15.
  • the mouth of the respective bore 19 at the respective end face 15 is spaced from the groove 16, in the direction of the outside 11. In this way, through the bores 19, cooling gas can pass from the cooling gas side or from the cooling gas path 10 to the hot gas side of the gap 17, which is open toward the hot gas path 9.
  • the individual holes 19 are according to Fig. 2 spaced apart in the axial direction formed on the respective end face 15 of the stator heat shield 6.
  • the front side 15 provided with the bores 19 is equipped with the recess 20.
  • both end faces 15 are provided with holes 19 and such a recess 20.
  • the recesses 20 also allow the cooling gas to escape sufficiently through the bores 19 if the gap 17 becomes comparatively narrow in the circumferential direction due to relative movements of the adjacent stator heat shields 6.
  • a cooling of the sealing elements 18 can be effected during operation of the gas turbine 1.
  • a cooling gas film can be produced on the hot gas side of the sealing elements 18, which obstructs direct hot gas loading of the sealing elements 18.
  • the circumferential end regions of the respective stator heat shield 6 provided with the end faces 15 can effectively be cooled thereby, on the one hand by the flow of these end regions with cooling gas and on the other hand by the formation of the cooling gas film on the areas of the front side 15 and the outside 11 exposed to the hot gas path 9 ,
  • a recess 21 is formed.
  • the ribs 13 are arranged, in such a way that within the recess 21, a system of mutually communicating channels 22 is formed.
  • the at least one baffle plate 14 covers this system from channels 22 to the cooling gas path 10 from.
  • Within these channels 22 there is a convective heat transfer between the respective stator heat shield 6 and the respective baffle plate 14.
  • a cooling gas flow is conducted through the channel system formed with the channels 22.
  • the respective baffle plate 14 has a plurality of passage openings 23 through which cooling gas can pass from the cooling gas path 10 through the baffle plate 14 into the channels 22.
  • the aforementioned holes 19 now open on the inner side 12 in said recess 21 or in one of the channels 22.
  • brackets 24 are formed here, with the aid of which the respective baffle plate 14 can be fixed to the stator heat shield 6.
  • the respective holders 24 overlap the respective flat plate 14 for this purpose.
  • the ribs 13 each have a certain rib height 25, with which they extend in the radial direction. With this fin height 25, the ribs 13 are here from a bottom of the recess 21 from. Furthermore, the individual ribs 13 in the circumferential direction on a rib spacing 26 from each other. The fin height 25 and fin spacing 26 are matched to one another such that a ratio of fin height 25 to fin spacing 26 is in a range of 0.328 to 0.492.
  • each individual hole 19 has in the axial direction a certain bore spacing 27 to each other. Furthermore, each individual bore has a specific bore diameter 28. The respective bore diameter 28 and the hole spacing 2 are matched to each other to give a bore diameter to hole spacing ratio 27 ranging from 0.0992 to 0.1488.

Abstract

The present invention relates to a stator heat shield (6) for a gas turbine (1), comprising an outer side (11) which, in the installed state, faces a hot gas path (9) of the gas turbine (1), an inner side (12) facing away from the outer side (11), multiple ribs which are formed at the inner side (12) and which, in the installed state, extend axially with respect to an axis of rotation (8) of a rotor (3) of the gas turbine (1) and which are at a distance from one another in the circumferential direction, at least one splash plate (14) which is disposed at the inner side (12) and which lies on the ribs (13), at least one groove (16) which is formed in a front face (15) which forms the boundary of the stator heat shield (6) in the circumferential direction and into which at least one sealing element (18) can be inserted, and multiple boreholes (19) which terminate at a distance from one another in the direction to the outer side (11), with one end at the inner side (12) and the other end at the front face (15) of the groove (16), and which are at a distance from one another in the axial direction.

Description

Technisches GebietTechnical area

Die Erfindung betrifft ein Statorhitzeschild für eine Gasturbine gemäß dem Oberbegriff des Anspruchs 1 sowie eine mit einem derartigen Statorhitzeschild ausgestattete Gasturbine.The invention relates to a stator heat shield for a gas turbine according to the preamble of claim 1 and a gas turbine equipped with such a stator heat shield.

Stand der TechnikState of the art

Statorhitzeschilde befinden sich im Einbauzustand an einem Stator beziehungsweise an einem Gehäuse einer Gasturbine. Dabei sind sie üblicherweise an einem Leitschaufelträger angebracht und bilden im Bereich von Laufschaufeln eines Rotors der Gasturbine eine radiale Begrenzung für einen Heißgaspfad der Gasturbine. Dabei ist in der Regel eine Vielzahl derartiger Statorhitzeschilde bezüglich einer Rotationsachse des Rotors in Umfangsrichtung zueinander benachbart angeordnet, wodurch ein geschlossener Ring aus einzelnen Statorhitzeschilden gebildet wird. Die einzelnen Statorhitzeschilde bilden dabei Ringsegmente. Die Statorhitzeschilde schützen das Gehäuse beziehungsweise den Leitschaufelträger vor einer Beaufschlagung mit dem Heißgas der Gasturbine. Dabei ist eine Außenseite der Statorhitzeschilde dem Heißgas ausgesetzt, während eine vom Heißgaspfad abgewandte Innenseite des jeweiligen Statorhitzeschilds mit einem geeigneten Kühlgas beaufschlagt wird, um das jeweilige Statorhitzeschild zu kühlen. Hierzu kann beispielhaft auf die EP1176285A2 , EP1048822A2 , EP1749975A2 , EP1775423A2 und US2001/0005555A1 verwiesen werden. Durch die Kühlung kann die Standzeit der Statorhitzeschilde vergrößert werden.Statorhitzeschilde are in the installed state of a stator or on a housing of a gas turbine. In this case, they are usually mounted on a guide blade carrier and form a radial boundary for a hot gas path of the gas turbine in the region of rotor blades of the gas turbine. In this case, a plurality of such Statorhitzeschilde is arranged adjacent to each other in the circumferential direction relative to a rotational axis of the rotor with respect to each other, whereby a closed ring of individual Statorhitzeschilden is formed. The individual stator heat shields form ring segments. The stator heat shields protect the housing or the guide blade carrier from being exposed to the hot gas of the gas turbine. In this case, an outside of the Statorhitzeschilde is exposed to the hot gas, while facing away from the hot gas path inside the respective stator heat shield is supplied with a suitable cooling gas to cool the respective stator heat shield. This can be exemplified in the EP1176285A2 . EP1048822A2 . EP1749975A2 . EP1775423A2 and US2001 / 0005555A1 to get expelled. By cooling the service life of the stator heat shields can be increased.

Grundsätzlich besteht jedoch das Bedürfnis, die Standtzeit derartiger Statorhitzeschilde zusätzlich zu vergrößern.In principle, however, there is a need to additionally increase the service life of such stator heat shields.

Darstellung der ErfindungPresentation of the invention

Hier setzt die vorliegende Erfindung an. Die Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, beschäftigt sich mit dem Problem, für ein Statorhitzeschild beziehungsweise für eine damit ausgestattete Gasturbine eine verbesserte Ausführungsform anzugeben, die sich insbesondere durch eine erhöhte Standzeit der Statorhitzeschilde auszeichnet.This is where the present invention begins. The invention, as characterized in the claims, deals with the problem of providing an improved embodiment for a stator heat shield or for a gas turbine equipped therewith, which is characterized in particular by an increased service life of the stator heat shields.

Erfindungsgemäß wird dieses Problem durch die Merkmale des Anspruches 1 gelöst. Vorteilhafte Ausführungsformen sind Gegenstand der abhängigen Ansprüche.According to the invention this problem is solved by the features of claim 1. Advantageous embodiments are the subject of the dependent claims.

Die vorliegende Erfindung beruht auf dem allgemeinen Gedanken, beim jeweiligen Statorhitzeschild eine Prallplattenkühlung, eine Konvektionskühlung und eine Dichtelementkühlung miteinander zu kombinieren und dabei mehrere an einer im Einbauzustand des Statorhitzeschilds von einem Heißgaspfad der Gasturbine abgewandten Innenseite ausgebildete Rippen vorzusehen, die sich im Einbauzustand bezüglich einer Rotationsachse eines Rotors der Gasturbine axial erstrecken und in Umfangsrichtung zueinander beabstandet sind, so dass sich an der Innenseite mehrere Kanäle ausbilden lassen. Gleichzeitig dienen diese Rippen zur Aussteifung des jeweiligen Statorhitzeschilds. An der Innenseite ist außerdem eine Prallplatte angeordnet, die auf den Rippen aufliegt. Auf diese Weise kann innerhalb der Kanäle durch Konvektion Wärme vom Statorhitzeschild auf die jeweilige Prallplatte übertragen werden. Die Prallplatte selbst ist im Betrieb der Gasturbine von einem Kühlgas beaufschlagt, wodurch die Wärme von der Prallplatte abführbar ist. Des weiteren ist das jeweilige Statorhitzeschild zumindest an einer das Statorhitzeschild in Umfangsrichtung begrenzenden Stirnseite mit einer Nut ausgestattet, in die zumindest ein Dichtelement einsetzbar ist. Zwei in Umfangsrichtung zueinander benachbarte Statorhitzeschilde grenzen im Bereich dieser Stirnseiten aneinander an, wobei in der Regel ein relativ kleiner Spalt ausgebildet ist. Das jeweilige Dichtelement greift nun in die zueinander fluchtend ausgerichteten Nuten der beiden einander im Spalt gegenüberliegenden Stirnseiten ein und verschließt dadurch den Spalt und somit die Verbindung zwischen dem der Außenseite zugewandten Heißgaspfad mit einem der Innenseite zugewandten Kühlgaspfad. Zur Kühlung dieser Dichtelemente wird vorgeschlagen, das Statorhitzeschild mit mehreren Bohrungen auszustatten, die jeweils einenends an der Innenseite und anderenends an der Stirnseite münden, und zwar so, dass sie von der Nut in Richtung zur Außenseite hin beabstandet münden. Ferner sind die Bohrungen in axialer Richtung voneinander beabstandet angeordnet. Über diese Bohrungen kann Kühlgas vom Kühlgaspfad auf die Heißgasseite in den Spalt zwischen in Umfangsrichtung benachbarten Statorhitzeschilden gelangen und kann dort die Dichtelemente mit Kühlgas beaufschlagen. Insbesondere kann im Bereich des Spalts eine Filmkühlung der Dichtelemente sowie der im Spalt einander gegenüberliegenden Stirnseiten der benachbarten Statorhitzeschilde erzielt werden. Eine gezielte Kühlung dieses Bereichs reduziert die Temperaturen am jeweiligen Statorhitzeschild an den stirnseitigen Enden, was die Hitzebelastung des Statorhitzeschilds reduziert. Durch eine Bemessung der Rippenhöhe sowie des Verhältnisses von Bohrungsdurchmesser zu Bohrungsabstand gemäß dem Kennzeichen des Anspruches 1 lässt sich dann die Standzeit des Hitzeschildes erheblich vergrößern.The present invention is based on the general idea of combining a flapper cooling, a convection cooling and a sealing element cooling with each other in the stator heat shield, thereby providing a plurality of ribs formed on an inner side facing away from a hot gas path of the gas turbine in the installed state of the stator heat shield, which ribs are in the installed state with respect to an axis of rotation a rotor of the gas turbine extend axially and are spaced apart in the circumferential direction, so that can be formed on the inside of several channels. At the same time, these ribs serve to stiffen the respective stator heat shield. On the inside of a baffle plate is also arranged, which rests on the ribs. In this way, heat can be transferred from the stator heat shield to the respective baffle plate by convection within the channels. The baffle plate itself is acted upon in the operation of the gas turbine by a cooling gas, whereby the heat from the baffle plate can be discharged. Furthermore, the respective stator heat shield is provided with a groove, at least on a front side delimiting the stator heat shield in the circumferential direction, into which groove at least one sealing element can be inserted. Two circumferentially adjacent stator heat shields adjoin one another in the region of these end faces, wherein a relatively small gap is formed as a rule. The respective sealing element now engages in the mutually aligned grooves of the two mutually opposite in the gap end faces and thereby closes the gap and thus the connection between the outside facing the hot gas path with a the inside facing cooling gas path. For cooling these sealing elements, it is proposed to provide the stator heat shield with a plurality of bores, which open at one end on the inside and the other end on the end face, in such a way that they open out from the groove in the direction of the outside. Further, the holes are arranged spaced apart in the axial direction. Through these holes, cooling gas can pass from the cooling gas path to the hot gas side in the gap between adjacent stator heat shields in the circumferential direction and can there apply cooling gas to the sealing elements. In particular, film cooling of the sealing elements as well as the opposite end faces of the adjacent stator heat shields in the gap can be achieved in the region of the gap. A targeted cooling of this area reduces the temperatures at the respective stator heat shield at the front ends, which reduces the heat load of the stator heat shield. By a sizing of the rib height as well the ratio of bore diameter to hole spacing according to the characterizing part of claim 1 can then significantly increase the service life of the heat shield.

Besonders vorteilhaft ist eine Ausführungsform, bei der an der jeweiligen Stirnseite eine zur Nut in Richtung zur Außenseite hin beabstandete Ausnehmung ausgebildet ist, die zur Außenseite hin offen ist, die sich in axialer Richtung über die Bohrungen der jeweiligen Stirnseite erstreckt und in der die Bohrungen münden. Durch das Vorsehen einer derartigen Ausnehmung wird erreicht, dass Kühlgas auch dann in den heißgasseitigen Bereich des Spalts eintreten kann, wenn die in Umfangsrichtung benachbarten Statorhitzeschilde mit ihren einander im Spalt gegenüberliegenden Stirnseiten aufeinanderzu verstellt sind, wodurch der Spalt minimiert wird. Eine derartige Spaltreduzierung kann in bestimmten Betriebssituationen der Gasturbine auftreten.Particularly advantageous is an embodiment in which at the respective end face to the groove towards the outside spaced recess is formed, which is open to the outside, which extends in the axial direction over the holes of the respective end face and in which open the holes , By providing such a recess it is achieved that cooling gas can enter into the hot gas side region of the gap even if the stator heat shields adjacent in the circumferential direction are moved towards one another with their end faces opposite each other in the gap, whereby the gap is minimized. Such a gap reduction can occur in certain operating situations of the gas turbine.

Weitere wichtige Merkmale und Vorteile der vorliegenden Erfindung ergeben sich aus den Unteransprüchen, aus den Zeichnungen und aus der zugehörigen Figurenbeschreibung anhand der Zeichnungen.Other important features and advantages of the present invention will become apparent from the dependent claims, from the drawings and from the associated figure description with reference to the drawings.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Ein bevorzugtes Ausführungsbeispiel der Erfindung ist in den Zeichnungen dargestellt und wird in der nachfolgenden Beschreibung näher erläutert, wobei sich gleiche Bezugszeichen auf gleiche oder ähnliche oder funktional gleiche Komponenten beziehen.A preferred embodiment of the invention is illustrated in the drawings and will be explained in more detail in the following description, wherein like reference numerals refer to the same or similar or functionally identical components.

Es zeigen, jeweils schematisch

Fig. 1
einen Axialschnitt durch eine Gasturbine im Bereich eines Statorhitzeschilds,
Fig. 2
eine perspektivische Ansicht eines Statorhitzeschilds,
Fig. 3
einen Querschnitt des Statorhitzeschilds im Bereich einer Stirnseite entsprechend Schnittlinien III in Fig. 2.
It show, each schematically
Fig. 1
an axial section through a gas turbine in the region of a Statorhitzeschilds,
Fig. 2
a perspective view of a stator heat shield,
Fig. 3
a cross-section of the Statorhitzeschilds in the region of a front side according to section lines III in Fig. 2 ,

Wege zur Ausführung der ErfindungWays to carry out the invention

Entsprechend Fig. 1 weist eine Gasturbine 1, von der hier nur ein kleiner Ausschnitt dargestellt ist, einen Stator 2 sowie einen Rotor 3 auf, die ebenfalls nur teilweise dargestellt sind. Vom Stator 2 sind Leitschaufeln 4 teilweise erkennbar sowie ein Abschnitt eines Leitschaufelträgers 5. Am Leitschaufelträger 5 sind zum einen die Leitschaufeln 4 befestigt zum andern sind am Leitschaufelträger 5 auch Statorhitzeschilde 6 angebracht, von denen hier eines erkennbar ist. Vom Rotor 3 ist hier nur eine Laufschaufel 7 erkennbar, die zwischen den beiden Leitschaufeln 4 angeordnet ist. Mit strichpunktierter Linie ist eine Rotationsachse 8 angedeutet, um welche der Rotor 3 im Betrieb der Gasturbine 1 rotiert und welche die axiale Richtung der Gasturbine 1 definiert. Axial bedeutet im vorliegenden Zusammenhang somit parallel zur Rotationsachse 8, während eine radiale Richtung senkrecht auf der Rotationsachse 8 steht und eine Umfangsrichtung entlang einer Kreisbahn um die Rotationsachse 8 orientiert ist. Dementsprechend ist die Laufschaufel 7 axial zwischen den beiden Leitschaufeln 4 angeordnet. Der Statorhitzeschild 6 ist radial der Laufschaufel 7 gegenüber angeordnet und axial zwischen den beiden Leitschaufeln 4 positioniert.Corresponding Fig. 1 has a gas turbine 1, of which only a small section is shown here, a stator 2 and a rotor 3, which are also shown only partially. From the stator 2 guide vanes 4 are partially visible and a portion of a vane carrier 5. On the guide vane 5 are on the one hand the vanes 4 attached to the other stator stator 5 are also attached to the stator vane 5, one of which is recognizable here. From the rotor 3, only one blade 7 can be seen here, which is arranged between the two guide vanes 4. A dot-dash line indicates a rotation axis 8 about which the rotor 3 rotates during operation of the gas turbine 1 and which defines the axial direction of the gas turbine 1. Axial in the present context thus means parallel to the axis of rotation 8, while a radial direction is perpendicular to the axis of rotation 8 and a circumferential direction along a circular path about the axis of rotation 8 is oriented. Accordingly, the blade 7 is arranged axially between the two guide vanes 4. The stator heat shield 6 is disposed radially of the blade 7 and positioned axially between the two vanes 4.

Die einzelnen Statorhitzeschilde 6 bilden Segmente, die in der Umfangsrichtung zueinander benachbart angeordnet sind und einen geschlossenen Kreisring bilden, der eine Laufschaufelreihe umschließt, die durch in Umfangsrichtung zueinander benachbarte Laufschaufeln 7 gebildet ist. Der jeweilige Statorhitzeschild 6 trennt einen durch einen Pfeil angedeuteten Heißgaspfad 9 der Gasturbine 1 von einem ebenfalls durch einen Pfeil angedeuteten Kühlgaspfad 10, der im wesentlichen im Stator 2 verläuft.The individual Statorhitzeschilde 6 form segments which are arranged adjacent to each other in the circumferential direction and form a closed circular ring which encloses a blade row, which is formed by circumferentially adjacent blades 7. The respective stator heat shield 6 separates a hot gas path 9 of the gas turbine 1, indicated by an arrow, from a cooling gas path 10, likewise indicated by an arrow, which runs essentially in the stator 2.

Entsprechend den Fig. 1 und 2 besitzt der jeweilige Statorhitzeschild 6 eine Außenseite 11, die im Einbauzustand dem Heißgaspfad 9 zugewandt ist. Ebenso weist der Statorhitzeschild 6 eine Innenseite 12 auf, die dem Kühlgaspfad 10 zugewandt ist beziehungsweise vom Heißgaspfad 9 und von der Außenseite 11 abgewandt ist. An seiner Innenseite 12 weist der Statorhitzeschild 6 mehrere Rippen 13 auf. Diese Rippen 13 erstrecken sich im Einbauzustand axial und sind vorzugsweise geradlinig ausgestaltet. Des weiteren sind die Rippen 13 in der Umfangsrichtung zueinander beabstandet angeordnet. Ferner ist an der Innenseite 12 zumindest eine Prallplatte 14 angeordnet, die auf den Rippen 13 aufliegt. In dem in Fig. 2 gezeigten Beispiel erstreckt sich die Prallplatte 14 nur über eine Hälfte der Innenseite 12. Eine die andere Hälfte abdeckende zweite Prallplatte 14 ist hier zur besseren Erkennbarkeit der Rippen 13 weggelassen. Ebenso kann eine einzige Prallplatte 14 vorgesehen sein, die sämtliche Rippen 13 abdeckt.According to the Fig. 1 and 2 the respective stator heat shield 6 has an outer side 11, which faces the hot gas path 9 in the installed state. Likewise, the stator heat shield 6 has an inner side 12, which faces the cooling gas path 10 and is remote from the hot gas path 9 and from the outer side 11. On its inner side 12, the stator heat shield 6 has a plurality of ribs 13. These ribs 13 extend axially in the installed state and are preferably designed in a straight line. Furthermore, the ribs 13 are spaced from each other in the circumferential direction. Furthermore, at least one baffle plate 14, which rests on the ribs 13, is arranged on the inner side 12. In the in Fig. 2 As shown, the baffle plate 14 extends only over one half of the inner side 12. A second baffle plate 14 covering the other half is omitted here for better recognition of the ribs 13. Likewise, a single baffle plate 14 may be provided which covers all the ribs 13.

Der jeweilige Statorhitzeschild 6 weist außerdem in der Umfangsrichtung zwei Stirnseiten 15 auf, die jeweils den Statorhitzeschild 6 in Umfangsrichtung begrenzen. In wenigstens eine dieser Stirnseiten 15 ist eine Nut 16 eingearbeitet. Vorzugsweise ist in beide Stirnseiten 15 jeweils eine derartige Nut 16 eingearbeitet. Im Einbauzustand grenzen zwei in Umfangsrichtung zueinander benachbarte Statorhitzeschilde 6 im Bereich dieser Stirnseiten 15 aneinander, wobei sich je zwei solche Stirnseiten 15 in einem in Fig. 3 angedeuteten Axialspalt 17 einander gegenüberliegen. Die Nuten 16 sind dabei so angeordnet, dass sie bei einander im Axialspalt 17 gegenüberliegenden Stirnseiten 15 zueinander fluchtend ausgerichtet sind. Die jeweilige Nut 16 dient zur Aufnahme wenigstens eines Dichtelements 18, das beispielsweise bandförmig oder streifenförmig ausgestaltet ist. Im Bereich des Axialspalts 17 greift ein derartiges Dichtelement 18 in zwei zueinander fluchtende Nuten 16 an zwei im Spalt 17 einander gegenüberliegenden Stirnseiten 15 gleichzeitig ein. Hierdurch kann das jeweilige Dichtelement 18 den Axialspalt 17 abdichten, also die dem Heißgaspfad 9 zugewandte Heißgasseite von der dem Kühlgaspfad 10 zugewandten Kühlgasseite trennen.The respective stator heat shield 6 also has, in the circumferential direction, two end faces 15, each delimiting the stator heat shield 6 in the circumferential direction. In at least one of these end faces 15, a groove 16 is incorporated. Preferably, in each case such a groove 16 is incorporated in both end faces 15. In the installed state, two stator heat shields 6 which are adjacent to one another in the circumferential direction adjoin one another in the region of these end faces 15, each two such end faces 15 in an in Fig. 3 indicated axial gap 17 are opposite to each other. The grooves 16 are arranged so that they are aligned with each other in the axial gap 17 opposite end faces 15 to each other. The respective groove 16 serves to receive at least one sealing element 18, which is configured, for example, band-shaped or strip-shaped. In the region of the axial gap 17, such a sealing element 18 engages in two mutually aligned grooves 16 at two in the gap 17 opposite end faces 15 at the same time. In this way, the respective sealing element 18 can seal off the axial gap 17, ie separate the hot gas path 9 facing the hot gas path from the cooling gas side facing the cooling gas path 10.

Entsprechend den Fig. 2 und 3 ist der Statorhitzeschild 6 außerdem mit mehren Bohrungen 19 ausgestattet. Jede dieser Bohrungen 19 verbindet die Innenseite 12 einer der Stirnseiten 15. Dementsprechend mündet die jeweilige Bohrung 19 einenends an der Innenseite 12 und anderenends an der jeweiligen Stirnseite 15. Die Mündung der jeweiligen Bohrung 19 an der jeweiligen Stirnseite 15 ist beabstandet zur Nut 16 angeordnet, und zwar in Richtung zur Außenseite 11 hin. Auf diese Weise kann durch die Bohrungen 19 Kühlgas von der Kühlgasseite beziehungsweise vom Kühlgaspfad 10 auf die Heißgasseite des Spalts 17 gelangen, der zum Heißgaspfad 9 hin offen ist. Die einzelnen Bohrungen 19 sind gemäß Fig. 2 in axialer Richtung zueinander beabstandet an der jeweiligen Stirnseite 15 des Statorhitzeschilds 6 ausgebildet.According to the FIGS. 2 and 3 the stator heat shield 6 is also equipped with several holes 19. Each of these holes 19 connects the inner side 12 of one of the end faces 15. Accordingly, the respective bore 19 opens at one end to the inner side 12 and the other end to the respective end face 15. The mouth of the respective bore 19 at the respective end face 15 is spaced from the groove 16, in the direction of the outside 11. In this way, through the bores 19, cooling gas can pass from the cooling gas side or from the cooling gas path 10 to the hot gas side of the gap 17, which is open toward the hot gas path 9. The individual holes 19 are according to Fig. 2 spaced apart in the axial direction formed on the respective end face 15 of the stator heat shield 6.

Entsprechend den Fig. 2 und 3 weist der Statorhitzeschild 6 an wenigstens einer der Stirnseiten 15 eine Ausnehmung 20 auf, die zur Außenseite 11 hin offen ist und die sich in axialer Richtung entlang der jeweiligen Seite 15 erstreckt. Beim hier gezeigten Beispiel ist die mit den Bohrungen 19 versehende Stirnseite 15 mit der Ausnehmung 20 ausgestattet. Dementsprechend erstreckt sich die Ausnehmung 20 entlang sämtlicher Bohrungen 19, so dass die Bohrungen 19 jeweils in der Ausnehmung 20 münden. Grundsätzlich kann es ausreichend sein, wenn bei zwei in Umfangsrichtung benachbarten Statorhitzeschilden 6 nur eine der im Spalt 17 einander gegenüberliegenden Stirnseiten 15 mit Bohrungen 19 ausgestattet ist und nur eine dieser Stirnseiten 15 mit einer solchen Ausnehmung 20 ausgestattet ist. Zweckmäßig sind jedoch beide Stirnseiten 15 mit Bohrungen 19 und einer solchen Ausnehmung 20 versehen.According to the FIGS. 2 and 3 the stator heat shield 6 on at least one of the end faces 15, a recess 20 which is open to the outside 11 and which extends in the axial direction along the respective side 15. In the example shown here, the front side 15 provided with the bores 19 is equipped with the recess 20. Accordingly, the extends Recess 20 along all holes 19, so that the holes 19 each open in the recess 20. In principle, it may be sufficient if, in the case of two stator heat shields 6 adjacent in the circumferential direction, only one of the end faces 15 opposite one another in the gap 17 is provided with bores 19 and only one of these end faces 15 is equipped with such a recess 20. Appropriately, however, both end faces 15 are provided with holes 19 and such a recess 20.

Die Ausnehmungen 20 ermöglichen es dem Kühlgas auch dann durch die Bohrungen 19 in ausreichendem Maße auszutreten, wenn der Spalt 17 in Umfangsrichtung aufgrund von Relativbewegungen der benachbarten Statorhitzeschilde 6 vergleichsweise eng wird. Mit Hilfe der Bohrungen 19 kann im Betrieb der Gasturbine 1 eine Kühlung der Dichtelemente 18 bewirkt werden. Insbesondere lässt sich an der Heißgasseite der Dichtelemente 18 ein Kühlgasfilm erzeugen, der eine unmittelbare Heißgasbeaufschlagung der Dichtelemente 18 behindert. Gleichzeitig lassen sich die mit den Stirnseiten 15 versehenen umfangsmäßigen Endbereiche des jeweiligen Statorhitzeschilds 6 hierdurch effektiv kühlen, und zwar einerseits durch die Durchströmung dieser Endbereiche mit Kühlgas und andererseits durch die Ausbildung des Kühlgasfilms an der dem Heißgaspfad 9 ausgesetzten Bereichen der Stirnseite 15 und der Außenseite 11.The recesses 20 also allow the cooling gas to escape sufficiently through the bores 19 if the gap 17 becomes comparatively narrow in the circumferential direction due to relative movements of the adjacent stator heat shields 6. With the help of the holes 19, a cooling of the sealing elements 18 can be effected during operation of the gas turbine 1. In particular, a cooling gas film can be produced on the hot gas side of the sealing elements 18, which obstructs direct hot gas loading of the sealing elements 18. At the same time, the circumferential end regions of the respective stator heat shield 6 provided with the end faces 15 can effectively be cooled thereby, on the one hand by the flow of these end regions with cooling gas and on the other hand by the formation of the cooling gas film on the areas of the front side 15 and the outside 11 exposed to the hot gas path 9 ,

Entsprechend den Fig. 2 und 3 ist an der Innenseite 12 zweckmäßig eine Vertiefung 21 ausgebildet. In dieser Vertiefung 21 sind die Rippen 13 angeordnet, und zwar so, dass innerhalb der Vertiefung 21 ein System von miteinander kommunizierenden Kanälen 22 entsteht. Die wenigstens eine Prallplatte 14 deckt dieses System aus Kanälen 22 zum Kühlgaspfad 10 hin ab. Innerhalb dieser Kanäle 22 kommt es zu einer konvektiven Wärmeübertragung zwischen dem jeweiligen Statorhitzeschild 6 und der jeweiligen Prallplatte 14. Gleichzeitig kann durch das mit den Kanälen 22 gebildete Kanalsystem eine Kühlgasströmung geführt werden. Beispielsweise weist dazu die jeweilige Prallplatte 14 eine Vielzahl von Durchtrittsöffnungen 23 auf, über die Kühlgas vom Kühlgaspfad 10 durch die Prallplatte 14 in die Kanäle 22 gelangen kann. Die zuvor genannten Bohrungen 19 münden nun an der Innenseite 12 in besagter Vertiefung 21 beziehungsweise in einem der Kanäle 22. Somit kann das durch die Durchtrittsöffnungen 23 in das Kanalsystem eintretende Kühlgas über die Bohrungen 19 wieder austreten und durch den Statorhitzeschild 6 hindurch zur Heißgasseite gelangen.According to the FIGS. 2 and 3 is on the inside 12 expedient a recess 21 is formed. In this recess 21, the ribs 13 are arranged, in such a way that within the recess 21, a system of mutually communicating channels 22 is formed. The at least one baffle plate 14 covers this system from channels 22 to the cooling gas path 10 from. Within these channels 22 there is a convective heat transfer between the respective stator heat shield 6 and the respective baffle plate 14. At the same time a cooling gas flow is conducted through the channel system formed with the channels 22. For example, for this purpose, the respective baffle plate 14 has a plurality of passage openings 23 through which cooling gas can pass from the cooling gas path 10 through the baffle plate 14 into the channels 22. The aforementioned holes 19 now open on the inner side 12 in said recess 21 or in one of the channels 22. Thus, the cooling gas entering the channel system through the passage openings 23 can exit via the holes 19 and pass through the stator heat shield 6 to the hot gas side.

An der Innenseite 12 sind hier mehrere Halterungen 24 ausgebildet, mit deren Hilfe die jeweilige Prallplatte 14 am Statorhitzeschild 6 festlegbar ist. Beispielsweise übergreifen hierzu die jeweiligen Halterungen 24 die jeweilige Plattplatte 14.On the inner side 12 a plurality of brackets 24 are formed here, with the aid of which the respective baffle plate 14 can be fixed to the stator heat shield 6. For example, the respective holders 24 overlap the respective flat plate 14 for this purpose.

Die Rippen 13 weisen jeweils eine bestimmte Rippenhöhe 25 auf, mit der sie sich in radialer Richtung erstrecken. Mit dieser Rippenhöhe 25 stehen die Rippen 13 hier von einem Boden der Vertiefung 21 ab. Des weiteren weisen die einzelnen Rippen 13 in der Umfangsrichtung einen Rippenabstand 26 voneinander auf. Die Rippenhöhe 25 und der Rippenabstand 26 sind so aufeinander abgestimmt, dass ein Verhältnis von Rippenhöhe 25 zu Rippenabstand 26 in einem Bereich von 0,328 bis 0,492 liegt.The ribs 13 each have a certain rib height 25, with which they extend in the radial direction. With this fin height 25, the ribs 13 are here from a bottom of the recess 21 from. Furthermore, the individual ribs 13 in the circumferential direction on a rib spacing 26 from each other. The fin height 25 and fin spacing 26 are matched to one another such that a ratio of fin height 25 to fin spacing 26 is in a range of 0.328 to 0.492.

Auch die einzelnen Bohrungen 19 weisen in axialer Richtung einen gewissen Bohrungsabstand 27 zueinander auf. Ferner weist jede einzelne Bohrung einen bestimmten Bohrungsdurchmesser 28 auf. Der jeweilige Bohrungsdurchmesser 28 und den Bohrungsabstand 2 sind so aufeinander abzustimmt, dass sich ein Verhältnis von Bohrungsdurchmesser 28 zu Bohrungsabstand 27 ergibt, das in einem Bereich von 0,0992 bis 0,1488 liegt.Also, the individual holes 19 have in the axial direction a certain bore spacing 27 to each other. Furthermore, each individual bore has a specific bore diameter 28. The respective bore diameter 28 and the hole spacing 2 are matched to each other to give a bore diameter to hole spacing ratio 27 ranging from 0.0992 to 0.1488.

Bezugszeichen listeReference number list

11
Gasturbinegas turbine
22
Statorstator
33
Rotorrotor
44
Leitschaufelvane
55
Leitschaufelträgerguide vane
66
Statorhitzeschildstator heat
77
Laufschaufelblade
88th
Rotationsachseaxis of rotation
99
HeißgaspfadHot gas path
1010
KühlgaspfadCooling gas path
1111
Außenseiteoutside
1212
Innenseiteinside
1313
Ripperib
1414
Prallplatteflapper
1515
Stirnseitefront
1616
Nutgroove
1717
Axialspaltaxial gap
1818
Dichtelementsealing element
1919
Bohrungdrilling
2020
Ausnehmungrecess
2121
Vertiefungdeepening
2222
Kanalchannel
2323
DurchgangsöffnungThrough opening
2424
Halterungbracket
2525
Rippenhöhefin height
2626
Rippenabstandrib spacing
2727
Bohrungsabstandhole spacing
2828
BohrungsdurchmesserBore diameter

Claims (7)

  1. A stator heat shield for a gas turbine (1),
    - with an outside (11) facing a hot-gas path (9) of the gas turbine (1) in the installation state,
    - with an inside (12) facing away from the outside (11),
    - with at least one groove (16) which is formed in an end face (15) delimiting the stator heat shield (6) in the circumferential direction and into which at least one sealing element (18) can be inserted,
    - with a plurality of bores (19) which in each case issue, at one end, on the end face (15) so as to be spaced apart from the groove (16) in the direction of the outside (11) and, at the other end, on the inside (12) and which are spaced apart from one another in the axial direction,
    characterized
    - in that a plurality of ribs (13) are provided which are formed on the inside (12) and which in the installation state extend axially with respect to an axis of rotation (8) of a rotor (3) of the gas turbine (1) and are spaced apart from one another in the circumferential direction,
    - in that at least one baffle plate (14) is provided which is arranged on the inside (12) and which lies on the ribs (13),
    - in that a ratio of rib height (25) to rib spacing (26) lies in a range of 0.41 ± 20%, and
    - in that a ratio of bore diameter (28) to bore spacing (27) lies in the range of 0.124 ± 20%.
  2. The stator heat shield as claimed in claim 1, characterized in that, on the end face (15), a recess (20) is formed which is spaced apart from the groove (16) in the direction of the outside (11), is open toward the outside (11) and extends in the axial direction over the bores (19) of the respective end face (15) and in which the bores (19) issue.
  3. The stator heat shield as claimed in claim 1 or 2, characterized in that, on the inside (12), a depression (21) is formed, in which the ribs (13) are arranged and form a system of intercommunicating channels (22) which is covered by the at least one baffle plate (14).
  4. The stator heat shield as claimed in claim 3, characterized in that the bores (19) issue in the depression (21) or respectively in one of the channels (22) .
  5. The stator heat shield as claimed in one of claims 1 to 4, characterized in that the at least one baffle plate (14) has a plurality of passage orifices (23) .
  6. The stator heat shield as claimed in one of claims 1 to 5, characterized in that at least one holding device (24) for securing the at least one baffle plate (14) to the stator heat shield (6) is formed on the inside (12).
  7. A gas turbine having at least one stator heat shield (6) as claimed in one of claims 1 to 6.
EP08735874A 2007-04-19 2008-04-07 Stator heat shield Active EP2137382B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SI200830743T SI2137382T1 (en) 2007-04-19 2008-04-07 Stator heat shield

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH6452007 2007-04-19
PCT/EP2008/054140 WO2008128876A1 (en) 2007-04-19 2008-04-07 Stator heat shield

Publications (2)

Publication Number Publication Date
EP2137382A1 EP2137382A1 (en) 2009-12-30
EP2137382B1 true EP2137382B1 (en) 2012-05-30

Family

ID=38349602

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08735874A Active EP2137382B1 (en) 2007-04-19 2008-04-07 Stator heat shield

Country Status (6)

Country Link
US (1) US7997856B2 (en)
EP (1) EP2137382B1 (en)
CA (1) CA2684371C (en)
MX (1) MX2009011266A (en)
SI (1) SI2137382T1 (en)
WO (1) WO2008128876A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014150182A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Interlocking rotor assembly with thermal shield

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
MX2009011266A (en) 2007-04-19 2009-11-02 Alstom Technology Ltd Stator heat shield.
IT1395732B1 (en) * 2009-08-03 2012-10-19 Ansaldo Energia Spa EQUIPMENT FOR THE EXPERIMENTAL INVESTIGATION OF GAS TURBINE AXIAL SEALING SYSTEMS
FR2968350B1 (en) * 2010-12-06 2016-01-29 Snecma SECTORIZED TURBINE RING FOR TURBOMACHINE, AND TURBOMACHINE EQUIPPED WITH SUCH A RING
US8876458B2 (en) * 2011-01-25 2014-11-04 United Technologies Corporation Blade outer air seal assembly and support
EP2508713A1 (en) * 2011-04-04 2012-10-10 Siemens Aktiengesellschaft Gas turbine comprising a heat shield and method of operation
US8814507B1 (en) 2013-05-28 2014-08-26 Siemens Energy, Inc. Cooling system for three hook ring segment
ES2581511T3 (en) * 2013-07-15 2016-09-06 Mtu Aero Engines Gmbh Turbomachine, sealing segment and guide blade segment
EP2835500A1 (en) * 2013-08-09 2015-02-11 Siemens Aktiengesellschaft Insert element and gas turbine
WO2015084550A1 (en) * 2013-12-03 2015-06-11 United Technologies Corporation Heat shields for air seals
EP2949873A1 (en) * 2014-05-27 2015-12-02 Siemens Aktiengesellschaft Turbomachine with an ingestion shield and use of the turbomachine
EP3183431B1 (en) 2014-08-22 2018-10-10 Siemens Aktiengesellschaft Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines
EP3118420A1 (en) * 2015-07-15 2017-01-18 Siemens Aktiengesellschaft Coolable wall element with impingement plate
ES2723400T3 (en) 2015-12-07 2019-08-27 MTU Aero Engines AG Housing structure of a turbomachine with thermal protection screen
US10513943B2 (en) 2016-03-16 2019-12-24 United Technologies Corporation Boas enhanced heat transfer surface
GB2559804A (en) * 2017-02-21 2018-08-22 Siemens Ag Heatshield for a gas turbine
US10428689B2 (en) * 2017-05-17 2019-10-01 Rolls-Royce Deutschland Ltd & Co Kg Heat shield for a gas turbine engine
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
US11168702B2 (en) 2017-08-10 2021-11-09 Raytheon Technologies Corporation Rotating airfoil with tip pocket

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3728039A (en) * 1966-11-02 1973-04-17 Gen Electric Fluid cooled porous stator structure
US4573865A (en) * 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
GB2125111B (en) * 1982-03-23 1985-06-05 Rolls Royce Shroud assembly for a gas turbine engine
DE19919654A1 (en) * 1999-04-29 2000-11-02 Abb Alstom Power Ch Ag Heat shield for a gas turbine
DE19963371A1 (en) * 1999-12-28 2001-07-12 Alstom Power Schweiz Ag Baden Chilled heat shield
JP3632003B2 (en) * 2000-03-07 2005-03-23 三菱重工業株式会社 Gas turbine split ring
US6340285B1 (en) * 2000-06-08 2002-01-22 General Electric Company End rail cooling for combined high and low pressure turbine shroud
US6354795B1 (en) * 2000-07-27 2002-03-12 General Electric Company Shroud cooling segment and assembly
JP4698847B2 (en) * 2001-01-19 2011-06-08 三菱重工業株式会社 Gas turbine split ring
GB0117110D0 (en) * 2001-07-13 2001-09-05 Siemens Ag Coolable segment for a turbomachinery and combustion turbine
US7033138B2 (en) * 2002-09-06 2006-04-25 Mitsubishi Heavy Industries, Ltd. Ring segment of gas turbine
US6905302B2 (en) * 2003-09-17 2005-06-14 General Electric Company Network cooled coated wall
US7387488B2 (en) * 2005-08-05 2008-06-17 General Electric Company Cooled turbine shroud
US7377742B2 (en) * 2005-10-14 2008-05-27 General Electric Company Turbine shroud assembly and method for assembling a gas turbine engine
MX2009011266A (en) 2007-04-19 2009-11-02 Alstom Technology Ltd Stator heat shield.

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014150182A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Interlocking rotor assembly with thermal shield
US10309251B2 (en) 2013-03-15 2019-06-04 United Technologies Corporation Interlocking rotor assembly with thermal shield

Also Published As

Publication number Publication date
CA2684371A1 (en) 2008-10-30
WO2008128876A1 (en) 2008-10-30
MX2009011266A (en) 2009-11-02
US20100047062A1 (en) 2010-02-25
US7997856B2 (en) 2011-08-16
EP2137382A1 (en) 2009-12-30
CA2684371C (en) 2014-10-21
SI2137382T1 (en) 2012-10-30

Similar Documents

Publication Publication Date Title
EP2137382B1 (en) Stator heat shield
EP2123860B1 (en) Combined vortex reducer
EP1736635B1 (en) Air transfer system between compressor and turbine of a gas turbine engine
EP2049841B1 (en) Combustion chamber of a combustion plant
EP2167792B1 (en) Vehicle turbocharger with a specific seal
EP1471211B1 (en) Sealing arrangement between stator blades and rotor of a high pressure turbine
DE102011000878B4 (en) Turbine blade with shielded coolant supply channel
DE102005015212A1 (en) Shaft sealing for e.g. rotary screw pump, has seal gap connected with locking gas chamber, and discharge opening connected with gas chamber and suction chamber, where seal gap is arranged between inner and outer sealing rings
DE102018204691A1 (en) Fluid distributor for fluid cooling of a hollow shaft
EP2302174A2 (en) Gas turbine shroud labyrinth seal
DE112017001529B4 (en) turbocharger
EP3239612A1 (en) Gas turbine combustor
EP3194812B1 (en) Guiding means for arrangement in the area of a transmission and/or a clutch of a motor vehicle
EP2886807B1 (en) Cooled flanged connection for a gas turbine engine
EP1621735B1 (en) Gas turbine rotor
DE10225264A1 (en) Air-cooled turbine blade has cover band component at its point and extending vertically to blade longitudinal axis and provided with at least one through bore for cooling air
EP1443182A2 (en) Cooling device
DE112016003287T5 (en) Oil seal construction and turbocharger
DE102011077732A1 (en) Air cooling arrangement for cooling cassette seal used for sealing e.g. ball bearing for shaft, has front toothed ring and air guiding ring axially arranged and rotatable relative to each other, where wings pass into guiding ring at line
DE102017221640A1 (en) Blade, rotor and aircraft engine with variable cooling
EP3875736A1 (en) Sealing device for a turbomachine, carrier ring for a sealing device and turbomachine
DE102017206686A1 (en) Bearing arrangement for mounting a transmission shaft
DE10058857A1 (en) Gas-cooled machine, especially a turbogenerator
DE102010038527B4 (en) Turbo engine
DE102012001603B4 (en) turbocharger

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20091012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 560179

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120615

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502008007320

Country of ref document: DE

Effective date: 20120726

REG Reference to a national code

Ref country code: NL

Ref legal event code: T3

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

Effective date: 20120502

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120830

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120831

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20121001

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120910

26N No opposition filed

Effective date: 20130301

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502008007320

Country of ref document: DE

Effective date: 20130301

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120830

BERE Be: lapsed

Owner name: ALSTOM TECHNOLOGY LTD

Effective date: 20130430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20130407

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130407

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130430

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20131231

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130407

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 560179

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130407

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130407

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SI

Payment date: 20140328

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20120530

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20080407

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130407

REG Reference to a national code

Ref country code: SI

Ref legal event code: KO00

Effective date: 20151215

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20150408

REG Reference to a national code

Ref country code: CH

Ref legal event code: PFA

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD, CH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502008007320

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

Ref country code: DE

Ref legal event code: R081

Ref document number: 502008007320

Country of ref document: DE

Owner name: ANSALDO ENERGIA SWITZERLAND AG, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

REG Reference to a national code

Ref country code: NL

Ref legal event code: HC

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH; CH

Free format text: DETAILS ASSIGNMENT: VERANDERING VAN EIGENAAR(S), VERANDERING VAN NAAM VAN DE EIGENAAR(S); FORMER OWNER NAME: ALSTOM TECHNOLOGY LTD

Effective date: 20161006

REG Reference to a national code

Ref country code: CH

Ref legal event code: PUE

Owner name: ANSALDO ENERGIA SWITZERLAND AG, CH

Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

REG Reference to a national code

Ref country code: NL

Ref legal event code: PD

Owner name: ANSALDO ENERGIA SWITZERLAND AG; CH

Free format text: DETAILS ASSIGNMENT: CHANGE OF OWNER(S), ASSIGNMENT; FORMER OWNER NAME: GENERAL ELECTRIC TECHNOLOGY GMBH

Effective date: 20170301

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 20170419

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 20170419

Year of fee payment: 10

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502008007320

Country of ref document: DE

Owner name: ANSALDO ENERGIA SWITZERLAND AG, CH

Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, BADEN, CH

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: NL

Ref legal event code: MM

Effective date: 20180501

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180501

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180430

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180430

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20230821

Year of fee payment: 16