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EP2173974B1 - Heat shield segment for a stator of a gas turbine - Google Patents

Heat shield segment for a stator of a gas turbine Download PDF

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Publication number
EP2173974B1
EP2173974B1 EP08761301A EP08761301A EP2173974B1 EP 2173974 B1 EP2173974 B1 EP 2173974B1 EP 08761301 A EP08761301 A EP 08761301A EP 08761301 A EP08761301 A EP 08761301A EP 2173974 B1 EP2173974 B1 EP 2173974B1
Authority
EP
European Patent Office
Prior art keywords
heat shield
turbine
shield segment
gas turbine
elevation
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
EP08761301A
Other languages
German (de)
French (fr)
Other versions
EP2173974A1 (en
Inventor
Alexander Khanin
Igor Kurganov
Sergey Vorontsov
Anatoly Shunin
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
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Publication of EP2173974A1 publication Critical patent/EP2173974A1/en
Application granted granted Critical
Publication of EP2173974B1 publication Critical patent/EP2173974B1/en
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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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer

Definitions

  • the invention relates to gas turbines according to the preamble of claim 1.
  • the EP 1 225 305 B1 shows "textbook" on how the heat shield high stress concentrations that can be caused in operation due to high temperature and pressure, can be reduced or safely absorbed by the component.
  • the known heat shield segment is amplified along critical lines.
  • the transverse reinforcing ribs (10a, 10b) extend both in the circumferential direction and in the longitudinal direction.
  • the US 5,380,150 shows as another example in Fig. 3 a high thermal stress heat shield segment with closed fin collar and adjacent reinforcing bumps at the end portions in the circumferential direction of the segments.
  • the ribbed ring extends in the interior and not in the end of the heat shield.
  • constructions are known in which, for reasons of weight, the ribs are dimensioned as short as possible, for example in the form of rib projections or elevations, so that a rib passing through between the end regions of the segment is dispensed with.
  • the ribs are dimensioned as short as possible, for example in the form of rib projections or elevations, so that a rib passing through between the end regions of the segment is dispensed with.
  • the heat shield segment of the gas turbine has a curved section in at least one region of the profile in the longitudinal direction of the gas turbine, wherein a radially outer surface of the heat shield segment in the region of the curved section in a first end region in the circumferential direction of the turbine with a is provided in the circumferential direction of the turbine extending increase.
  • the stresses in the heat shield segment are reduced in the region of the curved portion. This leads to a considerable extension of the service life.
  • the length of the increase in the circumferential direction is less than a quarter of the total length of the heat shield segment in the circumferential direction.
  • the heat shield segment is sufficiently strengthened without having to provide a fin extending between the end ribs, which avoids additional metal consumption, so that the weight of the heat shield can be kept low.
  • FIG. 4 is a heat shield segment 1 according to the prior art known from preliminary experiments.
  • a heat shield may include a number of such heat shield segments 1 that define an outer boundary of a hot gas flow along the turbine blades 2 (see, eg, FIG FIG. 3 ) form.
  • the profile of the heat shield segment 1 adapts to the basically conical guidance of a turbine rotor (not shown), and has a stepped cross section, as shown in FIG FIG. 3 can be seen.
  • Halterseiementen 3 On the radially outer side of the heat shield segment 1 are Halterseiementen 3, 4 are arranged, which serve for positioning of the heat shield segment 1 in the radial direction and in the circumferential direction.
  • FIG. 3 is a cross section through a turbine section with a heat shield segment according to said prior art shown.
  • the turbine blades 2 of the turbine rotor have a circumferential, on the Radial outside of the turbine rotor arranged and cylindrically extending shroud 5 on.
  • the shroud 5 has on its radial outer side two radially outwardly extending ribs 6.
  • the two ribs 6 in the radial direction opposite to the heat shield segment 1 each honeycomb structures 7 are fixedly connected, which serve to seal the distance between the rib tip 6 and the heat shield segment 1.
  • the inner mold 8 of the heat shield extends in a first section 9 substantially parallel to the longitudinal axis of the turbine.
  • the inner mold 8 of the heat shield segment 1 in a second portion 11 extend obliquely to the longitudinal axis of the turbine, wherein the flow direction of the hot gas through the turbine is indicated by arrow 10. Since the heat shield segment 1 is exposed to the high temperature of the hot gas flow and the high pressure loss in the flow direction, it can in the curved portion 12 of the heat shield segment 1 between the first portion 9 and the second portion 11 and in particular in the end portions 13 of the heat shield segment 1 in the circumferential direction of the turbine lead to high voltages that can significantly limit the life of the heat shield segment 1.
  • FIG. 1 a heat shield segment 1 according to a preferred embodiment of the invention is shown. Identical components are provided with the same reference numerals.
  • a radially outer side 15 of the heat shield segment 1 is provided in the region of the curved section 12 and in at least one end region 13 of the heat shield segment 1 in the circumferential direction with an elevation 14 or shoulder extending in the circumferential direction of the turbine. This increase or decrease reduces the stress concentration in this area of the heat shield segment 1.
  • An elevation or projection may be provided at each end 13 of the heat shield segment 1, respectively.
  • the elevation or neck in the longitudinal direction of the turbine is located at a location where the first portion 9 and the second portion 11 meet.
  • the length of the elevation 14 in the circumferential direction is less than one quarter of the total length of the heat shield segment 1 in the circumferential direction.
  • the additional metal consumption can be kept low because no running between the ends of the heat shield segment 1 rib must be provided. Thereby, the weight of the heat shield segment 1 can be kept low.
  • the radially outer surface 15 of the heat shield segment 1 is provided with two ribs 16 which extend at least partially at the ends of the heat shield segment 1 in the circumferential direction of the turbine in the longitudinal direction of the turbine.
  • the elevation 14 or projection protrudes from the respective rib 16 in the circumferential direction.
  • the profile of the heat shield segment 1 in the circumferential direction of the turbine and in the region of the elevation 14 have a two-stage shape, as shown in FIG. 2 is apparent.
  • the length of the increase in the circumferential direction of the turbine to the width of the increase in the longitudinal direction of the turbine in the ratio of 1: 2 to 3: 1 behaves.
  • the heat shield segment 1 has a curved section in at least two locations of the heat shield segment profile in the longitudinal direction of the turbine, that is to say that the heat shield cross section is formed essentially in two stages.
  • the radial outside of the heat shield segment is in each case in the regions of the curved sections and in a first and / or a second end region each provided in the circumferential direction of the heat shield segment with a 14 extending in the circumferential direction of the turbine elevation.
  • a heat shield may be equipped with a number of heat shield segments 1 according to the invention which have an outer boundary of a hot gas flow along the turbine blades 2 (cf. FIG. 3 ) form.
  • the heat shield segments 1 are provided with a running in the longitudinal direction of the turbine groove 17 respectively in the end sides, as shown in FIG. 2 is apparent.
  • the grooves 17 of two adjacent heat shield segments 1 serve to receive a seal plate (not shown) which prevents the penetration of hot combustion gases into the cooling air filled cavity 18 between the heat shield and the turbine housing 19.

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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 includes a turbine housing; a rotatable turbine rotor with turbine blades; and at least one heat shield segment for a stator. The heat shield segment is disposed radially between the rotor and the housing and attached to the housing and has a profile with a curved section in at least one region in an axial direction of the gas turbine and a radial outer surface. The heat shield segment includes a rib, a first boss, and a second boss disposed on the radial outer surface.

Description

Technisches GebietTechnical area

Die Erfindung betrifft Gasturbinen gemäß dem Oberbegriff des Anspruchs 1.The invention relates to gas turbines according to the preamble of claim 1.

Stand der TechnikState of the art

Es ist allgemein bekannt und üblich, in Gasturbinen segmentierte Hitzeschilde vorzusehen, um die thermische Beanspruchung des Gasturbinengehäuses zu begrenzen.It is well known and common to provide segmented heat shields in gas turbines to limit the thermal stress on the gas turbine casing.

Die EP 1 225 305 B1 zeigt "lehrbuchmäßig" auf, wie am Hitzeschild hohe Spannungskonzentrationen, die im Betrieb aufgrund hoher Temperatur- und Druckbeaufschlagung verursacht werden können, vermindert bzw. sicher vom Bauteil aufgenommen werden können.The EP 1 225 305 B1 shows "textbook" on how the heat shield high stress concentrations that can be caused in operation due to high temperature and pressure, can be reduced or safely absorbed by the component.

Mittels einer verstärkten Leichtbaukonstruktion mit spezieller Rippengestaltung am Außenrand sowie in den Querrichtungen, wie sie zum Beispiel in Fig. 2 der EP 1 225 305 B1 dargestellt sind, wird das bekannte Hitzeschildsegment entlang kritischer Linien verstärkt. Dabei erstrecken sich die quer verlaufenden Verstärkungsrippen (10a, 10b) sowohl in Umfangs- als auch in Längsrichtung.By means of a reinforced lightweight construction with special rib design at the outer edge as well as in the transverse directions, as for example in Fig. 2 of the EP 1 225 305 B1 are shown, the known heat shield segment is amplified along critical lines. In this case, the transverse reinforcing ribs (10a, 10b) extend both in the circumferential direction and in the longitudinal direction.

Die US 5 380 150 zeigt als weiteres Beispiel in Fig. 3 ein unter hohen thermischen Spannungen stehendes Hitzeschildsegment mit geschlossenem Rippenkranz und daran angrenzenden Verstärkungshöckern an den Endbereichen in Umfangsrichtung der Segmente. Hier erstreckt sich allerdings der Rippenkranz im Innenbereich und nicht im Endbereich des Hitzeschildes.The US 5,380,150 shows as another example in Fig. 3 a high thermal stress heat shield segment with closed fin collar and adjacent reinforcing bumps at the end portions in the circumferential direction of the segments. Here, however, the ribbed ring extends in the interior and not in the end of the heat shield.

Im Übrigen sind Konstruktionen bekannt, bei denen aus Gewichtsgründen die Rippen möglichst kurz bemessen werden, z.B. in Form von Rippenansätzen oder Erhöhungen, so dass eine zwischen den Endbereichen des Segmentes durchlaufende Rippe erübrigt wird. Jedoch ist aus dem Stand der Technik keinerlei Hinweis darauf zu entnehmen, dass speziell in einem gekrümmten Längsabschnitt des Hitzeschildsegmentes, wie es beispielsweise aus der DE 10 2005 013 798 A1 bekannt ist, in Umfangsrichtung aus den Endrippen herausragend jeweils eine Erhöhung mit spezieller Form vorgesehen werden sollte, um eine lokal gezielt eingesetzte Verstärkung gewichts- und spannungsoptimiert zu erreichen.Incidentally, constructions are known in which, for reasons of weight, the ribs are dimensioned as short as possible, for example in the form of rib projections or elevations, so that a rib passing through between the end regions of the segment is dispensed with. However, it can not be inferred from the prior art that, especially in a curved longitudinal section of the heat shield segment, as is known, for example, from US Pat DE 10 2005 013 798 A1 It is known, in the circumferential direction of the end ribs outstanding each an increase should be provided with a special shape in order to achieve a locally targeted reinforcement used weight and optimized voltage.

Darstellung der ErfindungPresentation of the invention

Hier setzt die Erfindung an. Dabei liegt der vorliegenden Erfindung die Aufgabe zugrunde, eine Gasturbine mit Hitzeschildsegmenten für den Stator der Gasturbine mit verbesserter Konstruktion bereit zu stellen, wobei die Spannungen im gekrümmten Bereich des Hitzeschildsegmentes deutlich vermindert werden sollen.This is where the invention starts. It is the object of the present invention to provide a gas turbine with heat shield segments for the stator of the gas turbine with improved design, wherein the stresses in the curved portion of the heat shield segment should be significantly reduced.

Erfindungsgemäß wird dies durch die kennzeichnenden Merkmale des Anspruches 1 gelöst.This is achieved by the characterizing features of claim 1 according to the invention.

Bei der Erfindung ist besonders bemerkenswert, dass das Hitzeschildsegment der Gasturbine in mindestens einem Bereich des Profils in Längsrichtung der Gasturbine einen gekrümmten Abschnitt aufweist, wobei eine radial äußere Fläche des Hitzeschildsegmentes im Bereich des gekrümmten Abschnitts in einem ersten Endbereich in Umfangsrichtung der Turbine mit einer sich in Umfangsrichtung der Turbine erstreckenden Erhöhung versehen ist. Dadurch werden die Spannungen im Hitzeschildsegment im Bereich des gekrümmten Abschnittes vermindert. Dies führt zu einer erheblichen Verlängerung der Lebensdauer.It is particularly noteworthy in the invention that the heat shield segment of the gas turbine has a curved section in at least one region of the profile in the longitudinal direction of the gas turbine, wherein a radially outer surface of the heat shield segment in the region of the curved section in a first end region in the circumferential direction of the turbine with a is provided in the circumferential direction of the turbine extending increase. As a result, the stresses in the heat shield segment are reduced in the region of the curved portion. This leads to a considerable extension of the service life.

In vorteilhafter Ausgestaltung der Erfindung beträgt die Länge der Erhöhung in Umfangsrichtung weniger als ein Viertel der Gesamtlänge des Hitzeschildsegmentes in Umfangsrichtung. Gleichwohl wird das Hitzeschildsegment genügend verstärkt, ohne dass eine zwischen den Endbereichen verlaufende Rippe vorgesehen werden muss, was zusätzlichen Metallverbrauch vermeidet, so dass das Gewicht des Hitzeschildes gering gehalten werden kann.In an advantageous embodiment of the invention, the length of the increase in the circumferential direction is less than a quarter of the total length of the heat shield segment in the circumferential direction. However, the heat shield segment is sufficiently strengthened without having to provide a fin extending between the end ribs, which avoids additional metal consumption, so that the weight of the heat shield can be kept low.

Weitere Vorteile und Ausgestaltungen der Erfindung ergeben sich aus der nachfolgenden Beschreibung und den beiliegenden Zeichnungen.Further advantages and embodiments of the invention will become apparent from the following description and the accompanying drawings.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Die Erfindung wird anhand eines Ausführungsbeispiels in den Zeichnungen schematisch dargestellt und im Folgenden unter Bezugnahme auf die Zeichnungen ausführlich beschrieben.The invention will be described schematically with reference to an embodiment in the drawings and described in detail below with reference to the drawings.

Es zeigen, jeweils schematisch,

Figur 1
in perspektivischer Ansicht ein Hitzeschildsegment gemäß einer Ausführungsform der Erfindung,
Figur 2
einen Schnitt durch das Hitzeschildsegment in Figur 1 im Bereich der Erhöhung entlang der Linie A-A,
Figur 3
einen Querschnitt durch einen Turbinenabschnitt mit einem Hitzeschildsegment gemäß einem Vorversuch der Patentinhaberin, bzw. -anmelderin,
Figur 4
in perspektivischer Ansicht ein Hitzeschildsegment gemäß dem Vorversuch der Patentinhaberin, bzw. -anmelderin.
Show, in each case schematically,
FIG. 1
a perspective view of a heat shield segment according to an embodiment of the invention,
FIG. 2
a section through the heat shield segment in FIG. 1 in the area of the increase along the line AA,
FIG. 3
a cross section through a turbine section with a heat shield segment according to a preliminary test of the patent owner,
FIG. 4
in perspective view of a heat shield segment according to the preliminary test of the patent owner, or -anmelderin.

Wiege zur Ausführung der ErfindungCradle for carrying out the invention

In Figur 4 ist ein Hitzeschildsegment 1 nach dem aus Vorversuchen bekannten Stand der Technik dargestellt. Ein Hitzeschild kann eine Anzahl von solchen Hitzeschildsegmenten 1 enthalten, die eine äußere Begrenzung einer heißen Gasströmung entlang den Turbinenlaufschaufeln 2 (vgl. z.B. Figur 3) bilden. Das Profil des Hitzeschildsegments 1 passt sich der grundsätzlich konischen Führung eines Turbinenrotors (nicht gezeigt) an, und weist einen gestuften Querschnitt auf, wie aus der Figur 3 zu erkennen ist. An der radial Außenseite des Hitzeschildsegments 1 sind Halterungseiementen 3, 4 angeordnet, die zur Positionierung des Hitzeschildsegments 1 in radialer Richtung und in Umfangsrichtung dienen.In FIG. 4 is a heat shield segment 1 according to the prior art known from preliminary experiments. A heat shield may include a number of such heat shield segments 1 that define an outer boundary of a hot gas flow along the turbine blades 2 (see, eg, FIG FIG. 3 ) form. The profile of the heat shield segment 1 adapts to the basically conical guidance of a turbine rotor (not shown), and has a stepped cross section, as shown in FIG FIG. 3 can be seen. On the radially outer side of the heat shield segment 1 are Halterseiementen 3, 4 are arranged, which serve for positioning of the heat shield segment 1 in the radial direction and in the circumferential direction.

In Figur 3 ist ein Querschnitt durch einen Turbinenabschnitt mit einem Hitzeschildsegment nach dem besagten Stand der Technik dargestellt. Die Turbinenschaufeln 2 des Turbinenrotors weisen ein umlaufendes, auf der radialen Außenseite des Turbinenrotors angeordnetes und zylindrisch verlaufendes Deckband 5 auf. Das Deckband 5 hat auf seiner radialen Außenseite zwei sich radial auswärts erstreckende Rippen 6. Den beiden Rippen 6 in radialer Richtung gegenüberliegend sind am Hitzeschildsegment 1 jeweils Honigwabenstrukturen 7 ortsfest verbunden, die der Abdichtung des Abstandes zwischen der Rippenspitze 6 und dem Hitzeschildsegment 1 dienen. Die Innenform 8 des Hitzeschilds verläuft in einem ersten Abschnitt 9 im Wesentlichen parallel zur Längsachse der Turbine. Stromaufwärts des ersten flachen Abschnitts 9 kann die Innenform 8 des Hitzeschildsegments 1 in einem zweiten Abschnitt 11 schräg zur Längsachse der Turbine verlaufen, wobei die Strömungsrichtung des Heißgases durch die Turbine mit Pfeil 10 bezeichnet ist. Da das Hitzeschildsegment 1 der hohen Temperatur des Heißgasstroms und dem hohen Druckverlust in Strömungsrichtung ausgesetzt ist, kann es im gekrümmten Bereich 12 des Hitzeschildsegments 1 zwischen dem ersten Abschnitt 9 und dem zweiten Abschnitt 11 und insbesondere in den Endbereichen 13 des Hitzeschildsegments 1 in Umfangsrichtung der Turbine zu hohen Spannungen führen, die die Lebensdauer des Hitzeschildsegments 1 beträchtlich beschränken können.In FIG. 3 is a cross section through a turbine section with a heat shield segment according to said prior art shown. The turbine blades 2 of the turbine rotor have a circumferential, on the Radial outside of the turbine rotor arranged and cylindrically extending shroud 5 on. The shroud 5 has on its radial outer side two radially outwardly extending ribs 6. The two ribs 6 in the radial direction opposite to the heat shield segment 1 each honeycomb structures 7 are fixedly connected, which serve to seal the distance between the rib tip 6 and the heat shield segment 1. The inner mold 8 of the heat shield extends in a first section 9 substantially parallel to the longitudinal axis of the turbine. Upstream of the first flat portion 9, the inner mold 8 of the heat shield segment 1 in a second portion 11 extend obliquely to the longitudinal axis of the turbine, wherein the flow direction of the hot gas through the turbine is indicated by arrow 10. Since the heat shield segment 1 is exposed to the high temperature of the hot gas flow and the high pressure loss in the flow direction, it can in the curved portion 12 of the heat shield segment 1 between the first portion 9 and the second portion 11 and in particular in the end portions 13 of the heat shield segment 1 in the circumferential direction of the turbine lead to high voltages that can significantly limit the life of the heat shield segment 1.

In Figur 1 ist ein Hitzeschildsegment 1 gemäß einer bevorzugten Ausführungsform der Erfindung dargestellt. Gleiche Bauteile werden mit gleichen Bezugszeichen versehen. Erfindungsgemäß ist eine radial Außenseite 15 des Hitzeschildsegments 1 im Bereich des gekrümmten Abschnitts 12 und in mindestens einem Endbereich 13 des Hitzeschildsegments 1 in Umfangsrichtung mit einer sich in Umfangsrichtung der Turbine erstreckenden Erhöhung 14 oder Ansatz versehen. Diese Erhöhung 14 oder Ansatz reduziert die Spannungskonzentration in diesem Bereich des Hitzeschildsegments 1. Eine Erhöhung oder Ansatz kann jeweils am jeweiligen Ende 13 des Hitzeschildsegments 1 vorgesehen werden.In FIG. 1 a heat shield segment 1 according to a preferred embodiment of the invention is shown. Identical components are provided with the same reference numerals. According to the invention, a radially outer side 15 of the heat shield segment 1 is provided in the region of the curved section 12 and in at least one end region 13 of the heat shield segment 1 in the circumferential direction with an elevation 14 or shoulder extending in the circumferential direction of the turbine. This increase or decrease reduces the stress concentration in this area of the heat shield segment 1. An elevation or projection may be provided at each end 13 of the heat shield segment 1, respectively.

Vorzugsweise ist die Erhöhung oder der Ansatz in Längsrichtung der Turbine an einer Stelle, an der der erste Abschnitt 9 und der zweite Abschnitt 11 sich treffen, angeordnet.Preferably, the elevation or neck in the longitudinal direction of the turbine is located at a location where the first portion 9 and the second portion 11 meet.

Vorzugsweise beträgt die Länge der Erhöhung 14 in Umfangsrichtung weniger als ein viertel der Gesamtlänge des Hitzeschildsegments 1 in Umfangsrichtung. Hierbei kann der zusätzliche Metallverbrauch gering gehalten werden, weil keine zwischen den Enden des Hitzeschildsegments 1 verlaufende Rippe vorgesehen werden muss. Dadurch kann das Gewicht des Hitzeschildsegments 1 gering gehalten werden.Preferably, the length of the elevation 14 in the circumferential direction is less than one quarter of the total length of the heat shield segment 1 in the circumferential direction. In this case, the additional metal consumption can be kept low because no running between the ends of the heat shield segment 1 rib must be provided. Thereby, the weight of the heat shield segment 1 can be kept low.

In der bevorzugten Ausführungsform in Figur 1 ist vorzugsweise die radial äußere Fläche 15 des Hitzeschildsegments 1 mit zwei Rippen 16 versehen, die sich jeweils an den Enden des Hitzeschildsegments 1 in Umfangsrichtung der Turbine in Längsrichtung der Turbine zumindest teilweise erstrecken. Die Erhöhung 14 oder Ansatz ragt aus der jeweiligen Rippe 16 in Umfangsrichtung heraus. Hierbei kann das Profil des Hitzeschildsegments 1 in Umfangsrichtung der Turbine und im Bereich der Erhöhung 14 eine zweistufige Form aufweisen, wie aus der Figur 2 ersichtlich ist. Vorzugsweise verhält sich die Länge der Erhöhung in Umfangsrichtung der Turbine zur Breite der Erhöhung in Längsrichtung der Turbine im Verhältnis 1:2 bis 3:1.In the preferred embodiment in FIG FIG. 1 Preferably, the radially outer surface 15 of the heat shield segment 1 is provided with two ribs 16 which extend at least partially at the ends of the heat shield segment 1 in the circumferential direction of the turbine in the longitudinal direction of the turbine. The elevation 14 or projection protrudes from the respective rib 16 in the circumferential direction. Here, the profile of the heat shield segment 1 in the circumferential direction of the turbine and in the region of the elevation 14 have a two-stage shape, as shown in FIG. 2 is apparent. Preferably, the length of the increase in the circumferential direction of the turbine to the width of the increase in the longitudinal direction of the turbine in the ratio of 1: 2 to 3: 1 behaves.

In einer weitern Ausführungsform (nicht gezeigt) weist das Hitzeschildsegment 1 an mindestens zwei Stellen des Hitzeschildsegmentprofils in Längsrichtung der Turbine einen gekrümmten Abschnitt auf, dass heißt, dass der Hitzeschildquerschnitt im Wesentlichen zweistufig ausgebildet ist. In diesem Fall ist die radiale Außenseite des Hitzeschildsegments jeweils in den Bereichen der gekrümmten Abschnitte und in einem ersten und/oder einem zweiten Endbereich in Umfangsrichtung des Hitzeschildsegments jeweils mit einer sich in Umfangsrichtung der Turbine erstreckenden Erhöhung 14 versehen.In a further embodiment (not shown), the heat shield segment 1 has a curved section in at least two locations of the heat shield segment profile in the longitudinal direction of the turbine, that is to say that the heat shield cross section is formed essentially in two stages. In this case, the radial outside of the heat shield segment is in each case in the regions of the curved sections and in a first and / or a second end region each provided in the circumferential direction of the heat shield segment with a 14 extending in the circumferential direction of the turbine elevation.

Ein Hitzeschild kann mit einer Anzahl von erfindungsgemäßen Hitzeschildsegmenten 1 ausgestattet sein, die eine äußere Begrenzung einer heißen Gasströmung entlang den Turbinenlaufschaufeln 2 (vgl. z.B. Figur 3) bilden. Die Hitzeschildsegmente 1 sind mit einer in Längsrichtung der Turbine verlaufenden Nut 17 jeweils in den Endseiten versehen, wie aus der Figur 2 ersichtlich ist. Die Nuten 17 von zwei benachbarten Hitzeschildsegmenten 1 dienen dazu, eine Dichtungsplatte (nicht gezeigt) aufzunehmen, die das Eindringen von heißen Verbrennungsgasen in den mit Kühlluft gefüllten Hohlraum 18 zwischen dem Hitzeschild und dem Turbinengehäuse 19 verhindert.A heat shield may be equipped with a number of heat shield segments 1 according to the invention which have an outer boundary of a hot gas flow along the turbine blades 2 (cf. FIG. 3 ) form. The heat shield segments 1 are provided with a running in the longitudinal direction of the turbine groove 17 respectively in the end sides, as shown in FIG. 2 is apparent. The grooves 17 of two adjacent heat shield segments 1 serve to receive a seal plate (not shown) which prevents the penetration of hot combustion gases into the cooling air filled cavity 18 between the heat shield and the turbine housing 19.

Die vorhergehende Beschreibung der Ausführungsbeispiele gemäß der vorliegenden Erfindung dient nur zu illustrativen Zwecken und nicht zum Zwecke der Beschränkung der Erfindung.The foregoing description of the embodiments according to the present invention is for illustrative purposes only, and not for the purpose of limiting the invention.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
HitzeschildsegmentHeat shield segment
22
TurbinenlaufschaufelTurbine blade
33
Halterungselementsupporting member
44
Halterungselementsupporting member
55
Deckbandshroud
66
Ripperib
77
HonigwabenstrukturHoneycomb structure
88th
Innenforminterior shape
99
erster Abschnittfirst section
1010
Strömungsrichtungflow direction
1111
zweiter Abschnittsecond part
1212
gekrümmter Bereichcurved area
1313
Endbereichend
1414
Erhöhungincrease
1515
radiale Außenseiteradial outside
1616
Ripperib
1717
Nutgroove
1818
Hohlraumcavity
1919
Turbinengehäuseturbine housing

Claims (7)

  1. Gas turbine, which has a rotatably mounted turbine rotor with turbine blades (2) and at least one stator-side heat shield segment (1), the respective heat shield segment (1) being arranged radially between the turbine rotor and a turbine casing (19) and fastened to the turbine casing (19) and having a profile which has a curved portion (12) in at least one region of the profile in the longitudinal direction of the turbine, characterized
    - in that, in the region of the curved portion (12) and in a first end region in the circumferential direction of the gas turbine, a radial outer side (15) of the heat shield segment (1) is provided with at least one elevation (14) extending in the circumferential direction of the gas turbine,
    - in that the radially outer face (15) of the heat shield segment (1) is provided with a rib (16), which, located at the end of the heat shield segment (1) in the circumferential direction of the gas turbine, at least partially extends in the longitudinal direction of the gas turbine, the elevation (14) protruding from the rib (16) in the circumferential direction,
    - in that, in the region of the curved portion (12) and in a second end region that is opposite from the first end region, the radially outer face (15) of the heat shield segment (1) is provided with a second elevation (14) extending in the circumferential direction of the turbine,
    - in that the profile of the heat shield segment (1) has in the region of the respective elevation (14) in the circumferential direction of the gas turbine a two-staged shape, a first stage leading from the radially outer face (15) of the heat shield segment (1) to the respective elevation (14), while a second stage leads from the respective elevation (14) to the rib (16).
  2. Gas turbine according to Claim 1, characterized in that the length of the elevation (14) in the circumferential direction of the gas turbine is less than one quarter of the total length of the heat shield segment (1) in the circumferential direction.
  3. Gas turbine according to one of the preceding claims, characterized in that the length of the elevation (14) in the circumferential direction of the turbine is in a ratio of 1:2 to 3:1 to the width of the elevation (14) in the longitudinal direction of the turbine.
  4. Gas turbine according to one of the preceding claims, characterized in that the heat shield segment (1) has at at least two points of the heat shield segment profile in the longitudinal direction of the turbine a curved portion (12), the radially outer face of the heat shield segment (1) being respectively provided in the region of the curved portions (12) and in a first and/or second end region in the circumferential direction of the heat shield segment (1) in each case with an elevation (14) extending in the circumferential direction of the turbine.
  5. Gas turbine according to one of the preceding claims, characterized in that the inner shape of the heat shield segment (1) has a first portion (9), running substantially parallel to the longitudinal direction of the turbine, and a second portion (11), adjacent to the first portion (9) in the upstream direction and running obliquely in relation to the longitudinal direction, the elevation (14) in the longitudinal direction of the turbine being arranged at a point at which the first and second portions (9, 11) meet.
  6. Gas turbine according to one of the preceding claims, characterized in that a groove (17) running in the longitudinal direction of the turbine is provided in a radially extending outer side of the heat shield segment (1), at least in the region of the elevation (14).
  7. Gas turbine according to one of the preceding claims, characterized in that a number of heat shield segments (1) form a heat shield, which forms an outer delimitation of a hot gas flow along the turbine blades (2).
EP08761301A 2007-06-28 2008-06-23 Heat shield segment for a stator of a gas turbine Active EP2173974B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH10432007 2007-06-28
PCT/EP2008/057946 WO2009000801A1 (en) 2007-06-28 2008-06-23 Heat shield segment for a stator of a gas turbine

Publications (2)

Publication Number Publication Date
EP2173974A1 EP2173974A1 (en) 2010-04-14
EP2173974B1 true EP2173974B1 (en) 2011-10-26

Family

ID=38508786

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08761301A Active EP2173974B1 (en) 2007-06-28 2008-06-23 Heat shield segment for a stator of a gas turbine

Country Status (7)

Country Link
US (1) US8182210B2 (en)
EP (1) EP2173974B1 (en)
AT (1) ATE530736T1 (en)
CA (1) CA2690705C (en)
SI (1) SI2173974T1 (en)
TW (1) TWI475152B (en)
WO (1) WO2009000801A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8926269B2 (en) * 2011-09-06 2015-01-06 General Electric Company Stepped, conical honeycomb seal carrier
WO2014105512A1 (en) * 2012-12-29 2014-07-03 United Technologies Corporation Mechanical linkage for segmented heat shield
US10233844B2 (en) 2015-05-11 2019-03-19 General Electric Company System for thermally shielding a portion of a gas turbine shroud assembly
DE102016213810A1 (en) 2016-07-27 2018-02-01 MTU Aero Engines AG Cladding element for a turbine intermediate housing
US10358922B2 (en) * 2016-11-10 2019-07-23 Rolls-Royce Corporation Turbine wheel with circumferentially-installed inter-blade heat shields

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3365173A (en) * 1966-02-28 1968-01-23 Gen Electric Stator structure
US4987736A (en) * 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
US5380150A (en) * 1993-11-08 1995-01-10 United Technologies Corporation Turbine shroud segment
DE19915049A1 (en) * 1999-04-01 2000-10-05 Abb Alstom Power Ch Ag Heat shield for a gas turbine
US6290459B1 (en) * 1999-11-01 2001-09-18 General Electric Company Stationary flowpath components for gas turbine engines
US6502622B2 (en) * 2001-05-24 2003-01-07 General Electric Company Casting having an enhanced heat transfer, surface, and mold and pattern for forming same
JP3632003B2 (en) * 2000-03-07 2005-03-23 三菱重工業株式会社 Gas turbine split ring
JP4698847B2 (en) * 2001-01-19 2011-06-08 三菱重工業株式会社 Gas turbine split ring
US6779597B2 (en) * 2002-01-16 2004-08-24 General Electric Company Multiple impingement cooled structure
DE102005013798A1 (en) * 2005-03-24 2006-09-28 Alstom Technology Ltd. Heat release segment for sealing a flow channel of a flow rotary machine
US8528339B2 (en) * 2007-04-05 2013-09-10 Siemens Energy, Inc. Stacked laminate gas turbine component

Also Published As

Publication number Publication date
US20100150712A1 (en) 2010-06-17
CA2690705A1 (en) 2008-12-31
SI2173974T1 (en) 2012-03-30
CA2690705C (en) 2015-08-04
EP2173974A1 (en) 2010-04-14
US8182210B2 (en) 2012-05-22
WO2009000801A1 (en) 2008-12-31
TWI475152B (en) 2015-03-01
ATE530736T1 (en) 2011-11-15
TW200925389A (en) 2009-06-16

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