EP2173974A1 - Heat shield segment for a stator of a gas turbine - Google Patents

Heat shield segment for a stator of a gas turbine

Info

Publication number
EP2173974A1
EP2173974A1 EP08761301A EP08761301A EP2173974A1 EP 2173974 A1 EP2173974 A1 EP 2173974A1 EP 08761301 A EP08761301 A EP 08761301A EP 08761301 A EP08761301 A EP 08761301A EP 2173974 A1 EP2173974 A1 EP 2173974A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
turbine
shield segment
circumferential direction
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.)
Granted
Application number
EP08761301A
Other languages
German (de)
French (fr)
Other versions
EP2173974B1 (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
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2173974A1 publication Critical patent/EP2173974A1/en
Application granted granted Critical
Publication of EP2173974B1 publication Critical patent/EP2173974B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 a heat shield segment for a stator of a gas turbine, according to the preamble of claim 1.
  • the turbine rotor of a gas turbine is usually surrounded in the radial direction by a housing that is usually referred to in this area as a heat shield.
  • the heat shield may include a number of heat shield segments, wherein the heat shield forms an outer boundary of a hot gas flow along the turbine blades.
  • the heat shield prevents hot combustion gases from entering the cooling air filled cavity between the heat shield and a radially outer housing.
  • the heat shield may have different shapes and the inner shape of the heat shield defines the flow area of the hot air flow in the turbine.
  • the turbine blades of the turbine rotor usually have a circumferential, arranged on the radial outer side of the turbine rotor, depending on the flow conditions cylindrically or conically extending shroud.
  • the shroud usually has two on its radial outside radially outwardly extending sealing ribs.
  • the two sealing ribs in the radial direction opposite to the heat shield each honeycomb structures are fixedly connected, which serve to seal the distance between the sealing ribs and the heat shield.
  • the inner shape of the heat shield in a first honeycomb structure portion is parallel to the longitudinal axis of the turbine. Upstream of the first flat section, the inner shape of the heat shield may be inclined in a second section to the longitudinal axis of the turbine. Since the heat shield is exposed to the high temperature of the hot air flow and the high pressure loss in the flow direction, it may lead to high stress concentrations in the curved portion of the heat shield between the first portion and the second portion. These stresses can significantly reduce the life of the heat shield.
  • the present invention has for its object to provide a heat shield segment for a stator of a gas turbine with an improved construction, which avoids the problems mentioned, that is, a construction which reduces the stresses in the curved portion of the heat shield segment.
  • the heat shield segment for a stator of a gas turbine having the features of claim 1.
  • Advantageous developments of the heat shield segment according to the invention will become apparent from the dependent claims.
  • the heat shield segment has a curved section in at least one region of the profile in the longitudinal direction of the gas turbine, with a radially outer surface of the heat shield segment provided in the region of the curved section and in a first end region in the circumferential direction of the turbine with an elevation extending in the circumferential direction of the turbine is.
  • the increase reduces the stresses in the heat shield segment in use and in the region of the curved section. This significantly prolongs the life of the heat shield.
  • 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 reinforced, without having to provide a rib extending between the end regions, which avoids additional metal consumption, so that the weight of the heat shield can be kept low.
  • Figure 1 is a perspective view of a heat shield segment according to a
  • FIG. 2 shows a section through the heat shield segment in FIG. 1 in the region of the elevation along the line A-A,
  • FIG. 3 shows a cross section through a turbine section with a
  • Figure 4 is a perspective view of a heat shield segment according to the prior art.
  • FIG. 4 shows a heat shield segment 1 according to the prior art.
  • a heat shield may include a number of such heat shield segments 1 that form an outer boundary of a hot gas flow along the turbine blades 2 (see, e.g., Figure 3).
  • 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 can be seen from FIG.
  • FIG. 3 shows a cross section through a turbine section with a heat shield segment according to the prior art.
  • 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 1 1 extend obliquely to the longitudinal axis of the turbine, wherein the flow direction of the hot gas through the turbine with arrow 10 is designated. 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 1 1 and in particular in the end portions 13 of the heat shield segment 1 in the circumferential direction of Turbine lead to high voltages that can significantly limit the life of the heat shield segment 1.
  • FIG. 1 shows a heat shield segment 1 according to a preferred embodiment of the invention. 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 can have a two-stage shape, as can be seen from FIG.
  • 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 provided with a number of heat shield segments 1 according to the invention which form an outer boundary of a hot gas flow along the turbine blades 2 (see, for example, Figure 3).
  • the heat shield segments 1 are provided with a groove 17 running in the longitudinal direction of the turbine, in each case in the end sides, as can be seen from FIG.
  • 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.

Landscapes

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

Abstract

The invention relates to a heat shield segment (1) for a stator of a gas turbine which comprises a rotatably received turbine rotor having turbine blades (2), a hot combustion air flow flowing toward said turbine rotor. The heat shield segment (1) is arranged radially between the turbine rotor and a turbine housing (19) and is fastened to the turbine housing. The heat shield segment (1) has a profile which has a curved section (12) in at least one position of the profile in the longitudinal direction of the turbine, a radial exterior (15) of the heat shield segment (1) having an elevated section (14) that extends in the circumferential direction of the turbine in the area of the curved section (12) and in a first terminal section in the circumferential direction of the heat shield segment (1).

Description

Hitzeschildsegment für einen Stator einer Gasturbine Heat shield segment for a stator of a gas turbine

Technisches GebietTechnical area

Die Erfindung betrifft ein Hitzeschildsegment für einen Stator einer Gasturbine, nach dem Oberbegriff des Anspruchs 1.The invention relates to a heat shield segment for a stator of a gas turbine, according to the preamble of claim 1.

Stand der TechnikState of the art

Der Turbinenrotor einer Gasturbine ist üblicherweise in radialer Richtung von einem Gehäuse umgeben, dass meist in diesem Bereich als Hitzeschild bezeichnet ist. Der Hitzeschild kann eine Anzahl von Hitzeschildsegmenten enthalten, wobei der Hitzeschild eine äußere Begrenzung einer heißen Gasströmung entlang den Turbinenlaufschaufeln bildet. Außerdem verhindert der Hitzeschild, dass heiße Verbrennungsgase in den mit Kühlluft gefüllten Hohlraum zwischen dem Hitzeschild und einem radialen äußeren Gehäuse eindringt. Der Hitzeschild kann unterschiedliche Formen haben und die Innenform des Hitzeschilds definiert den Durchflussquerschnitt des Heißluftstroms in der Turbine. Die Turbinenschaufeln des Turbinenrotors weisen üblicherweise ein umlaufendes, auf der radialen Außenseite des Turbinenrotors angeordnetes, je nach Strömungsbedingungen zylindrisch oder konisch verlaufendes Deckband auf. Das Deckband hat normalerweise auf seiner radialen Außenseite zwei sich radial auswärts erstreckende Dichtungsrippen. Den beiden Dichtungsrippen in radialer Richtung gegenüberliegend sind am Hitzeschild jeweils Honigwabenstrukturen ortsfest verbunden, die der Abdichtung des Abstandes zwischen den Dichtungsrippen und dem Hitzeschild dienen. Die Innenform des Hitzeschilds in einem ersten mit einer Honigwabenstruktur versehenen Abschnitt verläuft parallel zur Längsachse der Turbine. Stromaufwärts des ersten flachen Abschnitts kann die Innenform des Hitzeschilds in einem zweiten Abschnitt schräg zur Längsachse der Turbine verlaufen. Da der Hitzeschild der hohen Temperatur des Heißluftstroms und dem hohen Druckverlust in Strömungsrichtung ausgesetzt ist, kann es im gekrümmten Bereich des Hitzeschilds zwischen dem ersten Abschnitt und dem zweiten Abschnitt zu hohen Spannungskonzentrationen führen. Diese Spannungen können die Lebensdauer des Hitzeschilds beträchtlich verringern.The turbine rotor of a gas turbine is usually surrounded in the radial direction by a housing that is usually referred to in this area as a heat shield. The heat shield may include a number of heat shield segments, wherein the heat shield forms an outer boundary of a hot gas flow along the turbine blades. In addition, the heat shield prevents hot combustion gases from entering the cooling air filled cavity between the heat shield and a radially outer housing. The heat shield may have different shapes and the inner shape of the heat shield defines the flow area of the hot air flow in the turbine. The turbine blades of the turbine rotor usually have a circumferential, arranged on the radial outer side of the turbine rotor, depending on the flow conditions cylindrically or conically extending shroud. The shroud usually has two on its radial outside radially outwardly extending sealing ribs. The two sealing ribs in the radial direction opposite to the heat shield each honeycomb structures are fixedly connected, which serve to seal the distance between the sealing ribs and the heat shield. The inner shape of the heat shield in a first honeycomb structure portion is parallel to the longitudinal axis of the turbine. Upstream of the first flat section, the inner shape of the heat shield may be inclined in a second section to the longitudinal axis of the turbine. Since the heat shield is exposed to the high temperature of the hot air flow and the high pressure loss in the flow direction, it may lead to high stress concentrations in the curved portion of the heat shield between the first portion and the second portion. These stresses can significantly reduce the life of the heat shield.

Darstellung der ErfindungPresentation of the invention

Hier setzt die Erfindung an. Der vorliegenden Erfindung liegt die Aufgabe zugrunde, ein Hitzeschildsegment für einen Stator einer Gasturbine mit einer verbesserten Konstruktion bereitzustellen, die die genannten Probleme vermeidet, das heißt eine Konstruktion, die die Spannungen im gekrümmten Bereich des Hitzeschildsegments vermindert.This is where the invention starts. The present invention has for its object to provide a heat shield segment for a stator of a gas turbine with an improved construction, which avoids the problems mentioned, that is, a construction which reduces the stresses in the curved portion of the heat shield segment.

Erfindungsgemäß wird dieses Problem durch ein Hitzeschildsegment für einen Stator einer Gasturbine mit den Merkmalen des Anspruchs 1 gelöst. Vorteilhafte Weiterbildungen des erfindungsgemäßen Hitzeschildsegments ergeben sich aus den abhängigen Ansprüchen. Erfindungsgemäß weist das Hitzeschildsegment in mindestens einem Bereich des Profils in Längsrichtung der Gasturbine einen gekrümmten Abschnitt auf, wobei eine radial äußere Fläche des Hitzeschildsegments im Bereich des gekrümmten Abschnitts und in einem ersten Endbereich in Umfangsrichtung der Turbine mit einer sich in Umfangsrichtung der Turbine erstreckenden Erhöhung versehen ist. Durch die Erhöhung werden die Spannungen im Hitzeschildsegment im Einsatz und im Bereich des gekrümmten Abschnitts vermindert. Dadurch wird die Lebensdauer des Hitzeschilds erheblich verlängert.According to the invention, this problem is solved by a heat shield segment for a stator of a gas turbine having the features of claim 1. Advantageous developments of the heat shield segment according to the invention will become apparent from the dependent claims. According to the invention, the heat shield segment has a curved section in at least one region of the profile in the longitudinal direction of the gas turbine, with a radially outer surface of the heat shield segment provided in the region of the curved section and in a first end region in the circumferential direction of the turbine with an elevation extending in the circumferential direction of the turbine is. The increase reduces the stresses in the heat shield segment in use and in the region of the curved section. This significantly prolongs the life of the heat shield.

In vorteilhafter Ausgestaltung der Erfindung beträgt die Länge der Erhöhung in Umfangsrichtung weniger als ein viertel der Gesamtlänge des Hitzeschildsegments in Umfangsrichtung. Dabei 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 Hitzeschilds 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. In this case, the heat shield segment is sufficiently reinforced, without having to provide a rib extending between the end regions, 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 ist anhand eines Ausführungsbeispiels in den Zeichnungen schematisch dargestellt und wird im Folgenden unter Bezugnahme auf die Zeichnungen ausführlich beschrieben.The invention is schematically illustrated by means of an embodiment in the drawings and will be described in detail below with reference to the drawings.

Es zeigen, jeweils schematisch, Figur 1 in perspektivischer Ansicht ein Hitzeschildsegment gemäß einerShow, in each case schematically, Figure 1 is a perspective view of a heat shield segment according to a

Ausführungsform der Erfindung,Embodiment of the invention,

Figur 2 einen Schnitt durch das Hitzeschildsegment in Figur 1 im Bereich der Erhöhung entlang der Linie A-A,FIG. 2 shows a section through the heat shield segment in FIG. 1 in the region of the elevation along the line A-A,

Figur 3 einen Querschnitt durch einen Turbinenabschnitt mit einem3 shows a cross section through a turbine section with a

Hitzeschildsegment nach dem Stand der Technik,Heat shield segment according to the prior art,

Figur 4 in perspektivischer Ansicht ein Hitzeschildsegment nach dem Stand der Technik.Figure 4 is a perspective view of a heat shield segment according to the prior art.

Wege zur Ausführung der ErfindungWays to carry out the invention

In Figur 4 ist ein Hitzeschildsegment 1 nach dem 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 Halterungselementen 3, 4 angeordnet, die zur Positionierung des Hitzeschildsegments 1 in radialer Richtung und in Umfangsrichtung dienen.FIG. 4 shows a heat shield segment 1 according to the prior art. A heat shield may include a number of such heat shield segments 1 that form an outer boundary of a hot gas flow along the turbine blades 2 (see, e.g., Figure 3). 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 can be seen from FIG. On the radially outer side of the heat shield segment 1 support elements 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 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 1 1 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 1 1 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.FIG. 3 shows a cross section through a turbine section with a heat shield segment according to the prior art. 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 1 1 extend obliquely to the longitudinal axis of the turbine, wherein the flow direction of the hot gas through the turbine with arrow 10 is designated. 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 1 1 and in particular in the end portions 13 of the heat shield segment 1 in the circumferential direction of 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. 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.FIG. 1 shows a heat shield segment 1 according to a preferred embodiment of the invention. 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. 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 Figure 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. In this case, the profile of the heat shield segment 1 in the circumferential direction of the turbine and in the region of the elevation 14 can have a two-stage shape, as can be seen from FIG. 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 provided with a number of heat shield segments 1 according to the invention which form an outer boundary of a hot gas flow along the turbine blades 2 (see, for example, Figure 3). The heat shield segments 1 are provided with a groove 17 running in the longitudinal direction of the turbine, in each case in the end sides, as can be seen from FIG. 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. Insbesondere im Hinblick auf einige bevorzugte Ausführungsbeispiele entnimmt ihr der Fachmann, dass verschiedene Änderungen und Modifikationen in Gestalt und Einzelheiten gemacht werden können, ohne von dem Gedanken und Umfang der Erfindung abzuweichen. Dementsprechend soll die Offenbarung der vorliegenden Erfindung nicht einschränkend sein. Stattdessen soll die Offenbarung der vorliegenden Erfindung den Umfang der Erfindung veranschaulichen, der in den nachfolgenden Ansprüchen dargelegt ist. 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. With particular reference to some preferred embodiments, those skilled in the art will appreciate that various changes and modifications in form and detail may be made without departing from the spirit and scope of the invention. Accordingly, the disclosure of the present invention is not intended to be limiting. Instead, the disclosure of the present invention is intended to illustrate the scope of the invention, which is set forth in the following claims.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

HitzeschildsegmentHeat shield segment

TurbinenlaufschaufelTurbine blade

Halterungselementsupporting member

Halterungselementsupporting member

Deckbandshroud

Ripperib

HonigwabenstrukturHoneycomb structure

Innenform erster AbschnittInside shape first section

Strömungsrichtung zweiter Abschnitt gekrümmter BereichFlow direction second section curved area

Endbereichend

Erhöhung radiale AußenseiteIncrease radial outside

Ripperib

Nutgroove

Hohlraumcavity

Turbinengehäuse turbine housing

Claims

Patentansprüche claims 1. Hitzeschildsegment für einen Stator einer Gasturbine, die einen drehbar gelagerten Turbinenrotor (2) mit Turbinenschaufeln aufweist, wobei das Hitzeschildsegment (1) radial zwischen dem Turbinenrotor (2) und einem Turbinengehäuse (19) angeordnet und an dem Turbinengehäuse (19) befestigt ist und ein Profil aufweist, das in mindestens einem Bereich des Profils in Längsrichtung der Turbine einen gekrümmten Abschnitt (12) aufweist, dadurch gekennzeichnet, dass eine radiale Außenseite (15) des Hitzeschildsegments (1) im Bereich des gekrümmten Abschnitts (12) und in einem ersten Endbereich in Umfangsrichtung der Gasturbine mit wenigstens einer sich in Umfangsrichtung der Gasturbine erstreckenden Erhöhung (14) versehen ist.A heat shield segment for a stator of a gas turbine having a rotatably mounted turbine rotor (2) with turbine blades, wherein the heat shield segment (1) is disposed radially between the turbine rotor (2) and a turbine housing (19) and fixed to the turbine housing (19) and a profile which has a curved section (12) in at least one region of the profile in the longitudinal direction of the turbine, characterized in that a radial outer side (15) of the heat shield segment (1) in the region of the curved section (12) and in a first end region in the circumferential direction of the gas turbine is provided with at least one extending in the circumferential direction of the gas turbine increase (14). 2. Hitzeschildsegment nach Anspruch 1, dadurch gekennzeichnet, dass die Länge der Erhöhung (14) in Umfangsrichtung der Gasturbine weniger als ein viertel der Gesamtlänge des Hitzeschildsegments (1) in Umfangsrichtung beträgt.2. heat shield segment according to claim 1, characterized in that the length of the elevation (14) in the circumferential direction of the gas turbine is less than a quarter of the total length of the heat shield segment (1) in the circumferential direction. 3. Hitzeschildsegment nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die radial äußere Fläche (15) des Hitzeschildsegments (1) mit einer Rippe (16) versehen ist, die sich am Ende des Hitzeschildsegments (1) in Umfangsrichtung der Gasturbine befindend in Längsrichtung der Gasturbine zumindest teilweise erstreckt, wobei die Erhöhung (14) aus der Rippe (16) in Umfangsrichtung herausragt.Third heat shield segment according to one of the preceding claims, characterized in that the radially outer surface (15) of the heat shield segment (1) is provided with a rib (16) located at the end of the heat shield segment (1) in the circumferential direction of the gas turbine in the longitudinal direction the gas turbine extends at least partially, wherein the elevation (14) protrudes from the rib (16) in the circumferential direction. 4. Hitzeschildsegment nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die radial äußere Fläche (15) des Hitzeschildsegments (1) im Bereich des gekrümmten Abschnitts (12) und in einem dem ersten Endbereich gegenüberliegenden zweiten Endbereich mit einer sich in Umfangsrichtung der Turbine erstreckenden zweiten Erhöhung (14) versehen ist.4. heat shield segment according to one of the preceding claims, characterized in that the radially outer surface (15) of the heat shield segment (1) in the region of the curved portion (12) and in a first end region opposite the second end portion extending in the circumferential direction of the turbine second increase (14) is provided. 5. Hitzeschildsegment nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Profil des Hitzeschildsegments (1) in Umfangsrichtung der Gasturbine und im Bereich der Erhöhung (14) eine zweistufige Form aufweist.5. Heat shield segment according to one of the preceding claims, characterized in that the profile of the heat shield segment (1) in the circumferential direction of the gas turbine and in the region of the elevation (14) has a two-stage shape. 6. Hitzeschildsegment nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass sich die Länge der Erhöhung (14) in Umfangsrichtung der Turbine zur Breite der Erhöhung (14) in Längsrichtung der Turbine im Verhältnis 1 :2 bis 3:1 verhält.6. Heat shield segment according to one of the preceding claims, characterized in that the length of the elevation (14) in the circumferential direction of the turbine to the width of the elevation (14) in the longitudinal direction of the turbine in the ratio 1: 2 to 3: 1 behaves. 7. Hitzeschildsegment nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Hitzeschildsegment (1) an mindestens zwei Stellen des Hitzeschildsegmentprofils in Längsrichtung der Turbine einen gekrümmten Abschnitt (12) aufweist, wobei die radial äußere Fläche des Hitzeschildsegments (1) jeweils im Bereich der gekrümmten Abschnitte (12) und in einem ersten und/oder einem zweiten Endbereich in Umfangsrichtung des Hitzeschildsegments (1 ) jeweils mit einer sich in Umfangsrichtung der Turbine erstreckenden Erhöhung (14) versehen ist. 7. heat shield segment according to one of the preceding claims, characterized in that the heat shield segment (1) at least two points of the heat shield segment profile in the longitudinal direction of the turbine has a curved portion (12), wherein the radially outer surface of the heat shield segment (1) respectively in the region of curved portions (12) and in a first and / or a second end region in the circumferential direction of the heat shield segment (1) each having a circumferentially extending the turbine increase (14) is provided. 8. Hitzeschildsegment nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Innenform des Hitzeschildsegments (1) einen im Wesentlichen parallel zur Längsrichtung der Turbine verlaufenden ersten Abschnitt (9) und einen an dem ersten Abschnitt (9) stromaufwärts angrenzenden und schräg zur Längsrichtung verlaufenden zweiten Abschnitt (11) aufweist, wobei die Erhöhung (14) in Längsrichtung der Turbine an einer Stelle, an der der erste und der zweite Abschnitte (9, 11) sich treffen, angeordnet ist.8. heat shield segment according to one of the preceding claims, characterized in that the inner shape of the heat shield segment (1) extending substantially parallel to the longitudinal direction of the turbine first portion (9) and one of the first portion (9) upstream and extending obliquely to the longitudinal direction second portion (11), wherein the elevation (14) in the longitudinal direction of the turbine at a location at which the first and second portions (9, 11) meet, is arranged. 9. Hitzeschildsegment nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass eine in Längsrichtung der Turbine verlaufende Nut (17) in einer sich radial erstreckenden Seite des Hitzeschildsegments (1) wenigstens im Bereich der Erhöhung (14) vorgesehen ist.9. heat shield segment according to one of the preceding claims, characterized in that in the longitudinal direction of the turbine extending groove (17) in a radially extending side of the heat shield segment (1) is provided at least in the region of the elevation (14). 10. Hitzeschild, der eine Anzahl von Hitzeschildsegmenten (1) nach einem der vorhergehenden Ansprüche enthält, wobei der Hitzeschild eine äußere Begrenzung einer heißen Gasströmung entlang den Turbinenlaufschaufeln bildet. A heat shield comprising a number of heat shield segments (1) according to any one of the preceding claims, wherein the heat shield forms an outer boundary of a hot gas flow along the turbine blades.
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 true EP2173974A1 (en) 2010-04-14
EP2173974B1 EP2173974B1 (en) 2011-10-26

Family

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EP08761301A Active EP2173974B1 (en) 2007-06-28 2008-06-23 Heat shield segment for a stator of a gas turbine

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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)

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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

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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
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Also Published As

Publication number Publication date
WO2009000801A1 (en) 2008-12-31
TW200925389A (en) 2009-06-16
US8182210B2 (en) 2012-05-22
CA2690705C (en) 2015-08-04
TWI475152B (en) 2015-03-01
SI2173974T1 (en) 2012-03-30
CA2690705A1 (en) 2008-12-31
US20100150712A1 (en) 2010-06-17
ATE530736T1 (en) 2011-11-15
EP2173974B1 (en) 2011-10-26

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