EP2173974B1 - Segment de bouclier thermique destiné au stator d'une turbine à gaz - Google Patents

Segment de bouclier thermique destiné au stator d'une turbine à gaz 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)
English (en)
Other versions
EP2173974A1 (fr
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/fr
Application granted granted Critical
Publication of EP2173974B1 publication Critical patent/EP2173974B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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.

Landscapes

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

Claims (7)

  1. Turbine à gaz, qui présente un rotor de turbine monté à rotation, avec des aubes de turbine (2) ainsi qu'au moins un segment de bouclier thermique (1) du côté du stator, le segment de bouclier thermique (1) respectif étant disposé radialement entre le rotor de turbine et un carter de turbine (19), et étant fixé sur le carter de turbine (19), et présentant un profilé qui présente dans au moins une région du profilé, dans la direction longitudinale de la turbine, une portion courbe (12),
    caractérisée en ce
    - qu'un côté extérieur radial (15) du segment de bouclier thermique (1) est pourvu, dans la région de la portion courbe (12) et dans une première région d'extrémité dans la direction périphérique de la turbine à gaz, d'au moins un rehaussement (14) s'étendant dans la direction périphérique de la turbine à gaz,
    - que la surface radialement extérieure (15) du segment de bouclier thermique (1) est pourvue d'une nervure (16) qui se situe à l'extrémité du segment de bouclier thermique (1) dans la direction périphérique de la turbine à gaz et qui s'étend au moins en partie dans la direction longitudinale de la turbine à gaz, le rehaussement (14) faisant saillie hors de la nervure (16) dans la direction périphérique,
    - que la surface radialement extérieure (15) du segment de bouclier thermique (1) est pourvue, dans la région de la portion courbe (12) et dans une deuxième région d'extrémité opposée à la première région d'extrémité, d'un deuxième rehaussement (14) s'étendant dans la direction périphérique de la turbine à gaz,
    - que le profilé du segment de bouclier thermique (1), dans la région du rehaussement respectif (14), présente dans la direction périphérique de la turbine à gaz une forme à deux étages, un premier étage conduisant depuis la surface radialement extérieure (15) du segment de bouclier thermique (1) au rehaussement respectif (14), tandis qu'un deuxième étage conduit depuis le rehaussement respectif (14) jusqu'à la nervure (16).
  2. Turbine à gaz selon la revendication 1, caractérisée en ce que
    la longueur du rehaussement (14) dans la direction périphérique de la turbine à gaz est inférieure à un quart de la longueur totale du segment de bouclier thermique (1) dans la direction périphérique.
  3. Turbine à gaz selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    la longueur du rehaussement (14) dans la direction périphérique de la turbine est dans un rapport, par rapport à la largeur du rehaussement (14) dans la direction longitudinale de la turbine, de 1:2 à 3:1.
  4. Turbine à gaz selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    le segment de bouclier thermique (1) présente, en au moins deux emplacements du profilé de segment de bouclier thermique, dans la direction longitudinale de la turbine, une portion courbe (12), la surface radialement extérieure du segment de bouclier thermique (1) étant pourvue, à chaque fois dans la région des portions courbes (12) et dans une première et/ou une deuxième région d'extrémité, dans la direction périphérique du segment de bouclier thermique (1), à chaque fois d'un rehaussement (14) s'étendant dans la direction périphérique de la turbine.
  5. Turbine à gaz selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    la forme intérieure du segment de bouclier thermique (1) présente une première portion (9) s'étendant essentiellement parallèlement à la direction longitudinale de la turbine et une deuxième portion (11) adjacente en amont à la première portion (9) et s'étendant obliquement par rapport à la direction longitudinale, le rehaussement (14) étant disposé dans la direction longitudinale de la turbine en un emplacement au niveau duquel la première et la deuxième portion (9, 11) se rejoignent.
  6. Turbine à gaz selon l'une quelconque des revendications précédentes,
    caractérisée en ce
    qu'une rainure (17) s'étendant dans la direction longitudinale de la turbine est prévue dans un côté extérieur s'étendant radialement du segment de bouclier thermique (1) au moins dans la région du rehaussement (14).
  7. Turbine à gaz selon l'une quelconque des revendications précédentes,
    caractérisée en ce
    qu'un certain nombre de segments de bouclier thermique (1) forment un bouclier thermique, qui forme une limitation extérieure d'un écoulement de gaz chaud le long des aubes mobiles (2) de la turbine.
EP08761301A 2007-06-28 2008-06-23 Segment de bouclier thermique destiné au stator d'une turbine à gaz Active EP2173974B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH10432007 2007-06-28
PCT/EP2008/057946 WO2009000801A1 (fr) 2007-06-28 2008-06-23 Segment de bouclier thermique destiné au stator d'une turbine à gaz

Publications (2)

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

Family

ID=38508786

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08761301A Active EP2173974B1 (fr) 2007-06-28 2008-06-23 Segment de bouclier thermique destiné au stator d'une turbine à gaz

Country Status (7)

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

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
EP2938863B1 (fr) * 2012-12-29 2019-09-25 United Technologies Corporation Liaison mécanique destinée à un écran thermique segmenté
US10233844B2 (en) 2015-05-11 2019-03-19 General Electric Company System for thermally shielding a portion of a gas turbine shroud assembly
DE102016213810A1 (de) 2016-07-27 2018-02-01 MTU Aero Engines AG Verkleidungselement für ein Turbinenzwischengehäuse
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 (de) * 1999-04-01 2000-10-05 Abb Alstom Power Ch Ag Hitzeschild für eine Gasturbine
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
EP1178182B1 (fr) * 2000-03-07 2013-08-14 Mitsubishi Heavy Industries, Ltd. Anneau fendu de turbine a gaz
JP4698847B2 (ja) * 2001-01-19 2011-06-08 三菱重工業株式会社 ガスタービン分割環
US6779597B2 (en) * 2002-01-16 2004-08-24 General Electric Company Multiple impingement cooled structure
DE102005013798A1 (de) * 2005-03-24 2006-09-28 Alstom Technology Ltd. Wärmestausegment zum Abdichten eines Strömungskanals einer Strömungsrotationsmaschine
US8528339B2 (en) * 2007-04-05 2013-09-10 Siemens Energy, Inc. Stacked laminate gas turbine component

Also Published As

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

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