EP0224817B1 - Hitzeschildanordnung, insbesondere für Strukturteile von Gasturbinenanlagen - Google Patents

Hitzeschildanordnung, insbesondere für Strukturteile von Gasturbinenanlagen Download PDF

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Publication number
EP0224817B1
EP0224817B1 EP86116167A EP86116167A EP0224817B1 EP 0224817 B1 EP0224817 B1 EP 0224817B1 EP 86116167 A EP86116167 A EP 86116167A EP 86116167 A EP86116167 A EP 86116167A EP 0224817 B1 EP0224817 B1 EP 0224817B1
Authority
EP
European Patent Office
Prior art keywords
heat shield
hat
supporting structure
arrangement according
shield arrangement
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.)
Expired
Application number
EP86116167A
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German (de)
English (en)
French (fr)
Other versions
EP0224817A1 (de
Inventor
Bernard Dr. Becker
Helmut Dipl.-Math. Maghon
Wilhelm Dipl.-Ing. Schulten
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP0224817A1 publication Critical patent/EP0224817A1/de
Application granted granted Critical
Publication of EP0224817B1 publication Critical patent/EP0224817B1/de
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures

Definitions

  • the present invention relates to a heat shield arrangement for protecting a support structure against a hot fluid according to the preamble of claim 1.
  • a heat shield arrangement is known for example from GB-PS 790 292.
  • heat shield elements arranged next to one another and anchored in a heat-mobile manner are described, which have a hat part and a shaft part in the manner of a mushroom, the hat part being a flat or spatial, polygonal plate body.
  • a disadvantage of this arrangement is that the plate bodies can expand and bend depending on the temperature, as a result of which the cooling fluid spade changes greatly, which in turn impairs the cooling fluid flow. In particular, the gaps are much larger at low temperature than at high temperature.
  • the object of the present invention is to provide an improved heat shield arrangement of the generic type which is suitable for lining complicated-shaped structures, but which has the lowest possible and uniform cooling air consumption in all operating states.
  • this column is only of limited use as a defined throttle point for the cooling fluid flow. It is therefore important to arrange baseboards opposite these columns on the supporting structure, which form a defined distance from the hat parts.
  • These skirting boards can also have defined depressions on their upper side, which lie transversely to the course of the skirting board, which ensure a minimum flow of cooling fluid even when there are heat shield elements. It may even be advantageous to dimension the skirting boards and heat shield elements so that they lie against one another during the initial assembly, and that a gap may not form until commissioning due to the effects of heat.
  • any spatial surfaces of support structures with such heat shield elements.
  • Such surfaces can always be broken down into segments of a suitable size, depending on the specific shape, whether triangles, polygons or segments of a surface of the rotating body are the cheapest solution.
  • the resulting triangles are generally not equilateral and not completely identical to one another, but it is desirable to use triangles that are almost equilateral if possible.
  • a cooling fluid preferably air
  • impingement cooling This effect alone cools the hat parts considerably.
  • the cooling fluid flows to the edges of the hat parts and through the gaps between the hat parts and, thus deflected by the hot fluid flowing past, additionally forms a cooling film on the top of the hat parts.
  • the heat shield arrangement shown schematically in simplified form in FIGS. 1 and 2 is particularly suitable for gas turbine systems, and in particular for the turbine housing, through which the hot gases coming from the combustion chamber flow. So far, it has been difficult to cool such support structures 1 or to protect them by means of heat shield arrangements. Therefore, such tag structures were mostly used without heat shields while accepting the disadvantages.
  • the support structure 1 is now provided with cooling air passages 2, which are distributed uniformly or in accordance with the cooling requirement over the support structure 1.
  • HG is the hot gas side
  • KG is the cold gas side; the latter presses cooling air under pressure through the passages 2, as indicated by arrows.
  • Heat shield elements are anchored to the support structure 1, which have a hat part 3 and a shaft part 5 in the manner of a mushroom.
  • the shaft part consists of an anchor bolt 5, which penetrates the support structure 1 in a through hole 8. It is held by means of an annular shoulder 5.2 on its reinforced head 5.1 to the hot gas side HG of the support structure 1 at a distance a1 and in each case braced against the support structure 1 by a fastening nut 5.3 screwed onto its free end, the fastening nuts being secured against rotation by a welding point (not shown) Cold gas side KG of the support structure 1 are connected.
  • the cooling air flowing through the cooling air passages 2 enters the space 6 between the support structure and the hat part, impacts against the underside 3.1 of the hat part 3 and then flows along this underside 3.1 to the cooling air gaps 4 between the individual hat parts 3.
  • Skirting boards 1.4 in the space 6 below the Cooling air gaps 4 cause defined throttling points and prevent the entry of hot gas into the intermediate space 6.
  • the cooling air emerging from the cooling air gaps 4 is deflected on the hot gas side HG by the gas flow prevailing there and thus forms a cooling air film on the top of the hat parts 3, as a result of which an additional cooling effect occurs.
  • the hat parts 3 of the individual heat shield elements and their anchor bolts 5 are preferably both z. B.
  • the anchor bolts 5 are each welded to the central region 7.
  • the heat shield elements have similar hat parts of the shape of equilateral triangles.
  • an irregularly curved surface must be composed of different polygons, preferably triangles.
  • Such polygons or triangles always have a precisely definable center of gravity, but the anchor bolts do not necessarily have to be fastened exactly in this center of gravity.
  • anchoring outside the center of gravity can be advantageous for reasons of the tendency of individual sections of the polygons to vibrate.
  • the baseboards 1.4 bring about defined throttling points for the cooling gas, which, as explained above, adjust themselves to uniform cross sections.
  • the exact width of the cooling air gaps 4 between the hat parts 3 is therefore not important if they are sufficiently wide. This is also an advantage because these gaps change constantly under different operating conditions.
  • FIG. 3 shows a longitudinal section through part of the heat shield arrangement
  • FIG. 4 shows a section through FIG. 3 along the line IV-IV
  • FIG. 5 shows a view from above of a heat shield element.
  • the support structure 31 has again rum cooling air holes 32 and firmly anchored heat shield elements with triangular hat parts 33. Between the individual hat parts 33 there are cooling air gaps of width a33. Between the support structure 31 and the underside 33.1 of the hat parts 33 there is an intermediate space 36 of width a31.
  • the hat parts 33 have in their central area a pot-like shape 33.2, 33.3, which has a through hole 33.4 in its underside 33.3.
  • a bolt 35 is passed through this bore 33.4 and a corresponding through bore 38 in the support structure 31, the bolt head 35.1 being in the pot-like configuration 33.2, 33.3, preferably in alignment with the surface of the hat part 33 on the hot gas side HG.
  • the bolt head 35.1 z. B. have a hexagon or a similar attack possibility for a tool for tightening.
  • This bolt is braced against the cold gas side KG of the support structure 31 by means of a nut, the nut 35.2 having claw-shaped brackets 35.3 which are supported against the support structure 31 and are welded to it 35.4.
  • the nut 35.2 itself does not need to touch the support structure 31, so that a suitable pretension can be achieved by the claw-shaped arms 35.3.
  • the through bore 38 in the support structure 31 and the corresponding bore 33.4 are at least in some areas significantly wider than the diameter of the bolt 35, cooling air can flow along the bolt 35 and thus cool the latter and, in particular, its head 35.1.
  • Suitable drainage channels 33.6 must be provided in the pot-like shape 33.2, 33.3.
  • Other solutions for maintaining the pretensioning force of the bolt 35 are also conceivable, such as expansion screws, spring plates and the like.
  • Additional cooling fluid passages for example in the form of bores 33.6, can be provided in the pot-like shape 33.2, 33.3. Additional cooling fluid passages 33.7 can also be provided at points of the heat shield elements 33 which are to be cooled, but should not be aligned with the cooling fluid bores 32. 3 also shows realistic arrangements for skirting boards 31.4, 31.6, 31.7 as throttling points 39 for the cooling gas flow. These baseboards can in the shape of the support structure 31 z. B. taken into account by casting from the beginning or applied later. As shown in the skirting board 31.4, they should have a surface shape 31.5 adapted to the course of the adjacent hat parts 33, but this is not absolutely necessary if only a defined throttle point is formed.
  • skirting boards in the area of the contact points of several heat shield elements can be difficult because of the large accumulations of material.
  • the skirting board which is otherwise also possible, may have special shapes, z. B. as shown with the baseboards 31.6, 31.7, an annular course with a, for example, hemispherical recess 31.8 inside. In this way, defined throttle points 39 remain at a suitable distance a32 without too much material being piled up at one point.
  • FIG. 6 shows an example of the division of a curved surface into suitable triangles.
  • an inner casing of a gas turbine with relatively few triangles can be approximated very well without the individual heat shield elements having to be curved.
  • a better approximation of the shape is possible either through a larger number of polygons, especially triangles, or through the use of curved heat shield elements.
  • a major advantage of using triangles, however, is that three points always define a plane, so that the division of a curved surface into triangles presents the fewest problems in the later manufacture of the heat shield elements.
  • the present invention is particularly suitable for hot gas ducts, combustion chambers and similar parts of gas turbines, but is not restricted to such applications.
  • This heat shield arrangement enables higher temperatures inside a support structure or simplifies its construction and reduces its loads.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP86116167A 1985-12-02 1986-11-21 Hitzeschildanordnung, insbesondere für Strukturteile von Gasturbinenanlagen Expired EP0224817B1 (de)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE3542531 1985-12-02
DE3542531 1985-12-02
DE3623744 1986-07-14
DE3623744 1986-07-14

Publications (2)

Publication Number Publication Date
EP0224817A1 EP0224817A1 (de) 1987-06-10
EP0224817B1 true EP0224817B1 (de) 1989-07-12

Family

ID=25838380

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86116167A Expired EP0224817B1 (de) 1985-12-02 1986-11-21 Hitzeschildanordnung, insbesondere für Strukturteile von Gasturbinenanlagen

Country Status (4)

Country Link
US (1) US4749029A (enrdf_load_stackoverflow)
EP (1) EP0224817B1 (enrdf_load_stackoverflow)
DE (1) DE3664374D1 (enrdf_load_stackoverflow)
IN (1) IN165091B (enrdf_load_stackoverflow)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1989012789A1 (fr) * 1988-06-13 1989-12-28 Siemens Aktiengesellschaft Bouclier thermique n'exigeant que peu de fluide de refroidissement
WO1998013645A1 (de) 1996-09-26 1998-04-02 Siemens Aktiengesellschaft Hitzeschildkomponente mit kühlfluidrückführung und hitzeschildanordnung für eine heissgasführende komponente
US5735115A (en) * 1994-01-24 1998-04-07 Siemens Aktiengesellschaft Gas turbine combustor with means for removing swirl
US6029455A (en) * 1996-09-05 2000-02-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Turbojet engine combustion chamber with heat protecting lining
US6223538B1 (en) 1998-11-30 2001-05-01 Asea Brown Boveri Ag Ceramic lining
US6276142B1 (en) 1997-08-18 2001-08-21 Siemens Aktiengesellschaft Cooled heat shield for gas turbine combustor
DE10036211A1 (de) * 2000-07-25 2002-02-07 Rolls Royce Deutschland Brennkammerschindel
EP1284390A1 (de) 2001-06-27 2003-02-19 Siemens Aktiengesellschaft Hitzeschildanordnung für eine Heissgas führende Komponente, insbesondere für Strukturteile von Gasturbinen
EP1507116A1 (de) 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Hitzeschildanordnung für eine ein Heissgas führende Komponente, insbesondere für eine Brennkammer einer Gasturbine
US7021061B2 (en) 2001-05-25 2006-04-04 Siemens Aktiengesellschaft Heat shield arrangement for a hot-gas conducting component, in particular for structural pieces of gas turbines and method for production of said arrangement
EP1852616A3 (en) * 2006-05-02 2011-05-11 United Technologies Corporation Fastener
RU209161U1 (ru) * 2021-12-01 2022-02-03 Антон Владимирович Новиков Теплозащитный экран для камеры сгорания газовой турбины
RU209216U1 (ru) * 2021-08-30 2022-02-07 Антон Владимирович Новиков Теплозащитный экран для камеры сгорания газовой турбины

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DE19502730A1 (de) * 1995-01-28 1996-08-01 Abb Management Ag Keramische Auskleidung
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DE19623300A1 (de) * 1996-06-11 1997-12-18 Siemens Ag Hitzeschildanordnung, insbesondere für Strukturteile von Gasturbinenanlagen, mit geschichtetem Aufbau
DE59706557D1 (de) * 1997-07-28 2002-04-11 Alstom Keramische Auskleidung
JP4172913B2 (ja) * 1998-03-19 2008-10-29 シーメンス アクチエンゲゼルシヤフト 燃焼器用壁セグメントおよび燃焼器
US6286317B1 (en) * 1998-12-18 2001-09-11 General Electric Company Cooling nugget for a liner of a gas turbine engine combustor having trapped vortex cavity
GB9926257D0 (en) 1999-11-06 2000-01-12 Rolls Royce Plc Wall elements for gas turbine engine combustors
DE10114619B4 (de) * 2000-03-27 2006-07-27 Cummins Inc., Columbus Belüftendes Befestigungselement
US6711900B1 (en) * 2003-02-04 2004-03-30 Pratt & Whitney Canada Corp. Combustor liner V-band design
US7146815B2 (en) * 2003-07-31 2006-12-12 United Technologies Corporation Combustor
US7114321B2 (en) * 2003-07-31 2006-10-03 General Electric Company Thermal isolation device for liquid fuel components
US7338244B2 (en) * 2004-01-13 2008-03-04 Siemens Power Generation, Inc. Attachment device for turbine combustor liner
EP1865258A1 (de) * 2006-06-06 2007-12-12 Siemens Aktiengesellschaft Gepanzerte Maschinenkomponente und Gasturbine
GB0705458D0 (en) * 2007-03-22 2007-05-02 Rolls Royce Plc A Location ring arrangement
US8435007B2 (en) * 2008-12-29 2013-05-07 Rolls-Royce Corporation Hybrid turbomachinery component for a gas turbine engine
US8973375B2 (en) * 2008-12-31 2015-03-10 Rolls-Royce North American Technologies, Inc. Shielding for a gas turbine engine component
EP2270395B1 (de) * 2009-06-09 2015-01-14 Siemens Aktiengesellschaft Hitzeschildelementanordnung und Verfahren zur Montage eines Hitzeschildelementes
GB0913580D0 (en) * 2009-08-05 2009-09-16 Rolls Royce Plc Combustor tile
CH703656A1 (de) * 2010-08-27 2012-02-29 Alstom Technology Ltd Von Heissgasen durchströmbarer Gehäusekörper mit innerem Hitzeschild.
US10378775B2 (en) * 2012-03-23 2019-08-13 Pratt & Whitney Canada Corp. Combustor heat shield
US20130298564A1 (en) * 2012-05-14 2013-11-14 General Electric Company Cooling system and method for turbine system
US9335049B2 (en) 2012-06-07 2016-05-10 United Technologies Corporation Combustor liner with reduced cooling dilution openings
US9239165B2 (en) 2012-06-07 2016-01-19 United Technologies Corporation Combustor liner with convergent cooling channel
US9243801B2 (en) * 2012-06-07 2016-01-26 United Technologies Corporation Combustor liner with improved film cooling
US9217568B2 (en) 2012-06-07 2015-12-22 United Technologies Corporation Combustor liner with decreased liner cooling
DE102012213637A1 (de) * 2012-08-02 2014-02-06 Siemens Aktiengesellschaft Brennkammerkühlung
EP2711634A1 (de) * 2012-09-21 2014-03-26 Siemens Aktiengesellschaft Hitzeschild mit einer Tragstruktur und Verfahren zum Kühlen der Tragstruktur
EP2711630A1 (de) * 2012-09-21 2014-03-26 Siemens Aktiengesellschaft Vorrichtung zum Kühlen einer Tragstruktur eines Hitzeschildes und Hitzeschild
US9322334B2 (en) * 2012-10-23 2016-04-26 General Electric Company Deformable mounting assembly
DE102012023297A1 (de) * 2012-11-28 2014-06-12 Rolls-Royce Deutschland Ltd & Co Kg Schindelbefestigungsanordnung einer Gasturbinenbrennkammer
ITMI20131115A1 (it) * 2013-07-03 2015-01-04 Ansaldo Energia Spa Piastrella per il rivestimento di camere di combustione, in particolare di impianti per la produzione di energia elettrica a turbina a gas, e camera di combustione comprendente detta piastrella
DE102013226490A1 (de) * 2013-12-18 2015-06-18 Rolls-Royce Deutschland Ltd & Co Kg Gekühlte Flanschverbindung eines Gasturbinentriebwerks
DE102013226488A1 (de) 2013-12-18 2015-06-18 Rolls-Royce Deutschland Ltd & Co Kg Unterlegscheibe einer Brennkammerschindel einer Gasturbine
DE102015202097A1 (de) * 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Ringbrennkammer mit Bypasssegment
US9869204B2 (en) * 2015-03-06 2018-01-16 United Technologies Corporation Integrated inner case heat shield
US10767863B2 (en) * 2015-07-22 2020-09-08 Rolls-Royce North American Technologies, Inc. Combustor tile with monolithic inserts
US10935236B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10830433B2 (en) * 2016-11-10 2020-11-10 Raytheon Technologies Corporation Axial non-linear interface for combustor liner panels in a gas turbine combustor
US10655853B2 (en) * 2016-11-10 2020-05-19 United Technologies Corporation Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor
US10935235B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
DE102017212575A1 (de) * 2017-07-21 2019-01-24 Siemens Aktiengesellschaft Verfahren zur Erhöhung der Leistung einer Gasturbine
US20190112946A1 (en) * 2017-10-13 2019-04-18 United Technologies Corporation Double wall service tube with annular airflow passage
US10801469B2 (en) * 2017-11-07 2020-10-13 General Electric Company Wind blade joints with floating connectors
US11204169B2 (en) * 2019-07-19 2021-12-21 Pratt & Whitney Canada Corp. Combustor of gas turbine engine and method
US10969106B2 (en) * 2019-08-13 2021-04-06 General Electric Company Axial retention assembly for combustor components of a gas turbine engine
FR3111414B1 (fr) * 2020-06-15 2022-09-02 Safran Helicopter Engines Production par fabrication additive de pièces complexes

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1989012789A1 (fr) * 1988-06-13 1989-12-28 Siemens Aktiengesellschaft Bouclier thermique n'exigeant que peu de fluide de refroidissement
US5735115A (en) * 1994-01-24 1998-04-07 Siemens Aktiengesellschaft Gas turbine combustor with means for removing swirl
US6029455A (en) * 1996-09-05 2000-02-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Turbojet engine combustion chamber with heat protecting lining
WO1998013645A1 (de) 1996-09-26 1998-04-02 Siemens Aktiengesellschaft Hitzeschildkomponente mit kühlfluidrückführung und hitzeschildanordnung für eine heissgasführende komponente
US6047552A (en) * 1996-09-26 2000-04-11 Siemens Aktiengesellschaft Heat-shield component with cooling-fluid return and heat-shield configuration for a component directing hot gas
US6276142B1 (en) 1997-08-18 2001-08-21 Siemens Aktiengesellschaft Cooled heat shield for gas turbine combustor
US6223538B1 (en) 1998-11-30 2001-05-01 Asea Brown Boveri Ag Ceramic lining
DE10036211A1 (de) * 2000-07-25 2002-02-07 Rolls Royce Deutschland Brennkammerschindel
US7021061B2 (en) 2001-05-25 2006-04-04 Siemens Aktiengesellschaft Heat shield arrangement for a hot-gas conducting component, in particular for structural pieces of gas turbines and method for production of said arrangement
US6675586B2 (en) 2001-06-27 2004-01-13 Siemens Aktiengesellschaft Heat shield arrangement for a component carrying hot gas, in particular for structural parts of gas turbines
EP1284390A1 (de) 2001-06-27 2003-02-19 Siemens Aktiengesellschaft Hitzeschildanordnung für eine Heissgas führende Komponente, insbesondere für Strukturteile von Gasturbinen
EP1507116A1 (de) 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Hitzeschildanordnung für eine ein Heissgas führende Komponente, insbesondere für eine Brennkammer einer Gasturbine
WO2005019730A1 (de) * 2003-08-13 2005-03-03 Siemens Aktiengesellschaft Hitzeschildanordnung für eine ein heissgas führende komponente, insbesondere für eine brennkammer einer gasturbine
US7849694B2 (en) 2003-08-13 2010-12-14 Siemens Aktiengesellschaft Heat shield arrangement for a component guiding a hot gas in particular for a combustion chamber in a gas turbine
EP1852616A3 (en) * 2006-05-02 2011-05-11 United Technologies Corporation Fastener
EP3330553A1 (en) * 2006-05-02 2018-06-06 United Technologies Corporation Fastener
RU209216U1 (ru) * 2021-08-30 2022-02-07 Антон Владимирович Новиков Теплозащитный экран для камеры сгорания газовой турбины
RU209161U1 (ru) * 2021-12-01 2022-02-03 Антон Владимирович Новиков Теплозащитный экран для камеры сгорания газовой турбины

Also Published As

Publication number Publication date
US4749029A (en) 1988-06-07
IN165091B (enrdf_load_stackoverflow) 1989-08-12
DE3664374D1 (en) 1989-08-17
EP0224817A1 (de) 1987-06-10

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