EP1666797A1 - Elément de bouclier thermique, son procédé de fabrication, bouclier thermique et chambre de combustion - Google Patents

Elément de bouclier thermique, son procédé de fabrication, bouclier thermique et chambre de combustion Download PDF

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Publication number
EP1666797A1
EP1666797A1 EP04028445A EP04028445A EP1666797A1 EP 1666797 A1 EP1666797 A1 EP 1666797A1 EP 04028445 A EP04028445 A EP 04028445A EP 04028445 A EP04028445 A EP 04028445A EP 1666797 A1 EP1666797 A1 EP 1666797A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
thermal expansion
shield element
hot
coefficient
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.)
Withdrawn
Application number
EP04028445A
Other languages
German (de)
English (en)
Inventor
Holger Grote
Andreas Heilos
Marc Tertilt
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
Priority to EP04028445A priority Critical patent/EP1666797A1/fr
Priority to EP05803716A priority patent/EP1817147A1/fr
Priority to PCT/EP2005/012447 priority patent/WO2006058629A1/fr
Priority to US11/792,068 priority patent/US8522559B2/en
Priority to US11/792,130 priority patent/US20080104963A1/en
Priority to PCT/EP2005/056127 priority patent/WO2006058851A1/fr
Priority to EP05811090.9A priority patent/EP1817528B1/fr
Publication of EP1666797A1 publication Critical patent/EP1666797A1/fr
Priority to US12/774,049 priority patent/US9314939B2/en
Priority to US13/477,354 priority patent/US20120228468A1/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
    • 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 element, in particular a ceramic heat shield element, a method for producing a ceramic heat shield element, a built-up of heat shield elements Heisgasausposed and provided with a Heisgasausposed combustion chamber, which may be formed in particular as a gas turbine combustor.
  • the walls of hot gas-carrying combustors, such as gas turbine plants require thermal shielding of their supporting structure against hot gas attack.
  • the thermal shielding can be realized, for example, by means of a hot gas lining upstream of the actual combustion chamber wall, for example in the form of a ceramic heat shield.
  • a ceramic heat shield Such a Heisgasausstage usually constructed of a number of metallic or ceramic heat shield elements with which the combustion chamber wall is lined flat. Ceramic materials are ideally suited for the construction of a hot gas lining compared to metallic materials because of their high temperature resistance, corrosion resistance and low thermal conductivity.
  • a ceramic heat shield is described, for example, in EP 0 558 540 B1.
  • metallic heat shield elements have a higher resistance to thermal fluctuations and mechanical loads than ceramic heat shield elements, however, for example in gas turbine combustion chambers, they require complex cooling of the heat shield, since they have a higher thermal conductivity than ceramic heat shield elements.
  • metallic heat shield elements are more susceptible to corrosion and can due to their lower temperature stability can not be exposed to as high temperatures as ceramic heat shield elements.
  • the object of the present invention is to provide a heat shield element in which the tendency for cracking is reduced.
  • Another object of the present invention is to provide an advantageous heat shield and a combustion chamber equipped with an advantageous heat shield.
  • the first object of the invention is achieved by a heat shield element according to claim 1, the second object by a heat shield according to claim 7 and a combustion chamber according to claim 8 and the third object by a method according to claim 9.
  • the remaining claims contain advantageous developments of the invention.
  • a heat shield element according to the invention has a hot side to be turned towards a hot medium, a cold side to be turned away from the hot medium, and circumferential surfaces connecting the hot side to the cold side.
  • the hot side, the cold side and the peripheral surfaces limit the material volume of the heat shield element.
  • the heat shield element according to the invention is characterized in that the volume of material comprises at least two areas of material which differ in their coefficients of thermal expansion.
  • the thermal expansion of the material regions can be influenced in a targeted manner.
  • the stresses within the heat shield element can be reduced during operation of a heat shield.
  • At least one material region with a relatively low coefficient of thermal expansion adjoins the hot side of the heat shield element, whereas at least one material region with a relatively high thermal expansion coefficient adjoins the cold side of the heat shield element.
  • On the hot side occur at the transition from the ambient temperature (for example, when a gas turbine plant) to maximum operating temperature (for example, at full load of a gas turbine plant) greater temperature differences than on the cooled cold side of the heat shield element.
  • At least one material region with a relatively high coefficient of thermal expansion adjoins the peripheral surface of the heat shield element and at least one material region with a relatively low coefficient of thermal expansion, viewed from the peripheral surfaces, in the interior of the heat shield element Material volume can be arranged.
  • a material region with a relatively low coefficient of thermal expansion on the hot side and a material region with a relatively high coefficient of thermal expansion can also adjoin the cold side. Since the heat shield elements of a heat shield are cooled in particular in the area of the peripheral surfaces due to the blocking air flow, high temperature stresses occur in heat shield elements with a homogeneous coefficient of thermal expansion in the region of the peripheral surfaces, which occur due to the particularly low operating temperatures compared to the rest of the heat shield element. The fact that the coefficient of thermal expansion is increased in the region of the peripheral surfaces compared to the interior (seen from the peripheral surfaces) of the heat shield element, the voltages occurring can be reduced.
  • adjoining material regions with different coefficients of thermal expansion are configured in such a way that a smooth transition from the thermal expansion coefficient of one material region to the thermal expansion coefficient of the other material region takes place in the zone of transition from one material region to the other material region. Due to the smooth transition of the thermal expansion coefficient, the risk of destruction of the heat shield during the manufacturing process, in particular during the sintering process, which takes place at elevated, approximately homogeneous temperature, can be reduced.
  • the heat shield element according to the invention can in particular be designed as a ceramic heat shield element.
  • the reduced voltage formation due to the different coefficients of thermal expansion when spatial temperature gradients occur within the ceramic heat shield element leads to a reduced tendency to crack. This reduces the risk in a ceramic heat shield of formation of long cracks, which would lead to an exchange of the heat shield element. In addition, the reduced cracking tendency leads to a longer service life of the heat shield elements and thus to a reduction in the replacement rates of heat shield elements in hot gas linings.
  • a barrier fluid in particular sealing air can be used.
  • the heat shield according to the invention is characterized in that the heat shield elements are designed as heat shield elements according to the invention.
  • a combustion chamber according to the invention is lined with a heat shield according to the invention. It can be designed in particular as a gas turbine combustion chamber.
  • the method according to the invention for producing a ceramic heat shield element pressing or casting of a base material mixture takes place and subsequent sintering of the pressed or cast base material mixture.
  • the method according to the invention is characterized in that before the sintering of the pressed or cast base material mixture, the thermal expansion coefficients of different material regions are adjusted. By adjusting the thermal expansion coefficients of different material regions, the resistance of a heat shield element produced by means of the method according to the invention to temperature gradients within the heat shield element can be increased.
  • the adjustment of the coefficients of thermal expansion can be carried out, for example, by using base material mixtures having different compositions during pressing or casting for the corresponding material regions.
  • the composition of the base material mixture can be changed over in a fluid manner from one composition to the other composition, so that a smooth transition of the thermal expansion coefficient can be realized.
  • thermal expansion coefficients by after the pressing or casting of the base material mixture and before sintering a post-treatment of at least one material area, which after sintering compared to the rest of the base material mixture changed, for example.
  • a relatively low thermal Expansion coefficient should have.
  • the aftertreatment can be carried out, for example, by impregnating the at least one material area to be post-treated with a liquid. This approach allows a particularly good definition of material areas, which should have a relation to the rest of the base material mixture modified thermal expansion coefficient.
  • FIG. 1 shows a ceramic heat shield element 1 in a perspective view.
  • the heat shield element 1 has a hot side 3, which faces the hot medium after installation of the heat shield element 1 in a heat shield.
  • the hot side 3 is opposite the cold side 5 of the heat shield element 1, which faces after installation in a heat shield of the supporting structure of the combustion chamber wall and thus faces away from the hot medium.
  • Hot side 3 and cold side 5 are connected to each other via first peripheral surfaces 7 and second peripheral surfaces 9.
  • the second peripheral surfaces 9 have grooves 11 into which retaining clips (not shown) connected to the support structure of the combustion chamber wall can engage to hold the heat shield element in position after installation in a ceramic hot gas lining.
  • the first peripheral surfaces 7, however, have no groove.
  • the hot side 3, the cold side 5, the first peripheral surfaces 7 and the second peripheral surfaces 9 enclose the material volume of the heat shield element, which provides the thermal shielding effect.
  • a first embodiment of the heat shield element according to the invention is shown in Figure 2a in section.
  • the section runs along the line A-A from FIG. 1.
  • the hot side 13, the cold side 15 and the groove-free circumferential surfaces 17 of the heat shield element 10 of the first embodiment can be seen.
  • the heat shield element 10 has a first material region 19 and second material regions 21, which differ from the material region 19 by their thermal expansion coefficient.
  • the thermal expansion coefficient of the material regions 21 is greater than the thermal expansion coefficient of the material region 19. In this sense, the material region 19 has a relatively low thermal expansion coefficient, whereas the material regions 21 have a relatively high coefficient of thermal expansion.
  • the load-bearing structure of the combustion chamber wall is lined with a number of heat shield elements 10 area-covering.
  • the heat shield elements 10 are attached to one another in such a way that expansion gaps remain between adjacent heat shield elements 10. These expansion gaps serve to expand the heat shield elements 10 during operation of the combustion chamber on the basis of allow high operating temperatures without the heat shield elements 10 touching each other.
  • the expansion gaps are flushed with sealing air, which simultaneously serves to cool the holding elements holding the heat shield elements 10. For this reason, prevail at the Sperrluftumströmten first peripheral surfaces 17 and the likewise Sperrluftumströmten second peripheral surfaces (not visible in Fig. 2a) during operation of the combustion chamber lower temperatures than in the central region 23 of the Hitzeschildiatas 10.
  • the combustion chamber would therefore be the centrally located material area 19 of a conventional heat shield element, a higher thermal expansion experienced than the area located in the peripheral surfaces of material regions 21. In the low temperature areas, which are positively associated with the higher temperature range, it is therefore the formation of tensile stresses.
  • the relatively cool material regions 21 in a conventional heat shield element would be subject to stress due to their relatively low thermal expansion from the hot central region 19 experiencing greater thermal expansion, and could crack when exceeding the material strength.
  • the cracks would emanate from the edges of the heat shield and extend toward the heat shield interior. Such cracking can reduce the life of a heat shield element.
  • the stresses described with reference to a conventional heat shield element are reduced, in particular in the cool peripheral regions, since the material regions 21 have a higher thermal expansion coefficient than the central material region 19.
  • the higher temperature of the central material region 19 is thus compensated by the larger thermal expansion coefficient of the material regions 21 in the region of the peripheral surfaces 17.
  • the thermal expansion coefficients of the material regions 19 and 21 and the extent of these material regions in the material volume of the heat shield element 10 can be numerically optimized in such a way that the stresses in the heat shield element 10 are minimized.
  • the extent of the material regions 21 can be determined with relatively high coefficients of thermal expansion, by first performing a calculation of the temperature field which occurs in the desired operating state under corresponding boundary conditions in the heat shield element. Subsequently, on the basis of this result, the size of the regions 21 for the selected coefficient of thermal expansion can be adjusted such that a minimization of the stresses in the heat shield element 10 takes place.
  • the thermal expansion coefficients and the expansions of the material regions can be optimized simultaneously. However, it is also possible to specify the extent, for example, of the circumferential material regions 21 and to find suitable thermal expansion coefficients by means of an optimization.
  • material regions 21 are provided with an increased thermal expansion coefficient and reduced thermal conductivity compared with the central material region 19.
  • the heat shield element 10 according to the invention can also have material regions 20 with a thermal expansion coefficient increased compared to the central material region 19 and reduced thermal conductivity in the region of the second peripheral surfaces, ie in the region of the circumferential surfaces provided with grooves 18 (FIG.
  • a second embodiment of the heat shield element according to the invention is shown in section in FIG.
  • the section runs along the line A-A shown in FIG. Accordingly, the hot side 113, the cold side 115 and the groove-free peripheral surfaces 117 of the heat shield element 110 can be seen.
  • the heat shield element 110 has on the hot side a material region 119 with a relatively low coefficient of thermal expansion and a relatively low thermal conductivity. On the cold side, it has a material region 121 with respect to the hot-side material region 119 increased thermal expansion coefficient, increased thermal conductivity and increased mechanical strength.
  • This embodiment takes into account the fact that the hot side 113 of a heat shield element during operation of a combustion chamber is exposed to a higher temperature than the generally cooled cold side 115. In the heat shield element 110, therefore, a temperature gradient forms from the hot side 113 to the cold side 115 out. The lower temperature of the cold-side material region 121 is then compensated during operation of the combustion chamber by its thermal expansion coefficient, which is higher in comparison with the hot-side material region 119. Stress due to the temperature gradient can therefore be reliably avoided.
  • a third embodiment of the heat shield element according to the invention is shown in Figure 4 in section.
  • the section runs along the line AA shown in FIG. Accordingly, the cold side 213, the hot side 215 and the groove-free peripheral surfaces 217 of the heat shield element 210 can be seen.
  • the heat shield element 210 has a first, hot-side material region 219 having a first coefficient of thermal expansion, peripheral second material regions 221 having a second thermal expansion coefficient, and a cold-side material region 223 having a third coefficient of thermal expansion. there the second and third thermal expansion coefficients may also be identical.
  • stresses that occur due to temperature gradients in the interior of the heat shield element 210 can be reliably minimized.
  • the regions with different coefficients of expansion should preferably not be in the form of sharp boundaries of material properties, but rather in the form of smooth transitions of the material properties, the risk of destruction of the heat shield during the manufacturing process, especially during sintering, at elevated, substantially homogeneous temperature takes place, to avoid.
  • FIG. 5a shows a first step of the production method
  • FIG. 5b shows a second step.
  • the method comprises casting material mixtures into a mold 340 so as to form a green body, and then sintering the greenware to complete the ceramic heat shield element.
  • FIGS. 5a and 5b The casting of the material mixtures is shown in FIGS. 5a and 5b.
  • a material mixture 321 having a first composition is poured into the mold 340 (FIG. 5a).
  • a material mixture 319 having a second composition is poured over the first material mixture 321.
  • the consistency of the material mixtures is such that no complete mixing of the two material mixtures occurs. However, mixing at the interface 320 is desirable.
  • compositions of the material mixtures 319 and 321 are selected such that the material mixture 319 has a lower coefficient of thermal expansion after the sintering than the material mixture 321.
  • the casting of the heat shield element takes place when the casting mold is stationary, i. that part of the mold which forms the cold side and that part of the mold which forms the hot side are side walls of the mold, whereas the bottom of the mold is a part of the mold which forms one of the peripheral surfaces of the heat shield element.
  • Fig. 5c shows a standing mold in plan view.
  • templates 346, 347 may serve to separate different portions 348, 349, 350 of the mold 345 from each other.
  • different material mixtures are poured.
  • three different material mixtures can be used with the mold of FIG.
  • the templates are removed to effect bonding of the cast material mixes. Again, the consistency of the material mixtures is selected such that in the region of the interfaces after the removal of the templates, a mixing of the material mixtures.
  • FIGS. 6a and 6b A second manufacturing method for heat shield elements according to the invention will now be described with reference to FIGS. 6a and 6b.
  • a material mixture 419 is placed in a mold 440, 450 and then pressed.
  • the result is a green body 410 of the heat shield element.
  • This green compact 410 is shown in FIG. 6b. It can be seen the hot side 413, the cold side 415 and the groove-free peripheral surfaces 417 of the green body 410.
  • the green body 410 is impregnated with a liquid which influences the sintering process.
  • the liquid is selected such that the impregnated regions 421 after sintering have a higher coefficient of thermal expansion than the non-impregnated region 419.
  • the grooved circumferential surfaces of the green body 410 may also be soaked to increase the thermal expansion coefficient of the respective regions.
  • the result of the method described with reference to FIGS. 6a and 6b is a heat shield element as shown in FIG.
  • the mold can be filled horizontally or vertically and the filling of material mixtures done using templates.
  • the mold can thereby - as well as the mold when pouring a heat shield element - are placed or filled at any angle.
  • FIG. 3 Although the manufacture of a heat shield element as shown in FIG. 3 is described by way of example with reference to FIGS. 5a and 5b, it is also possible with the same method to use heat shield elements as shown in FIGS 2 or 4 are shown to produce. The same applies to the method which has been described with reference to FIGS. 6a and 6b. Even with this method, it is not only possible to produce a heat shield element as described with reference to FIG. Rather, it is also possible with this method to produce heat shield elements, as shown in Figures 3 or 4.
EP04028445A 2004-12-01 2004-12-01 Elément de bouclier thermique, son procédé de fabrication, bouclier thermique et chambre de combustion Withdrawn EP1666797A1 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
EP04028445A EP1666797A1 (fr) 2004-12-01 2004-12-01 Elément de bouclier thermique, son procédé de fabrication, bouclier thermique et chambre de combustion
EP05803716A EP1817147A1 (fr) 2004-12-01 2005-11-21 Element ecran thermique, procede et moule pour sa fabrication, revetement a gaz chaud et chambre de combustion
PCT/EP2005/012447 WO2006058629A1 (fr) 2004-12-01 2005-11-21 Element ecran thermique, procede et moule pour sa fabrication, revetement a gaz chaud et chambre de combustion
US11/792,068 US8522559B2 (en) 2004-12-01 2005-11-21 Heat shield element, method and mold for the production thereof, hot-gas lining and combustion chamber
US11/792,130 US20080104963A1 (en) 2004-12-01 2005-11-22 Heat Shield Element, Method for Its Production, Hot Gas Lining, and Combustion Chamber
PCT/EP2005/056127 WO2006058851A1 (fr) 2004-12-01 2005-11-22 Element ecran thermique, son procede de production, revetement gaz chaud et chambre de combustion
EP05811090.9A EP1817528B1 (fr) 2004-12-01 2005-11-22 Procédé de production d'un élément d'écran thermique
US12/774,049 US9314939B2 (en) 2004-12-01 2010-05-05 Heat shield element, method and mold for the production thereof, hot-gas lining and combustion chamber
US13/477,354 US20120228468A1 (en) 2004-12-01 2012-05-22 Heat Shield Element, Method and Mold for the Production Thereof, Hot-Gas Lining and Combustion Chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04028445A EP1666797A1 (fr) 2004-12-01 2004-12-01 Elément de bouclier thermique, son procédé de fabrication, bouclier thermique et chambre de combustion

Publications (1)

Publication Number Publication Date
EP1666797A1 true EP1666797A1 (fr) 2006-06-07

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EP04028445A Withdrawn EP1666797A1 (fr) 2004-12-01 2004-12-01 Elément de bouclier thermique, son procédé de fabrication, bouclier thermique et chambre de combustion
EP05811090.9A Not-in-force EP1817528B1 (fr) 2004-12-01 2005-11-22 Procédé de production d'un élément d'écran thermique

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05811090.9A Not-in-force EP1817528B1 (fr) 2004-12-01 2005-11-22 Procédé de production d'un élément d'écran thermique

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US (1) US20080104963A1 (fr)
EP (2) EP1666797A1 (fr)
WO (1) WO2006058851A1 (fr)

Families Citing this family (8)

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Publication number Priority date Publication date Assignee Title
EP2428647B1 (fr) * 2010-09-08 2018-07-11 Ansaldo Energia IP UK Limited Zone de transition pour une chambre de combustion d'une turbine à gaz
DE102012201650A1 (de) 2012-02-03 2013-08-08 Sgl Carbon Se Hitzeschild mit äußerer Faserwicklung
US9423129B2 (en) 2013-03-15 2016-08-23 Rolls-Royce Corporation Shell and tiled liner arrangement for a combustor
EP2986916A1 (fr) * 2013-05-21 2016-02-24 Siemens Aktiengesellschaft Carreau en faïence pour bouclier thermique de chambre de combustion
US10935235B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine 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
US10830433B2 (en) 2016-11-10 2020-11-10 Raytheon Technologies Corporation Axial non-linear interface for combustor liner panels in a gas turbine combustor
US10935236B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor

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US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4838030A (en) * 1987-08-06 1989-06-13 Avco Corporation Combustion chamber liner having failure activated cooling and dectection system
WO1992009850A1 (fr) * 1990-11-29 1992-06-11 Siemens Aktiengesellschaft Ecran thermique en ceramique monte sur une structure portante
EP1302723A1 (fr) * 2001-10-15 2003-04-16 Siemens Aktiengesellschaft Revêtement pour parois intérieures de chambre de combustion

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US3174444A (en) * 1964-01-27 1965-03-23 Harbison Walker Refractories Suspended hot patch brick
GB1272591A (en) * 1968-03-28 1972-05-03 Delaney Gallay Ltd Improvements in and relating to heat shields
FR2664585B1 (fr) * 1990-07-13 1993-08-06 Europ Propulsion Structures refractaires refroidies et procede pour leur fabrication.
US6733907B2 (en) * 1998-03-27 2004-05-11 Siemens Westinghouse Power Corporation Hybrid ceramic material composed of insulating and structural ceramic layers
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EP1191285A1 (fr) * 2000-09-22 2002-03-27 Siemens Aktiengesellschaft Bouclier thérmique , chambre de combustion avec garnissage interne et turbine à gaz
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US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4838030A (en) * 1987-08-06 1989-06-13 Avco Corporation Combustion chamber liner having failure activated cooling and dectection system
WO1992009850A1 (fr) * 1990-11-29 1992-06-11 Siemens Aktiengesellschaft Ecran thermique en ceramique monte sur une structure portante
EP1302723A1 (fr) * 2001-10-15 2003-04-16 Siemens Aktiengesellschaft Revêtement pour parois intérieures de chambre de combustion

Also Published As

Publication number Publication date
EP1817528A1 (fr) 2007-08-15
WO2006058851A1 (fr) 2006-06-08
EP1817528B1 (fr) 2016-10-19
US20080104963A1 (en) 2008-05-08

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