EP3237803A2 - Supporting member for thermoinsulating tiles of gas turbine combustion chambers - Google Patents

Supporting member for thermoinsulating tiles of gas turbine combustion chambers

Info

Publication number
EP3237803A2
EP3237803A2 EP15830868.4A EP15830868A EP3237803A2 EP 3237803 A2 EP3237803 A2 EP 3237803A2 EP 15830868 A EP15830868 A EP 15830868A EP 3237803 A2 EP3237803 A2 EP 3237803A2
Authority
EP
European Patent Office
Prior art keywords
weight
supporting member
member according
thermoinsulating
coupling head
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
EP15830868.4A
Other languages
German (de)
French (fr)
Other versions
EP3237803B1 (en
Inventor
Francesco Fusi
Alberto ZERAH
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.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia SpA
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 Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Publication of EP3237803A2 publication Critical patent/EP3237803A2/en
Application granted granted Critical
Publication of EP3237803B1 publication Critical patent/EP3237803B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23M5/04—Supports for linings

Definitions

  • the present invention relates to a supporting member for thermoinsulating tiles of gas turbine combustion chambers.
  • thermoinsulating coating generally consists of a plurality of tiles of refractory material arranged in contiguous rows on the inner surface of the casing of the combustion chamber, so as to define a substantially continuous surface.
  • the tiles are arranged on circumferences around the rotor axis. Normally, the tiles are fastened to the casing by supporting members which couple to seats on the sides of the tiles themselves.
  • the supporting members comprise a plate having, at one end, a coupling head which couples to a respective tile and, at the opposite end, a connection area that is connected to a guide on the casing.
  • the supporting members are elastic and, once the tiles are placed in the seat, are loaded to ensure a stable mounting.
  • connection elements are subject to important wear because of the hot gases that penetrate between adjacent tiles of the same row or of contiguous rows.
  • the gaps between adjacent tiles are not in fact sealed and hot gases may permeate, reaching the supporting members.
  • the coupling heads of the supporting members tend to oxidize and may undergo premature breaking.
  • the excessively high temperature may cause phenomena of hot viscous creeping and relaxation of the material forming the supporting members, which tend to lose the loading state.
  • the object of the present invention is therefore to provide a supporting member for thermoinsulating tiles of gas turbine combustion chambers, which allows to overcome or at least reduce the limitations described above and, in particular, allows to mitigate the harmful effects of leakage of hot gases from the combustion chamber.
  • a supporting member for thermoinsulating tiles of gas turbine combustion chambers as defined in claim 1 is provided.
  • FIG. 1 is a side view, sectioned along a vertical axial plane, of a combustion chamber for gas turbines;
  • FIG. 2 is a front view of the combustion chamber of Figure 1, sectioned along the plane II-II of Figure 1, with parts removed for clarity;
  • FIG. 3 shows an enlarged detail of the combustion chamber of Figure 1, partly exploded and with parts removed for clarity;
  • FIG. 4 is a rear perspective view of a supporting member for thermoinsulating tiles of gas turbine combustion chambers according to an embodiment of the present invention
  • FIG. 5 is a front perspective view of the supporting member of Figure 4;
  • - Figure 6 shows an enlarged detail of the supporting member of Figure 4;
  • FIG. 7 is a rear perspective view of a supporting member for thermoinsulating tiles of gas turbine combustion chambers according to a different embodiment of the present invention.
  • FIGS 1 and 2 illustrate a combustion chamber 1 of a gas turbine (not fully shown) .
  • the combustion chamber 1 comprises a toroidal casing 2 extending around an axis A and is provided with a thermoinsulating coating 3 that covers internally the casing 2.
  • the thermoinsulating coating 3 comprises a plurality of thermoinsulating tiles 4 of refractory material, arranged in adjacent rows, along circumferences, around the axis A of the combustion chamber 1.
  • thermoinsulating tiles 4 are fastened to the casing 2 by supporting members 5. More in detail, the thermoinsulating tiles 4 have a quadrangular shape and have, on opposite sides, respective grooves 7 and ribs 8 for coupling with the supporting members 5.
  • the supporting members 5 engage circumferential guides 9, which are formed on an inner face of the casing 2 and extend around the axis A.
  • thermoinsulating tile 4 is arranged in the seat and the supporting members 5 for the other side of the insulating tile 4 are fitted.
  • FIG. 4-7 One of the supporting members 5 is illustrated with more detail in Figures 4-7. It is understood that the supporting members can be made all in the same way or, according to necessity, some supporting members may have a different structure .
  • the supporting member 5 comprises an elongated plate 10, having a coupling head 12 at a first end.
  • the elongated plate 10 and the coupling head 12 are made en bloc.
  • the coupling head 12 is shaped to couple with a rib 8 of one of the thermoinsulating tiles 4. More precisely, the coupling head 12 is T-shaped, with arms extending transversely to the elongated plate 10, and is bent to form a coupling seat 13 for the thermoinsulating tiles 4.
  • the coupling head has an inner coupling surface 12a and an outer surface 12b.
  • a second end of the elongated plate 11 is provided with a connection area 15, formed so as to engage one of the circumferential guides 9 of the casing 2 of the combustion chamber 1.
  • the supporting member 5 further comprises a leaf spring 17, superimposed in longitudinal direction to the elongated plate 10 and fastened thereto, for example by spot welding.
  • the leaf spring 17 is connected for being loaded by the bending of the elongated plate 10, for example when the supporting member 5 is mounted to connect one of the thermoinsulating tiles 4 to the casing 2.
  • the elongated plate 10, including the coupling head 12, and the leaf spring 17 are made of the same material, for example a J' phase precipitation hardening nickel alloy.
  • the alloy contains molybdenum, which helps to increase the alloy heat characteristics by means of the hardening mechanism by solid solution.
  • the composition of the alloy forming the elongated plate 10 and the leaf spring 17, expressed in percentage by weight may be the following:
  • the outer surface 12b of the coupling head 12 is coated with a protective coating 20, which comprises a protective metal layer 21 having a thickness comprised between 17 ⁇ and 270 ⁇ and a thermal barrier layer 22 of ceramic material having a thickness comprised between 350 ⁇ 550 ⁇ .
  • the protective metal layer 21 is applied directly to the outer surface 12 of the coupling head and is made of a MCrAlY alloy, where M is cobalt or nickel, or a combination of cobalt and nickel .
  • the MCrAlY alloy may have a composition selected from the following:
  • Co between 21% and 23% by weight, Cr between 16% and 18% by weight, Al between 12% and 13% by weight, Y between 0.5% and 0.7% by weight, Si between 0.3% and 0.5% by weight, Hf between 0.2% and 0.3% by weight, balance Ni;
  • the protective metal layer 21 may be deposited by a HVOF (High Velocity Oxygen Fuel), LPPS (Low-Pressure Plasma Spray), VPS (Vacuum Plasma Spray) or APS (Air Plasma Spray) process and has the dual function of preventing the oxidation of the coupling head 12, which is the hottest part of the supporting member 1, and to allow the anchorage of the thermal barrier layer 22.
  • HVOF High Velocity Oxygen Fuel
  • LPPS Low-Pressure Plasma Spray
  • VPS Vauum Plasma Spray
  • APS Air Plasma Spray
  • the protective metal layer 21 can then accommodate the different expansion of the elongated plate 11 and of the thermal barrier layer 22 and avoid the detachment of the latter.
  • the thermal barrier layer 22 is applied to the protective metal layer and is made of a ceramic material.
  • the thermal barrier layer 22 is a single layer of homogeneous ceramic material and has an exposed surface 22a.
  • the thermal barrier layer 22 is made of yttria stabilized zirconia.
  • the thermal barrier layer 22 may contain:
  • the thermal barrier layer 22 may be obtained by APS (Air Plasma Spray) deposition. Thanks to the reflective properties of the ceramic material, the exposed surface 22a of the thermal barrier layer 22 allows to keep the temperature of the coupling head within values for which the phenomena of hot viscous creeping and relaxation will not occur, or are restricted. The effect is further favored by the low thermal conductivity of the ceramic material.
  • the protective coating comprises only the protective metal layer 21 made of MCrAlY alloy.
  • the protective metal layer 21, even in the absence of ceramic coating, is anyway able to effectively prevent the oxidation of the coupling head 12 and thus to substantially reduce the wear of the component, to the benefit of its useful life.
  • This solution can be used for example for portions of the combustion chamber 2 where the high temperature is less, while elsewhere the supporting members 5 of the Figures 4-6 are used .
  • the protective coating can cover entirely or only in part, the coupling head 12, or extend to further portions of the elongated plate 11, according to specifications .

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

A supporting member for thermoinsulating tiles of gas turbine combustion chambers comprises an elongated plate (10), having a coupling head (12) at a first end, the coupling head (12) being structured to couple with a thermoinsulating tile (4) and having an inner coupling surface (12a) and an outer surface (12b). The outer surface (12b) of the coupling head (12) is at least partly coated with a protective coating (20).

Description

" SUPPORTING MEMBER FOR THERMOINSULATING TILES OF GAS TURBINE
COMBUSTION CHAMBERS "
TECHNICAL FIELD
The present invention relates to a supporting member for thermoinsulating tiles of gas turbine combustion chambers.
BACKGROUND ART
As known, the combustion chamber of a gas turbine must be internally provided with a thermoinsulating coating of refractory material, due to the high temperatures reached during the machine operation. The thermoinsulating coating generally consists of a plurality of tiles of refractory material arranged in contiguous rows on the inner surface of the casing of the combustion chamber, so as to define a substantially continuous surface. In the combustion chambers of toroidal type, the tiles are arranged on circumferences around the rotor axis. Normally, the tiles are fastened to the casing by supporting members which couple to seats on the sides of the tiles themselves. More precisely, the supporting members comprise a plate having, at one end, a coupling head which couples to a respective tile and, at the opposite end, a connection area that is connected to a guide on the casing. The supporting members are elastic and, once the tiles are placed in the seat, are loaded to ensure a stable mounting.
The connection elements are subject to important wear because of the hot gases that penetrate between adjacent tiles of the same row or of contiguous rows. The gaps between adjacent tiles are not in fact sealed and hot gases may permeate, reaching the supporting members. In particular, the coupling heads of the supporting members tend to oxidize and may undergo premature breaking. Also, the excessively high temperature may cause phenomena of hot viscous creeping and relaxation of the material forming the supporting members, which tend to lose the loading state.
DISCLOSURE OF INVENTION
The object of the present invention is therefore to provide a supporting member for thermoinsulating tiles of gas turbine combustion chambers, which allows to overcome or at least reduce the limitations described above and, in particular, allows to mitigate the harmful effects of leakage of hot gases from the combustion chamber. According to the present invention, a supporting member for thermoinsulating tiles of gas turbine combustion chambers as defined in claim 1 is provided.
BRIEF DESCRIPTION OF THE DRAWINGS
The present invention will now be described with reference to the accompanying drawings, which illustrate some examples of non-limiting embodiments, wherein:
- Figure 1 is a side view, sectioned along a vertical axial plane, of a combustion chamber for gas turbines;
- Figure 2 is a front view of the combustion chamber of Figure 1, sectioned along the plane II-II of Figure 1, with parts removed for clarity;
- Figure 3 shows an enlarged detail of the combustion chamber of Figure 1, partly exploded and with parts removed for clarity;
- Figure 4 is a rear perspective view of a supporting member for thermoinsulating tiles of gas turbine combustion chambers according to an embodiment of the present invention;
- Figure 5 is a front perspective view of the supporting member of Figure 4; - Figure 6 shows an enlarged detail of the supporting member of Figure 4; and
- Figure 7 is a rear perspective view of a supporting member for thermoinsulating tiles of gas turbine combustion chambers according to a different embodiment of the present invention.
BEST MODE FOR CARRYING OUT THE INVENTION
Figures 1 and 2 illustrate a combustion chamber 1 of a gas turbine (not fully shown) . The combustion chamber 1 comprises a toroidal casing 2 extending around an axis A and is provided with a thermoinsulating coating 3 that covers internally the casing 2. The thermoinsulating coating 3 comprises a plurality of thermoinsulating tiles 4 of refractory material, arranged in adjacent rows, along circumferences, around the axis A of the combustion chamber 1.
With reference to Figure 3, the thermoinsulating tiles 4 are fastened to the casing 2 by supporting members 5. More in detail, the thermoinsulating tiles 4 have a quadrangular shape and have, on opposite sides, respective grooves 7 and ribs 8 for coupling with the supporting members 5.
The supporting members 5 engage circumferential guides 9, which are formed on an inner face of the casing 2 and extend around the axis A.
Once the supporting members 5 for a side of a thermoinsulating tile 4 have been housed in the circumferential guides 9 and fastened to the casing 2 by grub screws 6, the thermoinsulating tile 4 is arranged in the seat and the supporting members 5 for the other side of the insulating tile 4 are fitted.
One of the supporting members 5 is illustrated with more detail in Figures 4-7. It is understood that the supporting members can be made all in the same way or, according to necessity, some supporting members may have a different structure .
The supporting member 5 comprises an elongated plate 10, having a coupling head 12 at a first end. In one embodiment, the elongated plate 10 and the coupling head 12 are made en bloc. The coupling head 12 is shaped to couple with a rib 8 of one of the thermoinsulating tiles 4. More precisely, the coupling head 12 is T-shaped, with arms extending transversely to the elongated plate 10, and is bent to form a coupling seat 13 for the thermoinsulating tiles 4. In addition, the coupling head has an inner coupling surface 12a and an outer surface 12b. A second end of the elongated plate 11 is provided with a connection area 15, formed so as to engage one of the circumferential guides 9 of the casing 2 of the combustion chamber 1. The supporting member 5 further comprises a leaf spring 17, superimposed in longitudinal direction to the elongated plate 10 and fastened thereto, for example by spot welding. The leaf spring 17 is connected for being loaded by the bending of the elongated plate 10, for example when the supporting member 5 is mounted to connect one of the thermoinsulating tiles 4 to the casing 2.
In a non-limiting embodiment, the elongated plate 10, including the coupling head 12, and the leaf spring 17 are made of the same material, for example a J' phase precipitation hardening nickel alloy. In one embodiment, the alloy contains molybdenum, which helps to increase the alloy heat characteristics by means of the hardening mechanism by solid solution. By way of non-limiting example, the composition of the alloy forming the elongated plate 10 and the leaf spring 17, expressed in percentage by weight, may be the following:
Ni 57% by weight
Cr 20% by weight
Co 10% by weight
Mo 8.5% by weight
Ti 2.1% by weight
Al 1.5% by weight
Fe 1.5% by weight
Mn 0.3% by weight
Si 0.15% by weight
C 0,06% by weight
B 0.005% by weight Once the leaf spring 17 has been welded to the elongated plate 10, the two together may be subjected to aging treatment, in order to precipitate the J' phase which strengthens the alloy.
The outer surface 12b of the coupling head 12 is coated with a protective coating 20, which comprises a protective metal layer 21 having a thickness comprised between 17 μπι and 270 μπι and a thermal barrier layer 22 of ceramic material having a thickness comprised between 350 μπι 550 μπι. The protective metal layer 21 is applied directly to the outer surface 12 of the coupling head and is made of a MCrAlY alloy, where M is cobalt or nickel, or a combination of cobalt and nickel . For example, the MCrAlY alloy may have a composition selected from the following:
Ni between 29% and 31% by weight, Cr between 27% and 29% by weight, Al between 7.5% and 7.8% by weight, Y between 0.5% and 0.7% by weight, Si between 0.3% and 0.7% by weight, balance Co; Ni between 30% and 37% by weight, Cr between 18% and 25% by weight, Al between 7% and 9% by weight, Y between 0.1% and 0.7% by weight, balance Co;
Co between 21% and 23% by weight, Cr between 16% and 18% by weight, Al between 12% and 13% by weight, Y between 0.5% and 0.7% by weight, Si between 0.3% and 0.5% by weight, Hf between 0.2% and 0.3% by weight, balance Ni;
Co between 11% and 13% by weight, Cr between 20% and 22% by weight, Al between 10.5% and 11.5% by weight, Y between 0.3% and 0.5% by weight, Re between 1.5% and 2.5% by weight, balance Ni;
Co between 24% and 26% by weight, Cr between 16% and 18% by weight, Al between 9.5% and 11% by weight, Y between 0.3% and 0.5% by weight, Re between 1% and 1.8% by weight, balance Ni; Co between 23% and 25% by weight, Cr between 16% and 18% by weight, Al between 9.5% and 11% by weight, Y between 0.3% and 0.5% by weight, Ir between 1.1% and 1.5% by weight, balance Ni . The protective metal layer 21 may be deposited by a HVOF (High Velocity Oxygen Fuel), LPPS (Low-Pressure Plasma Spray), VPS (Vacuum Plasma Spray) or APS (Air Plasma Spray) process and has the dual function of preventing the oxidation of the coupling head 12, which is the hottest part of the supporting member 1, and to allow the anchorage of the thermal barrier layer 22. As a result of its composition, in fact, the MCrAlY alloy of the protective metal layer 21 has intermediate thermal expansion coefficient between the J' phase precipitation hardening nickel alloy of the elongated plate 11 and the ceramic material of the thermal barrier layer 22. The protective metal layer 21 can then accommodate the different expansion of the elongated plate 11 and of the thermal barrier layer 22 and avoid the detachment of the latter. The thermal barrier layer 22 is applied to the protective metal layer and is made of a ceramic material. In one embodiment, the thermal barrier layer 22 is a single layer of homogeneous ceramic material and has an exposed surface 22a. In addition, the thermal barrier layer 22 is made of yttria stabilized zirconia. For example, the thermal barrier layer 22 may contain:
Y203 from 6.0% to 8.0% by weight
Hf02 <2.50% by weight
MgO <0.20% by weight
U and Th <0.05% by weight
CaO <0.20% by weight
A1203 <0.20% by weight
Fe203 <0.20% by weight
Si02 <0.70% by weight
Ti02 <0.40% by weight
Zr02 balance .
The thermal barrier layer 22 may be obtained by APS (Air Plasma Spray) deposition. Thanks to the reflective properties of the ceramic material, the exposed surface 22a of the thermal barrier layer 22 allows to keep the temperature of the coupling head within values for which the phenomena of hot viscous creeping and relaxation will not occur, or are restricted. The effect is further favored by the low thermal conductivity of the ceramic material.
According to a different embodiment of the invention, illustrated in figure 7, in a supporting member 105, the protective coating comprises only the protective metal layer 21 made of MCrAlY alloy. The protective metal layer 21, even in the absence of ceramic coating, is anyway able to effectively prevent the oxidation of the coupling head 12 and thus to substantially reduce the wear of the component, to the benefit of its useful life. This solution can be used for example for portions of the combustion chamber 2 where the high temperature is less, while elsewhere the supporting members 5 of the Figures 4-6 are used .
Finally, it is evident that to the supporting member described modifications and variations can be made, without departing from the scope of the present invention, as defined in the appended claims.
In particular, the protective coating can cover entirely or only in part, the coupling head 12, or extend to further portions of the elongated plate 11, according to specifications .

Claims

1. A supporting member for thermoinsulating tiles of gas turbine combustion chambers, comprising an elongated plate (11), having a coupling head (12) at a first end, the coupling head (12) being structured to couple with a thermoinsulating tile (4) and having an inner coupling surface (12a) and an outer surface (12b);
wherein the elongated plate (11) and the coupling head (12) are made of J' phase precipitation hardening nickel alloy;
and wherein the outer surface (12b) of the coupling head (12) is at least partly coated with a protective coating (20) comprising :
a protective metal layer (21) made of MCrAlY alloy applied to the coupling head (12), M being cobalt or nickel, or a combination of cobalt and nickel; and
a thermal barrier layer (22), applied to the protective metal layer (21) and made of a ceramic material.
2. The supporting member according to claim 1, wherein the MCrAlY alloy has a composition selected from the group consisting of:
Ni between 29% and 31% by weight, Cr between 27% and 29% by weight, Al between 7.5% and 7.8% by weight, Y between 0.5% and 0.7% by weight, Si between 0.3% and 0.7% by weight;
Ni between 30% and 37% by weight, Cr between 18% and 25% by weight, Al between 7% and 9% by weight, Y between 0.1% and 0.7% by weight ;
Co between 21% and 23% by weight, Cr between 16% and 18% by weight, Al between 12% and 13% by weight, Y between 0.5% and 0.7% by weight, Si between 0.3% and 0.5% by weight, Hf between 0.2% and 0.3% by weight;
Co between 11% and 13% by weight, Cr between 20% and 22% by weight, Al between 10.5% and 11.5% by weight, Y between 0.3% and 0.5% by weight, Re between 1.5% and 2.5% by weight; Co between 24% and 26% by weight, Cr between 16% and 18% by weight, Al between 9.5% and 11% by weight, Y between 0.3% and 0.5% by weight, Re between 1% and 1.8% by weight;
Co between 23% and 25% by weight, Cr between 16% and 18% by weight, Al between 9.5% and 11% by weight, Y between 0.3% and 0.5% by weight, Ir between 1.1% and 1.5% by weight, balance Ni .
3. The supporting member according to any one of the preceding claims, wherein the thermal barrier layer (22) is a single layer of homogeneous ceramic material and has an exposed surface (22a) .
4. The supporting member according to any one of the preceding claims, wherein the protective metal layer (21) has intermediate thermal expansion coefficient between the coupling head (12) and the thermal barrier layer (22) .
5. The supporting member according to any one of the preceding claims, wherein the thermal barrier layer (22) is made of yttria stabilized zirconia.
6. The supporting member according to any one of the preceding claims, wherein the thermal barrier layer (22) contains:
Y203 from 6.0% to 8.0% by weight
Hf02 < 2.50% by weight
MgO < 0.20% by weight
U and Th < 0.05% by weight
CaO < 0.20% by weight
A1203 < 0.20% by weight
Fe203 < 0.20% by weight
Si02 < 0.70% by weight
Ti02 < 0.40% by weight
ZrC>2 balance.
7. The supporting member according to any one of the preceding claims, wherein the J' phase precipitation hardening nickel alloy contains molybdenum.
8. The supporting member according to claim 7, wherein the J' phase precipitation hardening nickel alloy contains:
Ni 57% by weight
Cr 20% by weight
Co 10% by weight
Mo 8.5% by weight
Ti 2.1% by weight
Al 1.5% by weight
Fe 1.5% by weight
Mn 0.3% by weight
Si 0.15% by weight
C 0.06% by weight
B 0.005% by weight
9. The supporting member according to any one of the preceding claims, comprising a leaf spring (17) fastened to the elongated plate (11) and superimposed in the longitudinal direction .
10. The supporting member according to claim 9, wherein the elongated plate (11) and the leaf spring (17) are made of the same material.
11. The supporting member according to any one of the preceding claims, wherein the coupling head (12) extends transverse to the elongated plate (11) and is bent to form a coupling seat (13) for a thermoinsulating tile (4) .
12. The supporting member according to any one of the preceding claims, wherein a second end of the elongated plate (11) is provided with a connection area (15), for connection to a guide (9) of a casing (2) of a combustion chamber (1) of a gas turbine.
13. Gas turbine comprising:
a combustion chamber (1) ;
a thermoinsulating coating (3), including a plurality of thermoinsulating tiles (4) fastened to a casing (2) of the combustion chamber (1);
at least one supporting member (5; 105) according to any one of the preceding claims, connecting a respective thermoinsulating tile (4) to the casing (2) of the combustion chamber (1) .
EP15830868.4A 2014-12-24 2015-12-24 Supporting member for thermoinsulating tiles of gas turbine combustion chambers Active EP3237803B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITMI20142253 2014-12-24
PCT/IB2015/059979 WO2016103231A2 (en) 2014-12-24 2015-12-24 Supporting member for thermoinsulating tiles of gas turbine combustion chambers

Publications (2)

Publication Number Publication Date
EP3237803A2 true EP3237803A2 (en) 2017-11-01
EP3237803B1 EP3237803B1 (en) 2019-09-25

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Country Status (3)

Country Link
EP (1) EP3237803B1 (en)
CN (1) CN107208892B (en)
WO (1) WO2016103231A2 (en)

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Publication number Priority date Publication date Assignee Title
CN108611588B (en) * 2018-07-18 2020-05-19 中国科学院上海硅酸盐研究所 A kind of alloy coating resistant to high temperature oxidation and corrosion of sulfur and chlorine and preparation method thereof
CN112197297B (en) * 2020-11-02 2025-03-21 上海电气燃气轮机有限公司 Mounting member for covering a heat insulation layer on a combustion chamber shell and combustion chamber
CN115962487B (en) * 2022-12-19 2025-09-23 上海电气燃气轮机有限公司 A connection device for heat shield in combustion chamber of gas turbine and heat shield
CN116573925B (en) * 2023-05-18 2024-05-10 中国科学院过程工程研究所 A ceramic thermal insulation tile and its preparation method and application

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Publication number Priority date Publication date Assignee Title
US4419416A (en) * 1981-08-05 1983-12-06 United Technologies Corporation Overlay coatings for superalloys
US5273712A (en) * 1989-08-10 1993-12-28 Siemens Aktiengesellschaft Highly corrosion and/or oxidation-resistant protective coating containing rhenium
JP4264926B2 (en) * 2002-07-05 2009-05-20 日本発條株式会社 Method for producing precipitation-strengthened Co-Ni heat resistant alloy
US7094450B2 (en) * 2003-04-30 2006-08-22 General Electric Company Method for applying or repairing thermal barrier coatings
ES2378375T3 (en) * 2005-02-07 2012-04-11 Siemens Aktiengesellschaft Thermal display
EP1715248A1 (en) * 2005-04-19 2006-10-25 Siemens Aktiengesellschaft Holding element and heatshield member for a heatshield and combustion chamber including said heatshield

Also Published As

Publication number Publication date
CN107208892A (en) 2017-09-26
EP3237803B1 (en) 2019-09-25
CN107208892B (en) 2019-11-26
WO2016103231A3 (en) 2016-08-18
WO2016103231A2 (en) 2016-06-30

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