WO2016103231A2 - Élément de support pour carreaux d'isolation thermique de chambres de combustion de turbine à gaz - Google Patents

Élément de support pour carreaux d'isolation thermique de chambres de combustion de turbine à gaz Download PDF

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Publication number
WO2016103231A2
WO2016103231A2 PCT/IB2015/059979 IB2015059979W WO2016103231A2 WO 2016103231 A2 WO2016103231 A2 WO 2016103231A2 IB 2015059979 W IB2015059979 W IB 2015059979W WO 2016103231 A2 WO2016103231 A2 WO 2016103231A2
Authority
WO
WIPO (PCT)
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.)
Ceased
Application number
PCT/IB2015/059979
Other languages
English (en)
Other versions
WO2016103231A3 (fr
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
ASEN Ansaldo Sviluppo Energia SRL
Original Assignee
Ansaldo Energia SpA
ASEN Ansaldo Sviluppo Energia SRL
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, ASEN Ansaldo Sviluppo Energia SRL filed Critical Ansaldo Energia SpA
Priority to EP15830868.4A priority Critical patent/EP3237803B1/fr
Priority to CN201580070456.8A priority patent/CN107208892B/zh
Publication of WO2016103231A2 publication Critical patent/WO2016103231A2/fr
Publication of WO2016103231A3 publication Critical patent/WO2016103231A3/fr
Anticipated expiration legal-status Critical
Ceased 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
    • F23R3/007—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

L'invention concerne un élément de support pour des carreaux d'isolation thermique de chambres de combustion de turbine à gaz comprenant une plaque allongée (10) présentant une tête d'accouplement (12) au niveau d'une première extrémité, la tête d'accouplement (12) étant structurée pour s'accoupler avec un carreau d'isolation thermique (4) et présentant une surface d'accouplement interne (12a) et une surface externe (12b). La surface externe (12b) de la tête d'accouplement (12) est au moins partiellement revêtue d'un revêtement de protection (20).
PCT/IB2015/059979 2014-12-24 2015-12-24 Élément de support pour carreaux d'isolation thermique de chambres de combustion de turbine à gaz Ceased WO2016103231A2 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP15830868.4A EP3237803B1 (fr) 2014-12-24 2015-12-24 Élément de support pour carreaux d'isolation thermique de chambres de combustion de turbine à gaz
CN201580070456.8A CN107208892B (zh) 2014-12-24 2015-12-24 用于燃气轮机燃烧室的隔热瓦的支撑构件

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITMI20142253 2014-12-24
ITMI2014A002253 2014-12-24

Publications (2)

Publication Number Publication Date
WO2016103231A2 true WO2016103231A2 (fr) 2016-06-30
WO2016103231A3 WO2016103231A3 (fr) 2016-08-18

Family

ID=52682807

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2015/059979 Ceased WO2016103231A2 (fr) 2014-12-24 2015-12-24 Élément de support pour carreaux d'isolation thermique de chambres de combustion de turbine à gaz

Country Status (3)

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

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108611588B (zh) * 2018-07-18 2020-05-19 中国科学院上海硅酸盐研究所 一种耐高温氧化和抗硫、氯腐蚀的合金涂层及其制备方法
CN112197297B (zh) * 2020-11-02 2025-03-21 上海电气燃气轮机有限公司 用于将隔热层覆盖于燃烧室壳体的安装构件及燃烧室
CN115962487B (zh) * 2022-12-19 2025-09-23 上海电气燃气轮机有限公司 一种用于燃气轮机燃烧室热屏的连接装置及热屏
CN116573925B (zh) * 2023-05-18 2024-05-10 中国科学院过程工程研究所 一种陶瓷隔热瓦及其制备方法和应用

Family Cites Families (6)

* Cited by examiner, † Cited by third party
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 (ja) * 2002-07-05 2009-05-20 日本発條株式会社 析出強化型Ｃｏ−Ｎｉ基耐熱合金の製造方法
US7094450B2 (en) * 2003-04-30 2006-08-22 General Electric Company Method for applying or repairing thermal barrier coatings
ES2378375T3 (es) * 2005-02-07 2012-04-11 Siemens Aktiengesellschaft Pantalla térmica
EP1715248A1 (fr) * 2005-04-19 2006-10-25 Siemens Aktiengesellschaft Élément de fixation et portion correspondante d'un bouclier thermique ainsi que chambre de combustion munie d'un tel bouclier

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Also Published As

Publication number Publication date
CN107208892A (zh) 2017-09-26
EP3237803B1 (fr) 2019-09-25
CN107208892B (zh) 2019-11-26
WO2016103231A3 (fr) 2016-08-18
EP3237803A2 (fr) 2017-11-01

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