WO1998034068A1 - Installation de turbine a gaz comportant une enveloppe de chambre a combustion a revetement de briques de ceramique - Google Patents

Installation de turbine a gaz comportant une enveloppe de chambre a combustion a revetement de briques de ceramique Download PDF

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Publication number
WO1998034068A1
WO1998034068A1 PCT/DE1998/000324 DE9800324W WO9834068A1 WO 1998034068 A1 WO1998034068 A1 WO 1998034068A1 DE 9800324 W DE9800324 W DE 9800324W WO 9834068 A1 WO9834068 A1 WO 9834068A1
Authority
WO
WIPO (PCT)
Prior art keywords
ceramic
gas turbine
coating
combustion chamber
layer
Prior art date
Application number
PCT/DE1998/000324
Other languages
German (de)
English (en)
Inventor
Andreas Neidel
Klaus Raschke
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP98909340A priority Critical patent/EP0960308B1/fr
Priority to UA99074363A priority patent/UA41485C2/uk
Priority to JP53245998A priority patent/JP4294736B2/ja
Priority to DE59802328T priority patent/DE59802328D1/de
Publication of WO1998034068A1 publication Critical patent/WO1998034068A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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

Definitions

  • the invention relates to a gas turbine system with a combustion chamber housing which is lined on the inside with solid ceramic stones, with a rotor provided with rotor blades and with a housing provided with guide vanes, in particular at least the first blades on the turbine side carrying a ceramic thermal barrier coating.
  • Such a gas turbine is known for example from DE-OS 43 43 319.
  • the combustion chamber housings in particular their flame tubes, are designed to be extremely heat-resistant in modern gas turbines.
  • the inner walls can be covered with ceramic insulation layers or provided with a shield made of solid ceramic stones.
  • the blades of the turbine part of the gas turbine systems are often provided with ceramic thermal barrier layers as thermal protective layers, which consist, for example, of yttrium oxide-stabilized zirconium oxide layers.
  • the present invention is therefore based on the object of taking measures in a gas turbine of the type mentioned at the outset, on the one hand to protect the combustion chamber and the blades from thermal overload and on the other hand to extend the life of the turbine blades.
  • the object is achieved in that the ceramic stones are provided on their surface with a coating.
  • the ceramic stones have the advantage over heat shield plates made of other materials, for example super alloys, that higher material temperatures are possible and permissible. Only the stone fasteners need to be cooled. Because of the higher permissible material temperatures, for example, this leads to incomplete combustion of the combustion chamber lining
  • Shovels act on these like projectiles and have a strong abrasive effect.
  • the coating of the ceramic stones according to the invention effectively prevents the detachment of such particles from the surface of the ceramic stones. It seems particularly favorable here to coat the ceramic stones before installation in the combustion chamber housing. For this purpose, the coating must be such that good adhesion to the ceramic stones and good cohesion of the layer is ensured in order to avoid flaking off under thermal alternating stresses.
  • the coating of the ceramic stones thus forms a layer for fixing the surface particles. This enables the use of ceramic thermal barrier layers on the blades in combination with solid ceramic stones as the combustion chamber lining.
  • An embodiment of the invention provides that the coating consists of a metallic material and is applied in particular by means of vacuum plasma spraying (VPS).
  • VPS vacuum plasma spraying
  • Different corrosion protection layers which can be processed by VPS can be used for this purpose, e.g. B. the type M Cr A1Y, where M is Ni or Co.
  • a combination coating consisting of a metallic bond coat as an adhesion promoter with an overlying ceramic cover layer could also be used.
  • the ceramic cover layer can be partially applied by air plasma spraying.
  • the slight difference in the thermal expansion coefficients between ceramic stones and a ceramic APS coating has a favorable effect on the resistance to alternating thermal stress.
  • the execution of a ceramic layer as a thermal barrier layer has the additional advantage that the cooling air requirement of the combustion chamber lining is further reduced.
  • Conventional thermal insulation layers such as Yr 2 0 3 - stabilized Zr0 2 or Si0 2 or Al 2 0 3 are conceivable as ceramic coatings.
  • the invention can also be advantageously configured in that the ceramic cover layer is applied by means of the air plasma spraying process (APS).
  • APS air plasma spraying process
  • the APS procedure is a cheaper alternative to the VPS procedure.
  • the multilayer coating of the ceramic stones can also be advantageous for thermal reasons or for reasons of better cohesion of the layer.
  • both the binding layer and the outer coating can be designed as a graded layer, at that the thermal expansion behavior and the chemical composition change constantly over the layer thickness.
  • FIG. 1 schematically shows a longitudinal section of part of a gas turbine
  • Figure 2 schematically shows a section of the combustion chamber housing wall with distorted proportions in order to make the coating recognizable.
  • FIG. 1 schematically shows a gas turbine system according to the invention in a longitudinal section with a housing 1, in which fixed guide blades 3, 4 are fastened, and a rotor 2, to which rotor blades 5, 6 are fastened.
  • the fuel injected via the burners 14, 15 is burned with the air from the compressor 16.
  • Compressor 16 is the input part of the gas turbine system in which incoming air (arrows 17, 18) is compressed before it flows into combustion chamber 7.
  • a generator 20 for generating electrical energy is driven by means of the connecting shaft 19.
  • FIG. 2 the surface area of the annular combustion chamber is shown in simplified cross-section.
  • ceramic stones 10 are attached to the combustion chamber housing wall 11, which consists for example of metal.
  • the ceramic stones 10 consist for example of silicon or aluminum oxide.
  • a coating of the ceramic stones 10 is shown enlarged in two layers, of which the lower layer forms a binding layer (bond coat) 12, the upper layer forms a ceramic layer 13 which adheres particularly well to the binding layer 12.
  • the layers 12 and 13 together form a solid layer covering the ceramic stones 10, which binds any particles detached from the surface of the ceramic stones 10. Such particles can therefore have no erosive effect on the thermal barrier layer of the turbine blades of the housing or of the rotor.
  • the adhesion-promoting layer 12 preferably consists of a metal-chromium-aluminum-yttrium alloy (MCrAlY), while the heat insulation layer 13 preferably consists of yttrium oxide-stabilized zirconium oxide, SiO 2 or Al 2 O 3 .
  • a single-layer coating 22 of a ceramic stone is shown as an example in area 21 of FIG. 2, the coating consisting of ceramic.

Landscapes

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

Abstract

Installation de turbine à gaz dont l'enveloppe de la chambre de combustion (7) disposée entre le compresseur et la turbine est revêtue de briques de céramique massives (10), et dont le rotor (2) et les sections du bâti qui l'entourent sont garnis d'aubes (3, 4, 5, 6), dont au moins les premières séries (3, 5) portent, côté turbine, des couches thermiquement isolantes en céramique, caractérisée en ce que les briques en céramique (10) sont munies à leur surface d'un revêtement (12, 13) empêchant le 'sablage' des couches de céramique et la destruction consécutive desdites couches thermiquement isolantes.
PCT/DE1998/000324 1997-01-29 1998-01-29 Installation de turbine a gaz comportant une enveloppe de chambre a combustion a revetement de briques de ceramique WO1998034068A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP98909340A EP0960308B1 (fr) 1997-01-29 1998-01-29 Installation de turbine a gaz comportant une enveloppe de chambre a combustion a revetement de briques de ceramique
UA99074363A UA41485C2 (uk) 1997-01-29 1998-01-29 Газотурбінна установка з корпусом камери згоряння, внутрішній бік якого покритий масивними керамічними цеглинами
JP53245998A JP4294736B2 (ja) 1997-01-29 1998-01-29 燃焼室がセラミックブロックで内張りされているガスタービン設備
DE59802328T DE59802328D1 (de) 1997-01-29 1998-01-29 Gasturbinenanlage mit einem mit keramiksteinen ausgekleideten brennkammergehäuse

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19704976A DE19704976C2 (de) 1997-01-29 1997-01-29 Gasturbinenanlage mit einem mit Keramiksteinen ausgekleideten Brennkammergehäuse
DE19704976.1 1997-01-29

Publications (1)

Publication Number Publication Date
WO1998034068A1 true WO1998034068A1 (fr) 1998-08-06

Family

ID=7819815

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE1998/000324 WO1998034068A1 (fr) 1997-01-29 1998-01-29 Installation de turbine a gaz comportant une enveloppe de chambre a combustion a revetement de briques de ceramique

Country Status (6)

Country Link
EP (1) EP0960308B1 (fr)
JP (1) JP4294736B2 (fr)
DE (2) DE19704976C2 (fr)
RU (1) RU2178530C2 (fr)
UA (1) UA41485C2 (fr)
WO (1) WO1998034068A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1072573A1 (fr) 1999-07-30 2001-01-31 Siemens Aktiengesellschaft Procédé de fabrication d'une pièce réfractaire et brique céramique de chambre de combustion
PL200773B1 (pl) * 2003-04-18 2009-02-27 System Spo & Lstrok Ka Akcyjna Sposób wykonywania antykorozyjnej powłoki na ekranach grzewczych komór paleniskowych
RU2447361C2 (ru) * 2007-11-23 2012-04-10 Сименс Акциенгезелльшафт Элемент горелки и горелка с покрытием из оксида алюминия и способ покрытия элемента горелки
EP2169311A1 (fr) * 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Mélange de matière destiné à la fabrication d'une matière ignifuge, corps ignifuge et son procédé de fabrication
EP2233835A1 (fr) * 2009-03-23 2010-09-29 Siemens Aktiengesellschaft Chambre de combustion brasée avec des inserts en céramique
ITMI20111519A1 (it) 2011-08-08 2013-02-09 Ansaldo Energia Spa Piastrella di materiale ceramico per il rivestimento di camere di combustione, in particolare di turbine a gas, e relativo metodo di fabbricazione
RU2554690C1 (ru) * 2014-07-01 2015-06-27 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения"(АО"ВПК"НПО машиностроения") Камера сгорания силовой установки крылатой ракеты

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB602149A (en) * 1946-01-09 1948-05-20 Anglo Saxon Petroleum Co Improvements in and relating to combustion chamber linings
US2763919A (en) * 1950-07-28 1956-09-25 Thompson Prod Inc Coated refractory body
DE2630247A1 (de) * 1976-07-06 1978-01-19 Daimler Benz Ag Gasleitung mit einer waermeisolierenden auskleidung
US4159357A (en) * 1975-03-13 1979-06-26 Motoren- Und Turbinen-Union Munchen Gmbh Process for surface treating parts made of ceramic material
DE3638658C1 (de) * 1986-11-12 1988-04-21 Daimler Benz Ag Waermedaemmende Auskleidung fuer eine Gasturbine
EP0310043A2 (fr) * 1987-10-01 1989-04-05 Gte Laboratories Incorporated Revêtement résistant à l'oxydation et à des cycles thermiques à hautes températures pour substrats contenant du silicium et procédé de fabrication
US5169674A (en) * 1990-10-23 1992-12-08 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method of applying a thermal barrier coating system to a substrate
DE4343319A1 (de) 1993-12-18 1995-06-22 Abb Patent Gmbh Brennkammer mit keramischer Auskleidung
US5496644A (en) * 1993-03-15 1996-03-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Plasma sprayed mullite coatings on silicon-base ceramics
WO1997001436A1 (fr) * 1995-06-26 1997-01-16 General Electric Company Composite pour revetement formant barriere thermique protege, a couches multiples

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3446649A1 (de) * 1984-12-20 1986-06-26 G + H Montage Gmbh, 6700 Ludwigshafen Auskleidung fuer hochtemperatur-gasturbinen

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB602149A (en) * 1946-01-09 1948-05-20 Anglo Saxon Petroleum Co Improvements in and relating to combustion chamber linings
US2763919A (en) * 1950-07-28 1956-09-25 Thompson Prod Inc Coated refractory body
US4159357A (en) * 1975-03-13 1979-06-26 Motoren- Und Turbinen-Union Munchen Gmbh Process for surface treating parts made of ceramic material
DE2630247A1 (de) * 1976-07-06 1978-01-19 Daimler Benz Ag Gasleitung mit einer waermeisolierenden auskleidung
DE3638658C1 (de) * 1986-11-12 1988-04-21 Daimler Benz Ag Waermedaemmende Auskleidung fuer eine Gasturbine
EP0310043A2 (fr) * 1987-10-01 1989-04-05 Gte Laboratories Incorporated Revêtement résistant à l'oxydation et à des cycles thermiques à hautes températures pour substrats contenant du silicium et procédé de fabrication
US5169674A (en) * 1990-10-23 1992-12-08 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Method of applying a thermal barrier coating system to a substrate
US5496644A (en) * 1993-03-15 1996-03-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Plasma sprayed mullite coatings on silicon-base ceramics
DE4343319A1 (de) 1993-12-18 1995-06-22 Abb Patent Gmbh Brennkammer mit keramischer Auskleidung
WO1997001436A1 (fr) * 1995-06-26 1997-01-16 General Electric Company Composite pour revetement formant barriere thermique protege, a couches multiples

Also Published As

Publication number Publication date
JP4294736B2 (ja) 2009-07-15
UA41485C2 (uk) 2001-09-17
DE19704976A1 (de) 1998-07-30
JP2001509874A (ja) 2001-07-24
DE59802328D1 (de) 2002-01-17
DE19704976C2 (de) 1999-02-25
EP0960308A1 (fr) 1999-12-01
EP0960308B1 (fr) 2001-12-05
RU2178530C2 (ru) 2002-01-20

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