EP0960308B1 - 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
EP0960308B1
EP0960308B1 EP98909340A EP98909340A EP0960308B1 EP 0960308 B1 EP0960308 B1 EP 0960308B1 EP 98909340 A EP98909340 A EP 98909340A EP 98909340 A EP98909340 A EP 98909340A EP 0960308 B1 EP0960308 B1 EP 0960308B1
Authority
EP
European Patent Office
Prior art keywords
ceramic
gas turbine
coating
combustion chamber
turbine installation
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 - Lifetime
Application number
EP98909340A
Other languages
German (de)
English (en)
Other versions
EP0960308A1 (fr
Inventor
Andreas Neidel
Klaus Raschke
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of EP0960308A1 publication Critical patent/EP0960308A1/fr
Application granted granted Critical
Publication of EP0960308B1 publication Critical patent/EP0960308B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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 with massive inside Ceramic stones are lined with a with blades provided rotor and one with guide vanes Housing, in particular at least the first blades a ceramic thermal barrier coating on the turbine side wear.
  • Such a gas turbine is for example from DE-OS 43 43 319 known.
  • the combustion chamber housing, especially their Flame tubes in modern gas turbines can withstand extreme thermal loads executed.
  • the interior walls can be covered with ceramic Insulation layers covered or with a sign massive ceramic stones.
  • the blades of the turbine part of the gas turbine systems in particular the blades of the combustion chamber adjacent Steps often with ceramic thermal barrier layers as thermal protective layers provided, for example yttrium oxide stabilized zirconium oxide layers exist.
  • the present invention is therefore based on the object in the case of a gas turbine of the type mentioned at the beginning meet the combustion chamber and the blades to protect thermal overload and on the other hand the service life to extend the turbine blades.
  • the object is achieved in that the ceramic stones provided with a coating on its surface are.
  • 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, this leads to the fact that incompletely burned flue gas particles that get onto the surface of the combustion chamber lining are completely burned there and less toxic CO (carbon monoxide) is produced in the exhaust gas, since this is converted into non-toxic CO 2 (carbon dioxide).
  • the cooling air which is less required in comparison to metallic linings, is now additionally available for combustion. As a result, a lower flame temperature and noticeably fewer nitrogen oxides are formed, which, for known reasons, also pollute the environment.
  • the ceramic stones according to the invention By coating the ceramic stones according to the invention is the detachment of such particles from the surface of the ceramic stones effectively prevented. Appears particularly cheap Here, the ceramic stones before installation in the combustion chamber housing to coat. The coating must be so be able to adhere well to the ceramic stones and good cohesion of the layer is guaranteed to to prevent flaking in the case of alternating thermal stresses. The coating of the ceramic stones thus forms one Layer to fix the surface particles.
  • the coating of the ceramic stones thus forms one Layer to fix the surface particles.
  • An embodiment of the invention provides that the coating consists of a metallic material and in particular is applied by means of vacuum plasma spraying (VPS).
  • VPS vacuum plasma spraying
  • Different corrosion protection layers that can be processed using VPS can be used for this purpose are used, e.g. B. the type M Cr AlY, where M is Ni or Co.
  • a combination coating made of a metallic Bond coat as an adhesion promoter with an overlying ceramic cover layer would be applicable.
  • the ceramic cover layer can be advantageous applied by air plasma spraying process his.
  • VPS bondcoat can be dispensed with, is also the immediate coating of the stones with ceramic layers conceivable.
  • the slight difference in the coefficient of thermal expansion 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.
  • Typical thermal insulation layers such as Yr 2 O 3 -stabilized ZrO 2 or SiO 2 or Al 2 O 3, are conceivable as ceramic coatings.
  • the invention can also be advantageously configured by that the ceramic cover layer by means of air plasma spraying (APS) is applied.
  • APS air plasma spraying
  • the APS procedure provides a cheaper alternative the VPS method.
  • the multilayer coating of the ceramic stones can also for thermal reasons or for reasons of better Cohesion of the layer can be advantageous.
  • both the binding layer and the outer layer Coating can be carried out as a graded layer the thermal expansion behavior and chemical composition change constantly over the layer thickness.
  • FIG. 1 schematically shows a gas turbine system according to the invention in a longitudinal section with a housing 1, in the fixed Guide blades 3, 4 are attached and a rotor 2, on the blades 5, 6 are attached.
  • housing 7 is injected via the burners 14, 15 Fuel burned with the air from the compressor 16.
  • the compressor 16 the input part of the Gas turbine plant referred to in the incoming air (Arrows 17, 18) compressed before flowing into the combustion chamber 7 becomes.
  • a generator 20 is used to generate the connection shaft 19 electrical energy.
  • FIG 2 is the surface area of the annular combustion chamber shown in simplified cross-section.
  • 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 thermal insulation layer 13 preferably consists of yttrium oxide-stabilized zirconium oxide, SiO 2 or Al 2 O 3 .
  • the coating is made of ceramic.

Landscapes

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

Claims (5)

  1. Installation de turbine à gaz, comprenant un corps (7) de chambre de combustion qui est revêtu sur la face intérieure de briques (10) pleines en céramique, un rotor (2) muni d'aubes (5, 6) mobiles et une enveloppe (1) munie d'aubes (3, 4) directrices, au moins notamment les premières aubes du côté de la turbine portant une couche calorifuge céramique,
       caractérisée en ce que les briques (10) en céramique sont munies sur leur surface d'un revêtement (12, 13).
  2. Installation de turbine à gaz suivant la revendication 1,
       caractérisée en ce que le revêtement (12, 13) est en matériau métallique et est déposé notamment au moyen d'une projection sous vide par plasma (VPS).
  3. Installation de turbine à gaz suivant la revendication 2,
       caractérisée en ce que le revêtement est constitué d'un revêtement de liaison et d'une couche de finition en céramique et en ce que la couche (13) de finition en céramique est déposée notamment au moyen d'un procédé de pulvérisation air-plasma (APS).
  4. Installation de turbine à gaz suivant la revendication 1 ou l'une des suivantes,
       caractérisée en que le revêtement est constitué sous la forme d'une couche céramique.
  5. Installation de turbine à gaz suivant la revendication 1 ou l'une des suivantes,
       caractérisée par un revêtement à plusieurs strates des briques (10) en céramique.
EP98909340A 1997-01-29 1998-01-29 Installation de turbine a gaz comportant une enveloppe de chambre a combustion a revetement de briques de ceramique Expired - Lifetime EP0960308B1 (fr)

Applications Claiming Priority (3)

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

Publications (2)

Publication Number Publication Date
EP0960308A1 EP0960308A1 (fr) 1999-12-01
EP0960308B1 true EP0960308B1 (fr) 2001-12-05

Family

ID=7819815

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98909340A Expired - Lifetime 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

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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013021354A2 (fr) 2011-08-08 2013-02-14 Ansaldo Energia S.P.A. Carreau de céramique pour le revêtement intérieur de chambres de combustion, en particulier de turbines à gaz, et son procédé de fabrication

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
WO2009065625A1 (fr) * 2007-11-23 2009-05-28 Siemens Aktiengesellschaft Élément de brûleur et brûleur comportant un placage en alumine et procédé de placage d'un élément de brûleur
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
RU2430306C1 (ru) * 2010-02-18 2011-09-27 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Корпус камеры сгорания летательного аппарата
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

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DE2630247A1 (de) * 1976-07-06 1978-01-19 Daimler Benz Ag Gasleitung mit einer waermeisolierenden auskleidung
US4422648A (en) * 1982-06-17 1983-12-27 United Technologies Corporation Ceramic faced outer air seal for gas turbine engines
DE3446649A1 (de) * 1984-12-20 1986-06-26 G + H Montage Gmbh, 6700 Ludwigshafen Auskleidung fuer hochtemperatur-gasturbinen
DE3638658C1 (de) * 1986-11-12 1988-04-21 Daimler Benz Ag Waermedaemmende Auskleidung fuer eine Gasturbine
AU2211488A (en) * 1987-10-01 1989-04-06 Gte Laboratories Incorporated Oxidation resistant, high temperature thermal cyling resistant coatings on silicon-based substrates and process for the production thereof
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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
RU2027044C1 (ru) * 1993-02-22 1995-01-20 Борис Мартынович Юнкер Камера сгорания газотурбинной установки
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US5391404A (en) * 1993-03-15 1995-02-21 The United States Of America As Represented By The National Aeronautics And Space Administration Plasma sprayed mullite coatings on silicon-base ceramics
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013021354A2 (fr) 2011-08-08 2013-02-14 Ansaldo Energia S.P.A. Carreau de céramique pour le revêtement intérieur de chambres de combustion, en particulier de turbines à gaz, et son procédé de fabrication
EP2742289B1 (fr) * 2011-08-08 2017-01-18 Ansaldo Energia S.p.A. Carreau de céramique pour le revêtement intérieur de chambres de combustion, en particulier de turbines à gaz, et son procédé de fabrication

Also Published As

Publication number Publication date
DE19704976A1 (de) 1998-07-30
UA41485C2 (uk) 2001-09-17
DE19704976C2 (de) 1999-02-25
JP4294736B2 (ja) 2009-07-15
WO1998034068A1 (fr) 1998-08-06
RU2178530C2 (ru) 2002-01-20
JP2001509874A (ja) 2001-07-24
EP0960308A1 (fr) 1999-12-01
DE59802328D1 (de) 2002-01-17

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