RU99118768A - GAS TURBINE INSTALLATION WITH FACED CERAMIC STONES COMBUSTION CHAMBER HOUSING - Google Patents

GAS TURBINE INSTALLATION WITH FACED CERAMIC STONES COMBUSTION CHAMBER HOUSING

Info

Publication number
RU99118768A
RU99118768A RU99118768/06A RU99118768A RU99118768A RU 99118768 A RU99118768 A RU 99118768A RU 99118768/06 A RU99118768/06 A RU 99118768/06A RU 99118768 A RU99118768 A RU 99118768A RU 99118768 A RU99118768 A RU 99118768A
Authority
RU
Russia
Prior art keywords
coating
ceramic
combustion chamber
gas turbine
chamber housing
Prior art date
Application number
RU99118768/06A
Other languages
Russian (ru)
Other versions
RU2178530C2 (en
Inventor
Андреас НАЙДЕЛЬ
Клаус РАШКЕ
Original Assignee
Сименс Акциенгезелльшафт
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
Priority claimed from DE19704976A external-priority patent/DE19704976C2/en
Application filed by Сименс Акциенгезелльшафт filed Critical Сименс Акциенгезелльшафт
Publication of RU99118768A publication Critical patent/RU99118768A/en
Application granted granted Critical
Publication of RU2178530C2 publication Critical patent/RU2178530C2/en

Links

Claims (5)

1. Газотурбинная установка, содержащая корпус (7) камеры сгорания, облицованный на внутренней стороне массивными керамическими камнями (10), ротор (2), снабженный направляющими лопатками (5, 6), и кожух (1), также снабженный направляющими лопатками (3, 4), причем, в частности, по меньшей мере, первые лопатки на стороне турбины несут керамический теплоизолирующий слой, отличающаяся тем, что керамические камни (10) снабжены на своей поверхности покрытием (12, 13).1. A gas turbine installation comprising a housing (7) of a combustion chamber, lined on the inside with massive ceramic stones (10), a rotor (2) equipped with guide vanes (5, 6), and a casing (1) also equipped with guide vanes (3 , 4), and, in particular, at least the first blades on the turbine side carry a ceramic heat-insulating layer, characterized in that the ceramic stones (10) are provided with a coating on their surface (12, 13). 2. Установка по п.1, отличающаяся тем, что покрытие (12, 13) состоит из металлического материала и нанесено, в частности, плазменным напылением в вакууме (VPS). 2. Installation according to claim 1, characterized in that the coating (12, 13) consists of a metal material and is applied, in particular, by plasma spraying in vacuum (VPS). 3. Установка по п.2, отличающаяся тем, что покрытие состоит из связующего слоя и керамического покрывающего слоя, при этом керамический покрывающий слой нанесен, в частности, плазменным напылением на воздухе (APS). 3. Installation according to claim 2, characterized in that the coating consists of a bonding layer and a ceramic coating layer, while the ceramic coating layer is applied, in particular, by plasma spraying in air (APS). 4. Установка по п.1 или одному из последующих пунктов, отличающаяся тем, что покрытие выполнено в виде керамического слоя. 4. Installation according to claim 1 or one of the following paragraphs, characterized in that the coating is made in the form of a ceramic layer. 5. Установка по п.1 или одному из последующих пунктов, отличающаяся тем, что она имеет многослойное покрытие керамических камней (10). 5. Installation according to claim 1 or one of the following paragraphs, characterized in that it has a multilayer coating of ceramic stones (10).
RU99118768/06A 1997-01-29 1998-01-29 Gas-turbine plant with combustion chamber housing lined with ceramic stones RU2178530C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19704976.1 1997-01-29
DE19704976A DE19704976C2 (en) 1997-01-29 1997-01-29 Gas turbine system with a combustion chamber casing lined with ceramic stones

Publications (2)

Publication Number Publication Date
RU99118768A true RU99118768A (en) 2001-07-20
RU2178530C2 RU2178530C2 (en) 2002-01-20

Family

ID=7819815

Family Applications (1)

Application Number Title Priority Date Filing Date
RU99118768/06A RU2178530C2 (en) 1997-01-29 1998-01-29 Gas-turbine plant with combustion chamber housing lined with ceramic stones

Country Status (6)

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

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1072573A1 (en) 1999-07-30 2001-01-31 Siemens Aktiengesellschaft Method of making a refractory body and ceramic combustion chamber stone
PL200773B1 (en) * 2003-04-18 2009-02-27 System Spo & Lstrok Ka Akcyjna Method for applying anticorrosive coating on furnace waterwalls
US20100285415A1 (en) * 2007-11-23 2010-11-11 Boettcher Andreas Burner Element and Burner Having Aluminum Oxide Coating and Method for Coating a Burner Element
EP2169311A1 (en) * 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Material mixture for producing a fire-retardant material, fire-retardant moulding body and method for its manufacture
EP2233835A1 (en) * 2009-03-23 2010-09-29 Siemens Aktiengesellschaft Combustion chamber brazed with ceramic inserts
ITMI20111519A1 (en) * 2011-08-08 2013-02-09 Ansaldo Energia Spa TILE OF CERAMIC MATERIAL FOR THE COATING OF COMBUSTION CHAMBERS, IN PARTICULAR OF GAS TURBINES, AND ITS RELATED MANUFACTURING METHOD
RU2554690C1 (en) * 2014-07-01 2015-06-27 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения"(АО"ВПК"НПО машиностроения") Cruise missile engine combustion chamber

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL69245C (en) * 1946-01-09
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 (en) * 1976-07-06 1978-01-19 Daimler Benz Ag Exhaust gas pipe for internal combustion engines - lined with thermal insulation so gas has high temp. when it meets purificn. catalyst
DE3446649A1 (en) * 1984-12-20 1986-06-26 G + H Montage Gmbh, 6700 Ludwigshafen Lining for high-temperature gas turbines
DE3638658C1 (en) * 1986-11-12 1988-04-21 Daimler Benz Ag Heat-insulating lining for a gas turbine
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
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
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
DE4343319A1 (en) * 1993-12-18 1995-06-22 Abb Patent Gmbh Combustion chamber with a ceramic lining
CH690582A5 (en) * 1995-06-26 2000-10-31 Gen Electric Composite material protected by multiple trains Over thermal barrier coating.

Similar Documents

Publication Publication Date Title
SE8303368L (en) FOR GAS TURBINE ENGINES DESIGNED WITH CERAMIC SURFACE PROVIDED SEAL TO OUTDOOR AIR
JPS58113503A (en) Blade of fluid machine and its manufacture
EP0752052A1 (en) Airfoil having a seal and an integral heat shield
EP0937946A3 (en) Wall structure for a gas turbine combustor
EP1013885A3 (en) Turbine vane mounting arrangement
GB2239678B (en) Gas turbine engine blade shroud assembly
EP1149985A3 (en) Metallic shroud structure
EP0466501A3 (en) Curved film cooling holes for gas turbine engine vanes
GB2076066A (en) Turbomachine casing liner
EP1392957A4 (en) Abradeable seal system
IL115715A0 (en) Gas turbine vane with enhanced cooling
GB2125111A (en) Shroud assembly for a gas turbine engine
SE8803415D0 (en) GAS TURBINE ENGINE
SE8505156D0 (en) COOLABLE SEAL SEGMENT FOR A ROTATING MACHINE
GB9405473D0 (en) A gas turbine engine fan blade assembly
RU99118768A (en) GAS TURBINE INSTALLATION WITH FACED CERAMIC STONES COMBUSTION CHAMBER HOUSING
ES2063636A2 (en) Stator vane assembly for controlling air flow in a gas turbine engien
FR2662741B1 (en) STATOR FOR A GAS TURBINE TO WHICH A COATING HAVING CERTAIN THERMAL CONDUCTIVITY IS SELECTIVELY APPLIED.
CA2046173A1 (en) Bladed stator having fixed blades made of thermostructural composite material, e.g. for a turbine, and manufacturing process therefor
JP4294736B2 (en) Gas turbine equipment with combustion chamber lined with ceramic blocks
EP0921276A3 (en) Gas turbine blade
DE69101623D1 (en) Assembly of a ceramic volute casing in a gas turbine engine.
JPS5733796A (en) Sealing device
GB2293415B (en) High thermal efficiency gas turbine engine
RU96102814A (en) GAS TRACT