GB2390569A - Ceramic materials for thermal insulation - Google Patents

Ceramic materials for thermal insulation Download PDF

Info

Publication number
GB2390569A
GB2390569A GB0215958A GB0215958A GB2390569A GB 2390569 A GB2390569 A GB 2390569A GB 0215958 A GB0215958 A GB 0215958A GB 0215958 A GB0215958 A GB 0215958A GB 2390569 A GB2390569 A GB 2390569A
Authority
GB
United Kingdom
Prior art keywords
ceramic
fibres
ceramic material
base layer
material according
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.)
Withdrawn
Application number
GB0215958A
Other versions
GB0215958D0 (en
Inventor
Nigel Anthony Rhodes
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.)
Alstom SA
Original Assignee
Alstom SA
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 Alstom SA filed Critical Alstom SA
Priority to GB0215958A priority Critical patent/GB2390569A/en
Publication of GB0215958D0 publication Critical patent/GB0215958D0/en
Publication of GB2390569A publication Critical patent/GB2390569A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
    • C04B41/52—Multiple coating or impregnating multiple coating or impregnating with the same composition or with compositions only differing in the concentration of the constituents, is classified as single coating or impregnation
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
    • C04B41/81—Coating or impregnation
    • C04B41/89—Coating or impregnation for obtaining at least two superposed coatings having different compositions
    • 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
    • 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
    • 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
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2111/00—Mortars, concrete or artificial stone or mixtures to prepare them, characterised by specific function, property or use
    • C04B2111/00474—Uses not provided for elsewhere in C04B2111/00
    • C04B2111/0081—Uses not provided for elsewhere in C04B2111/00 as catalysts or catalyst carriers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5024—Heat conductivity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments
    • 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
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05004—Special materials for walls or lining
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Laminated Bodies (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A ceramic material is provided which is suitable for coating hot fluid stream components such as a gas turbine combustion can. The ceramic material 1 comprises a base layer 2 and a plurality of ceramic fibres 4. A first end of the fibres is bonded to the base layer 2 and a second end 6 is free to move in the hot fluid stream 10. The microstructure appearance of the ceramic material 1 generally resembles an animal fur. The base layer may be a ceramic or ceramic textile product. It may be bonded to a metallic or ceramic matrix load bearing substrate 8.

Description

TITLE Ceramic materials DESCRIPTION
5 Technical Field
The present invention relates to ceramic materials, and in particular to ceramic materials for providing thermal insulation.
Background Art
10 The gas turbine industry is continually striving to increase the efficiency and power output of its engines. One way of doing this is to increase the temperature of combustion. However, this places a restriction on the types of materials that can be used for those components within the gas turbine engine that are exposed to high temperatures. In some cases it is necessary to make the components from special 15 high-temperature materials that are extremely expensive or to maintain the components at a lower temperature by providing them with a flow of relatively cool air through cooling ducts within the design of the engine. This has the effect of reducing the efficiency of the gas turbine engine and therefore offsets some of the advantage of increasing the temperature.
Another solution is to coat hot gas stream components such as turbine blades and combustor cans with a thermal barrier coating. Ceramic materials are commonly used as thermal barrier coatings because they are able to withstand extremely high temperatures. 'Turbine blades usually have a nickel-based superalloy substrate and the 25 ceramic thermal barrier coating enables them to operate in environments that are hotter than the nominal maximum working temperature of the alloy. One of the difficulties with this approach is the mismatch of thermal expansion coefficient between the ceramic thermal barrier coating and the superalloy substrate. This places a limit on the maximum thickness of the thermal barrier coating and hence the degree 30 of insulation that it can supply. Furthermore, ceramic materials generally lack toughness and have a low tolerance to defects and damage.
- 2 One way of overcoming these problems is to use so-called ceramic matrix composites. Such materials are well known and offer defect and damage tolerances close to that of metals. This is achieved by a complex combination of fracture mechanisms involving crack deflection, crack bridging and fibre pull out. If the 5 ceramic matrix composite requires further thermal insulation properties then this is best achieved using a ceramic material coating with extremely low density. This ceramic material can take the form of a foam or a fibreboard, for example. Figure 1 is a high-resolution image taken by scanning electron microscope showing the microstructure of fibreboard. It can be seen that the fibreboard consists of a number 10 of fibres laying at random orientations but predominantly in the plane of the fibreboard. The fibres are contiguous and held together by small areas of sinter necks that form at points of contact. A large volume of stationary gas is trapped in the spaces between the fibres and provides the fibreboard with excellent thermal insulation properties. However, the fibres on the surface are only weakly bonded to 15 their neighbours and the fibreboard therefore lacks the strength and erosion resistance that is found in more dense ceramic materials. To overcome this the surface of the fibreboard is normally coated with an erosion resistant layer to prevent the rapid removal of fibres.
20 Efforts have been made to use ceramic fibreboard as a thermal protection system for the inner surface of a ceramic matrix composite gas turbine engine combustor can (Nice, W. PhD Thesis, Thermally-insulating Materials for the Combustion Section of Industrial Gas Turbines, UMIST, UK, 1996). In this case a bond-coat layer was used to provide good adhesion to the combustor can and a reasonable match of thermal 25 expansion coefficient. A fibreboard layer was then bonded to the bondcoat layer and coated with an erosion resistant layer.
The thermal protection system performed well during combustion trials. The high gas pressure inside the combustor can was found to be matched by the high gas pressure 30 within the fibreboard and the ceramic matrix composite remained intact. This remained the case until the combustion flame was suddenly and rapidly extinguished.
This was accompanied by a rapid change in the gas pressure within the combustor
- 3 can. The pressure of the stationary gas trapped within the fibreboard was not able to equalise with the rapidly dropping pressure in the combustor can and the ceramic fibreboard layer was blown off the inner surface of the combustor can resulting in catastrophic failure.
It is therefore a purpose of the present invention to provide a ceramic material that can be used as a thermal protection system for metallic or ceramic components in hot fluid streams. 10 Summary of the Invention
The present invention provides a ceramic material for coating hot fluid stream components, the material comprising a base layer and a plurality of ceramic fibres having a first end bonded to the base layer and a second end that is free to move in the hot fluid stream.
The fluid can be a liquid or a gas.
Each fibre can be formed from a single ceramic filament or a bundle of ceramic filaments. The fibres can be substantially straight or formed as loops. The individual 20 fibres are preferably orientated substantially perpendicular to the base layer.
The fibres preferably are formed from an oxide because these have a superior oxidation resistance to non-oxide fibres. However, it will be readily appreciated that the fibres can be formed of any suitable ceramic material.
The fibres are preferably fine enough to provide maximum thermal insulation and maximum flexibility without being so fine as to sinter together when exposed to high temperatures in the hot fluid stream. The surface of the fibres is preferably as smooth as possible so as to maximise the flexural strength of the fibres and to minimise the 30 damage caused to the fibres if they abrade against one another.
-4 The fibres can have a uniform or non-uniform length and are spaced at a predetermined density.
The base layer is preferably a ceramic or a ceramic textile product and can be bonded 5 to a metallic load bearing substrate or to a ceramic matrix composite load bearing substrate. Alternatively, if the base layer is a ceramic textile product then the base layer (but not the fibres) can be impregnated with a compatible ceramic matrix to form a ceramic matrix composite. This allows the ceramic material (i.e. the thermal protection layer) and the load bearing substrate to be combined to form a single 10 integral structure.
Although the fibres are said to be bonded to the base layer it will be readily appreciated that the fibres and the base layer may be integrally formed.
15 The ceramic material is suitable for coating the inner surface of a gas turbine combustor can. The ceramic material has excellent thermal insulation properties because of the large volume of stationary gas that can be trapped between the fibres.
When the gas turbine engine is operating the fibres are free to flex in the moving hot gas stream present in the combustor can. If the combustion flame is suddenly and 20 rapidly extinguished and there is a rapid change in the gas pressure within the combustor can then the fibres simply straighten up and allow any trapped gas to escape. Furthermore, because each fibre is individually bonded to the base layer it means that the ceramic material has better erosion resistance than the fibreboard and does not need to be coated with an erosion resistant layer.
The ceramic material is also suitable for use with automotive catalyst substrates and with catalyst substrates for the chemical industry. It is also possible to use the ceramic material with high temperature static and dynamic brush seals.
30 Because the free ends of the fibres are not constrained in any way the fibres are free to expand and contract with changes in temperature. This lack of constraint means that the thermal stresses in the load bearing substrate are reduced.
- 5 In addition to its thermal insulation properties, the ceramic material also has sound dampening properties because the fibres are able to flex in response to impinging sound waves. The ceramic material is therefore suitable for coating aircraft engine 5 components where it can help to reduce noise pollution.
Drawings Figure 1 is a high-resolution image taken by scanning electron microscope showing the microstructure of a ceramic fibreboard; 10 Figure 2 is a schematic diagram showing a ceramic material in accordance with the present invention in a non-operating condition; and Figure 3 is a schematic diagram showing the ceramic material of Figure 2 in an operating condition.
IS The coating material 1 shown in Figures 2 and 3 consists of a ceramic base layer 2 and a number of upstanding ceramic fibres 4. The ceramic fibres 4 are individually bonded to the base layer 2 and have a free end 6. A layer of stationary gas (not shown) is trapped in the space between the fibres 4 and provides the coating material 1 with thermal insulation properties. The microstructure appearance of the coating 20 material I generally resembles an animal fur.
The base layer 2 is bonded to a load bearing substrate 8 that forms the combustor can of a gas turbine engine. The load bearing substrate 8 can be a ceramic matrix composite or metallic.
When the gas turbine engine is operating the fibres 4 are able to flex in the moving hot gas stream 10 within the combustor can as shown in Figure 3. When the gas turbine engine is not operating then the fibres 4 are able to straighten up so that they are orientated substantially perpendicular to the base layer 2 as shown in Figure 2.
30 This allows any stationary gas that is trapped in the space between the fibres 4 to escape.

Claims (12)

- 6 CLAIMS
1. A ceramic material for coating hot fluid stream components, the material comprising a base layer and a plurality of ceramic fibres each having a first end bonded to the base layer and a second end that is free to move in the hot fluid stream.
2. A ceramic material according to claim 1, wherein the fibres are substantially straight.
3. A ceramic material according to claim 1, wherein the fibres are loops.
4. A ceramic material according to any preceding claim, wherein the fibres are orientated substantially perpendicular to the base layer.
5. A ceramic material according to any preceding claim, wherein the fibres are 15 formed from an oxide.
6. A ceramic material according to any preceding claim, wherein the fibres have a uniform length.
20
7. A ceramic material according to any of claims 1 to 5, wherein the fibres have a non-uniform length.
8. A ceramic material according to any preceding claim, wherein the fibres have a predetermined density.
9. A ceramic material according to any preceding claim, wherein the base layer is a ceramic.
10. A ceramic material according to any preceding claim, wherein the base layer 30 is a ceramic textile product and is impregnated with a compatible ceramic matrix to form a ceramic matrix composite.
- 7
11. A combustor can for a gas turbine engine coated on its inner surface with a ceramic material according to any of claims 1 to 9.
12. A ceramic material substantially as herein described and with reference to 5 Figures 2 and 3 of the drawings.
GB0215958A 2002-07-10 2002-07-10 Ceramic materials for thermal insulation Withdrawn GB2390569A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0215958A GB2390569A (en) 2002-07-10 2002-07-10 Ceramic materials for thermal insulation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0215958A GB2390569A (en) 2002-07-10 2002-07-10 Ceramic materials for thermal insulation

Publications (2)

Publication Number Publication Date
GB0215958D0 GB0215958D0 (en) 2002-08-21
GB2390569A true GB2390569A (en) 2004-01-14

Family

ID=9940174

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0215958A Withdrawn GB2390569A (en) 2002-07-10 2002-07-10 Ceramic materials for thermal insulation

Country Status (1)

Country Link
GB (1) GB2390569A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012160095A1 (en) * 2011-05-25 2012-11-29 Technische Universität Bergakademie Freiberg Heat exchanger composed of ceramic material, in particular for recuperator burners, and method for production of the same
EP3008387A4 (en) * 2013-06-14 2016-10-12 United Technologies Corp Conductive panel surface cooling augmentation for gas turbine engine combustor
EP3366888A1 (en) * 2017-02-27 2018-08-29 Rolls-Royce North American Technologies, Inc. Ceramic seal component for gas turbine engine and process of making the same

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2120972A (en) * 1982-05-26 1983-12-14 Rolls Royce Composite structure
EP0162645A1 (en) * 1984-05-11 1985-11-27 Masami Harada Carbon-fiber-covered material
GB2293417A (en) * 1994-09-14 1996-03-27 Mtu Muenchen Gmbh Sealing in turbine engines
JPH1038277A (en) * 1996-07-18 1998-02-13 Ishikawajima Harima Heavy Ind Co Ltd Combustor of gas turbine
DE29822549U1 (en) * 1998-12-18 1999-03-11 Silca GmbH, 40822 Mettmann Thermal insulation system in lightweight construction
US20010022431A1 (en) * 2000-02-28 2001-09-20 Stefan Beichl Brush for a brush seal

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2120972A (en) * 1982-05-26 1983-12-14 Rolls Royce Composite structure
EP0162645A1 (en) * 1984-05-11 1985-11-27 Masami Harada Carbon-fiber-covered material
GB2293417A (en) * 1994-09-14 1996-03-27 Mtu Muenchen Gmbh Sealing in turbine engines
JPH1038277A (en) * 1996-07-18 1998-02-13 Ishikawajima Harima Heavy Ind Co Ltd Combustor of gas turbine
DE29822549U1 (en) * 1998-12-18 1999-03-11 Silca GmbH, 40822 Mettmann Thermal insulation system in lightweight construction
US20010022431A1 (en) * 2000-02-28 2001-09-20 Stefan Beichl Brush for a brush seal

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012160095A1 (en) * 2011-05-25 2012-11-29 Technische Universität Bergakademie Freiberg Heat exchanger composed of ceramic material, in particular for recuperator burners, and method for production of the same
EP3008387A4 (en) * 2013-06-14 2016-10-12 United Technologies Corp Conductive panel surface cooling augmentation for gas turbine engine combustor
EP3366888A1 (en) * 2017-02-27 2018-08-29 Rolls-Royce North American Technologies, Inc. Ceramic seal component for gas turbine engine and process of making the same
US10794205B2 (en) 2017-02-27 2020-10-06 Rolls-Royce North American Technologies Inc. Ceramic seal component for gas turbine engine and process of making the same
US11255206B2 (en) 2017-02-27 2022-02-22 Rolls-Royce North American Technologies Inc. Ceramic seal component for gas turbine engine and process of making the same

Also Published As

Publication number Publication date
GB0215958D0 (en) 2002-08-21

Similar Documents

Publication Publication Date Title
US4594053A (en) Housing for a fluid flow or jet engine
US8802199B2 (en) Method for microstructure control of ceramic thermal spray coating
US8007899B2 (en) Segmented abradable coatings and process(es) for applying the same
US20110151219A1 (en) Coating Systems for Protection of Substrates Exposed to Hot and Harsh Environments and Coated Articles
US10808308B2 (en) Thermal barrier coating, turbine member, and gas turbine
EP1642993B1 (en) Segmented gadolinia zirconia coatings
EP3162917B1 (en) Methods of repairing a thermal barrier coating of a gas turbine component and the resulting components
US20100104859A1 (en) Bond coating and thermal barrier compositions, processes for applying both, and their coated articles
JP2004036443A (en) Gas turbine shroud structure
US6767659B1 (en) Backside radiative cooled ceramic matrix composite component
US20030224124A1 (en) Method of depositing a compositionally-graded coating system
EP1432571A2 (en) Hybrid ceramic material composed of insulating and structural ceramic layers
JPH11311103A (en) High temperature parts, high temperature parts for gas turbine, and their manufacture
US8722202B2 (en) Method and system for enhancing heat transfer of turbine engine components
US11053855B2 (en) Reflective coating and coating process therefor
JP2009041059A (en) High-temperature wear-resistant member and its manufacturing method
US10662786B2 (en) CMC articles having small complex features for advanced film cooling
EP0136071A1 (en) Varying thickness thermal barrier for combustion turbine baskets
GB2390569A (en) Ceramic materials for thermal insulation
Sabelkin et al. Effects of combustion and salt-fog exposure on fatigue behavior of two ceramic matrix composites and a superalloy
Steinhauser et al. A new concept for thermal protection of all-mullite composites in combustion chambers
EP1531192A1 (en) Thermal barrier coating having a heat radiation absorbing topcoat
JPH06256926A (en) Coating film for heat shielding
US20100209733A1 (en) Hot Gas-Guided Component of a Turbomachine
CN116752071A (en) Low-heat-conductivity high-reflectivity composite coating and preparation method thereof

Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)