GB2130244A - Forming coatings by hot isostatic compaction - Google Patents

Forming coatings by hot isostatic compaction Download PDF

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Publication number
GB2130244A
GB2130244A GB08305965A GB8305965A GB2130244A GB 2130244 A GB2130244 A GB 2130244A GB 08305965 A GB08305965 A GB 08305965A GB 8305965 A GB8305965 A GB 8305965A GB 2130244 A GB2130244 A GB 2130244A
Authority
GB
United Kingdom
Prior art keywords
coating
article
binder
alloy
hot isostatic
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Withdrawn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
GB08305965A
Other versions
GB8305965D0 (en
Inventor
Ralph Ivor Conolly
Raymond George Ubank
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of GB8305965D0 publication Critical patent/GB8305965D0/en
Publication of GB2130244A publication Critical patent/GB2130244A/en
Withdrawn legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
    • C23C24/082—Coating starting from inorganic powder by application of heat or pressure and heat without intermediate formation of a liquid in the layer
    • C23C24/085—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/08—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
    • 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
    • C04B41/50—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials
    • C04B41/5025—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials with ceramic materials
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • 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

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Ceramic Engineering (AREA)
  • Metallurgy (AREA)
  • General Engineering & Computer Science (AREA)
  • Structural Engineering (AREA)
  • Composite Materials (AREA)
  • Inorganic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Laminated Bodies (AREA)

Abstract

A thermal barrier coating consists of a composite material of oxide particles of low thermal conductivity in a binder, densified and bonded to a surface of a component by hot isostatic pressing of the powders. The coating may be an oxide such as zirconia in a metal binder such as an alloy of chromium, aluminium and yttrium with cobalt and/or nickel (MCrAlY) or an oxide such as zirconia in a ceramic binder such as zirconium silicate which is ductile at elevated temperature. A metallic interlayer of an MCrAlY type of alloy may be used. The ceramic particles are preferably hollow spheres for a thermal barrier coating or where light weight is necessary. Other coatings described are abrasive, abradable or lightweight shrouds on rotor blade tips.

Description

SPECIFICATION Composite material coating and a method for the application thereof to articles The present invention relates to a composite material coating and a method by which it may be applied to an article.
Composite rnaterials, including ceramics or glasses, are used as thermal barrier coatings on components such as turbine blades and discs in gas turbine engines to reduce the rate of heat flow from the surrounding atmosphere into the component.
As conventionally applied, e.g. by flame spraying, the coatings are porous and the air gaps entrapped within the coatings significantly improve the thermal insulation characteristics. The air gaps, however, reduce the density of the coatings whereby they are less resistant to erosion and have relatively poor adhesion to the metal substrate.
Simiiar problems arise with adhesion of other composite coatings such as abrasive or abradable coatings on rotor blades and casings of gas turbine engines and which are used to minimise the effects of rubbing contact between the tips of the blades and the casings.
It is an object of the present invention to provide a method for the application of a composite material coating to an article and which provides good adhesion of the coating to the substrate while retaining the properties required in the coating.
According to the present invention a method of applying a composite coating to an article comprises the steps of mixing a ceramic material in particle form with a binder and compacting the mixture onto a surface of the article by a hot isostatic pressing operation.
Also according to the present invention a method of applying a thermal barrier coating to an article comprises the steps of mixing particles of a ceramic material having a lower thermal conductivity than the material of the article with a metal or glass binder, applying the mixture so formed as a coating to the article and subjecting the coated article to a hot isostatic pressing operation to compact the coating and bond it onto the article.
The ceramic particles are preferably oxide particles but may be other forms of ceramic, e.g. a Nitride, or a mixed oxide, e.g. Magnesium Zirconate or a Magnesium Silicate, depending on the properties required of the coating.
Preferably the ceramic particles are spherical and, particularly in the case of a thermal barrier coating, the spherical particles are hollow.
In one form of the invention in a coating particularly for use as a thermal barrier coating, the binder is a metal binder preferably of a high temperature and corrosion resistant alloy material, the oxide particles providing for a reduction in thermal conductivity of the composite coating, while the metal matrix, compacted on to the article surface by the hot isostatic pressing process, forms a diffusion bond with the metal substrate giving good adhesion. The metal matrix acts as a compliant layer between the relatively low expansion oxide material and the substrate material, and its composition is selected, inter alia, to assist in alleviating the mis-match between the thermal expansions of the two materials.
Examples of low thermal conductivity oxides are Zirconia, Alumina and Silica of which the preferred choice would be Zirconia because it has the lowest thermal conductivity.
It will be appreciated that Zirconia needs stabilising agents so that throughout this specification references to Zirconia should be taken to refer to stabilised Zirconia.
The metal binder is preferably an alloy, the composition of which is also affected by the environment in which it has to operate. In a gas turbine engine environment, properties such as oxidation resistance or general corrosion resistance are almost aiways required, so that preferred coating compositions would be a Nickel Aluminium alloy for oxidation resistance, or one of the known Chromium Aluminium Yttrium alloys with Cobalt or Nickel for general corrosion resistance.
In another form of the invention the binder is a non-metallic ductile binder, for example, a glass ceramic such as Zirconium Silicate. This further reduces the conductivity of the outer layer by eliminating any metal which is highly conductive, but may necessitate the addition of an intermediate layer to provide good adhesion to the metal substrate.
The thickness of the coating will obviously depend on the use to which it is to be put. For a thermal barrier coating the thickness may be of the order of 0.010 ins. to 0.020 ins. However, abradable or abrasive coatings, for example, on the tips of rotor blades are usually somewhat thicker and may be in the range 0.020 ins. to 0.04 ins. thick.
In one embodiment of the invention a lightweight shroud may be applied to the tip of a rotor blade and which is sufficiently thick to enable it to be machined to a specific shape.
The term "coating" is to be construed to include such a shroud.
The invention will now be more particularly described with reference to the accompanying drawings in which: Figure 1 illustrates part of a gas turbine engine blade having a coating provided in accordance with the present invention, Figure 2 illustrates part of a gas turbine engine blade having an alternative coating provided in accordance with the present invention, and, Figure 3 is an enlarged photo-micrograph of a coating of the present invention using mainly ceramic spheres and bonded to a metal substrate.
Referring now to the drawings, there is shown a gas turbine engine blade 1 having a composite thermal barrier coating 2 which consists of particles of Zirconia 3 in a Nickei-Aluminium binder.
The composite coating is applied as a slurry in one or more layers by spraying, dipping or any other suitable method. After drying, a further coating of Nickel is applied over the surface by electro-deposition. This further coating provides a gas tight pressure transmitting coating for the later hot isostatic pressing process, and its composition or method of application is not a critical part of the invention. For example, it may be applied by a plasma spray, or vapour deposition, or may be in the form of a close fitting metal bag which is welded and evacuated. In fact a glass coating may be substituted provided that there is no possibility of an inter-action with the composite coating.
After the further coating has been applied the component is placed in a vessel and hot isostatic pressure is applied thereto to bond the composite coating to the metal substrate.
The hot isostatic pressing process is known per se and is not described here in detail. It suffices to say that during the process the turbine blade is subjected to a pressure of between 10 and 25 ksi at a temperature in excess of 8000 C. Where possible, the hot isostatic pressing process may be combined with a required heat treatment of the blade to reduce the overall cost of the coated blade, since these heat treatment processes usually take place at temperatures between 8000 C and 13000 C.
After the hot isostatic pressing process is complete the metal or other outer coating is removed by a suitable process, e.g. chemical etching to expose the now densified thermal barrier coating.
The coating in this form of the invention is directly adhered to the metal substrate by a diffusion bond of the metal binder, and the metal binder is selected for oxidation resistance or corrosion resistance at high temperatures as well as for its thermal expansion properties. In the place of the Nickel-Aluminium coating described above, any of the conventional corrosion resistant coatings could be used, for example, alloy coatings known generaily under a class name of MCrAIY coatings where the Cr Al and Y are shorthand for Chromium, Aluminium and Yttrium and the M may be Cobalt, Nickel or a mixture of the two.
The inclusion of a metal binder in the thermal barrier coating does reduce the effectiveness of the coating due to the thermal conductivity of the metal.
However, the thermal conductivity of the coating may be further reduced if the ceramic particles are spherical and hollow. Using spherical particles a much closer control over the density of the coating may be achieved. There is a theoretical maximum volume of spheres which can be put in any fixed volume, and by using different sizes of spheres, the density of the coating may be graded to give greater metal volume near to the surface of the article and maximum ceramic volume at the outside. The maximum volume of the ceramic in the mixture is of the order of 70 per cent. We have found that a mixture of hollow Zirconia spheres will bond adequately with a Cobalt Chromium Aluminium Yttrium alloy binder and with a Nickelbased alloy substrate.
The thickness of the thermal barrier coating shown obviously must be optimised for the conditions to which it will be exposed but a useful range of thicknesses is from 0.010 ins. to 0.020 ins. Since there are likely to be conflicting requirements between the maximum attainable reduction in thermal conductivity, requiring a thicker coating, and minimum weight requiring a thinner coating, trial and error will be needed to determine the optimum thickness and properties.
If the maximum volume of ceramic spheres can be achieved so that they are all touching each other, it may be possible to leach some or all of them out of the coating to leave air spaces in the coating.
In the alternative form of the invention shown in Figure 2, a wholly non-metallic coating 10 is applied to the blade, and the adhesion is improved by the use of an intermediate coating 11 between the thermal barrier and the metal substrate.
Because the hot isostatic pressing process gives a dense coating, there is no longer any flexibility in the coating to deal with the thermal strains developed in it due to the temperature difference across it. In the alternative coating, therefore, the oxide material is embedded in a ductile binder to accommodate the thermal strain.
The thermal barrier coating is in this case a composite of Zirconia particles 12 which may be hollow spheres and a Zirconium Silicate binder, the Zirconium Silicate being very ductile at high temperature.
To improve adhesion and to reduce differential thermal expansion problems, an intermediate layer 11, preferably a metallic layer formed from one of the above-described MCrAIY alloy compositions is provided on the substrate. The metallic interlayer forms a compliant layer between the coating and the substrate and provides corrosion resistance.
Where the coating is to be an abradable or abrasive coating the shape of the particles is preferably irregular rather than spherical and the thickness may range up to 0.040 ins. The ceramic material for an abrasive coating is preferably Alumina or a Magnesium Silicate having the formula MgO2SiO2.
Once the oxide material is encapsulated in the binder, it may not be important whether or not the bond between the oxide material and the binder remains intact.
In Figure 3 it can be seen that the metal part of the composite coating (light areas) has infiltrated thoroughly between the ceramic particles (dark zones) and has formed a good bond with the substrate (large light area).
Although the invention has been described in relation to turbine blades for gas turbine engines, it is clearly applicable to any components in which thermal barrier or other coatings are at present in use or may be used in the future. One example of an alternative use is in thermal barrier coatings for combustion chamber liners in gas turbine engines.
A further example is a poppet valve for a piston engine.
The invention is not limited to the use of thin coatings. The composite coating material can be very lightweight if low density ceramic particles are used and particularly if hollow ceramic spheres are used. Also the metal binder gives very good adhesion to a substrate when bonded by a hot isostatic process.
The inventive concept herein disclosed can, therefore, include for example the attachment of a thick lightweight coating up to, say, 0.25 ins. thick to the tip of an aerofoil shaped rotor blade, as an oversized block which can subsequently be machined into the shape of a blade shroud. The word "coating" is thus used herein in a very broad sense.

Claims (18)

1. A method of applying a composite coating to an article comprises the steps of mixing a ceramic material in particle form with a binder and compacting the mixture onto a surface of the article by a hot isostatic pressing operation.
2. A method according to Claim 1 and in which the ceramic particles are of spherical shape.
3. A method according to Claim 2 and in which the ceramic particles are hollow spheres.
4. A method according to any preceding claim and in which the binder is a metal powder.
5. A method according to Claim 4 and in which the binder is an alloy of Nickel and Aluminium.
6. A method according to Claim 4 and in which the binder is an alloy of Chromium, Aluminium and Yttrium with Cobalt and/or Nickel.
7. A method according to Claim 1 and in which the binder is a ceramic material which is more ductile than the material of the ceramic particles at elevated temperature.
8. A method according to Claim 7 and in which the binder is Zirconium Silicate.
9. A method according to any one of Claims 1 to 6 and in which the ceramic particles are made from a material chosen from Zirconium, Alumina, Silica or a Magnesium Silicate having the chemical composition Mg02SiO2.
10. An article having a composite coating applied thereto in accordance with any one of the preceding claims.
1 An article according to Claim 10 and in which the coating is a thermal barrier coating.
12. An article according to Claim 10 and in which the coating is an abrasive coating.
13. An article according to Claim 10 and in which the coating is an abradable coating.
14. An article according to Claim 10 and in which the coating is a lightweight coating which is subsequently machined to form a required shape.
1 5. An article according to any one of Claims 10 to 14 and in which the article is an aerofoil shaped blade or vane for a gas turbine engine.
16. An article according to any one of Claims 1 2 to 14 and in which the article is an aerofoil shaped rotor blade for a gas turbine engine and the coating is applied to the tip of the blade.
1 7. A method of applying a thermal barrier coating to an article comprising the steps of mixing a quantity of hollow Zirconia spheres with a binder in the form of a powder of Nickel or Cobalt-based alloy, applying the mixture to the surface of the article and bonding it thereto by a hot isostatic pressing process.
18. A method of applying a composite coating to an article substantially as hereinbefore more particularly described and with reference to the accompanying drawings.
1 9. A coated article substantially as hereinbefore more particularly described and with reference to the accompanying drawings.
GB08305965A 1982-03-05 1983-03-04 Forming coatings by hot isostatic compaction Withdrawn GB2130244A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB8206582 1982-03-05

Publications (2)

Publication Number Publication Date
GB8305965D0 GB8305965D0 (en) 1983-04-07
GB2130244A true GB2130244A (en) 1984-05-31

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GB08305965A Withdrawn GB2130244A (en) 1982-03-05 1983-03-04 Forming coatings by hot isostatic compaction

Country Status (4)

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JP (1) JPS58194782A (en)
DE (1) DE3307749A1 (en)
FR (1) FR2522543A1 (en)
GB (1) GB2130244A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4692376A (en) * 1986-12-01 1987-09-08 Deutsch Daniel Harold Microporous coating for solid members to reduce stress, wear and fatigue at liquid interfaces
FR2640688A1 (en) * 1988-12-16 1990-06-22 United Technologies Corp PNEUMATIC CERAMIC SEALING DEVICE THAT CAN BE USED BY FRICTION, IN PARTICULAR FOR TURBOMOTORS
US5197852A (en) * 1990-05-31 1993-03-30 General Electric Company Nozzle band overhang cooling
WO2000052307A1 (en) * 1999-03-03 2000-09-08 Siemens Westinghouse Power Corporation High temperature erosion resistant, abradable thermal barrier composite coating
US6197424B1 (en) 1998-03-27 2001-03-06 Siemens Westinghouse Power Corporation Use of high temperature insulation for ceramic matrix composites in gas turbines
WO2002018130A1 (en) * 2000-08-29 2002-03-07 Amorphous Technologies International Article including a composite of unstabilized zirconium oxide particles in a metallic matrix, and its preparation
WO2007112727A2 (en) * 2006-04-06 2007-10-11 Mtu Aero Engines Gmbh Method for production of a honeycomb seal
DE102008058614A1 (en) * 2008-11-22 2010-05-27 Mtu Aero Engines Gmbh Producing a ceramic heat insulation layer on a high-temperature loaded or hot gas-loaded component of a gas turbine or aircraft engine, comprises applying a slicker on an area of a component surface having metallic adhesive mediator layer
US11686208B2 (en) 2020-02-06 2023-06-27 Rolls-Royce Corporation Abrasive coating for high-temperature mechanical systems

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3422138A1 (en) * 1984-06-14 1985-12-19 M.A.N. Maschinenfabrik Augsburg-Nürnberg AG, 8000 München METHOD AND COATING MATERIAL FOR PRODUCING CERAMIC / METAL COMPOSITE COATINGS
IL75564A (en) * 1984-06-25 1988-02-29 United Technologies Corp Abrasive surfaced article for high temperature service
DE3601794A1 (en) * 1986-01-22 1987-07-23 Georg Dr Ing Gliemeroth Thermal-shock-resistant ceramic material and process for its manufacture
AT526435B1 (en) * 2023-01-26 2024-03-15 Andritz Ag Maschf DRAINAGE ELEMENT FOR DRAINAGE OF A FIBER METAL
DE102023002027A1 (en) 2023-05-19 2024-01-18 Mercedes-Benz Group AG Method for producing a metal-ceramic composite component and the metal-ceramic composite component

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Publication number Priority date Publication date Assignee Title
GB1317956A (en) * 1969-05-28 1973-05-23 Gte Sylvania Inc Erosian resistant composites
GB1319144A (en) * 1969-12-29 1973-06-06 Plansee Metallwerk Outlet nozzles for hot gases
GB1380381A (en) * 1972-06-27 1975-01-15 Crucible Inc Method of manufacturing composite articles
GB1414413A (en) * 1973-05-18 1975-11-19 Contour Saws Bimetal saw blade stock and method of making the same
GB2073783A (en) * 1980-04-10 1981-10-21 Cameron Iron Works Inc Lining valves by hot isostatic pressing

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GB1238166A (en) * 1968-03-23 1971-07-07
CH575047A5 (en) * 1972-04-12 1976-04-30 Union Carbide Corp
GB1462385A (en) * 1974-01-31 1977-01-26 Toyo Kohan Co Ltd Manufacture of hollow metal bodies
DE2737248C2 (en) * 1977-08-18 1985-09-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München High strength component with a complex geometric shape and process for its manufacture
US4137619A (en) * 1977-10-03 1979-02-06 General Electric Company Method of fabricating composite structures for water cooled gas turbine components
NL7905973A (en) * 1979-08-03 1981-02-05 Skf Ind Trading & Dev METHOD FOR APPLYING A DENSE, HARD, TIGHT AND WEAR-RESISTANT COAT OF CERMETS OR CERAMIC MATERIAL ON A METAL ARTICLE AND OBTAINED THEREFORE.

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1317956A (en) * 1969-05-28 1973-05-23 Gte Sylvania Inc Erosian resistant composites
GB1319144A (en) * 1969-12-29 1973-06-06 Plansee Metallwerk Outlet nozzles for hot gases
GB1380381A (en) * 1972-06-27 1975-01-15 Crucible Inc Method of manufacturing composite articles
GB1414413A (en) * 1973-05-18 1975-11-19 Contour Saws Bimetal saw blade stock and method of making the same
GB2073783A (en) * 1980-04-10 1981-10-21 Cameron Iron Works Inc Lining valves by hot isostatic pressing

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4692376A (en) * 1986-12-01 1987-09-08 Deutsch Daniel Harold Microporous coating for solid members to reduce stress, wear and fatigue at liquid interfaces
FR2640688A1 (en) * 1988-12-16 1990-06-22 United Technologies Corp PNEUMATIC CERAMIC SEALING DEVICE THAT CAN BE USED BY FRICTION, IN PARTICULAR FOR TURBOMOTORS
US5197852A (en) * 1990-05-31 1993-03-30 General Electric Company Nozzle band overhang cooling
US6197424B1 (en) 1998-03-27 2001-03-06 Siemens Westinghouse Power Corporation Use of high temperature insulation for ceramic matrix composites in gas turbines
WO2000052307A1 (en) * 1999-03-03 2000-09-08 Siemens Westinghouse Power Corporation High temperature erosion resistant, abradable thermal barrier composite coating
US6235370B1 (en) 1999-03-03 2001-05-22 Siemens Westinghouse Power Corporation High temperature erosion resistant, abradable thermal barrier composite coating
WO2002018130A1 (en) * 2000-08-29 2002-03-07 Amorphous Technologies International Article including a composite of unstabilized zirconium oxide particles in a metallic matrix, and its preparation
US6376091B1 (en) * 2000-08-29 2002-04-23 Amorphous Technologies International Article including a composite of unstabilized zirconium oxide particles in a metallic matrix, and its preparation
KR100849385B1 (en) * 2000-08-29 2008-07-31 리퀴드메탈 테크노로지스 Article including a composite of unstabilized zirconium oxide particles in a metallic matrix, and its preparation
WO2007112727A2 (en) * 2006-04-06 2007-10-11 Mtu Aero Engines Gmbh Method for production of a honeycomb seal
WO2007112727A3 (en) * 2006-04-06 2007-12-21 Mtu Aero Engines Gmbh Method for production of a honeycomb seal
DE102008058614A1 (en) * 2008-11-22 2010-05-27 Mtu Aero Engines Gmbh Producing a ceramic heat insulation layer on a high-temperature loaded or hot gas-loaded component of a gas turbine or aircraft engine, comprises applying a slicker on an area of a component surface having metallic adhesive mediator layer
US11686208B2 (en) 2020-02-06 2023-06-27 Rolls-Royce Corporation Abrasive coating for high-temperature mechanical systems

Also Published As

Publication number Publication date
GB8305965D0 (en) 1983-04-07
JPS58194782A (en) 1983-11-12
DE3307749A1 (en) 1983-10-13
FR2522543A1 (en) 1983-09-09

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