CA2294261C - Method and apparatus for gas phase coating complex internal surfaces of hollow articles - Google Patents
Method and apparatus for gas phase coating complex internal surfaces of hollow articles Download PDFInfo
- Publication number
- CA2294261C CA2294261C CA002294261A CA2294261A CA2294261C CA 2294261 C CA2294261 C CA 2294261C CA 002294261 A CA002294261 A CA 002294261A CA 2294261 A CA2294261 A CA 2294261A CA 2294261 C CA2294261 C CA 2294261C
- Authority
- CA
- Canada
- Prior art keywords
- coating
- gas flow
- gas
- internal surfaces
- passages
- 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
Links
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
- C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
- C23C16/04—Coating on selected surface areas, e.g. using masks
- C23C16/045—Coating cavities or hollow spaces, e.g. interior of tubes; Infiltration of porous substrates
Landscapes
- Chemical & Material Sciences (AREA)
- General Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Chemical Vapour Deposition (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
- Spray Control Apparatus (AREA)
Abstract
A method and apparatus is provided to coat the internal surfaces of a hollow article having gas flow passages by supplying a coating gas to the passages with the coating gas flow rate to at least two of the passages controlled to a different rate to deposit a coating of desired thickness on the internal surfaces of each passage.
Description
Method And Apparatus For Gas Phase Coating Complex Internal Surfaces Of Hollow Articles Background of the Invention This invention relates to a method and apparatus for gas phase coating of complex internal surfaces of a hollow article, and, more particularly, gas phase deposition of metallic coatings, such as aluminum coatings, on the internal surfaces of a turbine engine component having at least two gas flow passages.
The aluminizing process is well-known in the art. The process is used to apply an aluminide coating to substrates, such as nickel-base superalloy articles. Some of these articles require a coating on internal surfaces. For some articles, such as turbine airfoils, the internal surfaces are complex and accessible only through narrow, restricted passageways. To cool these turbine airfoils, manufacturers are designing the internal surfaces to provide multiple gas passages.
Advanced turbine engines have resulted in the need for improved methods for coating the turbine airfoils. The internal surfaces of advanced turbine hardware are now subjected to such elevated temperatures that uncoated portions of such hardware are oxidized in service. As the oxide scale is formed in these narrow, serpentine passageways, a thickened scale grows from the surface, resulting in a narrowing of the passageway, which in turn reduces the effectiveness of the cooling air. The result is that the degradation process proceeds at an ever-increasing rate. This accelerated oxidation process can be stopped only by effectively coating the entire interior passageway of the part.
Several methods currently exist for coating the interior surfaces of articles, such as turbine airfoils. Each has limitations which may add significantly to the cost and time required to process the articles, or which may result in a failure to adequately coat the internal surfaces, particularly complex internal surfaces having multiple gas passages.
The aluminizing process is well-known in the art. The process is used to apply an aluminide coating to substrates, such as nickel-base superalloy articles. Some of these articles require a coating on internal surfaces. For some articles, such as turbine airfoils, the internal surfaces are complex and accessible only through narrow, restricted passageways. To cool these turbine airfoils, manufacturers are designing the internal surfaces to provide multiple gas passages.
Advanced turbine engines have resulted in the need for improved methods for coating the turbine airfoils. The internal surfaces of advanced turbine hardware are now subjected to such elevated temperatures that uncoated portions of such hardware are oxidized in service. As the oxide scale is formed in these narrow, serpentine passageways, a thickened scale grows from the surface, resulting in a narrowing of the passageway, which in turn reduces the effectiveness of the cooling air. The result is that the degradation process proceeds at an ever-increasing rate. This accelerated oxidation process can be stopped only by effectively coating the entire interior passageway of the part.
Several methods currently exist for coating the interior surfaces of articles, such as turbine airfoils. Each has limitations which may add significantly to the cost and time required to process the articles, or which may result in a failure to adequately coat the internal surfaces, particularly complex internal surfaces having multiple gas passages.
One of the methods currently used to coat articles is a pack diffusion process. In this process, the surfaces of the articles to be coated are embedded in a source of finely divided particles including an aluminum source, a volatile halide to act as a chemical transfer medium for the aluminum, and a ceramic phase, such as alumina powder, to prevent the agglomeration of the metallic components, and heated to an elevated temperature, usually at least 1200 F, all within a retort. Among the problems encountered is the accumulation of powdered particles in the narrow passages or openings of the parts prevents the flow of the aluminum gas through the narrow serpentine passageways. The result is a lack of a coating in the blocked passageways. Even in openings which are not blocked, it has been observed that the coating thickness tends to be thicker at or near the opening, and decreases rapidly with increasing distance from the opening. This nonuniform coating frequently results in unacceptable airfoils.
Another method used to coat articles is referred to as an over the pack process, such as described in Benden, U.S. Patent No. 4,132,816 dated January 2, 1979. This process is a simple modification of the pack process, in that the parts to be processed are suspended over the powdered material rather than embedded in the powdered material. In order to deposit the gaseous aluminum, produced by the elevated temperature decomposition of aluminum in the presence of the halide activator, onto the suspended parts, an inert gas is introduced into the retort and passed over the surfaces to be coated. This process is an improvement over pack processes since no powder mixture is in contact with the surfaces, and hence cannot block the openings to the narrow passageways. Although an improvement for coating internal passageways as compared to pack processing, the only control over the deposition rate as the reaction proceeds is control over the argon gas pressure, the chemistry of the powdered mixture, flow and modification of the reaction temperature and time at temperature. However, such a system lacks control over the coating of the internal passageways.
Another method used to coat articles is referred to as an over the pack process, such as described in Benden, U.S. Patent No. 4,132,816 dated January 2, 1979. This process is a simple modification of the pack process, in that the parts to be processed are suspended over the powdered material rather than embedded in the powdered material. In order to deposit the gaseous aluminum, produced by the elevated temperature decomposition of aluminum in the presence of the halide activator, onto the suspended parts, an inert gas is introduced into the retort and passed over the surfaces to be coated. This process is an improvement over pack processes since no powder mixture is in contact with the surfaces, and hence cannot block the openings to the narrow passageways. Although an improvement for coating internal passageways as compared to pack processing, the only control over the deposition rate as the reaction proceeds is control over the argon gas pressure, the chemistry of the powdered mixture, flow and modification of the reaction temperature and time at temperature. However, such a system lacks control over the coating of the internal passageways.
A modification of this method is described in Benden, U.S. Patent No.
4,148,275 dated April 10, 1979, in which the retort has two chambers for effecting simultaneous coating for the exterior and the interior portions of the article. Each chamber has separate powder mixtures. The improvement allows better control of the coating of the internal passageways by controlling the flow rate of the carrier gas into the chamber which contains the aluminum source, the inert filler and the metal halide. This control is in addition to control available through variations in temperature and time.
Another method of applying a coating to articles having narrow, serpentine passageways, such as turbine airfoils, is chemical vapor deposition, also referred to as CVD. In CVD, the part to be coated is placed in a retort.
An aluminum-bearing gas is generated at an elevated temperature in a reaction chamber outside of the retort, typically by reacting an aluminum source with an activator gas, such as a halide. The aluminum halide gas is then transported from the reaction chamber to the retort by a carrier gas (eg. H2 or argon). The aluminum halide gas then reacts at the surface of the article, depositing an aluminide coating. The resultant, halide-bearing gas is exhausted from the retort. See, for example, U.S. Patent 5,264,245.
While these gas phase coating methods are effective they do not accommodate for the complex internal surfaces containing multiple gas passages of modern airfoils resulting in a non-uniform intemal coating thereof.
There therefore exists a need for improved apparatus and improved processing methods for applying, gas phase coating on complex internal surfaces.
Summary of the Invention Briefly this invention provides a method and apparatus for coating the internal surfaces of a hollow article having at least two gas flow passages by supplying a coating gas to the passages with the coating gas flow rate to at least two of the passages controlled to a different rate to deposit a uniform coating of desired thickness on the internal surfaces of each passage.
Description of the Drawings FIG. I is a sectional view of a Siemens V84 first blade showing four gas flow passages.
FIG. II is a sectional view of a GE 90 blade showing three gas flow passages.
FIG. III is a sectional view of a manifold for supplying coating gas to each passage of the Siemens V84 first blade having supply tubes of different diameters.
FIG. IV is a sectional view of a manifold for supply coating gas to each passage of the GE 90 blade having supply tubes of different diameters.
FIG. V is partial sectional view of the coating gas supply manifold of FIG. III assembled with the Siemens V84 first blade of FIG. I to supply coating gas.
FIG. VI is a partial sectional view of the coating gas supply manifold of FIG. IV assembled with the GE 90 blade of FIG. II to supply coating gas.
FIG. VII is a sectional view of a coating set-up for practicing the present invention.
Detailed Description of the Invention In order to cool modern airfoils of gas turbine engines, these airfoils are being designed with complex internal surfaces having a plurality of gas flow paths (i.e. passages, channels, circuits or chambers) therein with differing gas flow characteristics. See, for example, U.S. Patent No. 5,591,007 which depicts a turbine airfoil with a plurality of serpentine cooling passages or circuits. Figures I and II depict airfoils having multiple gas flow passages therein, with Figure I showing a blade I having four gas flow passages 2-5 and Figure II showing a blade 6 having three gas flow passages 7-9. The requirements to properly coat the internal surfaces of each passage can vary.
By measuring the gas flow characteristics, the length of the passage, the number and size of cooling exit holes through each passage, the internal surface area to be coated, the volume of the passage and desired coating thickness of each passage the requirements to coat each passage is established.
Another method of applying a coating to articles having narrow, serpentine passageways, such as turbine airfoils, is chemical vapor deposition, also referred to as CVD. In CVD, the part to be coated is placed in a retort.
An aluminum-bearing gas is generated at an elevated temperature in a reaction chamber outside of the retort, typically by reacting an aluminum source with an activator gas, such as a halide. The aluminum halide gas is then transported from the reaction chamber to the retort by a carrier gas (eg. H2 or argon). The aluminum halide gas then reacts at the surface of the article, depositing an aluminide coating. The resultant, halide-bearing gas is exhausted from the retort. See, for example, U.S. Patent 5,264,245.
While these gas phase coating methods are effective they do not accommodate for the complex internal surfaces containing multiple gas passages of modern airfoils resulting in a non-uniform intemal coating thereof.
There therefore exists a need for improved apparatus and improved processing methods for applying, gas phase coating on complex internal surfaces.
Summary of the Invention Briefly this invention provides a method and apparatus for coating the internal surfaces of a hollow article having at least two gas flow passages by supplying a coating gas to the passages with the coating gas flow rate to at least two of the passages controlled to a different rate to deposit a uniform coating of desired thickness on the internal surfaces of each passage.
Description of the Drawings FIG. I is a sectional view of a Siemens V84 first blade showing four gas flow passages.
FIG. II is a sectional view of a GE 90 blade showing three gas flow passages.
FIG. III is a sectional view of a manifold for supplying coating gas to each passage of the Siemens V84 first blade having supply tubes of different diameters.
FIG. IV is a sectional view of a manifold for supply coating gas to each passage of the GE 90 blade having supply tubes of different diameters.
FIG. V is partial sectional view of the coating gas supply manifold of FIG. III assembled with the Siemens V84 first blade of FIG. I to supply coating gas.
FIG. VI is a partial sectional view of the coating gas supply manifold of FIG. IV assembled with the GE 90 blade of FIG. II to supply coating gas.
FIG. VII is a sectional view of a coating set-up for practicing the present invention.
Detailed Description of the Invention In order to cool modern airfoils of gas turbine engines, these airfoils are being designed with complex internal surfaces having a plurality of gas flow paths (i.e. passages, channels, circuits or chambers) therein with differing gas flow characteristics. See, for example, U.S. Patent No. 5,591,007 which depicts a turbine airfoil with a plurality of serpentine cooling passages or circuits. Figures I and II depict airfoils having multiple gas flow passages therein, with Figure I showing a blade I having four gas flow passages 2-5 and Figure II showing a blade 6 having three gas flow passages 7-9. The requirements to properly coat the internal surfaces of each passage can vary.
By measuring the gas flow characteristics, the length of the passage, the number and size of cooling exit holes through each passage, the internal surface area to be coated, the volume of the passage and desired coating thickness of each passage the requirements to coat each passage is established.
To meet these requirements and based on these measurements, the coating gas flow rate to each passage relative to the other is determined. These measurements are used to adjust the coating gas flow rate into each passage to have the desired volume of coating gas exit from each passage. A ratio of the gas flow rates of each internal passage modified to take into account the quantity and size of cooling exit holes in each passage can be used to determine coating gas flow requirements of each passage. In one embodiment the relative coating gas flow rate into each passage is controlled to approximately the relative gas flow rates of each gas flow passage. Even after these calculations, empirical experiments can be used to fine tune the final adjustments on coating gas flow rates into each passage to get the desired coating thickness in each passage.
Based on the coating requirements, the coating gas flow rate to at least two of the passages is separately controlled to a different rate to deliver the appropriate flow rate and volume of coating gas to each internal passage providing the appropriate coating thickness for each passage. Generally, the flow rate is adjusted so that the coating thickness of the internal surfaces of each passage is approximately the same, although it is possible to adjust the flow rate so the internal surfaces of each passage can have a different coating thickness. The means for controlling the gas flow rate can vary and can be, for example, utilizing different size (ie. orifice or diameter) tubes for supplying the coating gas into each passage from a common coating gas supply source, or a valve to control the flow rate to at least one of the passages in the article.
Figure III shows a supply manifold 10 provided with supply tubes 11-14 for supplying coating gas into the corresponding gas flow passages 2-5 of Figure I, as shown in Figure V. The diameters of each of the supply tubes 11-14 are restricted to control the flow of coating gas therethrough. Likewise, Figure IV shows a supply manifold 15 provided with supply tubes 16-18 for supplying coating gas into the corresponding gas flow passages 7-9 of Figure II, as shown in Figure VI. In each of the Figures III-IV tube 19 is used to supply the coating gas to the supply manifold from a coating gas supply.
Based on the coating requirements, the coating gas flow rate to at least two of the passages is separately controlled to a different rate to deliver the appropriate flow rate and volume of coating gas to each internal passage providing the appropriate coating thickness for each passage. Generally, the flow rate is adjusted so that the coating thickness of the internal surfaces of each passage is approximately the same, although it is possible to adjust the flow rate so the internal surfaces of each passage can have a different coating thickness. The means for controlling the gas flow rate can vary and can be, for example, utilizing different size (ie. orifice or diameter) tubes for supplying the coating gas into each passage from a common coating gas supply source, or a valve to control the flow rate to at least one of the passages in the article.
Figure III shows a supply manifold 10 provided with supply tubes 11-14 for supplying coating gas into the corresponding gas flow passages 2-5 of Figure I, as shown in Figure V. The diameters of each of the supply tubes 11-14 are restricted to control the flow of coating gas therethrough. Likewise, Figure IV shows a supply manifold 15 provided with supply tubes 16-18 for supplying coating gas into the corresponding gas flow passages 7-9 of Figure II, as shown in Figure VI. In each of the Figures III-IV tube 19 is used to supply the coating gas to the supply manifold from a coating gas supply.
The coating gas can provide for the gas phase deposition of metallic coatings, such as aluminides, which are particularly useful in protecting the internal surfaces of turbine airfoils. The gaseous aluminum coating gas can be supplied by an above the pack process (as generally described in U.S. Patent 4,148,275) or chemical vapor deposition process as detailed above. For example, a coating mixture including aluminum powder, aluminum oxide and aluminum fluoride (AIF3 activator) is heated to approximately 1975 F with a carrier gas of hydrogen or argon to deliver the coating gas to the part.
A coating set-up 20 is shown in Figure VII. This set-up will coat both the external and internal surfaces of the airfoils. In this set-up the airfoil and supply manifold shown in Fig. VI are exemplified. A gaseous metallic coating gas is generated from upper reactor bed 22 to coat the external surfaces of the blade 6 and lower reactor bed 23 to coat the internal surfaces. A carrier gas is introduced through tube 24 to carry the coating gas through tubes 19 into supply manifold 15 and through supply tubes 16-18 into the internal passages of the blade 6.
Example 1 The Siemens V84 First Blade illustrated in Figure I has four gas flow passages 2-5 with the following gas flow characteristics. It is noted that passages 3 and 4 are crosslinked (ie. by gas flow orifices). The coating gas supply manifold 10 shown in Figure III utilized supply tubes 11-14 with sizes (i.e. different diameters) as per the indicated orifice areas to control the flow rate into each passage to provide the desired uniform coating thickness in each passage.
Passage Avg. Passage Gas Floa Supply Tube Supply Tube ] ength (in.) pds/sec. Orifice Area (in~) 2 15 0.000108 0.077 11 3 5 0.000044 0.050 12 4 10 0.000044 0.040 13 5 0.000023 0.035 14 An above the pack raw materials coating mixture of 2% aluminum fluoride, 5% aluminum and 93% alumina is used to fill the lower reactor bed only in a coating set-up as illustrated in Fig. VII loaded with 20 blades to coat only the intemal surfaces of the blades. Typical amounts are approximately 35 pounds of material in the lower reactor bed. A diffusor gas flow rate of 200 cubic ft. per hour is used to carry the coating gases into the parts.
Approximately 10 cubic ft. per hour of argon is used as the carrier gas to deliver the coating gases into each part. A flow rate of 100 cu. ft./hour is also used as a purge gas. The assembly is heated to 1975 F +/- 25 F and held at temperature for four hours while the coating gas flow is maintained through the parts. .
A uniform aluminide coating thickness of 1.5 mils +/- 1.0 mils was observed in each passage.
Example 2 The GE 90 first stage turbine blade illustrated in Figure II has three passages 7-9 with the following gas flow characteristics. The coating gas supply manifold 15 shown in Figure IV utilized supply tubes with different sizes (i.e. diameters) as per the indicated orifice areas to control the flow rate into each passage to provide the desired uniform coating thickness in each passage.
Pasaagc Avg. Passage Gas Flow Supply Tube Supply Tube Length (in.) pda/acc. Ori6ce Area (in') 7 6.7 0.000030 0.006 16 8 15.3 0.000179 0.04 17 6.7 0.000030 0.006 18 :d I I
An above the pack raw materials coating mixture of 2% aluminum fluoride, 3% aluminum and 95% alumina is used to fill the reactor bed in a coating set up as illustrated in Fig. VII loaded with 35 blades. Typical amounts are approximately 30 pounds of material in the lower reactor bed for the internal feed. The raw materials coating mixture used to coat the externai portions of the blade have a mixture of 3% aluminum trifluoride and 7%
aluminum with a total mixture by weight of 40 pounds in the upper reactor bed for the external surface. A gas flow rate of 150 cubic ft. per hour is used as the carrier gas to carry the coating gases into the parts. Approximately 4.3 cubic feet per hour of argon is used as the carrier gas to deliver the coating gases into each part. A flow rate of 100 cubic feet/hour is also used as a purge gas. The assembly is heated to 1975 F +/- 25 F and held at temperature for 5.5 hours while the coating gas flow is maintained through the parts.
A uniform aluminide coating thickness of 1.5 mils +/- 1.0 mils was observed in each passage.
A coating set-up 20 is shown in Figure VII. This set-up will coat both the external and internal surfaces of the airfoils. In this set-up the airfoil and supply manifold shown in Fig. VI are exemplified. A gaseous metallic coating gas is generated from upper reactor bed 22 to coat the external surfaces of the blade 6 and lower reactor bed 23 to coat the internal surfaces. A carrier gas is introduced through tube 24 to carry the coating gas through tubes 19 into supply manifold 15 and through supply tubes 16-18 into the internal passages of the blade 6.
Example 1 The Siemens V84 First Blade illustrated in Figure I has four gas flow passages 2-5 with the following gas flow characteristics. It is noted that passages 3 and 4 are crosslinked (ie. by gas flow orifices). The coating gas supply manifold 10 shown in Figure III utilized supply tubes 11-14 with sizes (i.e. different diameters) as per the indicated orifice areas to control the flow rate into each passage to provide the desired uniform coating thickness in each passage.
Passage Avg. Passage Gas Floa Supply Tube Supply Tube ] ength (in.) pds/sec. Orifice Area (in~) 2 15 0.000108 0.077 11 3 5 0.000044 0.050 12 4 10 0.000044 0.040 13 5 0.000023 0.035 14 An above the pack raw materials coating mixture of 2% aluminum fluoride, 5% aluminum and 93% alumina is used to fill the lower reactor bed only in a coating set-up as illustrated in Fig. VII loaded with 20 blades to coat only the intemal surfaces of the blades. Typical amounts are approximately 35 pounds of material in the lower reactor bed. A diffusor gas flow rate of 200 cubic ft. per hour is used to carry the coating gases into the parts.
Approximately 10 cubic ft. per hour of argon is used as the carrier gas to deliver the coating gases into each part. A flow rate of 100 cu. ft./hour is also used as a purge gas. The assembly is heated to 1975 F +/- 25 F and held at temperature for four hours while the coating gas flow is maintained through the parts. .
A uniform aluminide coating thickness of 1.5 mils +/- 1.0 mils was observed in each passage.
Example 2 The GE 90 first stage turbine blade illustrated in Figure II has three passages 7-9 with the following gas flow characteristics. The coating gas supply manifold 15 shown in Figure IV utilized supply tubes with different sizes (i.e. diameters) as per the indicated orifice areas to control the flow rate into each passage to provide the desired uniform coating thickness in each passage.
Pasaagc Avg. Passage Gas Flow Supply Tube Supply Tube Length (in.) pda/acc. Ori6ce Area (in') 7 6.7 0.000030 0.006 16 8 15.3 0.000179 0.04 17 6.7 0.000030 0.006 18 :d I I
An above the pack raw materials coating mixture of 2% aluminum fluoride, 3% aluminum and 95% alumina is used to fill the reactor bed in a coating set up as illustrated in Fig. VII loaded with 35 blades. Typical amounts are approximately 30 pounds of material in the lower reactor bed for the internal feed. The raw materials coating mixture used to coat the externai portions of the blade have a mixture of 3% aluminum trifluoride and 7%
aluminum with a total mixture by weight of 40 pounds in the upper reactor bed for the external surface. A gas flow rate of 150 cubic ft. per hour is used as the carrier gas to carry the coating gases into the parts. Approximately 4.3 cubic feet per hour of argon is used as the carrier gas to deliver the coating gases into each part. A flow rate of 100 cubic feet/hour is also used as a purge gas. The assembly is heated to 1975 F +/- 25 F and held at temperature for 5.5 hours while the coating gas flow is maintained through the parts.
A uniform aluminide coating thickness of 1.5 mils +/- 1.0 mils was observed in each passage.
Claims (9)
1. A process for coating the internal surfaces of a hollow article having at least two gas flow passages comprising:
supplying a coating gas into the gas flow passages of the article with the coating gas flow rate to at least two of the gas flow passages separately controlled to a different rate to deposit a coating of desired thickness on the internal surfaces of each of the gas flow passages.
supplying a coating gas into the gas flow passages of the article with the coating gas flow rate to at least two of the gas flow passages separately controlled to a different rate to deposit a coating of desired thickness on the internal surfaces of each of the gas flow passages.
2. Process of claim 1 wherein the gas flow rate is controlled to a different rate by supplying the coating gas into each gas flow passage through a supply tube with a different orifice size.
3. Process of claim 2 wherein at least two of the gas flow passages have different gas flow rates.
4. Process of claim 1 wherein the coating gas flow rate is controlled to provide approximately the same thickness coating in all of the gas flow passages.
5. Process of claim 1 wherein a valve controls the coating gas flow rate to at least one of the gas flow passages.
6. Process of claim 1 wherein the hollow article is an airfoil of a gas turbine engine.
7. Process of claim 6 wherein the coating gas provides an aluminide coating.
8. Process of claim 3 wherein the relative coating gas flow rate into each gas flow passage is controlled to approximately the relative gas flow rate of each gas flow passage.
9. An apparatus for coating the internal surfaces of a hollow article having at least two gas flow passages, comprising:
a, an enclosure for generating a coating gas;
b. means for supplying the coating gas into the gas flow passages of the article;
c. means for controlling the coating gas flow rate into at least two of the gas flow passages to a different rate to deposit a coating of desired thickness on the internal surfaces of each of the gas flow passages.
a, an enclosure for generating a coating gas;
b. means for supplying the coating gas into the gas flow passages of the article;
c. means for controlling the coating gas flow rate into at least two of the gas flow passages to a different rate to deposit a coating of desired thickness on the internal surfaces of each of the gas flow passages.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US08/896,579 | 1997-07-18 | ||
| US08/896,579 US5928725A (en) | 1997-07-18 | 1997-07-18 | Method and apparatus for gas phase coating complex internal surfaces of hollow articles |
| PCT/US1998/009420 WO1999003599A1 (en) | 1997-07-18 | 1998-05-08 | Method and apparatus for gas phase coating complex internal surfaces of hollow articles |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2294261A1 CA2294261A1 (en) | 1999-01-28 |
| CA2294261C true CA2294261C (en) | 2007-12-18 |
Family
ID=25406443
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002294261A Expired - Lifetime CA2294261C (en) | 1997-07-18 | 1998-05-08 | Method and apparatus for gas phase coating complex internal surfaces of hollow articles |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US5928725A (en) |
| EP (1) | EP1017510B1 (en) |
| JP (1) | JP2001512181A (en) |
| KR (1) | KR100556273B1 (en) |
| CN (1) | CN1120756C (en) |
| AU (1) | AU1059899A (en) |
| CA (1) | CA2294261C (en) |
| DE (1) | DE69829488T2 (en) |
| WO (1) | WO1999003599A1 (en) |
Families Citing this family (50)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6183811B1 (en) * | 1998-12-15 | 2001-02-06 | General Electric Company | Method of repairing turbine airfoils |
| US6224941B1 (en) * | 1998-12-22 | 2001-05-01 | General Electric Company | Pulsed-vapor phase aluminide process for high temperature oxidation-resistant coating applications |
| US6273678B1 (en) * | 1999-08-11 | 2001-08-14 | General Electric Company | Modified diffusion aluminide coating for internal surfaces of gas turbine components |
| US6332926B1 (en) | 1999-08-11 | 2001-12-25 | General Electric Company | Apparatus and method for selectively coating internal and external surfaces of an airfoil |
| US6283714B1 (en) * | 1999-08-11 | 2001-09-04 | General Electric Company | Protection of internal and external surfaces of gas turbine airfoils |
| US6296447B1 (en) * | 1999-08-11 | 2001-10-02 | General Electric Company | Gas turbine component having location-dependent protective coatings thereon |
| US6485262B1 (en) * | 2001-07-06 | 2002-11-26 | General Electric Company | Methods and apparatus for extending gas turbine engine airfoils useful life |
| US6793966B2 (en) | 2001-09-10 | 2004-09-21 | Howmet Research Corporation | Chemical vapor deposition apparatus and method |
| FR2830874B1 (en) * | 2001-10-16 | 2004-01-16 | Snecma Moteurs | METHOD OF PROTECTION BY ALUMINIZATION OF METAL PARTS OF TURBOMACHINES PROVIDED WITH HOLES AND CAVITES |
| US6986814B2 (en) * | 2001-12-20 | 2006-01-17 | General Electric Company | Gas distributor for vapor coating method and container |
| KR100438034B1 (en) * | 2002-04-25 | 2004-07-01 | 김조권 | The coating device of pipe using fiber reinforced plastic |
| US6932570B2 (en) * | 2002-05-23 | 2005-08-23 | General Electric Company | Methods and apparatus for extending gas turbine engine airfoils useful life |
| US7008553B2 (en) * | 2003-01-09 | 2006-03-07 | General Electric Company | Method for removing aluminide coating from metal substrate and turbine engine part so treated |
| US6929825B2 (en) * | 2003-02-04 | 2005-08-16 | General Electric Company | Method for aluminide coating of gas turbine engine blade |
| US7026011B2 (en) * | 2003-02-04 | 2006-04-11 | General Electric Company | Aluminide coating of gas turbine engine blade |
| US20040180232A1 (en) * | 2003-03-12 | 2004-09-16 | General Electric Company | Selective region vapor phase aluminided superalloy articles |
| US7094450B2 (en) * | 2003-04-30 | 2006-08-22 | General Electric Company | Method for applying or repairing thermal barrier coatings |
| US6896488B2 (en) * | 2003-06-05 | 2005-05-24 | General Electric Company | Bond coat process for thermal barrier coating |
| US6905730B2 (en) * | 2003-07-08 | 2005-06-14 | General Electric Company | Aluminide coating of turbine engine component |
| US7163718B2 (en) | 2003-10-15 | 2007-01-16 | General Electric Company | Method of selective region vapor phase aluminizing |
| US6989174B2 (en) * | 2004-03-16 | 2006-01-24 | General Electric Company | Method for aluminide coating a hollow article |
| CA2560834C (en) * | 2004-03-23 | 2014-05-27 | Velocys, Inc. | Tailored and uniform coatings in microchannel apparatus |
| US7874432B2 (en) * | 2004-03-23 | 2011-01-25 | Velocys | Protected alloy surfaces in microchannel apparatus and catalysts, alumina supported catalysts, catalyst intermediates, and methods of forming catalysts and microchannel apparatus |
| WO2005103324A1 (en) * | 2004-04-19 | 2005-11-03 | Siemens Aktiengesellschaft | Process for coating the inside of a through-channel |
| US7255940B2 (en) | 2004-07-26 | 2007-08-14 | General Electric Company | Thermal barrier coatings with high fracture toughness underlayer for improved impact resistance |
| US7875119B2 (en) * | 2004-10-01 | 2011-01-25 | United Technologies Corporation | Apparatus and method for coating an article |
| US20060093849A1 (en) * | 2004-11-02 | 2006-05-04 | Farmer Andrew D | Method for applying chromium-containing coating to metal substrate and coated article thereof |
| EP1655091A1 (en) * | 2004-11-09 | 2006-05-10 | Siemens Aktiengesellschaft | Method for electrolytically processing a workpiece and workpiece having a through hole |
| US7252480B2 (en) * | 2004-12-17 | 2007-08-07 | General Electric Company | Methods for generation of dual thickness internal pack coatings and objects produced thereby |
| US20060216415A1 (en) * | 2005-03-24 | 2006-09-28 | United Technologies Corporation | Vapor aluminide coating gas manifold |
| US20070039176A1 (en) | 2005-08-01 | 2007-02-22 | Kelly Thomas J | Method for restoring portion of turbine component |
| EP1772533A1 (en) * | 2005-10-07 | 2007-04-11 | Siemens Aktiengesellschaft | Apparatus for coating inner surfaces, retort and method therefor |
| WO2007047373A1 (en) * | 2005-10-13 | 2007-04-26 | Velocys, Inc. | Microchannel apparatus comprising a platinum aluminide layer and chemical processes using the apparatus |
| US7700154B2 (en) * | 2005-11-22 | 2010-04-20 | United Technologies Corporation | Selective aluminide coating process |
| EP1806426A1 (en) * | 2006-01-09 | 2007-07-11 | Siemens Aktiengesellschaft | Supporting device for metallic turbine components |
| US8025730B2 (en) * | 2007-07-09 | 2011-09-27 | United Technologies Corporation | Apparatus and method for coating internal surfaces of a turbine engine component |
| EP2133572B1 (en) | 2008-06-12 | 2017-11-15 | General Electric Company | Centrifugal compressor for wet gas environments and method of manufacture |
| GB0902633D0 (en) | 2009-02-18 | 2009-04-01 | Rolls Royce Plc | A method and an arrangement for vapour phase coating of an internal surface of at least one hollow article |
| SG169243A1 (en) * | 2009-08-21 | 2011-03-30 | United Technologies Corp | Applying vapour phase aluminide coating on airfoil internal cavities using improved method |
| EP2360288A1 (en) * | 2010-02-23 | 2011-08-24 | Siemens Aktiengesellschaft | Process for the adjustment of coolant consumption inside an actively cooled component and component |
| EP2476776B1 (en) * | 2011-01-18 | 2015-08-12 | Siemens Aktiengesellschaft | Method for adjusting the coolant consumption within actively cooled components |
| DE102011108771B3 (en) * | 2011-07-28 | 2012-09-27 | Mtu Aero Engines Gmbh | Process for producing a localized diffusion layer and reactor therefor |
| US8636890B2 (en) | 2011-09-23 | 2014-01-28 | General Electric Company | Method for refurbishing PtAl coating to turbine hardware removed from service |
| US9771644B2 (en) * | 2013-11-08 | 2017-09-26 | Praxair S.T. Technology, Inc. | Method and apparatus for producing diffusion aluminide coatings |
| EP3059394B1 (en) * | 2015-02-18 | 2019-10-30 | Ansaldo Energia Switzerland AG | Turbine blade and set of turbine blades |
| US9844799B2 (en) | 2015-12-16 | 2017-12-19 | General Electric Company | Coating methods |
| KR102116875B1 (en) * | 2018-02-26 | 2020-05-29 | 두산중공업 주식회사 | Internal cooling channel vapor coating device and method |
| KR102164394B1 (en) * | 2018-03-07 | 2020-10-12 | 두산중공업 주식회사 | Method for surface treatment of turbine parts and surface-treated turbine parts by the same method |
| US20190284940A1 (en) * | 2018-03-16 | 2019-09-19 | United Technologies Corporation | Turbine airfoil with internals coated by atomic layer deposition |
| US20200010946A1 (en) * | 2018-07-05 | 2020-01-09 | The Board Of Trustees Of The University Of Illinois | Ferrous structural component for use in fouling and corrosive environments, and method of making and using a ferrous structural component |
Family Cites Families (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2886469A (en) * | 1954-05-31 | 1959-05-12 | Siemens Planiawerke Ag | Method of coating metallic bodies with aluminum utilizing vaporous sub-chlorides |
| US3079276A (en) * | 1960-10-14 | 1963-02-26 | Union Carbide Corp | Vapor diffusion coating process |
| US3335028A (en) * | 1963-11-26 | 1967-08-08 | Ritter Pfaudler Corp | Complex fluoro salt cementation method for coating refractory metallic substrates |
| FR1433497A (en) * | 1965-02-16 | 1966-04-01 | Snecma | Process for depositing a protective layer on a metal part by a vapor phase method |
| US3694255A (en) * | 1970-06-03 | 1972-09-26 | Chromalloy American Corp | Method for coating heat resistant alloys |
| US3764373A (en) * | 1972-02-07 | 1973-10-09 | Chromalloy American Corp | Diffusion coating of metals |
| US4132816A (en) * | 1976-02-25 | 1979-01-02 | United Technologies Corporation | Gas phase deposition of aluminum using a complex aluminum halide of an alkali metal or an alkaline earth metal as an activator |
| DE2718518C3 (en) * | 1977-04-26 | 1984-04-19 | Siemens Ag, 1000 Berlin Und 8000 Muenchen | Process for depositing a layer on the inside of cavities in a workpiece |
| US4347267A (en) * | 1979-10-31 | 1982-08-31 | Alloy Surfaces Company, Inc. | Diffusion coating through restrictions |
| US4292871A (en) * | 1979-02-01 | 1981-10-06 | The L. S. Starrett Company | Welded edge band saw tooth geometry |
| US4501776A (en) * | 1982-11-01 | 1985-02-26 | Turbine Components Corporation | Methods of forming a protective diffusion layer on nickel, cobalt and iron base alloys |
| GB2167773A (en) * | 1984-11-29 | 1986-06-04 | Secr Defence | Improvements in or relating to coating processes |
| US5217757A (en) * | 1986-11-03 | 1993-06-08 | United Technologies Corporation | Method for applying aluminide coatings to superalloys |
| FR2633641B1 (en) * | 1988-06-30 | 1993-02-05 | Snecma | METHOD AND DEVICE FOR THE SIMULTANEOUS PROTECTION OF INTERNAL AND EXTERNAL SURFACES, IN PARTICULAR BY ALUMINIZING HOT-RESISTANT ALLOY PARTS, BASED ON NI, CO OR FE |
| US5071678A (en) * | 1990-10-09 | 1991-12-10 | United Technologies Corporation | Process for applying gas phase diffusion aluminide coatings |
| DE4035790C1 (en) * | 1990-11-10 | 1991-05-08 | Mtu Muenchen Gmbh | |
| US5221354A (en) * | 1991-11-04 | 1993-06-22 | General Electric Company | Apparatus and method for gas phase coating of hollow articles |
| US5264245A (en) * | 1991-12-04 | 1993-11-23 | Howmet Corporation | CVD method for forming uniform coatings |
| US5591007A (en) * | 1995-05-31 | 1997-01-07 | General Electric Company | Multi-tier turbine airfoil |
-
1997
- 1997-07-18 US US08/896,579 patent/US5928725A/en not_active Expired - Lifetime
-
1998
- 1998-05-08 WO PCT/US1998/009420 patent/WO1999003599A1/en active IP Right Grant
- 1998-05-08 EP EP98953150A patent/EP1017510B1/en not_active Expired - Lifetime
- 1998-05-08 KR KR1019997011952A patent/KR100556273B1/en not_active IP Right Cessation
- 1998-05-08 CA CA002294261A patent/CA2294261C/en not_active Expired - Lifetime
- 1998-05-08 JP JP2000502882A patent/JP2001512181A/en active Pending
- 1998-05-08 CN CN98806861A patent/CN1120756C/en not_active Expired - Lifetime
- 1998-05-08 AU AU10598/99A patent/AU1059899A/en not_active Abandoned
- 1998-05-08 DE DE69829488T patent/DE69829488T2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| CA2294261A1 (en) | 1999-01-28 |
| EP1017510B1 (en) | 2005-03-23 |
| AU1059899A (en) | 1999-02-10 |
| CN1261829A (en) | 2000-08-02 |
| EP1017510A4 (en) | 2004-04-28 |
| KR20010013930A (en) | 2001-02-26 |
| EP1017510A1 (en) | 2000-07-12 |
| KR100556273B1 (en) | 2006-03-03 |
| JP2001512181A (en) | 2001-08-21 |
| CN1120756C (en) | 2003-09-10 |
| US5928725A (en) | 1999-07-27 |
| DE69829488T2 (en) | 2006-02-09 |
| WO1999003599A1 (en) | 1999-01-28 |
| DE69829488D1 (en) | 2005-04-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2294261C (en) | Method and apparatus for gas phase coating complex internal surfaces of hollow articles | |
| US5221354A (en) | Apparatus and method for gas phase coating of hollow articles | |
| US7429403B2 (en) | Gas distributor for vapor coating method and container | |
| US6224941B1 (en) | Pulsed-vapor phase aluminide process for high temperature oxidation-resistant coating applications | |
| US6929825B2 (en) | Method for aluminide coating of gas turbine engine blade | |
| US8118941B2 (en) | Semiconductor processing parts having apertures with deposited coatings and methods for forming the same | |
| US20010021414A1 (en) | CVD method | |
| JPH04263073A (en) | Method and device for forming gas phase diffusing aluminide film | |
| JP2014208997A (en) | Vapor phase aluminizing process of metallic component and donor liner of turbomachine, and turbomachine blade including such liner | |
| US7927656B2 (en) | Method and apparatus for controlling diffusion coating of internal passages | |
| US7026011B2 (en) | Aluminide coating of gas turbine engine blade | |
| EP1705262B1 (en) | Gas manifold with a flow divider | |
| US20030072878A1 (en) | Method of protecting metal parts of turbomachines having holes and cavities by aluminizing the parts | |
| US20080107808A1 (en) | Method and an apparatus for the coating of a base body | |
| JPH01159376A (en) | Method and device for coating inside of heat-resistant member with aluminum |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKEX | Expiry |
Effective date: 20180508 |
|
| MKEX | Expiry |
Effective date: 20180508 |