Patent Grant
7093993
This invention relates to apparatus and methods for cleaning and repairing of thermal barrier coatings for components exposed to high temperatures, such as the hostile thermal environment of a gas turbine engine. More particularly, this invention is directed to tools and methods for cleaning and priming of specially coated surfaces on gas-turbine powered aircraft, such as a thermal barrier coating that has suffered localized spallation due to thermal fatigue and stress, poor coating processes, coating defects, localized damage, impact damage and other mechanical damage.
Higher operating temperatures for gas turbine engines are continuously sought in order to increase their efficiency. However, as operating temperatures increase, the high temperature durability of the components of the engine must correspondingly increase. Significant advances in high temperature capabilities have been achieved through the formulation of nickel and cobalt-base superalloys. Nonetheless, when used to form components of the turbine, combustor and augmentor sections of a gas turbine engine, such alloys alone are often susceptible to damage by oxidation and hot corrosion attack and may not retain adequate mechanical properties. For this reason, these components are often protected by an environmental and/or thermal-insulating coating, the latter of which is termed a thermal barrier coating (TBC) system. Ceramic materials, and particularly yttria-stabilized zirconia (YSZ), are widely used as a thermal barrier coating (TBC), or topcoat, of TBC systems used on gas turbine engine components. These particular materials are widely employed because they can be readily deposited by plasma spray, flame spray and vapor deposition techniques. A commonly used type of TBC is a coating based on zirconia stabilized with yttria, for example about 93 wt. % zirconia stabilized with about 7 wt. % yttria. This general type of TBC has been reported in such United States patents as U.S. Pat. No. 4,055,705, U.S. Pat. No. 4,328,285, and U.S. Pat. No. 5,236,745, which are incorporated herein by reference.
During routine operation of the engine and aircraft, the coated surfaces, particularly those in or near the flowpath (intake, compression, combustion and exhaust) of the gas turbine engine, are subjected to heat, pressure and other forces can cause the coating to suffer localized damage such as spallation due to thermal fatigue and stress, defects, impact damage and other mechanical damage. For these reasons, the coated surfaces must be routinely inspected and meticulously repaired to avoid further damage to the coated surfaces and the underlying substrate. Maintenance personnel must inspect all visible surfaces, often requiring the use of flashlights, mirrors, and other inspection tools to access remote areas such as the small cooling holes and exhaust ports in a gas turbine engine. In the case of aircraft turbine engines and large power generation turbines, removing the turbine from service for repairs results in significant costs in terms of labor and downtime. For these reasons, removing components having TBCs that have suffered only localized damage such as spallation is not economically desirable. As a result, components identified as having only localized coating damage are often analyzed to determine whether the damage has occurred in a high stress area, and a judgment is then made as to the risk of damage to the turbine due to the reduced thermal protection of the component that could lead to catastrophic failure of the component.
Once a localized damaged coating area is located by inspection, and the decision is made to effect a field repair in situ, maintenance personnel must clean and prime the damaged area. Optionally, the field personnel may also apply a repair coating composition to the damaged surface, such as the compositions described in commonly-owned U.S. Pat. No. 6,413,578, for example. Current tools for cleaning, priming and optionally applying a repair coating are inadequate. Known tools are often too large, too small, or otherwise insufficient to perform the cleaning, priming and repairs. For example, maintenance personnel often use spray bottles and other containers for dispensing cleaning solutions such as solvents and detergents, beakers containing primers and coating repair compositions, and multiple brushes for cleaning and applying cleaning solutions, primers and repair compositions. In addition to the cumbersome use of so many different items, this situation creates a safety hazard to the personnel as well as a mechanical hazard to subsequent operation of the engine. While maintenance protocols require an accounting of each item used in the engine area, the use of a large number of tools makes the accounting process difficult, and more prone to errors that can have catastrophic results.
For all these reasons, there exists a continuing need for maintenance tools that can be effectively and efficiently used in limited access areas of engine and flowpath areas to clean, prime, and optionally repair damaged coated surfaces. There is additionally a need for maintenance tools and cleaning methods that can be used to perform one or more of the tasks of cleaning, priming, and repairing of coated surfaces in situ.
Accordingly, it would be desirable if a cleaning, priming and repair method were available that could be performed on localized damaged areas of TBC on turbine hardware in field and in situ, without necessitating that the component be removed from the turbine, so that downtime and scrappage are minimized.
The present invention provides apparatus and methods for cleaning, priming and repairing of coated surfaces, such as thermal barrier coatings, on a coated component that has suffered localized coating damage due to spallation, fatigue, stress damage, mechanical damage, or wear of the thermal barrier coating. The apparatus and methods of the present invention allow on-wing, in-field, in situ cleaning, priming, and repair of defects and damage to coatings such as TBCs.
The present invention provides handheld apparatus for cleaning and application of cleaning, priming, and repair materials for in situ repair of a damaged coating. In one embodiment, the apparatus of the invention provides an applicator communicably connected by a dispensing tube to a liquid reservoir such as a squeeze bulb, so that liquid such as cleaning solvent may be dispensed through the applicator by squeezing the bulb. Preferably, the applicator is a brush having a plurality of bristles, and the liquid reservoir or dispensing tube has valve means to prevent unintended dispensing of liquid.
In another embodiment, the apparatus of the invention provides an applicator that is attached to, but not communicably connected with, a fluid dispensing unit. The fluid dispensing unit is comprised of a liquid reservoir, such as a squeeze bulb, communicably connected to one end of a dispensing tube, and a dispensing tip communicably connected to the opposite end of the dispensing tube. Liquid, such as cleaning solution, primers, and coating repair compositions may be dispensed through dispensing tube and out of the dispensing tip by squeezing the bulb. Preferably, the applicator is a brush having a plurality of bristles, and the liquid reservoir or dispensing tube has valve means to prevent unintended dispensing of liquid. Preferably, the dispensing tip is disposed so as to evenly dispense liquid in close proximity to the cleaning head. The dispensing tip has an internal channel that is generally converging in shape so as to restrict fluid flow to allow precise distribution of small amounts of fluid from the tip onto a surface such as a damaged surface coating on an article.
In yet another embodiment, apparatus of the invention provides an applicator that is attached to, but not communicably connected with, a fluid dispensing unit. The fluid dispensing unit is comprised of a liquid reservoir, such as a squeeze bulb, communicably connected to a plurality of dispensing tubes, each dispensing tube communicably connected to a dispensing tip. Preferably, each dispensing tip is disposed so as to evenly dispense liquid in close proximity to the cleaning head. Although each dispensing tip may have a different sized or shaped opening, each dispensing tip has an internal channel that is generally converging in shape so as to restrict fluid flow to allow precise distribution of small amounts of fluid from each tip onto a surface such as a damaged surface coating on an article. Optionally, one or more tips may have closing means such as a closable valve or cap to allow a user to distribute fluid from only selected ones of the tips.
Liquid, such as cleaning solutions, primers, and repair coating compositions may be dispensed through the dispensing tubes and out of the dispensing tips by squeezing the bulb. Preferably, the applicator is a brush having a plurality of bristles, and the fluid dispensing unit has valve means to prevent unintended dispensing of liquid. Preferably, at least one of the dispensing tips is disposed so as to dispense liquid in close proximity to the cleaning head.
The method of cleaning, priming, and optionally repairing a coated surface of the present invention involves cleaning of a damaged area of a coating with an apparatus having an applicator, dispensing a liquid from the apparatus, and applying the liquid using the applicator to distribute the liquid. Preferably, the liquid is a cleaning solution, a primer, or a repair composition. Additional steps may include providing a second apparatus having an applicator and a liquid dispensing unit comprised of a liquid reservoir containing a liquid such as a primer or repair coating composition, wherein the liquid reservoir is communicably connected to one end of a dispensing tube, and a dispensing tip is communicably connected to the opposite end of the dispensing tube, dispensing a liquid from the dispensing tip of the second apparatus by applying external pressure to the liquid reservoir; distributing the liquid using the applicator of the second apparatus.
In view of the above, it can be appreciated that the invention overcomes several disadvantages of prior methods used to clean, prime, and optionally repair damaged coatings in the flowpath of gas turbine engines. In particular, the method of this invention does not require the simultaneous or concurrent use of multiple handheld apparatus such as beakers, spray bottles, brushes to effect the application of cleaning fluids, primers, and repair coating compositions to a localized damaged coating area. Additionally, the design of the apparatus of the present invention allows controlled release of liquid regardless of the orientation of the apparatus or vertical disposition of the coated surface. Thus, the apparatus can be used in overhead surfaces and other ergonomically challenging positions. Additionally, the apparatus is designed for single-hand use, thus providing improved access to remote and limited access areas such as the exhaust outlets of a turbine engine, and further providing the operator with a free hand to perform other functions.
As a further advantage, the repair process involves a minimum of tools since the apparatus provides both an applicator and means for storing and dispensing a liquid.
Other objects and advantages of this invention will be better appreciated from the following detailed description. Other features and advantages of the present invention will be apparent from the following more detailed description of the preferred embodiments, taken in conjunction with the accompanying drawings which illustrate, by way of example, the principles of the invention.
Whenever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts.
The present invention is directed to an apparatus and method for cleaning, priming and repairing of coated surfaces, such as thermal barrier coatings, on a coated component that has suffered localized coating damage due to spallation, fatigue, stress damage, mechanical damage, or wear of the thermal barrier coating. The apparatus and method of the present invention allow on-wing, in-field, in situ cleaning, priming, and repair defects and damage to coatings such as TBCs.
In a first embodiment shown in
In a second embodiment shown in
As shown in
While the advantages of this invention are particularly applicable to components of gas turbine engines and to coated parts in or near the flowpath of such engines, the invention is generally applicable to any coated component that requires cleaning, priming, or repair of local coating damage.
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this invention, but that the invention will include all embodiments falling within the scope of the appended claims.
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| Number | Date | Country | |
|---|---|---|---|
| 20050111903 A1 | May 2005 | US |
