专利汇可以提供METHODS FOR REPAIRING GAS TURBINE ENGINE COMPONENTS专利检索,专利查询,专利分析的服务。并且Methods for repairing gas turbine engine components are provided. In this regard, a representative method includes: applying a surface treatment to the component such that locations at an exterior surface of the component exhibiting inter-granular attack are protected from erosion during a cleaning process; and cleaning the component using hydrogen fluoride ion cleaning to clean the component.,下面是METHODS FOR REPAIRING GAS TURBINE ENGINE COMPONENTS专利的具体信息内容。
This application claims priority to Singapore Patent Application Number 200808264-6, which was filed Nov. 6, 2008.
1. Technical Field
The disclosure generally relates to repair of gas turbine engine components.
2. Description of the Related Art
Gas turbine engine components typically experience harsh operating conditions such as high temperature cycling, which can result in thermal fatigue. Additionally, some engines are exposed to harsh environment conditions such as salt ingestion that can occur during transoceanic flights, for example. Due to these and other factors, gas turbine engine components can wear and/or become damaged. In this regard, repair of gas turbine engine components oftentimes involves dimensionally restoring the components. Unfortunately, repair of these components oftentimes is impractical because various processes required for such repairs (e.g., relatively aggressive cleaning) can damage the components even further.
Methods for repairing gas turbine engine components are provided. In this regard, an exemplary embodiment of a method includes: applying a surface treatment to the component such that locations at an exterior surface of the component exhibiting inter-granular attack are protected from erosion during a cleaning process; and cleaning the component using hydrogen fluoride ion cleaning to clean the component.
Another exemplary embodiment of a method includes: providing a gas turbine engine component having a thermal coating, the component having a defect exhibiting oxidation; removing the thermal coating from the component; applying a sacrificial coating to the component; cleaning the component such that at least some of the sacrificial coating and at least some of the oxidation are removed; and repairing the defect.
Other systems, methods, features and/or advantages of this disclosure will be or may become apparent to one with skill in the art upon examination of the following drawings and detailed description. It is intended that all such additional systems, methods, features and/or advantages be included within this description and be within the scope of the present disclosure.
Many aspects of the disclosure can be better understood with reference to the following drawings. The components in the drawings are not necessarily to scale. Moreover, in the drawings, like reference numerals designate corresponding parts throughout the several views.
Methods for repairing gas turbine engine components are provided, several exemplary embodiments of which will be described in detail. In some embodiments, a gas turbine engine component is repaired for return to service by filling cracks that open to the surface of the component. Prior to filling the defect or cracks, the component is cleaned with a relatively aggressive cleaning process, such as hydrogen fluoride ion cleaning. In order to alleviate the potential surface damage caused by the cleaning process, one or more sacrificial coatings can be applied to the surface of the component so that the cleaning removes the sacrificial coating. In some embodiments, the sacrificial coating is plated onto the surface of the component with the assistance of ultrasonic vibrations to enhance uniformity of the plated sacrificial coating.
In this regard, reference is made to the schematic diagram of
In block 132 (
In block 134, a sacrificial coating 162 is applied to the component 150, such as shown in
Such a sacrificial coating can be applied, for example, via a plating process. In order to enhance uniformity of application of the sacrificial coating during plating, ultrasonic energy can be used. Use of ultrasound to enhance a plating process will be described later. In the embodiment of
System 170 also includes an ultrasonic transducer 180 that propagates sound energy into the plating solution. The ultrasonic transducer 180 produces ultrasonic vibrations in the plating solution in a frequency range of between approximately 15 KHz and approximately 25 KHz, preferably approximately 20 Khz.
In operation, the ultrasonic vibrations imparted to the plating solution 174 by the transducer 180 enhance the uniformity of material plating onto the exterior surface of the component 176. The plating uniformity tends to reduce the ability of hydrogen fluoride gas from attacking the grain boundaries during cleaning, thereby reducing inter-granular attack.
In block 136 (
Such cleaning can include exposing components to repeated cycles of hydrogen fluoride gas and hydrogen gas, as well as vacuum atmosphere at various temperatures. At cycle temperatures of approximately 1079.4° C. (1975° F.), oxides react with hydrogen fluoride gas, resulting in removal of the oxides from the components. Residuals from this hydrogen fluoride reaction can be removed by processing with the hydrogen gas and vacuum atmosphere.
Then, as depicted in block 138 (
In block 140 (
It should be emphasized that the above-described embodiments are merely possible examples of implementations set forth for a clear understanding of the principles of this disclosure. Many variations and modifications may be made to the above-described embodiments without departing substantially from the spirit and principles of the disclosure. All such modifications and variations are intended to be included herein within the scope of this disclosure and protected by the accompanying claims.
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