Compressor stator chord restoration repair method and apparatus

A method for defining an airfoil with a radiused shape edge includes joining a filler material to the airfoil such that the filler material defines excess material that extends beyond an operational condition edge location of the edge of the airfoil, placing the airfoil within a barrel, providing an abrasive finishing media in the barrel with the airfoil, rotating the barrel to produce relative motion between the abrasive finishing media and the airfoil. Contact between the abrasive finishing material and the airfoil facilitates removing the excess material that extended beyond the operational condition edge location of the edge of the airfoil.

BACKGROUND

The present invention relates to airfoil repair methods and apparatuses, and more particularly to methods and apparatuses for airfoil chord repairs that involve restoring radiused leading and trailing edges.

Gas turbine engines utilize airfoils, including compressor stators (or vanes), that interact with fluid flows through the engine. During use, those airfoils can become worn or damaged. For instance, it is common for wear or damage at leading and trailing edges of airfoils to occur. Worn or damaged airfoils can be replaced in order to keep the engine in service. Alternatively, the worn or damaged airfoils can be repaired to keep the original airfoils in service in the engine, which can provide significant cost savings over the use of replacement parts.

A known repair for airfoil leading and trailing edges involves removing parent material of the airfoil at the location of the damage or wear, adding filler material to replace the removed parent material, performing a coining (or forging) operation on the filler material, and then machining the coined filler material to original blueprint dimensions. However, this known repair method has drawbacks. For instance, in order to machine leading and trailing edges to original blueprint dimensions, a relatively expensive robotic adaptive blending machine is typically required, such as a 5-axis computer numeric controlled (CNC) automated blending machine with a vision system that can cost on the order of $1 million U.S. dollars.

Vibratory finishing processes are known for processing edges of airfoils using a media placed in a vibration bowl with the airfoil. However, these known vibratory finishing processes are primarily for polishing, and may be inadequate, or at a minimum inefficient, for restoring airfoil edges following a coining operation.

SUMMARY

A method for defining an airfoil with a radiused shape edge includes joining a filler material to the airfoil such that the filler material defines excess material that extends beyond an operational condition edge location of the edge of the airfoil, placing the airfoil within a barrel, providing an abrasive finishing media in the barrel with the airfoil, rotating the barrel to produce relative motion between the abrasive finishing media and the airfoil. Contact between the abrasive finishing material and the airfoil facilitates removing the excess material that extended beyond the operational condition edge location of the edge of the airfoil.

An assembly for abrasively forming a radiused edge on an airfoil includes a barrel in which the airfoil is positioned and an abrasive media mixture placed in the barrel to remove material from the airfoil when the barrel is rotated. The abrasive media mixture includes a particulate material having generally pyramid-shaped particles with an average particle size of approximately 10 mm by 10 mm by 10 mm (⅜ inch by ⅜ inch by ⅜ inch), water and a detergent.

DETAILED DESCRIPTION

FIG. 1is a flow chart of an exemplary repair method for chord restoration of an airfoil (e.g., a compressor stator) for a gas turbine engine. The method is applicable to repairing airfoils having damage or wear at a radiused leading edge and/or trailing edge, that is, a leading or trailing edge with a profile defined by a radius swept through a given angle about an axis. After a damaged and/or worn airfoil is removed from an engine, a structural analysis is first performed to identify the location of damage and/or wear to the airfoil. The structural analysis also facilitates identifying high stress locations on the airfoil. Such high stress locations are generally structurally weaker as compared to other lower stress locations of the airfoil. Because an interface where filler material is joined to parent material of the airfoil during repair is also known to be a relatively weak location of the repaired airfoil structure, intersection of repair boundaries with the identified high stress locations may be avoided. The structural analysis further facilitates identifying a suitable manner in which to remove the damaged and/or worn region of the airfoil without unduly weakening the structural integrity of the airfoil (step20).

Following structural analysis, parent material of the airfoil is removed at the worn or damaged area(s) as a function of the structural analysis (step22). Parent material of the airfoil is removed from at least one region at a leading edge or trailing edge of the airfoil, thereby removing parent material past an original blueprint or engine manual serviceable limit dimension of a given edge of the airfoil, that is, past a predefined operational condition edge location of a given edge of the airfoil. Material removal may be accomplished using machining, grinding, or any other suitable techniques. Next, a filler material is joined to the parent material of the airfoil at the location where parent material was removed (step24). The filler material is applied beyond the operational condition edge location (i.e., the original blueprint or engine manual serviceable limit edge location) of the airfoil edge, in order to build-up a suitable amount of the filler material with some excess. In one embodiment, the filler material is added to a thickness of approximately 120-140% of the desired finished thickness at the operational condition edge location. The filler material may be joined to the parent material of the airfoil using laser clad welding, micro metal inert gas (micro MIG) welding, micro plasma transferred arc (micro-PTA) powder cladding, or other suitable processes that facilitate limiting a heat affected zone (HAZ) produced by the joining process. After the step of joining the filler material, some optional, limited pre-machining (e.g., manual or automated blending) may be performed to ensure a desired thickness ratio of the filler material to the parent material of the airfoil (step25).

Cold working of the airfoil with the joined filler material is then performed (step26). In one embodiment, the cold working is coining (i.e., forging), which can be performed in stages with optional removal of excess filler material between stages of the coining process. Next, the filler material is trimmed leaving a sufficient amount of excess filler material beyond the operational condition edge location (i.e., the original blueprint or engine manual serviceable limit edge location) of the airfoil (step28). Where the airfoil has a radiused edge, the filler material is removed with a straight cut perpendicular to a mean chord line of the airfoil (seeFIG. 2). More particularly, material is removed along a line parallel to a tangent line that intersects the operational condition edge location of the airfoil, and where the edge is a leading edge the tangent line is located at a stagnation point along the operational condition edge location of the airfoil. In one embodiment, excess filler material is left to a thickness of approximately 0.127 mm (0.005 inch) beyond the operational condition edge location of the airfoil. The filler material may be removed during this step using machining or other known techniques. Next, manual or automated blending may optionally be performed in order to smooth any step formations or rough edges produced by the filler material and remaining after the coing operation (step30). The manual blending at this step is typically minimal, and is used to bring the airfoil to original blueprint or engine manual serviceable limit dimensions except at the leading and trailing edges where excess filler material remains that may be removed by a media finish operation as described below.

The repaired edge of the airfoil may be restored to original blueprint or engine manual serviceable limit dimensions, which may include a radiused edge. For example, an abrasive media mixture may be used to remove excess filler material and shape the filler material to the operational condition edge location of the airfoil. Initially, a mask is applied to the airfoil to protect selected areas of the airfoil, such as a root portion, attachment feet, a platform, etc., from contact with the abrasive media mixture (step32). The mask may include protective fixture block (seeFIG. 3), and may further include tape (e.g., vinyl tape) adhered to the airfoil at areas not covered by the fixture block. Once masked, the airfoil is secured within a barrel along with the abrasive media mixture enabling the abrasive media mixture to come into contact with the airfoil (step34) (seeFIG. 4andFIG. 5). The abrasive media mixture may include, for example, a particulate material, a detergent and water all placed in the barrel. The composition of the abrasive media mixture is described further below. Next, the barrel containing the airfoil and the abrasive media mixture is rotated using, for example, a centrifugal barrel finishing machine (step36). Movement of the barrel induces relative movement between the airfoil and the abrasive media mixture (seeFIG. 6), such that the particulate material in the abrasive media mixture contacts the airfoil to remove portions of the filler material to facilitate returning the airfoil to original blueprint or engine manual serviceable limit dimensions (seeFIG. 7), for instance, restoring a radiused edge shape in the filler material at the operational condition edge location of the airfoil. The detergent in the abrasive media mixture may act as a wetting agent, a corrosion inhibitor, and/or a polishing agent.

After the processing the airfoil using the abrasive media mixture, the airfoil may optionally undergo a brightening process (step38). The brightening process may involve placing a brightening media mixture in the barrel with the airfoil and rotating the barrel in a manner similar to that described above with respect to the abrasive media mixture.

Next, the airfoil may undergo heat treatment, as desired (step40). Lastly, the airfoil undergoes a final inspection to ensure that the repair has returned the airfoil to a condition suitable for return to service (step42). The repair is then completed, and the airfoil may be returned to service in an engine.

FIG. 2is a schematic cross-sectional view of a leading edge portion of an exemplary airfoil100during repair, subsequent to a coining operation performed on the airfoil100. The airfoil100includes parent material102and defines a mean chord line103. As shown inFIG. 2, a portion of the parent material102has been removed in order to remove worn and/or damaged areas of the edge of the airfoil100. A filler material104is joined to the parent material102where the portion of the parent material102was removed. An operational condition edge location (i.e., the original blueprint or engine manual serviceable limit edge location)106is shown in phantom superimposed on the filler material104inFIG. 2, illustrating one embodiment of a final radiused leading edge configuration for a completed airfoil repair. The operational condition edge location106includes a radiused nose portion defined about a center of curvature108. A stagnation point110is defined along the operational condition edge location106. It should be noted that althoughFIG. 2illustrates a leading edge portion of an airfoil, the exemplary repair method is also applicable to a trailing edge location.

In the illustrated embodiment ofFIG. 2, the parent material102has been removed to a depth D beyond the operational condition edge location106in the direction of the mean chord line103, and the parent material102has remained at operational condition locations (i.e., at original blueprint or engine manual serviceable specifications) along opposed sidewalls112and114(i.e., pressure and suction sides) of the airfoil100downstream from the filler material104. In one embodiment, the distance D can be approximately 2.54 mm (0.100 inch). The filler material104may be joined to the parent material102to a thickness of approximately 120-140% of a finished thickness of the operational condition edge location106. As illustrated, the filler material104has been applied to generally a thickness beyond the operational condition edge location106with respect to the sidewalls112and114of the airfoil100, and a forging or coining operation has formed the filler material104to a shape very close to the operational condition edge location106over most of the repair area. Some limited manual or automated blending may be performed to achieve the final geometry. As shown inFIG. 2, a cut has been made in the filler material104along a line116that is located parallel to a tangent line118that intersects the operational condition edge location106at the stagnation point110. The cut forms a planar face120in the filler material104adjacent to the operational condition edge location106. A straight cut forming the planar face120is relatively simple to achieve, and generally does not require complex and expensive machining equipment of the type that would be required to machine the filler material104to the operational condition edge location106according to prior art methods. Formation of the planar face120leaves an excess of the filler material104to a thickness T beyond the operational condition edge location106, and with a non-radiused shape. In one embodiment, the thickness T is approximately 0.127 mm (0.005 inch).

FIG. 3is a side elevation view of the airfoil100during repair with a mask fixture130affixed thereto subsequent to a coining operation. In the illustrated embodiment, the filler material104forms elongate strips at both a leading edge132and a trailing edge134, both extending to a tip136of the airfoil100. The airfoil includes a platform138and a pair of feet140and142located opposite the tip136. The feet140and142are secured within the mask fixture130, and the platform138is covered by the mask fixture130. Once affixed, the mask fixture130covers portions of the airfoil100to help protect those portions from exposure to abrasive media mixture particles, for example. Portions of the airfoil100not covered by the mask fixture130but still desired to be masked may be covered by adhesive tape, such as a conventional vinyl tape. In one embodiment, exposed portions of the platform138of the airfoil100not covered by the mask fixture130are covered with adhesive vinyl tape. It should be noted that the mask fixture130may accommodate multiple airfoils100simultaneously affixed adjacent to each other in a desired arrangement.

As described above, the exemplary repair may involve material removal with an abrasive media mixture that is placed in a barrel with the airfoil100.FIG. 4is a perspective view of a barrel (or container)150with a number of airfoils100mounted to the mask fixture130placed therein. The barrel150includes a cover (not shown) that is removed to expose an interior of the barrel150. In the illustrated embodiment, the barrel150has a hexagonal profile with a twenty liter capacity, and the mask fixture130is secured to a sidewall of the barrel150. In this way the airfoils100secured to the mask fixture130extend inward from the sidewall of the barrel150. In further embodiments, multiple mask fixtures130each retaining one or more airfoils100may be secured within the barrel150, though for some applications it may be desirable to limit the number of airfoils100in the barrel150to fifteen or less. It should be appreciated that the barrel150may include any profile shape with any capacity capable of containing the airfoil and/or abrasive media mixture.

FIG. 5is a schematic cross-sectional view of the barrel150positioned relative to a central axis152with the airfoils100(only one airfoil100is visible inFIG. 5) mounted to the mask fixture130and an abrasive media mixture154placed therein. The abrasive media mixture154includes a particulate material156, cold water and a detergent (the water and the detergent are collectively designated by reference number158).

The particulate material156may be pyramid-shaped plastic media having a 10 mm by 10 mm by 10 mm (⅜ inch by ⅜ inch by ⅜ inch) size and a specific weight of about 1.8 to about 1.9 g/cm3, or more particularly about 1.85 g/cm3. In one embodiment, the composition of the particulate material156includes, by weight, approximately 60% zircon and approximately 40% polyester, with incidental impurities. One suitable particulate material is “ZI Fast Cut (Zircon)” in a generally pyramid shape in 10 mm by 10 mm by 10 mm (⅜ inch by ⅜ inch by ⅜ inch) size, available from Vibra Finish Company, Sylmar, Calif., USA. As illustrated inFIG. 5, the particulate material156is added to the barrel150containing the airfoils100such that approximately half the capacity of the barrel150is full with the particulate material156. That is, where the barrel150has a twenty liter capacity, approximately ten liters of the particulate material156may be used.

A volume of the water is added to the barrel150after the particulate material156has been added, to a level approximately 2.54 cm (1 inch) above a top most level of the particulate material156(when the barrel150is oriented with the central axis152vertical). The detergent may be a liquid detergent added to the barrel150at a volume of approximately 1% of the volume of the water added. In one embodiment, the detergent is in liquid form and includes propylene glycol, a surfactant, and a derivative of diethanolamine. One suitable detergent is sold under the trade name “SC-388” by SPIRE Private Ltd., Singapore.

Once the airfoil100has been positioned in the barrel150along with the abrasive media mixture154, the barrel150may be covered, placed in a conventional centrifugal barrel finishing machine (not shown), and rotated to produce relative movement and contact between the abrasive media mixture154and the airfoils100. Typically, the centrifugal barrel finishing machine may hold multiple barrels150for simultaneous rotation. A suitable centrifugal barrel finishing machine is a model “CB-60” available from Top Abrasive Company, Wuxi New District, Jiangsu, P. R. China.

FIG. 6is a schematic view illustrating movement of the barrel150holding the mask fixtures130and the airfoils100in a centrifugal barrel finishing machine. As shown inFIG. 6, the barrel150is configured to rotate about the central axis152in a first direction160. In the illustrated embodiment, the first direction160is counter-clockwise. Simultaneously, the barrel150is rotated about a second axis162(located at a distance from the barrel150) in a second direction164that is opposite to the first direction160. In the illustrated embodiment, the second direction164is clockwise. Thus, the barrel150is simultaneously counter-rotated in two directions160and164by the centrifugal finishing machine. Rotation of the barrel150causes the abrasive media mixture154(not shown inFIG. 6for simplicity) to move and contact the airfoils100within the barrel150, illustrated schematically by arrows166, and to remove the excess of the filler material104that extended beyond the operational condition edge location106of the edge of the airfoil100. The barrel150may be rotated for more than 30 minutes. In one embodiment, the barrel150is rotated by the centrifugal barrel finishing machine for approximately 2-3 hours at approximately 40 Hz.

FIG. 7is a close-up schematic view of the particulate material156of the abrasive media mixture154relative to the airfoil100in the barrel150during rotation by the centrifugal barrel finishing machine. The rotational movement of the barrel150tends to concentrate contact between the particulate material156of the abrasive media mixture154at edges of the airfoil100while limiting contact along sidewalls112and114(i.e., pressure and suction sides) of the airfoil100in a middle region168located between opposite leading and trailing edges of the airfoil100. The illustrated movement helps to produce radiused edges on the airfoil100, while also limiting undesirable material removal at other locations on the airfoil100, particularly along the sidewalls112and114.

Once rotation of the barrel150in the centrifugal barrel finishing machine is complete, the airfoils100may be removed, washed and then proceed to any desired finishing steps, such as heat treatment, coating, and final inspection. The airfoils100may be washed by (a) being flushed fully with clean cold water and then air dried with filtered ambient air, or (b) fully immersed in hotter water at 66-93° C. (150-200° F.) to flash dry. The particulate material156may be cleaned and re-used.

As noted above, the airfoils100may optionally undergo a brightening process following processing with the abrasive media mixture154. The brightening process may involve placing a brightening media in the barrel150with the airfoils100instead of the particulate material156and rotating the barrel150in a manner similar to that described above with respect to the abrasive media mixture154(seeFIGS. 5-7). The brightening media may have random shaped particles with an average size of approximately 3.5-8.2 mm (0.138-0.323 inch), a specific gravity of approximately 2.4 g/cm3, and a composition of about 93% by weight Al2O3. One suitable brightening media is sold under the trade name “3P-6” by Tipton US Corporation, Lebanon, Ohio, USA. The brightening process may be preformed by rotating the barrel150with the centrifugal barrel finishing machine for greater than 30 minutes at approximately 40 Hz. In one embodiment, the barrel150is rotated for approximately one hour to accomplish brightening.

In the disclosed embodiments, use of an abrasive media mixture facilitates reducing the amount of machining or blending required for an airfoil chord restoration or edge repair, thereby saving time and effort, compared to the prior art. Moreover, the use of an abrasive media mixture facilitates reducing capital expenditure on repair equipment by eliminating the use of more complex machining equipment like a 5-axis CNC automated blending machine with a vision system used with prior art repairs. The use of the abrasive media mixtures in a centrifugal finishing machine also facilitates faster and more efficient material removal from an airfoil as compared to use of known vibratory finishing methods, thus potentially saving hours of processing time. Additionally, the disclosed embodiments facilitates the restoration of a radiused edge of an airfoil, in contrast to other known abrasive media methods that may tend to produce elliptical edges on repaired airfoils.

Although the exemplary disclosure has been described with reference to preferred embodiments, workers skilled in the art will recognize that changes may be made in form and detail without departing from the spirit and scope of the invention. For example, it should be understood that a repair according to the present invention may include additional steps not specifically mentioned, and may be performed in conjunction with additional repairs to a given airfoil.