US20010000831A1 - Shim removing method - Google Patents
Shim removing method Download PDFInfo
- Publication number
- US20010000831A1 US20010000831A1 US09/748,041 US74804100A US2001000831A1 US 20010000831 A1 US20010000831 A1 US 20010000831A1 US 74804100 A US74804100 A US 74804100A US 2001000831 A1 US2001000831 A1 US 2001000831A1
- Authority
- US
- United States
- Prior art keywords
- handle
- clip
- tool
- dovetail
- shim
- 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.)
- Granted
Links
Images
Classifications
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/70—Disassembly methods
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49815—Disassembling
- Y10T29/49822—Disassembling by applying force
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49815—Disassembling
- Y10T29/49822—Disassembling by applying force
- Y10T29/49824—Disassembling by applying force to elastically deform work part or connector
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/53—Means to assemble or disassemble
- Y10T29/53613—Spring applier or remover
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/53—Means to assemble or disassemble
- Y10T29/53709—Overedge assembling means
- Y10T29/53783—Clip applier
Definitions
- This invention relates generally to tools and, more particularly, to a tool for removing a shim from a stage 2 fan blade for an aircraft engine rotor.
- Gas turbine engines typically include a multistage axial flow high pressure compressor which supplies high pressure air to a combustor, and a high pressure turbine downstream from the combustor.
- the compressor and turbine include multiple stages, and each stage includes a stationary member referred to as a stator and a rotational member referred to as a rotor.
- a “stage 2 ” turbine stage includes a plurality of fan blades attached to, and extending radially from, a fan disk. Each blade includes an airfoil and a dovetail that fits into a dovetail slot on a circumference of the fan disk. Dovetail shims are used to provide a proper fit between each dovetail and dovetail slot.
- the airfoils extend from the dovetail slots in a radial direction with respect to a center axis of the turbine engine, and define a flowpath for combustion gases.
- a tool for removing a dovetail shim from a rotor fan disk blade includes a clip and a handle.
- the clip includes a base and opposing sides extending from the base.
- a release edge is located at an end of one side and is configured to be located between the dovetail and the shim.
- the handle is configured to be located between the opposing sides of the clip and cooperates with the release edge to remove a dovetail shim from a dovetail when the handle and the clip are rotated together about an axis of the handle.
- the wood handle has a longitudinal axis and a substantially square cross sectional shape.
- the handle is inserted between the opposing sides of the clip and extends from the clip so that the longitudinal axis of the handle is substantially parallel to the longitudinal axes of the clip sides.
- the tool is located so that the release edge is engaged with a lip of a dovetail shim, and the handle contacts the exterior surface of the shim.
- the release edge separates the shim lip from the dovetail, and the handle applies a frictional force to the exterior of the shim that facilitates removal of the shim without damaging the dovetail.
- FIG. 1 is a perspective view of a partially assembled aircraft fan rotor
- FIG. 2 is a perspective view of a fan blade
- FIG. 3 is a perspective view of a shim used to secure the fan blade shown in FIG. 2 to the rotor shown in FIG. 1;
- FIG. 4 is a side elevational view of an embodiment of a tool for removing the shim shown in FIG. 3 from the fan blade shown in FIG. 2;
- FIG. 5 is a front elevational view of the tool shown in FIG. 4;
- FIG. 6 is an illustration of the tool shown in FIG. 4 in use
- FIG. 7 is a partial side view of the tool shown in FIG. 4 positioned to remove a shim from a blade;
- FIG. 8 is a partial side view of the tool and blade shown in FIG. 7 after the tool has been rotated slightly.
- FIG. 9 is a side elevational view of an alternative embodiment of a shim removal tool.
- FIG. 1 is a perspective view of a portion of a stage 2 fan rotor 20 for a turbine engine (not shown).
- Rotor 20 includes a fan disk 22 including a plurality of dovetail slots 24 .
- a fan blade 26 is inserted into each dovetail slot 24 so that blade 26 extends radially from a center axis 28 of rotor 20 .
- Disk 22 further includes a forward flange 30 and a blade retaining ring 32 .
- FIG. 2 is a perspective view of fan blade 26 including an airfoil 34 , a platform 36 , and a dovetail 38 .
- Platform 36 is inclined relative to a bottom 40 of dovetail 38 .
- Airfoil 34 extends above platform 36 , includes a tip crop 42 and is aerodynamically shaped to direct combustion gases through rotor 20 (shown in FIG. 1 ).
- Dovetail 38 extends below platform 36 and includes an upper portion 44 of substantially constant width and a rounded lower portion 46 including a maximum width near a lower portion midsection and decreasing width above and below its midsection.
- Dovetail 38 further includes a pair of side surfaces 48 that include a pressure face 50 extending substantially parallel to dovetail bottom 40 and between the dovetail lower portion midsection and dovetail upper portion 44 .
- An aluminum bronze coating is applied to dovetail pressure face 50 .
- FIG. 3 illustrates a dovetail shim 52 shaped to be inserted onto dovetail lower portion 46 (shown in FIG. 2).
- Dovetail shim 52 includes upper flares 54 having outwardly curved sidewalls, i.e., convex to a center axis 56 of shim 52 , and a lower portion 58 having inwardly curved sidewalls, i.e., concave with respect to center axis 56 .
- Shim 52 is generally shaped like an hourglass with an open top.
- shim 52 includes an interior surface 60 and an exterior surface 62 .
- Interior surface 60 includes a pressure face 64 and upper flares 54 include flared lips 66 .
- FIGS. 4 and 5 are side elevational and front elevational views, respectively, of a tool 68 for removing dovetail shim 52 (shown in FIG. 3) from dovetail 38 (shown in FIG. 2).
- Tool 68 includes a clip 70 including a first short side 72 , a second long side 74 , and a base 76 .
- Long side 74 extends a greater distance from base 76 than does short side 74 .
- Long side 74 includes a first end 78 adjacent base 76 and a second end 80 .
- a wire handle 82 extends from, and is connected to, second end 80 .
- Short side 72 includes a first end 84 adjacent base 76 and a second end 86 including a release edge 88 .
- Opposing sides 72 and 74 form a channel 90 therebetween having an interior surface 92 .
- clip 70 is continuously curved or spiraled.
- clip 70 includes three sides substantially perpendicular to one another and a fourth side having a release edge.
- a substantially square handle 94 is configured to be inserted into channel 90 of tool 68 .
- Handle 94 includes a longitudinal axis 96 and is positioned in channel 90 so that longitudinal axis 96 is substantially parallel to long side 74 . Further, an exterior surface 98 of square handle 94 is flush with long side 74 , contacts base 76 , and is separated from second side and release edge 88 . A portion of handle 94 protrudes from channel 90 and handle 94 occupies only a portion of channel 90 .
- handle 94 has a partially curved cross section.
- handle 94 has a cross section with two or more sides of unequal length, such as a generally triangular or rectangular cross sectional shape.
- FIG. 6 illustrates removing shim 52 from dovetail 38 using tool 68 .
- Tool 68 is shown in a right hand orientation.
- Handle 94 extends from clip 70 to the right as clip is viewed from long side 74 .
- Handle 94 is gripped with a right hand 100 and a thumb 102 is placed on clip 70 , thereby holding handle 94 properly positioned with respect to clip 70 .
- Fan blade 26 is held in a left hand 104 and clip 70 and handle 94 are rotated together counterclockwise about longitudinal axis 96 of handle 94 to remove shim 52 from dovetail 38 .
- tool 68 has a left hand orientation and handle 94 extends to the left as clip 70 is viewed from long side 74 .
- Tool 68 is gripped with left hand 104 , and blade 26 is in a right hand 100 .
- handle 94 is fixed to clip 70 .
- FIGS. 7 and 8 illustrate, in more detail, removing shim 52 by rotating tool 68 which has the right hand orientation.
- Release edge 88 of clip 70 is brought into contact with flared lip 66 of shim 52
- exterior surface 98 of handle 94 is brought into contact with exterior surface 62 of shim 52 .
- Rotating handle 94 and clip 70 about handle longitudinal axis 96 (shown in FIG. 8) separates flared lip 66 from dovetail pressure face 50 and pulls shim 52 from dovetail 38 .
- exterior surface 98 of handle 94 pushes down on exterior surface 62 of shim 52 and shim 52 slips off of dovetail lower portion 46 .
- shim 52 is removed quickly and easily, and damage to both dovetail 38 and shim 52 is avoided.
- FIG. 9 illustrates an alternative orientation of tool 68 .
- Handle 94 is rotated approximately 90°about clip 70 so that longitudinal axis 96 is parallel to long side 74 of clip 70 , but is transverse to base 76 and short side 72 so that longitudinal axis 96 intersects interior surface 92 of clip channel 90 .
- Tool 68 has the right hand orientation.
- Handle 94 is gripped with a right hand (not shown) with thumb placed over wire handle 82 .
- Release edge 88 is engaged with shim flared lip 66 (shown in FIG. 7) and pressure is applied to handle 94 toward shim 52 , i.e., to the left in FIG. 9, causing clip 70 to rotate and separate shim 52 from dovetail 38 (shown in FIG. 8).
- tool 68 is used in a left hand orientation by positioning tool 68 and handle 94 as a mirror image of FIG. 9.
- Clip 70 is fabricated from a 1 inch capacity spring steel clip binder, such as a clip according to Federal Supply Service Manufacturing No. AC072100 or a Large Binder Clip No. 10220 manufactured for United Stationers Supply Company of Des Plaines, Ill. and sold under the trademark UNIVERSAL.
- One side of the binder clip is trimmed to form short side 72 that extends for 0.25 inches measured perpendicular from base 76 .
- the rough edges of short side 72 are filed and then stone sharpened to form release edge 88 .
- a 0.75 inch square piece of nonmetallic material, such as wood, is cut to a length of about 7 inches to form handle 94 , and handle 94 exterior is beveled and smoothed with an abrasive cloth.
- Wire handle 82 may be removed from long side 74 of clip 70 or used to facilitate positioning of the handle 94 inside clip 70 .
- Tool 68 is inexpensive, simple to manufacture, and simple to use. Because clip 70 is made of carbon steel, tool 68 is reliable as clip 70 will not weaken after repeated use. A worker can easily and quickly remove dovetail shims from a full set of forty six fan blades while using tool 68 . Damage to both dovetail 38 and shim 52 is avoided. Thus considerable time and expense is saved in aircraft maintenance and repair.
Abstract
A tool for removing a shim from a dovetail of a fan blade for a turbine engine rotor includes a clip and a handle. The clip includes a release edge configured to engage a flared lip of a dovetail shim. The handle extends from the clip and contacts the exterior surface of the shim. When the handle and the clip are rotated about a longitudinal axis of the handle, the release edge separates the flared lip of the shim from the dovetail and the handle applies a downward force to easily remove the shim from the dovetail.
Description
- 1. The United States Government has rights in this invention pursuant to Contract No. F33657-95-C-0055 awarded by the Department of the Air Force.
- 2. This invention relates generally to tools and, more particularly, to a tool for removing a shim from a stage 2 fan blade for an aircraft engine rotor.
- 3. Gas turbine engines typically include a multistage axial flow high pressure compressor which supplies high pressure air to a combustor, and a high pressure turbine downstream from the combustor. The compressor and turbine include multiple stages, and each stage includes a stationary member referred to as a stator and a rotational member referred to as a rotor.
- 4. A “stage 2” turbine stage includes a plurality of fan blades attached to, and extending radially from, a fan disk. Each blade includes an airfoil and a dovetail that fits into a dovetail slot on a circumference of the fan disk. Dovetail shims are used to provide a proper fit between each dovetail and dovetail slot. The airfoils extend from the dovetail slots in a radial direction with respect to a center axis of the turbine engine, and define a flowpath for combustion gases.
- 5. During maintenance and repair, removing a dovetail shim from a stage 2 fan blade is difficult. Because of the shape of the dovetail, conventional tools are ill-equipped for the removal of dovetail shims. Thus, removing a shim from a dovetail is often difficult and time consuming.
- 6. Accordingly, it would be desirable to provide an inexpensive tool that facilitates the quick and easy removal of dovetail shims from stage 2 fan blades without damaging the dovetails.
- 7. In an exemplary embodiment of the invention, a tool for removing a dovetail shim from a rotor fan disk blade includes a clip and a handle. The clip includes a base and opposing sides extending from the base. A release edge is located at an end of one side and is configured to be located between the dovetail and the shim. The handle is configured to be located between the opposing sides of the clip and cooperates with the release edge to remove a dovetail shim from a dovetail when the handle and the clip are rotated together about an axis of the handle.
- 8. More specifically, the wood handle has a longitudinal axis and a substantially square cross sectional shape. The handle is inserted between the opposing sides of the clip and extends from the clip so that the longitudinal axis of the handle is substantially parallel to the longitudinal axes of the clip sides. The tool is located so that the release edge is engaged with a lip of a dovetail shim, and the handle contacts the exterior surface of the shim. When the handle and clip are rotated about the axis of the handle. The release edge separates the shim lip from the dovetail, and the handle applies a frictional force to the exterior of the shim that facilitates removal of the shim without damaging the dovetail.
- 9.FIG. 1 is a perspective view of a partially assembled aircraft fan rotor;
- 10.FIG. 2 is a perspective view of a fan blade;
- 11.FIG. 3 is a perspective view of a shim used to secure the fan blade shown in FIG. 2 to the rotor shown in FIG. 1;
- 12.FIG. 4 is a side elevational view of an embodiment of a tool for removing the shim shown in FIG. 3 from the fan blade shown in FIG. 2;
- 13.FIG. 5 is a front elevational view of the tool shown in FIG. 4;
- 14.FIG. 6 is an illustration of the tool shown in FIG. 4 in use;
- 15.FIG. 7 is a partial side view of the tool shown in FIG. 4 positioned to remove a shim from a blade;
- 16.FIG. 8 is a partial side view of the tool and blade shown in FIG. 7 after the tool has been rotated slightly; and
- 17.FIG. 9 is a side elevational view of an alternative embodiment of a shim removal tool.
- 18.FIG. 1 is a perspective view of a portion of a stage 2
fan rotor 20 for a turbine engine (not shown).Rotor 20 includes afan disk 22 including a plurality ofdovetail slots 24. Afan blade 26 is inserted into eachdovetail slot 24 so thatblade 26 extends radially from acenter axis 28 ofrotor 20.Disk 22 further includes aforward flange 30 and ablade retaining ring 32. - 19.FIG. 2 is a perspective view of
fan blade 26 including anairfoil 34, aplatform 36, and adovetail 38.Platform 36 is inclined relative to abottom 40 ofdovetail 38. Airfoil 34 extends aboveplatform 36, includes atip crop 42 and is aerodynamically shaped to direct combustion gases through rotor 20 (shown in FIG. 1).Dovetail 38 extends belowplatform 36 and includes anupper portion 44 of substantially constant width and a roundedlower portion 46 including a maximum width near a lower portion midsection and decreasing width above and below its midsection.Dovetail 38 further includes a pair ofside surfaces 48 that include apressure face 50 extending substantially parallel todovetail bottom 40 and between the dovetail lower portion midsection and dovetailupper portion 44. An aluminum bronze coating is applied todovetail pressure face 50. - 20.FIG. 3 illustrates a
dovetail shim 52 shaped to be inserted onto dovetail lower portion 46 (shown in FIG. 2).Dovetail shim 52 includesupper flares 54 having outwardly curved sidewalls, i.e., convex to acenter axis 56 ofshim 52, and alower portion 58 having inwardly curved sidewalls, i.e., concave with respect tocenter axis 56. Shim 52 is generally shaped like an hourglass with an open top. Further,shim 52 includes aninterior surface 60 and anexterior surface 62.Interior surface 60 includes apressure face 64 andupper flares 54 include flaredlips 66. Aftershim 52 is installed ondovetail 38,pressure face 64 contactsdovetail pressure face 50 andupper flares 54 are separated by dovetail upper portion 44 (shown in FIG. 2). - 21.FIGS. 4 and 5 are side elevational and front elevational views, respectively, of a
tool 68 for removing dovetail shim 52 (shown in FIG. 3) from dovetail 38 (shown in FIG. 2).Tool 68 includes aclip 70 including a firstshort side 72, a secondlong side 74, and abase 76.Long side 74 extends a greater distance frombase 76 than doesshort side 74.Long side 74 includes afirst end 78adjacent base 76 and asecond end 80. Awire handle 82 extends from, and is connected to,second end 80.Short side 72 includes afirst end 84adjacent base 76 and asecond end 86 including arelease edge 88. Opposingsides channel 90 therebetween having aninterior surface 92. In an alternative embodiment,clip 70 is continuously curved or spiraled. In a further alternative embodiment,clip 70 includes three sides substantially perpendicular to one another and a fourth side having a release edge. - 22. A substantially
square handle 94 is configured to be inserted intochannel 90 oftool 68.Handle 94 includes alongitudinal axis 96 and is positioned inchannel 90 so thatlongitudinal axis 96 is substantially parallel tolong side 74. Further, anexterior surface 98 ofsquare handle 94 is flush withlong side 74, contacts base 76, and is separated from second side andrelease edge 88. A portion ofhandle 94 protrudes fromchannel 90 and handle 94 occupies only a portion ofchannel 90. In an alternative embodiment, handle 94 has a partially curved cross section. In a further alternative embodiment, handle 94 has a cross section with two or more sides of unequal length, such as a generally triangular or rectangular cross sectional shape. - 23.FIG. 6 illustrates removing
shim 52 fromdovetail 38 usingtool 68.Tool 68 is shown in a right hand orientation.Handle 94 extends fromclip 70 to the right as clip is viewed fromlong side 74.Handle 94 is gripped with aright hand 100 and athumb 102 is placed onclip 70, thereby holdinghandle 94 properly positioned with respect to clip 70.Fan blade 26 is held in aleft hand 104 andclip 70 and handle 94 are rotated together counterclockwise aboutlongitudinal axis 96 ofhandle 94 to removeshim 52 fromdovetail 38. - 24. In an alternative embodiment,
tool 68 has a left hand orientation and handle 94 extends to the left asclip 70 is viewed fromlong side 74.Tool 68 is gripped withleft hand 104, andblade 26 is in aright hand 100. In a further alternative embodiment, handle 94 is fixed to clip 70. - 25.FIGS. 7 and 8 illustrate, in more detail, removing
shim 52 by rotatingtool 68 which has the right hand orientation.Release edge 88 ofclip 70 is brought into contact with flaredlip 66 ofshim 52, andexterior surface 98 ofhandle 94 is brought into contact withexterior surface 62 ofshim 52. Rotatinghandle 94 andclip 70 about handle longitudinal axis 96 (shown in FIG. 8) separates flaredlip 66 fromdovetail pressure face 50 and pullsshim 52 fromdovetail 38. Meanwhile,exterior surface 98 ofhandle 94 pushes down onexterior surface 62 ofshim 52 andshim 52 slips off of dovetaillower portion 46. Hence,shim 52 is removed quickly and easily, and damage to bothdovetail 38 andshim 52 is avoided. - 26.FIG. 9 illustrates an alternative orientation of
tool 68.Handle 94 is rotated approximately 90°aboutclip 70 so thatlongitudinal axis 96 is parallel tolong side 74 ofclip 70, but is transverse to base 76 andshort side 72 so thatlongitudinal axis 96 intersectsinterior surface 92 ofclip channel 90.Tool 68 has the right hand orientation.Handle 94 is gripped with a right hand (not shown) with thumb placed over wire handle 82.Release edge 88 is engaged with shim flared lip 66 (shown in FIG. 7) and pressure is applied to handle 94 towardshim 52, i.e., to the left in FIG. 9, causingclip 70 to rotate andseparate shim 52 from dovetail 38 (shown in FIG. 8). In an alternative embodiment,tool 68 is used in a left hand orientation by positioningtool 68 and handle 94 as a mirror image of FIG. 9. - 27.
Clip 70 is fabricated from a 1 inch capacity spring steel clip binder, such as a clip according to Federal Supply Service Manufacturing No. AC072100 or a Large Binder Clip No. 10220 manufactured for United Stationers Supply Company of Des Plaines, Ill. and sold under the trademark UNIVERSAL. One side of the binder clip is trimmed to formshort side 72 that extends for 0.25 inches measured perpendicular frombase 76. The rough edges ofshort side 72 are filed and then stone sharpened to formrelease edge 88. A 0.75 inch square piece of nonmetallic material, such as wood, is cut to a length of about 7 inches to formhandle 94, and handle 94 exterior is beveled and smoothed with an abrasive cloth. Wire handle 82 may be removed fromlong side 74 ofclip 70 or used to facilitate positioning of thehandle 94 insideclip 70. - 28.
Tool 68 is inexpensive, simple to manufacture, and simple to use. Becauseclip 70 is made of carbon steel,tool 68 is reliable asclip 70 will not weaken after repeated use. A worker can easily and quickly remove dovetail shims from a full set of forty six fan blades while usingtool 68. Damage to bothdovetail 38 andshim 52 is avoided. Thus considerable time and expense is saved in aircraft maintenance and repair. - 29. While the invention has been described in terms of various specific embodiments, those skilled in the art will recognize that the invention can be practiced with modification within the spirit and scope of the claims.
Claims (20)
1. A tool for removing a dovetail shim from a rotor fan disk blade, the blade including a dovetail, the shim including an exterior surface and first and second pressure faces clamped to the dovetail portion, each of the pressure faces having a flared lip extending therefrom, said tool comprising a clip comprising a base and opposing sides extending from said base, and a release edge at an end of one said side for being located between the dovetail and the shim.
2. A tool in accordance with wherein one of said sides extends a greater distance from said base than the other side.
claim 1
3. A tool in accordance with wherein said release edge is separated from said opposing side.
claim 1
4. A tool in accordance with further comprising a handle configured to be located so as to extend from said clip interior surface.
claim 1
5. A tool in accordance with wherein said handle includes a longitudinal axis, said clip comprises a channel, and said axis of said handle extends through said channel.
claim 4
6. A tool in accordance with wherein said handle partially fills said channel.
claim 5
7. A tool in accordance with wherein said handle has a substantially square cross section.
claim 6
8. A tool in accordance with wherein said handle comprises a nonmetallic material.
claim 7
9. A tool in accordance with wherein said handle is fixed to said channel.
claim 4
10. A tool for removing a dovetail shim from a rotor fan disk blade, the blade including a dovetail portion, the shim including an exterior surface and first and second pressure faces clamped to the dovetail portion, each of the pressure faces having a flared lip extending therefrom, said tool comprising a clip comprising a side and a release edge configured for contacting the flared lip as said side is rotated about an axis external of the side.
11. A tool in accordance with wherein said clip further comprises a second side resiliently separable from said release edge.
claim 10
12. A tool in accordance with wherein said clip comprises metal.
claim 11
13. A tool in accordance with wherein said clip further comprises a wire handle connected to said second side.
claim 12
14. A tool in accordance with further comprising a handle substantially square in cross section.
claim 10
15. A tool in accordance with wherein said handle is fixed to said clip.
claim 14
16. A tool in accordance with wherein said longitudinal axis of said handle is transverse to said side of said clip.
claim 14
17. A method for removing a dovetail shim from a rotor fan disk blade with a tool, the blade including an airfoil portion and a dovetail portion, the shim including an exterior surface and first and second pressure faces clamped to the dovetail portion, each of the pressure faces having a flared lip extending therefrom, the tool including a clip having a release edge configured to engage the flared lip of the shim, and a handle inserted into, and extending from, the clip, the handle separated from the release edge and having a longitudinal axis, said method comprising the steps of:
inserting the release edge of the clip between the flared lip of the shim and the dovetail; and
rotating the handle about the longitudinal axis of the handle so that the handle tangentially contacts the exterior surface of the shim and the release edge separates a pressure face of the shim from the dovetail.
18. A method in accordance with wherein the clip further includes an interior surface, the method further comprising the step of:
claim 17
extending the handle of the clip so that the axis extends through the clip substantially parallel to the surface.
19. A method in accordance with wherein the clip further comprises an interior surface, the method further comprising the step of:
claim 17
pivoting the handle about the clip so that the longitudinal axis of the handle is transverse to the surface of the clip;
gripping the handle; and
pushing the handle toward the dovetail.
20. A method in accordance with wherein said method further comprises the steps of:
claim 19
holding the blade with a first hand;
placing a thumb of a second hand on the clip of the tool; and
gripping the handle with a remainder of the second hand.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/748,041 US6412161B2 (en) | 1999-07-30 | 2000-12-22 | Shim removing method |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/364,604 US6202273B1 (en) | 1999-07-30 | 1999-07-30 | Shim removing tool |
US09/748,041 US6412161B2 (en) | 1999-07-30 | 2000-12-22 | Shim removing method |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/364,604 Division US6202273B1 (en) | 1999-07-30 | 1999-07-30 | Shim removing tool |
Publications (2)
Publication Number | Publication Date |
---|---|
US20010000831A1 true US20010000831A1 (en) | 2001-05-10 |
US6412161B2 US6412161B2 (en) | 2002-07-02 |
Family
ID=23435266
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/364,604 Expired - Fee Related US6202273B1 (en) | 1999-07-30 | 1999-07-30 | Shim removing tool |
US09/748,041 Expired - Fee Related US6412161B2 (en) | 1999-07-30 | 2000-12-22 | Shim removing method |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/364,604 Expired - Fee Related US6202273B1 (en) | 1999-07-30 | 1999-07-30 | Shim removing tool |
Country Status (9)
Country | Link |
---|---|
US (2) | US6202273B1 (en) |
EP (1) | EP1144163A3 (en) |
JP (1) | JP2003508672A (en) |
CN (1) | CN1340129A (en) |
AU (1) | AU2421801A (en) |
BR (1) | BR0006975A (en) |
CA (1) | CA2346035A1 (en) |
MY (1) | MY133515A (en) |
WO (1) | WO2001015869A2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1443180A2 (en) * | 2003-01-31 | 2004-08-04 | General Electric Company | Snap-on turbineblade shim |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6431835B1 (en) * | 2000-10-17 | 2002-08-13 | Honeywell International, Inc. | Fan blade compliant shim |
US20030139795A1 (en) * | 2002-01-23 | 2003-07-24 | Scimed Life Systems, Inc. | Stent delivery system loading tool |
FR2903138B1 (en) * | 2006-06-28 | 2017-10-06 | Snecma | MOBILE AUB AND ROTOR DISC OF TURBOMACHINE, AND DEVICE FOR ATTACHING SUCH A DAWN TO SUCH A DISK |
US7806655B2 (en) * | 2007-02-27 | 2010-10-05 | General Electric Company | Method and apparatus for assembling blade shims |
US8210819B2 (en) * | 2008-02-22 | 2012-07-03 | Siemens Energy, Inc. | Airfoil structure shim |
JP5444932B2 (en) * | 2009-08-19 | 2014-03-19 | 株式会社Ihi | Rotor fixing device, blade rotating device, and method of assembling blade rotating device |
US9650902B2 (en) * | 2013-01-11 | 2017-05-16 | United Technologies Corporation | Integral fan blade wear pad and platform seal |
US9154864B1 (en) * | 2014-04-30 | 2015-10-06 | Harman International Industries, Inc. | Speaker assembly |
FR3049306B1 (en) * | 2016-03-24 | 2018-03-23 | Snecma Mexico, S.A. De C.V. | CALES EXTRACTION TOOL IN A TURBOMACHINE |
FR3124215A1 (en) * | 2021-06-22 | 2022-12-23 | Safran Aircraft Engines | METHOD FOR RE-ENGAGING FOILERS FOR TURBOMACHINE BLADE AND DEVICE FOR REENGAGING A FOILER |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1664529A (en) * | 1927-04-08 | 1928-04-03 | Continental Railway Supply Cor | Tool |
US2126225A (en) * | 1937-02-05 | 1938-08-09 | Simons Glenn | Staple clincher for steel fences |
US3822468A (en) * | 1972-03-22 | 1974-07-09 | Merit Metal Prod Corp | Tool for removal of deterrent spring clip |
FR2334473A1 (en) * | 1975-12-11 | 1977-07-08 | Naudascher Jacques | Hand lever removing blade spring glazing retention bar - has end bent to form inverted hook with half round channel in outer angle |
US5225246A (en) * | 1990-05-14 | 1993-07-06 | United Technologies Corporation | Method for depositing a variable thickness aluminide coating on aircraft turbine blades |
FR2666266B1 (en) * | 1990-09-05 | 1992-10-30 | Snecma | TOOL FOR DEPOSITING BALANCING MASSES ON TURBINE. |
US5392504A (en) * | 1994-03-04 | 1995-02-28 | Everts & Van Der Weijden Exploitatie Maatschappij Ewen B.V. | Spring clip remover and removal method |
US5806147A (en) * | 1997-06-16 | 1998-09-15 | Sato; Hisao | Clip |
US6023833A (en) * | 1999-01-29 | 2000-02-15 | Jacobsmeier; Ernest G. | Tool for installation and removal of fastener clips |
-
1999
- 1999-07-30 US US09/364,604 patent/US6202273B1/en not_active Expired - Fee Related
-
2000
- 2000-06-16 MY MYPI20002731 patent/MY133515A/en unknown
- 2000-06-30 CN CN00801570A patent/CN1340129A/en active Pending
- 2000-06-30 AU AU24218/01A patent/AU2421801A/en not_active Abandoned
- 2000-06-30 EP EP00987949A patent/EP1144163A3/en not_active Withdrawn
- 2000-06-30 BR BR0006975-2A patent/BR0006975A/en not_active Application Discontinuation
- 2000-06-30 CA CA002346035A patent/CA2346035A1/en not_active Abandoned
- 2000-06-30 JP JP2001520266A patent/JP2003508672A/en not_active Withdrawn
- 2000-06-30 WO PCT/US2000/015590 patent/WO2001015869A2/en not_active Application Discontinuation
- 2000-12-22 US US09/748,041 patent/US6412161B2/en not_active Expired - Fee Related
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1443180A2 (en) * | 2003-01-31 | 2004-08-04 | General Electric Company | Snap-on turbineblade shim |
EP1443180A3 (en) * | 2003-01-31 | 2006-06-28 | General Electric Company | Snap-on turbineblade shim |
Also Published As
Publication number | Publication date |
---|---|
US6202273B1 (en) | 2001-03-20 |
JP2003508672A (en) | 2003-03-04 |
MY133515A (en) | 2007-11-30 |
BR0006975A (en) | 2001-06-12 |
WO2001015869A2 (en) | 2001-03-08 |
CA2346035A1 (en) | 2001-03-08 |
CN1340129A (en) | 2002-03-13 |
US6412161B2 (en) | 2002-07-02 |
EP1144163A2 (en) | 2001-10-17 |
AU2421801A (en) | 2001-03-26 |
EP1144163A3 (en) | 2001-11-28 |
WO2001015869A3 (en) | 2001-08-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US6837686B2 (en) | Blade retention scheme using a retention tab | |
US6412161B2 (en) | Shim removing method | |
US6302625B1 (en) | Method and apparatus for refurbishing a gas turbine airfoil | |
JP4870954B2 (en) | Method and apparatus for assembling a gas turbine engine rotor assembly | |
US6786696B2 (en) | Root notched turbine blade | |
EP2154333A2 (en) | Cooled airfoil and corresponding turbine assembly | |
US8157620B2 (en) | System and method for cleaning stator slots | |
US20040148793A1 (en) | Apparatus and method for inspecting and marking repair areas on a blade | |
US8172518B2 (en) | Methods and apparatus for fabricating a rotor assembly | |
US6773234B2 (en) | Methods and apparatus for facilitating preventing failure of gas turbine engine blades | |
CN105781625B (en) | Fixture and method for mounting turbine buckets | |
CZ20011777A3 (en) | Retention device for turbine blades | |
US20140304989A1 (en) | Rotor blade assembly tool for gas turbine engine | |
EP1507066A2 (en) | Center-located cutter teeth on shrouded turbine blades | |
US6905311B2 (en) | Fan blade assembly | |
US8992180B2 (en) | Replaceable staking insert assembly and method | |
JP2008106778A (en) | Blade/disk dovetail backcut for blade/disk stress reduction (7fa, stage 1) | |
JP2008540920A (en) | Rotor blade / disk dovetail backcut to reduce stress on rotor blade / disk (9FA + e, 2nd stage) | |
JPH0687603U (en) | Turbine blade protector | |
US8668459B2 (en) | Turbine blade walking prevention | |
MXPA01003253A (en) | Shim removing tool and method | |
US20180112542A1 (en) | Gas turbine engine rotor | |
US7367778B2 (en) | Rotor end piece | |
JP2003300170A (en) | Shaping tool and method for shaping curved surface on workpiece | |
JPH0660701U (en) | Integrated wing wheel |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: UNITED STATES AIR FORCE, OHIO Free format text: CONFIRMATORY LICENSE;ASSIGNOR:GENERAL ELECTRIC COMPANY;REEL/FRAME:011781/0029 Effective date: 20010326 |
|
REMI | Maintenance fee reminder mailed | ||
LAPS | Lapse for failure to pay maintenance fees | ||
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20060702 |