the disclosed examples facilitate depositing additional material on worn blade tips . fig1 schematically illustrates an example gas turbine engine 10 including ( in serial flow communication ) a fan section 14 , a low pressure compressor 18 , a high pressure compressor 22 , a combustor 26 , a high pressure turbine 30 , and a low pressure turbine 34 . the gas turbine engine is circumferentially disposed about an engine centerline x . during operation , the fan section 14 intakes air , the compressors 18 , 22 pressurize the air . the combustor 26 burns fuel mixed with the pressurized air . the high and low pressure turbines 30 , 34 extract energy from the combustion gases flowing from the combustor 26 . in a two - spool design , the high pressure turbine 30 utilizes the extracted energy from the hot combustion gases to power the high pressure compressor 22 through a high speed shaft 38 , and a low pressure turbine 34 utilizes the energy extracted from the hot combustion gases to power the low pressure compressor 18 and the fan section 14 through a low speed shaft 42 . the example method is not limited to the two - spool gas turbine architecture described above and may be used with other architectures such as a single spool axial design , a three spool axial design and other architectures . that is , there are various types of gas turbine engines , many of which could benefit from the examples disclosed herein , which are not limited to the design shown . referring now to fig2 , a worn turbine blade 60 within the high pressure turbine 30 of fig1 includes an airfoil profile 66 extending from a base 65 toward a tip portion 68 , which is generally the portion of the airfoil profile 66 furthest from the base 65 . in this example , a dashed line 62 a is shown within the tip portion 68 of the airfoil profile . the blade 60 includes a worn area 70 near the tip portion 68 . as known , stress from the blade 60 rubbing within the gas turbine engine 10 removes material from the tip portion 68 causing the worn area 70 . for example , the blade 60 may rub against a surrounding engine portion such as an outer air seal . although shown as a turbine blade 60 , it should be understood that disclosed examples may be applied to a blade in the compressor 18 or low pressure turbine 34 . as shown in fig3 , an example method 100 for repairing the blade 60 of fig2 includes a step 104 of removing the worn area to smooth the blade tip portion 68 . in this example , approximately 25 mm of the worn area 70 is removed to smooth a tip end of the blade 60 prior to further repairs . machine grinders or similar tools may remove the worn area . after removing the worn area 70 , the end of the blade 60 corresponds generally to the blade surface 62 , as illustrated by the dashed line 62 a in fig2 . other examples may remove more or less material depending on the desired location of the blade surface 62 and how severely the blade 60 is worn . the method 100 next includes inserting the tip portion 68 into a guide at step 108 to secure the blade 60 . material is added to the tip portion at step 112 . at step 116 the guide is removed , and at step 120 a different tip is shaped from the material added at step 112 . in another example , the step of inserting the tip portion 68 into the guide at step 108 is eliminated . in such an example , additional material is added to the tip portion at step 112 without using the guide . fig4 - 7 are used to describe an example implementation of the method 100 . referring to fig4 , an example guide 72 a includes an aperture 76 a for receiving the tip portion 68 of the blade 60 ( fig2 ). the profile of the aperture 76 a aligns with the airfoil profile 66 of the tip portion 68 . in this example , two milled guide halves are joined with tack welds 77 to fabricate the aperture 76 a within the guide 72 a . slots 78 or seams are created where the halves join . the example guide 72 a is a plate , but other guides 72 a could be used and fall within the scope of this disclosure . fig5 shows another example guide 72 b without slots 78 . an electrical discharge machining ( edm ) cutter forms the aperture 76 b within the guide 72 b , for example . a fixture assembly 80 secures the guide 72 b relative to the blade 60 when adding additional material 84 using a welder 88 . other examples include utilizing manual welding processes to add the additional material 84 , such as , adding the additional material 84 with a handheld welder for example . securing the guide 72 b and the blade 60 within the fixture 80 represents step 108 of the fig3 method . the worn area 70 of the blade 60 ( fig1 ) is typically removed prior to securing the blade 60 within the fixture 80 . in this example , the additional material 84 is added to the blade surface 62 using a modified metal inert gas ( mig ) welding process , such as the cold metal transfer welding process developed by fronius inc . as known , cold metal transfer and similar processes facilitate weld droplet formation . cold metal transfer and similar processes also utilize less heat than other welding processes to facilitate reducing burn through or warp . both automated and manual cold metal transfer welding processes may be used to add the additional material 84 to the blade surface 62 . in this example , the fixture 80 secures the guide 72 b relative to the blade 60 such that the blade surface 62 is substantially flush with a surface 73 of the guide 72 b . together , the blade surface 62 and the surface 73 of the guide 72 b provide a relatively flat rectangular area larger than the blade surface 62 . although application of the additional material 84 is desired on the blade surface 62 , moving the welder 88 in multiple directions to apply additional material 84 to the blade surface 62 is undesirable in some examples . that is , an operator of the welder 88 may desire to apply the additional material 84 by moving the welder 88 in a single direction rather than multiple directions . adding the guide 72 b to provide the relatively rectangular area facilitates supporting additional material 84 in areas other than the blade surface 62 . thus , the welder 88 may move in a single direction to apply the additional material 84 without the additional material 84 dripping down the blade 60 or otherwise moving away from the blade surface 62 . in other examples , the worn area 70 of the blade 60 is secured within the aperture 76 b , but slightly above or recessed from the surface 73 of the guide 72 b . other examples include applying the additional material 84 on the blade surface 62 without using the guide 72 b or the fixture 80 , such as when manually applying the additional material 84 . referring again to the example utilizing the guide 72 b and the fixture 80 , when the blade surface 62 is positioned within the aperture 76 b , the guide 72 b limits movement of the additional material 84 away from the blade surface 62 toward the base 65 of the blade 60 . the additional material 84 instead remains near the blade surface 62 , the surface 73 of the guide 72 b or both . without the guide 72 b , additional material 84 would spill down the sides of the blade 60 toward the base 65 . thus the guide 72 b acts like a platform to hold the additional material , here weld filler , near the blade surface 62 , which facilitate concentrated application of the additional material 84 to the blade surface 62 . fig6 and 6a illustrate the intermediately repaired blade 60 removed from the fixture 80 and having additional material 84 secured to the blade surface 62 and the guide 72 a . as shown , particularly in the top view of fig6 a , the example welder 88 adds the additional material 84 in a single pass represented by the illustrated directional arrows . previously , adding additional material 84 to the airfoil profile of the worn area 70 required complex multi - directional control of the welder 88 . using the guide 72 b enables the welder 88 to apply more additional material 84 during the single pass without the additional material moving away from the blade surface 62 , such as down the sides of the blade 60 toward the base 65 . the added additional material 84 forms a repaired section of the blade 60 . as known , the width of the additional material 84 , here a weld bead , can be controlled by adjusting welding parameters . after removing the blade 60 and guide 72 b from the fixture 80 , the guide 72 b is separated from the additional material 84 and the blade 60 , which may require cutting the guide 72 b from the blade 60 . after removing the guide 72 b from the blade 60 , the additional material 84 is shaped to form a different blade tip 90 and repaired blade 60 , as shown in fig7 . grinders or similar machining tools are often used to shape the additional material 84 into the desired airfoil profile . although a preferred embodiment has been disclosed , a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention . for that reason , the following claims should be studied to determine the true scope and content of this invention .