US2011306275A1PendingUtilityA1

Component finishing tool

40
Individually held — no corporate assignee on recordPriority: Jun 13, 2010Filed: Jun 13, 2010Published: Dec 15, 2011
Est. expiryJun 13, 2030(~3.9 yrs left)· nominal 20-yr term from priority
Inventors:Matthew D. NicolsonDavid ValentineJohn M. Schmartz
B24B 33/05B24B 19/02B24B 19/009B24B 33/088
40
PatentIndex Score
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Cited by
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References
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Claims

Abstract

An example finishing tool form assembly includes a base and a superabrasive bonded to a surface of the base. The superabrasive is configured to be reciprocated with the base relative to a longitudinally extending recess of a component to finish at least one surface of the component.

Claims

exact text as granted — not AI-modified
1 ) A finishing tool form comprising:
 a base; and   a superabrasive bonded to a surface of the base, wherein the superabrasive is configured to be reciprocated with the base relative to a longitudinally extending recess of a component to finish at least one surface of the component.   
     
     
         2 ) The finishing tool form assembly of  claim 1  wherein the base comprises cast iron. 
     
     
         3 ) The finishing tool form assembly of  claim 1  wherein the superabrasive is plated to the base. 
     
     
         4 ) The finishing tool form assembly of  claim 3 , wherein the superabrasive is nickel-plated to the base. 
     
     
         5 ) The finishing tool assembly of  claim 1 , wherein the superabrasive comprises cubic boron nitride. 
     
     
         6 ) The finishing tool assembly of  claim 1 , wherein the superabrasive bonded to a surface of the base is 0.0015 inches thick. 
     
     
         7 ) The finishing tool assembly of  claim 1 , wherein the superabrasive comprises an ASTM 400 grit. 
     
     
         8 ) A turbomachine component finishing tool assembly comprising:
 a fixture; and   a form mountable to the fixture, the form including an abrasive bonded to a base, wherein the fixture is configured to reciprocate the form relative to a surface of a turbomachine component.   
     
     
         9 ) The turbomachine component finishing tool assembly of  claim 8 , wherein the form is spring biased toward a rotational axis of the turbomachine component. 
     
     
         10 ) The turbomachine component finishing tool assembly of  claim 8 , wherein the turbomachine component is a rotor establishing a blade receiving slot. 
     
     
         11 ) The turbomachine component finishing tool assembly of  claim 10 , wherein cross-sectional dimensions of the form are the same as desired cross-sectional dimensions of the blade receiving slot. 
     
     
         12 ) The turbomachine component finishing tool assembly of  claim 8 , wherein the form has an enlarged head. 
     
     
         13 ) The turbomachine component finishing tool assembly of  claim 8 , wherein the turbomachine component is a gas turbine engine component. 
     
     
         14 ) A turbomachine surface finishing method comprising:
 reciprocating a base relative to a surface of a turbomachine component; and   finishing the surface with an abrasive bonded to the reciprocating base.   
     
     
         15 ) The turbomachine surface finishing method of  claim 14 , wherein the base is spring biased toward a rotational axis of the component. 
     
     
         16 ) The turbomachine surface finishing method of  claim 14 , wherein the base moves back and forth along a single axis during the reciprocating. 
     
     
         17 ) The turbomachine surface finishing method of  claim 14 , wherein the surface of the turbomachine component is a surface of a blade slot within a gas turbine engine.

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