US2013216391A1PendingUtilityA1

Method for the production of a one-piece rotor area and one-piece rotor area

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Individually held — no corporate assignee on recordPriority: Apr 12, 2011Filed: Apr 12, 2012Published: Aug 22, 2013
Est. expiryApr 12, 2031(~4.7 yrs left)· nominal 20-yr term from priority
Inventors:Goetz G. Feldmann
B23P 9/02B24B 39/04Y10T29/49332C21D 7/08F05D 2230/26F01D 5/147F01D 5/02Y02T50/60
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Claims

Abstract

The present invention describes a method for the production of a one-piece rotor area, preferably of a jet engine. The rotor area includes an annular base body and several, circumferentially distributed blade elements extending essentially radially from the base body. Residual stresses are imparted to the blade elements in surface-near areas by way of roller compression using a rolling tool introduced between the blade elements. During roller compression, one each area of a blade element is arranged between areas of the rolling tool, with longitudinal sides of the blade element being simultaneously roller-compressed. According to the present invention, the rolling tool is radially introduced between the blade elements and the surfaces of the blade elements are roller-compressed, thus at least the blade elements having a roller-compressed surface.

Claims

exact text as granted — not AI-modified
1 . Method for the production of a one-piece rotor area, preferably a rotor area of a jet engine, with the rotor area including an annular base body and several, circumferentially distributed blade elements extending essentially radially from the base body, with residual stresses being imparted to the blade elements in surface-near areas by way of roller compression using a rolling tool introduced between the blade elements, with one each area of a blade element being arranged between areas of the rolling tool during roller compression, and with longitudinal sides of the blade element being simultaneously roller-compressed, characterized in that the rolling tool is radially introduced between the blade elements and the surfaces of the blade elements are roller-compressed. 
     
     
         2 . Method in accordance with  claim 1 , characterized in that the surfaces of the blade elements are roller-compressed by sequential radial traversing at least in certain areas. 
     
     
         3 . Method in accordance with  claim 1 , characterized in that the surfaces of the blade elements are roller-compressed by sequential axial traversing at least in certain areas. 
     
     
         4 . Method in accordance with  claim 1 , characterized in that the surfaces of the blade elements are roller-compressed by arbitrarily moving the rolling tool along the surfaces of the blade elements at least in certain areas. 
     
     
         5 . Method in accordance with  claim 1 , characterized in that the transition areas between the surfaces of the blade elements and the surface of the base body between the blade elements are roller-compressed using a rolling tool. 
     
     
         6 . Method in accordance with  claim 1 , characterized in that the surface of the base body between the blade elements is roller-compressed using a rolling tool. 
     
     
         7 . Method in accordance with  claim 1 , characterized in that the surfaces of several blade elements axially arranged one behind the other are roller-compressed. 
     
     
         8 . Method in accordance with  claim 1 , characterized in that a rolling force for setting a residual stress profile on the surfaces of the blade elements and/or the transition areas and/or the surface of the base body is variable between the blade elements. 
     
     
         9 . One-piece rotor area with an annular base body and several blade elements distributed over the circumference of the base body and extending essentially radially from the base body, characterized in that at least the blade elements feature a roller-compressed surface. 
     
     
         10 . One-piece rotor area in accordance with  claim 9 , characterized in that the transition areas between the surfaces of the blade elements and the surface of the base body between the blade elements feature a roller-compressed surface. 
     
     
         11 . One-piece rotor area in accordance with  claim 9 , characterized in that the base body features a roller-compressed surface at least in the area between the blade elements. 
     
     
         12 . One-piece rotor area in accordance with  claim 9 , characterized in that several blade elements axially arranged one behind the other on the base body are provided with a roller-compressed surface.

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