公开(公告)号：AT381976T

公开(公告)日：2008-01-15

申请号：AT05250321

申请日：2005-01-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PALAZZINI CHRISTOPHER M ,  WEISSE MICHAEL A ,  SENECAL DOUGLAS A

IPC: B23P15/04 ,  F01D5/14 ,  F01D5/18 ,  F02C7/00 ,  F04D29/32 ,  F04D29/38

Abstract: Hollow fan blades (30) for turbo fan gas turbine engines are formed of two separate detail halves (30a;30b). Each detail half (30a;30b) has a plurality of cavities (40) and ribs (42) machined out to reduce weight. The floor (48) and opposite interior walls (50) of each cavity (40) are machined simultaneously. The configuration minimizes the number of cutter plunge cuts for the internal cavities, and maximizes cutter size, in order to minimize the time required to machine them. These detail halves (30a;30b) are subsequently bonded and given an airfoil shape in the forming operation.

公开(公告)号：DE602005003973T2

公开(公告)日：2009-01-08

申请号：DE602005003973

申请日：2005-01-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PALAZZINI CHRISTOPHER M ,  WEISSE MICHAEL A ,  SENECAL DOUGLAS A

IPC: B23P15/04 ,  F01D5/14 ,  F01D5/18 ,  F02C7/00 ,  F04D29/32 ,  F04D29/38

Abstract: Hollow fan blades (30) for turbo fan gas turbine engines are formed of two separate detail halves (30a;30b). Each detail half (30a;30b) has a plurality of cavities (40) and ribs (42) machined out to reduce weight. The floor (48) and opposite interior walls (50) of each cavity (40) are machined simultaneously. The configuration minimizes the number of cutter plunge cuts for the internal cavities, and maximizes cutter size, in order to minimize the time required to machine them. These detail halves (30a;30b) are subsequently bonded and given an airfoil shape in the forming operation.

公开(公告)号：DE602005003973D1

公开(公告)日：2008-02-07

申请号：DE602005003973

申请日：2005-01-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PALAZZINI CHRISTOPHER M ,  WEISSE MICHAEL A ,  SENECAL DOUGLAS A

IPC: B23P15/04 ,  F01D5/14 ,  F01D5/18 ,  F02C7/00 ,  F04D29/32 ,  F04D29/38

Abstract: Hollow fan blades (30) for turbo fan gas turbine engines are formed of two separate detail halves (30a;30b). Each detail half (30a;30b) has a plurality of cavities (40) and ribs (42) machined out to reduce weight. The floor (48) and opposite interior walls (50) of each cavity (40) are machined simultaneously. The configuration minimizes the number of cutter plunge cuts for the internal cavities, and maximizes cutter size, in order to minimize the time required to machine them. These detail halves (30a;30b) are subsequently bonded and given an airfoil shape in the forming operation.