IP Library Granted Patent US 7,530,788
Granted Patent B2
US 7,530,788 · App. 11/473,020 · Granted May 12, 2009

Hollow turbomachine blade

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Quick Facts
Patent No.
US 7,530,788
App. No.
11/473,020
Granted
May 12, 2009
Kind
B2
Abstract

A hollow turbomachine blade including an internal cooling passage, an open cavity situated at the free end of the blade and defined by an end wall and the side wall of at least one rim which extends between the leading edge and the trailing edge of the blade, and at least one cooling channel connecting said internal cooling passage to said open cavity, said cooling channel opening out at the base of the rim and the wall of the rim forming an angle relative to said end wall that is obtuse, being strictly greater than 90°. An indentation may be formed in the wall of the rim at the outlet from said cooling channel. Said blade advantageously does not include a pressure rim.

Claims (8)

1. A hollow turbomachine blade including an internal cooling passage, an open cavity situated at a free end of the blade and defined by an end wall and a side wall of at least one rim extending between a leading edge and a trailing edge of the blade, and at least one cooling channel connecting said internal cooling passage to said open cavity, wherein said cooling channel opens out at the base of said side wall of the rim, wherein said side wall forms an angle A relative to said end wall that is obtuse, being strictly greater than 90°, wherein an indentation is formed in said side wall at an outlet from said cooling channel, and wherein said indentation comes to an end before the top end of the rim.

2. A hollow blade according to claim 1 , wherein the blade of the invention does not have a pressure rim or has only a fraction of a pressure rim.

3. A hollow blade according to claim 1 , wherein the angle formed between the side wall and the end wall lies in the range 110° to 135°, and is advantageously situated at about 120°.

4. A hollow blade according to claim 1 , wherein the outline of said indentation is generally triangular in shape.

5. A hollow blade according to claim 1 , wherein the bottom of said indentation is curved.

6. A hollow blade according to claim 1 , wherein said cooling channel is in two portions: an adjustment portion formed by a drilled hole and a diffusion portion formed in part by said indentation.

7. A hollow blade according to claim 1 , wherein a plurality of cooling channels are distributed regularly along said side wall.

8. A hollow blade according to claim 1 , wherein said indentation comes to an end close to half way up the height of said rim.

Assignments (4)
CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Recorded Aug 24, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046939/0336 →
CHANGE OF NAME Recorded May 23, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046479/0807 →
CORRECTED FORM PTO-1595 TO CORRECT ASSIGNOR # 1'S NAME PREVIOUSLY RECORDED ON REEL 018261 FRAME 0145. Recorded Nov 6, 2006
From: BOURY, JACQUES AUGUSTE AMEDEE; BONNEAU, DAMIEN; FACHAT, THIERRY
To: SNECMA
Reel/Frame 018513/0034 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Sep 1, 2006
From: BOURY, JACQUES; BONNEAU, DAMIEN; FACHAT, THIERRY
To: SNECMA
Reel/Frame 018261/0145 →