| US 7,553,131 B2 | ||
| Integrated platform, tip, and main body microcircuits for turbine blades | ||
| Francisco J. Cunha, Avon, Conn. (US); and William Abdel-Messeh, Middletown, Conn. (US) | ||
| Assigned to United Technologies Corporation, Hartford, Conn. (US) | ||
| Filed on Jul. 21, 2006, as Appl. No. 11/491,405. | ||
| Prior Publication US 2008/0019841 A1, Jan. 24, 2008 | ||
| Int. Cl. F01D 5/18 (2006.01) | ||
| U.S. Cl. 416—92 [416/97 R; 416/193 A; 415/115] | 18 Claims |
| 1. A turbine engine component having an airfoil portion with a pressure side and a suction side comprising:
means for cooling said suction side of said airfoil portion;
said cooling means comprising a first cooling microcircuit embedded within a first wall forming said suction side; and
said first cooling microcircuit having means for allowing a cooling fluid in said first cooling microcircuit to exit at a
tip of said airfoil portion,
wherein said cooling fluid exits at said tip by means of film blowing from the pressure side to the suction side of the airfoil
portion.
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