Patent ID: 7901181
Filing Date: 2011-03-08
Classification: F01D

Abstract:
1. A turbine rotor blade comprising: a leading edge and a trailing edge; a pressure side wall and a suction side wall extending between the leading edge and the trailing edge; a first triple pass serpentine flow cooling circuit located in a forward section of the blade and having a first leg located against the pressure side wall and a second and third legs located against the suction side wall, the first leg being connected to a first row of film cooling holes that open onto the pressure side wall; a second triple pass serpentine flow cooling circuit located in a middle section of the blade and having a first leg located against the pressure side wall and a second and third legs located against the suction side wall, the first leg being connected to a second row of film cooling holes that open onto the pressure side wall; and, a third triple pass serpentine flow cooling circuit located in an aft section of the blade and having a first leg located against the pressure side wall and a second and third legs located against the suction side wall, the first leg being connected to a third row of film cooling holes that open onto the pressure side wall; a row of exit holes opening along the trailing edge of the blade and connected to the third leg of the third triple pass serpentine flow cooling circuit; and, the third leg of the third triple pass serpentine flow cooling circuit is connected to a row of film cooling holes that open onto the pressure side wall of the blade.