Patent ID: 8257041
Filing Date: 2012-09-04
Classification: F01D

Abstract:
1. A turbine rotor blade comprising: a leading edge region and a trailing edge region; a pressure side wall and a suction side wall both extending between the leading edge region and the trailing edge region of the blade; a leading edge impingement cavity located in the leading edge region and connected to a showerhead arrangement of film cooling holes; a first three-pass serpentine flow cooling circuit having a first leg located on the pressure side wall and a second and a third leg located on the suction side wall opposite to the first leg on the pressure side wall; a second three-pass serpentine flow cooling circuit having a first leg located on the pressure side wall and a second and a third leg located on the suction side wall opposite to the first leg on the pressure side wall; a third three-pass serpentine flow cooling circuit having a first leg located on the pressure side wall and a second leg located on the suction side wall opposite from the first leg and a third leg aft of the first and second legs; a row of trailing edge exit holes connected to the third leg of the third three-pass serpentine flow cooling circuit; the first legs of the first and second and third three-pass serpentine flow cooling circuits extending from the leading edge impingement cavity to the third leg of the third three-pass serpentine flow cooling circuit without any other cooling channels formed between them; and, the second and third legs of the first and second three-pass serpentine flow cooling circuits and the second leg of the third three-pass serpentine flow cooling circuit extending from the leading edge impingement cavity to the third leg of the third three-pass serpentine flow cooling circuit without any other cooling channels formed between them.