Patent ID: 6595748
Filing Date: 2003-07-22
Classification: F01D,F05D,Y02T

Abstract:
A turbine blade comprising:airfoil pressure and suction sidewalls joined together at leading and trailing edges and extending from a root to tip; a leading edge flow chamber disposed between said sidewalls behind said leading edge, and bounded by a forward bridge extending between said sidewalls; an aft bridge spaced from said forward bridge and extending between said sidewalls; a septum extending chordally between said forward and aft bridges and spaced inboard from said sidewalls to define a first side channel along said pressure sidewall and a second side channel along said suction sidewall; and a row of feed holes disposed through said forward bridge in flow communication between said first side channel and said leading edge chamber for channeling a coolant therethrough; a row of film cooling gill holes disposed through said suction sidewall in flow communication with said second side channel; and said first and second side channels have respective first and second inlets disposed below said blade root, and said second inlet is sized for metering said coolant to said second side channel at a reduced pressure to reduce backflow margin at said gill holes.