Airfoil isolated leading edge cooling
First Claim
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1. 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 and behind said leading edge;
pressure and suction side flow channels laterally bounding an isolation flow channel therebetween and extending continuously over the full chordal length thereof, and separated from said leading edge chamber by a forward bridge therebetween; and
a row of feed holes disposed through said forward bridge in flow communication between said isolation channel and said leading edge chamber for channeling a coolant therethrough.
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Abstract
A turbine blade includes an airfoil having a leading edge flow chamber disposed behind a leading edge in flow communication with an isolation flow channel disposed therebehind. The isolation channel is bounded on opposite sides by a pair of side flow channels.
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Citations
20 Claims
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1. A turbine blade comprising:
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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 and behind said leading edge;
pressure and suction side flow channels laterally bounding an isolation flow channel therebetween and extending continuously over the full chordal length thereof, and separated from said leading edge chamber by a forward bridge therebetween; and
a row of feed holes disposed through said forward bridge in flow communication between said isolation channel and said leading edge chamber for channeling a coolant therethrough. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
wherein said third inlet is smaller than said second inlet for metering said coolant to said suction side channel at a reduced pressure to reduce backflow margin at said gill holes.
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10. A blade according to claim 5 further comprising a tip chamber disposed under said airfoil tip and extending from said aft bridge to said trailing edge, with said aft bridge including an outlet hole disposed in flow communication between said isolation channel and said tip chamber for channeling said coolant thereto.
- 11. A turbine blade comprising an airfoil having a leading edge flow chamber disposed behind a leading edge in flow communication with an isolation flow channel disposed therebehind, with said isolation channel being bounded on opposite sides by a single pair of side flow channels.
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17. A turbine blade comprising:
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an airfoil having a leading edge flow chamber disposed behind a leading edge in flow communication with an isolation flow channel disposed therebehind;
with said isolation channel being bounded on opposite sides by a pair of side flow channels extending between forward and aft bridges joining opposite pressure and suction sidewalls of said airfoil; and
a serpentine mid flow channel terminating at said aft bridge for supplying coolant in parallel to said pair of side channels. - View Dependent Claims (18, 19, 20)
said forward bridge includes a row of feed holes disposed in flow communication between said leading edge chamber and said isolation channel; - and
said leading edge includes a row of film cooling holes for discharging said coolant from said leading edge chamber.
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19. A blade according to claim 18 wherein each of said isolation channel and side channels has an independent inlet for receiving said coolant in parallel.
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20. A blade according to claim 19 further comprising a row of film cooling gill holes disposed through said suction sidewall in flow communication with one of said side channels, and said inlet thereof is smaller than said inlet to said other side channel for reducing backflow margin across said gill holes.
Specification