To provide a platform cooling apparatus (130) in a turbine rotor blade (100) having a platform (110), wherein the rotor blade includes an internal cooling passage (116), and wherein, in operation, the internal cooling passage (116) comprises a high-pressure coolant region and a low-pressure coolant region, and wherein the platform (110) includes a platform underside (114).
The platform cooling apparatus (130) includes a first plate (132) that resides inboard and in a spaced relation to the platform underside (114) and forming a first plenum (133); a second plate (138) that resides inboard and in a spaced relation to the first plate (132), the second plate forming a second plenum (139). The second plenum (139) includes an inlet channel (141) that connects to the high-pressure coolant region of the internal cooling passage (116), and the first plenum (133) includes an outlet channel (142) that connects to the low-pressure coolant region of the internal cooling passage (116).
HARRIS JOHN WESLEY JR
SCOTT ADRIAN LIONAL
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Hirokazu Ogura
Toshihisa Kurokawa
Next Patent: APPARATUS AND METHOD FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES