Closed circuit blade-cooled turbine
AssigneeHitachi, Ltd.
InventorsShinya Marushima, Shunichi Anzai, Masami Noda, Manabu Matsumoto, Nobuaki Kizuka, Tsuyoshi Takano
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AssigneeHitachi, Ltd.
InventorsShinya Marushima, Shunichi Anzai, Masami Noda, Manabu Matsumoto, Nobuaki Kizuka, Tsuyoshi Takano
Estimating the term…
In a closed circuit moving blade cooled turbine, holes in the radial direction formed in the outer periphery of a second stage wheel are led to cooling air supply holes to second stage moving blades. The holes in the radial direction and the cooling air supply holes are interconnected and supply members covering the connections are installed. The cooling air after cooling the second stage moving blades is introduced into collection holes formed in the outer periphery of the spacer via the cooling air collection holes. The cooling air collection holes and collection holes are interconnected and collection members covering the connection are installed. To make the sum of minimum sectional areas of the respective paths of the second stage moving blades, smaller than the sum of minimum sectional areas of thee respective path of the first stage moving blades, a minimum sectional member is incorporated into the supply member.
A gas turbine having rotor wheels of a plurality of stages and moving blades of a plurality of stages arranged in a flow direction of a main flow gas of the gas turbine, said moving blades being fixed to outer peripheries of said rotor wheels of said respective stages, and a coolant being supplied to moving blades of at least first and second stages of said plurality of stages on an upstream side with respect to the main gas flow, wherein
A gas turbine having rotor wheels of a plurality of stages and moving blades of a plurality of stages arranged in a flow direction of a main flow gas of the gas turbine, said moving blades being fixed to outer peripheries of said rotor wheels of said respective stages, and a coolant being supplied to moving blades of at least first and second stages of said plurality of stages on an upstream side with respect to the main gas flow, wherein
A gas turbine having moving blades of a plurality of stages arranged in a flow direction of a main flow gas of the gas turbine, said moving blades being fixed to an outer periphery of a rotor, and a coolant being supplied to moving blades of at least a first and second stages of said plurality of stages on an upstream side with respect to the main gas flow, wherein
Dependencies are inferred from the claim text.