Inboard cooled nozzle doublet
First Claim
1. A turbine nozzle comprising:
- radially outer and inner bands integrally joined to a doublet of hollow vanes extending radially in span therebetween;
each of said vanes including circumferentially opposite pressure and suction sidewalls extending axially between opposite leading and trailing edges, and spaced apart to define an internal plenum extending radially between said bands for receiving an air coolant therein;
said vanes being spaced apart from each other to define a flow passage therebetween for channeling hot combustion gases bound by corresponding pressure and suction sidewalls of said vanes facing inboard toward each other, with the remaining suction and pressure sidewalls of said vanes facing outboard; and
said doublet of vanes including different cooling configurations, to bias more of said coolant to said inboard sidewalls than to said outboard sidewalls.
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Accused Products
Abstract
A turbine nozzle includes outer and inner bands integrally joined to a doublet of hollow vanes extending radially therebetween. Each of the vanes includes opposite pressure and suction sidewalls extending between opposite leading and trailing edges, and spaced apart to define an internal plenum extending radially between the bands for receiving an air coolant. The vanes are spaced apart from each other to define a flow passage for channeling hot combustion gases which are bound by corresponding pressure and suction sidewalls of the vanes facing inboard toward each other, with the remaining suction and pressure sidewalls of the vanes facing outboard. The vanes include different cooling configurations to bias more of the coolant to the inboard sidewalls than to the outboard sidewalls.
53 Citations
36 Claims
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1. A turbine nozzle comprising:
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radially outer and inner bands integrally joined to a doublet of hollow vanes extending radially in span therebetween; each of said vanes including circumferentially opposite pressure and suction sidewalls extending axially between opposite leading and trailing edges, and spaced apart to define an internal plenum extending radially between said bands for receiving an air coolant therein; said vanes being spaced apart from each other to define a flow passage therebetween for channeling hot combustion gases bound by corresponding pressure and suction sidewalls of said vanes facing inboard toward each other, with the remaining suction and pressure sidewalls of said vanes facing outboard; and said doublet of vanes including different cooling configurations, to bias more of said coolant to said inboard sidewalls than to said outboard sidewalls. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A turbine nozzle comprising:
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radially outer and inner bands integrally joined to a doublet of hollow vanes extending radially in span therebetween; each of said vanes including circumferentially opposite pressure and suction sidewalls extending axially between opposite leading and trailing edges, and spaced apart to define an internal plenum extending radially between said bands for receiving an air coolant therein; said vanes being spaced apart from each other to define a flow passage therebetween for channeling hot combustion gases bound by corresponding pressure and suction sidewalls of said vanes facing inboard toward each other, with the remaining suction and pressure sidewalls of said vanes facing outboard; and means for biasing more of said coolant to said inboard sidewalls than to said outboard sidewalls. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26, 27, 28, 29, 30, 31, 32, 33, 34, 35, 36)
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Specification