Inboard cooled nozzle doublet

  • US 20050135921A1
  • Filed: 12/17/2003
  • Published: 06/23/2005
  • Est. Priority Date: 12/17/2003
  • Status: Active Grant
First Claim
Patent Images

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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