F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 5/18 (2006.01) B22C 9/04 (2006.01) B22C 9/10 (2006.01)
Patent
CA 2383961
A cooled gas turbine engine airfoil comprises a flow deflector arrangement adapted to re-direct a cooling fluid away from an unfilled opening left by a support member of a casting core used during the casting of the airfoil. The provision of the flow deflector arrangement advantageously allows for a larger core support, thereby facilitating the manufacture of the airfoil.
La présente invention concerne un profil de turbine à gaz refroidi qui comprend un agencement déflecteur de flux adapté pour réorienter un fluide de refroidissement à distance d'une ouverture non colmatée laissée par un élément porteur d'un noyau de coulée utilisé pendant la coulée de ce profil. L'apport de cet agencement déflecteur de flux permet d'utiliser avantageusement un support de noyau plus grand, facilitant ainsi la fabrication de ce profil.
Abdel-Messeh William
Papple Michael
Tibbott Ian
Bailey Todd D.
Pratt & Whitney Canada Corp.
Pratt & Whitney Canada Corp./pratt & Whitney Canada Cie.
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