Gas turbine blade inlet cooling flow deflector

Details Gas turbine blade inlet cooling flow deflector Gas turbine blade inlet cooling flow deflector

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/08 (2006.01) F01D 5/30 (2006.01)

Patent

CA 2527305

An internally cooled turbine blade (26) including at least one deflector (48) extending into an air cavity (38) generally from a first wall (53a) towards a second wall (53) for diverting cooling air (49) away from the first wall (53a) and generally towards the second wall (53) to thereby improve cooling flow distribution among a plurality of cooling path inlets (41,43,45).

L'invention concerne une aube (26) de turbine à refroidissement interne, comprenant au moins un déflecteur (48) qui s'avance dans une cavité (38) d'air, sensiblement d'une première paroi (53a) vers une seconde paroi (53), et sert à dévier l'air (49) de refroidissement de manière à l'éloigner de la première paroi (53a) et à le diriger sensiblement vers la seconde paroi (53) afin d'améliorer la répartition du flux de refroidissement entre une pluralité d'entrées (41,43,45) de voies de refroidissement.

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