Airfoil assembly with a fluid circuit

Abstract

An airfoil assembly for a gas turbine engine having a core with a working airflow. The airfoil assembly comprising a dovetail, a platform, an airfoil, a fluid circuit and at least one curvilinear cooling passage. The platform extending from the dovetail and having an outer surface confronting the working airflow. The at least one curvilinear fluid passage extending between an inlet in direct fluid communication with the fluid circuit and an outlet on the outer surface.

1 - 20 . (canceled) 
     
     
         21 . An airfoil assembly for a turbine engine having a core with a working airflow, the airfoil assembly comprising:
 a dovetail;   a platform extending from the dovetail and having an outer surface confronting the working airflow;   an airfoil extending from the outer surface and having an outer wall bounding an interior and defining a pressure side and a suction side extending axially between a leading edge to a trailing edge and extending radially between a root and a tip, with the root being adjacent the platform;   a fluid circuit formed at least partially within the dovetail and being fluidly coupled to the interior of the airfoil; and   at least one curvilinear fluid passage having a single continuous bend including and extending between an inlet in direct fluid communication with the fluid circuit and an outlet on the outer surface.   
     
     
         22 . The airfoil assembly of  claim 21 , wherein the at least one curvilinear fluid passage defines a centerline, which at the outlet, defines an included angle with the outer surface. 
     
     
         23 . The airfoil assembly of  claim 22 , wherein the included angle is less than 30 degrees. 
     
     
         24 . The airfoil assembly of  claim 23 , wherein the included angle is less than 20 degrees. 
     
     
         25 . The airfoil assembly of  claim 21 , wherein the at least one curvilinear fluid passage defines a plurality of curvilinear fluid passages, each extending between a corresponding inlet and outlet. 
     
     
         26 . The airfoil assembly of  claim 25 , wherein at least some of the plurality of curvilinear fluid passages have their outlets aligned with a flow streamline about the airfoil. 
     
     
         27 . The airfoil assembly of  claim 21 , wherein the at least one curvilinear fluid passage is cast within the platform. 
     
     
         28 . The airfoil assembly of  claim 21 , wherein the outlet is located in a rear half of the airfoil in a chord-wise direction. 
     
     
         9 . The airfoil assembly of  claim 21 , wherein the outlet is located above the suction side. 
     
     
         30 . An airfoil assembly for a turbine engine having a core with a working airflow, the airfoil assembly comprising:
 a dovetail;   a platform extending from the dovetail and having an outer surface confronting the working airflow;   an airfoil extending from the outer surface and having an outer wall bounding an interior and defining a pressure side and a suction side extending axially between a leading edge to a trailing edge and extending radially between a root and a tip, with the root being adjacent the platform;   a fluid circuit formed at least partially within the dovetail and being fluidly coupled to the interior of the airfoil; and   at least one curvilinear fluid passage extending between an inlet in direct fluid communication with the fluid circuit and an outlet on the outer surface;   wherein the at least one curvilinear fluid passage defines a centerline, which at the outlet, defines an included angle with the outer surface and the included angle being less than or equal to 30 degrees and greater than 0 degrees such that the fluid emerging from the outlet can align with a flow streamline of the working airflow to form a fluid film on the outer surface.   
     
     
         31 . The airfoil assembly of  claim 30 , wherein the included angle is less than or equal to 20 degrees. 
     
     
         32 . The airfoil assembly of  claim 30 , wherein the at least one curvilinear fluid passage defines a plurality of curvilinear fluid passages, each extending between a corresponding inlet and outlet. 
     
     
         33 . The airfoil assembly of  claim 32 , wherein each fluid passage of the plurality of curvilinear fluid passages includes a respective included angle. 
     
     
         34 . The airfoil assembly of  claim 32 , wherein at least some of the plurality of curvilinear fluid passages have their outlets aligned with a flow streamline about the airfoil. 
     
     
         35 . The airfoil assembly of  claim 30 , wherein the at least one curvilinear fluid passage is cast within the platform. 
     
     
         36 . The airfoil assembly of  claim 30 , wherein the outlet is located in a rear half of the airfoil in a chord-wise direction. 
     
     
         37 . The airfoil assembly of  claim 30 , wherein the outlet is located above the suction side. 
     
     
         38 . A method of supplying a fluid to an airfoil for a turbine engine, the airfoil extending from an outer surface of a platform with the outer surface confronting a working airflow of the turbine engine, the method comprising:
 supplying fluid air to a fluid circuit within a dovetail to an interior of an airfoil;   passing the fluid through a curvilinear passage having a single continuous bend in the platform, the single continuous bend of the curvilinear passage including and extending between an inlet in direct fluid communication with the fluid circuit and an outlet provided on the outer surface; and   emitting at least a portion of the fluid through the outlet of the curvilinear passage.   
     
     
         39 . The method of  claim 38 , further comprising emitting the fluid from the outlet along a path forming an included angle of less than 30 degrees relative to the platform. 
     
     
         40 . The method of  claim 38 , further comprising emitting the fluid at an aft half of the airfoil.