Platform lip impingement features

Abstract

An exemplary gas turbine engine includes a turbine section positioned about an engine central longitudinal axis. The turbine section includes a component with a platform providing a lip, a rail extending radially from the platform and at an axial location spaced from an outer axial extension of the lip. An inner face of the rail and a surface of the platform at least partially provide a cavity. At least one opening extends from the inner face to an outer face of the rail opposite the inner face to provide fluid communication from the cavity to the lip.

What is claimed is: 
     
         1 . A gas turbine engine, comprising:
 a turbine section positioned about an engine central longitudinal axis;   the turbine section including a component including
 a platform providing a lip; 
 a rail extending radially from the platform with respect to the engine central longitudinal axis and at an axial location spaced from an outer axial extension of the lip, wherein an inner face of the rail and a surface of the platform at least partially provide a cavity; and 
 at least one opening extending from the inner face to an outer face of the rail opposite the inner face to provide fluid communication from the cavity to the lip; and 
 a sloped flow diverter at the outer face for diverting the fluid to the lip. 
   
     
     
         2 . The gas turbine engine as recited in  claim 1 , wherein the flow diverter comprises a piece of sheet metal attached to the rail. 
     
     
         3 . The gas turbine engine as recited in  claim 1 , wherein the flow diverter includes an attachment portion for attachment to the rail and a sloped diverting portion. 
     
     
         4 . The gas turbine engine as recited in  claim 3 , wherein the sloped diverting portion extends radially outward as it extends axially aft. 
     
     
         5 . The gas turbine engine as recited in  claim 4 , wherein the flow diverter comprises a piece of sheet metal attached to the rail. 
     
     
         6 . The gas turbine engine as recited in  claim 5 , wherein the piece of sheet metal is welded to the rail. 
     
     
         7 . The gas turbine engine as recited in  claim 1 , comprising:
 a rotor section adjacent the component, the rotor section including a rotor component with a rotor platform lip, wherein the flow diverter is axially between the outer face and a forward-most edge face of the adjacent rotor platform lip.   
     
     
         8 . The gas turbine engine as recited in  claim 7 , wherein at least a portion of the flow diverter is radially outward of the rotor platform lip. 
     
     
         9 . A gas turbine engine, comprising:
 a turbine section positioned about an engine central longitudinal axis; and   at least one rotor section within the turbine section including
 a rotor platform including a rotor platform lip, 
 a buttress extending inwardly from the rotor platform and including an opening, 
 a cavity provided at least partially by the platform and the buttress, 
 wherein the opening is configured to provide fluid communication from the cavity to the rotor platform lip. 
   
     
     
         10 . The gas turbine engine as recited in  claim 9 , wherein a portion of the platform of the rotor section is radially outward of and axially aligned with a portion of a vane platform of an adjacent vane section to provide a radial gap therebetween. 
     
     
         11 . The gas turbine engine as recited in  claim 10 , wherein the opening is angled to direct the fluid communication axially along an inner surface of the rotor platform lip and through the radial gap. 
     
     
         12 . The gas turbine engine as recited in  claim 9 , wherein the opening is angled such that an axis extending through the opening intersects a radially inner surface of the rotor platform lip at a target point configured to receive the fluid communication from the cavity to the rotor platform lip. 
     
     
         13 . The gas turbine engine as recited in  claim 12 , wherein the axis of the at least one opening and the engine central longitudinal axis define an angle between 20 and 60 degrees. 
     
     
         14 . The gas turbine engine as recited in  claim 9 , wherein the opening is an elongated slot. 
     
     
         15 . A gas turbine engine, comprising:
 a turbine section positioned about an engine central longitudinal axis; and   at least one blade outer air seal within the turbine section including
 a seal portion providing a seal surface, a second surface opposite the seal surface, and a lip, 
 a support rail extending from the second surface and including an opening, 
 a cavity provided at least partially by the support rail and the second surface, 
 wherein the opening is configured to provide fluid communication from the cavity to the lip. 
   
     
     
         16 . The gas turbine engine as recited in  claim 15 , wherein the opening is angled such that an axis extending through the opening intersects a radially inner surface of the lip at a target point configured to receive the fluid communication from the cavity to the lip. 
     
     
         17 . The gas turbine engine as recited in  claim 16 , wherein the axis of the at least one opening and the engine central longitudinal axis define an angle between 20 and 60 degrees. 
     
     
         18 . The gas turbine engine as recited in  claim 15 , wherein the opening is an elongated slot. 
     
     
         19 . The gas turbine engine as recited in  claim 15 , comprising a sloped flow diverter at the support rail for diverting the fluid to the lip. 
     
     
         20 . The gas turbine engine as recited in  claim 19 , wherein the flow diverter comprises a piece of sheet metal attached to the rail.