Turbine rotor disks and turbine assemblies

Abstract

A turbine rotor disk is provided. The turbine rotor disk includes a hub, a ring attached to the hub, the ring including a plurality of posts extending radially outwardly and disposed around a circumference of the ring, each post including a first radially-extending face, a second radially-extending face, and a blade attachment surface extending axially between the first and second radially-extending faces, a main cooling air feed channel formed in each post and extending from the first radially-extending face toward the second radially-extending face, and a plurality of ancillary jet openings formed in each post and extending from the main cooling air feed channel to the blade attachment surface.

1 . A turbine rotor disk comprising:
 a hub;   a ring attached to the hub, the ring including a plurality of posts extending radially outwardly and disposed around a circumference of the ring, each post including a first radially-extending face, a second radially-extending face, and a blade attachment surface extending axially between the first and second radially-extending faces;   a main cooling air feed channel formed in each post and extending from the first radially-extending face toward the second radially-extending face; and   a plurality of ancillary jet openings formed in each post and extending from the main cooling air feed channel to the blade attachment surface.   
     
     
         2 . The turbine rotor disk of  claim 1 , wherein the plurality of ancillary jet openings includes a first set of ancillary jet openings and a second set of ancillary jet openings, one or more jet openings of the first set of ancillary jet openings extending from the main cooling air feed channel at an angle away from the first set of ancillary jet openings. 
     
     
         3 . The turbine rotor disk of  claim 1 , wherein the plurality of ancillary jet openings includes a first set of ancillary jet openings and a second set of ancillary jet openings, the first set of ancillary jet openings including more jet openings than the second set of ancillary jet openings. 
     
     
         4 . The turbine rotor disk of  claim 1 , wherein each jet opening of the plurality of ancillary jet openings has a largest diameter that is between about 4 to about 20 times smaller than a largest diameter of the main cooling air feed channel. 
     
     
         5 . The turbine rotor disk of  claim 1 , wherein the main cooling air feed channel has an inlet formed on the forward face. 
     
     
         6 . The turbine rotor disk of  claim 1 , wherein the main cooling air feed channel has an inlet formed on the aft face. 
     
     
         7 . A turbine assembly comprising:
 a disk including a hub and a ring attached to the hub, the ring including a plurality of posts extending radially outwardly and disposed around a circumference of the ring to define a plurality of blade attachment slots, each post including a first radially-extending face, a second radially-extending face, and a blade attachment surface extending axially between the first and second radially-extending faces, a main cooling air feed channel formed in each post and extending from the first radially-extending face toward the second radially-extending face, and a plurality of ancillary jet openings formed in each post and extending from the main cooling air feed channel to the blade attachment surface; and   a plurality of blades disposed in corresponding slots of the plurality of blade attachment slots, each blade including an airfoil, a root, and a platform, the platform supporting the airfoil and having an airfoil-facing wall and a root-facing wall, the root-facing wall defining a cooling cavity with the blade attachment surface for receiving cooling air from the plurality of ancillary jet openings.   
     
     
         8 . The turbine assembly of  claim 7 , wherein the plurality of ancillary jet openings includes a first set of ancillary jet openings and a second set of ancillary jet openings, one or more jet openings of the first set of ancillary jet openings extending from the main cooling air feed channel at an angle away from the first set of ancillary jet openings. 
     
     
         9 . The turbine assembly of  claim 7 , wherein:
 the first radially-extending face forms a forward face of the rotor;   the main cooling air feed channel has an inlet formed on the forward face; and   the turbine assembly further comprises a forward seal plate disposed adjacent to the first radially-extending face of the rotor to form a flow cavity for directing cooling air to the main cooling air feed channel.   
     
     
         10 . The turbine assembly of  claim 9 , wherein:
 the forward seal plate includes an annular sealing flange and a delivery channel, the annular sealing flange extends axially from the forward seal plate and seals against a root of a corresponding blade to divide the flow cavity into an inner radial cavity and an outer radial cavity, the delivery channel extending through the forward seal plate to provide communication between the inner radial cavity and the outer radial cavity.   
     
     
         11 . The turbine assembly of  claim 9 , wherein
 the second radially-extending face forms an aft face of the rotor;   the turbine assembly further comprises an aft seal plate disposed adjacent to the second radially-extending face of the rotor, the aft seal plate having an outermost radial section disposed radially inward from the platform of the blade; and   air flows through a gap formed, in part, by an underside of the platform of the blade.   
     
     
         12 . The turbine assembly of  claim 9 , wherein
 the second radially-extending face forms an aft face of the rotor;   the turbine assembly further comprises an aft seal plate disposed adjacent to the second radially-extending face of the rotor, the aft seal plate having an outermost radial section contacting the platform of the blade; and   a wall of the platform of the blade including an exit channel for air to flow therethrough.   
     
     
         13 . The turbine assembly of  claim 12 , wherein
 the wall of the platform includes an aft portion of the blade.   
     
     
         14 . The turbine assembly of  claim 7 , wherein:
 the second radially-extending face forms an aft face of the rotor;   the main cooling air feed channel has an inlet formed on the aft face; and   the turbine assembly further comprises an aft seal plate disposed adjacent to the second radially-extending face of the disk to form a flow cavity for directing cooling air to the main cooling air feed channel.   
     
     
         15 . The turbine assembly of  claim 14 , wherein the main cooling air feed channel has an inlet formed on the aft face. 
     
     
         16 . The turbine assembly of  claim 14 , wherein:
 the aft seal plate includes an annular sealing flange and a delivery channel, the annular sealing flange extends axially from the aft seal plate and seals against a root of a corresponding blade to divide the flow cavity into an inner radial cavity and an outer radial cavity, the delivery channel extending through the forward seal plate to provide communication between the inner radial cavity and the outer radial cavity.   
     
     
         17 . The turbine assembly of  claim 14 , wherein:
 the aft seal plate includes an annular sealing flange extending axially from the aft seal plate and seals against a root of a corresponding blade to divide the flow cavity into an inner radial cavity and an outer radial cavity;   the corresponding blade is spaced apart from a surface defining a corresponding blade attachment slot to form a flow channel; and   the corresponding blade including a delivery channel providing communication between the flow channel and the outer radial cavity.   
     
     
         18 . The turbine assembly of  claim 14 , wherein
 the second radially-extending face forms an aft face of the rotor;   the turbine assembly further comprises a forward seal plate disposed adjacent to the second radially-extending face of the rotor, the forward seal plate having an outermost radial section disposed radially inward from the platform of the blade; and   air flows through a gap formed, in part, by an underside of the platform of the blade.   
     
     
         19 . The turbine assembly of  claim 14 , wherein
 a wall of the platform of the blade including an exit channel for air to flow therethrough.