Turbine engine components, turbine engine assemblies, and methods of manufacturing turbine engine components

Abstract

Turbine engine components are provided for use with a plurality of blades, where each blade has an attachment portion defined by a wall and a surface. The components include a disk having a first side, a second side, and an outer radial section with a rim and an overhang. Disk slots extend radially inwardly from the disk rim, and each is configured to receive the attachment portion of a corresponding blade such that when the blade is disposed therein, the wall of the blade attachment portion is substantially flush with an adjacent portion of the first side of the disk and each disk slot defines a cooling air passage with the surface of the blade attachment portion, where the cooling air passage extends axially from the disk first side to the disk second side. A cooling air slot is formed in the disk first side and extends radially outward from the overhang of the disk to the cooling air passage.

1 . A turbine engine component for use with a plurality of blades, each blade having an attachment portion defined by a wall and a surface, the turbine engine component comprising:
 a disk having a first side, a second side, and an outer radial section, the outer radial section including a rim and an overhang;   a plurality of disk slots extending radially inwardly from the rim of the disk, each disk slot configured to receive the attachment portion of a corresponding blade of the plurality of blades such that when the blade is disposed therein, the wall of the blade attachment portion is substantially flush with an adjacent portion of the first side of the disk and each disk slot defines a cooling air passage with the surface of the blade attachment portion, the cooling air passage extending axially from the disk first side to the disk second side; and   a cooling air slot formed in the disk first side extending radially outward from the overhang of the disk to the cooling air passage.   
   
   
       2 . The turbine engine component of  claim 1 , wherein the cooling air slot is configured to allow at least a portion of the air to flow radially outward in a first direction and into the cooling air passage in a second direction that is about 90° relative to the first direction. 
   
   
       3 . The turbine engine component of  claim 1 , wherein the cooling air slot has a radial length and a decreasing cross-sectional flow area along the radial length. 
   
   
       4 . The turbine engine component of  claim 1 , further comprising a rounded corner between the cooling air passage and a corresponding cooling air slot. 
   
   
       5 . The turbine engine component of  claim 1 , wherein the cooling air passage includes an inlet formed on the disk first side and the cooling air slot extends radially outwardly from the overhang to the inlet. 
   
   
       6 . The turbine engine component of  claim 1 , wherein the cooling air passage includes an inlet formed on the disk first side and the cooling air slot extends radially outwardly from the overhang to a location in the cooling air passage that is axially downstream from the inlet. 
   
   
       7 . A turbine engine assembly comprising:
 a disk having a first side, a second side, and an outer radial section, the outer radial section including a rim and an overhang;   a plurality of blades, each blade having an attachment portion defined by a wall and a surface;   a plurality of disk slots extending radially inwardly from the rim of the disk, each disk slot configured to receive the attachment portion of a corresponding blade of the plurality of blades such that when the blade is disposed therein, the wall of the blade attachment portion is substantially flush with an adjacent portion of the first side of the disk and each disk slot defines a cooling air passage with the surface of the blade attachment portion, the cooling air passage extending axially from the disk first side to the disk second side; and   a cooling air slot formed in the disk first side extending radially outward from the overhang of the disk to the cooling air passage.   
   
   
       8 . The turbine engine assembly of  claim 7 , further comprising a seal plate disposed adjacent to and spaced apart from the first side of the disk to define a cavity through which the air flows, wherein the seal plate includes a vane disposed proximate the disk. 
   
   
       9 . The turbine engine assembly of  claim 8 , wherein the vane comprises a straight vane. 
   
   
       10 . The turbine engine assembly of  claim 7 , wherein the cooling air slot is configured to allow at least a portion of the air to flow radially outward in a first direction and into the cooling air passage in a second direction that is about 90° relative to the first direction. 
   
   
       11 . The turbine engine assembly of  claim 7 , wherein the cooling air slot has a radial length and a decreasing cross-sectional flow area along the radial length. 
   
   
       12 . The turbine engine assembly of  claim 7 , further comprising a rounded corner between the cooling air passage and a corresponding cooling air slot. 
   
   
       13 . The turbine engine assembly of  claim 7 , wherein the cooling air passage includes an inlet formed on the disk first side and the cooling air slot extends radially outwardly from the overhang to the inlet. 
   
   
       14 . The turbine engine assembly of  claim 7 , wherein the cooling air passage includes an inlet formed on the disk first side and the cooling air slot extends radially outwardly from the overhang to a location in the cooling air passage that is axially downstream from the inlet. 
   
   
       15 . A method of manufacturing a turbine engine component, the method comprising the steps of:
 forming a plurality of disk slots into a disk, each disk slot extending radially inwardly from a rim of the disk; and   forming a plurality of cooling air slots into a first side of the disk, each cooling air slot corresponding with a disk slot of the plurality of disk slots and extending and located radially inwardly therefrom.   
   
   
       16 . The method of  claim 15 , further comprising inserting a plurality of blades into a corresponding disk slot such that each wall of each blade attachment portion of each blade of the plurality of blades is substantially flush with an adjacent portion of the first side of the disk and each corresponding disk slot defines a cooling air passage with the surface of the blade attachment portion to thereby extend axially from the disk first side to the disk second side and to have an opening formed substantially flush with the disk first side. 
   
   
       17 . The method of  claim 15 , further comprising rounding a corner between the cooling air passage and a corresponding cooling air slot. 
   
   
       18 . The method of  claim 15 , wherein the step of forming the plurality of cooling air slots comprises extending the cooling air slots from an overhang of the disk to a corresponding disk slot. 
   
   
       19 . The method of  claim 15 , wherein the step of forming the plurality of cooling air slots comprises extending the cooling air slots from an overhang of the disk to an inlet of a corresponding disk slot, the inlet formed in a first side of the disk. 
   
   
       20 . The method of  claim 15 , wherein the step of forming the plurality of cooling air slots comprises using a ball cutter to form the cooling air slots.