Fluid brush seal with segment seal land

Abstract

A turbine rotor for a turbine engine includes multiple rotor disks having rotor blades mounted about the circumference of each of the rotor disks. A fluid seal extends about the circumference of each rotor disk in close proximity to a stationary component of the rotor to separate the space between the rotor blades and a stationary component into separate cavities. The fluid seal includes a seal land on the rotor disk and a brush seal extending from the stationary component. A plurality of disk land segments and a plurality of blade land segments form the seal land. The disk seal segments are located on the rotor disk between the rotor blades. The blade land segments are located on the rotor blades. After the rotor blades are assembled, the blade land segments and the disk land segments fit together to form a segmented ring-like seal land around the circumference of the rotor disk.

1 . A turbine engine comprising:
 a rotor disk to rotate about an axis defining a disk rim and having a plurality of rotor blades mounted to the disk rim;   a plurality of disk land segments extending from the disk rim between each of the plurality of rotor blades;   a plurality of blade land segments extending from each of the plurality of rotor blades, wherein the plurality of disk land segments and the plurality of blade land segments form a seal land located about a circumference of the disk rim; and   a brush seal extending from a stationary component of the turbine engine and contacting the seal land.   
   
   
       2 . The turbine engine of  claim 1 , wherein the plurality of disk land segments are integrally formed in the rotor disk. 
   
   
       3 . The turbine engine of  claim 1 , wherein the plurality of blade land segments are integrally formed in each of the plurality of rotor blades. 
   
   
       4 . The turbine engine of  claim 1 , wherein the seal land comprises a radial face and the brush seal extends axially to contact the radial face. 
   
   
       5 . The turbine engine of  claim 1 , wherein the seal land comprises an axial face and the brush seal extends radially inward to contact the axial face. 
   
   
       6 . The turbine engine of  claim 1 , wherein the stationary component is a tangential on-board injector. 
   
   
       7 . The turbine engine of  claim 1 , wherein the brush seal further comprises an axial locking feature to prevent axial movement of the brush seal. 
   
   
       8 . The turbine engine of  claim 1 , wherein an interfitting structure on each of the plurality of disk land segments and the plurality of blade land segments align the plurality of disk land segments and the plurality of blade land segments. 
   
   
       9 . A fluid seal assembly for a jet engine comprising:
 a plurality of rotor disks rotating about an axis and each defining a disk rim and having a plurality of rotor blades mounted to the disk rim;   a plurality of disk land segments extending from the disk rim between each of the plurality of rotor blades;   a plurality of blade land segments extending from each of the plurality of rotor blades, wherein the plurality of disk land segments and the plurality of blade land segments form a seal land located about the circumference of the disk rim; and   a brush seal extending from a stationary component of the turbine engine to contact the seal land.   
   
   
       10 . The fluid seal assembly of  claim 9 , wherein the plurality of disk land segments are integrally formed with the rotor disk. 
   
   
       11 . The fluid seal assembly of  claim 9 , wherein the plurality of blade land segments are integrally formed with each of the plurality of rotor blades. 
   
   
       12 . The fluid seal assembly of  claim 9 , wherein the seal land comprises a radial face and the brush seal extends axially to contact the radial face. 
   
   
       13 . The fluid seal assembly of  claim 9 , wherein the seal land comprises an axial face and the brush seal extends in a radial inward direction to contact the axial face. 
   
   
       14 . The fluid seal assembly of  claim 9 , wherein the brush seal further comprises an axial locking feature to prevent axial movement of the brush seal. 
   
   
       15 . The fluid seal assembly of  claim 9 , the wherein interfitting structure on each of the plurality of disk land segments and the plurality of blade land segments align the plurality of disk land segments and the plurality of blade land segments. 
   
   
       16 . A rotor blade comprising:
 a blade platform having a blade root extending from the blade platform for receiving in a blade slot of a rotor disk; and   a blade seal segment extending from the blade root, wherein the blade seal segment defines a seal land for contacting a brush seal extending from a stationary turbine engine component.   
   
   
       17 . The rotor blade of  claim 16 , comprising a first interlocking feature on the blade seal segment for interfitting with a second interlocking feature on a disk seal segment of the rotor disk.