Rotor assembly for gas turbines

Abstract

A rotor assembly is disclosed. The rotor assembly may include a first rotor disk defining a first axially extending slot and a second rotor disk defining a second axially extending slot. Additionally, the rotor assembly may include a pin extending lengthwise between the first and second rotor disks. The pin may include a first end terminating within the first axially extending slot and a second end terminating within the second axially extending slot.

1 . A rotor assembly comprising:
 a first rotor disk, the first rotor disk defining a first axially extending slot;   a second rotor disk adjacent to the first rotor disk, the second rotor disk defining a second axially extending slot; and   a pin extending lengthwise between the first and second rotor disks, the pin including a first end terminating within the first axially extending slot and a second end terminating within the second axially extending slot.   
     
     
         2 . The rotor assembly of  claim 1 , wherein each of the first and second axially extending slots and the pin defines a generally rectangular cross-sectional shape. 
     
     
         3 . The rotor assembly of  claim 1 , wherein at least a portion of the first and second axially extending slots and at least a portion of the pin defines a generally wedged cross-sectional shape. 
     
     
         4 . The rotor assembly of  claim 3 , wherein each of the first and second axially extending slots and the pin includes a rectangular portion defining a generally rectangular cross-sectional shape and a wedged portion defining a generally wedged cross-sectional shape. 
     
     
         5 . The rotor assembly of  claim 1 , wherein a radial height of the first and second axially extending slots is chosen such that a radial gap is defined between the first and second axially extending slots and at least one of a top surface of the pin and a bottom surface of the pin. 
     
     
         6 . The rotor assembly of  claim 1 , further comprising a spacer disk disposed between the first and second rotor disks. 
     
     
         7 . The rotor assembly of  claim 6 , wherein the spacer disk defines an axially extending through-slot, the pin being configured to extend through the axially extending through-slot and into the first and second axially extending slots. 
     
     
         8 . The rotor assembly of  claim 1 , wherein the first and second rotor disks each define a plurality of axially extending slots, the rotor assembly further comprising a plurality of pins extending between the first and second rotor disks. 
     
     
         9 . The rotor assembly of  claim 1 , wherein the first and second rotor disks comprise compressor rotor disks. 
     
     
         10 . The rotor assembly of  claim 1 , wherein the first and second rotor disks comprise turbine rotor disks. 
     
     
         11 . A gas turbine comprising:
 a compressor section;   a combustion section downstream of the compressor section;   a turbine section downstream of the combustion section; and   a rotor assembly comprising:
 a first rotor disk, the first rotor disk defining a first axially extending slot; 
 a second rotor disk adjacent to the first rotor disk, the second rotor disk defining a second axially extending slot; and 
 a pin extending lengthwise between the first and second rotor disks, the pin including a first end terminating within the first axially extending slot and a second end terminating within the second axially extending slot. 
   
     
     
         12 . The gas turbine of  claim 11 , wherein each of the first and second axially extending slots and the pin defines a generally rectangular cross-sectional shape. 
     
     
         13 . The gas turbine of  claim 11 , wherein at least a portion of the first and second axially extending slots and at least a portion of the pin defines a generally wedged cross-sectional shape. 
     
     
         14 . The gas turbine of  claim 13 , wherein each of the first and second axially extending slots and the pin includes a rectangular portion defining a generally rectangular cross-sectional shape and a wedged portion defining a generally wedged cross-sectional shape. 
     
     
         15 . The gas turbine of  claim 11 , wherein a radial height of the first and second axially extending slots is chosen such that a radial gap is defined between the first and second axially extending slots and at least one of a top surface of the pin and a bottom surface of the pin. 
     
     
         16 . The gas turbine of  claim 11 , further comprising a spacer disk disposed between the first and second rotor disks. 
     
     
         17 . The gas turbine of  claim 16 , wherein the spacer disk defines an axially extending through-slot, the pin being configured to extend through the axially extending through-slot and into the first and second axially extending slots. 
     
     
         18 . The gas turbine of  claim 11 , wherein the first and second rotor disks each define a plurality of axially extending slots, the rotor assembly further comprising a plurality of pins extending between the first and second rotor disks. 
     
     
         19 . The gas turbine of  claim 11 , wherein the rotor assembly comprises a compressor rotor assembly. 
     
     
         20 . The gas turbine of  claim 11 , wherein the rotor assembly comprises a turbine rotor assembly.