Turbomachine rotor thermal regulation systems

Abstract

A turbomachine includes an aft stage including a rotor disk having a rotor disk bore hole and a rotor disk rim, and a valve disposed within the turbomachine and in fluid communication with the rotor disk bore hole. The valve is in selective fluid communication with a first pressure source such that, in an first position, the valve allows fluid to flow from the first pressure source through the rotor disk bore hole and radially outward along the aft rotor disk toward the aft rotor disk rim.

What is claimed is: 
     
         1 . A turbomachine, comprising:
 an aft stage including a rotor disk having a rotor disk bore hole and a rotor disk rim; and   a valve disposed within the turbomachine and in fluid communication with the rotor disk bore hole, wherein the valve is in selective fluid communication with a first pressure source, such that in an first position, the valve allows fluid to flow from the first pressure source through the rotor disk bore hole and radially outward along the aft rotor disk toward the aft rotor disk rim.   
     
     
         2 . The turbomachine of  claim 1 , wherein the first pressure source is a cold air source. 
     
     
         3 . The turbomachine of  claim 1 , wherein the first pressure source is a hot air source. 
     
     
         4 . The turbomachine of  claim 1 , further including a second pressure source including a fluid of a different temperature than the first pressure source. 
     
     
         5 . The turbomachine of  claim 4 , wherein the first pressure source is a cold air source and the second pressure source is a hot air source. 
     
     
         6 . The turbomachine of  claim 1 , wherein the aft stage includes an anti-vortex tube disposed in a cavity between the aft rotor disk and a second rotor disk that is forward of the aft rotor disk to facilitate radially outward flow therein. 
     
     
         7 . The turbomachine of  claim 1 , including at least one intermediate stage rotor disk including an intermediate stage rotor disk bore hole in fluid communication with the valve. 
     
     
         8 . The turbomachine of  claim 7 , wherein each intermediate stage includes an anti-vortex tube disposed thereon to facilitate radially outward flow therealong. 
     
     
         9 . The turbomachine of  claim 8 , wherein each anti-vortex tube is sized to balance a pressure drop between each stage. 
     
     
         10 . The turbomachine of  claim 1 , further including a forward stage rotor disk that is sealed at a forward stage rotor disk bore to prevent flow from any rotor disk aft thereof from flowing therethrough. 
     
     
         11 . The turbomachine of  claim 1 , wherein the valve is operatively connected to a control system for determining when to allow flow from the first pressure source. 
     
     
         12 . The turbomachine of  claim 1 , wherein the valve is configured to modify flow rate from the first pressure source. 
     
     
         13 . The turbomachine of  claim 1 , wherein the valve is configured to shut off flow from the first pressure source. 
     
     
         14 . The turbomachine of  claim 5 , wherein the valve is operatively connected to a control system for determining when to allow flow from the first pressure source and/or the second pressure source based on an operational characteristic of the turbomachine. 
     
     
         15 . A method, comprising:
 determining an operational characteristic of a turbomachine; and   providing high pressure air to a rotor disk of a turbomachine compressor for thermal regulation of the rotor disk based on the operational characteristic.   
     
     
         16 . The method of  claim 15 , wherein providing an airflow includes modifying a state of a valve to allow at least one of a cold air or a hot air to flow to the rotor disk or to modify the total flow rate of the cold air and/or the hot air based on the operational characteristic. 
     
     
         17 . The method of  claim 15 , wherein determining the operational characteristic includes determining the temperature of one or more components of the turbomachine. 
     
     
         18 . The method of  claim 15 , wherein determining the operational characteristic includes determining the speed of one or more components of the turbomachine. 
     
     
         19 . The method of  claim 15 , wherein determining the operational characteristic includes determining the power setting and/or output of the turbomachine.