Geared turbomachine fan and compressor rotation

Abstract

A high-bypass ratio geared turbomachine comprises a compressor section of a high-bypass ratio geared turbomachine. The compressor section provides at least a low-pressure compressor and a high-pressure compressor, wherein a rotor of the low-pressure compressor rotates together with a rotor of a fan.

We claim: 
     
         1 . A high-bypass ratio geared turbomachine, comprising:
 a compressor section of a high-bypass ratio geared turbomachine, the compressor section providing at least a low-pressure compressor and a high-pressure compressor, wherein a rotor of the low-pressure compressor rotates together with a rotor of a fan.   
     
     
         2 . The high-bypass ratio geared turbomachine of  claim 1 , wherein the rotor of the low pressure compressor and the rotor of the fan rotate at the same speed and in the same direction. 
     
     
         3 . The high-bypass ratio geared turbomachine of  claim 1 , wherein the high-bypass ratio geared turbomachine has a fan bypass ratio greater than about 8. 
     
     
         4 . The high-bypass ratio geared turbomachine of  claim 1 , wherein the high-bypass ratio geared turbomachine has an overall compression ratio greater than about 40. 
     
     
         5 . The high-bypass ratio geared turbomachine of  claim 1 , wherein the high-pressure compressor has a pressure ratio greater than about 20. 
     
     
         6 . The high-bypass ratio geared turbomachine of  claim 1 , wherein the fan includes a shaft that is rotatably supported by a plurality of tapered bearings. 
     
     
         7 . The high-bypass ratio geared turbomachine of  claim 1 , including a turbine shaft that rotates a geared architecture to rotate the rotor of the low-pressure compressor and the rotor of the fan. 
     
     
         8 . The high-bypass ratio geared turbomachine of  claim 7 , wherein at least one thrust bearing rotatably supports the turbine shaft, and the at least one thrust bearing is located axially between the geared architecture and a turbine secured to the turbine shaft. 
     
     
         9 . The high-bypass ratio geared turbomachine of  claim 8 , wherein the at least one thrust bearing is a bi-directional tapered bearing. 
     
     
         10 . The high-bypass ratio geared turbomachine of  claim 7 , wherein the shaft is a low-pressure turbine shaft. 
     
     
         11 . The high-bypass ratio geared turbomachine of  claim 7 , wherein the geared architecture is a planetary geared architecture. 
     
     
         12 . A high-bypass ratio turbomachine, comprising:
 a fan rotor that rotates together with an compressor rotor at a first speed in a turbomachine having a high-bypass ratio, wherein the fan rotor and the compressor rotor are driven by a shaft that rotates at a second speed different than the first speed.   
     
     
         13 . The high-bypass ratio turbomachine of  claim 12 , wherein the shaft rotates a geared architecture to rotate the fan rotor and the compressor rotor. 
     
     
         14 . The high-bypass ratio turbomachine of  claim 12 , wherein the compressor rotor is axially forward of a fan frame extending radially across a fan bypass flow path. 
     
     
         15 . The high-bypass ratio turbomachine of  claim 12 , wherein the fan rotor and the compressor rotor rotate at the same speed. 
     
     
         16 . The high-bypass ratio turbomachine of  claim 12 , including a high-pressure turbine, a combustor section, and a low-pressure turbine arranged axially sequentially within the geared turbomachine. 
     
     
         17 . The high-bypass ratio turbomachine of  claim 12 , wherein exclusively axial compressors provide compression in the geared turbomachine. 
     
     
         18 . The high-bypass ratio turbomachine of  claim 12 , wherein the compressor is a low-pressure compressor. 
     
     
         19 . A method of operating a high-bypass ratio turbomachine, comprising:
 rotating a geared architecture with a first shaft;   rotating a second shaft with the geared architecture; and   rotating a fan rotor and a compressor rotor with the second shaft.   
     
     
         20 . The method of  claim 19 , wherein the turbomachine has a fan bypass ratio greater than 8.