Gas turbine engine assembly and methods of assembling same

Abstract

A turbine engine assembly includes, a core gas turbine engine, a first low-pressure turbine section in serial flow communication with the core gas turbine engine, the first low-pressure turbine section configured to rotate in a first rotational direction, a first gear assembly coupled to the first low-pressure turbine section, a second low-pressure turbine section coupled to the gear assembly, the second low-pressure turbine section configured to rotate in a second rotational direction, and a fan assembly coupled to the second low-pressure turbine section.

1 . A turbine engine assembly comprising;
 a core gas turbine engine;   a first low-pressure turbine section in serial flow communication with said core gas turbine engine, said first low-pressure turbine section configured to rotate in a first rotational direction;   a first gear assembly coupled to said first low-pressure turbine section;   a second low-pressure turbine section coupled to said gear assembly, said second low-pressure turbine section configured to rotate in a second rotational direction; and   a fan assembly coupled to said second low-pressure turbine section.   
   
   
       2 . A turbine engine assembly in accordance with  claim 1  further comprising a booster compressor coupled to said second low-pressure turbine section. 
   
   
       3 . A turbine engine assembly in accordance with  claim 1  wherein said core gas turbine engine comprises a high pressure core. 
   
   
       4 . A turbine engine assembly in accordance with  claim 2  further comprising a second gear assembly coupled between said booster compressor and said second low-pressure turbine section. 
   
   
       5 . A turbine engine assembly in accordance with  claim 2  wherein said booster compressor is configured to rotate in the second direction. 
   
   
       6 . A turbine engine assembly in accordance with  claim 1  wherein said fan assembly comprises a single stage fan. 
   
   
       7 . A turbine engine assembly in accordance with  claim 1  wherein said first direction is opposite said second direction. 
   
   
       8 . A turbine engine assembly in accordance with  claim 1  wherein said fan assembly is configured to rotate in said second rotational direction. 
   
   
       9 . A method for assembling a gas turbine engine, the method comprising:
 coupling a first section of a low pressure turbine downstream of a core gas turbine engine, wherein the first section of the low pressure turbine rotates in a first direction;   coupling a first gear assembly to the first section of the low pressure turbine;   coupling a second section of the low pressure turbine to the first gear assembly, wherein the second section of the low pressure turbine rotates in a second direction; and   coupling a single stage fan assembly to the second section of the low pressure turbine.   
   
   
       10 . A method in accordance with  claim 9  further comprising:
 coupling a second gear assembly to said fan assembly; and   coupling a booster compressor to the second gear assembly.   
   
   
       11 . A method in accordance with  claim 9  further comprising coupling a booster compressor to the second section of the low-pressure turbine. 
   
   
       12 . A method in accordance with  claim 9  wherein coupling a first stage of a low pressure turbine to a core turbine engine further comprises coupling a first stage of a low pressure turbine to a high pressure ratio core turbine engine. 
   
   
       13 . A method in accordance with  claim 9  wherein coupling a single stage fan assembly to the second section of the low pressure turbine engine further comprises coupling a single stage fan assembly configured to rotate in a second direction to the second section of the low pressure turbine engine. 
   
   
       14 . A method in accordance with  claim 11  wherein coupling a booster compressor to the second section of the low-pressure turbine further comprises coupling the booster compressor configured to rotate in the second direction to the second section of the low-pressure turbine. 
   
   
       15 . A gas turbine engine assembly comprising:
 a core gas turbine engine;   a first low-pressure turbine section in serial flow communication with said core gas turbine engine;   a second low-pressure turbine section in serial flow communication with said core gas turbine engine aft of said first low-pressure turbine section;   a fan assembly coupled to said second low-pressure turbine section;   a booster compressor coupled to said first low-pressure turbine section; and   a gear assembly coupled between said booster compressor and said fan assembly.   
   
   
       16 . A gas turbine engine assembly in accordance with  claim 15  wherein said booster compressor rotates in a first direction and said second low-pressure turbine section rotates in a second direction, opposite the first direction. 
   
   
       17 . A gas turbine engine assembly in accordance with  claim 15  wherein said booster compressor is coupled to said first low-pressure turbine section via a first drive shaft and said fan assembly is coupled to said second low-pressure turbine section via a second drive shaft. 
   
   
       18 . A gas turbine engine assembly in accordance with  claim 15  wherein said booster compressor rotates at a first rotational speed and said second low pressure turbine section rotates at a second rotational speed, wherein the first rotational speed is substantially faster than the second rotational speed. 
   
   
       19 . A gas turbine engine assembly in accordance with  claim 15  wherein said fan assembly comprises a single stage fan assembly.