Gas turbine engine compressor arrangement

Abstract

A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. The engine includes a combination of quantities providing beneficial operation.

We claim: 
     
         1 . A gas turbine engine comprising:
 a fan section;   a gear arrangement configured to drive said fan section;   a compressor section, including both a low pressure compressor section and a high pressure compressor section;   a turbine section configured to drive said compressor section and said gear arrangement; and   wherein an overall pressure ratio provided by the combination of said low pressure compressor section and said high pressure compressor section being greater than or equal to about 35; wherein a pressure ratio across said low pressure compressor section being less than or equal to about 8; wherein said turbine section includes a low pressure turbine section driving said low pressure compressor section; and wherein a pressure ratio across said low pressure turbine section being greater than about 5.   
     
     
         2 . A gas turbine engine comprising:
 a fan section;   a gear arrangement configured to drive said fan section;   a compressor section, including both a low pressure compressor section and a high pressure compressor section;   a turbine section configured to drive said compressor section and said gear arrangement; and   wherein an overall pressure ratio provided by the combination of said low pressure compressor section and said high pressure compressor section being greater than or equal to about 35; wherein a pressure ratio across said high pressure compressor section being greater than or equal to about 7; wherein said turbine section includes a low pressure turbine section driving said low pressure compressor section; and wherein a pressure ratio across said low pressure turbine section being greater than about 5.   
     
     
         3 . A gas turbine engine comprising:
 a fan section;   a gear arrangement configured to drive said fan section;   a compressor section, including both a low pressure compressor section and a high pressure compressor section;   a turbine section configured to drive said compressor section and said gear arrangement; and   wherein said high pressure compressor includes 8 or more stages; wherein said low pressure compressor includes fewer stages than said high pressure compressor; and wherein said gear arrangement defines a gear reduction ratio being greater than or equal to about 2.3.