Compressor flowpath

Abstract

A core flowpath through a low pressure compressor section of a gas turbine engine includes an outer diameter, which has a slope angle relative to an axis defined by the core flowpath. The slope angle is a slope angle that is operable to prevent flow separation of a fluid passing through the core flowpath.

1 . A turbine engine comprising:
 a compressor section having at least a low pressure compressor, and a core flowpath passing through said low pressure compressor, said core flowpath having an inner diameter and an outer diameter, wherein said outer diameter has a slope angle of between approximately 0 degrees and approximately 15 degrees relative to an engine central longitudinal axis;   a combustor in fluid communication with the compressor section; and   a turbine section in fluid communication with the combustor.   
     
     
         2 . The turbine engine of  claim 1 , further comprising a fan. 
     
     
         3 . The turbine engine of  claim 2 , wherein said fan is connected to at least a low speed spool through a geared architecture. 
     
     
         4 . The turbine engine of  claim 1 , wherein said slope angle is in the range of approximately 0 degrees to approximately 10 degrees relative to said engine central longitudinal axis. 
     
     
         5 . The turbine engine of  claim 4 , wherein said slope angle is approximately 6 degrees relative to said engine central longitudinal axis. 
     
     
         6 . The turbine engine of  claim 4 , wherein said slope angle is in the range of approximately 5 degrees to 7 degrees, relative to said engine central longitudinal axis. 
     
     
         7 . The turbine engine of  claim 1 , wherein said slope angle slopes toward said engine central longitudinal axis along a fluid flow direction of said core flowpath. 
     
     
         8 . The turbine engine of  claim 1 , wherein said low pressure compressor comprises at least one variable vane. 
     
     
         9 . The turbine engine of  claim 1 , wherein said low pressure compressor further comprises an exit guide vane, wherein said exit guide vane is located in a low pressure compressor outlet section of said core flowpath. 
     
     
         10 . The turbine engine of  claim 9 , wherein said low pressure compressor further comprises a low pressure bleed located between a low pressure compressor rotor and said exit guide vane. 
     
     
         11 . The turbine engine of  claim 10  wherein said low pressure bleed further comprises a bleed trailing edge, and wherein said bleed trailing edge extends into said core flowpath beyond said outer diameter of said core flowpath. 
     
     
         12 . The turbine engine of  claim 1 , wherein said low pressure compressor is a multi-stage compressor. 
     
     
         13 . The turbine engine of  claim 1 , wherein said inner diameter of said core flowpath increases through the low pressure compressor along a fluid flow direction. 
     
     
         14 . The turbine engine of  claim 1 , wherein said outer diameter slope angle is operable to reduce a tip clearance of a compressor rotor, and thereby reduce flow separation. 
     
     
         15 . A low pressure compressor for a turbine engine comprising a core flowpath, wherein said core flowpath has an inner diameter and an outer diameter, and wherein said outer diameter has a slope angle of between approximately 0 degrees and approximately 15 degrees relative to an engine central longitudinal axis about which said low pressure compressor rotates. 
     
     
         16 . The low pressure compressor of  claim 15 , wherein said slope angle is between approximately 0 degrees and approximately 10 degrees. 
     
     
         17 . The low pressure compressor of  claim 16 , wherein said slope angle is approximately 6 degrees. 
     
     
         18 . The low pressure compressor of  claim 15 , further comprising at least one variable vane. 
     
     
         19 . The low pressure compressor of  claim 15 , further comprising an outlet section of said core flowpath, wherein said outlet section includes an exit guide vane. 
     
     
         20 . The low pressure compressor of  claim 19 , further comprising a low pressure bleed located between a low pressure compressor rotor and said exit guide vane. 
     
     
         21 . The low pressure compressor of  claim 20 , wherein said low pressure bleed comprises a bleed trailing edge, and wherein said bleed trailing edge extends into said core flowpath beyond said outer diameter of said core flowpath. 
     
     
         22 . The low pressure compressor of  claim 15 , wherein said low pressure compressor is a multi-stage compressor. 
     
     
         23 . The low pressure compressor of  claim 15 , wherein said inner diameter of said core flowpath increases through the low pressure compressor along a fluid flow direction. 
     
     
         24 . The low pressure compressor of  claim 15 , wherein said outer diameter slope angle is operable to reduce a tip clearance of a compressor rotor, and thereby reduce flow separation.