COMPRESSOR FLOWPATH
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.