Gas turbine engine and a diffuser therefor

Details Gas turbine engine and a diffuser therefor Gas turbine engine and a diffuser therefor

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 1/08 (2006.01) F01D 25/30 (2006.01) F01N 5/00 (2006.01) F02B 37/00 (2006.01) F02G 5/02 (2006.01) F02K 3/00 (2006.01) F04D 29/54 (2006.01) F15D 1/04 (2006.01)

Patent

CA 2153534

A gas turbine engine (10) with first and second axial flow compressors (14,22) and an intercooler (20) therebetween is provided with a bend diffuser (16) and a radial flow diffuser (18) to diffuse the air leaving the downstream end (38) of the first axial flow compressor (14) at a first radial distance (R1) from the axis (A) to the upstream end of the intercooler (20) at a second radial distance (R2) from the axis (A). The bend diffuser (16) comprises a first radially outer wall (54) and a second radially inner wall (56). The first wall (54) is elliptical and the second wall (56) has a profile derived from a relationship between the local area ratio and the path length around the arc such there is rapid diffusion in the bend diffuser (16) without fluid flow separation from the first wall (54).

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