Segmented effusion cooled gas turbine engine combustor

Details Segmented effusion cooled gas turbine engine combustor Segmented effusion cooled gas turbine engine combustor

F - Mech Eng,Light,Heat,Weapons

23

R

F23R 3/04 (2006.01) F01D 25/12 (2006.01) F02C 7/12 (2006.01)

Patent

CA 2575277

A combustor (124) includes two or more sets of effusion cooling holes (402) that extend through the inner and outer liners (202, 204). Each set of effusion cooling holes (402) includes one or more initial rows (406) of effusion cooling holes (404), one or more final rows (408) of effusion cooling holes (404) disposed downstream of the one or more initial rows (406), and a plurality of interposed rows (412) of effusion cooling holes (404) disposed between the initial and final rows (406, 408). Each effusion cooling hole (404) is disposed at a tangential angle relative to an axial line. The tangential angle of the effusion cooling holes (404) in each set of effusion cooling holes (402) gradually transitions from a substantially transverse tangential angle in each initial row (406) to a substantially axial tangential angle in each final row (408).

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