SEGMENTED EFFUSION COOLED GAS TURBINE ENGINE COMBUSTOR

摘要

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 hole s (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 fin al row (408).