Reverse flow ceramic matrix composite combustor

摘要

A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner (17) enclosing a combustion chamber (36). The inner liner (17) has a dome portion (24) at an upstream end of the combustor and a downstream combustor exit (27) defined between a small exit duct (28) portion and a large exit duct portion (26). At least one of the dome portion (24), the small exit duct portion (28) and the large exit duct portion (26) is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite.