Reverse flow ceramic matrix composite combustor

摘要

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

主权项

1. An annular reverse-flow combustor for a gas turbine engine, the combustor defining a combustion chamber therewithin, the combustor comprising:
an inner liner substantially enclosing said combustion chamber and having at least three liner portions including a dome, a small exit duct and a large exit duct, each of the three liner portions being an independently formed hemi-toroidal shell; and a radially inner and a radially outer concentric metallic rings disposed between and interconnecting the dome with the small exit duct and the large exit duct, the radially outer metallic ring is disposed between an upstream end of the large exit duct and a radially outer end of the dome, and the radially inner metallic ring is disposed between an upstream end of the small exit duct and a radially inner end of the dome, wherein at least one of the three liner portions is made of a ceramic matrix composite and a remainder of the three liner portions are metallic, the at least one of the three liner portions made of the ceramic matrix composite having a compressive pre-load force applied thereto.