Patent ID: 8745989

Claim:
An annular reverse-flow combustor of a gas turbine engine, the combustor defining a combustion chamber therewithin, the combustor comprising: an inner liner having liner portions substantially enclosing said combustion chamber, the liner portions including a dome liner portion, a small exit duct liner portion and a large exit duct liner portion, the dome liner portion and the large exit duct liner portion being hemi-toroidal shells composed of a ceramic matrix composite; radially inner and outer concentric metallic rings disposed between and interconnecting the dome portion with the small and large exit duct portions, wherein the outer metallic ring is disposed between an upstream end of the long exit duct portion and a radially outer end of the dome portion, and the inner metallic ring is disposed between an upstream end of the small exit duct portion and a radially inner end of the dome portion; external metallic shells corresponding to and surrounding each of said three liner portions, the external metallic shells being spaced apart from the liner portions to define an annular gap therebetween which is free of other material, the external metallic shell surrounding the small exit duct portion being fastened to the inner metallic ring and retaining the small exit duct portion in place; and one or more spring element disposed between said dome liner portion and said large exit duct liner portion and a corresponding one of said metallic shells, said spring element producing a force against the corresponding liner portion in a direction toward the inner and outer metallic rings thereby generating a substantially axially directed compressive pre-load force in the corresponding liner portions composed of the ceramic matrix composite.