Gas turbine engine and casing assembly therefor

A gas turbine engine, comprising:

• a fan section, compressor section, combustor section, and turbine section in serial flow arrangement, at least one of the fan section, the compressor section, or the turbine section comprising:
• a rotor comprising a plurality of blades and rotatable about a rotational axis;
• and
• a casing assembly disposed at least partially around the rotor, the casing assembly comprising:
• a forward casing section;
• an aft casing section;
• an outer ring coupled to the forward casing section and the aft casing section, the outer ring coupled to the forward casing section at a joint;
• and
• an inner containment ring radially inward of the outer ring, and at least partially axially aligned with the plurality of blades, the inner containment ring extending axially between a leading edge and a trailing edge;
• wherein the leading edge is axially forward of the joint, with respect to the rotational axis.

A gas turbine engine, comprising:

• a fan section, compressor section, combustor section, and turbine section in serial flow arrangement, at least one of the fan section, the compressor section, or the turbine section comprising:
• a rotor comprising a plurality of blades and rotatable about a rotational axis;
• and
• a casing assembly disposed at least partially around the rotor, the casing assembly comprising:
• a forward casing section;
• an aft casing section;
• an outer ring coupled to the forward casing section and the aft casing section, the outer ring coupled to the forward casing section at a joint;
• and
• an inner containment ring radially inward of the outer ring, and at least partially axially aligned with the plurality of blades;
• wherein the outer ring includes a first composite material, and the inner containment ring includes a second composite material that is co-cured or pre-molded with the first composite material.