Method of forming a thermally isolated gas turbine engine housing

A method for thermally isolating a gas turbine engine housing having an outer ring-shaped housing member and an inner hub attached by housing struts from high temperatures created by combustion gases flowing through the turbine engine, comprising the steps of:

• positioning a floating liner assembly between the inner hub and the outer ring-shaped housing member and arranging a plurality of liner struts to enclose the housing struts, with a plurality of openings extending through the floating liner;
• positioning an outer baffle assembly about the floating liner assembly, with a plurality of openings extending through portions of the outer baffle assembly;
• positioning an inner baffle assembly within the floating liner assembly, with a plurality of openings extending through portions of the inner baffle;
• creating a single, continuous passageway for delivering pressurized air through openings in the outer ring-shaped housing member that impacts and flows through the openings in the outer baffle assembly, the floating liner assembly, the liner struts and the inner baffle assembly for collecting heat from the floating liner and expelling the heat to a stream of combustion gases flowing through the gas turbine engine;
• and
• forming the floating liner assembly as separate inner and outer ring-shaped liner members having a number of openings, forming a cooling air passageway adjacent each of the floating liner ring-shaped members;
• and
• welding the inner ring-shaped liner member within the outer ring-shaped liner member to form a unitary floating liner assembly.

A method for thermally isolating a gas turbine outer ring-shaped housing member from high temperatures created by combustion gases flowing through the turbine engine, comprising the steps of:

• positioning a floating liner assembly between an inner hub and the outer ring-shaped housing member and forming the floating liner assembly from separate, inner and outer ring-shaped liner members, having a number of openings, forming an cooling air passageway around each of the floating liner members;
• positioning an outer baffle assembly having two similar, generally cylindrically-shaped members to surround the floating liner outer ring-shaped member, and forming the outer baffle assembly with a plurality of through openings;
• positioning an inner baffle assembly having two similar, generally cylindrically-shaped members within the floating liner inner ring-shaped member, and forming the inner baffle assembly with a plurality of through openings;
• and
• creating a single, continuous passageway for delivering pressurized air through openings in the outer ring-shaped housing member that impacts and flows through the openings in the outer baffle assembly, the floating liner assembly, the liner struts and the inner baffle assembly for collecting heat from the floating liner and expelling the heat to a stream of combustion gases flowing through the gas turbine engine.