Methods and apparatus for gas turbine bending isolation

A gas turbine engine, comprising:

• a first section including a fan section;
• a second section including at least one of a high pressure compressor, a low pressure turbine, or a high pressure turbine;
• and
• a pinned joint, the pinned joint including a first mating surface disposed radially about the first section and a second mating surface disposed radially about the second section, the first mating surface and the second mating surface joined via a plurality of pins, between the first section and the second section, the pinned joint enabling the first section to rotate about the second section while retaining the gas turbine engine to a vehicle mount during operation of the engine,
• a ring disposed between the first mating surface and the second mating surface;
• a first one of the plurality of pins coupling the first mating surface to the ring;
• and
• a second one of the plurality of pins coupling the second mating surface to the ring.

An apparatus comprising;

• a gas turbine engine having a first section and a second section;
• means for coupling the first section to the second section, the means for coupling enabling the first section to rotate about the second section and retain the engine to a vehicle mount during operation of the gas turbine engine, the means for coupling including a pinned joint that includes a first mating surface disposed radially around the first section and a second mating surfaced disposed radially about the second section, the first mating surface and the second mating surface joined via a plurality of means for pinning;
• a ring disposed between the first mating surface and the second mating surface;
• a first one of the means for pinning, to couple the first mating surface to the ring;
• and
• a second one of the means for pinning, to couple the second mating surface to the ring.