Abstract: Systems, apparatus, articles of manufacture, and methods for mounting a gas turbine engine to a pylon are disclosed. An example gas turbine engine disclosed herein a first mount, a first frame portion to be coupled to a pylon via the first mount, a second frame portion coupled to the first frame portion such that second frame portion is cantilevered from the first frame portion, and a second mount to couple the second frame portion to the pylon, the second mount defining a load path between the pylon and the second frame portion, the second mount including an elastic element disposed in the load path.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.

Abstract: Methods, apparatus, systems and articles of manufacture for mounting a gas turbine engine are described. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon includes: a thrust link coupled to the gas turbine engine and an aft mount, the gas turbine engine coupled to the pylon via a forward mount and the aft mount, a bending restraint having a first end and a second end, the bending restraint including an actuator positioned at the first end to apply a force to a fan section of the gas turbine engine, a first joint positioned at the first end of the bending restraint, the first joint coupled to the first end of the bending restraint and the fan section, and a second joint positioned at the second end of the bending restraint, the second joint coupled to the second end of the bending restraint.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon includes: a thrust link coupled to the gas turbine engine and an aft mount, the gas turbine engine coupled to the pylon via a forward mount and the aft mount, a bending restraint having a first end and a second end, the bending restraint including an actuator positioned at the first end to apply a force to a fan section of the gas turbine engine, a first joint positioned at the first end of the bending restraint, the first joint coupled to the first end of the bending restraint and the fan section, and a second joint positioned at the second end of the bending restraint, the second joint coupled to the second end of the bending restraint.

Abstract: Dual function links for gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of a gas turbine engine to a pylon, the apparatus includes a first pin and a linkage including a first linkage portion including the first pin, a second linkage portion, the second linkage portion forming a first load path between the gas turbine engine and the pylon, the second linkage portion arranged with respect to the first linkage portion such that a gap prevents the first linkage portion from forming a second load path between the gas turbine engine and the pylon.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.

Abstract: Dual function links for gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of a gas turbine engine to a pylon, the apparatus includes a first pin and a linkage including a first linkage portion including the first pin, a second linkage portion, the second linkage portion forming a first load path between the gas turbine engine and the pylon, the second linkage portion arranged with respect to the first linkage portion such that a gap prevents the first linkage portion from forming a second load path between the gas turbine engine and the pylon.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed to methods and apparatus for gas turbine bending isolation. An example mechanical interface to couple a first section of a gas turbine to a second section of the gas turbine, the mechanical interface comprising a first mating surface disposed on the first section, and a second mating surface disposed on the second section and circumferentially around the first mating surface, wherein the coupling of the first mating surface to the second mating surface enables the first section to rotate about the mechanical interface during operation of the gas turbine.

Abstract: Damper engine mount links are disclosed. An example engine assembly includes a core including a fore portion and an aft portion, the fore portion of the core to couple to a fan hub frame, the aft portion of the core to couple to a turbine rear frame or a turbine center frame. The engine assembly further includes a forward mount to couple the fan hub frame to an aircraft, and a damper link to couple the turbine rear frame or the turbine center frame to an aircraft mount.

Abstract: Bearings with visually distinct wear indicators are disclosed. An example bearing disclosed herein includes a movable portion, a race to receive the movable portion along a first surface to thereby permit movement of the movable portion within the race, and a liner disposed on the first surface of the race, the liner having a first layer and a second layer, the first layer disposed on top of the second layer, the first layer visually distinctive from the second layer.

Abstract: Damper engine mount links are disclosed. An example engine assembly includes a core including a fore portion and an aft portion, the fore portion of the core to couple to a fan hub frame, the aft portion of the core to couple to a turbine rear frame or a turbine center frame. The engine assembly further includes a forward mount to couple the fan hub frame to an aircraft, and a damper link to couple the turbine rear frame or the turbine center frame to an aircraft mount.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed to methods and apparatus for gas turbine bending isolation. An example mechanical interface to couple a first section of a gas turbine to a second section of the gas turbine, the mechanical interface comprising a first mating surface disposed on the first section, and a second mating surface disposed on the second section and circumferentially around the first mating surface, wherein the coupling of the first mating surface to the second mating surface enables the first section to rotate about the mechanical interface during operation of the gas turbine.

Abstract: Bearings with visually distinct wear indicators are disclosed. An example bearing disclosed herein includes a movable portion, a race to receive the movable portion along a first surface to thereby permit movement of the movable portion within the race, and a liner disposed on the first surface of the race, the liner having a first layer and a second layer, the first layer disposed on top of the second layer, the first layer visually distinctive from the second layer.

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A mechanical linkage for mounting a gas turbine engine to a pylon includes: a bending restraint having a first end and a second end; a first joint at the first end of the bending restraint to connect the first end of the bending restraint to a fan section of the gas turbine engine; and a second joint at the second end of the bending restraint to connect the second end of the bending restraint to the pylon.