US 12,246,845 B2
Methods and apparatus for mounting a gas turbine engine
Michael Cline, Evendale, OH (US); Jonathan E. Coleman, Evendale, OH (US); Craig W. Higgins, Evendale, OH (US); Daniel E. Mollmann, Evendale, OH (US); Mark E. Linz, Evendale, OH (US); Guillaume Glemarec, Paris (FR); Valerio Capasso, Paris (FR); Jean-Baptiste Manuel Nicolas Vignes, Paris (FR); Nicolas Maurice Hervé Aussedat, Paris (FR); and Francois Gallet, Paris (FR)
Assigned to General Electric Company, Evendale, OH (US); and Safran Aircraft Engines, Paris (FR)
Appl. No. 18/246,478
Filed by General Electric Company, Schenectady, NY (US); and Safran Aircraft Engines, Paris (FR)
PCT Filed May 20, 2021, PCT No. PCT/US2021/033476
§ 371(c)(1), (2) Date Mar. 23, 2023,
PCT Pub. No. WO2022/245363, PCT Pub. Date Nov. 24, 2022.
Prior Publication US 2023/0356853 A1, Nov. 9, 2023
Int. Cl. B64D 27/40 (2024.01)
CPC B64D 27/40 (2024.01) [B64D 27/406 (2024.01)] 20 Claims
OG exemplary drawing
 
1. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine engine including an upstream section and a downstream section, the gas turbine engine defining a roll axis, a yaw axis, and a pitch axis, the apparatus comprising:
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; and
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, and a center of gravity of the gas turbine engine is between the first mount and the second mount, such that the downstream section is cantilevered from the upstream section.