Granted Patent B2

US 12,246,845 · App. 18/246,478 · Granted Mar 11, 2025

Inventors: Michael Cline (Evendale, OH); Jonathan E. Coleman (Evendale, OH); Craig W. Higgins (Evendale, OH); Daniel E. Mollmann (Evendale, OH); Mark E. Linz (Evendale, OH); Guillaume Glemarec (Paris, FR); Valerio Capasso (Paris, FR); Jean-Baptiste Manuel Nicolas Vignes (Paris, FR); Nicolas Maurice Hervé Aussedat (Paris, FR); Francois Gallet (Paris, FR)

Assignees: General Electric Company; Safran Aircraft Engines

B64D27/40B64D27/406

Abstract

Claims (34)

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.

2. The apparatus of claim 1 , wherein at least one of (1) the first mount is to be indirectly coupled to the upstream section or (2) the second mount is to be indirectly coupled to the downstream section.

3. The apparatus of claim 1 , wherein the first mount is to be coupled to a fan casing of the gas turbine engine and the second mount is to be coupled to an intermediate compressor casing of the gas turbine engine.

4. The apparatus of claim 1 , wherein the first mount is to surround a first outer guide vane of the gas turbine engine.

5. The apparatus of claim 4 , wherein the first outer guide vane is oriented along the yaw axis.

6. The apparatus of claim 1 , wherein the first mount is to be at substantially the same position along the roll axis as a second outer guide vane of the gas turbine engine and a third outer guide vane of the gas turbine engine, the first mount disposed circumferentially between the second outer guide vane and the third outer guide vane.

7. The apparatus of claim 1 , wherein the second mount constrains rotation about the roll axis of the gas turbine engine, the second mount includes:

a first fastener disposed within the pylon; and

a second fastener disposed within the pylon, the second fastener opposite the first fastener about the pylon.

8. The apparatus of claim 7 , wherein the first fastener forms a clevis with a boss of the pylon.

9. The apparatus of claim 1 , wherein the first mount includes at least one of a trunnion or a yoke, the first mount to constrain translation along the pitch axis of the gas turbine engine and translation along the yaw axis of the gas turbine engine.

10. A gas turbine engine coupled to a pylon, the gas turbine engine defining a roll axis, a yaw axis, and a pitch axis, the gas turbine engine comprising:

a first section;

a second section coupled to the first section, the second section downstream from the first section;

a first mount to couple the first section of the gas turbine engine to the pylon;

a second mount to couple the first section of the gas turbine engine to the pylon, the second mount downstream of the first mount; and

a thrust linkage to couple the first section to the pylon,

wherein the second section is decouplable from the first 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 second section is cantilevered from the first section.

11. The gas turbine engine of claim 10 , wherein the first section includes a low pressure compressor, and the second section includes a high pressure compressor, a combustor, a high-pressure turbine, and a low-pressure turbine.

12. The gas turbine engine of claim 10 , wherein the first section includes a fan casing and an intermediate compressor casing, the first mount coupled to the fan casing and the second mount is coupled to the intermediate compressor casing.

13. The gas turbine engine of claim 10 , further including a first outer guide vane, the first mount surrounding the first outer guide vane.

14. The gas turbine engine of claim 13 , wherein the first outer guide vane is oriented along the yaw axis.

15. The gas turbine engine of claim 10 , further including a second outer guide vane and a third outer guide vane and wherein the first mount is at a substantially the same position along the roll axis of the gas turbine engine as the second outer guide vane of the gas turbine engine and the third outer guide vane of the gas turbine engine, the first mount disposed circumferentially between the second outer guide vane and the third outer guide vane.

16. The gas turbine engine of claim 10 , wherein the second mount constrains rotation about the roll axis, the second mount includes:

a first fastener disposed within the pylon; and

a second fastener disposed within the pylon, the second fastener opposite the first fastener about the pylon.

17. The gas turbine engine of claim 16 , wherein the first fastener forms a clevis with a boss of the pylon.

18. The gas turbine engine of claim 10 , wherein the first mount includes at least one of a trunnion or a yoke, the first mount to constrain translation along the pitch axis of the gas turbine engine and translation along the yaw axis of the gas turbine engine.

19. The apparatus of claim 1 , wherein the downstream section is a core section.

20. The gas turbine engine of claim 10 , wherein the second section is a core section.

Assignments (2)

Continuity (1)

References Cited (25)

Cited By (1)

US 12,703,496