Gas turbine engine aircraft mounting system
AssigneeRtx Corporation
InventorsMurat Yazici, Andrew E. Breault
Life of this patent
Estimating the term…
Abstract
An aircraft system is provided that includes a pylon, a gas turbine engine, a forward mount, an aft mount, and a thrust link. The gas turbine engine includes a compressor section, a fan section, and a turbine exhaust case (TEC). The gas turbine engine has an axially extending engine centerline. The forward mount is connected to the compressor section and the pylon along a mount plane. The aft mount is connected to the TEC and the pylon. The thrust link extends along a thrust link centerline between the forward mount and the compressor section. The thrust link is oriented such that a thrust link vector coincident with the thrust link centerline intersects with the mount plane at an intersection point that is located below the engine centerline.
Claims20
An aircraft system, comprising:
- a pylon;
- a gas turbine engine comprising a compressor section, a fan section, and a turbine exhaust case (TEC), wherein the gas turbine engine has an axially extending engine centerline;
- a forward mount connected to the compressor section and to the pylon along a mount plane;
- an aft mount connected to the TEC and to the pylon;
- and
- a thrust link that extends along a thrust link centerline between the forward mount and the compressor section;
- wherein the thrust link is oriented such that a thrust link vector coincident with the thrust link centerline intersects with the mount plane at an intersection point that is located below the engine centerline.
An aircraft system, comprising:
- a pylon;
- a gas turbine engine comprising an axially extending engine centerline, a fan section, a compressor section, a turbine exhaust case (TEC), and a fan drive gear system (FDGS), wherein the fan section has a fan outer radial diameter value;
- a forward mount connecting the compressor section to the pylon at a connection point, wherein a mount plane extends through the connection point;
- an aft mount (AM) connected to the TEC and to the pylon, wherein the aft mount is separated from the forward mount by a mount separation distance value;
- a thrust link that extends along a thrust link centerline between the forward mount and the compressor section, wherein the thrust link is oriented such that a thrust link vector coincident with the thrust link centerline intersects with the mount plane at an intersection point;
- wherein the FDGS includes a center of gravity (CG) and the FDGS CG is separated from the intersection point by an FDGS axial distance value;
- wherein the system is configured such that when a parameter value “P” is determined using the mount separation distance value, the fan outer radial diameter value, the FDGS axial distance value, and the AM radial distance value, and an expression:
- P=(B/E)*(−C/D)
- wherein within the expression, “B” represents the fan outer radial diameter value, “E” represents the mount separation distance value, “C” represents the FDGS axial distance value, and “D” represents the vertical distance between the engine centerline and the connection point, and the determined value for “P” is less than zero.
Dependencies are inferred from the claim text.