CPC F01D 25/243 (2013.01) [B64D 27/26 (2013.01); F01D 25/285 (2013.01); B64D 2027/262 (2013.01); B64D 2027/264 (2013.01); B64D 2027/266 (2013.01); B64D 2027/268 (2013.01); F05D 2220/32 (2013.01); F05D 2240/90 (2013.01)] | 13 Claims |
1. A gas turbine engine comprising:
a casing,
a rotor rotatable around a rotation axis relative the casing, the casing extending along and around the rotation axis, an axial orientation defined parallel to the rotation axis, a vertical radial orientation defined normal to the axial orientation, the vertical radial orientation extending from a bottom to a top, and a horizontal radial orientation defined normal to both the axial orientation and to the vertical radial orientation, the horizontal radial orientation extending from a first side of the rotation axis to a second side of the rotation axis that is opposite the first side;
a first component mounted externally to the casing by a first mount, the first mount defining a torsion axis extending along the vertical radial orientation, the first component having a center of gravity located on the first side of the torsion axis;
a second component mounted externally to the casing on the second side, extending along the vertical radial orientation from a bottom portion of the second component to a top portion of the second component, a second mount connecting the bottom portion of the second component to the casing; and
a structure connecting the top portion of the second component to at least one of the first component and the first mount, on the second side of the torsion axis;
wherein the structure is more elastically flexible in the axial orientation than in the horizontal radial orientation, and has an end freely slidable along the vertical radial orientation.
|