An aircraft including a pylon attached to a gas turbine engine and a mounting system attaching the engine to the pylon. The mounting system including a first and a second frame each of three elongate members arranged in a triangle, each frame respectively arranged such that a core of the engine is p
An aircraft including a pylon attached to a gas turbine engine and a mounting system attaching the engine to the pylon. The mounting system including a first and a second frame each of three elongate members arranged in a triangle, each frame respectively arranged such that a core of the engine is positioned extending through an area defined between the three elongate members of each frame. Each frame forming at least part of a load bearing connection between the pylon and the engine. Each frame consisting of two portions, each portion corresponding to each side of the engine as attached to the pylon. The triangle formed by each frame being symmetrical about a plane separating the two portions. The engine is attached to the mounting system such that both frames are positioned axially forward of a radially extending projection of a first turbine stage in the core.
대표청구항▼
1. An aircraft comprising: a pylon;a gas turbine engine attached to the pylon; anda mounting system attaching the gas turbine engine to the pylon, the mounting system including: a first frame of three elongate members arranged in a triangle, the first frame being arranged such that a core of the gas
1. An aircraft comprising: a pylon;a gas turbine engine attached to the pylon; anda mounting system attaching the gas turbine engine to the pylon, the mounting system including: a first frame of three elongate members arranged in a triangle, the first frame being arranged such that a core of the gas turbine engine is positioned extending through an area defined between the three elongate members of the first frame, the first frame forming at least part of a load bearing connection between the pylon and the gas turbine engine, the first frame consisting of two portions, each portion respectively corresponding to each side of the gas turbine engine as attached to the pylon at a location of the first frame, the triangle formed by the first frame being symmetrical about a first plane separating the two portions of the first frame; anda second frame of three elongate members arranged in a triangle, the second frame being arranged such that the core of the gas turbine engine is positioned extending through an area defined between the three elongate members of the second frame, the second frame forming at least part of the load bearing connection between the pylon and the gas turbine engine, the second frame consisting of two portions, each portion respectively corresponding to each side of the gas turbine engine as attached to the pylon at a location of the second frame, the triangle formed by the second frame being symmetrical about a second plane separating the two portions of the second frame whereinthe gas turbine engine is attached to the mounting system such that both of the first frame and the second frame are positioned axially forward of a radially extending projection of a first turbine stage in the core of the gas turbine engine. 2. The aircraft according to claim 1, wherein the first plane separating the two portions of the first frame is the same as a plane extending along a rotating axis of the gas turbine engine. 3. The aircraft according to claim 1, wherein the first frame is oriented parallel to a plane perpendicular to a rotating axis of the gas turbine engine. 4. The aircraft according to claim 1, wherein the first frame and the second frame are axially separated and oriented parallel to each other. 5. The aircraft according to claim 1, wherein the mounting system further includes a first elongate spar extending from the pylon and is attached to one of the elongate members of the first frame. 6. The aircraft according to claim 5, wherein the first elongate spar extends in a direction parallel to the one of the elongate members of the first frame to which the first elongate spar is attached. 7. The aircraft according to claim 5, wherein the mounting system is configured such that the first frame is lowered directly vertically when the first elongate spar is disengaged from the first frame, and such that the first frame is raised directly vertically to engage the first elongate spar with the first frame and mount the first frame. 8. The aircraft according to claim 5, wherein the mounting system further includes a second elongate spar extending from the pylon and is attached to one of the elongate members of the second frame. 9. The aircraft according to claim 1, wherein the gas turbine engine is attached to the mounting system such that at least one of the first frame and the second frame is positioned axially rearward of a radially extending projection of a final compressor stage in the core of the gas turbine engine. 10. The aircraft according to claim 1, wherein frame links extend from vertices of the first frame and attach the mounting system to the core of the gas turbine engine. 11. A gas turbine engine comprising: a mounting system attaching the gas turbine engine to a pylon of an aircraft, the mounting system including: a first frame of three elongate members arranged in a triangle, the first frame being arranged so that a core of the gas turbine engine is positioned extending through an area defined between the three elongate members of the first frame, the first frame being arranged so that the first frame forms at least part of a load bearing connection between the pylon and the gas turbine engine, the first frame consisting of two portions, each portion respectively corresponding to each side of the gas turbine engine as attached to the pylon at a location of the first frame, the triangle formed by the first frame being symmetrical about a first plane separating the two portions of the first frame; anda second frame of three elongate members arranged in a triangle, the second frame being arranged so that the core of the gas turbine engine is positioned extending through an area defined between the three elongate members of the second frame, the second frame being arranged so that the second frame forms at least part of the load bearing connection between the pylon and the gas turbine engine, the second frame consisting of two portions, each portion respectively corresponding to each side of the gas turbine engine as attached to the pylon at a location of the second frame, the triangle formed by the second frame being symmetrical about a second plane separating the two portions of the second frame; whereinthe gas turbine engine is attached to the mounting system such that both of the first frame and the second frame are positioned axially forward of a radially extending projection of a first turbine stage in the core of the gas turbine engine. 12. An aircraft comprising the gas turbine engine according to claim 11.
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이 특허에 인용된 특허 (3)
O\Brien Michael T. (Cincinnati OH) Bobo ; deceased Melvin (late of Cincinnati OH by Beatrice L. Bobo ; executor), Aircraft gas turbine engine sideways mount.
Taylor Mike C. (Derby GB2) Hodgkinson Carl (Derby GB2) Wright Kenneth W. (Derby GB2) Perry Derek (Derby GB2), Mounting arrangement for a gas turbine engine.
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