Assembly for supporting a gas turbine engine comprises a support member including mounting sites for attachment to an associated aircraft. The support member includes integral slider tracks disposed on opposed sidewalls for selective engagement with a translatable cowl. The translatable cowl is tran
Assembly for supporting a gas turbine engine comprises a support member including mounting sites for attachment to an associated aircraft. The support member includes integral slider tracks disposed on opposed sidewalls for selective engagement with a translatable cowl. The translatable cowl is translatable along the slider tracks to selectively cover and expose a cascade thrust-reversing structure. The cascade structure includes arcuate segments mounted in hinged relationship to the support member. Rearward translation of the translatable cowl to a service position permits the cascade structure to be opened for access to the core engine.
대표청구항▼
1. A system comprising: an engine assembly comprising a gas turbine engine having a core cowl, a nacelle structure surrounding the gas turbine engine, and a by-pass duct between the nacelle structure and the core cowl of the gas turbine engine; andan integrated thrust reverser/pylon sub-assembly ada
1. A system comprising: an engine assembly comprising a gas turbine engine having a core cowl, a nacelle structure surrounding the gas turbine engine, and a by-pass duct between the nacelle structure and the core cowl of the gas turbine engine; andan integrated thrust reverser/pylon sub-assembly adapted for mounting the engine assembly to an aircraft, the integrated thrust reverser/pylon assembly comprising:a pylon including opposed sidewalls, opposed integral slider tracks disposed on the opposed sidewalls, opposed guide members disposed on the opposed sidewalls and spaced apart from the integral slider tracks, hinge mounts disposed on the opposed sidewalls between the guide members and the integral slider tracks, at least first forward and aft mounting sites connecting the pylon to the gas turbine engine, at least second forward mounting sites adapted to connect the pylon to the nacelle structure, and at least one mounting site adapted for mounting the pylon to the aircraft;a translatable cowl comprising an arcuate body having radially inner and outer panels defining an internal cavity therebetween, the inner panels of the translatable cowl being supported by the slider tracks of the pylon and the outer panels of the translatable cowl being supported by the guide members of the pylon for translation of the translatable cowl between at least a forward, closed position and a rearward, deployed position; andan openable cascade structure comprising arcuate cascade segments that are each mounted in hinged relationship to the pylon with the hinge mounts, wherein the cascade structure is at least partially disposed within the internal cavity when the translatable cowl is in the closed position and exposed when the translatable cowl is in the deployed position;wherein the core cowl is disposed generally radially inward of the translatable cowl when the translatable cowl is in the forward position, and the core cowl includes at least one movable panel operable to close and open an opening in the core cowl;wherein the sidewalls of the pylon are convergent in a radially inward direction to a lower extremity thereof adjacent the core cowl and thereby provide an upper bifurcation having an inverted triangular cross-section within the by-pass duct of the, as turbine engine; anda track or rail, provided on a cascade support member disposed generally diametrically opposed to the pylon, to support and direct movement of the translatable cowl, wherein the track or rail does not extend into the by-pass duct; andwherein the by-pass duct does not comprise a lower bifurcation. 2. An integrated thrust reverser/pylon assembly adapted for mounting an aircraft engine assembly to an aircraft, the aircraft engine assembly comprising a gas turbine engine having a core cowl, a nacelle structure surrounding the gas turbine engine, and a by-pass duct between the nacelle structure and the core cowl of the gas turbine engine, the integrated thrust reverser/pylon assembly comprising: a pylon including opposed sidewalls within the by-pass duct, at least first forward and aft mounting sites adapted to connect the pylon to the gas turbine engine, at least second forward mounting sites adapted to connect the pylon to the nacelle structure, and at least one mounting site adapted for mounting the pylon to the aircraft; wherein the sidewalls of the pylon are convergent in a radially inward direction to a lower extremity thereof adjacent the core cowl and thereby provide an upper bifurcation having an inverted triangular cross-section within the by-pass duct of the gas turbine engine;opposed integral slider tracks disposed on the opposed sidewalls, opposed guide members disposed on the opposed sidewalls and spaced apart from the integral slider tracks, and hinge mounts disposed on the opposed sidewalls between the guide members and the integral slider tracks;a translatable cowl comprising an arcuate body having radially inner and outer panels defining an internal cavity therebetween, the inner panels of the translatable cowl being supported by the slider tracks of the pylon and the outer panels of the translatable cowl being supported by the guide members of the pylon for translation of the translatable cowl between at least a forward, closed position and a rearward, deployed position;an openable cascade structure comprising arcuate cascade segments that are each mounted in hinged relationship to the pylon with the hinge mounts, wherein the cascade structure is at least partially disposed within the internal cavity when the translatable cowl is in the closed position and exposed when the translatable cowl is in the deployed position;a track or rail, provided on a cascade support member disposed generally diametrically opposed to the pylon, to support and direct movement of the translatable cowl, wherein the track or rail does not extend into the by-pass duct; andwherein the by-pass duct does not comprise a lower bifurcation. 3. The integrated thrust reverser/pylon assembly according to claim 2 wherein the radially inner and outer panels of the translatable cowl are coupled at a rearward end, and wherein the radially inner panel is slidably engageable with the slider tracks. 4. The integrated thrust reverser/pylon assembly according to claim 3 wherein the radially inner panel includes an inner surface configured to form at least a portion of the by-pass duct of the aircraft engine assembly. 5. The integrated thrust reverser/pylon assembly according to claim 2 wherein the translatable cowl is independently translatable relative to the cascade structure. 6. The integrated thrust reverser/pylon assembly according to claim 3 wherein the radially outer panel comprises at least one element of a v-groove/v-blade attachment at a forward end thereof for axial engagement with the nacelle structure of the aircraft engine assembly. 7. The integrated thrust reverser/pylon assembly according to claim 2 wherein the cascade structure comprises at least one element of a v-groove/v-blade attachment at a forward end thereof for radial engagement with a structure of the aircraft engine assembly. 8. The integrated thrust reverser/pylon assembly according to claim 2 wherein the arcuate body is substantially continuous through about a 330° structure. 9. The integrated thrust reverser/pylon assembly according to claim 2 wherein the arcuate cascade segments of the cascade structure comprise first and second arcuate cascade segments each being mounted in independent hinged relationship with the pylon, wherein each of the first and second arcuate cascade segments is selectively movable between a closed, operational condition and an open, serviceable condition. 10. The integrated thrust reverser/pylon assembly according to claim 9 wherein the cascade structure includes a latch operable to engage the first and second arcuate cascade segments in the operational condition. 11. The integrated thrust reverser/pylon assembly according to claim 2 wherein the translatable cowl is selectively operably engageable with the cascade support member.
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이 특허에 인용된 특허 (5)
Newton Arnold C,GBX, Cascade structure arrangement for a gas turbine engine.
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