A plurality of hatches are distributed on the rear periphery of an engine cowl. The hatches are opened only when turbojet engine power is greater than cruising power. In an open position, the hatches draw hot air jets passing through an intermediate chamber before ejecting the jets through longitudi
A plurality of hatches are distributed on the rear periphery of an engine cowl. The hatches are opened only when turbojet engine power is greater than cruising power. In an open position, the hatches draw hot air jets passing through an intermediate chamber before ejecting the jets through longitudinally-distributed communication components.
대표청구항▼
1. A turbofan turbine engine for an aircraft, comprising: a hollow nacelle having a longitudinal axis and comprising, at the front, an air inlet and, at the rear, an air outlet;a fan placed axially in said nacelle opposite said air inlet and capable of generating the cold flow of said turbine engine
1. A turbofan turbine engine for an aircraft, comprising: a hollow nacelle having a longitudinal axis and comprising, at the front, an air inlet and, at the rear, an air outlet;a fan placed axially in said nacelle opposite said air inlet and capable of generating the cold flow of said turbine engine;a generator placed axially in said nacelle, behind said fan, said generator being capable of generating the axial hot flow of said turbine engine surrounded by said cold flow and being enclosed in an engine cowl; anda fan channel inner cowl coaxially surrounding said hot flow generator so as: to delimit with the nacelle a channel of annular section for said cold flow, the channel terminates in said air outlet of the nacelle;to delimit with said engine cowl an intermediate chamber of annular section; andto converge via a rear portion of the fan channel inner cowl with a rear portion of said engine cowl so that respective rear edges of the rear portions form an edge of an outlet orifice of said hot flow at a rear portion of said intermediate chamber,wherein:provided in the rear portion of said intermediate chamber are communication means placed about said longitudinal axis and configured to place said intermediate chamber in communication with the outside, in the vicinity of a boundary between said cold flow and said hot flow;a plurality of hatches are provided that are arranged in said rear portion of the engine cowl, while being distributed on the periphery of the rear portion of the engine cowl;said hatches are opened only when the speed of said turbine engine is greater than a threshold corresponding to at least the cruising speed of the aircraft; andin the open position, said hatches draw off, from said hot flow, individual jets of hot air flowing into said intermediate chamber before leaving the intermediate chamber through said communication means while being distributed about said longitudinal axis. 2. The turbine engine as claimed in claim 1, wherein said communication means comprise a plurality of individual communication openings distributed on the periphery of said rear portion of the intermediate chamber. 3. The turbine engine as claimed in claim 1, in which, on the periphery of said outlet orifice of the hot flow, only one of said rear edges of said fan channel inner cowl or of said engine cowl is notched by recesses for attenuating the jet noise of said turbine engine, wherein said recesses form at least in part said communication means. 4. The turbine engine as claimed in claim 3, in which each recess has at least the approximate shape of a triangle, wherein an individual jet of hot air flows out in the corresponding recess through a side edge of said recess. 5. The turbine engine as claimed in claim 1, in which said rear edges of said fan channel inner cowl and of said engine cowl arrange between them a slot, wherein at least portions of said slot form at least in part said communication means. 6. The turbine engine as claimed in claim 1, wherein said threshold is such that said hatches are opened on take-off of the aircraft. 7. The turbine engine as claimed in claim 1, for an aircraft comprising a plurality of such turbine engines, wherein said threshold is such that said hatches are opened for the speed that must be adopted, in the case of a failure of at least one of said turbine engines, by those of said turbine engines that are in working order. 8. The turbine engine as claimed in claim 1, wherein with each hatch is associated a closing and opening system sensitive to the value of a physical magnitude characterizing the state of said hot flow. 9. The turbine engine as claimed in claim 8, wherein each closing and opening system of a hatch comprises a bimetallic strip. 10. The turbine engine as claimed in claim 9, wherein each hatch comprises an elastic strip configured to interact with an opening made in said rear portion of said engine cowl, said elastic strip is fixedly attached to said rear portion along an edge of said opening and said bimetallic strip system is fixedly attached, on one side, to said rear portion and, on the other side, to said elastic strip. 11. The turbine engine as claimed in claim 1, wherein said hatches are opened in the direction of said intermediate chamber. 12. The turbine engine as claimed in claim 8, wherein said system for closing and opening each hatch is on the side of said intermediate chamber. 13. The turbine engine as claimed in claim 1, wherein, on a side of said intermediate chamber, each hatch is protected by a rearward-opening casing. 14. The turbine engine as claimed in claim 1, wherein, provided behind said hatches are means for the guidance of said jets of hot air. 15. The turbine engine as claimed in claim 13, wherein said guidance means comprise said protective casings.
Subramaniyan, Moorthi; Hansen, Christian Michael; Huntington, Richard A.; Denman, Todd Franklin, System and method for exhausting combustion gases from gas turbine engines.
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