초록

A pre-cooler having an annular cross-sectional shape about the axis of a pod and arranged inside the rear part of an inner shroud in external contact with a cold flow exiting a fan duct channel and in close contact with a cooling air stream drawn from the cold flow.

대표청구항 ▼

1. A bypass turbine engine for an aircraft, comprising: a hollow nacelle of longitudinal axis provided, at the front, with an air inlet and, at the rear, with an air outlet;a central hot-stream generator, positioned axially in said nacelle;a fan positioned axially in said nacelle forward of said cen

1. A bypass turbine engine for an aircraft, comprising: a hollow nacelle of longitudinal axis provided, at the front, with an air inlet and, at the rear, with an air outlet;a central hot-stream generator, positioned axially in said nacelle;a fan positioned axially in said nacelle forward of said central generator and able to generate a cold stream for said turbine engine;an outer fairing borne internally by said nacelle and an inner fairing surrounding said central generator, said outer and inner fairings between them delimiting a fan duct of annular cross section for said cold stream and said inner fairing delimiting with said central generator an intermediate chamber of annular cross section surrounding said central generator and provided with at least one rear orifice at the periphery of said hot stream; anda precooler comprising an inlet for a current of hot air bled from said central generator and an outlet for a current of cooled hot air generated using said cold stream, wherein:said precooler is positioned inside said intermediate chamber in thermal contact with the rear part of the inner fairing, forming an intermediate passage between said precooler and said central generator; andforward of said precooler, there is at least one air intake passing through said inner fairing and bleeding from said cold stream, a current of cooling air able at least partially to cool said current of hot air entering said precooler. 2. The turbine engine as claimed in claim 1, wherein said air intake is fitted with a controllable shut-off device. 3. The turbine engine as claimed in claim 1, wherein, inside said intermediate chamber and to the rear of said air intake there are means for setting said current of cooling air bled from said cold stream, in rotation about said longitudinal axis. 4. The turbine engine as claimed in claim 1, wherein said precooler and said intermediate passage have a shape of annular cross section and extend over the entire periphery of said rear part of the inner fairing about said longitudinal axis. 5. The turbine engine as claimed in claim 1, wherein, at least in its rear part said inner fairing comprises an inner wall and an outer wall which are parallel and separated from one another by a space in the form of an annular gap, and said cooler is positioned in said space. 6. The turbine engine as claimed in claim 5, further comprising: a distribution pipe, connected to said inlet for the current of hot air and able to distribute said hot air to at least approximately the entire length of said annular space; anda collection pipe connected to said outlet for the current of cooled hot air and able to collect said cooled hot air over at least approximately the entire length of said annular space. 7. The turbine engine as claimed in claim 6, wherein, between said distribution pipe and said collection pipe, said precooler comprises a plurality of curved ducts for guiding the hot air, said ducts being transverse to the longitudinal axis of the nacelle and distributed over the length of said annular space. 8. The turbine engine as claimed in claim 7, wherein said ducts are formed by a framework reinforcing said rear part of the inner fairing and secured to said inner and outer walls. 9. The turbine engine as claimed in claim 1, further comprising a bypass duct mounted in parallel with said precooler and connecting said inlet for the current of hot stream and said outlet for the current of cooled hot stream. 10. The turbine engine as claimed in claim 9, wherein said bypass duct is equipped with a controllable valve.