This application claims priority, under Section 371 and/or as a continuation under Section 120, to PCT Application No. PCT/FR2010/050004, filed on Jan. 5, 2010, which claims priority to French Application No. 0900032, filed on Jan. 7, 2009.
The present invention relates to an aircraft turbine engine, as well as the use of such a turbine engine.
As known, modern turbine engines for aircrafts are efficient, although bulky, thereby increasing substantially the difficulty for mounting them on such aircrafts. Such a mounting difficulty is made worse due to the monobloc structure of such turbine engines. As a result, such a mounting operation is frequently to be associated with significant modifications and adaptations of the structure of said aircrafts and including of the airfoil of the engines.
However, such modifications and adaptations might not be desirable, for instance for technical matters and obvious cost reasons.
The present invention aims at solving such a drawback and more specifically, at making mounting such turbine engines on an aircraft easier.
To this end, according to the invention, the aircraft turbine engine comprising:
Thus, thanks to this invention, the structure and the shape of the turbine engine can be adapted, so as to make mounting thereof on an aircraft easier.
In the case where the blower is being rotated by the hot flow generator through a reducing mechanism, said shifting means advantageously consist in, at least in part, said reducing mechanism, so as to allow for the shifting of the axis of said blower transverse to the axis of said hot flow generator.
Said reducing mechanism could comprise an epicycloidal reducer and a straight reducer.
Obviously, the present invention further relates to the use of the aircraft turbine engine such as previously described.
Advantageously, when said turbine engine is hung to the airfoil of said aircraft via a suspension pylon, the axis of said blower could be shifted upwards transverse to the axis of said hot flow generator, so as to increase the ground clearance of said turbine engine.
Thus, in the particular case of re-motorization of an aircraft, this invention makes it possible to replace the existing turbine engines thereof with new modern (generally bulkier) turbine engines, while keeping as such the original airfoil of the turbine engines. Indeed, the upward shifting of the blower of the turbine engine allows the pod to be lifted without modifying the airfoil of the engine. The ground clearance of the turbine engine is then increased by a value equal to the shifting of the axis of the blower.
Alternatively, when said turbine engine is mounted on the airfoil of said aircraft, the axis of said blower can be shifted upwards transverse to the axis of said hot flow generator, so as to shift the air input from said turbine engine to the exterior. Thereby, the volume of air able to cross the air input of said turbine engine is increased, thus improving the performances thereof.
In another alternative of the present invention, said turbine engine being hung under the airfoils of said aircraft, the axis of said blower can be shifted downwards transverse to the axis of said hot flow generator, so as to shift the air input from said turbine engine to the exterior so as to increase the air volume penetrating into the latter.
Furthermore, the present invention also relates to an aircraft comprising at least one turbine engine such as previously described.
The FIGS. of the appended drawings will better explain how this invention can be implemented. In these FIGS., like reference numerals relate to like components,
In an embodiment of the aircraft turbine engine according to this invention described with reference to
Usually, as shown on
As an illustrative numerical but not limitative example, the ground clearance of such a double flow turbine engine 1 (that is, the space between the ground G and the lowest point of the pod 13), designated by GC on
According to the invention, as shown on
To this end, the usual reducing mechanism 10 of
As shown on
Thus, thanks to this invention, the ground clearance of the turbine engine 1a is increased by AGC, corresponding to the upward shifting value of the axis la-la of the blower 9a.
According to the above mentioned numerical example, such a shifting could be equal to 150 mm, so that the ground clearance GC+ΔGC of the turbine engine 1a becomes equal to 673 mm.
In another embodiment according to this invention illustrated on
Furthermore, as shown on
Number | Date | Country | Kind |
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09 00032 | Jan 2009 | FR | national |
Filing Document | Filing Date | Country | Kind | 371c Date |
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PCT/FR2010/050004 | 1/5/2010 | WO | 00 | 6/13/2011 |
Publishing Document | Publishing Date | Country | Kind |
---|---|---|---|
WO2010/079294 | 7/15/2010 | WO | A |
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Number | Date | Country |
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2903389 | Oct 1979 | DE |
0798207 | Oct 1997 | EP |
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Entry |
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European Patent Office, International Search Report PCT/FR2010/050004, Apr. 8, 2010 (2 pgs) , Form PCT/ISA/237 (5 pgs.) English language translation of Form PCT/ISA/237 (6 pgs). |
Number | Date | Country | |
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20110314788 A1 | Dec 2011 | US |