Aircraft Turbine Engine And Use Of Such A Turbine Engine

Abstract

The invention relates to an aircraft turbine engine and to the use of such a turbine engine. According to the invention, the turbine engine (la) comprises a means for shifting the axis (la-la) of the blower (9a) transverse to the axis (La-La) of the hot flow generator (4a).

Description

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:

a hot flow generator with an at least substantially horizontal axis, fastened to the airfoil of said aircraft through at least one fastener;

a cold flow blower with an at least substantially horizontal axis, being rotated by said hot flow generator; and

a pod surrounding said hot flow generator and said cold flow blower and forming a cold flow channel with an annular section around said hot flow generator, is remarkable in that it comprises means being able to shift the axis of said blower transverse to the axis of said hot flow generator.

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 drawing will better explain how this invention can be implemented. In these FIGS., like reference numerals relate to like components

FIG. 1 is a side schematic longitudinal sectional view of a turbine engine being hung under the wing of an aircraft via a suspension pylon.

FIG. 2 is identical to FIG. 1, the wing turbine engine being according to an embodiment of the present invention.

FIG. 3 shows, in a side schematic view, the wing turbine engine of FIG. 1 (in mixed line), as well as the wing turbine engine of FIG. 2 (in solid line) according to the present invention.

FIG. 4 is a side schematic longitudinal sectional view of a turbine engine mounted on the airfoil of an aircraft, in accordance with another embodiment according to the present invention.

FIG. 5 shows, in a side schematic longitudinal sectional view, a turbine engine being hung under the airfoil of an aircraft, still according to another embodiment of the present invention.

In an embodiment of the aircraft turbine engine according to this invention described with reference to FIGS. 1 to 3, the re-motorization of an aircraft is considered with modern and efficient engines, without modifying the airfoil of the original (less efficient) turbine engines and, more specifically, without modifying the wings, the suspension pylons, the fasteners on such pylons that remain unchanged. Such a re-motorization could be required, so as, for instance, to reduce the fuel consumption of the aircraft, increase the available power thereof, reduce the sound emissions thereof, etc.

FIG. 1 shows a double flow turbine engine 1 fastened on the wing 2 of an aircraft via a suspension pylon 3.

Usually, as shown on FIG. 1, the double flow turbine engine 1 comprises:

a hot flow generator 4 with an at least substantially horizontal axis L-L. The generator 4 is fastened through a front fastener 5 and a rear fastener 6 to the suspension pylon 3. The front fastener 5 and the rear fastener 6 are mounted on the generator 4 at the level respectively of a high-pressure compressor 7 and of a low-pressure turbine engine 8 of said generator 4;

a cold flow blower 9 with an at least substantially horizontal axis I-I. The axis l-l of the blower 9 matches the axis L-L of the hot flow generator 4. The latter rotates said blower 9, by means of a reducing mechanism 10 (for instance an epicycloidal gear reducer) mechanically connecting the driving shaft 11 of the generator 4 to the driving shaft 12 of the blower 9, the rotation speed of the blower 9 being lower than that of the generator 4; and

a pod 13 surrounding the hot flow generator 4 and the cold flow blower 9 and forming a cold flow channel 14, being axisymmetric with respect to the axis l-l or L-L and having an annular section around said generator 4. The pod 13 is bounded at the ends thereof, respectively, by an air input hole 15 and by a cold flow output hole 16, being located at the front of the leading edge 17 of the wing 2.

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 FIG. 2, could be equal to 523 mm.

According to the invention, as shown on FIG. 2 (where the elements corresponding to the turbine engine on FIG. 1 respectively have the same reference, but with a suffix a), the axis la-la of the blower 9a has been shifted upwards transverse to the axis La-La of the hot flow generator 4, maintaining as such the characteristics of the suspension pylon 3 and the fastening points 5 and 6 of the aircraft (FIG. 1).

To this end, the usual reducing mechanism 10 of FIG. 1 has been replaced by an adapted reducing mechanism comprising, for instance, an epicycloidal reducer 10a and a straight reducer 18 associated with each other. Moreover, the epicycloidal reducer 10a and the straight reducer 18 are directly connected respectively to the driving shaft 12a of the blower 9a and the driving shaft 11a of the hot flow generator 4a. Obviously, other reducing mechanisms could also be contemplated.

As shown on FIGS. 2 and 3, the upward shifting of the blower 9a allows the pod 13a of the turbine engine la to be lifted by a value equal to the shift of the axis la-la, without modifying either the suspension pylon 3 or the fasteners 5 and 6. As a result of the shifting of the blower 9a, a modification of the cold flow annular channel 14a is achieved, that is no longer axisymmetric.

Thus, thanks to this invention, the ground clearance of the turbine engine la 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 15 mm, so that the ground clearance GC AGC of the turbine engine la becomes equal to 673 mm.

In another embodiment according to this invention illustrated on FIG. 4, the turbine engine la.I is mounted on the airfoil 2.I of an aircraft. The hot flow generator thereof is fastened to the airfoil 2.I through front and rear fasteners (5.I, 6.I). The axis la-la of the blower 9a is shifted upwards by AGC, transverse to the axis La-La of the hot flow generator 4a, so as to substantially increase the volume of air crossing the air input 15a. Thereby, the filling of the turbine engine la.I with air is improved.

Furthermore, as shown on FIG. 5, still another embodiment of the present invention provides a turbine engine la.II under a wing 2.II of an aircraft. Such a turbine engine la.II is fastened under the wing 2.II through a front fastener 5.II and a rear fastener 6.II, both mounted on the hot flow generator 4a. The axis la-la of the blower 9a is shifted downwards by GC, transverse to the axis La-La of the hot flow generator 4a, so as to substantially increase the volume of air crossing the air input 15a. The filling of the turbine engine la.I with air is thereby improved.

Claims

1-7. (canceled)

8. An aircraft turbine engine comprising: a hot flow generator with an at least substantially horizontal axis, fastened to the airfoil of said aircraft via at least one fastener;a cold flow blower with an at least substantially horizontal axis, being rotated by said hot flow generator; anda pod surrounding said hot flow generator and said cold flow blower and forming a cold flow channel with an annular section around said hot flow generator,wherein it comprises means (10a, 18) being able to shift the axis (la-la) of said blower (9a) transverse to the axis (La-La) of said hot flow generator (4a).

9. The aircraft wing turbine engine according to claim 8, wherein said blower is rotated by said hot flow generator through a reducing mechanism, wherein said shifting means consist in, at least in part, said reducing mechanism (10a, 18), so to allow for the shifting of the axis (la-la) of said blower (9a) transverse to the axis (La-La) of said hot flow generator (4a).

10. The aircraft wing turbine engine according to claim 9, wherein said reducing mechanism (10a, 18) comprises an epicycloidal reducer (10a) and a straight reducer (18).

11. A use of an aircraft turbine engine such as specified in claim 8, for which said turbine engine is hung to the airfoil (2) of said aircraft by means of a suspension pylon (3), wherein the axis of said blower (9a) is shifted upwards transverse to the axis of said hot flow generator (4a) so as to increase the ground clearance of said turbine engine (la).

12. The use of an aircraft turbine engine, as specified in claim 8, wherein said turbine engine (la.I) being mounted on the airfoil (2.I) of said aircraft, the axis (la-la) of said blower (9a) is shifted upwards transverse to the axis (La-La) of said hot flow generator (4a) so as to shift the air input (15a) from said turbine engine (la.I) to the exterior.

13. The use of an aircraft turbine engine, as specified in claim 8, wherein said turbine engine (la.II) being hung under the airfoil (2.II) of said aircraft, the axis (la-la) of said blower (9a) is shifted downwards transverse to the axis (La-La) of said hot flow generator (4a) so as to shift the air input (15a) from said turbine engine (la.II) to the exterior.

14. An aircraft, wherein it comprises at least one turbine engine (la) such as specified in claim 8.