Jet engine with a linking device

Abstract

A jet engine with a linking device for linking the jet engine at an element of an aircraft optionally in a first mounting position and at least one second mounting position, and with at least one operating equipment appliance that has a first fluid area and a second fluid area. In the first mounting position, the first fluid area is assigned to a first functionality and the second fluid area is assigned to a second functionality. In the second mounting position, the fluid areas are assigned to the respectively other functionality. What is further described is an aircraft with at least one such jet engine.

Claims

1. A jet engine comprising: an attachment member for linking the jet engine at an element of an aircraft in a first mounting position and a second mounting position, an operating equipment appliance which has a first fluid area and a second fluid area for connect to the aircraft, wherein, in the first mounting position the first fluid area is assigned to a first functionality and the second fluid area is assigned to a second functionality, wherein, in the second mounting position, the first fluid area is assigned to the second functionality and the second fluid area is assigned to the first functionality.

2. The jet engine according to claim 1, wherein the fluid areas are assigned to re-circulation and venting as functionalities.

3. The jet engine according to claim 1, wherein the fluid areas have conduit areas that are arranged at a distance to each other in a circumferential direction of the jet engine, wherein the conduit areas are arranged so as to be symmetrical to the attachment member in the circumferential direction of the jet engine.

4. The jet engine according to claim 1, wherein the attachment member includes two engine attachment points, wherein the attachment member is connected to a carrier structure of the jet engine in an area of the engine attachment points.

5. The jet engine according to claim 4, wherein the attachment member comprises an interface device to the aircraft positioned centrally to the two engine attachment points in the circumferential direction.

6. The jet engine according to claim 1, and further comprising two lifting points configured for mounting the jet engine distributed in a circumferential direction of the jet engine, wherein the lifting points are arranged to be symmetrical to the interface device in the circumferential direction.

7. The jet engine according to claim 1, and further comprising a support strut extending in a radial direction through a bypass channel of the jet engine, wherein the fluid areas extend inside the support strut.

8. The aircraft with a jet engine according to claim 1, and further comprising a radially outer engine cladding and an auxiliary device gear appliance that comprises multiple auxiliary devices and that is configured to be driven by an auxiliary shaft that is in operative connection with an engine shaft that rotates about a central axis, wherein the auxiliary device gear appliance is arranged in a radial direction of the jet engine substantially outside the outer engine cladding of the jet engine.

9. The aircraft according to claim 8, wherein the auxiliary device gear appliance is linked to a frame appliance that is directly connected to at least one chosen from an aircraft fuselage and an aircraft wing.

10. The aircraft according to claim 9, wherein the frame appliance is arranged at least partially inside an engine pylon that is assigned to the jet engine.

11. The aircraft according to claim 9, wherein the frame appliance has linking elements for at least one chosen from the auxiliary devices, a conduit, a tube and a wiring harness.

12. The aircraft according to claim 8, wherein the auxiliary device gear appliance is arranged at least partially inside at least one chosen from an aircraft fuselage, an engine pylon and an aircraft wing.

13. The aircraft according to claim 12, wherein the auxiliary shaft that drives the auxiliary device gear appliance extends through a support strut of the jet engine, with the jet engine being linked to the at least one chosen from the aircraft fuselage, the engine pylon, and the aircraft wing in an area of the support strut.

Description

(1) FIG. 1 shows a simplified three-dimensional view of an aircraft with jet engines that are arranged in the tail area at an aircraft fuselage;

(2) FIG. 2 shows a simplified longitudinal section view of a jet engine of the aircraft according to FIG. 1, wherein a linkage of the jet engine to the aircraft fuselage can be seen;

(3) FIG. 3 shows a strongly schematized cross sectional rendering of a jet engine of FIG. 2 of the aircraft according to FIG. 1 in isolation;

(4) FIG. 4 shows a further strongly schematized sectional view of a jet engine of the aircraft according to FIG. 1 in isolation;

(5) FIG. 5 shows a schematic front view of the jet engine according to FIG. 3 and FIG. 4 in a first mounting position installed on a first side of the aircraft; and

(6) FIG. 6 shows a view of the jet engine according to FIG. 5 in a second mounting position installed on a second side of the aircraft.

(7) Referring to FIG. 1, what is shown is a passenger aircraft 1 that can be driven by three jet engines 2, 3, 4. The first jet engine 2 is arranged on a left side of the aircraft in the tail area of the aircraft 1 in the area of a vertical stabilizer 6 and linked to an aircraft fuselage 8 in the area of an engine pylon 7. The second jet engine 3 is connected to the aircraft fuselage 8 in a substantially mirror-symmetrical manner on a right side of the aircraft.

(8) The third jet engine 4 is positioned at the rear end of aircraft fuselage 8 and attached at an inner fuselage strut that is arranged below the vertical stabilizer 6 of the aircraft 1. For supplying air to the third jet engine 4, an air inlet 10 is provided that is arranged in the flight direction in front of the vertical stabilizer 6 on a top side of the aircraft fuselage 8 and is connected to the third jet engine 4 inside the aircraft fuselage 8.

(9) In general, a variety of arrangements of jet engines at an aircraft is possible, wherein, besides the shown positions, a jet engine can for example also be arranged in the area of an aircraft wing, below or above the same.

(10) In FIG. 2, the jet engine 2 is shown in a longitudinal section view and formed with a bypass channel 12 and an inflow area 13, wherein a fan 14 connects to the inflow area 13 downstream in a per se known manner. Downstream of the fan 14, the fluid flow is in turn divided in the jet engine 2 into a bypass flow and a core flow, wherein the bypass flow flows through the bypass channel 12 and the core flow flows into an engine core 15 or core flow channel, which is in turn embodied in a per se known manner with a compressor appliance 16, a burner 17 and a turbine appliance 18. In the present case, the turbine appliance 18 has three rotor devices 19, 20 and 21 that are mounted so as to be rotatable about a central axis 22.

(11) In the embodiment of the jet engine 2 according to FIG. 2, an auxiliary device gear appliance 23 or auxiliary unit gear appliance is arranged in the radial direction of the jet engine 2 outside of a nacelle installation space 26 forming an outer engine cladding. In the present case, the auxiliary device gear appliance 23 can be driven via a drive shaft 24 that extends substantially in the radial direction of the jet engine 2 and that is connected to an engine shaft, here a high-pressure shaft 54, rotating about a central axis 22 of the jet engine 2, which in the present case is realized via a bevel gear 25. Thus, the auxiliary device gear appliance 23 that comprises different auxiliary units 27, such as for example a starter, a generator, an oil separator or the like, are driven or supplied with a torque by the high-pressure shaft 54 during operation of the jet engine 2.

(12) As can further be seen from FIG. 2, the auxiliary device gear appliance 23 is arranged inside the engine pylon 7, wherein the conduits 29 by means of which the auxiliary units 27 are connected to the jet engine 2 can also be seen.

(13) Arranged inside the engine pylon 7 is a frame appliance 30, a so-called space frame to which, besides the auxiliary units 27 of the auxiliary device gear appliance 23, also conduits, tubes and wiring harnesses can be linked by means of schematically shown linking elements 31. The frame appliance 30 is in particular embodied with a grid structure that can be adjusted depending on the elements to be arranged.

(14) As can further be seen from FIG. 2, in the present case three connection appliances 33 are provided, by means of which the frame appliance 30 is linked to the aircraft fuselage 8 or possibly to an aircraft wing. In further embodiments, also two or more than three connection appliances can be provided.

(15) By arranging the auxiliary device gear appliance 23 with the auxiliary units 27 substantially outside the nacelle installation space 26, the latter can be reduced to a cross section as shown by the dashed line 26″ in contrast to a cross section that is shown by the solid line 26′ and as its would have to be provided if the auxiliary device gear appliance was arranged inside the nacelle installation space 26.

(16) By arranging the auxiliary device gear appliance 23 outside the nacelle installation space 26, a length of the jet engine 2 can also be reduced, so that an aerodynamic resistance of the jet engine 2 and thus also of the aircraft 1 is advantageously low, and the aircraft 1 has an advantageously low fuel consumption. In addition, in this manner the auxiliary device gear appliance 23 is subjected to more favorable temperature and vibration conditions, so that the auxiliary device gear appliance 23 has a long service life.

(17) FIG. 3 to FIG. 6 show strongly simplified cross-sectional renderings of the jet engine 2 in the area of the engine pylon 7 with the auxiliary device gear appliance 23.

(18) FIG. 3 shows a schematic rendering of linking device 36 which, in the present case, has two engine attachment points 37, 38 by means of which, in the present case, the linking device 36 is connected to a fan housing 55. Further, in the present case, the linking device 36 has an interface device 40 by means of which the linking device 36 is connected to the frame appliance 30 and thus to the aircraft fuselage 8. Alternatively, the interface can also be provided at the pylon or directly at the aircraft fuselage.

(19) As can be seen in FIG. 4, in which the jet engine 2 is shown in a “neutral” position, i.e. not in installation position, here the interface device 40 as well as the engine attachment points 37, 38 are arranged in the circumferential direction U of the jet engine 2 respectively in the area of a support strut 42, wherein the support struts 42 extend in the radial direction R of the jet engine 2 through the bypass channel 12 and connect the fan housing 55 to an intermediate housing 43. In the present case, ten support struts 42 are provided in a manner evenly distributed in the circumferential direction U. However, the number can also be more or less than that, and can for example vary between 4 and 28 or more.

(20) The interface device towards the aircraft 1 is arranged in the area of a support strut 42A. The engine attachment points 37 and 38 are provided at the support struts 42B and 42C adjacent on both sides, thus arranged substantially symmetrical to the interface device 40, wherein in the present case an angle between the engine attachment points 37, 38 is 72°, as viewed in the circumferential direction U. In addition, in FIG. 4 to FIG. 6, the drive shaft 24 of the auxiliary device gear appliance 23, which is not shown here in any more detail, can respectively be seen in the area of the support strut 42A leading to the interface device 40.

(21) Further, FIG. 4 to FIG. 6 show, in sections, an operating equipment appliance that is embodied as a hydraulic appliance 45, wherein the hydraulic appliance 45 has two fluid areas 46, 47. Here, each of the mirror-inverted manner fluid areas 46, 47 is designed in such a manner that it can optionally be used for venting (vent) as well as for oil draining and oil recirculation (drain/scavenge). The conduit areas 48, 49 of the fluid areas 46, 47 respectively extend through support struts 42D and 42E from the intermediate housing 43 in the direction of the fan housing 55, with a further conduit area 50, 51 respectively connecting thereto, extending in the circumferential direction U towards the interface device 40 in the nacelle installation space 26.

(22) The support struts 42D and 42E that receive the conduit areas 48, 49 are in turn arranged to be symmetrical to the support strut 42A that is assigned to the interface device 40 and thus to the interface device 40, wherein in the present case an angle between the conduit areas 48, 49 is 144°, as viewed in the circumferential direction U.

(23) Further, in the area of further support struts 42F and 42G, lifting points 52, 53 are arranged, which are formed with corresponding attachment means and at which the jet engine 2 can be supported for being mounted at the aircraft 1. Here, the support struts 42F and 42G again extend symmetrically to the interface device 40 and in a mirror-inverted manner to the support struts 42B, 42C of the engine attachment points 37, 38.

(24) Of course, the distance between the support struts, in which the engine attachment points, the conduits of the fluid areas and lifting points are received, varies with the total number of support struts. Thus, in the embodiment according to FIG. 4, an angle between the lifting points 52, 53, as viewed in the circumferential direction U, is for example 72°, whereas the angle in the embodiment according to FIG. 5 and FIG. 6 is 144°.

(25) FIG. 5 and FIG. 6 show the jet engine 2 in a first mounting position and in a differing second mounting position at the aircraft 1, wherein in FIG. 5 the jet engine 2 is shown in a mounting position on the right side of the aircraft, and in FIG. 6 is shown pivoted by 144° in a mounting position on the left side of the aircraft. The fluid area 46 that serves for venting when the jet engine 2 is mounted on the right side according to FIG. 5 becomes an oil return line in case of a mounting on the left side according to FIG. 6, while the fluid area 47 that serves for oil recirculation when mounted on the right side serves for venting when mounted on the left side.

(26) As follows from a comparison of FIG. 4 and FIG. 5, the arrangement of the jet engine 2 on the right side of the aircraft is substantially mirror-inverted to the arrangement of the jet engine 2 on the left side of the aircraft with respect to an aircraft median longitudinal plane, wherein the lifting points 52, 53, the conduit areas 47, 48 and the engine attachment points 37, 38 respectively take a position that is switched with respect to one another, and the functionalities of the fluid areas 46, 47 are switched.

(27) Thus, it is principally possible to use jet engines of identical design to link these at the aircraft 1 on different sides of the aircraft 1 with differing linking angles.

PARTS LIST

(28) 1 aircraft 2, 3, 4 jet engine 6 vertical stabilizer 7 engine pylon 8 aircraft fuselage 10 air inlet 12 bypass channel 13 inflow area 14 fan 15 engine core flow channel 16 compressor appliance 17 burner 18 turbine appliance 19, 20, 21 rotor device 22 central axis 23 auxiliary device gear appliance 24 drive shaft 25 bevel gear 26 nacelle installation space 27 auxiliary units 28 engine shaft, low-pressure shaft 29 conduits 30 frame appliance 31 linking elements 33 connection appliance 36 linking device 37, 38 engine attachment point 40 interface device 42, 42A to G support strut 43 intermediate housing 45 operating equipment appliance; hydraulic appliance 46, 47 fluid area 48, 49 conduit area 50, 51 further conduit area 52, 53 lifting point 54 engine shaft, high-pressure shaft 55 carrier structure, fan housing R radial direction of the jet engine U circumferential direction of the jet engine