Aircraft comprising at least one turbomachine oriented approximately parallel to a wing spar

Abstract

Aircraft comprising at least one turbomachine oriented approximately parallel to a spar of a wing The invention relates to an aircraft comprising a fuselage (42), at least one wing (44) on each side of the fuselage (42), at least one propulsion unit (46) connected to the wing (44) each comprising a propeller (56), a turbomachine (58) and a coupling system connecting the propeller (56) and the turbomachine (58). The turbomachine (58) comprises a rotor and at least one ejection zone (78) into which pieces of the turbomachine (58) are potentially ejected in the event of an incident. According to a characteristic of the invention, the turbomachine (58) is arranged so that the axis of rotation of its rotor forms an angle of between -45° and +45° with a plane perpendicular to the longitudinal axis (X) of the fuselage (42). Additionally, the coupling system includes an angle gear connecting the rotor and the propeller (56).Thus, the ejection zone (78) does not interfere with the fuselage (42). Figure 4.

Description

Title of the invention: Aircraft comprising at least one turbomachine oriented approximately parallel to a spar of a wing

[0001] The present application relates to an aircraft comprising at least one turbomachine oriented approximately parallel to a spar of a wing.

[0002] According to an embodiment visible in [Fig.l], an aircraft comprises a fuselage 10 having a longitudinal axis X, wings 12 which extend on either side of the fuselage 10, several propulsion units 14 connected to the wings 12 and positioned on either side of the fuselage 10, at least one fuel tank 16 as well as pipes 18, 18' connecting the fuel tank 16 and the propulsion units 14.

[0003] As illustrated in [Fig.2], each propulsion unit 14 comprises a propeller 20, a turbomachine 22 and a coupling system 24 connecting the propeller 20 and the turbomachine 22. The turbomachine 22 comprises a rotor 26, an air inlet 28, at least one compressor 30 connected to the rotor 26, at least one combustion chamber 32, a turbine 34 connected to the rotor 26 and an exhaust 36.

[0004] The propeller 20 has a first axis of rotation A20. The rotor 26 has a second axis of rotation A26. According to one configuration, the first and second axes of rotation A20, A26 are parallel to each other and to the longitudinal axis X of the aircraft.

[0005] The turbine 34 has several discs positioned in planes perpendicular to the second axis of rotation A26, the pieces of which, in the event of accidental bursting, are ejected along trajectories included in an ejection zone 38 which extends on either side of a plane perpendicular to the second axis of rotation A26.

[0006] As illustrated in [Fig.l], this ejection zone 38 interferes with the junction zone of the wings 12 and the fuselage 10 as well as with a part of the latter.

[0007] For safety reasons, the fuel tanks 16 as well as the pipes 18, 18' must be located outside this ejection zone 38. This constraint greatly reduces the possibilities of installing the fuel tanks 16.

[0008] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0009] To this end, the invention relates to an aircraft comprising a fuselage extending along a longitudinal axis, at least one wing on each side of the fuselage and at least one propulsion unit fixed to each wing, each wing having at least one front spar extending along an axis intersecting the longitudinal axis and in an identical manner on each side of the fuselage; each propulsion unit comprising a propeller, a turbomachine and a coupling system connecting the propeller and the turbine turbomachine, the propeller having a first axis of rotation parallel to the longitudinal axis, the turbomachine comprising a rotor, at least one air inlet, at least one compressor connected to the rotor, at least one combustion chamber, at least one turbine connected to the rotor, at least one exhaust, the rotor having a second axis of rotation.

[0010] According to the invention, the second axis of rotation forms an angle between -45° and +45° with a plane perpendicular to the longitudinal axis, the coupling system comprising an angle transmission connecting the rotor and the propeller.

[0011] According to this solution, the ejection zone of each propulsion unit does not interfere with the fuselage. Thus, the fuel tanks can be positioned along the entire length of the fuselage, at the wings, near the fuselage or at the wingtips.

[0012] According to another characteristic, the second axis of rotation of the turbomachine of a propulsion unit is parallel to the front spar of the wing to which the propulsion unit is fixed.

[0013] According to another characteristic, the propeller of a propulsion unit comprises a hub spaced from the wing on which the propulsion unit is fixed and the coupling system comprises a housing in which the angle gear is positioned, located in line with the front spar of the wing as well as a transmission shaft connecting the angle gear and the hub.

[0014] According to another characteristic, the coupling system comprises a gearbox connecting the transmission shaft and the propeller hub. In addition, each propulsion unit comprises a structure having a first end connected to the wing and a second end connected to the gearbox.

[0015] According to another characteristic, the turbomachine comprises at least one body and the propulsion unit comprises at least one wing attachment connecting the body of the turbomachine and the front spar of the wing.

[0016] According to another characteristic, the propulsion unit comprises a first wing attachment connecting the body of the turbomachine and the front spar of the wing as well as a second wing attachment connecting the coupling system and the front spar of the wing.

[0017] According to another characteristic, the first wing attachment comprises a first part secured to the wing, a second part secured to the body of the turbomachine as well as two connecting rods each having a first end connected by a first pivoting joint to the first part and a second end connected by a second pivoting joint to the second part, the first and second pivoting joints having pivot axes parallel to each other and to the second axis of rotation.

[0018] According to another characteristic, the second wing attachment comprises a first part secured to the wing, a second part secured to the coupling system as well as two connecting rods each having a first end connected by a first pivoting joint to the first part and a second end connected by a second pivoting joint to the second part, the first and second pivoting joints having pivot axes parallel to each other and perpendicular to the second axis of rotation.

[0019] According to another characteristic, each propulsion unit comprises a fairing surrounding the turbomachine as well as the coupling system. In addition, the air intake comprises a first duct which has at least one elbow, a first end opening at the fairing, oriented forward and approximately parallel to the longitudinal axis as well as a second end connected to the body of the turbomachine.

[0020] According to another characteristic, the exhaust comprises a second duct which has at least one elbow, a first end connected to the body of the turbomachine as well as a second end opening at the fairing, oriented towards the rear and parallel to the longitudinal axis.

[0021] Other characteristics and advantages will emerge from the description of the invention which follows, a description given by way of example only, with reference to the appended drawings, among which:

[0022] [Fig.l] is a schematic top view of an aircraft illustrating an embodiment of the prior art,

[0023] [Fig.2] is a schematic representation of a propulsion assembly illustrating an embodiment of the prior art,

[0024] [Fig.3] is a perspective view of an aircraft,

[0025] [Fig.4] is a schematic top view of an aircraft illustrating a mode of rea lization of the invention,

[0026] [Fig.5] is a schematic top view of a propulsion unit illustrating an embodiment of the invention,

[0027] [Fig.6] is a bottom view of a propulsion unit without fairing illustrating an embodiment of the invention,

[0028] [Fig.7] is a bottom view of the propulsion unit visible in [Fig.6] with a fairing,

[0029] [Fig.8] is a perspective view of a propulsion unit without fairing illustrating an embodiment of the invention,

[0030] [Fig.9] is a perspective view of a connection system connecting a propulsion unit and a wing illustrating an embodiment of the invention, and

[0031] [Fig. 10] is a perspective view illustrating in detail the visible connection system on [Fig.9].

[0032] In Figures 3 and 4, an aircraft 40 comprises a fuselage 42 which extends between front and rear tips 42.1, 42.2, at least one wing 44 on each side of the fuselage, each connected to the fuselage 42, at least one propulsion unit 46 fixed to each wing 44 and positioned on either side of the fuselage 42, at least one fuel tank 48 as well as at least one fuel line 50 connecting each propulsion unit 46 to a fuel tank 48.

[0033] According to one application, the aircraft 40 operates on hydrogen, the fuel tank 48 is configured to store hydrogen and the fuel lines 50 are configured to channel hydrogen. The propulsion units are of the turboprop type.

[0034] The fuselage 42 has a longitudinal axis X connecting the front and rear tips 42.1, 42.2. The terms front and rear refer to the direction of airflow outside the aircraft in flight which flows from front to rear.

[0035] Each wing 44 has at least one leading edge 44.1 as well as at least one trailing edge 44.2. According to one embodiment, on the structural level, each wing 44 comprises at least one front spar 52.1 approximately parallel to the leading edge 44.1, at least one rear spar 52.2 approximately parallel to the trailing edge 44.2 as well as several frames 54 connecting the front and rear spars 52.1, 52.2. The other elements of the wing 44 are not described further because they are known to those skilled in the art.

[0036] For information purposes, the front spar 52.1 extends along an axis S intersecting the longitudinal axis X, identical on each side of the fuselage, forming an angle of between 60° and 90° with the longitudinal axis X.

[0037] As illustrated in [Fig. 5], each propulsion unit 46 comprises a propeller 56, a turbomachine 58 and a coupling system 60 connecting the propeller 56 and the turbomachine 58. The turbomachine 58 comprises a rotor 62, at least one air inlet 64, at least one compressor 66 connected to the rotor 62, at least one combustion chamber 68, at least one turbine 70 connected to the rotor 62 and at least one exhaust 72.

[0038] The propeller 56 comprises a hub 74 having a first axis of rotation A74 parallel to the longitudinal axis X as well as blades 76 connected to the hub 74.

[0039] The rotor 62 has a second axis of rotation A62.

[0040] The turbine 70 has several disks positioned in planes perpendicular to the second axis of rotation A62. The turbomachine 58 comprises at least one ejection zone 78 in which pieces of the turbomachine are potentially ejected, such as the disks of the turbine 70 or pieces of disk, for example, in the event of accidental bursting. This ejection zone 78 extends on either side on the other side of a plane perpendicular to the second axis of rotation A62.

[0041] According to a characteristic of the invention, the second axis of rotation A62 forms an angle a of between -45° and +45° with a plane perpendicular to the longitudinal axis X. This angle a is such that the ejection zone 78 of each propulsion unit 46 does not interfere with the fuselage 42, as illustrated in [Fig.4]. Thus, the fuel tanks 48 can be positioned along the entire length of the fuselage 42, at the wings 44, close to the fuselage 42 or at the ends of the wings 44.

[0042] This arrangement makes it possible to expand the possibilities in terms of the installation of the fuel tanks 48 and the fuel pipes 50.

[0043] According to one embodiment, the second axis of rotation A62 is parallel to the front spar 52.1 of the wing 44, positioned vertically and below said front spar 52.1.

[0044] The second axis of rotation A62 of the rotor 62 of the turbomachine 58 not being parallel to the first axis of rotation A74 of the propeller 56, the coupling system 60 comprises an angle transmission 80 for connecting the rotor 62 and the propeller 56. According to one embodiment, the coupling system 60 also comprises a reducer.

[0045] According to one configuration, the hub 74 of the propeller 56 is spaced forwardly relative to the leading edge 44.1 of the wing 44.

[0046] According to this configuration, the coupling system 60 comprises a housing 82 in which the angle transmission 80 is positioned, positioned in line with the front spar 52.1 of the wing 44 as well as a transmission shaft 84 connecting the angle transmission 80 and the hub 74.

[0047] The coupling system 60 comprises a gearbox 86 connecting the transmission shaft 84 and the hub 74, as illustrated in Figures 6 and 7.

[0048] The propulsion unit 46 comprises a structure 88 connecting the wing 44 and the propeller 56. According to an embodiment visible in Figures 6 and 7, this structure 88 has a box shape. According to another embodiment visible in Figures 8 to 10, the structure 88 is a mechanically welded structure.

[0049] This structure 88 comprises a first end connected by at least one attachment 90 to the wing 44 as well as a second end connected to the gearbox 86.

[0050] The turbomachine 58 comprises at least one body 92 in which the rotor 62, the compressor(s) 66, the combustion chamber(s) 68 and the turbine(s) 70 are positioned.

[0051] According to an embodiment visible in [Fig. 5], the turbomachine 58 comprises a first body 92 in which a section of the rotor 62 and the compressor(s) 66 are positioned as well as a second body 92' in which a section of the rotor 62, the turbine(s) 70 and the combustion chamber(s) 68 are positioned, the first and second bodies 92, 92' being positioned on either side of the coupling system 60 and more particularly its housing 82.

[0052] According to other embodiments visible in Figures 6 to 10, the turbomachine 58 comprises a single body 92, approximately cylindrical, in which the rotor 62, the compressor(s) 66, the combustion chamber(s) 68 and the turbine(s) 70 are positioned.

[0053] The propulsion unit 46 comprises at least one wing attachment 94 connecting the body 92 of the turbomachine 58 to the front spar 52.1 of the wing 44 and possibly to a frame 54 of the wing 44. Thus, the body 92 of the turbomachine 58 is suspended under the front spar 52.1 of the wing 44.

[0054] According to an embodiment visible in Figures 8 to 10, the propulsion unit 46 comprises a first wing attachment 94 connecting the body 92 of the turbomachine 58 to the front spar 52.1 of the wing 44 as well as a second wing attachment 94' connecting the housing 82 of the coupling system 60 to the front spar 52.1 of the wing 44.

[0055] According to an embodiment visible in detail in [Fig. 10], the first wing attachment 94 comprises a first part 96 secured to the wing 44, a second part 98 secured to the body 92 of the turbomachine 58 as well as two connecting rods 100, 100' which each have a first end connected by a first pivoting joint 100.1 to the first part 96 and a second end connected by a second pivoting joint 100.2 to the second part 98. According to one configuration, the first and second pivoting joints 100.1, 100.2 have pivot axes parallel to each other and to the second axis of rotation A62.

[0056] The second wing attachment 94' comprises a first part 102 secured to the wing 44, a second part 104 secured to the housing 82 of the coupling system 60 as well as two connecting rods 106, 106' which each have a first end connected by a first pivoting joint 106.1 to the first part 102 and a second end connected by a second pivoting joint 106.2 to the second part 104. According to one configuration, the first and second pivoting joints 106.1, 106.2 have pivot axes parallel to each other and perpendicular to the second axis of rotation A62.

[0057] The propulsion unit 46 comprises a fairing 108 surrounding the turbomachine 58 as well as the coupling system 60.

[0058] According to one embodiment, the air inlet 64 comprises a first duct 110 which has at least one elbow, a first end 110.1 opening at the fairing 108, oriented forward and approximately parallel to the longitudinal axis X as well as a second end 110.2 connected to the body 92 of the turbomachine 58.

[0059] According to one embodiment, the exhaust 72 comprises a second duct 112 which has at least one elbow, a first end 112.1 connected to the body 92 of the turbomachine 58 as well as a second end 112.2 opening at the level of the fairing 108, facing rearward and approximately parallel to the longitudinal axis X.

Claims

Claims

1. Aircraft comprising a fuselage (42) extending along a longitudinal axis (X), at least one wing (44) on each side of the fuselage (42) and at least one propulsion unit (46) fixed to each wing (44), each wing (44) having at least one front spar (52.1) extending along an axis (S) intersecting the longitudinal axis (X) and identically on each side of the fuselage; each propulsion unit (46) comprising a propeller (56), a turbomachine (58) and a coupling system (60) connecting the propeller (56) and the turbomachine (58), the propeller (56) having a first axis of rotation (A74) parallel to the longitudinal axis (X), the turbomachine (58) comprising a rotor (62), at least one air inlet (64), at least one compressor (66) connected to the rotor (62), at least one combustion chamber (68), at least one turbine (70) connected to the rotor (62), at least one exhaust (72),the rotor (62) having a second axis of rotation (A62); characterized in that the second axis of rotation (A62) forms an angle (a) between -45° and + 45° with a plane perpendicular to the longitudinal axis (X), in that the coupling system (60) comprises an angle transmission (80) connecting the rotor (62) and the propeller (56), in that the turbomachine (58) comprises at least one body (92), in that the propulsion unit (46) comprises a first wing attachment (94) connecting the body (92) of the turbomachine (58) and the front spar (52.1) of the wing (44) as well as a second wing attachment (94') connecting the coupling system (60) and the front spar (52.1) of the wing (44) and in that the second wing attachment (94') comprises a first part (102) integral with the wing (44), a second part (104) integral with the coupling system (60) as well as two connecting rods (106,106') each having a first end connected by a first pivoting joint (106.1) to the first part (102) and a second end connected by a second pivoting joint (106.2) to the second part (104), the first and second pivoting joints (106.1, 106.2) having pivot axes parallel to each other and perpendicular to the second axis of rotation (A62).,

2. Aircraft according to claim 1, characterized in that the second axis of rotation (A62) of the turbomachine (58) of a propulsion unit (46) is parallel to the front spar (52.1) of the wing (44) to which the propulsion unit is fixed.

3. Aircraft according to one of the preceding claims, characterized in that the propeller (56) of a propulsion unit (46) comprises a hub (74) spaced from the wing (44) on which the propulsion unit is fixed and in that the coupling system (60) comprises a housing (82) in which the angle gear (80) is positioned, positioned in line with the front spar (52.1) of said wing (44), as well as a transmission shaft (84) connecting the angle gear (80) and the hub (74).

4. Aircraft according to the preceding claim, characterized in that the coupling system (60) comprises a gearbox (86) connecting the transmission shaft (84) and the hub (74) of the propeller (56) and in that each propulsion unit (46) comprises a structure (88) having a first end connected to the wing (44) as well as a second end connected to the gearbox (86).

5. Aircraft according to one of the preceding claims, characterized in that the first wing attachment (94) comprises a first part (96) secured to the wing (44), a second part (98) secured to the body (92) of the turbomachine (58) as well as two connecting rods (100, 100') each having a first end connected by a first pivoting joint (100.1) to the first part (96) and a second end connected by a second pivoting joint (100.2) to the second part (98), the first and second pivoting joints (100.1, 100.2) having pivot axes parallel to each other and to the second axis of rotation (A62).

6. Aircraft according to one of claims 1 to 5, characterized in that each propulsion unit (46) comprises a fairing (108) surrounding the turbomachine (58) as well as the coupling system (60) and in that the air inlet (64) comprises a first duct (110) which has at least one elbow, a first end (110.1) opening at the fairing (108), oriented forward and approximately parallel to the longitudinal axis (X), as well as a second end (110.2) connected to the body (92) of the turbomachine (58).

7. Aircraft according to the preceding claim, characterized in that the exhaust (72) comprises a second duct (112) which has at least one elbow, a first end (112.1) connected to the body (92) of the turbomachine (58) as well as a second end (112.2) opening at the fairing (108), oriented towards the rear and parallel to the longitudinal axis (X).

Images