DE102018208297A1 - Aircraft with at least one jet engine - Google Patents

Abstract

The invention relates to an aircraft (100) having at least one nozzle drive (10, 20), in particular in a jacket flow design, with an air inlet (1) with a fan (2), a compressor device (3), a combustion device (4) and a turbine device (5) for driving the compressor device (5) and the fan (2), wherein a first part (A) of the air flowing into the air inlet (1) flows into the compressor device (3) and a second part (B) through a bypass channel (6), characterized in that the air inlet (1) and the bypass channel (6) of the at least one nozzle drive (10, 20) at least partially, in particular completely around an outer wall (31) of a payload region (30) of the aircraft (100) around are arranged.

Description

The present disclosure relates to an aircraft having the features of claim 1.

Aircraft, such as Passenger aircraft or drones may be powered by jet engines arranged in a known manner about an axis of rotation, having an air intake, a fan, a compressor device, a combustor device, and a turbine device.

These jet engines are arranged in known manner either on wings or on the outside of the fuselage of the aircraft. The axes of rotation of these jet engines are outside the fuselage, which has the payload range of the aircraft. The payload area may e.g. Passengers, cargo (such as cameras or other devices for drones) or both.

When a part of the jet engine, e.g. a rotor part, triggers in operation, it is due to the existing centrifugal forces at high speed to the outside, moved away from the jet engine. The part may e.g. cause severe damage to the fuselage of the aircraft when the part is being thrown straight in that direction.

Basically, it is known to arrange propellers of an aircraft propulsion outside of the fuselage, wherein the axis of rotation of the propeller drive lies outside the fuselage ( WO 2014/108125 A1 . US 2018/0030852 A1 ). However, propeller drives for aircraft are not efficient, especially at higher speeds.

Therefore, the task is to train existing solutions for aircraft.

This is achieved by an aircraft having the features of claim 1.

In this case, an aircraft has at least one nozzle drive, in particular in a jacket flow design. The at least one nozzle drive comprises an air inlet with a fan, a compressor device, a combustion device and a turbine device for driving the compressor device and the fan, wherein a first part of the air flowing into the air inlet flows into the compressor device and a second part through a bypass channel. The compressor device and the turbine device can each have several stages, e.g. a high pressure, a medium and a low pressure stage.

The air inlet and the bypass duct of the at least one nozzle drive are arranged at least partially, in particular completely, around an outer wall of a payload area of the aircraft. This means that the incoming air is passed through the annular nozzle drive. Should a rotating part, e.g. solve a compressor blade, it would fly away during operation of the nozzle drive by the centrifugal forces occurring to the outside of the payload range and thus prevent or minimize damage to the payload range.

The payload area may be formed in one embodiment as the hull and / or cargo space of a passenger aircraft of a cargo aircraft or a combined passenger cargo aircraft. These aircraft often have a payload area that is substantially circular in cross-section. The at least one nozzle drive can be arranged around this cross section.

Furthermore, it is possible that in an alternative embodiment of the payload range is arranged on a drone. Drones are unmanned aerial vehicles that can also be powered by jet engines. Drones can z. B. transport cameras or other devices.

Furthermore, in one embodiment, the compressor device, the combustion chamber device and / or the turbine device of the at least one nozzle drive partially, in particular completely, disposed within the outer wall of the payload area. In this case, parts of the at least one nozzle drive can also be arranged within the outer wall of the payload area. Thereby, the outer diameter of the nozzle drive can be kept small.

Alternatively, in one embodiment, the compressor device, the combustion chamber device and / or turbine device of the at least one nozzle drive partially, in particular completely, outside the outer wall of the payload range. Thus, the payload range can be increased.

It is also possible for rotors of the compressor device and / or of the turbine device to be arranged so as to be rotatable about the outer wall of the payload region. The main axis of rotation of the at least one nozzle drive is thus inside the payload area.

It is also possible that the at least one nozzle drive in the region of the stern of the Payload range or in front of a wing around the fuselage of the aircraft is arranged around.

To increase the redundancy, at least two nozzle drives, in particular in the form of jacket engines, can be used which are arranged axially one behind the other around the payload area. In this case, a second nozzle drive can have an air inlet with a larger diameter than the diameter of the first nozzle drive. The rear nozzle drive thus has more free inflow area to accommodate air flowing around the aircraft in the free stream. In this case, in one embodiment, the second nozzle drive is arranged axially behind the first nozzle drive outside the payload area.

Furthermore, the axial rear nozzle drive with a suitable design, suck the vapor trail of the axially forward nozzle drive and develop an increased thrust due to the increased media density.

To reduce the transmission of vibrations, the payload region, in particular the outer wall, a damping device. Thus, mechanical vibrations can be damped by damping elements (e.g., plastic) coupled to the outer wall.

The at least one nozzle drive can also be designed as a geared fan drive, in which a gear device serves to reduce the rotational speed of the fan relative to the rotational speed of the driving turbine device. In this case, the transmission device may be formed as a planetary gear, wherein the sun gear is fixed or rotatably connected to the outer wall of the payload area and rotate planetary gears on a sun gear.

In order to protect in particular the outer wall of the payload area from heat, in one embodiment, a thermal protection device of the outer wall of the payload area may be provided. Thereby, e.g. basically ceramic coatings or other structures may be provided.

In one embodiment, a flow-guiding device for mixing the gas emerging from the bypass duct and / or the turbine apparatus with the ambient air may be provided for a meaningful ducting of the hot gases which provide part of the thrust.

In addition to the at least one nozzle drive, which is arranged around the payload area, at least one further nozzle drive can be arranged on a support surface and / or on the fuselage. This means that jet engines arranged in a known manner can be combined with the nozzle drives according to claim 1.

• 1 eine Seitenansicht eines Flugzeugs mit einer Ausführungsform mit einem außen am Rumpf angeordneten Düsenantrieb;
• 2 eine Detail-Seitenschnittansicht einer Ausführungsform eines Luftfahrzeuges mit einem außen am Rumpf angeordneten Düsenantrieb;
• 3 eine Seitenschnittansicht einer Ausführungsform eines Luftfahrzeuges mit zwei axial hintereinander, außen am Rumpf angeordneten Düsenantrieben;
• 4 eine Seitenschnittansicht einer Ausführungsform eines Luftfahrzeuges mit einem außen am Heck angeordneten Düsenantrieb;
• 5 eine Detail-Seitenschnittansicht einer Ausführungsform eines Luftfahrzeuges mit einem außen am Rumpf angeordneten Düsenantrieb mit einer Getriebevorrichtung in Form eines Untersetzungsgetriebes;
• 6 eine Seitenansicht eines Flugzeuges mit einer weiteren Ausführungsform mit einem außen am Rumpf angeordneten Düsenantrieb

Embodiments will now be described by way of example with reference to the figures; in the figures show:

• 1 a side view of an aircraft with an embodiment with an externally arranged on the fuselage nozzle drive;
• 2 a detail side sectional view of an embodiment of an aircraft with a nozzle arranged on the outside of the fuselage;
• 3 a side sectional view of an embodiment of an aircraft with two axially behind each other, arranged on the outside of the fuselage nozzle drives;
• 4 a side sectional view of an embodiment of an aircraft with a nozzle arranged on the outside of the nozzle drive;
• 5 a detail side sectional view of an embodiment of an aircraft with an externally arranged on the fuselage nozzle drive with a transmission device in the form of a reduction gear;
• 6 a side view of an aircraft with a further embodiment with a nozzle arranged outside of the fuselage

In the following, for an embodiment as an aircraft, a passenger aircraft 100 described in which the payload range 30 is designed as a passenger cabin in the fuselage. It will be appreciated by those skilled in the art that this is merely an example of an aircraft 100 is. For example, freighters have a payload range 30 for freight up. There are also combinations of passenger and cargo aircraft. Furthermore, unmanned aerial vehicles can also be used 100 . d .H. Drones, a payload area 30 respectively.

The aircraft shown here 100 has in the area in front of the wing a nozzle drive 10 on, around the fuselage, ie around the payload area 30 around, is arranged. As will be explained below, this structure requires that also the air inlet 1 for the incoming air is arranged annularly around the hull around. A main axis of rotation 9 of the nozzle drive 10 is arranged in the interior of the fuselage.

This embodiment is merely an example, as will be apparent from the further embodiments. So it is quite possible, the jet engine 10 at another position, e.g. B. axially further forward or axially further back.

2 shows a sectional view of a portion of a nozzle drive 10 for example, around the payload range 30 of an aircraft 100 around (see 1 ) can be arranged.

The jet engine 10 has a main axis of rotation 9 due to the arrangement around the payload range 30 around inside the payload area 30 lies. As in 1 shown, surrounds the first nozzle drive 10 the payload area 30 outside, ie the first nozzle drive 10 is around the outside wall 31 of the payload range 30 arranged around.

The jet engine 10 includes an air inlet 1 and a fan 2 which generates two air streams: one core air stream A and a bypass airflow B , The jet engine 10 includes a core 11 that the core airflow A receives. The core engine 11 includes in axial flow order a compressor device 3 with a low pressure compressor 14 and a high pressure compressor 15 ,

Furthermore, the nozzle drive comprises 10 a combustion device 4 and a turbine device 5 with a high-pressure turbine 17 and a low-pressure turbine 19 and a core thruster 8th ,

A housing 12 surrounds the nozzle drive 10 and defines a bypass channel 6 and a bypass thruster 7 , The bypass airflow B flows through the bypass channel 6 , The fan 2 is about a wave 13 through the low-pressure turbine 19 driven.

During operation, the core air flow A through the low pressure compressor 14 accelerated, compressed and in the high pressure compressor 15 directed, where a further compaction takes place. The from the high pressure compressor 15 discharged compressed air is in the combustion device 16 where it is mixed with fuel and then the mixture is burned. The resulting hot combustion products then pass through the high pressure and low pressure turbines 17 . 19 and propel them through before they provide a certain thrust through the core thruster 8th be ejected.

The high pressure turbine 17 drives the high pressure compressor 15 through a suitable connecting shaft 18 on. The fan 2 generally provides the bulk of the thrust. Such an embodiment of a nozzle drive is also called turbofan engine.

In the illustrated embodiment, the air inlet 1 with the fan 2 and the bypass channel 8th of the nozzle drive 10 completely around the outside wall 31 of the hull of the passenger plane 100 arranged around.

The remaining components, such as compressor device 3 , Incinerator 4 and turbine device 5 , are completely or partially within the outer wall 31 arranged. In alternative embodiments, for example, all parts of the nozzle drive 10 outside the outer wall 31 be arranged.

The fuselage of the aircraft 100 is formed over a majority of its axial extent as a cylinder, as in 1 is shown. The cross section of the hull, ie the cross section of the outer wall 31 , can be assumed approximately circular. In other embodiments, the cross section may also deviate from the circular shape. The rotating parts of the nozzle drive 10 but must lie on a circular path, so that inter alia, a transitional body between a non-circular cross-section and the rotating parts is necessary.

A typical outer diameter of a hull d a modern wide-body aircraft 100 is for example 6 m. If one assumes that an embodiment of an aircraft 100 according to 1 or 2 a fuselage of comparable diameter, the annularly arranged around the hull nozzle drive 10 an outer diameter D of 10 m.

This means that the hull has an annular air intake 1 having, the ring has a height of 2 m.

These figures are to be understood as exemplary only, since they vary depending on the size of the aircraft 100 and the power of the first nozzle drive 10 can vary.

In the 3 is another embodiment of an aircraft 100 shown at the two nozzle drives 10 . 20 each around the payload range 30 of the aircraft 100 are arranged. The second jet engine 20 is arranged axially behind the support surface and has a larger diameter than the first nozzle drive 10 on, allowing it to release air from the free air flow to the aircraft 100 surrounds, can accommodate. Otherwise corresponds to the structure of the two nozzle drives 10 . 20 basically the construction, as in 2 so that reference may be made to the description.

Furthermore, at the outlets of the nozzle drives 10 . 20 in this embodiment, thermal protection devices 33 arranged. These can be used, for example, as ceramic coatings on the outer wall 31 of the payload range 30 be arranged. Also on the main tail and / or the Wings may have such thermal protection 33 to be ordered,

In the 4 a further embodiment is shown, which - like the embodiment according to FIG 1 - a single nozzle drive 10 having. This is around the payload area 30 at the stern of the aircraft 100 arranged. The tail is radially outward on the nozzle drive 10 arranged. Otherwise corresponds to the structure of the two nozzle drives 10 . 20 basically the construction, as in the embodiment in 2 so that reference may be made to the description.

In the 5 is a modification of the nozzle drive 10 pictured as he is in the 2 is shown. Basically, this description can be referred to. Here is the jet engine 10 as a - basically known - Getriebefantriebwerk trained. The drive of the fan 2 takes place with the interposition of a transmission device 40 over a wave 13 the low-pressure turbine 19 , This is designed as a reduction gear, so that the relatively high speed of the low-pressure turbine 19 lowered to the drive of the fan 2 can be used.

The transmission device 40 is designed as a planetary gear, wherein a possible embodiment comprises a sun gear fixed to the hull, ie the outer wall 31 of the payload range 30 , connected is. The planet wheels then run around this sun gear. But it is also possible that the sun gear and the planets around the fuselage, ie around the outer wall 31 of the payload range 30 , revolve and the ring gear is at rest relative to the other parts.

In the embodiment according to the 5 is also a damping device 32 provided to vibrations of the nozzle drive 10 from the payload area 30 keep away or minimize. The damping device 30 can be designed as a kind of foam, which drives the nozzle 10 radially inward surrounds. A damping device 32 can also be used in other embodiments.

In the 6 is a further modification of the embodiment according to the 1 and 2 so that reference may be made to the relevant description above. In the area of the core thrust nozzle 8th are in 6 schematically flow guides 34 represented, among other things, influence on the mixture of the exiting air currents. A possible embodiment of the flow guide elements 34 is a mixer (eg with a meandering structure), with which a mixing of primary and secondary current is possible, with a decomposition into several small beams. This enlargement of the radiation surface causes the number of vertebrae to be increased, but the size to be reduced. By beam mixing a noise reduction and a reduction of the specific fuel consumption should be achieved.

The meandering structure can be used as a flow guide 34 on the outer circumference of the inside of the core thrust nozzle 8th be arranged. In principle, it is also possible that only or also on the inner circumference of the core thrust nozzle 8th (ie also on the outer wall 31 of the payload range 30 ) a flow guide 34 is arranged.

LIST OF REFERENCE NUMBERS

1

air intake

1'

second air inlet

2

fan

3

compressor device

4

incinerator

5

turbine device

6

bypass channel

7

Bypassschubdüse

8th

Kernschubdüse

9

Main axis of rotation

10

first jet engine

11

Core of the nozzle drive

12

casing

13

wave

14

Low-pressure compressor

15

High-pressure compressors

17

High-pressure turbine

18

connecting shaft

19

Low-pressure turbine

20

second jet engine

30

payload range

31

Outside wall Payload area

32

damping device

33

thermal protection device

34

flow director

40

transmission device

100

aircraft

A

Core airflow

B

Bypass airflow

d

Inner diameter payload range

D

Outer diameter of the nozzle drive

QUOTES INCLUDE IN THE DESCRIPTION

This list of the documents listed by the applicant has been generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Cited patent literature

• WO 2014/108125 A1 [0005]
• US 2018/0030852 A1 [0005]

Claims (16)

Aircraft (100) having at least one nozzle drive (10, 20), in particular in a jacket flow design, with an air inlet (1) with a fan (2), a compressor device (3), a combustion device (4) and a turbine device (5) for Driving the compressor device (5) and the fan (2), a first part (A) of the air flowing into the air inlet (1) flowing into the compressor device (3) and a second part (B) through a bypass channel (6), characterized in that the air inlet (1) and the bypass duct (6) of the at least one nozzle drive (10, 20) are at least partially, in particular completely, arranged around an outer wall (31) of a payload area (30) of the aircraft (100). Aircraft after Claim 1 , characterized in that the payload area (30) as a fuselage and / or cargo space of a passenger aircraft (100), a cargo aircraft (100) or a combined passenger cargo aircraft (100) is formed. Aircraft after Claim 1 , characterized in that the payload area (30) is arranged on a drone. Aircraft according to at least one of the preceding claims, characterized in that the compressor device (3), the combustion chamber device (4) and / or the turbine device (5) of the at least one nozzle drive (10, 20) partially, in particular completely, within the outer wall (31 ) of the payload area (30) are arranged. Aircraft after at least one of Claims 1 to 4 , characterized in that the compressor device (3), the combustion chamber device (4) and / or turbine device (5) of the at least one nozzle drive (10, 20) partially, in particular completely, outside the outer wall (31) of the payload region (30) are arranged , Aircraft according to at least one of the preceding claims, characterized in that rotors (11) of the compressor device (3) and / or the turbine device (5) are rotatably arranged externally around the outer wall (31) of the payload region (30). Aircraft according to at least one of the preceding claims, characterized in that the at least one nozzle drive (10, 20) is arranged in the region of the rear of the payload region (30) or in front of a support surface around the fuselage of the aircraft (100). Aircraft according to at least one of the preceding claims, characterized in that at least two nozzle drives (10, 20) are arranged axially one behind the other around the payload area (30). Aircraft after Claim 8 , characterized in that at least two nozzle drives (10, 20) are provided, wherein a second nozzle drive (20) has an air inlet (1) with a larger diameter than the diameter (1 ') of the first nozzle drive (10). Aircraft after Claim 9 , characterized in that the second nozzle drive (20) is arranged axially behind the first nozzle drive (10) on the outside around the payload area (30). Aircraft according to at least one of the preceding claims, characterized in that the payload region (30), in particular the outer wall (31), a damping device (32) for vibrations of the at least one nozzle drive (10, 20). Aircraft according to at least one of the preceding claims, characterized by a transmission device (40) for reducing the rotational speed of the fan (1) relative to the rotational speed of the driving turbine device (5). Aircraft after Claim 12 , characterized in that the transmission device (40) is designed as a planetary gear, wherein the sun gear is fixed or rotatably connected to the outer wall (31) of the payload area (30) and planet wheels rotate on a sun gear. Aircraft according to at least one of the preceding claims, characterized by a thermal protection device (33) of the outer wall (31) of the payload region (30) with respect to hot gases emerging from the turbine device (5). Aircraft according to at least one of the preceding claims, characterized by a flow-guiding device (34) for mixing the gas emerging from the bypass duct (6) and / or the turbine apparatus (5) with the ambient air. Aircraft according to at least one of the preceding claims, characterized by at least one further nozzle drive on a wing and / or on the fuselage.

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