Pressure intensifier, arrangement in an aircraft or spacecraft comprising a device driven by means of a drive pressure differential, aircraft or spacecraft, and method

Abstract

Pressure intensifier (28; 128) designed as a vacuum intensifier, wherein the pressure intensifier (28; 128) has a motor part (34; 134) with a fluid inlet (41; 141) and a fluid outlet (48; 148) on the motor part side and a pump part (36; 136) with a fluid inlet (61; 161) and a fluid outlet (68; 168) on the pump part side; wherein the pressure intensifier (28; 128) can be driven by means of a motor-side fluid flow (74; 174) from the motor-side fluid inlet (41; 141) to the motor-side fluid outlet (48; 148) to convey a pump-side fluid flow (76; 176) from the pump-side fluid inlet (61; 161) to the pump-side fluid outlet (68; 168); and wherein the pressure intensifier (28; 128) is designed as a positive displacement machine with a rotatable rotor (85; 185a, 185b), characterized in that the rotor (85, 185a, 185b) of the pressure intensifier (28) is designed as a rotor (85, 185a, 185b) common to the motor part (34) and the pump part (36) and comes into contact section by section with the fluid flow (74) on the motor part side and the fluid flow (76) on the pump part side during operation and the motor part (34) and the pump part (36) together form a single unit, wherein a housing (80) common to the motor part (34) and the pump part (36) is provided and the housing (80) has the fluid inlet (41) on the motor part side, the fluid outlet (48) on the motor part side, the fluid inlet (61) on the pump part side and the fluid outlet (68) on the pump part side, such that the fluid inlet (41) on the motor part side, the fluid outlet (48) on the motor part side,the pump-side fluid inlet (61) and the pump-side fluid outlet (68) each have a fluid-carrying connection to an inner area of ​​the housing (80) defined by an inner contour (81), and wherein , a position of a rotation axis (86) of the rotor (85) relative to the housing (80) is adjustable.

Description

[0001] The invention relates to a pressure intensifier, in particular a vacuum intensifier. The invention further relates to an arrangement in an aircraft or spacecraft, comprising a device that can be driven by means of a drive pressure differential. The invention further relates to an aircraft or spacecraft with such a pressure intensifier and / or with such an arrangement, and to a method for operating a device in an aircraft or spacecraft.

[0002] Although the invention may be useful and beneficial in various technical fields where pressure intensification and, in particular, the appropriate provision of a pressure difference is desired, the invention and the underlying problem will below be described using the example of compacting waste in an aircraft by means of negative pressure.

[0003] Passenger aircraft typically generate a certain amount of waste during flight. This waste can include packaging materials for food or beverages and similar items, such as plastic, paper, or cardboard packaging, cups, bags, etc., which may also contain remnants of the packaged products. Initially, such waste occupies a large volume and requires considerable storage space.

[0004] For efficient, space-saving storage of waste, it can be compacted. For example, EP 2 949 459 A1 and US 2015 / 0343732 A1 describe a system for compacting waste in an aircraft using a vacuum. Further systems for waste compaction, e.g., in an aircraft, are described, for example, in DE 10 2016 108 362 A1.

[0005] Furthermore, pressure intensifiers designed as piston devices are known. The principle of such pressure intensifiers is based on a large piston being connected to a smaller piston. In this way, the pressure intensifier, driven by a large volume flow with a low differential pressure, can supply a smaller volume flow with a higher differential pressure. To prevent the process from ending at a dead point after a working cycle, a second, similarly designed unit is provided, which, during its subsequent working cycle, moves the first unit back to its starting position. Such pressure intensifiers require a control device to execute the individual working cycles sequentially as a continuous process.

[0006] Such piston-type pressure intensifiers can generate strong vibrations at high throughput and operate only with a single pressure ratio predetermined by their design. Furthermore, these piston devices require considerable space and are quite heavy.

[0007] Furthermore, rotary positive displacement pumps, i.e., positive displacement pumps with a stator and a rotatable rotor, such as vane pumps or rotary vane pumps, are known as such. Different designs include, for example, balanced and unbalanced vane pumps, whereby balanced vane pumps may have multiple inlets and outlets to compensate for the reaction forces acting on the rotor of the vane pump.

[0008] DE 10 2010 009 730 B3 describes a fluid conveying device with impellers designed as turbines, which convert the kinetic energy of the fluid flowing through it into the mechanical energy of a rotating shaft.

[0009] DE 10 2016 121 241 B4 concerns a hydraulic drive that is combined with a pump in an integrated design.

[0010] DE 10 2015 016 795 A1 discloses a pressure transducer, in particular a pneumatic pressure transducer, which can change the fluid pressure from a transducer inlet to a desired fluid pressure at the transducer outlet.

[0011] DE 101 90 888 T5 describes a hydraulic pressure converter for converting input hydraulic power into output hydraulic power. The pressure converter comprises a cam block with a cam opening that defines a pump section and a motor section. A rotor is arranged within the cam opening and is rotatable, with vanes arranged in radial slots. The pressure converter enables a simple and cost-effective conversion of hydraulic input power into hydraulic output power with variable pressure and flow rates.

[0012] Against this background, the invention is based on the objective of enabling the operation of a device driven by a pressure difference, for example a compacting device for waste, in a space-saving and weight-saving as well as vibration-free and reliable manner, even when a pressure difference available for operation, provided for example by a vacuum or negative pressure system already existing for other purposes, is insufficient in some situations or a larger pressure difference appears desirable.

[0013] According to the invention, this problem is solved by a pressure intensifier having the features of claim 1 and / or an arrangement having the features of claim 5 and / or an aircraft or spacecraft having the features of claim 10 and / or a method having the features of claim 11.

[0014] Accordingly, a pressure intensifier designed as a vacuum intensifier is proposed. The pressure intensifier comprises a motor section with a fluid inlet and a fluid outlet on the motor section, and a pump section with a fluid inlet and a fluid outlet on the pump section. The pressure intensifier can be driven by means of a fluid flow from the motor section's fluid inlet to the motor section's fluid outlet to pump a fluid flow from the pump section's fluid inlet to the pump section's fluid outlet. According to the invention, the pressure intensifier is designed as a positive displacement machine with at least one rotatable rotor.

[0015] Furthermore, an arrangement in an aircraft or spacecraft is proposed, comprising a device driven by a drive pressure differential. The arrangement further includes a vacuum amplifier for providing the drive pressure differential using an input pressure differential that is lower than the provided drive pressure differential.

[0016] Furthermore, an aircraft or spacecraft, in particular an airplane, is created with a pressure intensifier and / or an arrangement according to the invention.

[0017] Furthermore, according to the invention, a method for operating a device in an aircraft or spacecraft is proposed, wherein the method comprises: - Discharge of an initial fluid flow as an air volume flow from an interior space of a pressurized cabin of the aircraft or spacecraft via a motor part of a vacuum amplifier towards an external environment of the aircraft or spacecraft; - Driving the vacuum amplifier with the first fluid flow and, with the aid of the vacuum amplifier driven in this way, providing a second fluid flow as an air volume flow to a pump section of the vacuum amplifier, the second fluid flow being discharged towards the external environment of the aircraft or spacecraft; and - Operating the device by means of draining the second fluid flow.

[0018] One of the underlying ideas of the invention is that a rotating positive displacement machine, i.e., a positive displacement machine with a rotatable rotor, enables pressure intensification in continuous operation without the need for a control unit. Such a pressure intensifier or pressure transformer thus has a simple design, which also benefits the reliability of the pressure intensifier and the system equipped with it. Maintenance and inspection requirements can also be advantageously reduced. Furthermore, such a pressure intensifier can be built lightweight and compact. Positive displacement machines also operate effectively and efficiently for pressure intensification or transformation at relatively small volume flows and relatively low flow velocities.

[0019] A further insight underlying the invention is that, when using an input pressure differential, which is based, for example, on an existing vacuum or negative pressure, such as in the external environment of an aircraft or spacecraft, a desired or required drive pressure differential can be provided in a convenient, simple, and reliable manner to drive a device, even when conditions in the external environment vary, by providing a vacuum amplifier that provides the drive pressure differential using the input pressure differential. Advantageously, when using the vacuum amplifier, additional motorized drive devices for a vacuum pump or the like are not required to ensure a sufficient pressure differential.Instead, an existing pressure difference, for example between the pressurized cabin and the outside environment, can be used to drive the vacuum booster. In this respect, the present invention provides a vacuum booster which, similar to a turbocharger, does not require any additional motor drive components.

[0020] The invention thus makes it particularly advantageous to ensure the reliable operation of a device, for example for compacting waste by means of negative pressure, in a simple and reliable manner, even at lower flight altitudes of an aircraft or spacecraft with correspondingly higher air pressure in its external environment, such as during landing approach.

[0021] Advantageous designs and further developments result from the additional sub-claims as well as from the description with reference to the figures.

[0022] In one embodiment, the motor section and the pump section are designed such that a first volume flow corresponding to the fluid flow on the motor side is larger than a second volume flow corresponding to the fluid flow on the pump side. In this way, a larger pressure difference can be achieved by discharging a smaller volume flow, using a larger volume flow at a lower pressure differential.

[0023] The volume flow ratio can advantageously be chosen, for example, such that the volume flow on the motor side corresponds to two to three times the volume flow on the pump side. Such a volume flow ratio can be useful, for example, when using the pressure intensifier as a vacuum booster, such as for operating a waste compaction system in an aircraft or spacecraft.

[0024] In a further development of the invention, the pressure transducer is designed according to the principle of a vane cell machine.

[0025] In one embodiment, the at least one rotor has slidably arranged vanes. In particular, the motor section can be operated like a vane motor and the pump section like a vane pump. Such a design enables relatively uniform delivery on the pump side, combined with a simple, cost-effective construction and simultaneous reduction of vibration and noise. The motor section can thus be considered, in particular, as a compressed air-driven motor, such as a vane motor, which drives a compressed air pump, such as a vane pump.

[0026] According to the invention, the rotor of the pressure intensifier is designed as a rotor common to both the motor and pump sections, with the common rotor coming into contact with the fluid flow on the motor side and the fluid flow on the pump side in sections during operation. This further simplifies the design of the pressure intensifier. In particular, the pressure intensifier can be designed with a single rotor. By using a common rotor for both the motor and pump sections, the number of components is further reduced, which in turn can have a positive effect on the manufacturing effort and the reliability of the pressure intensifier. In particular, the number of rotating components can be advantageously reduced by having the fluid flows from both the motor and pump sections act on the same rotor, as described in this design. Furthermore, the required installation space for the pressure intensifier can also be further reduced with this design.

[0027] According to the invention, the motor section and the pump section together form a single unit. A common housing is provided for both the motor section and the pump section, the housing having fluid inlets, fluid outlets, and fluid inlets on the motor section and pump section, respectively, such that each of these fluid inlets and outlets has a fluid-carrying connection to an interior region defined by an internal contour of the housing. This design contributes to a compact and simple construction of the pressure intensifier. In particular, the common rotor can be housed within the interior region of the housing, with the housing forming a stator of the positive displacement machine.

[0028] According to the invention, the position of a rotor's axis of rotation relative to the housing is adjustable. This advantageously allows for adjustment of the ratios of the volume flows and pressure differentials on the motor and pump sides. The pressure intensifier can thus, for example, be better adapted to the driven device with regard to its function, or pressure intensifiers of the same design can be used for different driven devices.

[0029] In a further development, the position of the axis of rotation can be adjusted, for example, approximately in the direction of the greatest extent of the inner area of ​​the housing. This allows for a simple adjustment of the pressure ratio between the motor and pump sections.

[0030] In one embodiment, the pressure intensifier is designed to be driven by a pressure differential between the internal pressure of an aircraft or spacecraft's pressurized cabin and the external pressure in the aircraft's or spacecraft's surrounding environment. The existing pressure difference between the cabin's air pressure and the external air pressure can thus be used to drive the pump section of the pressure intensifier, with the fluid flow on the motor side being driven by this pressure differential. Therefore, no additional motor components are required for the pressure transformation.

[0031] In particular, the motor part can be driven by means of the pressure difference between the cabin interior pressure and the outside ambient pressure, while air is extracted from the device to be driven, in particular the waste compaction device, by means of the pump part driven by the motor part.

[0032] The pressure intensifier, acting as a vacuum amplifier, is specifically designed to generate a pressure differential on the pump side that is greater than the input pressure differential on the motor side, particularly between the internal air pressure in a pressurized cabin of an aircraft or spacecraft and the air pressure in the aircraft's or spacecraft's external environment. This pressure differential on the pump side can then be used as the drive pressure differential for the device being driven.

[0033] In one embodiment of the arrangement, the vacuum intensifier is designed as a rotating displacement machine, in particular as a pressure intensifier designed according to the invention. The advantages achievable with this have already been mentioned above.

[0034] In one embodiment of the arrangement, the device can be fluid-conducted to a vacuum source via a first line, the interior of a pressurized cabin of the aircraft or spacecraft can be fluid-conducted to the vacuum source via a second line, and the vacuum amplifier is arranged such that the first line leads through a pump section of the vacuum amplifier and the second line leads through a motor section of the vacuum amplifier. A volume flow generated via the second line by means of the air pressure difference between the interior of the pressurized cabin and the outside environment can thus be used to amplify the pressure difference when extracting a volume flow via the first line. Again, additional motors for driving the vacuum amplifier are unnecessary.

[0035] In one embodiment of the arrangement, the first and second lines can be connected to a drain mast of the aircraft's or spacecraft's wastewater system or to a line of the aircraft's or spacecraft's vacuum toilet system as a source of negative pressure. This allows an existing negative pressure source in the aircraft or spacecraft, such as a passenger aircraft, to be used for the operation of the device. A drain mast or a line of a vacuum toilet system can essentially provide the ambient pressure as the negative pressure.

[0036] A drain mast can be defined as a pipe-like structure, with an aerodynamically optimized shape on its outer surface, that extends from the fuselage of an aircraft or spacecraft, particularly an airplane, and through which wastewater from a hand basin or galley can be drained. The drain mast thus provides a connection to the outside environment and therefore to the outside air pressure, which is lower relative to the cabin pressure.

[0037] In one embodiment of the arrangement, the device, which is driven by the drive pressure differential, is designed as a waste compaction device. This allows for robust and effective compaction of the waste generated.

[0038] In a further embodiment of the arrangement, the device that can be driven by means of the drive pressure difference can be designed as an adjustment device for a component of a seating arrangement.

[0039] In one embodiment, the pressure intensifier is constructed from one or more plastic materials. In particular, the housing(s), and / or the rotor(s), and / or the blades can be made from one or more plastic materials. This advantageously results in a low weight for the pressure intensifier, which is beneficial, for example, in aerospace applications. Especially when the pressure intensifier is used as a vacuum booster to increase the vacuum for operating equipment, such as in an aircraft, the aforementioned weight reduction through the use of plastic materials is possible because no extreme temperatures are expected.

[0040] The above-described embodiments and further developments can each be applied analogously to the pressure intensifier, the arrangement, the aircraft or spacecraft and the method according to the invention.

[0041] The above embodiments and further developments can be combined with one another as appropriate. Further possible embodiments, further developments, and implementations of the invention also include combinations of features of the invention described previously or subsequently with regard to the exemplary embodiments, even if not explicitly mentioned. In particular, the person skilled in the art will also add individual aspects as improvements or additions to the respective basic form of the present invention.

[0042] The present invention will be explained in more detail below with reference to the exemplary embodiments shown in the schematic figures. These figures show: Fig. 1 a perspective view of an aircraft in which the invention can be applied according to exemplary embodiments; Fig. 2 a schematic representation to explain the operation of a waste compaction device operated by means of a pressure difference; Fig. 3 a schematic representation to illustrate the connection of the waste compaction device to a main line of a vacuum toilet system; Fig. 4 a schematic representation to illustrate how to connect the waste compaction unit to a drain mast; Fig. 5 a pressure translator according to a first embodiment in a schematic representation; Fig. 6 a pressure translator according to a second embodiment in a schematic representation; Fig. 7 a schematic representation of an arrangement in an aircraft, with a pressure intensifier, according to an exemplary embodiment; Fig. 8 A schematic representation of an arrangement in an aircraft, with a pressure intensifier, according to a further embodiment; and Fig. 9 A schematic representation of a seating arrangement, for example for an aircraft passenger, with an adjustment device operated by means of a pressure difference, according to a further embodiment.

[0043] The accompanying figures are intended to provide a further understanding of the embodiments of the invention. They illustrate embodiments and, in conjunction with the description, serve to explain the principles and concepts of the invention. Other embodiments and many of the advantages mentioned will become apparent with reference to the drawings. The elements of the drawings are not necessarily shown to scale.

[0044] In the figures of the drawing, identical, functionally equivalent and similarly acting elements, features and components - unless otherwise stated - are each provided with the same reference symbols.

[0045] Fig. Figure 1 shows an aircraft 1 with a schematically indicated pressurized cabin 2, in this example a passenger aircraft, in flight. Outside the aircraft 1, the ambient air pressure decreases with increasing altitude. There is therefore a pressure difference between the cabin pressure, which in modern passenger aircraft is maintained within a range compatible with the well-being of passengers and crew, and the static pressure of the outside atmosphere. At typical cruising altitudes, this difference can be up to approximately 650 mbar.

[0046] Food and / or drinks are often served on passenger aircraft, which can generate waste such as packaging, cups, napkins, etc. To store such waste, and potentially other travel waste, in a space-saving manner for later disposal, a waste compaction system 3 is provided in the passenger cabin of aircraft 1, which reduces the volume of the waste.

[0047] In Fig. Figure 2 schematically outlines the operation of the waste compaction device 3. Fig. Figure 2(a) shows uncompacted waste 4 collected in a waste collection area in the interior 8 of a mobile trolley 6. A compaction mechanism is provided above the waste 4, for example, a bellows 10 with a fixed compaction plate 11 arranged on its underside. The interior of the bellows 10 is pressurized to the cabin pressure, i.e., the air pressure inside the pressurized cabin 2, via an open top 12 of the bellows 10 or another fluid-carrying connection between an interior area of ​​the bellows 10 and the interior of the passenger cabin 2. The interior 8 of the trolley 6, which is sealed against the interior of the bellows 10, can be connected to a vacuum source (in the) by means of a line 15. Fig. 2 not shown) can be connected, e.g. by opening one or more valves.

[0048] In Fig. 2 (b) shows that the bellows 10 expands when the interior 8 is connected to the vacuum source while the cabin air pressure acts on the interior of the bellows 10.

[0049] The waste compactor 3, which operates using negative pressure, can also be referred to by the English term "vacuum trash compactor". Furthermore, the aforementioned negative pressure source can also be called a vacuum source, whereby the term "vacuum" is understood here in the broader sense of low pressure or negative pressure, such as that found in the external environment of the aircraft 1, for example at typical cruising altitude.

[0050] For example, a vacuum toilet system of aircraft 1 with a main line 20 or a wastewater system of aircraft 1 with a so-called drain mast 19 can serve as a vacuum source for the operation of the waste compaction device 3. This is shown by way of example. Fig. 3 or 4. The wastewater system and the toilet system are connected to the outside environment of the aircraft 1 via the drain mast 19 of the wastewater system or the main line 20 of the vacuum toilet system. In this way, both the wastewater system and the vacuum toilet system provide essentially the same negative pressure as a vacuum source for the waste compaction device 3. Fig. 3, Fig. Figure 4 also shows a valve 21 in line 15, through which the connection to the main line 20 or the drain mast 19 can be selectively established or disconnected. During operation of the waste compaction device 3, an air volume flow 24 can be discharged via line 15. It is understood that in one variant of the waste compaction device 3, a dedicated connection to the outside environment, bypassing the wastewater or toilet system, could be provided.

[0051] Fig. 3, Fig. Figure 4 shows ways in which the waste compaction unit 3 can be operated, particularly at cruising altitude. The compaction of the waste 4 in Fig. 2 (b) is thus effected by means of the pressure difference between the cabin air pressure and the static ambient air pressure outside the aircraft 1, and the waste compaction device 3 is therefore driven by this differential pressure. The cabin air pressure inside the bellows 10 is in Fig. 2 is schematically indicated by the arrow 16.

[0052] To achieve effective compaction of the waste 4 even at significantly lower altitudes than the usual cruising altitude, and thus at lower differential pressures between the cabin interior and the outside environment, a pressure intensifier 28 or 128 is provided in exemplary embodiments of the present invention. The pressure intensifier 28, 128, which functions as a vacuum booster and is described in more detail below, enables the waste compaction device 3 to be provided with an increased negative pressure, in other words, a greater pressure differential to the cabin interior pressure, for its operation.The waste compactor 3, which is driven by a drive pressure differential, is thus provided with the required or desired drive pressure differential by means of the vacuum amplifier 28 or 128, using an input pressure differential that corresponds in particular to the pressure difference between the air pressure inside the pressure cabin 2 and the outside environment, the latter being greater than the input pressure differential. Thus, even at low altitudes, a vacuum sufficient for reliable operation of the waste compactor 3 can be provided and a satisfactory degree of compaction of the waste 4 can be achieved.

[0053] Fig. Figure 5 shows a schematic representation of a pressure intensifier 128 for use as a vacuum intensifier according to an exemplary embodiment. The pressure intensifier 128 is designed as a combination of a vane motor and a vane pump, and thus as a rotary positive displacement machine. Specifically, the pressure intensifier 128 comprises a motor section 134, which is designed as a vane motor, and a pump section 136, which is designed as a vane pump.

[0054] The motor part 134 has a rotor 185a with an approximately circular cylindrical rotor body 190a, wherein the rotor body 190a, in the example shown, has radially arranged slots and blades 188a that are radially displaceable in the slots. The blades 188a are preferably extended outwards, relative to the rotor body 190a, by means of Fig. 5 spring elements, not shown in detail for the sake of clarity, are subjected to pressure.

[0055] The pump section 136 has a rotor 185b with an approximately circular cylindrical rotor base 190b. In the example shown, the rotor base 190b is provided with radially arranged slots, and the rotor 185b has vanes 188b that are radially displaceable within the slots. Also in the pump section 136, the vanes 188b are preferably subjected to a spring force in the outward direction, relative to the rotor base 190b, by spring elements (not shown in detail).

[0056] The rotors 185a and 185b are rotatably arranged about a common axis of rotation 186 and are connected for this purpose by means of a shaft 150 or arranged on the common shaft 150. The rotor 185a of the motor section 134 drives the rotor 185b of the pump section 136.

[0057] The rotor 185a is housed in a stator or casing 180a of the motor section 134 and is rotatable in an inner region of the casing 180a defined by an essentially circular inner contour 181a perpendicular to the axis of rotation 186, such that the vanes 188a contact an inner wall of the casing along the inner contour 181a. The casing 180a is further equipped with a fluid inlet 141 and a fluid outlet 148 on the motor section side, which have a fluid-carrying connection to the inner region of the casing 180a. The pressure intensifier 128 is driven by a fluid flow 174 on the motor section side, which is in particular an air volume flow, from the fluid inlet 141 to the fluid outlet 148.

[0058] The rotor 185b is housed in a stator or casing 180b of the pump section 136 and is rotatable about the axis 186 in an inner region of the casing 180b defined by an inner contour 181b that is also substantially circular in cross-section, such that the vanes 188b contact an inner wall of the casing along the inner contour 181b. The casing 180b is further provided with a fluid inlet 161 and a fluid outlet 168 on the pump section side, which have a fluid-carrying connection to the inner region of the casing 180b. By driving the rotor 185b via the shaft 150 from the rotor 185a, a fluid flow 176, in particular an air volume flow, is conveyed from the fluid inlet 161 to the fluid outlet 168 of the pump section 136.

[0059] The ratio of the volume flow corresponding to the fluid flow 174 on the motor side to the volume flow 176 on the pump side can be selected by choosing the size ratio between the motor part 134 and the pump part 136, specifically the size ratios of the rotors 185a,b, the housings 180a,b, and especially the formed cells 182a,b. In this way, the achievable pressure ratio between the pump side and the motor side is also set.

[0060] The print translator 128 of the Fig. 5 can operate continuously as a vacuum amplifier without the absolute necessity of a control unit and is driven by the existing differential pressure between the pressurized cabin 2 and the external environment of the aircraft 1. In this case, a large volume flow rate at a differential pressure that is relatively low at low altitudes, for example only about 200 mbar or less, can drive the vacuum amplifier as a unit for generating a small volume flow rate to represent a large differential pressure.

[0061] In this case, the motor-side volume flow 174 is therefore greater than the pump-side volume flow 176, whereby the volume flow 174 can be two to three times that of the volume flow 176.

[0062] The pressure intensifier 128 thus provides two separate rotors 185a, 185b, which are connected to each other in a rotationally fixed manner and run in their own housings 180a, 180b. It should be noted, however, that the two housings 180a, 180b can be connected or attached to each other as a single unit, or that the two housings 180a, 180b can be designed as sections of a common housing component. In either case, however, separate internal compartments are still provided for accommodating the rotors 185a, 185b.

[0063] A pressure intensifier 28 designed as a vacuum intensifier according to a further embodiment is shown schematically in Fig. Figure 6 is shown in a cross-sectional view. The pressure intensifier 28 also has a motor section 34 with a fluid inlet 41 and a fluid outlet 48 on the motor section, as well as a pump section 36 with a fluid inlet 61 and a fluid outlet 68 on the pump section. The pressure intensifier 28 is also designed as a rotating positive displacement machine and can be driven by a fluid flow 74 on the motor section, in particular an air volume flow, from the fluid inlet 41 to the fluid outlet 48 in order to convey a fluid flow 76 on the pump section, again in particular an air volume flow, from the fluid inlet 61 to the fluid outlet 68.

[0064] Also with the print translator 28 according to Fig. 6. The air volume flow corresponding to the fluid flow 74 on the motor side is greater than the air volume flow corresponding to the fluid flow 76 on the pump side. For example, the volume flow 74 can be two to three times the volume flow 76.

[0065] In contrast to the example of the Fig. 5. The pressure intensifier 28 does not have two separately provided rotors for the motor and pump sections, but rather it is in Fig. 6 A rotor 85 is provided that is common to the motor part 34 and the pump part 36. The motor part 34 and the pump part 36 thus form a compact, space-saving unit that requires few components.

[0066] Fig. Figure 6 shows that in the pressure intensifier 28, the rotor 85 is arranged in a stator or housing 80, the housing 80 being common to the motor part 34 and the pump part 36. The rotor 85 is rotatably mounted about a rotational axis 86. An inner contour 81 defines an inner region of the housing 80 in which the rotor 85 is arranged.

[0067] The inner contour 81, see Fig. 6, is essentially oval in cross-section perpendicular to the axis of rotation 86 of the rotor 85, thus rounded and elongated compared to a circular cross-section. The inner contour 81 could, for example, be in Fig. 6 terminate in their upper and lower regions with a circular arc shape, whereby the circular arc shapes can be connected, for example, by straight segments or alternatively by other, for example, slightly curved, segments. The oval shape of the inner contour 81 could alternatively be essentially an elliptical or ellipse-like shape.

[0068] The housing 80 has the motor-side fluid inlet 41, the motor-side fluid outlet 48, the pump-side fluid inlet 61 and the pump-side fluid outlet 68, each of which establishes a fluid-carrying connection to the interior area of ​​the housing 80 defined by the inner contour 81.

[0069] The rotor 85 of the exemplary embodiment in Fig. 6 has a substantially circular cylindrical rotor base body 90, which is in Fig. 6 extends in a thickness direction perpendicular to the plane of the drawing in the manner of a cylinder and, in the illustrated example, is provided with radial slots in which radially displaceable vanes 88 are arranged. The vanes 88 are preferably spring-loaded in the outward direction, relative to the rotor body 90, such that, when the rotor 85 rotates about the axis 86, the vanes 88 follow the inner contour 81 and bear against it, i.e., against an inner wall of the housing. In this way, cells 82a are formed on the motor side and cells 82b on the pump side.

[0070] During operation, and thus during the rotation of the rotor 85, the air volume flow 74 on the motor side comes into contact with the rotor 85 in a section that corresponds to a circumferential area 89a of the rotor 85 which is fixed relative to the housing 80. The air volume flow 76 on the pump side, on the other hand, comes into contact with the rotor 85 in a section that corresponds to a different circumferential area 89b of the rotor 85, which is also fixed relative to the housing 80 and differs from circumferential area 89a. It is understood, however, that all of the vanes 88, during continued rotation of the rotor 85, alternately limit cells 82a on the motor side and cells 82b on the pump side that fill and empty.

[0071] In Fig. Thus, the first part of the housing 80, shown as the upper part in the drawing, and the portion of the rotor 85 located in this first part are assigned to the motor part 34, while the second part of the housing 80, shown as the lower part in the drawing, and the portion of the rotor 85 located in this second part are assigned to the pump part 36. The first part also includes the inlet 41 and the outlet 48, and the second part also includes the inlet 61 and the outlet 68.

[0072] The axis of rotation 86 extends in Fig. 6 perpendicular to the plane of the drawing. By positioning the axis of rotation 86 along a direction 87, which essentially runs along a direction of the greatest extent of the cross-section of the inner contour 81 normal to the axis 86, the ratio of the volume flow corresponding to the fluid flow 74 on the motor side to the volume flow 76 on the pump side, as well as the pressure ratio in the motor and pump parts 34, 36, can be set.

[0073] In a first variant, the axis of rotation 86 can be fixedly positioned along the direction 87 and mounted relative to the housing 80 in order to determine the volume flow ratios. In this first variant of the pressure intensifier 28, the rotor axis of rotation 86 is therefore not displaceable. In a second variant of the pressure intensifier 28, Fig. 6 The rotor 85 can be mounted relative to the housing 80 in such a way that the position of the axis of rotation 86 can be adjusted along the direction 87 relative to the housing 80. In this way, the pressure intensifier 28 can be adapted for various tasks, for example, to increase a vacuum for the operation of the waste compactor 3 or another device.

[0074] In other words, according to this second variant, the pressure ratio and the ratio of the volume flows between the motor side and the pump side can be changed by altering the eccentricity of the rotor 85 by shifting the rotor axis of rotation 86 along the in Fig. 6 in the direction designated by reference numeral 87.

[0075] With the pressure transducer 28 according to the embodiment of the Fig. 6. Thus, the functions of the pump section 36 and the motor section 34 can be realized using the common rotor 85 with vanes or slides 88 slidably mounted in the rotor body 90. This eliminates the need for two separate rotors, further reducing space requirements and component diversity. Therefore, in Fig. 6 Both sides of a rotor 85 common to the motor and pump section 34, 36 are used. The pressure intensifier 28 can also be driven by means of a pressure difference between the interior air pressure of the pressure cabin 2 and the outside air pressure in the vicinity of the aircraft 1.

[0076] Fig. Figure 7 shows an arrangement 98 in aircraft 1. Here, the pressure intensifier 28 is the Fig. Figure 6 shows the vacuum intensifier installed in aircraft 1, with pressure intensifier 128 being an alternative to pressure intensifier 28. The following explanations apply analogously with regard to the use of pressure intensifier 128.

[0077] A first conduit 91 enables the waste compactor 3 to be coupled to the drain mast 19 as a vacuum source in a fluid-carrying manner. The first conduit 91 leads via the pump section 36 of the pressure intensifier 28, which acts as a vacuum amplifier and thus increases the applied vacuum. The fluid inlet 61 on the pump section is therefore coupled to the waste compactor 3, while the fluid outlet 68 on the pump section can be coupled to the drain mast 19.

[0078] The fluid flow 76 extracted from the waste compaction device 3, in the illustrated embodiment an air flow, is discharged downstream of the vacuum amplifier 28 via the drain mast 19, wherein a valve 21 is provided upstream of the drain mast 19, which allows regulation, for example, depending on the compaction requirement.

[0079] A second conduit path 92 is led from an interior of the pressure cabin 2 via the motor part 34 of the pressure intensifier 28, such that the motor part-side fluid inlet 41 is coupled to the interior of the pressure cabin 2 and the motor part-side fluid outlet 48 can be coupled to the drain mast 19.

[0080] Thus, a fluid flow 74, again an air flow, corresponding to a first volume flow, can be discharged from the interior of the pressure cabin 2 to the outside environment via a silencer 93 ("muffler") through the motor section 34 of the pressure intensifier 28 and guided through the motor section 34 of the pressure intensifier 28. A second volume flow, corresponding to the fluid flow 76, is smaller than the first volume flow. The first fluid flow 74 drives the pressure intensifier 28.

[0081] In this way, the pressure intensifier 28 increases the negative pressure applied to the waste compactor 3, enabling it to operate reliably even at low altitudes. The fluid flows 76, 74, which pass through the pump section 36 and the motor section 34, are in Fig. The fluid flows 74 and 76 are combined downstream of the pressure intensifier 28 and discharged via the drain mast 19, the flow being regulated by the valve 21. The valve 21 is located downstream of the point where the fluid flows 74 and 76 converge.

[0082] The in Fig. The arrangement shown in section 8 corresponds to that of the Fig. 7 with the exception of the vacuum source. In Fig. 8. A main line 20 of a vacuum toilet system is used as a vacuum source. Also in the variant of Fig. 8 can be used instead of the pressure translator 28. Fig. 6 in an analogous manner the print translator 128 of the Fig. 5 will be used.

[0083] In both embodiments of the Fig. 7 and Fig. 8 The air pressure difference between the interior of the pressure cabin 2 and the outside environment of the aircraft 1 is essentially used as the input pressure difference for the operation of the pressure intensifier 28 or 128 and the device 3. On the pump side, a drive pressure difference is provided by means of the pressure intensifier 28 or 128, which is greater than the input pressure difference on the motor side.

[0084] The pressure intensifier 28, 128, which functions as a vacuum intensifier, requires only a small amount of space for its installation and can also be designed to be lightweight. For applications in aerospace, for example in aircraft 1, the small size and low weight of the pressure intensifier 28, 128, and especially its particularly compact design, are advantageous.

[0085] Furthermore, the pressure intensifier 28, 128 has a simple design. A control unit for continuous operation is not required. Such a simple design is advantageous with regard to the desired reliability of the pressure intensifier 28, 128 and of the system in which it is used.

[0086] Furthermore, the pressure intensifier 28, 128 operates with low vibration, which is particularly advantageous when used in an aircraft or spacecraft, such as the aircraft 1. Impairment of passenger and crew comfort due to vibrations and / or noise can be avoided.

[0087] For a waste compaction device 3, it may prove advantageous, for example, if a volume flow of approximately 60 liters / min can be extracted from the interior 8. A vacuum amplifier 28 for use in conjunction with the waste compaction device 3, as in arrangements 98 or 99 of the Fig. 7 or 8, which can provide such a volume flow, could for example be designed with a diameter of approximately 100 mm and a depth of approximately 60 mm, whereby a rotational speed of approximately 20 revolutions per second is conceivable for the rotor 85.

[0088] Fig. Figure 9 schematically illustrates a further embodiment in which an adjustment device 103 for a backrest 104 of a seating arrangement 101 is driven by means of a pressure differential amplified by a vacuum amplifier 28 or 128. The device 103 can thus also be driven by the input pressure differential, i.e., the difference between cabin pressure and ambient pressure, using a drive pressure differential that is greater than the input pressure differential, by employing the proposed vacuum amplifier 28 or 128.

[0089] The exemplary embodiment of the Fig. 9 thus differs from the previously described embodiments in that the adjustment device 103 is now driven instead of the waste compacting device 3, in order to enable, for example, an aircraft passenger to comfortably adjust 106 the backrest angle. The further explanations of the preceding embodiments can also be applied to the example of the Fig. 9 can be applied analogously, although the numerical values ​​for volume flows, rotational speeds, and geometric dimensions of the vacuum amplifier given above as examples may differ depending on the requirements. The adjusting device 103 can be used analogously to the device 3 as described in Fig. 7 or Fig. 8 shown arranged and fluid-carrying coupled to the vacuum source, the vacuum amplifier 28, 128 and the interior of the pressure cabin 2.

[0090] In all the embodiments described above, the housings 80, 180a, 180b, the rotors 85, 185a, 185b with the rotor bodies 90, 190a, 190b, and the blades 88, 188a, 188b can each be made of a plastic material or essentially of a plastic material. The pressure intensifier 28, 128 is thus particularly lightweight. Components that slide against each other, for example, the blades 88 or 188a, b and the housing 80 or 180a, b, or the blades 88 or 188a, b and the rotor body 90, 190a, b, are preferably manufactured with plastic materials such that the material pairing of the sliding elements results in minimal friction and abrasion.

[0091] Although the present invention has been fully described above with reference to a preferred embodiment, it is not limited to this embodiment, but can be modified in many different ways.

[0092] For example, the proposed pressure intensifier can also be used effectively and profitably for other applications where, for instance, increased negative pressure is required, such as the extraction of gaseous fluids in a manufacturing process. Reference symbol list 1 airplane 2 Pressure cabin 3 Waste compaction unit 4 Waste 6 trolleys 8 Interior (rolling trolley) 10 bellows 11 Compacting plate 12 Top 15 Management 16 acting cabin interior pressure 19 Drain mast 20 Main line (vacuum toilet system) 21 valve 24 Volume flow 28, 128 print translators 34, 134 Engine part 36, 136 Pump part 41, 141 engine-side fluid inlet 48, 148 engine-side fluid outlet 150 wave 61, 161 pump-side fluid inlet 68, 168 pump-side fluid outlet 74, 174 engine-side fluid flow 76, 176 pump-side fluid flow 80 cases 180a,b Housing 81 Inner contour 181a, b inner contour 82a,b cell 182a,b cell 85 Rotor 185a,b Rotor 86 Rotation axis (Rotor 85) 186 Rotation axis (rotors 185a, 185b) 87 direction 88 wings 188a,b Wing 89a,b Circumference area (rotor) 90 Rotor base bodies 190a,b Rotor body 91 first route 92 second route 93 silencers 98, 99 order 101 Seating arrangement 103 Adjustment device 104 Backrest 106 Adjustment movement

Claims

[1] Pressure intensifier (28; 128) designed as a vacuum intensifier, wherein the pressure intensifier (28; 128) has a motor part (34; 134) with a fluid inlet (41; 141) and a fluid outlet (48; 148) on the motor part side and a pump part (36; 136) with a fluid inlet (61; 161) and a fluid outlet (68; 168) on the pump part side; wherein the pressure intensifier (28; 128) can be driven by means of a motor-side fluid flow (74; 174) from the motor-side fluid inlet (41; 141) to the motor-side fluid outlet (48; 148) to convey a pump-side fluid flow (76; 176) from the pump-side fluid inlet (61; 161) to the pump-side fluid outlet (68; 168); and wherein the pressure intensifier (28; 128) is designed as a positive displacement machine with a rotatable rotor (85; 185a, 185b), characterized by, that the rotor (85, 185a, 185b) of the pressure intensifier (28) is designed as a rotor (85, 185a, 185b) common to the motor part (34) and the pump part (36) and, during operation, comes into contact section by section with the fluid flow (74) on the motor part side and the fluid flow (76) on the pump part side, and the motor part (34) and the pump part (36) together form a single unit, wherein a housing (80) common to the motor part (34) and the pump part (36) is provided and the housing (80) has the fluid inlet (41) on the motor part side, the fluid outlet (48) on the motor part side, the fluid inlet (61) on the pump part side and the fluid outlet (68) on the pump part side, such that the fluid inlet (41) on the motor part side, the fluid outlet (48) on the motor part side, the fluid inlet (68) on the pump part side (61) and the pump-side fluid outlet (68) each have a fluid-carrying connection to an inner area of ​​the housing (80) defined by an inner contour (81) thereof, and wherein a position of a rotation axis (86) of the rotor (85) relative to the housing (80) is adjustable. [2] Print translator according to claim 1, characterized by , that the motor part (34; 134) and the pump part (36; 136) are designed such that a first volume flow corresponding to the fluid flow (74; 174) on the motor part side is greater than a second volume flow corresponding to the fluid flow (76; 176) on the pump part side. [3] Print translator according to claim 1 or 2, characterized by , that the rotor (85; 185a, 185b) has slidably arranged vanes (88; 188a, 188b) and in particular that the motor part (34; 134) can be operated in the manner of a vane motor and the pump part (36; 136) can be operated in the manner of a vane pump. [4] Printing translator according to any of the preceding claims, characterized by, that the pressure intensifier (28; 128) is designed to be driven by means of a differential pressure between the internal pressure in a pressure cabin (2) of an aircraft or spacecraft (1) and an external pressure in an external environment of the aircraft or spacecraft (1). [5] Arrangement (98; 99; 101) in an aircraft or spacecraft (1), comprising a device (3; 103) that can be driven by means of a drive pressure differential, and further comprising a vacuum amplifier (28; 128) for providing the drive pressure differential using an input pressure differential which is less than the provided drive pressure differential, wherein the vacuum amplifier (28; 128) is configured as a pressure intensifier according to any one of claims 1 to 4. [6] Arrangement according to claim 5, characterized by, that the device (3; 103) can be fluid-conducted to a vacuum source (19; 20) via a first conduit (91), an interior of a pressure cabin (2) of the aircraft or spacecraft (1) can be fluid-conducted to the vacuum source (19; 20) via a second conduit (92), and the vacuum amplifier (28; 128) is arranged such that the first conduit (91) leads via a pump part (36; 136) of the vacuum amplifier (28; 128) and the second conduit (92) leads via a motor part (34; 134) of the vacuum amplifier (28; 128). [7] Arrangement according to claim 5 or 6, characterized by , that the first and second conduit paths (91, 92) can be brought into fluid contact with a drain mast (19) of a wastewater system of the aircraft or spacecraft (1) or with a conduit (20) of a vacuum toilet system of the aircraft or spacecraft (1) as a source of negative pressure. [8] Arrangement according to any one of claims 5 to 7, characterized by, that the facility is designed as a waste compaction facility (3). [9] Arrangement according to any one of claims 5 to 7, characterized by that the device is designed as an adjustment device (103) for a component (104) of a seating arrangement (101). [10] Aircraft or spacecraft (1), in particular an aircraft, comprising a pressure intensifier (28; 128) according to any one of claims 1 to 4 and / or an arrangement (98; 99; 101) according to any one of claims 5 to 9. [11] Method for operating a device (3; 103) in an aircraft or spacecraft (1) with a pressure intensifier (28; 128) according to any one of claims 1 to 4 and / or with an arrangement (98; 99; 101) according to any one of claims 5 to 9, comprising: Discharge of a first fluid flow (74; 174) as an air volume flow from an interior of a pressure cabin (2) of the aircraft or spacecraft (1) via a motor part (34; 134) of a vacuum booster (28; 128) towards an external environment of the aircraft or spacecraft (1); Driving the vacuum amplifier (28; 128) by the first fluid stream (74; 174) and, with the aid of the vacuum amplifier (28; 128) driven in this way, providing a second fluid stream (76; 176) as an air volume stream at a pump section (36; 136) of the vacuum amplifier (28; 128), wherein the second fluid stream (76; 176) is discharged in the direction of the external environment of the aircraft or spacecraft (1); and Operating the device (3; 103) by means of the discharge of the second fluid flow (76; 176).

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