DE102016224779B4 - Electric propulsion arrangement for an aircraft, method for its operation and aircraft - Google Patents

Abstract

Drive arrangement (10) for integration into an aircraft or spacecraft structure (100), with at least one drive (20), by which at least one propulsor of the aircraft or spacecraft is electrically driven or driven, with a distributor, via which the at least one propulsor can be fed or fed with electrical energy, and with at least one conversion and / or storage device (30), which emits electrical energy to the distribution device, wherein the conversion and / or storage device (30) hybrid-electrically with at least one generator set (50 ) is designed as a primary electrical energy source and wherein the generator set (50) is provided with at least one heat exchanger means (70), wherein the at least one heat exchanger means (70) for hot gas recuperation or for compressor intercooling used or used.

Description

The invention relates to a drive arrangement for integration into an aircraft or spacecraft structure, with at least one drive, by which at least one propulsor of the aircraft or spacecraft is electrically driven or driven, with a distribution device, via which the at least one Propulsor with electrical energy can be fed or fed, and with at least one conversion and / or storage device that emits electrical energy to the distribution device. Moreover, the invention relates to a method for operating a drive assembly integrated in a structure of an aircraft or spacecraft and an aircraft and spacecraft.

Such drive arrangements are known, for example, from US 2008/0 184 906 A1 or from US Pat DE 10 2008 014 404 A1 ,

Novel approaches in the field of propulsion for aircraft are to use drive components apart from conventional internal combustion engines, such as electric drive components, comparable to the corresponding developments in the automotive sector. In this case, for example, electrical energy can be provided via energy converters in the manner of a storage means, that is to say from a battery or fuel cell or couplings thereof.

Based on the current state of the art, it is not possible in particular for larger aircraft (eg civil regional / short-haul and long-haul, military transporter) to represent purely electric propulsion based on batteries or fuel cells. The energy / power densities of these components are not sufficient (by about one factor) 50 based on the pure mechanical drive by gas turbine and fan (civil aircraft) or turboprop (military transporter).

It is therefore an object to provide a drive assembly available that covers the primary energy needs of a driven by an electric drive, common aircraft, and to optimize their thermodynamic efficiency in favor of reduced fuel requirements.

This object is achieved by features of claim 1. The solution consists in particular in that the conversion and / or storage device is hybrid-electric and that at least one engine of the generator set is provided with at least one heat transfer means, wherein the generator set is provided with at least one heat transfer means, wherein the at least one heat transfer means for Hot gas recuperation or for compressor intercooling or in a comparable heat exchange process can be used or used. The hybrid-electrical design of the drive structure can ensure that sufficient electrical energy can be made available for driving the respective aircraft. In this case, the electrical energy is thus provided on the one hand from a generator set and on the other hand from a storage device of some kind. The energy thus provided is passed through an electrical distribution network to the electrically driven propulsors (fan, propeller). As a result, in particular distributed drives can be realized without complex mechanical alternatives. A significant improvement in the efficiency can be achieved on the engine of the generator set by the arrangement of a heat transfer means, whereby the engine in question of the drive arrangement is designed as a heat exchanger engine.
In order to reduce the specific fuel requirement, the at least one heat exchanger means for hot gas recuperation or for compressor intercooling (charge air cooling) or in a comparable heat exchange process can be used in the drive arrangement according to the invention.

The drive structure of the drive assembly may form a hybrid hybrid drive, for example, in which one of the associated energy converter, here the generator set, has no mechanical connection to the drive axis of the electric drive and instead drives about an electric generator, the energy for operating the Electric drive provides or or the storage means loads. For short-term higher power requirements, such a storage means can provide additional power. The one or more driving electric motors of the drive assembly always provide the necessary total torque and the required power. But there are also parallel drive structures that allow access to several different energy converter on the drive train or hybrid hybrid drive structures, which can adjust the serial and parallel hybrid drive also during a flight variable according to the operating mode and / or driving condition, conceivable. The aforementioned turbine-supported generator set has, as already apparent from the above, at least one engine with an aircraft gas turbine, a generator and a mechanical coupling means coupling these, such as a shaft on.

Further advantageous features include the subclaims.

An advantageous embodiment of the drive arrangement can consist of providing the at least one generator set with turbine support and having at least one aircraft gas turbine, an electric generator and a power electronic device, so that the required amount of electrical energy at any time at the one or more drives of the drive assembly in sufficient quantity can be made available.

Likewise advantageously, in another embodiment of the drive arrangement according to the invention, the conversion and storage device can be provided with at least one storage means, in particular with a battery and / or a fuel cell or couplings thereof, which are able to cover, for example, an increased energy demand in the short term.

In an expedient development of the drive arrangement according to the invention, with which the energy of the combustion process can be used in different ways, ie converted and reused, the generator set can be formed with at least one aircraft gas turbine, which is provided as a jet turbine, as a shaft turbine or as a turbine mixing mold , In the embodiment as a shaft turbine about the output side of a shaft available rotational energy can be tapped and electrically converted. This is a shaft power engine as a derivative of a jet engine. In principle, a generator can also be connected to a jet turbine in which the aircraft gas turbine serves as the drive of the compressor, the so-called fan.

In another advantageous embodiment of the drive arrangement, the thermodynamic efficiency can be increased, for example, by transferring to the ceramic materials on the at least one aircraft gas turbine on the part of the combustion chamber, in particular on the part of the high-pressure turbine, for which reason the at least one aircraft gas turbine expediently consists of at least one or more ceramic materials, in particular with a fiber ceramic material, is formed. This is advantageous since the materials used so far in turbine construction, such as nickel and / or cobalt-based alloys, are already close to the limits of their thermal (strength) and oxidative / corrosive load capacity. As a result, a significant increase in the compressor-pressure ratio and thus an increase in the compressor outlet temperature can be achieved, whereby the efficiency is increased.

The drive arrangement according to the invention is provided with at least one turbine-based generator set as a primary source of electrical energy. For practical application, it is of fundamental advantage to drive the thermodynamic efficiency of the respective aircraft gas turbine using kerosene as fuel as high as possible, since it is known that the individual efficiencies of different components are multiplicatively included in the overall efficiency, and the individual efficiency of the aircraft gas turbine of the order of magnitude of 45% dominates the entire hybrid electric drive chain.

In an advantageous development, in the hot gas recuperation, the at least one heat exchanger means have at least one first transmission member, which is arranged downstream of the aircraft gas turbine and there extracts heated air and contacted at least indirectly with an incoming air flow to a combustion chamber for heating. Here, for example, this heating air can be taken behind the high-pressure compressor of the aircraft gas turbine as a partial flow or total flow and first the first transmission member, which forms a heat exchanger, are supplied. The heated after heat exchange with the heating air inflow air can then be finally returned and recycled after the high pressure compressor, but before the combustion chamber in the circulation.

In another advantageous development, at least one second transfer member of the heat transfer medium after a compression stage of the at least one engine of the generator set at least partially remove air from an air flow air, cool the extracted air and then perform the air flow after the compression stage again at a compressor intercooling. The removal of the air flow can be carried out as a partial flow or total flow, for example after a low pressure compressor of the aircraft gas turbine, the cooling can be performed by a heat exchanger as a transfer member and the cooled air are then fed back to the low pressure compressor.

In order to carry out the mentioned measures for increasing the thermodynamic efficiency in the various engine configurations, it is expedient to arrange the relevant transmission elements in the form of heat exchangers in the vicinity of the engine. The respective heat exchangers require materials which are resistant to high temperatures; these could conventionally be Ni or Co base alloys, however, which are comparatively heavy at specific gravities of about 9 g / cm ³ and, moreover, have a comparatively low thermal conductivity. In this respect Ni or Co base alloys are not optimal materials for the construction of heat exchangers, and as materials are not just good handle and process. In an advantageous embodiment of the drive arrangement according to the invention, therefore, a heat exchanger may be formed as the at least one transmission member and possibly other components of the heat exchanger of a high temperature resistant material, which is formed in particular of a ceramic material.

Advantageous developments may consist in that the high-temperature-resistant material comprises carbon or carbon-containing compounds, in particular one or more carbides, preferably silicon carbide (SiC) or silicon-infiltrated silicon carbide (SiSiC).

If one starts from conventional aircraft structures, then heat exchanger thrusters with their heat exchangers as transmission elements are not easy to establish due to the required installation space, since this installation space, or more precisely generally below a wing, is difficult to implement. It is therefore expedient, in another embodiment of the drive arrangement, to arrange the turbine-supported generator set and / or the transmission element of the heat exchanger means in the fuselage or in a region close to the fuselage, in particular in the region of wing roots, of the aircraft structure. In this case, the cargo space of the aircraft would be suitable for integrating one or more heat exchangers as transmission elements, while, for example, engines including electrical generators would be accommodated either in the wing root or completely in the fuselage. The mentioned fuselage integration has the advantage that it offers both a largely undisturbed engine flow, as well as a largely balance-neutral geometry. In addition, the wing or sails on the appropriately equipped aircraft sufficient space for flaps or high-lift systems.

The object stated above is also achieved by a method for operating a drive arrangement integrated in a structure of an aircraft or spacecraft. This has at least one electric drive, with a distribution device, via which at least one propulsor is supplied with electrical energy, and at least one formed as a serial hybrid conversion and storage device, is discharged through the energy converters by means of electrical energy to the distribution device. According to the invention, at least one engine of an energy converter designed as a generator set is operated with at least one heat transfer medium, by means of which a heat exchange process is carried out to increase the thermodynamic efficiency, for example a hot gas recuperation process and / or a compressor intercooling process.

Furthermore, the object is also achieved by an aircraft or spacecraft with at least one drive arrangement, by which the aircraft or spacecraft is at least partially electrically driven.

In one development of the aircraft or spacecraft according to the invention, this can be provided with a plurality of drives of a drive arrangement or of a plurality of drive arrangements which can be arranged or arranged distributed on the structure of the aircraft or spacecraft, which results in a balanced weight distribution of the units on the aircraft structure allowed.

The above embodiments and developments can, if appropriate, combine with each other as desired. Further possible refinements, developments and implementations of the invention also include combinations of features of the invention which have not been explicitly mentioned above or described below with regard to the exemplary embodiments. 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.

• 1 eine perspektivische Seitenansicht eines ersten Ausführungsbeispiels der Antriebsanordnung mit einem Generatorsatz, der eine Wellenleistungsturbine aufweist, die einen Generator speist;
• 2 eine perspektivische Seitenansicht einer in einem rumpfnahen Bereich einer Flügelwurzel eines Luftfahrzeugs integrierten Antriebsanordnung aus der 1;
• 3 eine perspektivische Seitenansicht einer im Rumpf eines Luftfahrzeugs integrierten Antriebsanordnung aus der 1; und
• 4 eine schematische Darstellung der verfahrenstechnischen Ausführung eines Rekuperators für Turbinenabgas eines Triebwerks eines Generatorsatzes einer erfindungsgemäßen Antriebsanordnung.

The invention is explained below with reference to embodiments in the drawing. In partially schematized representation here show the

• 1 a side perspective view of a first embodiment of the drive assembly with a generator set having a shaft power turbine feeding a generator;
• 2 a side perspective view of an integrated in a fuselage region of a wing root of an aircraft drive assembly of the 1 ;
• 3 a side perspective view of an integrated in the fuselage of an aircraft drive assembly of the 1 ; and
• 4 a schematic representation of the procedural embodiment of a recuperator for turbine exhaust of an engine of a generator set of a drive assembly according to the invention.

In all figures, the same or functionally identical elements and devices - unless otherwise stated - have been given the same reference numerals.

In that 1 to 3 one recognizes one with the whole 10 designated drive assembly for integration into an aircraft or spacecraft structure 100 which in the 2 as a fuselage Area 110 a wing root of the local aircraft structure 100 and in the 3 as a body section 120 the aircraft structure concerned 100 is shown, in which the in the 1 shown drive arrangement 10 each integrated.

The drive arrangement 10 is doing with a low pressure system of an otherwise not shown drive 20 shown, by which at least one non-illustrated propulsor of the aircraft or spacecraft is electrically driven or driven. Also due to the clarity was on the presentation of a distribution device over which the at least one propulsor is fed or fed with electrical energy dispensed. Moreover, the drive arrangement in each case has a conversion and / or storage device 30 , which emits electrical energy to the distribution device. The conversion and / or storage device 30 is hybrid-electric with at least one generator set 50 is designed as a primary electrical energy source, and the generator set 50 is with at least one heat transfer agent 70 Provided.

The 1 shows this in greater detail the generator set 50 the drive assembly 10 on which an aircraft gas turbine 52 as an engine, the powered generator 54 as well as the two connecting shaft 56 are recognizable as connecting means. The drive arrangement 10 the 1 is therefore provided with a shaft power engine.

The 2 shows a possibility of integration of the drive assembly 10 in the fuselage area 110 at the wing root of an aircraft. This has the advantage of a largely undisturbed of the engine flow and a largely balance-neutral geometry. In addition, this is the wing itself enough space for flaps or high-lift systems available. A thermal transfer element 75 a heat transfer agent 70 can be arranged, for example, in the area of a cargo hold of the respective aircraft.

In the 3 In contrast, one recognizes a possibility for integrating the drive arrangement 10 in a fuselage section 120 , the corresponding engine intake to the flow of the respective aircraft gas turbine 52 required, but this is to be realized in a simple manner. Due to the arrangement in a fuselage section, it is possible to use the transmission link 75 of the heat transfer agent 70 to position closer to the drive assembly.

In the 4 Finally, one recognizes a schematic representation of the procedural execution of a generator set 50 a drive arrangement 10 as a recuperator 80 for hot turbine exhaust into an aircraft structure 100 to integrate. In this case, by means of the arrows shown, the flow direction of the air flow 40 displayed. Starting from an inlet 82 At the left end for the viewer is the air flow 40 first at the generator 54 passed by and then passes through a low pressure compressor 84 and a high pressure compressor 86 a compression device 88 , Before the air flow 40 then in a combustion chamber 90 enters, he passes a sampling point 92 at which the air flow 40 taken as a partial flow or total flow and the thermal transfer element 75 that with a heat exchanger 76 is formed, supplied as cool, to be heated air. On the transmission link 75 takes place, for example, in countercurrent principle, a heat exchange, whereby the air is heated or heated, it is finally returned and after the high pressure compressor 86 in front of the combustion chamber 90 recycled to the circulation, where they subsequently pass through the combustion chamber 90 , High-pressure turbine 52a and low pressure turbine 52b the thermal transfer element 75 the Wärmeübertragermittels again, this time as a heat-releasing fluid, passes and is discharged as exhaust gas ..

The in the 4 illustrated drive assembly 10 So again shows a heat exchanger engine.

The in the 1 to 4 to be recognized heat exchanger engines represent a way to significantly increase the thermodynamic efficiency according to Joule-Brayton. This is associated with a reduction in specific fuel requirements and the reduction of pollutant emissions. Depending on the mission, increasing the thermodynamic efficiency can be up to 22%. Heat exchanger engines require integration with the fuselage of a conventional aircraft structure 100 due to the space requirements of the heat exchangers (eg, in compressor intercooling or exhaust recuperation).

Possible additional effects of such an integration of drive arrangements 10 as a heat exchanger engines forms about the establishment of distributed drives and thereby achievable increase of the bypass ratio (by-pass ratio). Distributed drives also offer the possibility of reducing the boundary layer thickness on the wing and / or the fuselage, depending on the arrangement of the distributed drives. When using hybrid electric drive technology, a variety of distributed drive configurations are relatively easy to represent.

Although the present invention has been described above with reference to preferred embodiments, it is not limited thereto, but modifiable in a variety of ways. In particular, the invention can be varied or modified in many ways without deviating from the gist of the invention.

LIST OF REFERENCE NUMBERS

10

drive arrangement

20

drive

30

Convertible and storage device

40

airflow

50

generator set

52

Passenger Rubies

52a

High-pressure turbine

52b

Low-pressure turbine

54

generator

56

wave

70

Wärmeübertragermittel

75

transmission member

76

heat exchangers

80

recuperator

82

inlet

84

Low-pressure compressor

86

High-pressure compressors

88

compressor means

90

combustion chamber

92

sampling point

100

Aircraft structure

110

fuselage area

120

fuselage section

Claims (15)

Drive arrangement (10) for integration into an aircraft or spacecraft structure (100), with at least one drive (20), by which at least one propulsor of the aircraft or spacecraft is electrically driven or driven, with a distribution device, via which the at least one propulsor can be fed or fed with electrical energy, and with at least one conversion and / or storage device (30), which emits electrical energy to the distribution device, wherein the conversion and / or storage device (30) hybrid-electrically with at least one generator set (50 ) is designed as a primary electrical energy source and wherein the generator set (50) is provided with at least one heat exchanger means (70), wherein the at least one heat exchanger means (70) for hot gas recuperation or for compressor intercooling used or used. Drive arrangement according to Claim 1 wherein the at least one generator set (50) is provided with turbine support and has at least one aircraft gas turbine (52), an electric generator (54) and a power electronic device. Drive arrangement according to Claim 1 or 2 , wherein the conversion and storage device (30) is provided with at least one storage means. Drive arrangement according to Claim 3 wherein the storage means is provided with a battery and / or a fuel cell. Drive arrangement according to Claim 2 wherein the at least one aircraft gas turbine (50) is designed as a jet turbine, as a shaft turbine or as a turbine mixing mold. Drive arrangement according to one of Claims 2 or 5 wherein the at least one aircraft gas turbine (52) is at least partially formed from one or more ceramic materials. Drive arrangement according to one of the preceding claims, wherein in the hot gas recuperation, the at least one heat transfer means (70) at least a first transmission member (75) which is downstream of the aircraft gas turbine (52) and a combustion chamber (90) inflowing air flow (40). Takes air after their compression takes. Drive arrangement according to one of the preceding claims, wherein in the compressor intercooling at least a second transmission member of the heat transfer means (70) after a compressor device (88) of the generator set (50) the air flow (40) at least partially removes air, the extracted air cools and then the Air flow (40) after the compressor device (88) feeds again. Drive arrangement according to Claim 7 wherein the at least one transmission member (75) and further components of the heat exchanger means (70) are formed of a high temperature resistant material. Drive arrangement according to Claim 9 wherein the high temperature resistant material comprises carbon or carbonaceous compounds having one or more carbides. Drive arrangement according to Claim 10 wherein the carbonaceous compounds are silicon carbide (SiC) or silicon-infiltrated silicon carbide (SiSiC). Drive arrangement according to one of the preceding claims, wherein the turbine-supported generator set (50) and / or the at least one transmission member (75) of the heat transfer means (70) in a fuselage section (120) or in a fuselage region (110) in the region of wing roots of the aircraft structure ( 100) is arranged. Method for operating a drive arrangement (10) integrated in a structure (100) of an aircraft or spacecraft according to one of the preceding claims, having at least one electric drive (20), with a distributor device, via which at least one propulsor is supplied with electrical energy, and with at least one conversion and storage device (30) designed as a serial hybrid, by means of which energy converters deliver electrical energy to the distribution device, at least one engine of an energy converter designed as a generator set (50) being operated with at least one heat exchanger (70), by means of which, to increase the efficiency, a heat exchange process is carried out, wherein a heat exchange process with at least the following steps is carried out on the at least one engine of the generator set (50): a. Downstream of a heat exchanger (76) as a transfer member (75) in the air flow (40) of the engine after an aircraft gas turbine (52) and coupling with a arranged after a compressor device (88) of the engine extraction point (92); b. Removing air from the air stream (40) at the extraction point (92) and supplying the air to the transmission member (75); c. Performing the heat exchange in countercurrent configuration; d. Return of the heated air after the heat exchange and supply to the air flow (40) after the compressor device (88). Method according to Claim 13 , with at least the following steps a. Arranging a sampling point (92) for a compressor device (88) of the engine; b. Removing air at the extraction point (92) and supplying the air to the transmission member (75); c. Cooling down the air at the transfer element (75) designed as a heat exchanger (76); d. Returning the cooled air to the extraction point (92) and then feeding it into the airflow (40) of the engine. An aircraft or spacecraft structure (100) having at least one drive assembly that is at least partially electrically powered, according to any one of Claims 1 to 12 wherein a plurality of drives (20) of a drive assembly (10) or a plurality of drive assemblies (10) are arranged distributed on the aircraft or spacecraft structure (100).

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