TRANSMISSION ASSEMBLY FOR AN ENGINE WITH A CONDUIT SYSTEM HAVING TWO FLUID GUIDES ON A STATIC PART

Abstract

The proposed solution relates to a gear box assembly for an engine, having a gear box for transmitting a torque, at least one first, static part, at least one second, rotating part, which is mounted so as to be rotatable relative to the first, static part and on which at least one element of the gear box is provided, and a conduit system for conveying a fluid to elements of the gear box.

A feed device of the conduit system on the first, static part has at least two separate fluid guides, of which a first fluid guide is provided for guiding fluid from at least one first feed opening to a first supply line in the second, rotating part and a second fluid guide is provided for guiding fluid from at least one second feed opening to a second supply line in the second, rotating part.

Claims

1. A gear box assembly for an engine, having a gear box for transmitting a torque, at least one first, static part, at least one second, rotating part, which is mounted so as to be rotatable relative to the first, static part and on which at least one element of the gear box is provided, and a conduit system for conveying a fluid to at least two different regions of the gear box, wherein the conduit system has at least one first supply line in the second, rotating part for the purposes of conveying fluid to a first region of the gear box and has at least one second supply line in the second, rotating part for the purposes of conveying fluid to a second region of the gear box, and wherein the conduit system has a feed device in the first, static part, by means of which feed device fluid can be guided to the first supply line and to the second supply line, wherein the feed device has at least two separate fluid guides, of which a first fluid guide is provided for guiding fluid from at least one first feed opening to the first supply line and a second fluid guide is provided for guiding fluid from at least one second feed opening to the second supply line.

2. The gear box assembly according to claim 1, wherein the at least two fluid guides are provided for guiding a fluid with different delivery pressures, speeds and/or temperatures.

3. The gear box assembly according to claim 1, wherein each fluid guide has at least one guide duct for the fluid that is to be guided to the respective supply line.

4. The gear box assembly according to claim 3, wherein the at least one guide duct extends in each case axially in relation to a rotation axis of the second, rotating part.

5. The gear box assembly according to claim 3, wherein a guide duct of the first fluid guide and a guide duct of the second fluid guide have different lengths.

6. The gear box assembly according to claim 3, wherein the feed device has a feed duct component on which both at least one guide duct of the first fluid guide and at least one guide duct of the second fluid guide are formed.

7. The gear box assembly according to claim 6, wherein the guide ducts of the at least two different fluid guides are arranged so as to alternate with one another along a circumferential direction on the guide duct component.

8. The gear box assembly according to claim 3, wherein the first fluid guide has at least two guide ducts to which the at least one first feed opening is assigned, and/or the second fluid guide has at least two guide ducts to which the at least one second feed opening is assigned.

9. The gear box assembly according to claim 8, wherein the feed device comprises a distributor component by means of which a fluid flow from the at least one first feed opening and/or a fluid flow from the at least one second feed opening can be divided up into multiple partial flows to the assigned guide ducts.

10. The gear box assembly according to claim 9, wherein the distributor component has at least two distributor openings by means of which fluid from a fluid flow can be guided to the at least two guide ducts.

11. The gear box assembly according to claim 10, wherein the feed device comprises a housing part on which the at least one first feed opening is provided and which, together with the distributor component, defines a distributor duct which runs in circumferentially encircling fashion in relation to the rotation axis of the second, rotating part and into which fluid can flow from the at least one first feed opening and from which the inflowing fluid can flow via the at least two distributor openings into the at least two guide ducts of the first fluid guide.

12. The gear box assembly according to claim 9, wherein, on the distributor component, there is provided at least one outflow opening via which fluid can flow from the respective guide duct to the assigned first or second supply line.

13. The gear box assembly according to claim 3, wherein a guide duct of a fluid guide is assigned exactly one feed opening.

14. The gear box assembly according to claim 3, wherein a guide duct is assigned in each case one outflow opening of the feed device, via which fluid can flow from the respective guide duct to the assigned first or second supply line.

15. The gear box assembly according to claim 14, wherein an outflow opening of the first fluid guide is axially offset with respect to an outflow opening of the second fluid guide in relation to the rotation axis of the second, rotating part.

16. The gear box assembly according to claim 1, wherein the first feed opening and the second feed opening are positioned offset with respect to one another axially, and/or in a circumferential direction, in relation to the rotation axis of the second, rotating part.

17. The gear box assembly according to claim 1, wherein the first supply line is provided for conveying the fluid to a bearing of the gear box and the second supply line is provided for conveying the fluid to a toothed gear pairing of the gear box.

18. The gear box assembly according to claim 17, wherein the first supply line is provided for conveying fluid to a plain bearing of the planet gear, which fluid is cooler than the fluid for the toothed gear pairing.

19. The gear box assembly according to claim 1, wherein the gear box is configured as a planetary gear box.

20. The gear box assembly according to claim 19, wherein the conduit system is part of an oil supply for a planet carrier of the planetary gear box.

21. The gear box assembly according to claim 17, wherein the first supply line is provided for conveying the fluid to a bearing by means of which a planet gear of the planetary gear box is rotatably mounted on the planet carrier, and the second supply line is provided for conveying the fluid to a toothed gear pairing between a planet gear and a sun gear of the planetary gear box.

22. An engine having a gear box assembly according to claim 1.

23. The engine according to claim 22, which at least comprises: a core engine that comprises a turbine, a compressor, and a core shaft connecting the turbine to the compressor, and a fan that is positioned upstream of the core engine, wherein the fan comprises a plurality of fan blades, wherein the gear box of the gear box assembly can be driven by the core shaft, and the fan can be driven at a lower rotational speed than the core shaft by means of the gear box.

Description

[0061] In the figures:

[0062] FIG. 1 shows, in a detail, a design variant of a proposed gear box assembly in cross section and in a view directed towards a first supply line within a second, rotating part, on which elements of the gear box are provided, of the gear box assembly, and towards a first fluid guide of a feed device in a first, static part of the gear box assembly;

[0063] FIG. 2 shows, likewise in a detail and in cross section, the gear box assembly of FIG. 1 in a view directed towards a second supply line and a second fluid guide of the feed device;

[0064] FIG. 3 shows, in an exploded illustration, parts of the feed device of FIGS. 1 and 2 for the spatial separation of the fluid flow, which feeds the first and second supply lines, in the first, static part;

[0065] FIGS. 4A-4B show, in different sectional views, a further design variant of a feed device for a gear box assembly of FIGS. 1 and 2, wherein the feed device is formed here with a single-part guide duct component, which also integrates feed openings and outflow openings;

[0066] FIG. 5 shows a cross-sectional view of the guide duct component of FIGS. 4A and 4B;

[0067] FIG. 6 shows a lateral sectional view of a gas turbine engine in which a proposed gear box assembly is used;

[0068] FIG. 7 shows a close-up lateral sectional view of an upstream portion of a gas turbine engine of FIG. 6;

[0069] FIG. 8 shows a partially cut-away view of a gear box for a gas turbine engine of FIGS. 6 and 7.

[0070] Before design variants of a proposed gear box assembly having a feed device 5 are described in more detail, a field of application of the proposed solution, namely a gas turbine engine 10 of an aircraft, will be described in conjunction with FIGS. 6 to 8.

[0071] FIG. 6 illustrates a gas turbine engine 10 having a main rotation axis 9. The engine 10 comprises an air intake 12 and a fan 23 that generates two air flows: a core air flow A and a bypass air flow B. The gas turbine engine 10 comprises a core 11 that receives the core air flow A. When viewed in the order corresponding to the axial direction of flow, the core engine 11 comprises a low-pressure compressor 14, a high-pressure compressor 15, a combustion device 16, a high-pressure turbine 17, a low-pressure turbine 19, and a core thrust nozzle 20. An engine nacelle 21 surrounds the gas turbine engine 10 and defines a bypass duct 22 and a bypass thrust nozzle 18. The bypass air flow B flows through the bypass duct 22. The fan 23 is attached to and driven by the low-pressure turbine 19 via a shaft 26 and an epicyclic planetary gear box 30.

[0072] During operation, the core air flow A is accelerated and compressed by the low-pressure compressor 14 and directed into the high-pressure compressor 15, where further compression takes place. The compressed air expelled from the high-pressure compressor 15 is directed into the combustion device 16, where it is mixed with fuel and the mixture is combusted. The resulting hot combustion products then propagate through the high-pressure and low-pressure turbines 17, 19 and thereby drive said turbines, before being expelled through the nozzle 20 to provide a certain thrust force. The high-pressure turbine 17 drives the high-pressure compressor 15 by way of a suitable connecting shaft 27. The fan 23 generally provides the major part of the thrust force. The epicyclic planetary gear box 30 is a reduction gear box.

[0073] An exemplary arrangement for a geared fan gas turbine engine 10 is shown in FIG. 6. The low-pressure turbine 19 (see FIG. 6) drives the shaft 26, which is coupled to a sun gear 28 of the epicyclic planetary gear box 30. Multiple planet gears 32, which are coupled to one another by a planet carrier 34, are situated radially to the outside of the sun gear 28 and mesh therewith. The planet carrier 34 guides the planet gears 32 in such a way that they circulate synchronously around the sun gear 28, whilst enabling each planet gear 32 to rotate about its own axis. The planet carrier 34 is coupled via linkages 36 to the fan 23 in order to drive its rotation about the engine axis 9. An external gear or ring gear 38 that is coupled via linkages 40 to a stationary support structure 24 is situated radially to the outside of the planet gears 32 and meshes therewith.

[0074] It should be noted that the expressions “low-pressure turbine” and “low-pressure compressor”, as used herein, can be taken to mean the lowest-pressure turbine stage and lowest-pressure compressor stage (i.e. not including the fan 23), respectively, and/or the turbine and compressor stages that are connected together by the connecting shaft 26 with the lowest rotational speed in the engine (i.e. not including the gear box output shaft that drives the fan 23). In some documents, the “low-pressure turbine” and the “low-pressure compressor” referred to herein may alternatively be known as the “intermediate-pressure turbine” and “intermediate-pressure compressor”. Where such alternative nomenclature is used, the fan 23 may be referred to as a first, or lowest-pressure, compression stage.

[0075] The epicyclic planetary gear box 30 is shown in greater detail by way of example in FIG. 8. The sun gear 28, planet gears 32 and ring gear 38 in each case comprise teeth on their periphery to allow meshing with the other toothed gears. However, for clarity, only exemplary portions of the teeth are illustrated in FIG. 8. Although four planet gears 32 are illustrated, it will be apparent to a person skilled in the art that more or fewer planet gears 32 may be provided within the scope of protection of the claimed invention. Practical applications of an epicyclic planetary gear box 30 generally comprise at least three planet gears 32.

[0076] The epicyclic planetary gear box 30 illustrated by way of example in FIGS. 7 and 8 is a planetary gear box in which the planet carrier 34 is coupled to an output shaft via linkages 36, with the ring gear 38 being fixed. However, any other suitable type of planetary gear box 30 may be used. As a further example, the planetary gear box 30 may be a star arrangement, in which the planet carrier 34 is held fixed, with the ring gear (or external gear) 38 being allowed to rotate. In such an arrangement, the fan 23 is driven by the ring gear 38. As a further alternative example, the gear box 30 may be a differential gear box in which both the ring gear 38 and the planet carrier 34 are allowed to rotate.

[0077] It is self-evident that the arrangement shown in FIGS. 7 and 8 is merely an example, and various alternatives fall within the scope of protection of the present disclosure. Purely by way of example, any suitable arrangement can be used for positioning the gear box 30 in the engine 10 and/or for connecting the gear box 30 to the engine 10. By way of a further example, the connections (such as the linkages 36, 40 in the example of FIG. 7) between the gear box 30 and other parts of the engine 10 (such as the input shaft 26, the output shaft and the fixed structure 24) may have a certain degree of stiffness or flexibility. As a further example, any suitable arrangement of the bearings between rotating and stationary parts of the engine 10 (for example between the input and output shafts of the gear box and the fixed structures, such as the gear casing) may be used, and the disclosure is not limited to the exemplary arrangement of FIG. 7. For example, where the gear box 30 has a star arrangement (described above), a person skilled in the art would readily understand that the arrangement of output and support linkages and bearing positions would usually be different from that shown by way of example in FIG. 7.

[0078] Accordingly, the present disclosure extends to a gas turbine engine having any arrangement of gear box types (for example star-shaped or epicyclic-planetary), support structures, input and output shaft arrangement, and bearing positions.

[0079] Optionally, the gear box may drive additional and/or alternative components (for example the intermediate-pressure compressor and/or a booster compressor).

[0080] Other gas turbine engines in which the present disclosure can be used may have alternative configurations. For example, such engines may have an alternative number of compressors and/or turbines and/or an alternative number of connecting shafts. As a further example, the gas turbine engine shown in FIG. 6 has a split flow nozzle 20, 22, meaning that the flow through the bypass duct 22 has its own nozzle, which is separate from and radially outside the engine core nozzle 20. However, this is not restrictive, and any aspect of the present disclosure can also apply to engines in which the flow through the bypass duct 22 and the flow through the core 11 are mixed or combined before (or upstream of) a single nozzle, which may be referred to as a mixed flow nozzle. One or both nozzles (whether mixed or split flow) can have a fixed or variable region. Although the example described relates to a turbofan engine, the disclosure may be applied for example to any type of gas turbine engine, for example an open-rotor engine (in which the fan stage is not surrounded by an engine nacelle) or a turboprop engine. In some arrangements, the gas turbine engine 10 potentially does not comprise a gear box 30.

[0081] The geometry of the gas turbine engine 10, and components thereof, is/are defined by a conventional axis system, which comprises an axial direction (which is aligned with the rotation axis 9), a radial direction (in the direction from bottom to top in FIG. 6), and a circumferential direction (perpendicular to the view in FIG. 6). The axial, radial and circumferential directions are mutually perpendicular.

[0082] For lubrication and/or heat dissipation, provision may be made for a friction-releasing and/or cooling fluid, for example oil, to be conveyed to various points of the planetary gear box 30. For example, specifically with regard to the high rotational speeds of rotating (gear box) elements of the planetary gear box 30, provision may be made for oil to be supplied to bearings for these rotating elements and/or to toothed gear pairings at this planetary gear box 30. This relates for example to a plain bearing arrangement for a planet gear 32 on the planet carrier 34. Here, in order to provide the greatest possible degree of fail safety, a conduit system for conveying oil to a corresponding plain bearing is provided. In the present case, a planet gear 32 rotates, at the respective plain bearing, in each case about a journal 61 of the planetary gear box 30. This journal 61 is illustrated as a detail in FIG. 1 together with a sun gear 28 of the planetary gear box 30. The sun gear 28 of the planetary gear box 30 can be driven via a drive shaft 60.

[0083] FIG. 1 shows further parts of a conduit system, which in the present case comprises inter alia a feed device 5 and a first supply line 5A to the bearings, configured here in the form of plain bearings, at the planet carrier 34. Here, the conduit system 5 of FIG. 1 is part of a design variant of a proposed gear box assembly which comprises a first, static part 55 and a second part 56, which is mounted so as to be rotatable relative to said first part and which rotates during the operation of the planetary gear box 30 and on which the planet carrier 34 is provided. Oil, which originates for example from a central oil reservoir, is conducted via the feed device 5 in the first, static part 55 to the second, rotating part 56 and is transferred at various points of the second, rotating part 56 to duct portions 560A and 560B (cf. also FIG. 2) that belong to different supply lines 5A and 5B. Whilst the first supply line 5A is provided for conveying oil to the plain bearings of the planet carrier 34, a second supply line 5B serves for conveying oil to the planet gears 32, and here in each case to a nozzle holder 325 between two planet gears 32, for the purposes of lubricating the toothed gear pairing between a respective planet gear 32 and the sun gear 28. In order to make it possible here to supply oil at different temperatures, for example, to the supply lines 5A, 5B that are provided for supplying oil to different regions of the gear box 30, the feed device 5 has two fluid guides 51, 52 in the first, static part 55.

[0084] The first fluid guide 51, which can be seen in the cross-sectional view of FIG. 1, has a single feed opening 510 for the connection of one fluid conduit. Via this (first) feed opening 510 of the first fluid guide 51, the oil passes via an axially extending fluid duct 512 that opens into an outflow opening 511 of the first fluid guide 51. Via this outflow opening 511, the oil can flow into the duct portion 560A, which is part of the first supply line 5A, in the second, rotating part 56. At the transition between the outflow opening 511 of the first fluid guide 51 and the duct portion 560A of the first supply line 5A, a seal with respect to the second, rotating part 56 is provided by way of seals 50a, 50b in the form of circumferentially encircling sealing rings.

[0085] Additionally, correspondingly to the cross-sectional view of FIG. 2, the feed device 5 also incorporates a second fluid guide 52, via which oil can be conducted to the second supply line 5B. For this purpose, the second fluid guide 52 has a second feed opening 520, which is axially offset with respect to the first feed opening 510 of the first fluid guide 51, for a fluid flow that is separated from the first fluid guide 51. Via the second feed opening 520, inflowing fluid passes into a guide duct 522 of the second fluid guide 52, which guide duct extends in the first, static part 55 likewise axially but so as to be offset in a circumferential direction with respect to a guide duct 512 of the first fluid guide 51. Here, a guide duct 522 of the second fluid guide 52 opens into an outflow opening 521. This outflow opening 521 of the second fluid guide 52 is offset axially, and in a circumferential direction about the rotation axis of the second, rotating part 56, with respect to an outflow opening 511 of the first fluid guide 51. Via the outflow opening 521 of the second fluid guide 52, the oil passes via a duct portion 560B, which is open towards the first, static part 55, to the second supply line 5B. A seal at the transition between the outflow opening 521 of the second fluid guide 52 and the duct portion 560B of the second supply line 5B is realized here likewise by means of two seals 50b, 50c, for example each in the form of sealing rings. Here, a seal 50b is consequently provided axially between the outflow openings 511 and 521 of the first and second fluid guides 51, 52. In principle, a construction with two central seals 50b may also be provided in order to reliably rule out leakage from one transition into the other.

[0086] Owing to the spatial separation of fluid flows to the different supply lines 5A and 5B that is realized by means of the feed device 5, it is possible in particular for oil at different temperatures to be supplied to the supply lines 5A and 5B for different regions in the planetary gear box 30. This encompasses in particular the possibility whereby relatively cool fluid is provided to the first supply line 5A for the plain bearing. Thus, during the operation of the gas turbine engine 10, a greater expansion of the planet gear 23 in relation to the bearing journal 61 of the plain bearing is intentionally allowed in order to provide a larger fluid gap at the plain bearing for a more stable lubricating (plain bearing) film. The proposed solution is however self-evidently not restricted to this. The independence of the fluid flow in the feed device 5 for the two supply lines 5A and 5B (or other supply lines) may self-evidently also be utilized in some other way.

[0087] FIG. 3 shows, in an exploded illustration, a structural design of the feed device 5 corresponding to FIGS. 1 and 2 with further details. Here, the feed device 5 is of multi-part form and, aside from a housing part 5.1, on which the first and second feed openings 510 and 520 are provided, comprises a distributor component 5.2 and a guide duct component 5.3. The distributor component is configured as a distributor pipe 5.2, which is at least partially received in the sleeve-shaped housing part 5.1 of the feed device 5. The guide duct component is in turn configured as an internally situated transfer pipe piece 5.3, which is received in the distributor pipe 5.2.

[0088] Via a feed opening 510 or 520, which is accessible radially from the outside, of the housing part 5.1, fluid—in this case oil—can flow into a distributor duct which is formed, for a respective fluid guide 51, 52 of the feed device 5, between an inner lateral surface of the housing part 5.1 and an outer lateral surface of the distributor pipe 5.2 and is sealed off axially to both sides. Fluid flowing in via a feed opening 510 or 520 can thus flow into the respective circumferentially encircling distributor duct. Via distributor openings 510A or 520A in the distributor pipe 5.2, the fluid can then flow in targeted fashion out of the respective distributor duct into guide ducts 511 and 512, which are formed on the inner transfer pipe piece 5.3.

[0089] The guide ducts 512 and 522 that are assigned to the different fluid guides 51 and 52 are (depending on which fluid guide 51 or 52 they are assigned to) formed over different lengths on an outer lateral surface of the inner transfer pipe piece 5.3. Thus, in the respective guide duct 512, 522, the fluid can flow over a defined flow path along an outer lateral surface of the inner transfer pipe piece 5.3. A fluid flow from one distributor duct is thus divided up into a multiplicity of partial fluid flows in guide ducts 512 or 522. A first type of fluid duct 512 is always only part of the first fluid guide 51 and thus assigned only to exactly one of the two distributor ducts. Likewise, a second type of fluid duct 522 is only part of the second fluid guide 52 and thus assigned to the other distributor duct.

[0090] The different types of fluid ducts are in the present case arranged so as to be distributed, in alternation with one another, over the outer circumference of the inner transfer pipe piece 5.3. Outflow openings 511 and 521 are additionally formed on the distributor pipe 5.2 downstream of the distributor openings 510A and 520A in relation to the respective partial fluid flow in a guide duct 512, 522. Here, a first set of outflow openings 511 opens into a duct, which is designed in the manner of a circumferential channel, on the distributor pipe 5.2, whilst a further duct is formed axially offset with respect to this on the distributor pipe 5.2, into which further duct a second set of outlet openings 521 opens. Owing to the different lengths of the guide ducts 512, 522, the outflow openings 511 are assigned to the guide ducts 512 of the first fluid guide 51, whilst the outflow openings 521, which are respectively axially offset with respect thereto, are assigned to the fluid ducts 522 of the second fluid guide 52. The outflow openings 511 and 521 of the different fluid guides 51 and 52 are furthermore offset with respect to one another in a circumferential direction on the distributor pipe 5.2, such that each guide duct 512 or 522 is assigned exactly one outflow opening 511 or 521 in the distributor pipe 5.2, and accordingly, a partial fluid flow from the respective guide duct 512 or 522 can flow radially outward only via the associated outflow opening 511 or 521 and then onward via the latter to the respectively associated duct portion 560A or 560B of the first or second supply line 5A, 5B.

[0091] In the design variant illustrated in FIG. 3, the distributor pipe 5.2 has exactly six distributor openings 510A or 520A for each fluid guide 51, 52, which distributor openings are arranged so as to be distributed uniformly over the circumference of the distributor pipe 5.2 in the respective distributor duct. In turn, only exactly one feed opening 510 or 520 is provided for each fluid guide 51 or 52 on the housing 5.1.

[0092] Instead of a multi-part feed device 5 with a housing part 5.1 and a distributor pipe 5.2 for dividing up the different fluid flows into a multiplicity of partial fluid flows in the direction of an associated first or second supply line 5A, 5B, the design variant of FIGS. 4A, 4B and 5 provides a single-piece form of the feed device 5 with a guide duct component 5.3* which incorporates not only the guide ducts 512 and 522 for the first and second fluid guides 51 and 52 but also the feed openings 510, 520 and the outflow openings 511, 521.

[0093] The guide duct component 5.3* illustrated in FIGS. 4A, 4B and 5 may be a component manufactured by additive processes. By means of an additive manufacturing process, it is for example also readily possible to form the feed openings 510 and 520 for the different fluid guides 51 and 52 without an axial offset with respect to one another on the guide duct component 5.3*. Here, a first feed opening 510 of the first fluid guide 51 is thus arranged so as to be offset with respect to a second feed opening 520 of the second fluid guide 52 only in a circumferential direction U (about the rotation axis of the second, rotating part 56), whereby the guide duct component 5.3* is made shorter in an axial direction. An offset may for example be 90°, correspondingly to the cross-sectional view in FIG. 5, such that two diametrically mutually oppositely situated first feed openings 510 to guide ducts 512 of a first fluid guide and two diametrically mutually oppositely situated second feed openings 520 to a respective guide duct 522 of a second fluid guide 52 are ultimately provided on a circumference of the fluid duct component 5.3*.

[0094] The guide ducts 512 and 522, which in the present case each extend over a circular ring segment in cross section, of a guide duct component 5.3* open in each case into an associated outflow opening 511 or 521. The outflow openings 511 and 521 are again arranged axially offset with respect to one another. Accordingly, in this design variant, too, the guide ducts 512, 522 are of different lengths in an axial direction in a manner dependent on whether the respective guide duct is a (first) guide duct 512 of the first fluid guide 51 or a (second) guide duct 522 of the second fluid guide 52.

[0095] The guide duct component 5.3*, manufactured by additive processes, of FIGS. 4A, 4B and 5 furthermore also incorporates circumferentially encircling grooves 500a, 500b and 500c, which are provided for the seals 50a, 50b and 50c. The seals 50a, 50b and 50c of the design variants of FIGS. 1, 2 and 3 are also received in corresponding grooves. These are however not illustrated in detail in FIGS. 1, 2 and 3.

[0096] By means of the different fluid guides 51 and 52 that are fluidically connected to different supply lines 5A and 5B for different regions of the planetary gear box 30, it is possible for specifically adapted fluid flows, in particular fluid flows that differ from one another in terms of their temperature, to be established at the respective region, which is to be lubricated and/or cooled, of the planetary gear box 30. This allows not only a flexibilization with regard to the conveyance of oil within the planetary gear box 30 but also a reduction in weight of the gear box assembly, because, in the event of doubt, it is also possible at least for one region to allow a higher temperature of the oil that is to be conveyed, which in turn allows the use of a smaller and therefore more lightweight oil cooler.

[0097] It is self-evident that the invention is not limited to the embodiments described above, and various modifications and improvements can be made without departing from the concepts described herein. Any of the features may be used separately or in combination with any other features, unless they are mutually exclusive, and the disclosure extends to and includes all combinations and subcombinations of one or more features that are described herein.

LIST OF REFERENCE DESIGNATIONS

[0098] 9 Main rotation axis [0099] 10 Gas turbine engine [0100] 11 Core engine [0101] 12 Air inlet [0102] 14 Low-pressure compressor [0103] 15 High-pressure compressor [0104] 16 Combustion device [0105] 17 High-pressure turbine [0106] 18 Bypass thrust nozzle [0107] 19 Low-pressure turbine [0108] 20 Core thrust nozzle [0109] 21 Engine nacelle [0110] 22 Bypass duct [0111] 23 Fan [0112] 24 Stationary support structure [0113] 26 Shaft [0114] 27 Connecting shaft [0115] 28 Sun gear [0116] 30 (Planetary) gear box [0117] 32 Planet gears [0118] 325 Nozzle holder [0119] 34 Planet carrier [0120] 36 Linkage [0121] 38 Ring gear [0122] 40 Linkage [0123] 5 Feed device [0124] 5A, 5B First/second supply line [0125] 50a, 50b, 50c Seal [0126] 500a/b/c Groove [0127] 51 First fluid guide [0128] 510 Feed opening [0129] 510a Distributor opening [0130] 511 Outflow opening [0131] 512 Guide duct [0132] 52 Second fluid guide [0133] 520 Feed opening [0134] 520a Distributor opening [0135] 521 Outflow opening [0136] 522 Guide duct [0137] 55 Static part [0138] 56 Rotating part [0139] 560A/B Duct portion [0140] 5.1 Housing part [0141] 5.2 Distributor pipe (distributor component) [0142] 5.3 Inner transfer pipe piece (guide duct component) [0143] 5.3* Guide duct component manufactured by additive processes [0144] 60 Drive shaft [0145] 61 Journal for planet gear [0146] A Core air flow [0147] B Bypass air flow