TURBOFAN ENGINE AND A METHOD FOR EXHAUSTING BREATHER AIR OF AN OIL SEPARATOR IN A TURBOFAN ENGINE

Abstract

A turbofan engine that comprises a primary flow channel inside of which a primary flow flows through a gas generator during operation, a secondary flow channel inside of which a secondary flow is guided past the gas generator during operation, and an oil separator of a lube oil system that has a pipeline for exhausting breather air, wherein the pipeline forms a pipeline end. It is provided that the pipeline end is arranged inside the secondary flow channel, and is provided and configured for the purpose of discharging breather air directly from the pipeline end into the secondary flow channel.

Claims

1. Turbofan engine, comprising: a primary flow channel inside of which a primary flow flows through a gas generator during operation; a secondary flow channel inside of which a secondary flow is guided past the gas generator during operation, and an oil separator of a lube oil system that has a pipeline for discharging breather air, wherein the pipeline forms a pipeline end, and wherein the pipeline end is arranged inside the secondary flow channel and is provided and configured for the purpose of discharging breather air directly from the pipeline end into the secondary flow channel.

2. Turbofan engine according to claim 1, wherein the pipeline end is formed at an end section of the pipeline that extends in parallel to the flow direction inside the secondary flow channel.

3. Turbofan engine according to claim 2, wherein the end section has a length that is at least equal to the internal diameter of the pipeline end, in particular equal to five times the internal diameter of the pipeline end.

4. Turbofan engine according to claim 1, wherein the turbofan engine has a mixer that performs an intermixing of the primary flow and the secondary flow, wherein the pipeline end is placed inside the secondary flow channel in such a manner that at least a part of the breather air that is discharged from the pipeline end is supplied to the mixer.

5. Turbofan engine according to claim 4, wherein the pipeline end is placed in such a manner inside the secondary flow channel that at least 30%, in particular at least 50%, in particular at least 70%, of the breather air that is discharged from the pipeline end is supplied to the mixer and is mixed inside the same with the air of the primary flow channel.

6. Turbofan engine according to claim 1, wherein the secondary flow channel has an inner wall and an outer wall between which the secondary flow channel is formed as an annular space, wherein the pipeline end is arranged closer to the inner wall.

7. Turbofan engine according to claim 6, wherein the pipeline end has a distance from the inner wall which is at least equal to the internal diameter of the pipeline end.

8. Turbofan engine according to claim 1, wherein the pipeline end is placed in a location inside the secondary flow channel, behind which no structures are present inside the secondary flow channel in the flow direction.

9. Turbofan engine according to claim 1, wherein the pipeline end is placed in a location inside the secondary flow channel, behind which no openings for bleed air are present in the secondary flow channel in the flow direction.

10. Turbofan engine according to claim 1, wherein the pipeline end is arranged inside the secondary flow channel in the rear 20%, in particular in the rear 10%, of the axial length of the same.

11. Turbofan engine according to claim 1, wherein the pipeline of the oil separator extends at least partially inside a structure that is arranged inside the secondary flow channel, wherein the pipeline end protrudes from the axially rear end of the structure in the flow direction.

12. Turbofan engine according to claim 11, wherein a strut is arranged as the structure inside the secondary flow channel, extending in the radial direction inside the secondary flow channel, wherein the pipeline is arranged at least partially inside the strut and the pipeline end protrudes from the axially rear end of the strut in the flow direction.

13. Turbofan engine according to claim 1, wherein the pipeline is configured without pipe loops between the oil separator and the pipeline end, and in that it extends in such a manner that it has an upward slope towards the pipeline end if the turbofan engine is arranged at the wing of an airplane.

14. Turbofan engine, comprising: a primary flow channel inside of which a primary flow flows through a gas generator during operation; a secondary flow channel inside of which a secondary flow is guided past the gas generator during operation, and an oil separator of a lube oil system that has a pipeline for discharging breather air, wherein the pipeline forms a pipeline end, wherein the pipeline end is arranged inside the secondary flow channel and is provided and configured for the purpose of discharging breather air directly from the pipeline end into the secondary flow channel, the pipeline end is formed at an end section of the pipeline that extends in parallel to the flow direction inside the secondary flow channel, and the pipeline end is arranged inside the secondary flow channel in the rear 20% of the axial length of the same.

15. Method for exhausting breather air of an oil separator in a turbofan engine, wherein the breather air is exhausted by means of a pipeline of the oil separator that comprises a pipeline end, wherein the breather air is exhausted by means of the pipeline directly into the secondary flow channel of the turbofan engine, wherein the pipeline end is arranged inside the secondary flow channel and the breather air is exhausted from the same directly into the secondary flow channel, and wherein the breather air is blown off into the secondary flow channel in the rear 20% of the axial length of the same.

16. Method according to claim 15, wherein, before being exhausted, the breather air is transported in an end section of the pipeline which is arranged inside the secondary flow channel and extends inside the same in parallel to the flow direction, and in that it is subsequently exhausted substantially in parallel to the flow direction.

17. Method according to claim 15, wherein the breather air is exhausted into the secondary flow channel closer to the inner wall of the secondary flow channel.

18. Method according to claim 15, wherein the breather air is exhausted into the secondary flow in front of a mixer, which performs an intermixing of the primary flow and the secondary flow, namely in such a manner that a part of the exhausted breather air is supplied to the mixer and a part of the exhausted breather air is guided past the mixer.

19. Method according to claim 15, wherein the breather air is blown off into the secondary flow channel in the rear 10% of the axial length of the same.

20. Method according to claim 15, wherein the pipeline of the oil separator extends at least partially inside a structure that is integrated inside the secondary flow channel, wherein the pipeline end protrudes from the axially rear end of the structure in flow direction and exhausts breather air at an axial distance from the structure.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The invention will be explained in more detail on the basis of exemplary embodiments with reference to the accompanying drawings in which:

[0028] FIG. 1 shows a simplified schematic sectional view of a turbofan engine, wherein the turbofan engine comprises an auxiliary device carrier that is arranged at a fan housing and has an oil separator;

[0029] FIG. 2 shows a turbofan engine corresponding to FIG. 1, wherein the auxiliary device carrier with the oil separator is arranged at the outer casing of the core engine;

[0030] FIG. 3 shows a turbofan engine according to FIG. 1 according to the state of the art, wherein an air discharge line of the oil separator ends at the outer circumference of the engine nacelle;

[0031] FIG. 4 shows an exemplary embodiment of a turbofan engine, in which the air discharge line of an oil separator that is arranged at the fan housing ends inside the secondary flow channel;

[0032] FIG. 5 shows an exemplary embodiment of a turbofan engine, in which the air discharge line of an oil separator that is arranged at the outer casing of the core engine ends inside the secondary flow channel;

[0033] FIG. 6 shows another exemplary embodiment of a turbofan engine, in which the air discharge line of an oil separator that is arranged at the fan housing ends shortly in front of the mixer inside the secondary flow channel;

[0034] FIG. 7 shows another exemplary embodiment of a turbofan engine, in which the air discharge line of an oil separator that is arranged at the outer casing of the core engine ends shortly in front of the mixer inside the secondary flow channel;

[0035] FIG. 8 shows a perspective view of the outer casing of a core engine, including the rendering of a strut that extends in the radial direction inside the secondary flow channel (not shown) and that accommodates a section of the air discharge line of an oil separator;

[0036] FIG. 9 shows a first detailed view of the arrangement of FIG. 8;

[0037] FIG. 10 shows a second detailed view of the arrangement of FIG. 8; and

[0038] FIG. 11 schematically shows the arrangement of the end section of an air discharge line of an oil separator inside the secondary flow channel of a turbofan engine.

DETAILED DESCRIPTION

[0039] FIGS. 1 and 2 show, in a schematic manner, a turbofan engine 100 that has a fan stage with a fan 10 as the low-pressure compressor, a high-pressure compressor 30, a combustion chamber 40, a high-pressure turbine 50, and a low-pressure turbine 70.

[0040] The turbofan engine 100 comprises two separate shafts, a low-pressure shaft 81 that connects the low-pressure turbine 70 to the fan 10, and a high-pressure shaft 83 that connects the high-pressure turbine 50 to the high-pressure compressor 30. If the turbofan engine additionally has a medium-pressure compressor and a medium-pressure turbine, also a low-pressure shaft is present that connects the medium-pressure turbine to the medium-pressure compressor.

[0041] The turbofan engine 100 has an engine nacelle 1 that forms an engine inlet 11 at the entrance side which supplies inflowing air to the fan 10. The fan 10 has a plurality of fan blades 101 that are connected to a fan disc 102. Here, the annulus of the fan disc 102 forms the radially inner delimitation of the flow path through the fan 10. Radially outside, the flow path is delimited by a fan housing 2. A nose cone is arranged upstream of the fan disc 102.

[0042] Behind the fan 10, the turbofan engine 100 forms a secondary flow channel 4 and a primary flow channel 5. The intake air is split behind the fan 10 by means of a splitter 55 into a secondary flow, which flows through the secondary flow channel 4, and a primary flow, which flows through the primary flow channel. The primary flow channel 5 leads through the core engine which comprises the gas turbine that is formed by the high-pressure compressor 30, the combustion chamber 40, the high-pressure turbine 50. The primary flow channel 5 is surrounded by a circumferential housing 60 which forms an annulus surface at the internal side, delimitating the primary flow channel 5 radially outside. Radially inside, the primary flow channel 5 is delimitated by corresponding rim surfaces of the rotors and the stators of the respective compressor stages, or by the hub, or by the elements of the corresponding drive shaft connected to the hub.

[0043] During operation of the turbofan engine 100, a primary flow flows through the primary flow channel 5 with the gas generator 30, 40, 50. The secondary flow channel 4, which is also referred to as the bypass flow channel, sheath flow channel or bypass channel, guides the air that is suctioned in by the fan 10 during operation of the turbofan engine 100 past the gas turbine 30, 40, 50.

[0044] The described components have a common symmetry axis 90. The symmetry axis 90 defines an axial direction of the turbofan engine. A radial direction of the turbofan engine extends perpendicularly to the axial direction.

[0045] The engine 100 further comprises an auxiliary device carrier 17 that drives a plurality of auxiliary devices via a main shaft. Among other components, an oil separator 20 is driven as an auxiliary device. The auxiliary device carrier 17 is coupled to a low-pressure shaft 81 via a radial shaft 16 and an angular gear 15. Alternatively, it can be provided that the auxiliary device carrier 17 is coupled to the high-pressure shaft 81 via a radial shaft and an angular gear. In FIG. 1, the auxiliary device carrier 17 with the oil separator 20 is arranged at the exterior side of the fan housing 2. In FIG. 2, it is alternatively provided that the auxiliary device carrier 17 with the oil separator 20 is arranged at the outer casing of the core engine, for example at the circumferential housing 60 or at a structure connected therewith.

[0046] The oil separator 20 fulfills the function of separating the lube oil of the engine lube oil system from the compressed air. It may for example be a centrifugal oil separator. Separated oil is supplied from an oil separator 20 to an oil tank (not shown), so that it remains inside the oil circuit of the engine lube oil system. The remaining compressed air, from which the lube oil has been separated, is blown off via an air discharge line of the oil separator 20.

[0047] In the context of the present invention, the design of such an air discharge line and the placement of the end of the air discharge line inside the engine are of particular importance, as will be described in the following.

[0048] Before the present invention is discussed in more detail, the design of an air discharge line according to the state of the art is explained based on FIG. 3 in order to provide a better understanding of the background of the invention. According to FIG. 3 it is provided that an air discharge line 21′ that is connected to the oil separator 20 is guided to the outer casing or the fairing of the engine nacelle 1. The breather air 25 that is contained in the air discharge line 21′ contains a share of residual oil. The blowing off of the breather air at the engine cowling leads to the latter being stained, which is undesirable due to esthetic reasons.

[0049] FIG. 4 shows, in a schematic manner, an exemplary embodiment of the invention. Via a main shaft (not shown), an auxiliary device carrier 17 drives an oil separator 20, among other components. In the oil separator 20, lube oil is separated from compressed air. The oil separator 20 has an air discharge line 21 which is a pipeline for discharging the breather air of the oil separator 20, and which contains a mixture of warm air and a share of residual oil. The compressed air that is separated in the oil separator 20 and blown off via the air discharge line 21 is also referred to as breather air. The air discharge line 21 can be embodied in a flexible or rigid manner, and can in principle be made of any material that is resistant against the present temperatures. It can for example be a metal pipe. It may at least in sections have a constant diameter. The air discharge line 21 will also be referred to as a pipeline in the following.

[0050] The pipeline 21 has a pipeline end 22 that is arranged inside the secondary flow channel 4 of the turbofan engine 100 and that exhausts or blows off breather air into the secondary flow channel 4 directly, i.e. without the breather air passing further components behind the pipeline end 22, such as for example another oil separator device or an oil collecting device. Breather air that is discharged from the pipeline end 22 is discharged from the pipeline end 22 directly into the secondary flow channel 4.

[0051] In FIG. 4, the auxiliary device carrier 17 with the oil separator 20 is arranged according to FIG. 1 at the exterior side of the fan housing 2. The direct discharge of breather air into the secondary flow channel 4 as it is provided according to the present invention can also be provided if the auxiliary device carrier 17 with the oil separator 20 is arranged at the circumferential housing 60 or at the outer casing of the core engine according to FIG. 2. FIG. 5 shows a pipeline 21 in such an arrangement, which is guided from the oil separator 20 into the secondary flow channel 4 and the end 22 of which is arranged inside the secondary flow channel 4 in order to blow off breather air contaminated with oil directly into the secondary flow channel 4.

[0052] FIGS. 4 and 5 further show a structure 41 that is arranged inside the secondary flow channel 4 and that extends in the radial direction between the inner wall 42 and the outer wall 43 of the secondary flow channel 4 while having a small extension in the circumferential direction as well as a certain axial extension. The structure 41 can for example be a strut (also referred to as a splitter) that serves for radially passing of engine instrumentations and lines for compressed air, fuel or oil, for example. The pipeline end 22 is arranged—with respect to the flow direction—behind the structure 41 inside the secondary flow channel 4.

[0053] In the embodiment of FIG. 4, the pipeline 21 is guided to the secondary flow channel 4 from the outside. In the embodiment of FIG. 5, the pipeline 21 is guided to the secondary flow channel 4 from the inside.

[0054] It is to be understood that the rendering of the pipeline 21 in FIGS. 4 and 5, and also in FIGS. 6 and 7 that will be explained in the following, represents merely a schematic illustration. In particular, it can be provided in contrast to the renderings in these FIGs. that the pipeline 21 is realized without any kink points, and that the pipeline end 22 is formed at an end section of the pipeline 21 which is not slanted but instead projects into the secondary flow channel 4 in flow direction, as will be described in the following.

[0055] FIG. 6 shows an exemplary embodiment that differs from the exemplary embodiment of FIG. 4 in that the pipeline end 22 ends at a short distance in front of a mixer 45 inside the secondary flow channel 4, which performs an intermixing of the primary flow and the secondary flow of the turbofan engine 100. At that, the pipeline end 22 ends adjoining the inner wall 42, but at a defined distance from the same.

[0056] FIG. 7 shows an exemplary embodiment that differs from the exemplary embodiment of FIG. 5 in that the pipeline end 22 ends at a small distance in front of a mixer 45 inside the secondary flow channel 4. The pipeline end 22 also ends adjoining the inner wall 42, but at a defined distance from the same.

[0057] As for the exemplary embodiments of FIGS. 4 to 7, the pipeline end 22 is placed in such a manner inside the secondary flow channel 4 that no further structures or openings (for example for bleed air) are present in the secondary flow channel 4 behind the pipeline end 22, so that the breather air that is blown into the secondary flow channel 4 has no or only minor turbulences.

[0058] Further it applies to all exemplary embodiments of FIGS. 4 to 7 that the pipeline end 22 is arranged inside the secondary flow channel 4 in the rear 20%, in particular in the rear 10%, of the axial length of the same. If thus the axial expansion of the secondary flow channel 4 between the fan 10 and the mixer 45 is regarded, the pipeline end 22 is arranged at a location inside the secondary flow channel 4 that lies in the 20% or the 10% of the axial extension of the secondary flow channel 4, which are formed in front of the mixer 45. At that, the axial distance of the pipeline end 22 to the mixer 45 is greater in the exemplary embodiments of FIGS. 4 and 5 than in the exemplary embodiments of FIGS. 6 and 7. In the exemplary embodiments of FIGS. 6 and 7, it lies in the rear 10%, in particular in the rear 5%, of the axial length of the secondary flow channel 4, for example.

[0059] Further, it also applies to FIGS. 6 and 7 that the pipeline end 22 is arranged at an axial distance to the axially rear end of the strut 41 in flow direction.

[0060] FIG. 8 shows, in a perspective view, the outer contours of the engine structures that encase the core engine. As far as the secondary flow channel is concerned, only a ring-shaped support structure 19 is shown that structurally supports the fan housing and that may comprise guide vanes, as well as a strut 41 is shown that extends in the radial direction between the inner wall and the outer wall of the secondary flow channel, for example serving for the radial passing of engine instrumentations and pipelines for compressed air, fuel or oil through the secondary flow channel. Further, a mixer 45 is shown that mixes the primary flow of the primary flow channel and the secondary flow of the secondary flow channel at the engine exit. The strut 41 extends downstream of the ring-shaped support structure 19 in an area between the support structure 19 and the mixer 45.

[0061] As can also be seen from FIGS. 9 and 10, which are detailed illustrations of FIG. 8, the pipeline 21 at least partially extends inside the strut 41. Thus, the pipeline 21 forms a first rear section 24 in front of the pipeline end 22 and a second rear section 23 connecting thereto, wherein the second rear section 23 forms the pipeline end 22. The first rear section 24 and the second rear section 23 extend in a rectangular manner with respect to each other. Here, the first rear section 24 is arranged inside the strut 41. The second rear section 22 partially extends inside the strut 41, but protrudes with respect to the same in flow direction, so that the pipeline end 22 is positioned freely, without any surrounding structures, inside the secondary flow channel 4.

[0062] FIG. 11 illustrates, in a schematic manner, the arrangement of the pipeline end 22 of a pipeline 21 for exhausting breather air of an oil separator in the secondary flow channel 4. The pipeline 21 comprises an end section 23 that forms the pipeline end 22.

[0063] The primary flow channel 5 and the secondary flow channel 4 are schematically shown as having a primary flow 54 and a secondary flow 44. The primary flow 54 and the secondary flow 44 are intermixed at the engine exit inside a mixer 45. The secondary flow channel 4 comprises an inner wall 42 and an outer wall 43.

[0064] The end section 23 of the pipeline 21 extends across a length d4 in the direction of the secondary flow 44. For this purpose, the end section 23 is configured in a straight manner and is aligned in such a manner that it extends at least approximately on a meridional line, i.e. on the line the points of which have the same spacing ratio to the inner wall 42 and the outer wall 43 of the secondary flow channel 4. By guiding the breather air inside the end section 23 it is achieved that the breather air that is guided inside the pipeline 21 is already aligned in parallel to the flow direction before being blown off into the flow 44. In this manner, any turbulences in the breather air, which is identified by the number 25 in FIG. 11, is avoided or minimized. According to an exemplary embodiment, the length d4 amounts to five times the internal diameter of the circular pipeline end 22.

[0065] FIG. 11 further shows a minimum distance d1 and a maximum distance d2 that the pipeline end 22 has from the inner wall 42. The minimum distance d1 can for example be equal to the internal diameter of the pipeline end 22. The maximum distance d2 can be designed in such a manner that the pipeline end 22 is arranged closer to the inner wall 42 than to the outer wall 43 of the secondary flow channel 4. Thus, it is provided in one embodiment of the invention that the pipeline end 22 is located closer to the inner wall 42. In this manner, it is ensured that a portion of the breather air 25 is supplied to the mixer 45 and is distributed by the same. For example, the maximum distance can be ten times, five times or ten times the internal diameter of the pipeline end 22.

[0066] FIG. 11 also shows a minimum distance d3 of the pipeline end 22 to the outer wall 43. This minimum distance d3 can also be equal to the internal diameter of the circular pipeline end 22, for example.

[0067] Due to its parallel alignment with respect to the flow 44, the breather air 25 that is blown off from the pipeline end 22 is blown off substantially without any turbulences. Thus, the breather air 25 flows substantially in parallel to the secondary flow 44, as shown in FIG. 11. If the pipeline end 22 is arranged in a suitable manner adjacent to the inner wall 42, a part 25-1 of the breather air 25 is supplied to the mixer 45, while another part 25-2 of the breather air is guided past the mixer 45 and does not participate in the mixing procedure. In this manner, a maximally large outlet area for the breather air 25 and thus a maximal degree of dilution of the contained oil particles can be achieved.

[0068] Depending on the placement of the pipeline end 22 in the secondary flow channel 4 it can be achieved that the breather air 25 is supplied to the mixer 45 in its entirety, partially or not at all.

[0069] Usually, the secondary flow 44 has a higher flow velocity than the breather air 25. Thus, a minor suction effect is present, sucking breather air 25 from the pipeline end 22.

[0070] The present invention is not limited in its embodiment to the above-described exemplary embodiments, that are to be understood merely as examples. For instance, the shape and the arrangement of the pipeline for discharging breather air are to be understood to be merely as examples.

[0071] It is furthermore pointed out that the features of the individually described exemplary embodiments of the invention can be combined in various combinations with one another. Where areas are defined, they include all the values within these areas and all the sub-areas falling within an area.