APPARATUS FOR OIL LUBRICATION OF A ROTATIONALLY FIXED CONNECTION BETWEEN TWO SHAFTS

Abstract

An apparatus for oil lubrication of a rotationally fixed connection between two shafts. A first shaft engages with a hollow region of the second shaft. The shafts are operatively connected to each other in a form-fitting manner in the overlapping region. Oil is introduced into a first chamber in the hollow region, which chamber is connected to a second chamber in the hollow region. The second chamber is connectable to a third chamber is arranged in the overlapping region. The fluidic connection between the second chamber and the third chamber is separated above a defined oil volume in the second chamber and above a rotational speed threshold of the shafts via a sealing element. The sealing element is reversibly deformable by the oil volume in the second chamber and the centrifugal force acting thereon and, in the deformed state, seals the connection between the second and third chambers.

Claims

1. An apparatus for oil lubrication of a rotationally fixed connection between two shafts, wherein a first shaft engages with a shaft region in a hollow-cylindrical shaft region of the second shaft, and the shafts are operatively connected to each other in a form-fitting manner in the overlapping region, wherein oil can be introduced in the axial direction through a central opening into a first chamber in the hollow-cylindrical region of the first shaft, which chamber is fluidically connected to a second chamber in the hollow-cylindrical region of the second shaft, wherein the second chamber is fluidically connectable to a third chamber, wherein the third chamber is arranged in the overlapping region between the first shaft and the second shaft, wherein the fluidic connection between the second chamber and the third chamber is separated above a defined oil volume in the second chamber and above a rotational speed threshold of the shafts via a sealing element which is reversibly deformable at least in regions by the oil volume in the second chamber and the centrifugal force acting thereon and, in the deformed state, seals the connection between the second chamber and the third chamber in relation to the second chamber.

2. The device according to claim 1, wherein the inside diameter of the central opening, the outside diameter of the first chamber, the outside diameter of the second chamber and the connections between the chambers are coordinated with one another in such a manner that, above the rotational speed threshold of the shafts, a defined oil level in each case arises in the first chamber and in the second chamber, and the sealing element is reversibly deformed at least in regions by the oil volume in the second chamber and the centrifugal force acting thereon and seals the connection between the second chamber and the third chamber.

3. The device according to claim 1, wherein the sealing element has an annular disk region which projects radially inwards into the second chamber and on which the oil volume present in the second chamber is supported in the axial direction, wherein at least one free inner edge region of the annular disk region is pressed by the oil volume in the second chamber in the axial direction against a free shaft end of the first shaft or against a boundary wall of the hollow-cylindrical region, said boundary wall bounding the second chamber and the third chamber, and seals the connection between the second chamber and third chamber if an oil volume above the defined oil volume is present in the second chamber and the rotational speed of the shafts is greater than the rotational speed threshold.

4. The device according to claim 3, wherein the inner edge region of the annular disk region of the sealing element is formed on the side facing the shaft end of the first shaft with a sealing bead which extends in the circumferential direction of the sealing element.

5. The device according to claim 1, wherein the connection between the first chamber and the second chamber comprises at least one passage opening, wherein the passage opening runs from the outside diameter of the first chamber in the direction of the second chamber or in the radial direction between the outside diameter of the first chamber and the inside diameter of the central opening in the direction of the second chamber.

6. The device according to claim 5, wherein the passage opening is provided in a radial wall region which separates the first chamber from the second chamber in the axial direction of the shafts.

7. The device according to claim 6, wherein the radial wall region is formed with a preferably central opening in the radial direction of the shafts, the central opening connecting the first chamber and the second chamber.

8. The device according to claim 1, wherein the inside diameter of the annular disk region of the sealing element at least approximately corresponds to the inside diameter of the central opening of the first chamber and is preferably smaller than the inside diameter of the central opening.

9. The device according to claim 1, wherein the chambers are bounded at least by a hollow-cylindrical component which is arranged in the hollow-cylindrical region of the second shaft and is connected fixedly to the second shaft and is preferably rotationally symmetrical.

10. The device according to claim 9, wherein the sealing element is formed integrally with the hollow-cylindrical component.

11. The device according to claim 1, wherein the sealing element lies in the axial direction on an annular contact surface of an axial step of the second shaft, wherein the contact surface of the step is spaced apart in the axial direction from the shaft end of the first shaft, and wherein the inside diameter of the contact surface is greater than the inside diameter of the annular disk region of the sealing element.

12. The device according to claim 1, wherein the sealing element comprises at least one flat sealing disk region which is arranged between an end face of the hollow-cylindrical component and the contact surface of the step.

13. The device according to claim 1, wherein the sealing element is arranged with a radial outer region in an inner groove of the hollow-cylindrical component and is connected fixedly to the hollow-cylindrical component.

14. The device according to claim 1, wherein the hollow-cylindrical component is designed in two parts, wherein the parts of the hollow-cylindrical component are arranged in the hollow-cylindrical region of the second shaft in a manner spaced apart from each other in the axial direction of the shafts, and, between the parts of the hollow-cylindrical component, the second chamber is bounded by the parts.

15. The device according to claim 1, wherein the sealing element is supported with a radially outer region on the second shaft, with an axial region on the shaft end of the first shaft, and with a further axial region on the hollow-cylindrical component, wherein the annular disk region of the sealing element can be placed by the oil volume in the second chamber against the shaft end of the first shaft in a sealing manner and separates a connection between the second chamber and the third chamber, which connection runs through the axial region of the sealing element.

Description

[0037] In the figures:

[0038] FIG. 1a shows a highly schematized longitudinal sectional view of a gas turbine engine with an auxiliary unit gearbox arranged in the blower housing;

[0039] FIG. 1b shows an illustration, corresponding to FIG. 1a, of a gas turbine engine with an auxiliary unit gearbox mounted in the region of the engine core;

[0040] FIG. 2 shows a partial longitudinal sectional view in the region of the auxiliary unit gearbox according to FIG. 1a and FIG. 1b, in which there is a rotationally fixed connection between a drive shaft of the auxiliary unit gearbox and a drive shaft of an auxiliary unit, wherein the gas turbine engine is in the switched-on operating state;

[0041] FIG. 3 shows an enlarged view of a region III, indicated specifically in FIG. 2;

[0042] FIG. 4 shows an illustration, corresponding to FIG. 2, of the region of the auxiliary unit gearbox in the switched-off state of the gas turbine engine during a discharge operating state of the gas turbine engine;

[0043] FIG. 5 shows an illustration, corresponding to FIG. 3, of the region Ill in the operating state of the gas turbine engine, on which the illustration according to FIG. 4 is based;

[0044] FIG. 6 shows an illustration, corresponding to FIG. 2, of the auxiliary unit gearbox in an operating state which the auxiliary unit gearbox is in after renewed starting of the gas turbine engine;

[0045] FIG. 7 shows an illustration, corresponding to FIG. 3, of the region Ill in an operating state of the auxiliary unit gearbox, on which the illustration according to FIG. 6 is based;

[0046] FIG. 8 shows an illustration, corresponding to FIG. 2, of a further embodiment of the auxiliary unit gearbox, in which a sealing element is mounted between an oil distributor and a step of the drive shaft of the auxiliary unit gearbox;

[0047] FIG. 9 shows an enlarged illustration of a region IX, indicated specifically in FIG. 8;

[0048] FIG. 10 shows an illustration, corresponding to FIG. 2, of a further embodiment of the auxiliary unit gearbox, wherein the sealing element is arranged in an inner groove of the oil distributor;

[0049] FIG. 11 shows an enlarged view of a region XI, indicated specifically in FIG. 10;

[0050] FIG. 12 shows an illustration, corresponding to FIG. 2 of a further embodiment of the auxiliary unit gearbox;

[0051] FIG. 13 shows an enlarged view of a region XIII, indicated specifically in FIG. 12;

[0052] FIG. 14 shows an enlarged view of a further embodiment of the auxiliary unit gearbox;

[0053] FIG. 15 shows an enlarged view of a development of the embodiment, illustrated in FIG. 10, of the auxiliary unit gearbox;

[0054] FIG. 16 shows an enlarged view of a region XVI, indicated specifically in FIG. 15; and

[0055] FIG. 17 shows an illustration, corresponding to FIG. 16, of the region XVI in an operating state of the sealing element, in which a connection between a second chamber and a third chamber is opened up by the sealing element.

[0056] FIG. 1a and FIG. 1b both show a gas turbine engine 1 in a longitudinal sectional view. The gas turbine engine 1 is formed with a bypass channel 2 and an inlet region 3, wherein a blower 4 adjoins the inlet region 3 downstream in a manner known per se. Downstream of the blower 4, in turn, the fluid flow in the gas turbine engine 1 is divided into a bypass flow B and a core flow A, the bypass flow B flowing through the bypass channel 2 and the core flow A flowing into an engine core 5. The engine core 5 is designed in a manner known per se with a compressor device 6, a burner 7 and a turbine device 8. The turbine device 8 comprises a plurality of rotors 9, 10 and 11 which are configured with a substantially comparable design and are connected to an engine shaft 12.

[0057] In the embodiment of the gas turbine engine 1 according to FIG. 1a, an auxiliary unit gearbox 13 is arranged in an outer engine housing 14. The engine housing 14 bounds the bypass channel 2 and is the outer circumferential region of the gas turbine engine 1. The auxiliary unit gearbox 13 here is connected via an inner gearbox 17, via a drive shaft 15 running in the radial direction of the gas turbine engine 1, to the engine shaft 12 and is therefore driven, and supplied with torque, by the engine shaft 12 during operation of the gas turbine engine 1. Various auxiliary units 16 are acted upon to the desired extent with torque by the auxiliary unit gearbox 13. In addition, an oil tank 18 is also provided in the region of the auxiliary unit gearbox 13, the oil tank being a hydraulic fluid reservoir from which oil is extracted for cooling and lubricating various regions of the gas turbine engine 1, such as bearing devices, gearwheel pairings of the inner gearbox 17 and the auxiliary unit gearbox 13, and further assemblies of the gas turbine engine 1 that are to be cooled and to be lubricated.

[0058] In contrast thereto, the auxiliary unit gearbox 13 with the auxiliary units 16 is arranged in the radial direction between the bypass channel 2 and the engine core 5, in the case of the gas turbine engine 1 according to FIG. 1b, in a component 19 bounding both the bypass channel 2 and the engine core 5.

[0059] FIG. 2 shows a partial longitudinal sectional view of the auxiliary unit gearbox 13 and one of the auxiliary units 16. The region of the auxiliary unit gearbox 13 that is illustrated in FIG. 2 comprises an apparatus 20, shown specifically in FIG. 3, for oil lubrication of a rotationally fixed connection 21 between two shafts 22, 23. The rotationally fixed connection is designed here as a splined joint in an overlapping region 65 between the two shafts 22 and 23 and is intended, in a manner described in more detail below, to be supplied in a targeted manner with oil and lubricated, without causing an undesirable escape of oil from an interior 24 of the auxiliary unit gearbox 13 to an environment 25.

[0060] An oil feed unit 26 is provided via which oil is introduced or injected or even sprayed, depending on the application, into a hollow-cylindrical region 27 of the shaft 22, which is the drive shaft of the auxiliary unit gearbox 13. An oil divider 28 is inserted here into the hollow-cylindrical region 27 of the shaft 22, the oil divider being designed as a substantially rotationally symmetrical, hollow-cylindrical component and bounding a first chamber 29 and a second chamber 30. The oil divider 28 is formed with a central opening 31 through which oil is introduced here in the form of an oil jet by the oil feed unit 26 into the first chamber 29.

[0061] An inside diameter Di31 of the central opening 31 of the oil divider 28 or of the first chamber 29 is provided in such a manner that, during operation of the gas turbine engine 1, a defined oil volume or what is referred to as a dynamic oil level 32 arises in the first chamber 29 and in the second chamber 30 above a defined rotational speed threshold of the shafts 22 and 23. The first chamber 29 and the second chamber 30 are connected to each other via connecting passages or connecting bores 33 which lead through a radial wall region 70 between the chambers 29 and 30. Oil is introduced from the first chamber 29 via the connecting bores 33 into the second chamber 30 when the dynamic oil level 32 in the first chamber 29 reaches the radial level of the connecting bores 33. The oil volume present in each case in the chambers 29 and 30 is applied in the manner illustrated in FIG. 2, because of the centrifugal force acting on the oil volume, to the outer circumference 66 of the oil divider 28 and therefore of the chambers 29 and 30. If the dynamic oil level 32 in the first chamber 29 circumferentially exceeds an inner ring region 34 of the central opening 31, oil flows back out of the first chamber 29 into the hollow-cylindrical region 27 of the shaft 22 and is supplied, for example, for lubricating and cooling a bearing unit 35 of the shaft 22.

[0062] In the last-mentioned operating state of the apparatus 20, the oil volume present in the second chamber 30 in conjunction with the centrifugal force acting thereon has the effect that a sealing element 36, which is formed integrally with the oil divider 28 in a region facing the shaft 23, is reversibly deformed in the manner shown specifically in FIG. 3. In the deformed state, the sealing element 36 closes a connection 37 between the second chamber 30 and a third chamber 38 in a sealing manner. The sealing element 36 lies with a flat sealing disk region 67 against an axial stop 39 of the shaft 22 or against a stop surface 40. An inside diameter Di39 of the axial stop 39 here is greater than an inside diameter Di41 of an annular disk region 41, projecting radially inwards into the second chamber 30, of the sealing element 36, which region comprises the flat sealing disk region 67. A free inner edge region 42 of the sealing element 36 can therefore be pressed by the oil volume in the second chamber 30 in the axial direction against an end face 43 of a shaft end 44 of the shaft 23 since the sealing element 36 in this region is not supported in the axial direction by the axial stop 39. The annular disk region 41 is then distorted by the oil volume in the second chamber 30 and the centrifugal force acting thereon above the stop surface 40 in the direction of the shaft end 44.

[0063] The inner edge region 42 of the sealing element 36 is formed on the side facing the shaft end 44 of the shaft 23 with a sealing bead or sealing lip 45 which constitutes an enlarged material region of the sealing element 36. As large a sealing surface as possible is achieved in the circumferential direction and in the radial direction between the sealing element 36 and the shaft end 44 or the end face 43 of the shaft end 44, as is a high sealing action, by means of the sealing bead 45.

[0064] FIG. 4 shows an illustration, corresponding to FIG. 2, of the auxiliary unit gearbox 13 and of the auxiliary unit 16 during an operating state of the gas turbine engine 1 in which the gas turbine engine 1 and the auxiliary unit gearbox 13 are in after the gas turbine engine 1 is switched off and during a discharge operation of the gas turbine engine 1. In the operating state which is shown, the rotational speed of the shafts 22 and 23 is already lower than the rotational speed threshold. If the rotational speed of the shafts 22 and 23 falls below the rotational speed threshold, the oil volume present in each of the chambers 29 and 30 in each case accumulates in the lower regions of the chambers 29 and 30 in the manner shown in FIG. 4 because of the acting weight force. The what are referred to as static oil levels 46 and 47 then arise in the chambers 29 and 30.

[0065] The static oil level 46 in the first chamber 29 depends on the inside diameter Di31 of the central opening 31 through which the oil then immediately flows out of the first chamber 29 into the hollow-cylindrical region 27 of the shaft 22. The height of the static oil level 46 corresponds to the radial height from the lower region of the first chamber 29 as far as the lower edge of the central opening 31.

[0066] The static oil level 47 arises in the second chamber 30 during the discharge operation of the gas turbine engine 1 owing to the fact that the oil flows out of the second chamber 30 counter to the resistance of the oil volume present in the first chamber 29 and, given a corresponding static filling level, also via a central venting bore 48 into the first chamber 29. The oil therefore flows out of the second chamber 30 substantially more slowly than out of the first chamber 29, and therefore the static oil level 47 is higher, at least for a limited period of time, than the static oil level 46 in the first chamber 29.

[0067] During normal operation of the gas turbine engine 1, air is conducted out of the second chamber 30 into the first chamber 29 via the venting bore 48 in order to avoid an undesirable increase in pressure in the second chamber 30. Such an increase in pressure in the second chamber would otherwise prevent oil from being admitted from the first chamber 29 via the venting bore 33 into the second chamber 30 and impair the sealing action, described in more detail above, of the sealing element 36 due to too low an oil level 32 in the second chamber 30.

[0068] Owing to the decreasing rotational speed of the shafts 22, 23 and the resultant reduction in centrifugal force, the oil pressure which bears in the axial direction against the sealing element 36 also decreases. Since the sealing element 36 is designed with corresponding spring elasticity and a corresponding restoring behavior which counteracts the oil pressure in the axial direction of the shafts 22 and 23, the free inner edge region 42 of the sealing element 36 springs back under the rotational speed threshold of the shafts 22 and 23 into the position illustrated in FIG. 5. In the process, the sealing element 36 lifts off the end face 43 of the shaft end 44 of the shaft 23 and opens up the connection 37 between the second chamber 30 and the third chamber 38. In this operating state, the annular disk region 41 again has a rectilinear and substantially uncurved profile above the stop surface 40 in the radial direction of the shafts 22, 23.

[0069] As long as the static oil level 47 in the second chamber 30 lies above the lower region of the free inner edge region 42 of the sealing element 36, oil flows out of the second chamber 29 via the free inner edge region 42 and through the connection 37 into the third chamber 38. The oil passes from there to the rotationally fixed connection or to the splined joint 21 between the two shafts 22 and 23, and therefore the rotationally fixed connection 21 is supplied to the desired extent with oil and lubricated.

[0070] If the gas turbine engine 1 is put into operation again at a later time, the rotational speed of the shafts 22 and 23 increases to values above the rotational speed threshold, and the first chamber 29 and the second chamber 30 are filled again with oil by the oil feed unit 26. If the dynamic oil level 32 in the two chambers 29 and 30 reaches the level shown in FIG. 2 and FIG. 6, the sealing element 36 is pressed by the oil volume in the second chamber 30, in turn, to the extent illustrated in FIG. 7, in a sealing manner against the end face 43 of the shaft end 44 and separates the fluidic connection between the second chamber 30 and the third chamber 38. During operation of the gas turbine engine 1, oil is therefore reliably prevented by the sealing element 36 from escaping from the second chamber 30 into the third chamber 38. In addition, in the region of the splined joint or the rotationally fixed connection 21 between the shafts 22 and 23, a further seal 49 is provided which prevents oil from escaping out of the third chamber 30, in which there is now already a certain oil volume 38A, in the direction of the environment 25.

[0071] However, if the gas turbine engine 1 is switched off, the third chamber 38 is acted upon with oil to the extent illustrated specifically in FIG. 4 and FIG. 5 again via the connection 37 between the second chamber 30 and the third chamber 38 when the sealing element 36 transfers from its sealing operating state into its operating state opening up the connection 37.

[0072] FIG. 8 and FIG. 9 show a further embodiment of the apparatus 20, in which the sealing element 36 is designed as a separate component and is in the shape of an annular disk. FIG. 9 shows an enlarged view of a region IX, indicated specifically in FIG. 8. The annular-disk-shaped sealing element 36 is mounted in the axial direction between the oil distributor 28 and the axial stop 39. The apparatus 20 that can therefore be integrated in a simple manner and with little structural outlay in existing gas turbine engines or in existing auxiliary unit gearboxes and, firstly, an undesirable escape of oil from the interior 24 of the auxiliary unit gearbox 13 in the direction of the environment 25 can be avoided and, secondly, a desired oil lubrication of the rotationally fixed connection between the shafts 22 and 23 can be ensured.

[0073] Furthermore, FIG. 9 shows a comparison of the dynamic oil levels 32 and of the static oil levels 46 and 47 in the two chambers 29 and 30. Below an axis of rotation 52 of the shafts 22 and 23, the chambers 29 and 30 are shown during the normal operation of the gas turbine engine 1, during which the filling level in the chambers 29 and 30 corresponds to the dynamic oil level 32. Above the axis of rotation 52, the chambers 29 and 30 are shown during a discharge operation of the gas turbine engine 1, during which the static oil level 46 in the first chamber 29 and the static oil level 47 in the second chamber 30 arise in each case to the previously described extent. Below the axis of rotation 52, the sealing element 36 therefore bears in a sealing manner against a partition 51 of the oil divider 28. In contrast thereto, the sealing element 36 opens up the connection 37 between the second chamber 30 and the third chamber 38 in the operating state illustrated above the axis of rotation 52.

[0074] FIG. 10 shows a further embodiment of the auxiliary unit gearbox 13 and of the apparatus 20, while FIG. 11 shows an enlarged view of the region XI indicated specifically in FIG. 10. In the embodiment of the auxiliary unit gearbox 13 according to FIG. 10, the oil divider 28 comprises two parts 28A and 28B. The first part 28A of the oil divider 28, which is a rotationally symmetrical, hollow-cylindrical component, bounds the first chamber 29. The second part 28B of the oil divider 28, together with the first part 28A, bounds the second chamber 30 within the hollow-cylindrical region 27 of the shaft 22. Oil is in turn introduced from the oil feed unit 26 through the central opening 31 of the first part 28A of the oil divider 28 into the first chamber 29. In the embodiment of the apparatus 20 according to FIG. 10 and FIG. 11, the sealing element 36 is mounted with a radial outer region 68 in an inner groove 50 of the second part 28B of the oil divider 28 and connected fixedly thereto.

[0075] Oil is introduced from the first chamber 29 via the connecting bores 33, which are provided in the outer circumference 66 of the first part 28A of the oil divider 28, substantially radially outward into the second chamber 30. Over the operating period, the dynamic oil levels 32 arise in turn in the chambers 29 and 30, which are bounded by the inside diameter Di31 of the central opening 31 and correspond to each other and are shown below the axis of rotation 52 in FIG. 11. FIG. 11 illustrates, above the axis of rotation 52, the static oil level 47 which arises in the second chamber 30 during a discharge operation of the gas turbine engine 1.

[0076] The dynamic oil level 32 in the second chamber 30 has the effect, in conjunction with rotational speeds of the shafts 32 and 23 above the rotation threshold, that the sealing element 36 is pressed to the previously described extent with its free inner edge region 42 in a sealing manner against a boundary wall 51 or partition of the oil divider 28. The partition 51 separates the second chamber 30 from the third chamber 38. The connection 37 which runs through the partition 51 between the second chamber 30 and the third chamber 38 is then blocked by the sealing element 36. This is in turn brought about by the hydraulic compressive force which acts on the sealing element 36 in the axial direction and results from the oil volume located in the second chamber 30 and the centrifugal force acting thereon above the rotational speed threshold. In addition, the second part 28B of the oil divider 28 comprises radial bores 60 via which oil is conducted out of the second chamber 30 in the direction of a further bearing unit 61.

[0077] FIG. 12 shows a further embodiment of the auxiliary unit gearbox 13 and of the apparatus 20 in an illustration, corresponding to FIG. 2, in a switched-on operating state of the gas turbine engine 1 and at a rotational speed of the shafts 22, 23 above the rotational speed threshold. The dynamic oil levels 32 then arise in each of the two chambers 29 and 30.

[0078] FIG. 13 in turn illustrates a comparison of the dynamic oil levels 32 and the static oil levels 46 and 47 in the two chambers 29 and 30 in an enlarged view of a region XIII, indicated specifically in FIG. 12. Above the axis of rotation 52 of the shafts 22 and 23, the chambers 29 and 30 are filled with oil corresponding to the dynamic oil levels 32 while there is a respective oil volume corresponding to the static oil level 46 or 47 in the chambers 29 and 30 below the axis of rotation 52. Above the axis of rotation 52, the sealing element 36 therefore bears in a sealing manner against the partition 51. In contrast thereto, the sealing element 36 opens up the connection 37 between the second chamber 30 and the third chamber 38 in the operating state illustrated below the axis of rotation 52.

[0079] The oil divider 28 is in turn divided and comprises the two parts 28A and 28B, between which the second chamber 30 is provided within the hollow-cylindrical region 27 of the shaft 22. The connecting bores 33 between the first chamber 29 and the second chamber 30 run in the axial direction through the first part 28A of the oil distributor 28. The oil feed unit 26 comprises introduction openings 53 which lead radially from the outside through the shaft 22 into the hollow-cylindrical region 27 of the shaft 22. Oil can be introduced through the shaft 22 into the first chamber 29 via the introduction openings 53.

[0080] FIG. 14 shows an illustration, corresponding to FIG. 13, of a further embodiment of the auxiliary unit gearbox 13 and of the apparatus 20, which substantially corresponds to the embodiment of the auxiliary unit gearbox 13 and of the apparatus 20 shown in FIG. 12 and FIG. 13. The first part 28A bounds the second chamber 30 in the axial direction and also, at least in regions, in the radial direction. In this embodiment of the auxiliary unit gearbox 13, there is in each case a smaller oil volume in the second chamber 30 during operation of the gas turbine engine 1 and also during the switching-off operation than is the case in the embodiment of the auxiliary unit gearbox 13 according to FIG. 13.

[0081] FIG. 15 shows a further embodiment of the auxiliary unit gearbox 13 and of the apparatus 20. The sealing element 36 according to FIG. 15 is supported with a radial outer region 54 on an inner side 55 of the hollow-cylindrical region 27 on the second shaft 22 with an axial region 56 on the shaft end 44 of the shaft 23 and with a further axial region 57 on the hollow-cylindrical component or on the oil divider 28 or on the second part 28B of the oil divider 28. The annular-disk-shaped region 41 of the sealing element 46 is applied by the oil volume in the second chamber 30 against the shaft end 44 of the shaft 23 in a sealing manner when the dynamic oil level 32 arises in the second chamber 30. The connection 37 between the second chamber 30 and the third chamber 38 is then separated or blocked in a sealing manner. In the embodiment of the apparatus 20 according to FIG. 15, the connection 37 is provided running through the axial region 56 of the sealing element 36. Via the sealing element 36 according to FIG. 15, an axial distance between the second part 28B of the oil divider 28 and the end side or end face 43 of the shaft end 44 of the shaft 23 can be compensated for in a simple manner.

[0082] If the gas turbine engine 1 transfers to the previously described extent during a switching-off operation into an operating state in which the static oil level 47 arises in the second chamber 30, the annular-disk-shaped region 41 of the sealing element 36 springs back in the manner illustrated in FIG. 17 from the deformed state illustrated in FIG. 16 and opens up the connection 37 between the second chamber 30 and the third chamber 38, and therefore oil flows out of the second chamber 30 into the third chamber 38.

[0083] The second part 28B of the oil divider 28 according to FIG. 15 has six outlet bores 58 which are arranged distributed uniformly over the circumference of the second part 28B of the oil divider 28 and via which oil can be conducted from the second chamber 30 to a further bearing unit of the shaft 22.

LIST OF REFERENCE SIGNS

[0084] 1 Gas turbine engine [0085] 2 Bypass flow channel [0086] 3 Inlet region [0087] 4 Blower [0088] 5 Engine core [0089] 6 Compressor device [0090] 7 Separator [0091] 8 Turbine device [0092] 9 to 11 Rotor of the turbine device [0093] 12 Engine shaft [0094] 13 Auxiliary unit gearbox [0095] 14 Engine housing [0096] 15 Drive shaft [0097] 16 Auxiliary unit [0098] 17 Inner gearbox [0099] 18 Oil tank [0100] 19 Component [0101] 20 Apparatus [0102] 21 Rotationally fixed connection [0103] 22 Shaft [0104] 23 Shaft [0105] 24 Interior of the auxiliary unit gearbox 13 [0106] 25 Environment of the auxiliary unit gearbox 13 [0107] 26 Oil feed unit [0108] 27 Hollow-cylindrical region of the shaft 22 [0109] 28 Oil distributor [0110] 28A, 28B Parts of the oil distributor [0111] 29 First chamber [0112] 30 Second chamber [0113] 31 Central opening of the oil distributor [0114] 32 Dynamic oil level [0115] 33 Connecting bores between the first chamber and the second chamber [0116] 34 Ring region [0117] 35 Bearing unit [0118] 36 Sealing element [0119] 37 Connection between the first chamber and the third chamber [0120] 38 Third chamber [0121] 38A Oil volume in the third chamber 28 [0122] 39 Axial stop [0123] 40 Stop surface of the stop 39 [0124] 41 Annular disk region of the sealing element [0125] 42 Free inner edge region of the annular disk region [0126] 43 End face of the shaft 23 [0127] 44 Shaft end of the shaft 23 [0128] 45 Sealing bead or sealing lip of the sealing element [0129] 46, 47 Static oil level [0130] 48 Central venting bore of the second chamber [0131] 49 Further seal [0132] 50 Inner groove of the oil distributor [0133] 51 Boundary wall [0134] 52 Axis of rotation [0135] 53 Introduction opening [0136] 54 Radial outer region of the sealing element 36 [0137] 55 Inner side of the shaft 22 [0138] 56 Axial region of the sealing element 36 [0139] 57 Further axial region of the sealing element [0140] 58 Discharge bores of the second part 28B of the oil distributor 28 [0141] 60 Radial bore [0142] 61 Further bearing unit [0143] 65 Overlapping region [0144] 66 Outer circumference of the oil distributor [0145] 67 Flat sealing disk region [0146] 68 Radial outer region of the sealing element [0147] 70 Radial wall region [0148] A Core flow [0149] B Bypass flow [0150] Di31 Inside diameter of the central opening 31 [0151] Di39 Inside diameter of the axial stop 39 [0152] Di41 Inside diameter of the annular disk region 41