LAGERKAMMERGEHÄUSE FÜR EINE STRÖMUNGSMASCHINE

Abstract

A bearing chamber housing (20) for bearing a shaft (3) of a turbomachine (1), including a housing outer shell (21) that delimits an oil chamber (33) of the bearing chamber housing (20) radially outwardly in relation to a rotational axis (4) of the shaft (3), and a housing inner shell (22) for bearing the shaft (3). The housing inner shell (22) is radially connected to the housing outer shell (21) via support ribs (23) that in each case extend axially, at least in part, and the housing inner shell (22), the housing outer shell (21), and two support ribs (23) that are next-adjacent to one another jointly delimit a cavity (41) that is axially open at the rear, and thus lead into a rear opening (32). The rear opening (32), viewed in tangential sections, has a clearance (35) in each case that constitutes at least 50% of a circumferential distance (43) between the next-adjacent support ribs (23).

Claims

1-15. (canceled)

16. A bearing chamber housing for bearing a shaft of a turbomachine, the bearing chamber housing comprising: a housing outer shell delimiting an oil chamber of the bearing chamber housing radially outwardly in relation to a rotational axis of the shaft; and a housing inner shell for bearing the shaft; the housing inner shell being radially connected to the housing outer shell via support ribs in each case extending axially, at least in part, and the housing inner shell, the housing outer shell and two support ribs next-adjacent to one another jointly delimiting a cavity axially open at a rear, and thus leading into a rear opening, the rear opening, viewed in tangential sections, having a clearance in each case constituting at least 50% of a circumferential distance between the next-adjacent support ribs.

17. The bearing chamber housing as recited in claim 16 wherein the support ribs each include two side faces, opposite one another in the circumferential direction, in each case converging solely convexly or concavely up to 75° with respect to a center axis of the bearing chamber housing, at an axially rear end of the particular support rib.

18. The bearing chamber housing as recited in claim 16 wherein at least one of the support ribs has a wall thickness, taken in the circumferential direction, variable over an axial extension or radial extension of the at least one support rib.

19. The bearing chamber housing as recited in claim 16 wherein at least some of the support ribs differ in wall thicknesses, and as a result have different average wall thicknesses.

20. The bearing chamber housing as recited in claim 16 wherein at least one of the support ribs, viewed in an axial section plane, has a front edge forming an angle of at least 20° and at most 80° with the housing inner shell and the housing outer shell.

21. The bearing chamber housing as recited in claim 16 wherein at least one of the support ribs, viewed in an axial section plane, has a rear edge forming an angle of at least 20° and at most 80° with the housing inner shell and the housing outer shell.

22. The bearing chamber housing as recited in claim 16 wherein an overall number of support ribs is at least 3 and at most 200.

23. The bearing chamber housing as recited in claim 16 wherein a fluid channel is integrated into one of the support ribs.

24. The bearing chamber housing as recited in claim 23 wherein the fluid channel has a nonlinear extension, at least in sections.

25. The bearing chamber housing as recited in claim 16 wherein a fluid channel is integrated into the housing inner shell.

26. A turbine intermediate housing for a turbomachine comprising the bearing chamber housing as recited in claim 16.

27. A method for manufacturing the bearing chamber housing as recited in claim 16, the method comprising generatively building up jointly the housing inner shell, the housing outer shell, and the support ribs.

28. The method as recited in claim 27 wherein the housing inner shell, the housing outer shell, and the support ribs are generatively built up from front to rear in the axial direction.

29. A method comprising using the bearing chamber housing as recited in claim 16 as a bearing chamber housing for a turbomachine.

30. The method as recited in claim 29 wherein the turbomachine is an aircraft engine.

31. A method for operating the bearing chamber housing as recited in claim 23 comprising flowing oil through the fluid channel.

32. A method for operating the bearing chamber housing as recited in claim 25 comprising flowing oil through the fluid channel.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The present invention is explained in greater detail below with reference to exemplary embodiments, it being possible for the individual features, within the scope of the other independent claims besides the main claim, to also be in some other combination that is essential to the present invention, in particular a distinction also not being made between the different claim categories.

[0026] FIG. 1 shows a jet engine in an axial section;

[0027] FIG. 2 shows a bearing chamber housing according to the present invention in an axial sectional side view; and

[0028] FIG. 3 shows the bearing chamber housing according to FIG. 2 in section A-A.

DETAILED DESCRIPTION

[0029] FIG. 1 shows a turbomachine 1, specifically, a jet engine, in a schematic view. Turbomachine 1 is functionally divided into a compressor 1a, a combustion chamber 1b, and a turbine 1c. In the present case, compressor 1a and turbine 1c are each made up of two modules. Turbine intermediate housing 1cc is situated between a high-pressure turbine module 1ca, directly downstream from combustion chamber 1b, and a low- or medium-pressure turbine module 1cb. The rotors of turbine module 1ca rotate on a shaft 3 about a rotational axis 4. A bearing or bearings for this shaft 3 is/are situated in turbine intermediate housing 1cc.

[0030] FIG. 2 shows a portion of a bearing chamber housing 20 according to the present invention in a partially axial sectional side view, the section plane thus encompassing rotational axis 4. Bearing chamber housing 20 includes a housing outer shell 21 that radially delimits an oil chamber 33. Housing inner shell 22 is radially connected to housing outer shell 21 via support ribs 23; these parts are generatively built up jointly. A front edge 28 of support rib 23 forms an angle 29 of approximately 35° with housing outer shell 21 (and also with housing inner shell 22). Rear edge 27 of the support rib forms an angle 30 of approximately 30° with housing outer shell 21 (and also with housing inner shell 22).

[0031] A fluid channel 25, shown by dashed lines, having a nonlinear progression in sections is integrated into support rib 23, and also extends into housing inner shell 22 and transports oil from the outside to oil nozzles 24, which supply the roller bearings with oil. Fluid channel 25 also transports oil between ribs 23 in housing inner shell 22. Reference numeral 34 denotes the axially rear end of rib 23 together with rear opening 32.

[0032] FIG. 3 shows the bearing chamber housing in section A-A according to FIG. 2. Reference numeral 43 denotes the circumferential distance between two next-adjacent support ribs 23. Support ribs 23 each include two side faces 42, opposite one another in the circumferential direction, which converge solely convexly at an axially rear end 34 of particular rib 23. Support ribs 23 have a wall thickness 44, taken in the circumferential direction, that is variable over the axial extension of support rib 23. Support ribs 23 also differ in their average wall thicknesses. In this preferred embodiment, clearance 35 of rear opening 32 in the tangential section corresponds to circumferential distance 43, and cavity 41 is thus axially open at the rear without constrictions, etc.

[0033] Apparent once again is fluid channel 25, which transports the oil in housing inner shell 22 between support ribs 23, and partially supplies the other oil nozzles 24, distributed over the circumference, with oil. Cavity 41 is delimited by housing inner shell 22, housing outer shell 21, and two next-adjacent support ribs 23.

LIST OF REFERENCE NUMERALS

[0034] 1 turbomachine [0035] 1a compressor [0036] 1b combustion chamber [0037] 1c turbine [0038] 1ca high-pressure turbine module [0039] 1cb low- or medium-pressure turbine module [0040] 1cc turbine intermediate housing [0041] 3 shaft [0042] 4 rotational axis [0043] 20 bearing chamber housing [0044] 21 housing outer shell [0045] 22 housing inner shell [0046] 23 support ribs [0047] 24 oil nozzle [0048] 25 fluid channel [0049] 27 rear edge of the support rib in the axial section [0050] 28 front edge of the support rib in the axial section [0051] 29 angle between the front edge and the housing outer shell [0052] 30 angle between the rear edge and the housing outer shell [0053] 31 axial extension of the support rib [0054] 32 rear opening of the cavity [0055] 33 oil chamber [0056] 34 axially rear end of the support rib [0057] 35 clearance of the rear opening [0058] 41 cavity [0059] 42 side faces [0060] 43 circumferential distance [0061] 44 wall thickness [0062] 45 radial extension of the support rib