HEAT-PROTECTION ELEMENT FOR A BEARING CHAMBER OF A GAS TURBINE

Abstract

Described is a heat-protection element (50) for a gas turbine (10), in particular an aircraft gas turbine, the heat-protection element (50) being adapted to at least partially surround a bearing chamber (60) of the gas turbine (10) and having at least one connecting portion (52) which is disposed in an axially forward region (VB) and connectable or connected by a material-to-material bond to a protective element (54) of a seal carrier, in particular a seal carrier with a carbon seal, at least one supporting portion (58) which is disposed in an axially central region (MB) and adapted to support the heat-protection element (50) radially on the bearing chamber (60), an end portion (64) which is disposed in an axially rearward region (HB) and forms a free end (66) of the heat-protection element (50) and which is configured such that the end portion surrounds (64) the bearing chamber (60) in a contactless manner.

Claims

1-12. (canceled)

13. A heat-protection element for a gas turbine, the heat-protection element adapted to at least partially surround a bearing chamber of the gas turbine and comprising: at least one connecting portion disposed in an axially forward region and connectable or connected by a material-to-material bond to a protective element of a seal carrier, at least one supporting portion disposed in an axially central region and adapted to support the heat-protection element radially on the bearing chamber; an end portion disposed in an axially rearward region and forming a free end of the heat-protection element and configured such that the end portion surrounds the bearing chamber in a contactless manner.

14. The heat-protection element as recited in claim 13 wherein the heat-protection element is formed as a single piece.

15. The heat-protection element as recited in claim 13 wherein the heat-protection element is configured such that, together with the protective element of the seal carrier, the heat-protection element forms a heat-protection unit attachable or attached to an axially forward flange portion of the bearing chamber.

16. The heat-protection element as recited in claim 15 wherein the heat-protection unit is slidable onto the bearing chamber or removable therefrom from an axially forward end.

17. The heat-protection element as recited in claim 13 wherein at least three circumferentially distributed, tab connecting portions are formed in the axially forward region.

18. The heat-protection element as recited in claim 13 wherein a single circumferential connecting portion is formed in the axially forward region.

19. The heat-protection element as recited in claim 18 wherein the connecting portion is in the form of a circumferential welded or brazed seam.

20. The heat-protection element as recited in claim 13 wherein the end portion is bent over axially forwardly.

21. The heat-protection element as recited in claim 13 wherein the end portion defines a brim.

22. The heat-protection element as recited in claim 13 wherein in the axially central region, at least three circumferentially distributed, radially inwardly formed corrugations are formed and serve as respective supporting portions.

23. The heat-protection element as recited in claim 13 wherein, in the axially central region, there is provided a single circumferential supporting portion contactable with, or is in contact with, an annular sealing device supported on the bearing chamber.

24. The heat-protection element as recited in claim 13 wherein the annular sealing device is a rope seal.

25. A heat-protection unit for a bearing chamber of a gas turbine, the heat-protection unit comprising the heat-protection element as recited in claim 13 and the protective element, the protective element being connected by the material-to-material bond to the heat-protection element in the axially forward region.

26. The heat-protection unit as recited in claim 25 wherein the seal carrier includes a carbon seal.

27. A gas turbine comprising: at least one bearing chamber; and the heat-protection element as recited in claim 13 disposed around the bearing chamber.

28. The gas turbine as recited in claim 27 wherein the gas turbine is an airline gas turbine.

29. The gas turbine as recited in claim 27 wherein the heat-protection element is provided in the region of a turbine center frame or as part of a turbine center frame.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The invention will now be described by way of example, and not by way of limitation, with reference to the accompanying drawings.

[0025] FIG. 1 is a simplified, schematic representation of an aircraft gas turbine;

[0026] FIG. 2 is a simplified schematic perspective view of a heat-protection element and a heat-protection unit;

[0027] FIG. 3 is a simplified schematic sectional view of a bearing chamber and a heat-protection element, corresponding substantially to the line III-III of FIG. 2;

[0028] FIG. 4 is a simplified schematic enlarged sectional view of an axially central portion and a rearward portion of the heat-shield element and of the bearing chamber, corresponding substantially to the region indicated by rectangle IV in FIG. 3.

DETAILED DESCRIPTION

[0029] FIG. 1 shows, in simplified schematic form, an aircraft gas turbine 10, illustrated, merely by way of example, as a turbofan engine. Gas turbine 10 includes a fan 12 surrounded by a schematically indicated casing 14. Disposed downstream of fan 12 in the axial direction AR of gas turbine 10 is a compressor 16 that is accommodated in a schematically indicated inner casing 18 and may be single-stage or multi-stage. Disposed downstream of compressor 16 is combustor 20. The flow of hot exhaust gas exiting the combustor then flows through the downstream turbine 22, which may be single-stage or multi-stage. In the present example, turbine 22 includes a high-pressure turbine 24 and a low-pressure turbine 26. A hollow shaft 28 connects high-pressure turbine 24 to compressor 16, in particular a high-pressure compressor 29, so that they are jointly driven or rotated. Another shaft 30 located further inward in the radial direction RR of the turbine connects low-pressure turbine 26 to fan 12 and to a low-pressure compressor 32 so that they are jointly driven or rotated. Disposed downstream of turbine 22 is an exhaust nozzle 33, which is only schematically indicated here.

[0030] In the illustrated example of an aircraft gas turbine 10, a turbine center frame 34 is disposed between high-pressure turbine 24 and low-pressure turbine 26 and extends around shafts 28, 30. Hot exhaust gases from high-pressure turbine 24 flow through turbine center frame 34 in its radially outer region 36. The hot exhaust gas then flows into an annular space 38 of low-pressure turbine 26. Compressors 29, 32 and turbines 24, 26 are illustratively represented by rotor blade rings 27. For the sake of clarity, the usually present stator vane rings 31 are shown, by way of example, only for compressor 32.

[0031] FIG. 2 shows, in a simplified schematic perspective view, a heat-protection element 50, which may be used in a gas turbine 10. In FIG. 2, there is indicated an axis of rotation DA, which coincides with the axes of the shafts 28, 30 (FIG. 1) of the gas turbine. Heat-protection element 50 is disposed in the region of a bearing chamber in which at least one shaft 28, 30 of the gas turbine is supported. Referring to FIG. 1, heat-protection element 50 may in particular be disposed in the region of turbine center frame 34, in particular radially inwardly of the radially outer region 36 shown in FIG. 1, in which hot gas flows.

[0032] Heat-protection element 50 has at least one connecting portion 52 in an axially forward region VB. The connecting portion(s) 52 is/are connected by a material-to-material bond to a protective element 54. Protective element 54 surrounds or covers a seal carrier (not specifically shown here). Heat-protection element 50 has a main body 56 which, beginning at the joint with protective element 54, extends axially rearwardly and has different radii along the axial length. In particular, the radius of heat-protection element 50 regionally increases discretely or continuously from an axially forward end toward an axially rearward end along portions of its length.

[0033] In the further description of heat-protection element 50, reference is also made simultaneously to the sectional views of FIGS. 3 and 4.

[0034] In an axially central region MB, a supporting portion 58 is provided which is adapted to support heat-protection element 50 radially on a bearing chamber 60, which is shown in simplified form in the sectional views. The support of heat-protection element 50 may be accomplished via a supporting element 62, which in FIGS. 3 and 4 is shown merely schematically to represent different types of support.

[0035] In an axially rearward region HB, heat-protection element 50 has an end portion 64, which forms a free end of heat-protection element 50. End portion 64 is formed or bent over in such a way that end portion 64 surrounds bearing chamber 60 in a contactless manner. In other words, a distance AB or clearance is formed between end portion 64 and bearing chamber 60.

[0036] The heat-protection element 50 shown in FIGS. 2 through 4 may be formed as a single piece. The above-described connecting portions 52, supporting portion 58, and end portion 64 may be made from a single workpiece or material.

[0037] Heat-protection element 50 and the protective element 54 of the seal carrier together form a heat-protection unit 70. Heat-protection unit 70 may be attachable or attached to an axially forward flange portion 72 (merely schematically indicated in FIG. 3) of bearing chamber 60. Heat-protection unit 70 may, for example, be slidable onto bearing chamber 60 or removable therefrom from an axially forward end.

[0038] For example, at least three circumferentially distributed, tab-like connecting portions 52 may be formed in axially forward region VB. Such a design can be seen, for example, in FIG. 2, where only two of several connecting portions 52 are shown.

[0039] Alternatively, heat-protection element 50 may have a single circumferential connecting portion 52, in particular in the form of a circumferential welded or brazed seam, in axially forward region VB.

[0040] As can be seen from FIGS. 2 through 4, end portion 64 of heat-protection element 50 is bent over axially forwardly. End portion 64 may also be described as being bent over in a brim-like manner. By shaping end portion 64 in this way, it is possible to achieve sufficient stability and stiffness for end portion 64, thereby making it possible to ensure its contactless arrangement (with a distance or clearance AB) with respect to bearing chamber 60, in particular also during operation of gas turbine 10 and under corresponding thermal and mechanical loading.

[0041] In accordance with embodiments, the above-mentioned schematically and representatively shown supporting element 62 may be configured such that at least three circumferentially distributed, radially inwardly formed corrugations are formed on heat-protection element 50 in axially central region MB, the corrugations serving as respective supporting portions 58 or supporting element 62.

[0042] Alternatively, in axially central region MB, a single circumferential supporting portion 58 may be provided which can be brought into contact with, or is in contact with, an annular sealing device supported on bearing chamber 60. In other words, the illustrated supporting element 62 may also be understood as being or representing such an annular sealing device.

[0043] Heat-protection unit 70 may, for example, be connected to bearing chamber 60 by threaded connecting means, as illustrated in FIG. 2 by holes 74.

[0044] With regard to axial regions VB, MB, HB, it should be noted that these regions may be determined or defined based on a percentage of the axial length of heat-protection element 50. Referring to FIG. 3, forward and rearward regions VB, HB are illustrated as being about 20% of the axial extent of heat-protection element 50, with central region MB being about 60%. This percentage distribution is purely exemplary. In particular, the forward or rearward region VB may also be defined to be shorter or longer, for example, in a range of about 5% to 30% of the axial extent of heat-protection element 50. As a consequence, central region MB may be about 40% to 90% of the axial extent.

[0045] A design of heat-protection element 50 as presented above makes it possible to prevent fretting-inducing contact between heat-protection element 50 and bearing chamber 60 in axially rearward region HB. In such design, the distance AB or clearance is formed between end portion 64 and bearing chamber 60. This distance AB may be a few millimeters. Despite the contactless arrangement, the heat-protection element 50 presented here enables good thermal shielding of bearing chamber 60 in axially rearward region HB of heat-protection element 50. In a departure from previous heat-protection elements, and due to the single-piece design of heat-protection element 50, a radially inwardly disposed, single-piece or single-part heat-protection element 50 is provided, so that there is no longer a plurality of parts, and, in particular, material-to-material bonding of an axially rearward heat-protection element can also be dispensed with.

LIST OF REFERENCE NUMERALS

[0046] 10 aircraft gas turbine [0047] 12 fan [0048] 14 casing [0049] 16 compressor [0050] 18 inner casing [0051] 20 combustor [0052] 22 turbine [0053] 24 high-pressure turbine [0054] 26 low-pressure turbine [0055] 28 hollow shaft [0056] 29 high-pressure compressor [0057] 30 shaft [0058] 31 stator vane ring [0059] 32 low-pressure compressor [0060] 33 exhaust nozzle [0061] 34 turbine center frame [0062] 36 radially outer region [0063] 38 annular space [0064] 50 heat-protection element [0065] 52 connecting portion [0066] 54 protective element [0067] 56 main body [0068] 58 supporting portion [0069] 60 bearing chamber [0070] 62 supporting element [0071] 64 end portion [0072] 66 free end [0073] 70 heat-protection unit [0074] 72 flange portion [0075] 74 hole [0076] AB distance or clearance [0077] AR axial direction [0078] RR radial direction [0079] HB axially rearward region [0080] MB axially central region [0081] VB axially forward region