TURBOENGINE, AND VANE CARRIER UNIT FOR TURBOENGINE

Abstract

A turboengine as disclosed includes an outer wall structure and an inner wall structure, wherein the inner wall structure is provided at a radially inner position with respect to the outer wall structure, and each of the wall structures has a surface, the surfaces being arranged facing each other in the radial direction. At least one guide vane member includes at least one airfoil, a radially inner end and a radially outer end. The inner wall structure and the outer wall structure are jointly provided as a vane carrier unit, wherein the inner wall structure and the outer wall structure are fixedly connected to each other by at least one bridging member extending between the inner wall structure and the outer wall structure.

Claims

1. A turboengine, the turboengine defining a radial direction (r), an axial direction (l), a circumferential direction, and a main working fluid flow direction extending in the axial direction, the turboengine comprising an outer wall structure and an inner wall structure, wherein the inner wall structure is provided at a radially inner position with respect to the outer wall structure, and each of the wall structures has a surface, each of said surfaces being arranged facing each other in the radial direction; a duct provided between the inner wall structure and the outer wall structure and having a downstream end with respect to the main working fluid flow direction; at least one guide vane member arranged at the downstream end of the duct, the guide vane member having at least one airfoil, a radially inner end and a radially outer end, the inner end of the guide vane member being supported at the inner wall structure and the outer end of the guide vane member being supported at the outer wall structure; and the inner wall structure and the outer wall structure being jointly provided as a vane carrier unit, wherein the inner wall structure and the outer wall structure are fixedly connected to each other by at least one bridging member extending between the inner wall structure and the outer wall structure, and wherein the bridging member is provided upstream the downstream end of the duct with respect to the main working fluid flow direction.

2. The turboengine according to claim 1, comprising: at least two vane carrier units along the circumferential direction of the turboengine to form an annular guide vane row.

3. The turboengine according to claim 1, wherein the bridging member is provided upstream the duct which is formed between the wall structures.

4. The turboengine according to claim 1, comprising: a multitude of bridging members along the circumferential direction, wherein at least two bridging members are provided at a circumferential distance from each other.

5. The turboengine according to claim 1, wherein the bridging member is one of curved or angled, and cantilevers from the outer wall structure in a first section in the upstream direction and extends in a second section radially inwardly to the inner wall structure.

6. The turboengine according to claim 1, wherein the inner wall structure comprises: an extension extending upstream of the duct.

7. The turboengine according to claim 1, wherein the inner wall structure and the bridging member are attached to each other by a flange connection.

8. The turboengine according to claim 1, wherein the guide vane member is an inlet guide vane member of an expansion turbine and is provided upstream a first row of running blades of the expansion turbine; and wherein the outer wall structure extends from an expansion turbine vane carrier, the duct being in fluid communication with the expansion turbine with the inlet guide vane member being interposed between the duct and the first row of running blades of the expansion turbine.

9. The turboengine according to claim 1, wherein the duct is provided with an annular downstream discharge face, the annular discharge face circumferentially extending around an axis of the turboengine and being in fluid communication with a circumferentially disposed row of guide vane members.

10. The turboengine according to claim 1, comprising: a multitude of can combustors circumferentially disposed around an axis of the turboengine and upstream of the duct, wherein each can combustor is in fluid communication with a duct at an upstream end thereof.

11. The turboengine according to claim 1, wherein the duct is provided as a combustor, wherein combustor liners are provided on mutually facing arranged surfaces of the wall structures.

12. The turboengine according to claim 1, wherein the guide vane member is attached to one of the outer and inner wall structures by an axially and radially fixed support arrangement, and is attached to the other one of the inner and outer wall structures by a support arrangement which provides a fixed support in the axial direction and provides a floating support in the radial direction.

13. A vane carrier unit for a turboengine, the vane carrier unit comprising: an outer wall structure and an inner wall structure, wherein the inner wall structure is provided at a radially inner position with respect to the outer wall structure, and each of the wall structures have a surface, each of said surfaces being arranged facing each other in the radial direction; and the inner wall structure and the outer wall structure being jointly provided as the vane carrier unit, wherein the inner wall structure and the outer wall structure are fixedly connected to each other by at least one bridging member extending between the inner wall structure and the outer wall structure.

14. A vane carrier unit for a turboengine according to claim 13, the vane carrier unit comprising: the outer wall structure and the inner wall structure each being provided with a surface facing the respective surface of the other wall structure, a free space being provided between the mutually facing surfaces; a first vane support feature being provided on the outer wall structure; a second vane support feature being provided on the inner wall structure and opposed the first vane support feature, the vane support features being provided at an end of the free space; and the bridging member connecting the outer and the inner wall structures and being provided distant from said end of the free space.

15. The vane carrier unit according to claim 13 wherein the bridging member is arranged outside a free space which is between mutually facing surfaces of the outer and inner wall structures and on an opposite side of vane support features.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The subject matter of the present disclosure is now to be explained in more detail by means of selected exemplary embodiments shown in the accompanying drawings. The figures show

[0037] FIG. 1 a first view of a part of a gas turbine engine, illustrating the arrangement of a vane carrier unit of the type initially mentioned, a can combustor, a rotor cover, and a first row of running blades of an expansion turbine in a view from a first circumferential position;

[0038] FIG. 2 a second view of a part of the gas turbine engine, illustrating the arrangement of a vane carrier unit of the type initially mentioned, a can combustor, a rotor cover, and a first row of running blades of an expansion turbine in a view from a different circumferential position;

[0039] FIG. 3 the support arrangement of a guide vane member at an outer wall structure;

[0040] FIG. 4 a detail view of a radially and axially fixed support assembly;

[0041] FIG. 5 a detail view of an auxiliary support assembly for facilitating inserting a guide vane member into a vane carrier unit;

[0042] FIG. 6 the support arrangement of a guide vane member at an inner wall structure; and

[0043] FIG. 7 a perspective view of a vane carrier unit of the type initially mentioned.

[0044] It is understood that the drawings are highly schematic, and details not required for instruction purposes may have been omitted for the ease of understanding and depiction. It is further understood that the drawings show only selected, illustrative embodiments, and embodiments not shown may still be well within the scope of the herein disclosed and/or claimed subject matter.

EXEMPLARY MODES OF CARRYING OUT THE TEACHING OF THE PRESENT DISCLOSURE

[0045] FIGS. 1 and 2 depict sections of a part of an exemplary gas turbine engine taken at different circumferential positions. The gas turbine engine defines a radial direction r and an axial direction e. A main working fluid flow direction extends essentially along the axial direction e, and is generally directed from a compressor, not shown in the present depiction, to an expansion turbine. The gas turbine engine comprises a vane carrier unit 1, which in turn comprises an outer wall structure 11, an inner wall structure 12, and a bridging member 13. Outer wall structure 11 and inner wall structure 12 are fixedly connected to each other by bridging member 13. A space or duct 14 is formed between opposed surfaces of the inner and outer wall structures, which surfaces face each other and delimit space or duct 14. Inner wall structure 12 comprises an extension extending upstream duct 14. A flange connection is provided at an upstream end of inner wall structure 12, or the extension, respectively, to connect inner wall structure 12 to bridging member 13. Bridging member 13 may be provided integrally, in one piece, with outer wall structure 11, or may be welded or otherwise suitably attached thereto. Bridging member 13 is sufficiently large-dimensioned to provide a high stiffness in the axial and radial directions, and to resist bending in the shown plane, and thus is suitable to support any forces acting on the inner and outer wall structures virtually without any deformation. Vane carrier unit 1 is arranged radially outside a rotor cover 7. Outer wall structure 11 is fixedly connected to an expansion turbine vane carrier 2, for instance by a flange connection. Blades 9 of a first row of running blades of an expansion turbine are arranged on a rotor 8. On an upstream end, space 14 is fluidly connected to a transition piece 4. A fuel discharge and/or mixing means 5 is arranged inside transition piece 4. A can combustor 3 joins into transition piece 4 at an upstream end thereof. Transition piece 4 and can combustor 3 are provided with a displaceable connection, such that can combustor 3 and transition piece 4 may displace with respect to each other along an axis of can combustor 3. Sealing means 6 are provided around a downstream end of can combustor 3 to provide a gas tight sealing between can combustor 3 and transition piece 4. It is for an instance known to apply so-called Hula seals for this purpose, which allow a displacement along a con combustor axis while at the same time providing a gas-tight sealing. In an exemplary embodiment, space 14 annularly extends around the circumference of the gas turbine engine. A multitude of can combustors 3 are arranged around the circumference of the gas turbine engine. A multitude of bridging members 13 are arranged around the circumference of the gas turbine engine. In particular, can combustors 3 and bridging members 13 are alternatingly arranged around the circumference of the gas turbine engine. Transition piece 4 provides a transition geometry from the exit of the can combustors to annularly extending space or duct 14. Still oxygen rich flue gas from can combustors 3 is annularly dispersed into annularly extending space 14 through transition piece 4. In certain states of operation, fuel may be discharged into the flue gas flow from can combustors 3, and be admixed with the flue gas through fuel discharge and/or mixing means 5 to form a flue gas/fuel mixture inside space 14. The mixture is subsequently combusted in space 14. In this respect, space 14 is provided as an annular combustor. Combustor liner segments may be provided on the surfaces of outer wall member 11 and inner wall member 12 which face each other and delimit duct or space 14, in a manner the skilled person is familiar with. An explicit illustration of the liners is omitted for the sake of clarity of depiction, and as they are familiar to the skilled person. The liner segments may be rounded such as to provide a circular cross section, or may be plane plates or tiles, thus resulting in a polygonial cross section approximating a circular cross section. The liner segments may be equipped with a near wall cooling arrangement, and/or with integrated dampers in order to attenuate thermoacoustic oscillations in the annular combustor. An expansion turbine is provided adjacent a downstream end of vane carrier unit 1. An expansion turbine vane carrier 2 and running blades 9 of a first row of expansion turbine running blades are mentioned above and shown in the present illustration. The skilled person will readily appreciate that a main working fluid flow direction of the gas turbine engine extends along the axial direction e, and from can combustor 3 to the expansion turbine. A guide vane member 20 of a stationary first or inlet guide vane row of the expansion turbine is interposed between the annular combustor and the first row of running blades 9 of the expansion turbine, and is provided downstream of the annular combustor. Guide vane member 20 is supported at an inner or hub side end at inner wall structure 12, and is supported at an outer end at outer wall structure 11. A sealing member 24 is provided between the hub side end of guide vane member 20 and rotor cover 7. Sealing member 24 is arranged such as to allow axial and radial relative displacement between guide vane member 20 and rotor cover 7. Vane carrier unit 1 and guide vane member 20 jointly form a guide vane unit or guide vane assembly, in which, in the exemplarily shown embodiment, the guide vanes are provided in a common assembly with an annular combustor 14. The support assemblies through which guide vane member 20 is supported by the outer wall structure 11 and the inner wall structure 12, respectively, are denoted at A and B, and are lined out in more detail below.

[0046] FIGS. 1 and 2 show views from different circumferential positions of the gas turbine engine. In the depiction of FIG. 1, a can combustor 3 partly hides a bridging member 13. In the depiction of FIG. 2, a bridging member 13 partly hides a can combustor 3.

[0047] FIG. 3 shows detail A of FIGS. 1 and 2, setting forth in more detail a support arrangement through which guide vane member 20 is supported by outer wall structure 11. Guide vane member 20 comprises one or more airfoils 21 and an outer platform 22, which constitutes a radially outer end of guide vane member 20. The support arrangement comprises a radially and axially fixed support assembly 15, provided at an upstream end of guide vane member 20, and an auxiliary support assembly 16, provided at a downstream end of guide vane member 20. Male support elements 25 and 26 extend radially outwardly from outer platform 22 and are received in female support features of outer wall structure 11. FIG. 4 shows more details of radially and axially fixed support assembly 15. Male support element 25 comprises a lug 251 which in turn comprises a locking protrusion 252. Lug 251 is received in a slot of the outer wall structure. The slot is provided with an undercut, which in turn receives locking protrusion 252. Lug 251 is received in the slot in a snug fit, that is, at least essentially without play, in the axial direction. Locking protrusion 252 is received in the undercut with a snug fit in the radial direction. Thus, a radially as well as axially fixed support assembly is provided. Male support element 25 may be inserted into the slot and the undercut in the circumferential direction of the gas turbine engine. In providing a radially as well as axially fixed support assembly at an upstream end of guide vane member 20, a transition between an inner surface of outer wall structure 11 and platform 22 is well-defined and may be provided without gaps, steps, or ledges, and may thus exhibit an outstanding aerodynamic performance. Auxiliary support assembly 16 is shown in more detail in FIG. 5. Male support element 26 comprises lug 261 and protrusion 262. Protrusion 262 engages an undercut of outer wall structure 11 with play in the radial as well as in the axial direction. Moreover, also lug 261 is provided distant from a counter surface of outer wall structure 11. Male support element 26 may thus displace with respect to outer wall structure 11 in the radial as well as in the axial direction, and has no support function in an assembled guide vane unit. However, when guide vane member 20 is inserted into vane carrier unit 1, auxiliary support assembly 16 may serve to temporarily support guide vane member 20 during the assembly process. Assembly of the guide vane unit is thus largely facilitated.

[0048] FIG. 6 shows detail B of FIGS. 1 and 2. Guide vane member 20 comprises, as noted above, at least one airfoil 21, and further radially inner or hub side platform 23, constituting a radially inner or hub side end of guide vane member 20. Guide vane member 20 is supported at an upstream and radially inner end thereof at inner wall structure 12 by a radially floating and axially fixed support assembly 17. Radially floating and axially fixed support assembly 17 is provided by a lug 27, which is provided as a male support element and extending radially inwardly from inner platform 23, and which is received in a female support feature of inner wall structure. Male support element 27 is received in the female support feature of inner wall structure 12 with a snug fit in the axial direction, while being free to displace and float in the radial direction. At a downstream end of guide vane member 20, sealing member 24 is provided for sealing between guide vane member 20 and rotor cover 7. Sealing member 24 is pivotably received by rotor cover 7 and abuts a suitably provided structure of guide vane member 20. Generally, for instance cooling air may be provided in a space between inner wall structure 12 and rotor cover 7. The pressure of said cooling air generally is higher than the working fluid pressure downstream the first guide vane row, and thus presses sealing member 24 to the sealing structure of guide vane member 20. Moreover, sealing member 24 may be provided as an elastic member. The sealing arrangement provided by sealing member 24 between the rotor cover 7 and guide vane member 20 allows for a relative axial and radial displacement between the rotor cover 7 and guide vane member 20.

[0049] By virtue of the support arrangement lined out above, guide vane member 20 is axially fixed at its upstream end to the vane carrier. A downstream end of guide vane member 20 is enabled to freely float in order to compensate differential thermal expansion. Guide vane member 20 is radially fixedly supported at the vane carrier unit at one radial end, while it is radially floatingly supported by the vane carrier unit at the other radial end. Differential thermal expansion in the radial direction is thus accounted for.

[0050] FIG. 7 shows a perspective view of a vane carrier unit 1 and rotor cover 7. The vane carrier unit 1 is provided as a generally semi-annular element. In arranging two of these vane carrier units circumferentially abutting each other, an annular arrangement is provided. An annular row of guide vanes is accordingly formed. A multitude of bridging members 13 are circumferentially distributed along the circumferential extent of vane carrier unit 1, and fixedly connect outer wall structure 11 and inner wall structure 12 in order to jointly form vane carrier unit 1.

[0051] While the subject matter of the disclosure has been explained by means of exemplary embodiments, it is understood that these are in no way intended to limit the scope of the claimed invention. It will be appreciated that the claims cover embodiments not explicitly shown or disclosed herein, and embodiments deviating from those disclosed in the exemplary modes of carrying out the teaching of the present disclosure will still be covered by the claims.

LIST OF REFERENCE NUMERALS

[0052] 1 vane carrier unit

[0053] 2 expansion turbine vane carrier

[0054] 3 can combustor

[0055] 4 transition piece

[0056] 5 fuel discharge and/or mixing means

[0057] 6 sealing means

[0058] 7 rotor cover

[0059] 8 rotor

[0060] 9 blade of first row of expansion turbine running blades

[0061] 11 outer wall structure

[0062] 12 inner wall structure

[0063] 13 bridging member

[0064] 14 space, duct

[0065] 15 support assembly

[0066] 16 auxiliary support assembly

[0067] 17 support assembly

[0068] 20 guide vane member

[0069] 21 airfoil

[0070] 22 outer platform

[0071] 23 inner platform, hub side platform

[0072] 24 sealing member

[0073] 25 male support element

[0074] 26 male support element

[0075] 27 27 male support element, lug

[0076] 251 lug

[0077] 252 locking protrusion

[0078] 261 lug

[0079] 262 protrusion

[0080] l axial direction

[0081] r radial direction