MODULAR NOZZLE RING FOR A TURBINE STAGE OF A CONTINUOUS FLOW MACHINE

Abstract

The invention relates to a modular nozzle ring for a turbine stage of a continuous flow machine. The modular nozzle ring has a carrier system having an an adjustment ring, and a blade module having a blade leaf. The blade module is detachably connected to the carrier system. Furthermore, an adjustment angle of the blade leaf by the carrier system, in particular by the adjustment ring spaced apart from a flow channel, is specified, which adjustment angle is unchangeable during operation. The blade module is designed to be detachably pressed to a turbine housing part on the flow side, in particular by the adjustment ring. The invention furthermore relates to a blade module for a modular nozzle ring of a turbine stage and the use of a carrier system for a modular nozzle ring.

Claims

1. A modular nozzle ring for a turbine stage of a turbomachine having: a carrier system having an adjustment ring; and a vane module having a vane leaf, wherein the vane module is releasably connected to the carrier system; wherein an adjustment angle (α) of the vane leaf is fixed by the carrier system; and wherein the vane module is configured to be releasably pressed resiliently against a flow-side turbine housing portion.

2. The modular nozzle ring as claimed in claim 1, wherein the vane module has an axially extended vane shaft, and wherein the adjustment ring has a vane shaft opening, wherein a bearing-side end portion of the vane shaft is at least partially arranged in the vane shaft opening of the adjustment ring.

3. The modular nozzle ring of claim 1, further having a clamping element which is configured to act counter to the vane module and the carrier system.

4. The modular nozzle ring as claimed in claim 3, wherein the clamping element is configured to axially press the vane module against the flow-side turbine housing portion.

5. The modular nozzle ring as claimed in claim 3, wherein the clamping element is arranged between the adjustment ring and the baseplate.

6. The modular nozzle ring as claimed in claim 3, wherein the clamping element is further configured to axially press the adjustment ring against a bearing-side housing portion of the turbomachine.

7. The modular nozzle ring of claim 1, further having a securing element which is releasably connected to the bearing-side end of the vane shaft.

8. The modular nozzle ring of claim 1, wherein the vane module has at a bearing-side end at least one connection element and the adjustment ring has at least one groove, wherein the adjustment angle (α) of the vane leaf is releasably fixed by a connection between the at least one connection element and the at least one groove.

9. The modular nozzle ring of claim 1, wherein the vane module has a first and a second connection element, and the adjustment ring has a first and a second groove, and wherein the first connection element is dimensioned in accordance with the first groove and wherein the second connection element is dimensioned in accordance with the second groove.

10. The modular nozzle ring of claim 1, wherein the vane module has a support structure which is arranged at the bearing side of the baseplate and at a radial end portion of the vane module, wherein the at least one connection element is arranged at the bearing-side end of the support.

11. The modular nozzle ring of claim 1, wherein the carrier system further has a carrier ring, wherein the carrier ring has an axially extended opening which is configured to receive the support structure and/or the vane shaft; and/or further having a large number of vane modules, wherein each of the vane modules is releasably connected to the carrier system.

12. The modular nozzle ring of claim 1, wherein the vane leaf, the vane shaft, the baseplate and the support structure are integrally constructed.

13. The modular nozzle ring of claim 1, wherein the vane module is further configured to be releasably pressed against a flow-side turbine housing portion by means of an air purge system.

14. The turbine stage of a turbomachine, having a modular nozzle ring of claim 1.

15. A vane module for a modular nozzle ring of a turbine stage, the vane module having: a vane leaf, and at least one connection element which is arranged at a bearing-side end and which is configured to fix an adjustment angle (α) of the vane leaf by means of a connection between the connection element and a groove of a carrier system of the modular nozzle ring; and wherein the vane module is configured to resiliently, releasably press against a flow-side turbine housing portion.

16. The carrier system for a modular nozzle ring of claim 1, having an adjustment ring; wherein the adjustment ring has a vane shaft opening; and wherein the adjustment ring has a first and a second groove; and wherein the first and second grooves have different cross sections.

17. The modular nozzle ring of claim 1, wherein the adjustment angle (α) is invariable during operation.

18. The modular nozzle ring of claim 1, wherein the adjustment angle (α) of the vane leaf is fixed by the adjustment ring which is spaced apart from a flow channel.

19. The modular nozzle ring of claim 1, wherein the vane module is configured to be releasably pressed resiliently by the adjustment ring against a flow-side turbine housing portion.

Description

BRIEF DESCRIPTION OF THE FIGURES

[0071] The invention is explained in greater detail below with reference to embodiments without the embodiments being intended to limit the scope of protection defined by the claims.

[0072] The appended drawings depict embodiments and are used together with the description to explain the principles of the invention. The elements of the drawings are not necessarily true-to-scale relative to each other. Identical reference numerals indicate correspondingly similar components.

[0073] In the Figures:

[0074] FIG. 1 shows a portion of a modular nozzle ring according to one embodiment.

[0075] FIG. 2 shows a portion of a modular nozzle ring according to one embodiment.

[0076] FIG. 3 shows a vane module for a modular nozzle ring according to one embodiment.

[0077] FIG. 4 shows a portion of a carrier system according to one embodiment.

[0078] FIG. 5 shows a portion of a modular nozzle ring according to one embodiment.

[0079] FIG. 6 shows a portion of a modular nozzle ring according to one embodiment.

[0080] FIG. 7 shows a portion of a modular nozzle ring according to one embodiment.

[0081] FIG. 8 shows a portion of a carrier system according to one embodiment.

[0082] FIG. 9 shows a portion of a modular nozzle ring according to one embodiment.

[0083] FIG. 10 shows a portion of a modular nozzle ring according to one embodiment.

[0084] FIG. 11 shows a portion of a modular nozzle ring according to one embodiment.

[0085] FIG. 12 shows a portion of a modular nozzle ring according to one embodiment.

EMBODIMENTS

[0086] FIG. 1 shows a portion of a modular nozzle ring 100 for a turbine stage of a turbomachine. The modular nozzle ring is illustrated in a turbine stage in the fitted state. The modular nozzle ring 100 has a vane module 300 and a carrier system 200.

[0087] One embodiment of the vane module 300 is shown separately in FIG. 3 (not fitted in the modular nozzle ring 100). The vane module 300 has the vane leaf 326 at a flow-side end portion. At the bearing side of the vane leaf 326, the vane module 300 has a baseplate 309. The baseplate 309 is typically configured to form a closure or, in other words, a housing wall portion, of the (primary) flow channel 120. At the bearing side of the baseplate 309, the vane module 300 has a lateral, axially extended support structure 313. The support structure 313 can have a plurality of support struts 317, 318. The vane module 300 shown in FIG. 3 has, for example, two support struts 317, 318 which are arranged at approximately 180° relative to each other, that is to say, approximately at opposite radial end portions of the vane module 300.

[0088] Two connection elements 330, 331 are arranged at the bearing-side end of the support structure 313 or of the two support struts 317, 318. The connection elements which are shown in FIG. 3 are in the form of a cam. The two cams 330, 331 have a similar cross sectional shape, but have a different cross section (or cross sectional size) 314, 315. The different cross sections 314, 315 allow a clear determination of an adjustment angle α of the vane leaf 326 and prevent, for example, the vane module from being able to be fixed to the carrier system 200 in a state rotated through 180° and the vane profile angle from thereby being incorrectly adjusted or the vane leaf from being orientated in an incorrect manner relative to the flow direction.

[0089] Adjustment faces 316 (only one is marked in FIG. 3) are arranged at the side of the bearing-side ends 314, 315 of the cams. The adjustment faces 316 are configured to move into contact with the grooves of the adjustment ring (described below) in order to determine an adjustment angle.

[0090] The vane module 300 further has a vane shaft 310. The vane shaft 310 extends from the baseplate 309 as far as a bearing-side end of the vane module 300. The vane shaft 310 is substantially axial and can further be arranged centrally. A securing groove 325 is arranged at a bearing-side end portion of the vane shaft 310. The securing groove 325 is not marked in FIG. 3 and can best be seen in FIG. 1.

[0091] The carrier system comprises an adjustment ring 203. A portion of the adjustment ring 203 is separately shown in FIG. 8 (not fitted in the modular nozzle ring 100).

[0092] The adjustment ring 203 has for each vane module 300 a vane shaft opening 221 for receiving the vane shaft 310. The vane module 300 can be secured to the vane shaft 310. The modular nozzle ring 100 has a securing element 208. The securing element 208 may, for example, be a securing ring 208, as clearly shown in FIGS. 7 and 9. The securing element 208 is releasably connected to the bearing-side end of the vane shaft 310, in particular the securing ring 208 is releasably connected to the securing groove 325 in a positive-locking manner. The securing element 208 prevents the vane module 300 from “sliding out” of the adjustment ring 203 at the flow side.

[0093] The adjustment ring 203 has for each vane module 300 at least one groove 220, 222 for fixing the adjustment angle α of the vane leaf 326. The adjustment angle α is fixed by a connection between the precise cam 330, 331 of the vane module and the groove 220, 222, which has corresponding and precise dimensions, of the adjustment ring 203. The adjustment faces 316 of the cams 330, 331 come into contact with the grooves 220, 222 at both sides. The cams 330, 331 and grooves 220, 222 which are configured with different cross sections ensure the correct installation position of the vane module 300 and only one installation position is therefore possible.

[0094] In addition, the carrier system may have a carrier ring 202 which can be seen only partially in FIG. 1. FIG. 2 shows a greater view of the modular nozzle ring 100 from FIG. 1. The carrier ring 202 is configured to receive the adjustment ring 203. At an end at the bearing side, the carrier ring 202 has a circular recess in which the adjustment ring 203 is inserted. The bearing-side end of the carrier ring 202 and the circular recess can be seen, for example, in FIG. 4. The adjustment ring 203 can be inserted in the carrier ring 202 in this case without being fixed to the carrier ring 202. The carrier ring 202 has a large number of openings 210 which are used to receive the vane modules 300 (only one of the openings 210 is marked in FIG. 4). In this case, the vane can be reliably guided through with cylindrically configured external faces of the support structure 313 in the opening 210 of the carrier ring 202 and inside a remaining radial residual gap.

[0095] The carrier ring 202 further has a central opening for receiving a turbine wheel or a shaft. The carrier ring 202 is fixed by a housing portion 104 at the bearing side, as can be seen, for example, in FIGS. 1 and 2. Additionally, the carrier ring 202 can also be axially clamped between the bearing-side housing portion 104 and a flow-side turbine housing portion 112.

[0096] The modular nozzle ring can further comprise a clamping element 106. For example, FIGS. 1 and 2 show as embodiments of the clamping element a clamping spring 106. The clamping element 106 is configured to act counter to the adjustment ring 203 and the vane module 300. A force transmission from the carrier system 200, in particular the adjustment ring 203, to the clamping element 106 and from the clamping element 106 to the vane module 300 can thereby be brought about.

[0097] The clamping element 106 is arranged between the adjustment ring 203 and the baseplate 309 and/or arranged inside the gap or empty space which is formed between the support structure 313 and the vane shaft 310. The clamping element 106 is supported against the bearing-side end of the baseplate 309 of the vane module 300. The clamping element 106 is further supported against a flow-side support face of the adjustment ring 203.

[0098] FIG. 5 shows the assembly comprising the adjustment ring 203 and a large number of vane modules 300. The vane modules 300 are in this case fixed at the adjustment angles α by the connection to the grooves and secured by means of the securing elements 208. The clamping element 106 leads to a clamping in the assembly comprising the adjustment ring 203 and the vane modules 300.

[0099] FIG. 6 shows a combination of FIGS. 4 and 5, that is to say, the combination of the carrier ring 202, adjustment ring 203 and a large number of vane modules 300. A cutout of this assembly is shown in FIGS. 9 and 10 for a vane module 300.

[0100] FIG. 7 shows a cutout from FIG. 6 as an exploded illustration. The narrow dot-dash line illustrates the longitudinal axis and the two bold arrows indicate the bearing-side direction along the longitudinal axis.

[0101] FIG. 8 shows the adjustment ring 203 and the grooves 220, 222 which are contained therein and the vane shaft opening 221. FIG. 8 additionally indicates two different angle positions of the adjustment angle α by the two dot-dash lines. The vane shaft opening 221 can be configured identically for all the adjustment angles α. The position of the grooves 220, 222 requires an adaptation to the desired adjustment angle α. FIG. 11 also indicates the changes at different adjustment angles at the central vane module shown and in particular the differently arranged vane leaf 326. FIG. 12 shows a cutout of a rear view from FIG. 11. By way of example, the positions of the grooves 220, 222 are shown for two different adjustment angles α.

[0102] As illustrated, for example, in FIGS. 1 and 2, the modular nozzle ring 100 is fitted between the flow-side turbine housing portion 112 and the bearing-side housing portion 104 of the turbomachine. The bearing-side housing portion 104 can have a recess for receiving the vane shaft 310 which projects out of the adjustment ring 203 at the bearing side.

[0103] The axial spacing between the flow-side turbine housing portion 112 and the bearing-side housing portion 104 is configured to be shorter in this case than the axial spacing between the bearing-side end of the adjustment ring 203 and the flow-side end 327 of the vane leaf 326. The modular nozzle ring 100 is axially compressed by the assembly, whereby the load on the securing elements 208 is axially decreased and the adjustment ring 203 and the vane leaf 326 are each pressed against the housing portion.

[0104] The bearing-side end of the adjustment ring 203 is configured to be pressed against the counter-contour 117, 118 of the bearing-side housing portion 104. The flow-side end 327 of the vane leaf 326 is configured to be pressed against the channel contour 111 of the flow-side turbine housing portion 112.

[0105] The modular nozzle ring 100 is consequently axially clamped in the context of the configured resilient force. As a result of the resilient pressing, and in particular the pretensioning, the components of the modular nozzle ring 100 are axially clamped and are thus secured during operation with respect to vibration forces which involve wear. This pretensioning of the components reduces the risk of oscillating friction wear at the connection faces between the components of the nozzle ring and the housing, whereby a long service-life is enabled and a possible failure of the nozzle ring construction is prevented.

[0106] Although specific embodiments have been illustrated and described herein, it is within the scope of the present invention to combine or to modify the embodiments shown in a suitable manner without departing from the scope of protection of the present invention.

LIST OF REFERENCE NUMERALS

[0107] 100 Modular nozzle ring

[0108] 104 Bearing-side housing portion

[0109] 106 Clamping element

[0110] 111 Channel contour (of the flow-side turbine housing portion)

[0111] 112 Flow-side turbine housing portion

[0112] 117, 118 Counter-contour of the bearing-side housing portion

[0113] 120 Flow channel

[0114] 200 Carrier system

[0115] 202 Carrier ring

[0116] 203 Adjustment ring

[0117] 208 Securing element

[0118] 210 Axially extended opening of the carrier ring

[0119] 220 First groove

[0120] 221 Vane shaft opening

[0121] 222 Second groove

[0122] 300 Vane module

[0123] 309 Baseplate

[0124] 310 Vane shaft

[0125] 313 Support structure

[0126] 314, 315 Bearing-side ends of the connection elements or cams

[0127] 316 Adjustment faces

[0128] 317, 318 Support struts

[0129] 325 Securing groove

[0130] 326 Vane leaf

[0131] 327 Flow-side end of the vane leaf

[0132] 330 First connection element or first cam

[0133] 331 Second connection element or second cam