JP2012082827A - Axial retention device for turbine system - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an improved retention device to retain a seal device and/or a turbine component in a support structure.SOLUTION: An axial retention device (50) for a turbine (16) is disclosed. The axial retention device (50) includes a latch (52) associated with a mating surface of one of the turbine component (34) and the support structure (32). The latch (52) has an outward bias and includes an axial load surface (70). The axial retention device (50) further includes a pocket (54) defined in a mating surface of the other of the turbine component (34) and the support structure (32). The pocket (54) is configured to accept the latch (52) therein and includes a mating axial load surface (72). Engagement of the latch (52) and the pocket (54) allows the axial load surface (70) and the mating axial load surface (72) to interact, preventing axial movement of the turbine component (34) with respect to the support structure in at least one direction.

Description

  The subject matter disclosed herein relates generally to turbine systems and, more particularly, to axial retention devices that retain turbine components within a turbine system.

  Turbine systems are widely used in fields such as power generation. For example, a conventional gas turbine system includes a compressor, a combustor, and a turbine. During operation of a gas turbine system, various components within the system may be exposed to high temperature flows, resulting in failure of the components. The high temperature flow generally results in improved performance, efficiency, and power output of the gas turbine system, so parts exposed to the high temperature flow must be cooled so that the gas turbine system can operate at high temperatures. Thus, the cooling medium can flow through the gas turbine system to cool various components.

  In addition, the hot flow and the coolant flow should generally be confined to each other to obtain optimum performance and efficiency of the turbine system. For example, in a turbine of a turbine system, turbine components are generally provided with a cooling medium independent of the hot stream to prevent inhalation of the hot stream into the interior during operation. In addition, the sealing device can be utilized to protect turbine components from high temperature flow leakage and to prevent cooling medium leakage.

  In many cases, the sealing device and turbine components are mounted on an annular support structure in the turbine. The sealing device and turbine component can be positioned circumferentially and axially relative to each other to prevent high temperature flow leakage and cooling medium leakage. In many cases, however, the sealing device and / or turbine component may be shifted, slid, or disengaged relative to the support structure, possibly allowing internal leakage or leakage therefrom. . This leakage and / or leakage can reduce the performance and efficiency of the turbine system and can also be detrimental to the system. Thus, in most cases, the sealing device and turbine components need not be shifted, slid or disengaged from the support structure.

  Accordingly, there is a need in the art for an improved retention device for retaining the seal device and / or turbine component within the support structure. For example, a sealing device and / or an axial holding device that prevents axial movement of the turbine component relative to the support structure are advantageous.

US Pat. No. 7,420,411

  Aspects and advantages of the invention are set forth in part in the following description, or may be obvious from the description, or may be learned by practice of the invention.

  In one embodiment, an axial retention device for a turbine is disclosed. An axial retainer includes a latch coupled to a mating surface of one of the turbine component and the support structure. The latch has an outward bias and includes an axial load surface. The axial retainer further includes a pocket defined in the mating surface of the other of the turbine component and the support structure. The pocket is configured to receive the latch therein and includes an interlocking axial load surface. The engagement of the latch and pocket allows the axial load surface and the mating axial load surface to interact and prevents axial movement of the turbine component relative to the support structure in at least one direction.

  These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the specification, serve to explain the principles of the invention.

Schematic of a turbine system. 1 is a side sectional view of a turbine of a turbine system according to an embodiment of the present disclosure. 1 is a side sectional view of a part of a turbine of a turbine system according to an embodiment of the present disclosure. FIG. 3 is an enlarged perspective view of a support structure and two turbine components according to an embodiment of the present disclosure. FIG. 3 is a cross-sectional view of an axial holding device according to an embodiment of the present disclosure. Sectional drawing of the axial direction holding | maintenance apparatus which concerns on another embodiment of this indication.

  DETAILED DESCRIPTION OF THE INVENTION This specification, with reference to the accompanying drawings, describes the complete and effective disclosure of the present invention including its best mode to those skilled in the art. Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of illustration and not limitation of the invention. Indeed, those skilled in the art will appreciate that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For example, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Accordingly, the present invention is intended to protect such modifications and variations as falling within the scope of the appended claims and their equivalents.

  FIG. 1 is a schematic diagram of a turbine system 10. Although the turbine system 10 described herein can generally be a gas turbine system, the turbine system 10 of the present disclosure is not limited to a gas turbine system and is not limited to any suitable including a steam turbine. It should be understood that such turbine systems are within the scope and spirit of the present disclosure.

  Accordingly, the illustrated system can include a compressor 12, a combustor 14, and a turbine 16. The compressor 12 and the turbine 16 can be coupled by a shaft 18. The shaft 18 can be a single shaft or a plurality of shaft segments that are joined together to form the shaft 18.

  Turbine 16 may include a plurality of turbine stages. For example, in one embodiment, the turbine 16 may have three stages as shown in FIG. For example, the first stage of the turbine 16 may include a plurality of circumferentially spaced nozzles 21 and buckets 22. The nozzle 21 can be arranged and fixed circumferentially around the shaft 18. The bucket 22 is circumferentially disposed about the shaft 18 and can be coupled to the shaft 18. The second stage of the turbine 16 may include a plurality of circumferentially spaced nozzles 23 and buckets 24. The nozzles 23 can be arranged and fixed around the shaft 18 at circumferential intervals. Bucket 24 may be circumferentially disposed about shaft 18 and coupled to shaft 18. The third stage of the turbine 16 may include a plurality of circumferentially spaced nozzles 25 and buckets 26. The nozzles 25 can be disposed and fixed circumferentially spaced around the shaft 18. Bucket 26 may be circumferentially disposed about shaft 18 and coupled to shaft 18. Various stages of the turbine 16 may be disposed in the path of the hot gas stream 28 in the turbine 16. It should be understood that the turbine 16 is not limited to three stages and can have any suitable number of stages.

  As shown in FIGS. 3 and 4, the plurality of annularly arranged sealing devices 30 includes a plurality of buckets (eg, buckets 22 or 24) and a plurality of adjacent buckets (eg, buckets 24 or 26). It can be provided in between. The sealing device 30 is provided to form an outer boundary for the path of the gas stream 28, thus preventing the gas stream 28 from moving through the outer boundary, and further, external to the path of the gas stream 28. A cooling flow (not shown) can be prevented from moving into the path through the outer boundary. The sealing device 30 can further interact with a plurality of nozzles, such as nozzles 21, 23, or 25, as shown in FIG. It should be understood that the sealing device 30 need not be designed as shown in FIGS. 3 and 4, but rather that any suitable device is within the scope and spirit of the present disclosure.

  Buckets 22, 24, 26 and seal device 30 must be retained within turbine 16. Accordingly, various support structures 32 may be provided in the turbine 16 to engage and support various turbine components 34, such as the sealing device 30 and / or buckets 22, 24, 26. The support structure 32 can be, for example, a rotor disk 36 configured to mate with the buckets 22, 24, 26. Alternatively, the support structure 32 can be, for example, a spacer rim structure configured to mate with the seal device 30.

  As shown, the turbine component 34 and the support structure 32 may include a mating appendage 40 and a cavity 42 for mating the turbine component 34 and the support structure 32 together. For example, in some embodiments, the appendage 40 can be a dovetail and the cavity 42 can be shaped and sized to receive the dovetail therein. In general, the turbine component 34 is engaged with the support structure 32 by sliding the appendage 40 approximately along the axial axis 44 into the cavity 42 as shown in FIG. Engaging the appendage 40 within the cavity 42 prevents movement of the turbine component 34 relative to the support structure 32 in substantially radial and tangential directions, but turbine component 34 relative to the support structure 32 in substantially axial direction. Cannot be prevented from moving. For example, when the appendage 40 is engaged with the cavity 42, the appendage is free to move along the axial axis 44 in the first direction 46 or the second direction 48.

  Accordingly, as shown in FIGS. 4 to 6, the axial holding device 50 is provided for holding the turbine component 34 in the axial direction in the support structure 32. The axial retaining device 50 includes a latch 52 and a pocket 54. In general, the latch 52 can be coupled to one of the turbine component 34 and the support structure 32, and the pocket 54 can be defined in the other of the turbine component 34 and the support structure 32. For example, in the exemplary embodiment, latch 52 can be coupled to support structure 32 and pocket 54 can be defined in turbine component 34. In an alternative embodiment, the latch 52 can be coupled to the turbine component 34 and the pocket 54 can be defined within the support structure 32.

  Further, as discussed above, a plurality of turbine components 34 may be arranged around the support structure 32 in an annular array. In some embodiments, each turbine component 34 includes an independent latch 52, or an independent pocket 54 configured to mate with the independent latch 52 or an independent pocket 54 included or defined within the support structure 32. Can be defined. However, in other embodiments, as shown in FIG. 4, two adjacent turbine components 34 may each include an independent latch 52 or may define an independent pocket 54, Both can be configured to mate with one latch 52 or pocket 54 contained or defined in the support structure 32.

  Turbine component 34 can define mating surface 56 and support structure 32 can define mating surface 58. The mating surfaces 56, 58 can be defined on the appendage 40 and in the cavity 42, or can be defined adjacent to the appendage 40 and the cavity 42, as shown in FIGS. . The mating surfaces 56, 58 generally engage together when the turbine component 34 and the support structure 32 are engaged with each other. The latch 52 may be coupled to the mating surface 56 or 58 of the turbine part 34 or the support structure 32, and the pocket 54 may be defined at the other of the mating surfaces 56 or 58 of the turbine part 34 or the support structure 32. Can do.

  The pocket 54 according to the present disclosure can be configured to receive the latch 52 therein. For example, the pocket 54 can be sized and shaped to accommodate at least a portion of the latch 52 therein, and further engages and interacts with the latch 52 as discussed below. It can have various features.

  The latch 52 according to the present disclosure can have a generally outward bias. “Outwardly” refers to a direction that is generally radially away from an associated base component, such as turbine component 34 or support structure 32. For example, in some exemplary embodiments, the latch 52 can pivot about a pivot point 60 as shown in FIG. Thus, the latch 52 can be biased outward about the pivot point 60. In other exemplary embodiments, as shown in FIG. 6, the latch 52 may simply have a generally radially outward bias.

  Further, in some exemplary embodiments, the axial retainer 50 can include a spring 62 or a plurality of springs 62. The spring 62 can provide an outward bias. In embodiments in which the latch 52 has a pivot point 60, the spring 62 can be positioned at or spaced from the pivot point 60, for example. However, it should be understood that the outward bias need not be provided by a spring, but rather the outward bias may be provided by any suitable bias, tension, or preload device. .

  In the exemplary embodiment, as shown in FIGS. 5-6, the mating surface 56 or 58 of the turbine component 34 or support structure 32 coupled to the latch 52 may be defined in the cavity 64. The latch 52 can be mounted in the cavity 64. Thus, in the exemplary embodiment, a portion of the latch 52 can protrude from the mating surface 56 or 58 when the latch 52 is biased outward. Further, in the exemplary embodiment, as discussed below, when the latch 52 is retracted, the uppermost portion of the latch 52 may be located at or below the mating surface 56 or 58. However, in an alternative embodiment, the top portion of the latch 52 can remain above the mating surface 56 or 58 when retracted. The cavity 64 can further include a side surface 66. The side surface 66 can interact with the contact point 68 of the latch 52 strip to prevent movement of the latch 52 along the axial axis 44.

  As shown, the latch 52 can include an axial load surface 70 and the pocket 54 can include a mating axial load surface 72. As shown in FIGS. 5 and 6, for example, the axial load surfaces 70, 72 can be substantially planar sides of the latch 52 and pocket 54, which can be substantially perpendicular to the axial axis 44. it can. However, it should be understood that the axial load surfaces 70, 72 can have any suitable profile and / or orientation. In general, the engagement of the latch 52 and the pocket 54 allows the axial load surfaces 70, 72 to interact and prevent axial movement of the turbine component 34 relative to the support structure 32 in at least one direction. Will be able to. For example, the interaction of the axial load surfaces 70, 72 can prevent axial movement of the turbine component 34 in the first direction 46 or the second direction 48, as shown in FIGS. 5 and 6.

  In some embodiments, as shown in FIG. 5, the axial retainer 50 can further include a stop 74 associated with one of the turbine component 34 or the support structure 32. The stop 74 interacts with the turbine component 34 or the other of the support structure 32 to prevent axial movement of the turbine component 34 in another direction relative to the support structure 32, and thereby in two directions. It can be configured to prevent axial movement. For example, the stop 74 can have a substantially planar side surface and can be substantially perpendicular to the axial axis 44. However, it should be understood that the stop 74 can have any suitable profile and / or orientation. In general, the engagement of the latch 52 and the pocket 54 allows the stop to interact with the turbine component 34 or the other side of the support structure 32, which provides axial movement of the turbine component 34 relative to the support structure 32. It becomes possible to block in at least one direction. For example, the interaction of the stop 74 with the turbine part 34 or the other of the support structure 32 prevents axial movement of the turbine part 34 in the second direction 48 or the first direction 46 as shown in FIG. can do.

  In another embodiment, as shown in FIG. 6, the latch 52 can include a plurality of axial load surfaces 70 and the pocket 54 can include a plurality of mating axial load surfaces 72. In general, the engagement of the latch 52 and the pocket 54 allows the axial load surfaces 70, 72 to interact and prevent axial movement of the turbine component 34 relative to the support structure 32 in two directions. become able to. For example, the interaction of the axial load surfaces 70, 72 can prevent axial movement of the turbine component 34 in both the first direction 46 and the second direction 48, as shown in FIGS. 5 and 6. .

  In some embodiments, one of the turbine component 34 and the support structure 32 that do not include the latch 52 may define an access hole 76, as shown in FIGS. The access hole 76 provides access to the latch 52 to release the latch 52 from the pocket 54 and is relative to the support structure 32 in at least one direction, such as the first direction 46 or the second direction 48. An axial movement of the turbine component 34 may be allowed. For example, the access hole 76 can allow the latch 52 to retract from the pocket 54 and thus provide access to disengage the axial load surfaces 70, 72. In one embodiment, the access hole 76 can be placed through the access hole 76 to interact with a tool such as a rod or, for example, an appendage, with the latch 52 and cause the latch 52 to retract.

  Further, in some embodiments shown in FIGS. 5 and 6, the latch 52 can include a sealing surface 78. The sealing surface 78 can be configured to seal the access hole 76 when the latch 52 and the pocket 54 are engaged. For example, the sealing surface 78 can be substantially parallel to the opening of the access hole 76 adjacent to the latch 52 and / or perpendicular to the central axis of the access hole 76. However, it should be understood that the sealing surface 78 can have any suitable profile and / or orientation sufficient to seal the access hole 76 when the latch 52 and pocket 54 are engaged. When the latch 52 and the pocket 54 are engaged, the sealing surface 78 abuts the opening of the access hole 76 adjacent to the latch 52, and thus the access hole 76 can be totally sealed. The sealing surface 78 may advantageously prevent or reduce the possibility of high temperature flow leakage and / or cooling medium leakage through the access hole 76 between the turbine component 34 and the support structure 32.

  Advantageously, the axial retention device 50 of the present disclosure can prevent axial movement of the turbine component 34 relative to the support structure 32 in one or more directions. By preventing axial movement, the possibility of hot flow leakage and / or cooling medium leakage between the turbine component 34 and the support structure 32 may be advantageously prevented or reduced.

  This written description discloses the invention using examples, including the best mode, and further includes any person skilled in the art to make and use any device or system and any method of inclusion. It is possible to carry out. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other embodiments are within the scope of the invention if they have structural elements that do not differ from the words of the claims, or if they contain equivalent structural elements that have slight differences from the words of the claims. It shall be in

DESCRIPTION OF SYMBOLS 10 Gas turbine system 12 Compressor 14 Combustor 16 Turbine 18 Shaft 21 First stage nozzle 22 First stage bucket 23 Second stage nozzle 24 Second stage bucket 25 Third stage nozzle 26 Third stage bucket 28 Hot gas flow 30 Seal Device 32 Support structure 34 Turbine component 36 Rotor disk 38 Spacer rim structure 40 Attachment 42 Cavity 44 Axial axis 46 First direction 48 Second direction 50 Axial holding device 52 Latch 54 Pocket 56 Mating surface (turbine component)
58 mating surface (support structure)
60 pivot point 62 spring 64 cavity 66 side surface 68 contact point 70 axial load surface (latch)
72 Axial load surface (pocket)
74 Stopping portion 76 Access hole 78 Seal surface

Claims (15)

An axial holding device (50) for the turbine (16),
A latch (52) coupled to one mating surface (56, 58) of the turbine component (34) and the support structure (32) has an outward bias and an axial load surface (70). A latch (52) comprising:
A meshing axial load surface defined on the other mating surface (56, 58) of the turbine component (34) and the support structure (32) and configured to receive the latch (52) therein. A pocket (54) including (72);
And the engagement of the latch (52) and the pocket (54) allows the axial load surface (70) and the mating axial load surface (72) to interact, and includes at least one An axial retainer (50) in which axial movement of the turbine component (34) relative to the support structure (32) in the direction is prevented.   One mating surface (56, 58) of the turbine part (34) and support structure (32) coupled to the latch (52) defines a cavity (64) therein, the latch (52). The axial retainer (50) of any preceding claim, wherein the is mounted in the cavity (64).   The axial retention device (50) according to claim 1 or 2, wherein the latch (52) is pivotable about a pivot point (60).   The axial retainer (50) of any preceding claim, further comprising a spring (62) that provides an outward bias.   A stop (74) associated with one of the turbine component (34) and the support structure (32) is further provided, the stop (74) being connected to the turbine component (34) and the support structure ( 32) interacting with the other of 32) and configured to prevent axial movement of said turbine part (34) relative to said support structure (32) in two directions. An axial holding device (50) according to any one of the preceding claims.   The axial load surface (70) is a plurality of axial load surfaces (70), the meshing axial load surface (72) is a plurality of meshing axial load surfaces (72), the latch (52) and The engagement of the pocket (54) allows the plurality of axial load surfaces (70) and the plurality of meshing axial load surfaces (72) to interact, and the support structure in two directions. The axial holding device (50) according to any of the preceding claims, wherein axial movement of the turbine part (34) relative to a body (32) is prevented.   The other of the turbine component (34) and the support structure (32) defines an access hole (76) that releases the latch (52) from the pocket (54). The access to the latch (52) for allowing the turbine component (34) to move axially relative to the support structure (32) in at least one direction. An axial holding device (50) according to any one of the preceding claims.   The latch (52) of claim 7, comprising a sealing surface (78) configured to seal the access hole (76) when the latch (52) and the pocket (54) are engaged. Axial holding device (50).   The latch (52) is coupled to the mating surface (58) of the support structure (32), and the pocket (54) is defined in the mating surface (56) of the turbine component (34); 9. Axial holding device (50) according to any one of the preceding claims. A support structure (32) having a mating surface (58);
At least one turbine component (34) having a mating surface (56);
A latch (52) coupled to one mating surface (56, 58) of the at least one turbine component (34) and the support structure (32), having an outward bias and axial A latch (52) including a load surface (70);
An engagement shaft defined in the other mating surface (56, 58) of the at least one turbine component (34) and the support structure (32) and configured to receive the latch (52) therein. A pocket (54) including a directional load surface (72);
With
Engagement of the latch (52) and the pocket (54) allows the axial load surface (70) and the meshing axial load surface (72) to interact, in at least one direction. A turbine (16) in which axial movement of the at least one turbine component (34) relative to the support structure (32) is prevented.   One mating surface (56, 58) of the at least one turbine component (34) and the support structure (32) coupled to the latch (52) defines a cavity (64) therein, The turbine (16) of claim 10, wherein the latch (52) is mounted within the cavity (64).   The turbine (16) according to claim 10 or 11, wherein the latch (52) is pivotable about a pivot point (60).   The turbine (16) according to any one of claims 10 to 12, further comprising a spring (62) that provides an outward bias.   It further comprises a stop (74) associated with one of the at least one preceding turbine component (34) and the support structure (32), said stop (74) being said at least one turbine component (34). ) And the other of the support structure (32), and configured to prevent axial movement of the turbine component (34) relative to the support structure (32) in two directions. A turbine (16) according to any one of claims 10 to 13.   The other of the at least one turbine component (34) and the support structure (32) defines an access hole (76), and the access hole (76) extends from the pocket (54) to the latch (52). 11) to provide access to the latch (52) for releasing and enabling axial movement of the turbine component (34) relative to the support structure (32) in at least one direction. A turbine (16) according to any one of the preceding claims.