JP6239237B2 - Rotating assembly for turbine assembly - Google Patents

Description

  The subject matter disclosed herein relates to turbine systems, and more particularly to tip shrouds.

  Turbine systems utilize several rotating components or assemblies such as, for example, a compressor stage and a turbine stage that rotate at high speed when the turbine is in operation. In general, a stage includes a plurality of free flow blades extending radially outward from a central hub. Some blades include a shroud that limits vibration within the stage. The shroud is typically positioned at the tip portion of the blade, the middle portion of the blade, or both the middle and tip portions of the blade. The shroud is designed so that at high speeds or operating speeds the floating blades are interconnected to form an integral rotating member, but the blades can be interconnected even at low speeds and possibly starting from a 0 rpm starting position. During the interconnection of the blades, wear occurs due to slip when the tip portions are interconnected. At low speeds, such as on a turbine turning gear, the blades may not interconnect and often collide with each other. The collision between the blades can cause damage that shortens the useful life of the turbomachine.

  In order to minimize damage caused by blade impact, a hard surface coating is applied where there is a possibility of contact. The hard surface coating enhances resistance to wear that may occur during blade operation and improves the durability of accessible locations that are susceptible to impact. Conventionally, the hard surface coating is metal bonded to the blade, for example, by welding, brazing, or spraying. The use of a welding process that joins the hard surface joint to the blade generates a significant amount of local heat that, if not properly controlled, is wear and impact resistance at the joint of the material being joined. As well as other metallic properties. Excessive heat can also cause cracks in adjacent materials being manufactured.

U.S. Pat. No. 7,771,171

  In accordance with one aspect of the present invention, a rotating assembly for a turbine assembly includes an airfoil extending radially outward from an axial centerline and rotatable about the axial centerline. Including. Also included is a tip shroud that is integrally connected proximate to the radially outer tip of the airfoil. Further included is a substrate operably coupled to the tip shroud. Furthermore, at least one hard surface joining member fixed to the substrate is included.

  In accordance with another aspect of the present invention, a rotating assembly for a turbine assembly includes a plurality of rotating members extending radially outward from an axial centerline and rotatable about the axial centerline. including. Also included is a tip shroud that is integrally connected adjacent to the radially outer tip of at least one of the plurality of rotating members. Further included is a substrate operably coupled to the tip shroud. Furthermore, a hard surface bonding member having a base portion and a plurality of edges is included, the base portion is fixed to the substrate, and a portion of the substrate at least partially covers at least one of the plurality of edges. Enclose.

  In accordance with yet another aspect of the present invention, a rotating assembly for a turbine assembly includes an airfoil extending radially outward from an axial centerline and rotatable about the axial centerline. including. Also included is a tip shroud that is integrally connected proximate to the radially outer tip of the airfoil. Further included is a substrate operably coupled to the tip shroud and including a plurality of grooved portions. Furthermore, at least one hard surface bonding member that is mechanically interconnected and metal bonded to the substrate is included.

  These and other advantages and features will become apparent from the following description with reference to the drawings.

  The subject matter regarded as the invention is particularly pointed out and distinctly claimed in the claims appended hereto. The above and other features and advantages of the present invention will be apparent from the following detailed description with reference to the accompanying drawings.

1 is a partial schematic cross-sectional view of a turbomachine including a rotating assembly. FIG. 3 is a partial perspective view of a rotating assembly including a plurality of rotating components. The front perspective view of the tip shroud of a 1st embodiment. FIG. 4 is a rear elevation view of the tip shroud of FIG. 3. FIG. 3 is a perspective view of a substrate having a plurality of substantially “U” shaped grooves. FIG. 5 is a perspective view of a substrate having a plurality of substantially “V” shaped grooves. The front perspective view of the tip shroud of a 2nd embodiment.

  This detailed description explains exemplary embodiments, together with advantages and features of the invention, by way of example with reference to the drawings.

  Referring to FIG. 1, a turbomachine, shown in the form of a gas turbine engine and configured in accordance with an exemplary embodiment of the present invention, is indicated generally by the reference numeral 10. Engine 10 includes a compressor 12 and a plurality of combustor assemblies arranged in a can-annular array, one of which is indicated by reference numeral 14. As shown, the combustor assembly 14 includes an end cover assembly 16 that seals and at least partially defines the combustion chamber 18. A plurality of nozzles 20-22 are supported by the end cover assembly 16 and extend into the combustion chamber 18. The nozzles 20-22 receive fuel and pressurized air from the compressor 12 through a common fuel inlet (not shown). The fuel and pressurized air enter the combustion chamber 18 and are ignited to form a high temperature and high pressure combustion product or air stream that is used to drive the turbine 24. The turbine 24 includes a plurality of rotating assemblies or stages 26-28 that are operatively connected to the compressor 12 through a compressor / turbine shaft 30 (sometimes referred to as a rotor).

  In operation, air flows into the compressor 12 and is pressurized to high pressure gas. High pressure gas is supplied to the combustor assembly 14 and mixed with fuel (eg, process gas and / or synthesis gas (syngas)) in the combustion chamber 18. The fuel / air or combustible mixture ignites to form a high pressure hot combustion gas stream of about 538 ° C to 1593 ° C (1000 ° F to 2900 ° F). Alternatively, combustor assembly 14 can burn fuel including, but not limited to, natural gas and / or fuel oil. In any event, combustor assembly 14 sends a combustion gas stream to turbine 24, which converts thermal energy into mechanical rotational energy.

  Here, since each rotating assembly or step 26-28 is similarly formed, the present invention will be described with reference to FIG. 2 under conditions where the remaining steps (ie, steps 27 and 28) have a similar structure. It should be understood that the stage 26 constructed in accordance with the first exemplary embodiment will be described. It should also be understood that the present invention can be utilized in the stage of the compressor 12 or in other rotating assemblies that require wear and / or impact resistant surfaces. In any event, the step 26 is shown to include a plurality of rotating members such as airfoils 32 that extend radially outward from a central hub 34 that each has an axial centerline 35. The airfoil 32 is rotatable about an axial centerline 35 of the central hub 34 and includes a base portion 36 and a tip portion 38.

  The tip shroud 50 covers the bucket or throat portion (not shown separately) of the airfoil 32. Tip shroud 50 is designed to receive or nest the tip shroud on an adjacent rotating member to form a continuous ring that extends circumferentially around step 26. The continuous ring creates an outer flow path boundary to reduce gas path air leakage beyond the top of stage 26 (not separately labeled) and improve stage efficiency as well as overall turbine performance. In the illustrated exemplary embodiment, during high speeds or operating speeds, adjacent airfoils 32 are interconnected through their respective tip shrouds 50 by centrifugal forces generated by the operation of the turbine 24. It should be understood that interconnection can occur even during very low speed operation, so that wear due to blade slippage can occur due to operation during interconnection. However, at low speeds, such as in a turbine turning gear, the rotational force may be insufficient to establish interconnection and adjacent rotating members may collide with each other. The collision can cause the rotating member to wear, which can shorten the overall useful life of the turbine 24. In addition, handling of workers at multiple manufacturing and assembly stages may result in such collisions. For this purpose, the tip shroud 50 comprises a wear / impact member as will be described more fully below.

  With reference to FIGS. 3 and 4, the tip shroud 50 includes a tip blade 52 extending generally along an upper surface 54 of the tip shroud 50. The tip blade 52 includes a first surface 56 and an opposing second surface 58, and a first edge 60 and a second edge 62. In the illustrated exemplary embodiment, the tip blade 52 also includes one or more cutter members, such as a first cutter member 64 and a second cutter member 66. The first cutter member 64 is disposed adjacent to the first edge 60 of the tip blade 52 and on the second surface 58, while the second cutter member 66 is adjacent to the second edge 62. And disposed on the first surface 56. Both the first cutter member 64 and the second cutter member 66 are configured to engage corresponding partial surfaces. An example of such a corresponding partial surface is the inner surface of an outer casing (not shown) such as a honeycomb structure. Engagement of the first cutter member 64 and the second cutter member 66 with the corresponding partial surface removes material from the corresponding partial surface, resulting in a seal configuration proximate the outer area of the step 26.

  With reference to FIGS. 5 and 6, the substrate 70 is operably coupled to the tip shroud 50 and includes a mechanical interconnect pattern 72. In the illustrated embodiment, the mechanical interconnect pattern 72 is illustrated schematically as a plurality of grooves 74, but it should be understood that it may be formed from a plurality of grooves, protrusions, or combinations thereof. The plurality of grooves 74 may have several geometric shapes, including but not limited to, for example, grooves having a relatively “U” shape (FIG. 5) or “V” shape (FIG. 6). it can. The “U” and “V” shaped embodiments are merely illustrative of various shapes that can be used to form a plurality of grooves 74. Regardless of the mechanical interconnect pattern 72 and specifically the groove or protruding configuration, this configuration increases the surface area of the hard surface joints 80 that are interconnected when installed when compared to a simple plane.

  Referring again to FIGS. 3 and 4, the substrate 70 is illustrated as providing a joint between the tip shroud 50 and the hard surface joint 80. The substrate 70 provides a holding and / or bonding function as the hard surface bonding portion 80 with respect to the tip shroud 50. The hard surface joint 80 is operatively fixed to the substrate 70 by, for example, welding or brazing. As described above, the mechanical interconnect pattern 72 of the substrate 70 increases the available surface area and enhances structural integrity by forming a fixed portion of the hard surface joint 80 to the substrate 70. The hard surface bonding portion 80 includes a base portion 80 and a plurality of edge portions 84. It is contemplated that the substrate 70 can be secured to the hard surface joint 80 at the base 70, at least one of the plurality of edges 84, or a combination thereof. The substrate 70 further provides structural integrity by partially or completely enclosing one or more of the edges 84, and with other structures during operation, installation, or handling. The possibility of damage to the hard surface joint 80 due to the collision is reduced. The hard surface joint 80 may be formed, for example, from a pre-sintered preform (PSP) material, but it should be understood that various materials can be utilized in different applications.

  Referring to FIG. 7, a tip shroud 50 similar to that shown in FIGS. 3 and 4 is illustrated. The tip shroud 50 of FIG. 7 includes a single cutter member 90 disposed proximate to a central location between the first edge 60 and the second edge 62 of the tip blade 52. The cutter member 90 extends away from both the first surface 56 and the second surface 58 so that regardless of the deformation of the tip shroud 50 or tip blade 52 during operation, the cutter member 90 can be of honeycomb structure. The function of removing the material from the above-described corresponding partial surface can be achieved. In the illustrated embodiment, the substrate 70 extends outward from the first surface 56 at a location proximate to the second edge 62. Similarly, the additional substrate portion can extend outward at various other locations, such as away from the second surface 58 at a location proximate to the first edge 60.

  Although the invention has been described in detail with respect to only a limited number of embodiments, it is to be understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate many variations, modifications, substitutions, or equivalent arrangements not described above, which correspond to the spirit and scope of the invention. In addition, while various embodiments of the invention have been described, it is to be understood that aspects of the invention can include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

10 Engine 12 Compressor 14 Combustor assembly 16 End cover 18 Combustion chamber 20-22 Nozzle 24 Turbine 26-28 Rotating assembly 30 Compressor / turbine shaft 32 Airfoil 34 Hub 35 Axial centerline 36 Base 38 Tip portion 50 Tip shroud 52 Tip blade 54 Top surface 56 First surface 58 Opposing second surface 60 First edge 62 Second edge 64 First cutter member 66 Second cutter member 72 Mechanical mutual Connecting pattern 74 Groove 80 Hard surface joint portion 82 Base portion 84 Edge portion 90 Single cutter member

Claims (20)

A rotating assembly for a turbine assembly,
An airfoil extending radially outward from an axial centerline and rotatable about the axial centerline;
A tip shroud integrally connected proximate to a radially outer tip of the airfoil;
At least one hard surface joining member joined to the tip shroud;
A substrate that is metal bonded to the at least one hard surface bonding member ;
A rotating assembly. The tip shroud is
A tip blade having a first surface, a second surface opposite the first surface, a first edge and a second edge;
A first cutter member disposed proximate to the first edge and the second surface;
The rotating assembly according to claim 1, comprising a second cutter member disposed proximate to the second edge and the first surface. The tip shroud includes a relatively flat tip blade having a first edge and a second edge, and the substrate is proximate to at least one of the first edge and the second edge. The rotating assembly according to claim 1, comprising a filled portion. The at least one hard surface joining member includes a base portion and a plurality of edges, and a portion of the substrate at least partially surrounds at least one of the plurality of edges . A rotating assembly according to any one of the above. The rotary assembly according to any of claims 1 to 4, wherein the at least one hard surface joining member is formed from a pre-sintered preform material. The rotary assembly according to any one of claims 1 to 5 , wherein the substrate includes a plurality of grooved portions.   The rotating assembly of claim 6, wherein the plurality of grooved portions are relatively U-shaped.   The rotating assembly of claim 6, wherein the plurality of grooved portions are relatively V-shaped. The rotating assembly according to claim 1, wherein the base member includes a plurality of protrusions. The rotating assembly according to any of claims 1 to 9, wherein the at least one hard surface joining member is brazed to the substrate. A rotating assembly for a turbine assembly,
A plurality of rotating members extending radially outward from an axial centerline and rotatable about the axial centerline;
A tip shroud integrally connected in proximity to a radially outer tip of at least one of the plurality of rotating members;
A hard surface bonding member bonded to the tip shroud, having a base portion and a plurality of edges;
A base material metal- bonded to the hard surface bonding member ;
A rotating assembly, wherein the base portion is fixed to the substrate, and a portion of the substrate at least partially surrounds at least one of the plurality of edges. A tip blade having a first surface, a second surface opposite to the first surface, a first edge and a second edge;
A first cutter member disposed proximate to the first edge and the second surface;
The rotating assembly according to claim 11, comprising a second cutter member disposed proximate to the second edge and the first surface. The tip shroud includes a relatively flat tip blade having a first edge and a second edge, and the substrate is proximate to at least one of the first edge and the second edge. 13. A rotating assembly according to claim 11 or 12, comprising a filled fillet portion. The rotary assembly according to any one of claims 11 to 13, wherein the hard surface joining member is formed from a pre-sintered preform material. The rotating assembly according to any of claims 11 to 14, wherein the substrate includes a plurality of grooved portions. The rotating assembly according to claim 11, wherein the base member includes a plurality of protrusions. A rotating assembly for a turbine assembly,
An airfoil extending radially outward from an axial centerline and rotatable about the axial centerline;
A tip shroud integrally connected proximate to a radially outer tip of the airfoil;
At least one hard surface joining member coupled to the tip shroud and a substrate metal- bonded to the at least one hard surface joining member and including a plurality of grooved portions;
A rotating assembly.   The rotating assembly of claim 17, wherein the plurality of grooved portions are relatively U-shaped.   The rotating assembly of claim 17, wherein the plurality of grooved portions are relatively V-shaped. 20. A rotating assembly as claimed in any of claims 17 to 19, wherein the at least one hard surface joining member is formed from a pre-sintered preform material.