Patent Application
20130272888
The subject matter disclosed herein relates to turbomachines, and, more particularly, a turbomachine blade tip shroud and a casing in a generally parallel configuration.
Turbomachines include compressors and turbines, such as gas turbines, steam turbines, and hydro turbines. Generally, turbomachines include a rotor, which may be a shaft or drum, to which turbomachine blades are attached. Certain turbomachine blades may include tip shrouds and/or seals to meet structural and/or performance requirements. For example, the tip shrouds and/or seals may reduce flow leakage through the cavity or passage between the turbomachine blades and a stationary structural component, such as a static shroud, surrounding the turbomachine blades and the rotor. Existing tip shroud and seal design may not adequately limit or reduce flow leakage between the turbomachine blades and the stationary structural component surrounding the turbomachine blades and the rotor, which may result in a reduction in turbomachine efficiency. Similarly, existing stationary structural component design may not adequately limit or reduce flow leakage between the turbomachine blades and the stationary structural component surrounding the turbomachine blades and the rotor.
Certain embodiments commensurate in scope with the originally claimed invention are summarized below. These embodiments are not intended to limit the scope of the claimed invention, but rather these embodiments are intended only to provide a brief summary of possible forms of the invention. Indeed, the invention may encompass a variety of forms that may be similar to or different from the embodiments set forth below.
In a first embodiment, a turbomachine includes a turbomachine blade and a stationary structural component. The turbomachine blade includes a tip shroud having a leading edge portion where the leading edge portion has a first surface. The stationary structural component is disposed about the turbomachine blade and includes a corresponding portion corresponding to the leading edge portion of the tip shroud, where the corresponding portion has a second surface, where the first surface and the second surface have generally parallel contours.
In a second embodiment, a system comprises a turbine having a turbine blade. The turbine blade includes a tip shroud having a first surface. The turbine further includes a stationary structural component disposed about the turbine blade, where the stationary structural component has a second surface disposed about the first surface of the tip shroud, where the first surface and the second surface have generally parallel contours.
In a third embodiment, a turbine includes a turbine blade and a stationary structural component. The turbine blade includes a tip shroud having a first surface, where the first surface has a leading edge surface of a leading edge overhang extending in an upstream direction from a leading edge of the turbine blade, a nose portion, and an upstream surface of a rail of a labyrinth seal of the tip shroud, where the leading edge surface of the leading edge overhang is adjacent the nose portion, and the nose portion is adjacent the upstream surface of the rail. The structural component is disposed about the turbine blade, where the stationary structural component includes a second surface, where the second surface has a first corresponding portion disposed generally opposite the leading edge surface of the leading edge overhang, a second corresponding portion disposed generally opposite the nose portion, and a third corresponding portion disposed generally opposite the upstream surface of the rail, where the first corresponding portion is adjacent the second corresponding portion and the second corresponding portion is adjacent the third corresponding portion, and where the first corresponding portion and the leading edge surface of the leading edge overhang have generally parallel contours, the second corresponding portion and the nose portion have generally parallel contours, and the third corresponding portion and the upstream surface of the rail have generally parallel contours.
These and other features, aspects, and advantages of the present invention will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:
One or more specific embodiments of the present invention will be described below. In an effort to provide a concise description of these embodiments, all features of an actual implementation may not be described in the specification. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be appreciated that such a development effort might be complex and time consuming, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure.
When introducing elements of various embodiments of the present invention, the articles “a,” “an,” “the,” and “said” are intended to mean that there are one or more of the elements. The terms “comprising,” “including,” and “having” are intended to be inclusive and mean that there may be additional elements other than the listed elements.
The disclosed embodiments include a turbomachine blade tip shroud and a turbomachine stationary structural component, where a leading edge portion of the turbomachine blade tip shroud and a corresponding portion of the turbomachine stationary structural component have a generally parallel configuration. As discussed in detail below, the generally parallel configuration between the leading edge portion of the turbomachine blade tip shroud and the corresponding portion of the turbomachine stationary structural component may provide a more tailored clearance between the turbomachine blade tip shroud and the turbomachine stationary structural component. This may reduce the leakage of flow escaping through the clearance or cavity between the turbomachine blade tip shroud and the turbomachine stationary structural component. Additionally, the more tailored clearance may also reduce the mixing and/or flow churning loss in the clearance or cavity. As a result, a turbomachine having blades with the described turbomachine blade tip shroud and stationary structural component may experience improved performance and efficiency. While the disclosed generally parallel configuration between the turbomachine blade tip shroud and the turbomachine stationary structural component may be utilized with turbomachine blades of a variety of turbomachines (e.g., turbines and compressors), the following discussion describes a generally parallel configuration between blade tip shrouds and a stationary structural component in the context of a turbine, such as a gas turbine or a steam turbine. However, it is important to note that the following discussion is not intended to limit the application of the generally parallel configuration to turbines.
Turning now to the drawings,
In the illustrated embodiment, the compressor 12 includes compressor blades 28. The compressor blades 28 within the compressor 12 are coupled to the rotor 24, and rotate as the rotor 24 is driven into rotation by the turbine 18, as discussed above. As the compressor blades 28 rotate within the compressor 12, the compressor blades 28 compress air from an air intake into pressurized air 30, which is routed to the combustors 14, the fuel nozzles 16, and other portions of the gas turbine system 10. The fuel nozzles 14 then mix the pressurized air and fuel to produce a suitable fuel-air mixture, which combusts in the combustors 14 to generate the combustion gases 20 to drive the turbine 18. Further, the rotor 24 may be coupled to a load 31, which may be powered via rotation of the rotor 24. For example, the load 31 may be any suitable device that may generate power via the rotational output of the gas turbine system 10, such as a power generation plant or an external mechanical load. For instance, the load 31 may include an electrical generator, a propeller of an airplane, and so forth. In the following discussion, reference may be made to various directions, such as an axial direction or axis 32, a radial direction or axis 34, and a circumferential direction or axis 36 of the turbine 18.
As mentioned above, the tip shroud 50 is disposed at the outer radial end 52 of the turbine blade 22. As will be appreciated, the tip shroud 50 may serve to block flow leakage between the outer radial end 52 of the turbine blade 22 and the stationary structural component 23. In other words, the tip shroud 50 may help block a fluid flow 58 (e.g., a flow of the combustion gases 20 from the combustor 14 of
In the illustrated embodiment, the tip shroud 50 includes a nose portion 72. As shown, the nose portion 72 of the tip shroud 50 and the remaining portion of the tip shroud 50 (i.e., the portion of the tip shroud 50 not including the nose portion 72) are not collinear. In other words, the nose portion 72 of the tip shroud 50 and the remaining portion of the tip shroud 50 form an angle 74, which may be less than 180 degrees. For example, the angle 74 between the nose portion 72 of the tip shroud 50 and the remaining portion of the tip shroud 50 may be approximately 1 to 180, 2 to 160, 3 to 140, 4 to 120, 5 to 100, 6 to 80, 7 to 60, or 8 to 40 degrees. In the illustrated embodiment, the nose portion 72 of the tip shroud 50 is generally parallel with the rotational axis 25 of the turbine 18, and the remaining portion of the tip shroud 50 is generally oriented at an angle 76 to the rotational axis 25 of the turbine 18. For example, the angle 76 between the remaining portion of the tip shroud 50 and the rotational axis 25 of the turbine 18 may be approximately 0 to 75, 5 to 60, 10 to 45, or 15 to 30 degrees. As discussed in detail below, in other embodiments, the nose portion 72 of the tip shroud 50 and the remaining portion of the tip shroud 50 may be collinear. For example, the nose portion 72 of the tip shroud 50 and the remaining portion of the tip shroud 50 may be collinear and may form a substantially constant angle with the rotational axis 25 of the turbine 18 (see, e.g.,
Additionally, as shown, the nose portion 72 of the tip shroud 50 includes a leading edge overhang 78. More specifically, the leading edge overhang 78 of the nose portion 72 of the tip shroud 50 extends over a leading edge 80 of the turbine blade 22 in an upstream axial direction 82. In this manner, the tip shroud 50 may further block the fluid flow 58 from passing from the leading edge 60 to the trailing edge 62 of the turbine blade 22 through the clearance 64 between the outer radial end 52 of the turbine blade 22 and the stationary structural component 23. For example, the leading edge overhang 78 may direct the fluid flow 58 down the turbine blade 22 generally in the radial direction 34, as indicated by arrow 84, or across the turbine blade 22 in the axial direction 32, as indicated by arrow 86.
As mentioned above, the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 have a generally parallel configuration. For example, in the illustrated embodiment, a leading edge 100 of the leading edge overhang 78 corresponds with a first corresponding portion 102 of the stationary structural component 23. As shown, the leading edge 100 of the leading edge overhang 78 and the first corresponding portion 102 each have a generally vertical orientation. In other words, the leading edge 100 of the leading edge overhang 78 and the first corresponding portion 102 each extend generally in the radial direction 34. Additionally, the first corresponding portion 102 of the stationary structural component 23 is disposed generally upstream from the leading edge 100 of the leading edge overhang 78, thereby creating an opening 104 of the clearance 64 between the tip shroud 50 and the stationary structural component 23.
The nose portion 72 of the tip shroud 50 corresponds with a second corresponding portion 106 of the stationary structural component 23. As previously discussed, the nose portion 72 of the tip shroud 50 is generally parallel with the rotational axis 25 of the turbine 18. Additionally, the second corresponding portion 106 of the stationary structural component 23 is generally parallel with the rotational axis 25 of the turbine 18. Furthermore, as similarly discussed above, the second corresponding portion 106 of the stationary structural component 23 is disposed generally upstream from the nose portion 72 of the tip shroud 50. Additionally, the nose portion 72 of the tip shroud 50 and the second corresponding portion 106 of the stationary structural component 23 are disposed generally opposite one another across the clearance 64 between the tip shroud 50 and the stationary structural component 23, thereby creating a generally parallel configuration between the nose portion 72 of the tip shroud 50 and the second corresponding portion 106 of the stationary structural component 23.
As discussed above, the remaining portion of the tip shroud 50 (i.e., the portion of the tip shroud 50 not including the nose portion 72) is generally disposed at the angle 76 relative to the rotational axis 25 of the turbine blade 18. For example, an intermediate portion 108 (i.e., the portion of the tip shroud 50 between the nose portion 72 of the tip shroud 50 and the rail 68 of the labyrinth seal 66) is generally oriented at the angle 76. The intermediate portion 108 of the tip shroud 50 corresponds to a third corresponding portion 110 of the stationary structural component 23, which also is generally oriented at the angle 76 relative to the rotational axis 25 of the turbine 18. Moreover, as similarly discussed above, the third corresponding portion 110 of the stationary structural component 23 is disposed generally upstream from the intermediate portion 108 of the tip shroud 50. In this manner, the intermediate portion 108 of the tip shroud 50 and the third corresponding portion 110 of the stationary structural component 23 are disposed generally opposite one another across the clearance 64 between the tip shroud 50 and the stationary structural component 23. Additionally, the intermediate portion 108 of the tip shroud 50 and the third corresponding portion 110 of the stationary structural component 23 are generally arranged in a parallel configuration. In other words, the contours of the intermediate portion 108 of the tip shroud 50 and the third corresponding portion 110 of the stationary structural component 23 are generally parallel with one another.
Furthermore, as mentioned above, the tip shroud 50 includes the rail 68 of the labyrinth seal 66, which generally extends in the radial direction 34. As shown, the rail 66 has an upstream surface 112, which is generally vertical. In other words, the upstream surface 112 of the rail 66 extends generally in the radial direction 34. In the illustrated embodiment, the upstream surface 112 of the rail 66 corresponds to a fourth corresponding portion 114 of the stationary structural component 23. The fourth corresponding portion 114 also extends generally in the radial direction 34 (i.e., the fourth corresponding portion 114 is generally vertical). Additionally, as similarly discussed above, the fourth corresponding portion 114 of the stationary structural component 23 is disposed generally upstream from the upstream surface 112 of the rail 68 of the labyrinth seal 66, and the upstream surface 112 of the rail 68 and the fourth corresponding portion 114 of the stationary structural component 23 are disposed opposite one another across the clearance 64. In this manner, the upstream surface 112 of the rail 68 and the fourth corresponding portion 114 of the stationary structural component 23 are arranged in a generally parallel configuration relative to one another.
As shown, the leading edge 100 of the leading edge overhang 78, the nose portion 72 of the tip shroud 50, the intermediate portion 108 of the tip shroud 50, and the upstream surface 112 of the rail 68 are arranged adjacent to one another and in consecutive order along the tip shroud 50 in the axial direction 32, with the leading edge 100 of the leading edge overhang 78 being the most upstream. Similarly, the portions of the stationary structural component 23 corresponding to each of the above-mentioned portions of the tip shroud 50 are arranged adjacent to one another and in consecutive order. Specifically, the first corresponding portion 102 of the stationary structural component 23, the second corresponding portion 106 of the stationary structural component 23, the third corresponding portion 110 of the stationary structural component 23, and the fourth corresponding portion 114 of the stationary structural component 23 are arranged in consecutive order along the stationary structural component 23 in the axial direction 32 and the radial direction 34, with the first corresponding portion 102 of the stationary structural component 23 being the most upstream.
As described above, each portion of the leading edge portion 54 of the tip shroud 50 (e.g., the leading edge 100, nose portion 72, etc.) and the portion of the stationary structural component 23 with which it corresponds (e.g., the first corresponding portion 102, the second corresponding portion 106, etc.) have similar (e.g., generally parallel) contours and are disposed opposite one another across the clearance 64 between the tip shroud 50 and the stationary structural component 23. In certain embodiments, each portion of the leading edge portion 54 of the tip shroud 50 and the portion of the stationary structural component 23 with which it corresponds may be offset in the axial direction 32 the same or similar distance as every other portion of the leading edge portion 54 and the portion of the stationary structural component 23 with which they correspond. In this manner, the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 are arranged in a generally parallel configuration. The generally parallel configuration of the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may help reduce leakage of the fluid flow 58 through the clearance 64 between the tip shroud 50 and the stationary structural component 23. Additionally, the generally parallel configuration may help reduce the generation of vortex flows within the clearance 64. For example, the generally parallel configuration between the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may provide a more tailored and/or reduced clearance 64 between the tip shroud 50 and the stationary structural component 23, resulting in increased blockage of the fluid flow 58 through the clearance 64.
In the illustrated embodiment, the leading edge 100 of the leading edge overhang 78 corresponds with a first corresponding portion 154 of the stationary structural component 23. In other words, the leading edge 100 of the leading edge overhang 78 and the first corresponding portion 154 each extend generally in the radial direction 34. Additionally, the first corresponding portion 154 of the stationary structural component 23 is disposed generally upstream from the leading edge 100 of the leading edge overhang 78, thereby creating the opening 104 of the clearance 64 between the tip shroud 50 and the stationary structural component 23.
The nose portion 72 of the tip shroud 50 corresponds with a second corresponding portion 156 of the stationary structural component 23. In the illustrated embodiment, the nose portion 72 of the tip shroud 50 is generally parallel with the rotational axis 25 of the turbine 18. Additionally, the second corresponding portion 156 of the stationary structural component 23 is generally parallel with the rotational axis 25 of the turbine 18. Furthermore, as similarly discussed above, the second corresponding portion 156 of the stationary structural component 23 is disposed generally upstream from the nose portion 72 of the tip shroud 50. Additionally, the nose portion 72 of the tip shroud 50 and the second corresponding portion 156 of the stationary structural component 23 are disposed generally opposite one another across the clearance 64 between the tip shroud 50 and the stationary structural component 23, thereby creating a generally parallel configuration between the nose portion 72 of the tip shroud 50 and the second corresponding portion 156 of the stationary structural component 23.
In the illustrated embodiment, the tip shroud 50 includes the first rail 150 of the labyrinth seal 66, which generally extends in the radial direction 34. As shown, the first rail 150 has an upstream surface 158, which is generally vertical. In other words, the upstream surface 158 of the first rail 150 extends generally in the radial direction 34. The upstream surface 158 of the first rail 150 corresponds to a third corresponding portion 160 of the stationary structural component 23. The third corresponding portion 160 also extends generally in the radial direction 34 (i.e., the third corresponding portion 160 is generally vertical). Additionally, as similarly discussed above, the third corresponding portion 160 of the stationary structural component 23 is disposed generally upstream from the upstream surface 158 of the first rail 150 of the labyrinth seal 66. In this manner, the upstream surface 158 of the rail 150 and the third corresponding portion 160 of the stationary structural component are arranged in a generally parallel configuration relative to one another.
Furthermore, in certain embodiments, a trailing edge portion 162 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may have a parallel configured. For example, the trailing edge portion 162 (e.g., a portion of the tip shroud 50 aft or downstream of the second rail 152) and a corresponding portion 164 the stationary structural component 23 may have a parallel configuration. In the illustrated embodiment, the trailing edge portion 162 of the tip shroud 50 and the corresponding portion 164 of the stationary structural component 23 have a conical configuration. In other words, the trailing edge portion 162 and the corresponding portion 164 have a slope approximately at the angle 76 relative to the rotational axis 25 of the turbine 18. In other embodiments, the trailing edge portion 162 of the tip shroud 50 and the corresponding portion 164 of the stationary structural component 23 may have a cylindrical configuration, as indicated by reference numeral 166. That is, the trailing edge portion 162 of the tip shroud 50 and the corresponding portion 164 of the stationary structural component 23 may be generally parallel to the rotational axis 25 of the turbine 18.
As shown, the leading edge 100 of the leading edge overhang 78, the nose portion 72 of the tip shroud 50, and the upstream surface 158 of the first rail 150 are arranged adjacent to one another and in consecutive order along the tip shroud 50 in the axial direction 32, with the leading edge 100 of the leading edge overhang 78 being the most upstream. Similarly, the portions of the stationary structural component 23 corresponding to each of the above-mentioned portions of the tip shroud 50 are arranged adjacent to one another and in consecutive order. Specifically, the first corresponding portion 154 of the stationary structural component 23, the second corresponding portion 156 of the stationary structural component 23, and the third corresponding portion 160 of the stationary structural component 23 are arranged in consecutive order along the stationary structural component 23 in the axial direction 32, with the first corresponding portion 154 of the stationary structural component 23 being the most upstream.
As described above, each portion of the leading edge portion 54 of the tip shroud 50 (e.g., the leading edge 100, nose portion 72, etc.) and the portion of the stationary structural component 23 with which it corresponds (e.g., the first corresponding portion 154, the second corresponding portion 156, etc.) have similar (e.g., generally parallel) contours and are disposed opposite one another across the clearance 64 between the tip shroud 50 and the stationary structural component 23. In certain embodiments, each portion of the leading edge portion 54 of the tip shroud 50 and the portion of the stationary structural component 23 with which it corresponds may be offset in the axial direction 32 the same or similar distance as every other portion of the leading edge portion 54 and the portion of the stationary structural component 23 with which they correspond. In this manner, the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 are arranged in a generally parallel configuration. The generally parallel configuration of the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may help reduce leakage of the fluid flow 58 through the clearance 64 between the tip shroud 50 and the stationary structural component 23. For example, the generally parallel configuration between the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may provide a more tailored and/or reduced clearance 64 between the tip shroud 50 and the stationary structural component 23, resulting in reduction of leakage of the fluid flow 58 through the clearance 64.
As similarly discussed above, the leading edge 100 of the leading edge overhang 78 corresponds with a first corresponding portion 182 of the stationary structural component 23. In other words, the leading edge 100 of the leading edge overhang 78 and the first corresponding portion 182 each extend generally in the radial direction 34. Additionally, the first corresponding portion 182 of the stationary structural component 23 is disposed generally upstream from the leading edge 100 of the leading edge overhang 78, thereby creating the opening 104 of the clearance 64 between the tip shroud 50 and the stationary structural component 23.
As mentioned above, the nose portion 72 of the tip shroud 50 is generally oriented at the angle 180 relative to the rotational axis 25 of the turbine 18. For example, the angle 180 between the nose portion 72 of the tip shroud 50 and the rotational axis 25 of the turbine 18 may be approximately 0 to 75, 5 to 60, 10 to 45, 15 to 30, or 20 to 25 degrees. In the illustrated embodiment, the nose portion 72 of the tip shroud 50 corresponds to a second corresponding portion 184 of the stationary structural component 23, which also is generally oriented at the angle 180 relative to the rotational axis 25 of the turbine 18. Moreover, as similarly discussed above, the second corresponding portion 184 of the stationary structural component 23 is disposed generally upstream from the nose portion 72 of the tip shroud 50. Additionally, the nose portion 72 of the tip shroud 50 and the second corresponding portion 184 of the stationary structural component 23 are disposed generally opposite one another across the clearance 64 between the tip shroud 50 and the stationary structural component 23. In this manner, the nose portion 72 of the tip shroud 50 and the second corresponding portion 184 of the stationary structural component 23 are arranged in a generally parallel configuration. In other words, the contours (e.g., surfaces) of the nose portion 72 of the tip shroud 50 and the second corresponding portion 184 of the stationary structural component 23 are generally parallel with one another.
In the illustrated embodiment, the tip shroud 50 includes the first rail 150 of the labyrinth seal 66, which generally extends in the radial direction 34. As shown, the first rail 150 has the upstream surface 158, which is generally vertical. In other words, the upstream surface 158 of the first rail 150 extends generally in the radial direction 34. The upstream surface 158 of the first rail 150 corresponds to a third corresponding portion 186 of the stationary structural component 23. The third corresponding portion 186 also extends generally in the radial direction 34 (i.e., the third corresponding portion 186 is generally vertical). Additionally, as similarly discussed above, the third corresponding portion 186 of the stationary structural component 23 is disposed generally upstream from the upstream surface 158 of the first rail 150 of the labyrinth seal 66. In this manner, the upstream surface 158 of the rail 150 and the third corresponding portion 186 of the stationary structural component 23 are arranged in a generally parallel configuration relative to one another.
As shown, the leading edge 100 of the leading edge overhang 78, the nose portion 72 of the tip shroud 50, and the upstream surface 158 of the first rail 150 are arranged adjacent to one another and in consecutive order along the tip shroud 50 in the axial direction 32, with the leading edge 100 of the leading edge overhang 78 being the most upstream. Similarly, the portions of the stationary structural component 23 corresponding to each of the above-mentioned portions of the tip shroud 50 are arranged adjacent to one another and in consecutive order. Specifically, the first corresponding portion 182 of the stationary structural component 23, the second corresponding portion 184 of the stationary structural component 23, and the third corresponding portion 186 of the stationary structural component 23 are arranged in consecutive order along the stationary structural component 23 in the axial direction 32, with the first corresponding portion 182 of the stationary structural component 23 being the most upstream.
As described above, each portion of the leading edge portion 54 of the tip shroud 50 (e.g., the leading edge 100, nose portion 72, etc.) and the portion of the stationary structural component 23 with which it corresponds (e.g., the first corresponding portion 182, the second corresponding portion 184, etc.) have similar (e.g., generally parallel) contours and are disposed opposite one another across the clearance 64 between the tip shroud 50 and the stationary structural component 23. In certain embodiments, each portion of the leading edge portion 54 of the tip shroud 50 and the portion of the stationary structural component 23 with which it corresponds may be offset in the axial direction 32 the same or similar distance as every other portion of the leading edge portion 54 and the portion of the stationary structural component 23 with which they correspond. In this manner, the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 are arranged in a generally parallel configuration. The generally parallel configuration of the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may help reduce leakage of the fluid flow 58 through the clearance 64 between the tip shroud 50 and the stationary structural component 23. For example, the generally parallel configuration between the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may provide a more tailored and/or reduced clearance 64 between the tip shroud 50 and the stationary structural component 23, resulting in reduction of leakage of the fluid flow 58 through the clearance 64.
As similarly discussed above, the leading edge 100 of the leading edge overhang 78 corresponds with a first corresponding portion 202 of the stationary structural component 23. Specifically, the leading edge 100 of the leading edge overhang 78 and the first corresponding portion 202 each extend generally in the radial direction 34. Additionally, the first corresponding portion 202 of the stationary structural component 23 is disposed generally upstream from the leading edge 100 of the leading edge overhang 78, thereby creating the opening 104 of the clearance 64 between the tip shroud 50 and the stationary structural component 23.
In the illustrated embodiment, the entire tip shroud 50, including the nose portion 72, is generally oriented at the angle 200 relative to the rotational axis 25 of the turbine 18. For example, the angle 200 between the tip shroud 50 and the rotational axis 25 of the turbine 18 may be approximately 0 to 75, 5 to 60, 10 to 45, 15 to 30, or 20 to 25 degrees. In the illustrated embodiment, the nose portion 72 of the tip shroud 50 corresponds to a second corresponding portion 204 of the stationary structural component 23, which also is generally oriented at the angle 200 relative to the rotational axis 25 of the turbine 18. Moreover, as similarly discussed above, the second corresponding portion 204 of the stationary structural component 23 is disposed generally upstream from the nose portion 72 of the tip shroud 50. Additionally, the nose portion 72 of the tip shroud 50 and the second corresponding portion 204 of the stationary structural component 23 are disposed generally opposite one another across the clearance 64 between the tip shroud 50 and the stationary structural component 23. In this manner, the nose portion 72 of the tip shroud 50 and the second corresponding portion 204 of the stationary structural component 23 are arranged in a generally parallel configuration. In other words, the contours (e.g., surfaces) of the nose portion 72 of the tip shroud 50 and the second corresponding portion 204 of the stationary structural component 23 are generally parallel with one another.
The tip shroud 50 includes the first rail 150 of the labyrinth seal 66, which generally extends in the radial direction 34. As shown, the first rail 150 has the upstream surface 158, which is generally vertical. In other words, the upstream surface 158 of the first rail 150 extends generally in the radial direction 34. The upstream surface 158 of the first rail 150 corresponds to a third corresponding portion 206 of the stationary structural component 23. The third corresponding portion 206 also extends generally in the radial direction 34 (i.e., the third corresponding portion 206 is generally vertical). Additionally, as similarly discussed above, the third corresponding portion 206 of the stationary structural component 23 is disposed generally upstream from the upstream surface 158 of the first rail 150 of the labyrinth seal 66. In this manner, the upstream surface 158 of the rail 150 and the third corresponding portion 206 of the stationary structural component 23 are arranged in a generally parallel configuration relative to one another.
As shown, the leading edge 100 of the leading edge overhang 78, the nose portion 72 of the tip shroud 50, and the upstream surface 158 of the first rail 150 are arranged adjacent to one another and in consecutive order along the tip shroud 50 in the axial direction 32, with the leading edge 100 of the leading edge overhang 78 being the most upstream. Similarly, the portions of the stationary structural component 23 corresponding to each of the above-mentioned portions of the tip shroud 50 are arranged adjacent to one another and in consecutive order. Specifically, the first corresponding portion 202 of the stationary structural component 23, the second corresponding portion 204 of the stationary structural component 23, and the third corresponding portion 206 of the stationary structural component 23 are arranged in consecutive order along the stationary structural component 23 in the axial direction 32, with the first corresponding portion 202 of the stationary structural component 23 being the most upstream.
As described above, each portion of the leading edge portion 54 of the tip shroud 50 (e.g., the leading edge 100, nose portion 72, etc.) and the portion of the stationary structural component 23 with which it corresponds (e.g., the first corresponding portion 202, the second corresponding portion 204, etc.) have similar (e.g., generally parallel) contours and are disposed opposite one another across the clearance 64 between the tip shroud 50 and the stationary structural component 23. In certain embodiments, each portion of the leading edge portion 54 of the tip shroud 50 and the portion of the stationary structural component 23 with which it corresponds may be offset in the axial direction 32 the same or similar distance as every other portion of the leading edge portion 54 and the portion of the stationary structural component 23 with which they correspond. In this manner, the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 are arranged in a generally parallel configuration. The generally parallel configuration of the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may help reduce leakage of the fluid flow 58 through the clearance 64 between the tip shroud 50 and the stationary structural component 23. Additionally, the generally parallel configuration may help reduce the generation of vortex flows within the clearance 64. For example, the generally parallel configuration between the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may provide a more tailored and/or reduced clearance 64 between the tip shroud 50 and the stationary structural component 23, resulting in increased blockage of the fluid flow 58 through the clearance 64.
As discussed in detail above, embodiments of the present disclosure include the tip shroud 50 of the turbine blade 22 arranged in a generally parallel configuration with the stationary structural component 23 of the turbine 18. Specifically, the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 are arranged in a generally parallel configuration relative to one another. The generally parallel configuration between the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may reduce flow leakage through the clearance 64 between the tip shroud 50 and the stationary structural component 23. For example, the generally parallel configuration between the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may provide a more tailored clearance 64 between the tip shroud 50 and the stationary structural component 23, resulting in reduction of leakage of the fluid flow 58 through the clearance 64. In this manner, a turbomachine, such as the turbine 18, having the described generally parallel arrangement between the leading edge portion 54 of the tip shroud 50 and the corresponding portion 56 of the stationary structural component 23 may experience improved performance and efficiency.
This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. 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 examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.
