Tip shroud with exit surface for cooling passages

Abstract

To allow removal of a material for mass balancing.SOLUTION: A tip shroud 220 includes a body 240 coupled to a radial outer end 222 of an airfoil 202 of a turbine blade. The tip shroud may include at least one circumferentially extending tip rail 250. A first edge wall 252 of the tip shroud extends axially and radially outwardly from the body along at least one of a circumferentially facing leading edge 234 and a circumferentially facing trailing edge 236 of the body, and includes a circumferentially facing surface 253. Cooling passages 246 are defined in the body and extend circumferentially therein to cool an area near the first edge wall. The tip shroud includes an exit surface 270 adjacent to the first edge wall, where the exit surface includes an exit opening 272 through which at least one of the cooling passages 246 exits the body. The exit surface is angled relative to the circumferentially facing surface 253 of the first edge wall in the range from 15° to 80°.SELECTED DRAWING: Figure 5

Description

[[TECHNICAL FIELD]]

[0001] The present disclosure relates generally to turbomachinery, and more specifically to mass equilibrium material removal for It is possible to do so , an outlet for a cooling passage surface relates to a tip shroud for a turbine blade having the same. [[BACKGROUND ART]]

[0002] Turbomachinery such as gas turbine systems provide power for generators of generation to and are utilized. Generally, a gas turbine system includes a turbine of the gas turbine system parts that passes a fluid (e.g., Ba hot gas) through vinegar to generate power. More specifically, intake air of enters a compressor Take and is drawn And compressed vinegar therein. Compressed did intake air of is mixed with fuel death in the combustor of the gas turbine system in and ignited death, of the gas turbine system Operation to form a fluid (e.g., Ba hot gas) ru . Next Ide the fluid of , Ta turbine parts drives a plurality of rotating blades and of a rotor or to rotate a shaft to generate power through the fluid flow path and flush . The fluid can be guided through the turbine and via a plurality of stationary nozzles arranged between rotating blades Do and arrangement a plurality of stationary nozzles or vanes of through the turbine parts . The plurality of rotating blades by of a rotor of the gas turbine system but rotate vinegar , and Rotation of the rotor coupled to the rotor deathgenerator in power generate can be achieved.

[0003] operation To improve efficiency, rotating blades may include a tip shroud at a radially outer end thereof a . The tip shroud Silence interacts with an inner surface of a stationary casing and guide the working fluid . The tip shroud The mass of the materials included presents how many various mechanical Health and integrity issues ru . One challenge is creep Or deformation acting on rotating blades ru under the stress of rotational force It progresses gradually that must be addressed for the tip shroud The transformation deformation. Creep causes various mechanical problems related to the deformation of the tip shroud at the airfoil or deformation of the tip shroud Several like causes various mechanical problems It could happen . In addition, mass imbalance in the tip shroud quality causes a high degree of bending moment past high bending moment When this happens which can exacerbate the creep problem fear . So Another object is Another challenge is, to ensure mass balance within the tip shroud to provide optimal aerodynamic, heat transfer, and mechanical and aerodynamic and mechanical performance. SUMMARY OF THE INVENTION

[0004] In the following, raise all aspects, examples, and features concrete examples and features can be Technique combined in any technically feasible manner combination .

[0005] One aspect of the present disclosure in is a tip shroud for a turbine blade, It provides, but this tip shroud is, a body coupled to the radially outer end of the airfoil of the turbine blade, the airfoil death includes a pressure side but and a suction side, the body and includes a suction side, the body front circumferential edge and rear circumferential edge comprises I am a main body, and from the main body to a radially outer side Continuing and of the main body Zhou in the direction length omitted along One or more that are present tip rail, and the main body Inside defined in Growth , Inside the main unit in the direction Persistent a first plurality of cooling passages, and of the main body Front circumferential edge and rear circumferential edge at least on the other hand along 1 or more first edge wall It has a structure and, first edge wall Each of the structures , wherein the first edge wall is from the main body Front circumferential edge and rear circumferential edge at least on the other hand along axially from the main body and to a radially outer side Persistent the first edge wall, The first Zhou sur Opposite a first edge wall including a face, and an outlet adjacent to the first edge wall surface , wherein the outlet 、 the outlet An outlet opening is defined on the surface, and that outlet opening through which death the The of the first plurality of cooling passages at least one exit from the main body 、 and the outlet surface includes And , and the outlet surface is inclined at an angle in a range of 15° to 80° relative to the first sur Zhou face Opposite of the first edge wall ru .

[0006] Another aspect of the present disclosure includes any of the foregoing aspects, Include wherein the first edge wall and the outlet and the outlet surface is on the main body Place the axis opposing in the direction a pair radial extension between walls in the axial direction Persistent .

[0007] Another aspect of the present disclosure includes any of the foregoing aspects, Include wherein the first edge wall The first veranda penetrating 1 or more an ope mouth ning is included.

[0008] Another aspect of this disclosure is any of the aspects described above. Include , the first multiple cooling passages at least one Opening the exit mouth This is in the first edge wall. 1 or more Open mouth And in a straight line Line up ru.

[0009] Another aspect of this disclosure is any of the aspects described above. Include The trailing edge of the main body adjacent to the trailing edge of the wing section Growth curved opening mouth Further includes And , curved opening mouth It is not filled by the body of the adjacent tip shroud.

[0010] Another aspect of this disclosure is any of the aspects described above. Include , curved opening mouth This depicts a plane inclined at an angle of 15° to 45° relative to the radial direction. Growth do.

[0011] Another aspect of this disclosure is any of the aspects described above. Include , the main unit Front circumferential edge and rear circumferential edge at least on the other hand in accordance with 1 or more The second veranda It has an additional structure , The 2nd veranda Each of the structures The main unit Front circumferential edge and rear circumferential edge at least on the other hand From the main body along the axis and Radially outward Persistent The second edge wall and the axial direction from the main body. and Radially outward Persistent Interior wall It includes, The inner wall is the second edge wall. and parallel That From the second veranda Zhou They are spaced apart in the direction and radially between them. extension Form a pocket And, Main unit Inside ni Growth So Furthermore, within the main body Direction Persistent Second multiple cooling passages at least one Therefore The exit opening is defined in the inner wall. , exit open mouth teeth In the circumferential direction , radial extension pocket It opens to .

[0012] Another aspect of this disclosure is any of the aspects described above. Include The second veranda wall is, The second veranda Penetrate 1 or more Open mouth Includes.

[0013] Another aspect of this disclosure is any of the aspects described above. Include , the first multiple cooling passages at least one Opening the exit mouth This is in the first edge wall. 1 or more Open mouth And in a straight line Line up ru.

[0014] Another aspect of this disclosure is any of the aspects described above. Include , 1 or more The front rail but Includes multiple end rails And , 1 or more The first veranda structure Between a pair of multiple end rails, in the axial direction arrangement It will be done.

[0015] Another aspect of this disclosure is any of the aspects described above. Include ,Exit surface It is not flat.

[0016] One aspect of this disclosure is a root section and a bounding box to the root section. death The airfoil section is on the positive pressure side. and The turbine blade comprises an airfoil section including the negative pressure side, and a tip shroud, which is coupled to the radially outer end of the airfoil section of the turbine blade. death The main body, and the airfoil section, is on the positive pressure side. and Including the negative pressure side And The main unit is, Front circumferential edge and rear circumferential edge The main body, which includes the main body, and radially outward from the main body Continuing and Main unit Zhou In terms of directional length omitted along One or more that are present The front rail and the main body Insideni Growth And so, Inside the main unit Direction Persistent The first set of multiple cooling passages and the main body Front circumferential edge and rear circumferential edge at least on the other hand in accordance with 1 or more The first veranda structure And, The 1 veranda Each of the structures , the main unit Front circumferential edge and rear circumferential edge at least on the other hand From the main body along the axis and Radially outward Persistent A first edge wall, the first edge wall is the first Zhou direction Opposite A first edge wall including the surface, and an exit adjacent to the first edge wall. surface And, exit surface The interior has a picture Growth The exit was opened. mouth It has, and The exit opening The first set of cooling passages through the opening at least one It comes out of the main unit 、 Exit surface and 1 or more The first veranda structure and And ,Exit surface is the first edge wall Zhou direction Opposite The present invention provides a turbine blade equipped with a tip shroud that is inclined to the surface at an angle of 15° to 80°.

[0017] Another aspect of this disclosure is any of the aspects described above. Include , the first veranda and Exit surface The main unit Place the axis Opposite direction a pair radial direction extension Between the walls, axially Persistent .

[0018] Another aspect of this disclosure is any of the aspects described above. Include The first veranda wall is, The first veranda Penetrate 1 or more Open mouth Includes.

[0019] Another aspect of this disclosure is any of the aspects described above. Include , the first multiple cooling passages at least one Each exit opening mouth It is linearly connected to one of the second set of cooling passages. Line up ru.

[0020] Another aspect of this disclosure is any of the aspects described above. Include The trailing edge of the main body adjacent to the trailing edge of the wing section Growth curved opening mouth Further includes And , curved opening mouth It is not filled by the body of the adjacent tip shroud.

[0021] Another aspect of this disclosure is any of the aspects described above. Include , the main unit Front circumferential edge and rear circumferential edge at least on the other hand in accordance with 1 or more The second veranda structure And, The 2nd veranda Each of the structures The main unit Front circumferential edge and rear circumferential edge at least on the other hand From the main body along the axis and Radially outward Persistent The second edge wall and the axial direction from the main body. and Radially outward Persistent Interior wall It includes The inner wall is the second edge wall. and parallel That From the second veranda Zhou They are spaced apart in the direction and radially between them. extension Form a pocket We The inner wall is the main body Inside ni Growth And so, Inside the main unit Direction Persistent Second multiple cooling passages at least one Paint inside for Growth The exit was opened. mouth Having We , each exit open mouth teeth In the circumferential direction , radial extension pocket It opens to .

[0022] Another aspect of this disclosure is any of the aspects described above. Include The second veranda wall is, The second veranda Penetrate 1 or more Open mouth Includes And , second multiple cooling passages at least one Opening the exit mouth It passes through the second veranda. 1 or more Open mouth One of them and in a straight line Line up ru.

[0023] Another aspect of this disclosure is any of the aspects described above. Include , 1 or more The end rail includes multiple end rails. And , 1 or more The first veranda structure This is axially positioned between a pair of multiple end rails. arrangement It will be done.

[0024] Another aspect of this disclosure includes a gas turbine comprising turbine blades of any of the aforementioned aspects.

[0025] this Invention Overview The manner described in the column Contains First, This disclosure The two items described above The above aspects union In this specification, specifically description Not an embodiment It is also acceptable to do so. .

[0026] 1 That's all. Details of the embodiment of, Attached drawing and The following explanation is provided below. vinegar ru. the Other features, purpose and The advantages are, Detailed information on the invention Description, drawing average Furthermore, it is clear from the claims. Naro cormorant.

[0027] This disclosure The above Other features Regarding various embodiments of this disclosure This document describes the following: Please refer to the attached drawings. The following details Detailed explanation By referring to understanding This will allow us to deepen our understanding. . [Brief explanation of the drawing]

[0028] [Figure 1] This is a schematic diagram of an exemplary gas turbine (GT) system. [Figure 2] Figure 1 is a cross-sectional view of an exemplary turbine that may be used in a GT system. [Figure 3] This is a perspective view of a type of turbine blade that may employ embodiments of the present disclosure. [Figure 4] This is a radially inward perspective view of a pair of turbine blades, each including a tip shroud, according to an embodiment of the present disclosure. [Figure 5] This is a perspective view of the tip shroud according to an embodiment of this disclosure. [Figure 6] This is a cross-sectional view taken along the line 6-6 in Figure 5 of the exit surface adjacent to the edge wall of the tip shroud according to the embodiment of this disclosure. [Figure 7] This is a cross-sectional view taken along the line 7-7 in Figure 5 of the inner wall adjacent to the edge wall of the tip shroud according to the embodiment of this disclosure. [Figure 8] This is a radially outward perspective view of the trailing edge of the airfoil and the front circumferential edge of the tip shroud according to another embodiment of the present disclosure. [Figure 9] This is a radially inward perspective view of the trailing edge of the airfoil and the front circumferential edge of the tip shroud according to another embodiment of the present disclosure. [Figure 10] This is a perspective view of a tip shroud according to another embodiment of the present disclosure. [Figure 11] This is a perspective view of a tip shroud according to another embodiment of the present disclosure. [Figure 12] A perspective view of the tip shroud according to another embodiment of the present disclosure. [Figure 13] A perspective view of the tip shroud according to another embodiment of this disclosure. [Figure 14] This is a cross-sectional view of an exit surface similar to that shown in Figure 6, according to another embodiment of this disclosure. [Figure 15] A cross-sectional view of the exit surface according to other embodiments of this disclosure is similar to that shown in Figure 6. [Modes for carrying out the invention]

[0029] Drawings of this disclosure is essential Zushimo Not to scale The drawings show typical embodiments of this disclosure. This is merely an example, This disclosure technical Something that limits the scope isn't it .drawing In , Similar sign is multiple Between drawings Similar configuration Represents an element.

[0030] first, In order to clearly explain the subject matter of this disclosure 、 Related machinery within turbomachinery Regarding the parts, and explain edge to, for Select a word It is necessary ru. as much as possible , In this technical field General for Words, Use in a manner consistent with its usual meaning. . See separate document for details. It was done Unless Use The word is, This application in context and Attached claims In accordance with Broad sense to interpretation should That is the case. How many parts A different or duplicate terms use hand mention that Many Something This is obvious to those skilled in the art. It is likely. In this specification, single Members and do Even if it is written down , In another context, multiple As something consisting of a number of parts Sometimes it is included. Alternatively, In a certain part of this specification multiple parts as including Even if it is written down , In another place Single part Material as Sometimes it is included. .

[0031] moreover In this specification how many Those descriptive terms Repeat For example, At the beginning of this column These terms If you do this useful It will These terms and The definition will be provided separately. Clearly state Unless otherwise specified, the following applies. Use "downstream" and "Upstream" The term teeth, Fluid flow (for example) Working fluid flowing through a turbine engine Flow , Or air passing through the combustor or turbine component system Coolant passing through one of them (The flow, etc.) to Regarding It is a term that indicates direction. The term "downstream" teeth fluid It flows away Corresponding to direction, the term "upstream" refers to flow. and The opposite direction (that is, flowing Direction say . "Front" and The term "rear" is, It means that the direction will not be specified further. "Front" is in front of the engine. direction or compressor Indicating the end And "rear" means behind the turbomachinery. direction Section Show vinegar.

[0032] Medium heart shaft to versus and parts placed at different radial positions There are many things that need to be explained. The term "radial direction" is shaft perpendicular to exercise or Position say For example, the first parts The second parts Rather shaft A place located in close proximity to If In this specification is the 1 parts is the "radially inward" of the second part or Proximal side of the central axis It is located in " It is stated On the other hand, the first parts The second parts Rather shaft Places located far away If In this specification, the first parts The second parts "Radially outward" or " Distal side of the central axis It is located in " It is statedThe term "axial direction" refers to a direction parallel to the axis. exercise or position This refers to .lastly," Zhou The term "direction" is, shaft In a direction perpendicular to, that is, exercise or Location Around the axis It refers to a certain plane. It should be obvious, but The term refers to the center of the turbine. Applied in relation to the axis .

[0033] Furthermore, in this specification, The following is described below. As , how many Those descriptive terms Repeat To use. 1 "The 2 " and "The 3 The term " " is a parts of Other parts and Compatible to distinguish Used for, individual parts of Location or The importance Sumo No.

[0034] In this specification Use The word is, Special This is merely to illustrate a specific embodiment. Disclosure content Limit Rumo This is not the case. In this context, even if it is written in the singular form, unless otherwise clear from the surrounding context, multiple This includes the case of . In this specification, "To prepare" and / or " include The term "" refers to the described features, integers, steps, operation , composition element and / or parts The existence of Show , One or more other Features, integers, steps, operation , composition element, parts and / or these group existence or addition This does not exclude . "Run" meaning " or " Appropriately " The term , The following terms were listed phenomenon or The situation occurred Even if you come Wake up You don't have to. thing or the part listed after that term or composition elements exist Even if existence You don't have to. This means We , Such description The event occurs Cases where it happens and cases where it does not, the parts Exist There are cases and there are do not have Includes cases .

[0035] be composition If an element or layer is different composition element or layer On top " Engage " Connect " or " Combined " In the case that , Another configuration element or layer Even if it is located directly on top of it, it is not directly on another component or layer engagement 、 connection or join doing That's fine, Or intervening composition element or Layers exist ite That's good too. in contrast, be composition The elements are different composition element or layer When referring to "directly on," "directly engaged with," "directly connected to," or "directly coupled to" intervening composition The elements or layers exist. do not have . composition To explain the relationships between elements for Others who can be there The terminology (for example, "between ~" and "directly between ~", "adjacent" and "directly adjacent," etc.) “interpreted ru This specification Use " and / or The term " " is This includes all possible combinations of one or more of the items listed. .

[0036] The above street This disclosure provides a tip shroud for turbine blades in a gas turbine system. The tip shroud is coupled to the radially outer end of the airfoil portion of the turbine blade. death It may include the main body. The airfoil section is on the positive pressure side. and Includes the negative pressure side. The main body of the tip shroud is, Front circumferential edge and rear circumferential edge Includes. The tip shroud extends radially outward from the main body. Continuing and Main unit Zhou Directional length omitted along One or more that are present It can include a front rail. To cool the area near the first edge wall, cooling passage but Main unit Inside ni Growth And so, Inside the main unit Direction Persistent . Tip shroud teeth , the main unit Front circumferential edge and rear circumferential edge at least on the other hand in accordance with 1 or more The first veranda The structure Contains I am First veranda structure The main body of the tip shroud Front circumferential edge and / or rear circumferential edge From the main body along the axis and Radially outward Persistent It may include a first veranda wall. The first veranda wall is Zhou direction Opposite Includes surfaces.

[0037] Even if not disclosed in this form, The tip shroud is separated from the first edge wall. It includes the inner side wall. , its inner side wall Through death The cooling passage exits the main body. ru case There are also In the embodiments of this disclosure, the tip shroud is located at the exit adjacent to the first edge wall. surface Includes I am . Exit on The exit is open The mouth is defined. ,So Outlet opening Through death cooling passage at least one It comes out of the main body. Exit surface is the first veranda wall Zhou direction Opposite It is inclined at an angle of 15° to 80° relative to the surface. Therefore, the exit surface teeth, To improve mass balance while providing proper cooling Shroud at the tip A predetermined circumference direction Opposite veranda in of material Reduce usage can ru .

[0038] Referring to the drawings, Figure 1 is a schematic diagram of an exemplary turbomachinery 90 in the form of a gas turbine (GT) system 100 (hereinafter, "GT system 100"). The GT system 100 includes a compressor 102 and Combustor 104 of Including. The combustor 104 is in the combustion area 105 and Fuel nozzle assembly 106 of Includes. GT System 100 includes Turbine 108 and Common compressor / turbine rotor shaft 110 (hereinafter referred to as "rotor shaft 110") That ) too Contains I am . be In a non-limiting embodiment, the GT system 100 is: Field Electric Company (Greenville, South Carolina, USA) From commercially available of This is the GT26 engine. This disclosure does not apply to any GT system to It is not limited to, for example General Electric Other products from the company include HA, F, B, LM, GT, and TM. and E Class Sue Engine Model average In addition, other companies' engine models Beginning, Other engines It may also be implemented regarding this matter. Furthermore, the teachings of this disclosure Content This does not necessarily mean a GT system It is not applicable only to, Other types of turbomachines, for example Steam Applicable to turbines, jet engines, compressors, etc. Possible .

[0039] Figure 2 shows the GT system 100 of Figure 1. in use Possible 4 rows Fall A cross-sectional view of an exemplary portion of turbine 108 having L0 to L3 is shown. Fall L0, L1, L2 and L3 and It is stated ru. dan Fall L0 is the It has one tier, and four tiers. Fall of Smallest within (Radially) in Yes, there is. Fall L1 is the It has two stages, and in the axial direction Next paragraph ( paragraph (Downstream of L0) in Yes, there is. Fall L2 is the It has 3 stages, and in the axial direction Next paragraph ( paragraph (Downstream of L1) in Yes, there is. Fall L3 is the best The fourth section (section) Fall (downstream of L2) maximum (Radially) in Yes, there are four rows. Fall teeth Non Limited one example It is nothing more than that, Each turbine It is acceptable to have 5 or more tiers, or even fewer than 4 tiers. .

[0040] In turbine 108, A pair stationary vane or Nozzle 11 2 is , A pair Rotary turbine blade 114 and Collaboration in Each stage of turbine 108 Fall L0 to L3 are formed, and a portion of the flow path passing through turbine 108 is defined. Growth Each set The rotating turbine blade 114 is Each rotor wheel 116 is connected to it. , Rotor wheel 116 is Rotating turbine blades 114 on rotor shaft 110 Zhou Bound in the direction do . In other words, , A pair Rotary turbine blade 114 teeth , to each rotor wheel 116 Zhou They are mechanically joined, separated in a directional manner. Silent Wings Section 115 is around the rotor shaft 110 around Separated in the direction multiple Includes stationary nozzles 112. Each nozzle 112 is connected to the airfoil section 130. 1 or more End wall ( or Platform) 120 , Includes 122 nothing .figure As shown In the example, the nozzle 112 is located on the radially outer end wall 120 andIt includes a radially inner end wall 122. The radially outer end wall 120 connects the nozzle 112 to the casing 124 of the turbine 108.

[0041] driving Inside, air but Compressor 102 of Compressed air is supplied to the combustor 104. Specifically, compressed air is supplied to the combustor 104. Built-in The fuel is supplied to the fuel nozzle assembly 106. is burn The fuel nozzle assembly 106 is in fluid communication with the burning region 105. teeth Fuel source (not shown in Figure 1) friend Fluid communication, fuel and Air is supplied to the combustion region 105. The combustor 104 supplies fuel ignition Then burn it. Combustor 104 It is in fluid communication with turbine 108, and there The thermal energy of the gas flow is converted into mechanical rotational energy. to Converted ru The turbine 108 is rotatably coupled to the rotor 110. do The rotor shaft 110 is driven by the compressor 102. too Rotor shaft 110 and Rotatably coupled doing In an exemplary embodiment, there are multiple combustors 104 and fuel nozzle assemblies 106. In the following description, Not specified separately As far as possible, each part Only one explanation do not At least of the rotating rotor shaft 110 On the other hand The end is Turbine 108 or The axis Direction Continuing But it's fine, limited It is not something that is done However, there are no generators, load compressors. and / or Another turbine like Attached to a load or machine (not shown) ite That's good too.

[0042] Figure 3 shows an exemplary turbine blade 200. Details Enlarged perspective view That is .explanation For convenience, a legend is provided in the drawing, X The axis is omitted. Axial axis (Extending in the same direction as arrow A) , Y The axis is Rotor shaft 110 (Figure 1) shaft A (abbreviated) vertical Continuing ( Zhou direction plane or (Indicating the circumferential direction), Z The axis is Rotor shaft 110 (Figure 1) shaft Radially relative to A Persistent Z The axis is X shaft and Y shaft It is perpendicular to the blade. The blade 200 is rotatable. Na blade (moving blade) And a turbine (for example) But -bin 108) be step Raku odor ite Around the rotor shaft 110 (Figure 1) around Dispersed in the direction A pair Turbine blade 114 one It is a department.

[0043] Turbine 108 driving In the middle, the working fluid (for example) Ba GT System 100 in gas or steam turbine in (Steam) on the airfoil of the blade to When guided, the blade 200 is on the rotor shaft (for example) Ba The rotor shaft 110) starts rotating, and the rotor shaft 110 draws Growth So The axis Rotate around A. In addition, Blade 200 has multiple similar or separate blades (for example) Ba Blade 200 or (Other blades) and (fasteners, welding contact , slots / grooves etc. by (Mechanically) Connected , turbine 108 (Figure 2) be step In the city of Kyoto, a pair Turbine blade 114 (Figure 2) form It is configured to ru Referring to Figure 2, blade 200 is Which step Raku Located at (L0~L3) It's okay to do so. .

[0044] Returning to FIG. 3, blade 200 has a pressure side 204 ( Book obscured in the figure Invisible ) and may include an airfoil portion 202 having a suction side 206 opposite the pressure side 204. Blade 200 also includes, between the pressure side 204 and the suction side 206, Persistent a leading edge 208 and, opposite the leading edge 208, between the pressure side 204 and the suction side 206, Persistent a trailing edge 210 ite . As described above As , the pressure side 204 of airfoil portion 202 generally faces upstream side and the suction side 206 generally faces downstream side .

[0045] As shown in the diagram , blade 200 may also be connected with airfoil portion 202 and include did a root section 212 and a turbine blade tip shroud 220 (hereinafter "tip shroud 220") on the radially outer end 222 of airfoil portion 202. Root section 212 is connected to airfoil portion 202 along the pressure side 204, the suction side 206, the leading edge 208 and and the trailing edge 210 Possible . In various embodiments So , blade 200 may include a fillet 214 at the radially inner end 226 of airfoil portion 202, the fillet 214 In the vicinity of connects teeth airfoil portion 202 and root section 212 and . The fillet 214 as can be formed by Examples include welded or brazed fillets. conventional MIG welding, TIG welding, brazing, or the like by . can . In Figure 3, Although root section 212 is described as including dovetail 224 As shown , root section 212 may have any suitable configuration for connection to rotor shaft 110 Possible . Specifically, root section 212 is configured for connection to a turbine rotor shaft (e.g., Ba the rotor wheel of rotor shaft 110) Response a slot (e.g. Ba a dovetail slot) fitted If and is configured to be adjacent Our adjacent contact parts to Pair another blade 200. The root section 212 is located radially inward of the airfoil 202 side and is formed in a complementary configuration to a rotor shaft ru .

[0046] The tip shroud 220 is connected to the airfoil 202 along the pressure side 204, the suction side 206, the leading edge 208 and and the trailing edge 210 can . In various embodiments So , the blade 200 may include a fillet 228 at the radially outer end 222 of the airfoil 202 In the vicinity of . The fillet 228 connects the airfoil 202 and the tip shroud 220 and . The fillet 228 as is formed Examples include welded or brazed fillets. by conventional MIG welding, TIG welding, brazing, or the like by . Can be achieved The tip shroud 220 is configured to interact with an inner surface of a casing 124 (FIG. 2) and / or inside the casing a casing shroud (not shown).

[0047] FIG. 4 shows a radially inward perspective view of a pair of adjacent turbine blades 200, particularly adjacent tip shrouds 220. FIG. 5 shows a perspective view of a single tip shroud 220. As will be apparent from the following description But , embodiments of the present disclosure include a repeating structure It's okay to stay that way. . For example, where the tip shroud 220 includes three Below tip rails 250 on the I am upper side As explained below , different the recesses The destination are located between adjacent end rails 250 Pair . To distinguish the repeating structures, as necessary The first edge wall structure 238 according to the embodiment of this disclosure is repeated. , reference signs Reference number such as A, B, C for example are used Reference characters may be added. . anti on the repeating structure No reference character is attached. In this case, sentence in response to the pulse, the structure When showing an example where there is only one, , or multiple structure Sometimes they are shown together. .

[0048] Referring to FIGS. 3 to 5, a tip shroud 220 of a turbine blade 200 is coupled to a radially outer end 222 of an airfoil portion 202 of the turbine blade 200 death and may include a main body 240. As described above As , the airfoil portion 202 includes a pressure side 204 and and a suction side 206. FIG. 4 and and FIG. 5 In show that, an airfoil cooling chamber 242 is formed in the airfoil portion 202 It is almost the same as has a shape We , and the most of the airfoil cooling chamber is located radially inward of the tip shroud 220. One cooling chamber (not shown) in the airfoil portion 202 That's all. feeds coolant but to the tip shroud 220 and and the airfoil cooling chamber 242 It can be understood that . A part of the coolant is cold guided from the cooling chamber 242 Discharge through the opening 244 and / or to a tip rail 250 to ru , while the remaining coolant is guided through Inside a coolant passage 246 defined Growth in the main body 240 Furthermore, within the main body in a direction (along Y shaft ) One or more sets that extend cooling passage 246 of . The cooling passage 246 appears as a rounded rib on a radially outer surface 248 (FIG. 5) of the main body 240. The tip shroud 220 has a leading edge 230 、 , a trailing edge 232 , front circumferential edge , 234 and rear circumferential edge and 236 of . Front circumferential edge 234 is located on the pressure side 204 of the airfoil portion 202 Therefore and is named as such, Back circumferential edge and 236 is located on the suction side 206 of the airfoil portion 202 Therefore and is named as such.

[0049] ​ Current technology In the field As is obvious From the wing section 202 of Tip shroud 220 Depending on the degree of overhang , causing mass imbalance fear There is. For example, Example shown in the figure So, Front circumferential edge 234 is, Back circumferential edge 236 Slightly larger From the airfoil section 202 It protrudes , imbalance It could happen .

[0050] Tip shroud 220 teeth , 1 or more It may include an end rail 250. Each end rail 250 extends radially outward from the main body 240. Continuing and Main unit 240 Zhou Directional length omitted along Persistent In this specification Use " omitted " is the main unit 240 Zhou Directional length omitted Accordingly, or 250mm tip rail omitted Parallel, etc. ± in the direction indicated Indicates within 5°. Explanation For convenience The tip shroud 220 is, shaft Separated in the direction 3 Tip rail 250A~C This primarily shows those that possess the following characteristics. . In this example, The tip shroud 220 extends radially outward from the main body 240. Continuing and Main unit 240 Zhou Directional length omitted along Persistent First tip rail 250A and Radially outward from the main body 240 Continuing and Main unit Zhou Directional length omitted along Persistent Second tip rail 250B of It can include. As shown in the figure In a non-specific example, tip shroud 220 teeth , radially outward from the main body 240 Continuing and Main unit 240 Zhou Directional length omitted along PersistentThird tip rail 250C too Contains I am Instructions in this disclosure Content is any number( example Ba 1 (Figure 12), 2 (Figure 13) and 4 Below above ) Tip rail The tip shroud 220 has too Applicable It is possible 2 Below Upper tip rail 250 of for stomach In this case, each end rail 250 is axially separated from the adjacent end rail. (X axis) Separating ru .figure As shown In the example, the second tip rail 250B is The The third end rail 250C is spaced axially away from the first end rail 250A. is the The tip of rail 250B is spaced axially away from the end rail. As shown in the figure As such, the multiple cooling passages 246 are Zhou Between adjacent end rails 250 in the direction ( example Ba 250mm front rail Each pair between ) So, the front rail is 250 (abbreviated) parallel Persistent The first set of cooling passages 246A are the first and Second tip rail 250A , During 250B Continuing The second set of cooling passages 246B are the second and Third tip rail 250B , During 250C Persistent .

[0051] Figure 6 shows an embodiment of the present disclosure. related First veranda structure Figure 5 of 238 6 -6 Arrow sight An enlarged cross-sectional view is shown. Below explanation As , The 1 veranda Each of the structures 238 is the main body 240 in order to reduce the mass Front circumferential edge 234 and rear circumferential edge at least 236 on the other handSelectively according to Possible to arrange Figure 4 and In the example in Figure 5, the first edge wall structure 238 First End shroud 220 Front circumferential edge Along 234 For example, to address the mass imbalance in that direction, Therefore, in the example shown in Figures 4 and 5, the first edge wall structure 238 is located on the positive pressure side 204 of the airfoil section 202.

[0052] First veranda structure 238 is the main unit 240 Front circumferential edge 234 (Illustration) and rear circumferential edge 236 (Example) Ba Figure 10) at least on the other hand Along the axis from the main body 240 and Radially outward Persistent Includes a first edge wall 252. Below Further explanation As The tip shroud 220 has multiple first edge walls structure 238 may also be included. In this case, the first edge wall 252A is of the main body 240 Front circumferential edge 234 (Illustration) and rear circumferential edge 236 (Example) Ba Figure 10) at least on the other hand Along the axis from the main body 240 and Radially outward Continuing Alternatively, another first edge wall 252B is of the main body 240 Front circumferential edge 234 and rear circumferential edge at least 236 on the other hand Along the axis from the main body 240 and Radially outward Continuing It is also possible. Each of the first edge walls 252 is Zhou direction Opposite Surface, i.e., airfoil section 202 Turned to the side Includes surface 253. The first edge wall 252 is the positive pressure side 204 of the airfoil portion 202. and / or The tip shroud 220 on the negative pressure side 206 Zhou It acts as an outer edge wall in the direction. In some cases, the first edge wall 252 may act as a reinforcement for the tip shroud 220. If a pair of tip rails 250 are present, the first edge wall structure238 is axially between the pair of tip rails 250 Continuing This may also be the case. For example, the first edge wall 252A is axially positioned between the first end rail 250A and the second end rail 250B. Continuing The first edge wall 252B is axially positioned between the second end rail 250B and the third end rail 250C (Figure 5). Persistent .

[0053] Figure 7 shows the second edge wall of the tip shroud 220. structure Figure 5 of 256 7 -7 Arrow sight An enlarged cross-sectional view is shown. The second edge wall. structure 256 is the same as the main unit 240 Front circumferential edge 234 and rear circumferential edge at least 236 on the other hand along arrangement And so, that is, here the first edge wall structure 238 does not exist, and there are cases where mass reduction is not necessary. Second edge wall structure 256 is the same as the main unit 240 Front circumferential edge 234 and rear circumferential edge at least 236 on the other hand Along the axis from the main body 240 and Radially outward Persistent Includes a second edge wall 254. In the example shown in Figures 4 and 5, the second edge wall structure 256 is located on the negative pressure side 206 of the airfoil section 202.

[0054] Second veranda structure 256 also extends axially from the main body 240. and Radially outward Persistent Includes inner wall 258. If a pair of end rails 250 are present, The 2nd veranda structure 256 Each of Between the pair of tip rails 250, in the axial direction Continuing This may also be the case. For example, the second edge wall 254A is axially positioned between the first end rail 250A and the second end rail 250B. Persistent The inner wall 258A may be included, and the second edge wall 254B is axially positioned between the second end rail 250B and the third end rail 250C (Figure 5). Continuing and Radially outward from the main body 240 Persistent It may include an inner wall 258B. The inner wall 258 is connected to each second edge wall 254 and parallel That , radially between them extension Picture Pocket 260 Growth From each second edge wall 254 Zhou They are separated in the radial direction. extension Pocket 260 is open radially outward but closed radially inward. The inner wall 258 is the main body 240 Inside ni Growth And so, Inside the main unit Direction Persistent Internally, a section is drawn for the cooling passage 246. Growth The exit was opened. mouth It has 262. Outlet open mouth 262 is In the circumferential direction , radial extension Pocket 260 It opens to The second veranda wall 254 also The second veranda wall 254 Penetrate 1 or more Open mouth 264 may be included. Cooling passage 246 1 or more Opening the exit mouth 262 opens through the second edge wall 254 mouth 264 and in a straight line Line up This is also acceptable. Therefore, the coolant exiting the cooling passage 246 is radially extension Pocket 260 or Opening at the second edge wall 254 mouth You can exit by going through route 264.

[0055] Referring to Figures 5 to 7, in the conventional tip shroud, both edge walls 252 , 254 is the second veranda wall structure 256, that is, has the configuration shown for the second edge wall 254 in Figure 7. According to the embodiment of the present disclosure, the inner wall 258 is Zhou direction Opposite veranda 234 and / orNear 236, it was found that providing a mass of material that is not necessary and could cause a mass imbalance that leads to a bending moment that exacerbates the creep problem. As shown in Figure 6, embodiments of this disclosure related Tip shroud 220, especially the first edge wall structure 238 is an exit adjacent to the first edge wall 252, not the inner wall 258 (Figure 7). surface Includes 270. Exit surface 270 has a picture inside Growth The exit was opened. mouth Includes 272 And ,So Exit opening 272 Multiple cooling passages 246 pass through at least one It comes out of the main body 240. In Figure 6, two outlet openings mouth 272 indicates do it However, any number of for ite (Figure 4) and (See Figure 5). Exit surface 270 is the first edge wall 252 Zhou direction Opposite It is inclined with respect to surface 253 in the range of 15° to 80° (see angle α). In this way, the first edge wall structure In 238, the coolant is located on the inner wall 258 and Pocket 260 structure (Figure 7) includes the second edge wall, which does not have the mass of the inner wall 258. structure It is directed towards the first edge wall 252 to cool with a similar effect to 256.

[0056] The tip shroud 220 is any currently known or Future manufacturing processes, such as casting and additive manufacturing, will be used to create an outlet inside. surface It can be initially manufactured to have 270. Or ,Exit surface 270 can be formed on the tip shroud 220 manufactured on the inner wall 258 (Figure 7) on the first edge wall 252, and can be machined to remove the inner wall 258 (Figure 7), for example, by grinding or cutting the inner wall 258. the Remove physically by other means, exit surface270 (Figure 6) can be formed. In either case, as best shown in Figure 5, the first edge wall 252 and Exit surface 270 is the same as the main unit 240. Place the axis Opposite direction a pair radial direction extension Between walls 276 in an axial direction Persistent It is possible. Radial direction extension Wall 276 is, for example, tip rail 250A , They may be spaced apart from each end rail, such as 250B. Radial direction extension One side of wall 276 Regarding As shown in Figure 6 do it ru.

[0057] Figure 5 and As shown in Figure 6, the first edge wall 252 is The first veranda wall 252 Penetrate 1 or more Open mouth It can include 278, therefore, exit surface 270 of Exit open mouth The coolant coming out of 272 is directed to the first edge wall 252 and Other downstream structures can be cooled. In one non-limiting example, multiple cooling passages 246 1 or more Opening the exit mouth 272 is an opening in the first edge wall 252 mouth 278 and in a straight line Line up It is fine to do so, for example, open mouth A one-to-one alignment may exist. However, this is not necessary in all cases. Any number of exit openings mouth 272 and / or Open mouth 278 You can use .

[0058] As shown in Figure 5, the tip shroud 220 is 3 Below If the upper tip rail 250, i.e., 250A~C is included, then the above structure This may be repeated between different pairs of tip rails 250. More specifically, tip rail 250B , As shown between 250C, the tip shroud 220 is axially separated from the body 240. and On the radially outward side, for example, between the tip rails 250B and 250C, on the positive pressure side 204 of the airfoil section 202 Persistent Another first edge wall including the first edge wall 252B structure It may include 238. The first edge wall 252B is Zhou direction Opposite Includes surface 253 (Figure 6). Tip rail 250B , Between 250C, there are several other cooling passages 246B in the main body 240 Inside ni Growth And so, Inside the main unit Direction Persistent Here is the second exit. surface 270B is adjacent to the first edge wall 252B. Second exit surface 270B is shown in Figure 6. thing The same as structure It has an exit. surface 270B (Figure 5) has a picture inside. Growth The exit was opened. mouth It has 272B (Figure 5), and Exit opening 272B Through the cooling passage 246B at least one It comes out of the main unit 240. Second exit surface 270B is the first edge wall 252B Zhou direction Opposite It is inclined with respect to surface 253 at an angle of 15° to 80° (angle α). Any number of first edge walls structure 238 You can use .

[0059] Figure 8 shows the trailing edge 210 of the airfoil section 202. and Tip shroud 220 Front circumferential edge Figure 9 shows a radially outward perspective view of 234. Figure 9 shows the trailing edge 210 of the airfoil section 202. and Tip shroud 220 Front circumferential edge Figures 4 and 5 show radially inward perspective views of 234. and Referring to Figure 9, in order to further reduce the mass imbalance, the tip shroud 220 is positioned at the trailing edge 232 of the main body 240 adjacent to the trailing edge 210 of the airfoil section 202. Growth curved opening mouth It can include 290. As shown In the example, mouth290 is located on the positive pressure side 204 of the airfoil section 202. mouth 290 is typically the rearmost tip rail 250C of the airfoil section 202. and trailing edge 210 Zhou In the direction forward Persistent Main unit 240 region It is formed in this way. how many In that situation, the adjacent tip shrouds 220 have interlocking surfaces, sometimes called Z-notches due to their Z-shape. Here, as shown in Figure 4, the curved opening mouth 290 is not filled by the body 240 of the adjacent tip shroud 220 and does not interlock with the adjacent surface. In one embodiment, curved opening mouth 290 defines a plane inclined (angle β) in the range of 15° to 45° with respect to the radial direction Z. Growth do.

[0060] Figure 10 shows the present disclosure another In the embodiment related Figure 10 shows a perspective view of the tip shroud 220. Front circumferential edge 234 and Back circumferential edge First edge wall along both sides of 236 structure An embodiment including 238 is shown. Here, mass imbalance may not exist, but mass reduction is still desirable.

[0061] Figure 11 further illustrates the present disclosure. Separate In the embodiment related Figure 11 shows a perspective view of the tip shroud 220. Figure 11 shows just one location (for example) Ba Between the tip rails 250A and 250B, Front circumferential edge One first edge wall along 234 structure An embodiment including 238 is shown. Here, the mass imbalance may exist only at the tip shroud 220 near the leading edge 204 of the airfoil section 202, and it is desirable that the mass reduction is less than that of the embodiment in Figure 5.

[0062] Figure 12 shows other embodiments of the present disclosure. related Figure 12 shows a perspective view of the tip shroud 220. Figure 12 shows the first edge wall, similar to that in Figure 5. structureThis shows one embodiment that includes 238 but does not include the end rails 250B-C. In other words, there is only one end rail 250A. As shown in the figure Thus, if not limited by the tip rail 250, the first and The second wall structure 238 , 256 may have any desired axial length.

[0063] Figure 13 shows other embodiments of the present disclosure. related Figure 13 shows a perspective view of the tip shroud 220. Front circumferential edge The first edge wall runs along 234 but has only two end rails 250A-B. structure An embodiment including 238 is shown. First edge wall structure It will be recognized that 238 can be used, for example, anywhere on the tip shroud 220 where a reduction in mass is desired to address a mass imbalance. Others not shown structure That is also possible.

[0064] For example, as shown in Figure 6 vinegar Like this, exit surface 270 has a flat surface. In other embodiments, the exit surface 270 is generally the first edge wall 252 Zhou direction Opposite It may have an angle with surface 253 and does not have to be flat. Figures 14-15 show the present disclosure. another In the embodiment related Outlet of tip shroud 220 surface A cross-sectional view of 270 is shown. Figure 14 shows the exit. surface 270 is stepped. Here is the exit. surface 270 is, how many It may also be produced by a machining step, and the angle α is defined by a consistent element of the step, for example, its outer corner. Growth It may be done. In Figure 15, the exit surface 270 is the outlet opening of the cooling passage 246 mouth On 272, for example, Exit surface Point where 270 intersects with the first edge wall 252 and Exit surfaceFrom the outermost radial point of 270, the angle α omitted While holding, it may, for example, be slightly arc-shaped inward. surface 270 is within the scope of this disclosure how many It can have other shapes.

[0065] Embodiments of this disclosure include internally Growth The exit was opened. mouth Includes And ,So Outlet opening Through the cooling passage of the tip shroud at least one This is the exit from the main unit. surface First veranda wall including structure Provides a tip shroud having an exit. surface The formation of the second wall structure This is achieved by removing mass that may contribute to mass imbalance while maintaining the cooling effect. Embodiments of this disclosure also include a curved opening near the trailing edge of the airfoil to remove additional mass. mouth This can provide a trailing edge of the tip shroud body having the following characteristics:

[0066] This specification and Claims Approximate representation used teeth, It is a modifier of quantity, and that quantity is Seki Person in charge To the basic functions Within acceptable limits that do not bring about change. It can fluctuate To express quantity Applicable It will be done Therefore, "approximately," "about," and "substantially" like term in Modified value That Limited to precise figures Not done . In some cases, approximate representation teeth, the Measure the value machine Corresponding to the precision of the instrument ru . Within this specification and the claims, the scope of numerical limitations teeth They are connected to each other. and / or exchange It is possible, The extent of this is clearly evident from the context, etc. Unless the range all of the Partial range Identify and include The word "approximately" used for a specific value within a range is, Upper and lower limits Applies to, the The accuracy of the instrument used to measure the value Except in cases of dependence, The number value ± It can show 10% a ru.

[0067] The following claims Configuration identified by functional description element of Corresponding structure, material, act And equivalents are The claims are specifically described other composition elements and combination hand machine Noh all Structure, materials or Includes the act . description Examples and explanation Its purpose is , exhaustive Unless it's something else , Disclosed Limited to form It's not that . Book Disclosure technical Scope and technical thought Deviating from Without doing so, Many fixes and Deformation This will be obvious to those skilled in the art. . The embodiments of this disclosure are The principles of disclosure and Practical Purpose The most appropriate explanation for those skilled in the art is Various embodiments Regarding the disclosures and various modifications suitable for specific uses understanding These are selected and listed so that it can be done. . [Explanation of Symbols]

[0068] 90 Turbomachinery 100 Gas Turbine (GT) System 102 Compressor 104 Combustor 105 Combustion Range 106 Fuel Nozzle Assembly 108 Turbine 110 Rotor Shaft 112 Stationary nozzle 114 Rotary Turbine Blades 115 Silent Wings section 116 Rotor Wheel 120 Radial outer end wall 122 Radial inner end wall 124 Casing 130 Airfoil 200 Turbine Blades 202 Airfoil 204 Positive pressure side, leading edge 206 Negative pressure side 208 Leading edge 210 Trailing edge 212 Root section 214 fillets 220 Turbine blade tip shroud 222 Radial outer end 224 Dovetail 226 Radial inner end 228 fillets 230 Leading edge 232 Trailing edge 234 Front circumferential edge , Zhou direction Opposite veranda 236 Back circumferential edge , Zhou direction Opposite veranda 238 First veranda structure 240 Main Unit 242 Airfoil Cooling Chamber 244 Open mouth 246 Cooling passage 246A First set of multiple cooling passages 246B Second set of cooling passages 248 Radial outer surface 250 tip rail 250A First tip rail 250B Second tip rail 250C Third tip rail 252 First veranda 252A First edge wall 252B First edge wall 253 Zhou direction Opposite surface 254 Second veranda 254A Second veranda 254B Second edge wall 256 Second veranda wall structure 258 Inner wall 258A Inner Wall 258B Inner wall 260 radius direction extension ポケット 262 Exit Open mouth 264 Open mouth 270 Exports surface 270B Exit 2 surface 272 Exit Open mouth 272B Export Open mouth 276 Radius direction extension wall 278 Open mouth 290 Bay Curve Opening mouth 6-6 line 7-7 line L0 segment L1 segment L2 segment L3 segment Z-radius direction α angle β angle

Claims

1. A tip shroud (220) for a turbine blade (114), comprising: a body coupled to a radially outer end of an airfoil of the turbine blade, the airfoil including a pressure side and a suction side, the body including a circumferentially facing leading edge and a circumferentially facing trailing edge; at least one tip rail (250) extending radially outward from said body (240) and extending generally along the circumferential length of said body (240); a first plurality of cooling passages (246A) defined in said body (240) and extending circumferentially therethrough; at least one first edge wall formation (238) along at least one of said circumferentially facing leading edge (234) and said circumferentially facing trailing edge (236) of said body (240), each first edge wall formation (238) comprising: a first edge wall (252) extending axially and radially outward from the body (240) along the at least one of the circumferentially facing leading edge (234) and the circumferentially facing trailing edge (236) of the body (240), the first edge wall (252) including a first circumferentially facing surface (253); an outlet surface (270) adjacent said first edge wall (252), said outlet surface (270) having an outlet opening (272) defined therein through which at least one of said first plurality of cooling passages (246A) exits said body (240); at least one first edge wall component (238) including: Equipped with said outlet surface (270) being inclined in the range of 15° to 80° relative to said first circumferentially facing surface (253) of said first edge wall (252); Tip shroud (220).

2. 2. The tip shroud of claim 1, wherein the first edge wall and the outlet surface extend axially between a pair of axially opposed radially extending walls of the body.

3. The tip shroud (220) of claim 1, wherein the first edge wall (252) includes at least one opening (278) therethrough.

4. 4. The tip shroud of claim 3, wherein the exit opening for the at least one of the first plurality of cooling passages is linearly aligned with the at least one opening in the first edge wall.

5. 2. The tip shroud of claim 1, further comprising a curved opening defined in a trailing edge of the body adjacent a trailing edge of the airfoil, the curved opening being unfilled by the body of an adjacent tip shroud.

6. The tip shroud (220) of claim 5, wherein the curved opening (290) has a plane inclined at an angle in the range of 15° to 45° with respect to the radial direction (Z).

7. at least one second edge wall formation (256) along at least one of said circumferentially facing leading edge (234) and said circumferentially facing trailing edge (236) of said body (240), each second edge wall formation (256) comprising: a second edge wall (254) extending axially and radially outward from the body (240) along the at least one of the circumferentially facing leading edge (234) and the circumferentially facing trailing edge (236) of the body (240); an inner wall (258) extending axially and radially outward from the body (240), the inner wall (258) being parallel to the second edge wall (254) and spaced circumferentially from the second edge wall (254) to form a radially extending pocket (260) therebetween, the inner wall (258) having an outlet opening (262) defined therein for at least one of a second plurality of cooling passages (246, 246B) defined in the body (240) and extending circumferentially therein, each outlet opening (262) being spaced apart from the inner wall (258) circumferentially facing the radially extending pocket (260); At least one second edge wall component (256) including The tip shroud (220) of claim 1 further comprising:

8. The tip shroud (220) of claim 7, wherein the second edge wall (254) includes at least one opening (278) therethrough.

9. 9. The tip shroud of claim 8, wherein the exit opening for the at least one of the second plurality of cooling passages is linearly aligned with one of the at least one opening through the second edge wall.

10. 2. The tip shroud of claim 1, wherein the at least one tip rail comprises a plurality of tip rails, and the at least one first edge wall configuration is axially positioned between a pair of the plurality of tip rails.

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