This patent arises from U.S. Non-Provisional patent application Ser. No. 17/343,454, which was filed on Jun. 9, 2021, and entitled “COMPLIANT SHROUD DESIGNS WITH VARIABLE STIFFNESS.” U.S. Non-Provisional patent application Ser. No. 17/343,454 is hereby incorporated herein by reference in its entirety. Priority to U.S. Non-Provisional patent application Ser. No. 17/343,454 is hereby claimed.
This disclosure relates generally to shrouds for gas turbines, and, more particularly, to shroud designs.
A gas turbine engine generally includes, in serial flow order, an inlet section, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, air enters the inlet section and flows to the compressor section where one or more axial compressors progressively compress the air until it reaches the combustion section, thereby creating combustion gases. The combustion gases flow from the combustion section through a hot gas path defined within the turbine section and then exit the turbine section via the exhaust section.
Methods, apparatus, systems, and articles of manufacture for compliant shroud designs with variable stiffness are disclosed.
Certain examples provide a shroud assembly for a gas turbine engine including a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.
Certain examples provide a gas turbine engine including a compressor including a compressor casing and at least one compressor blade, a combustion section, a turbine including a turbine casing and at least one turbine blade, a shaft to rotatably couple the compressor and the turbine, and a shroud assembly for at least one of the compressor or the turbine, the shroud assembly including a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.
Certain examples provide a shroud apparatus including first means for reducing blade damage having a first end and a second end, the first end to couple to an outer wall of the shroud assembly and the second end to couple to a first shroud pad, and second means for reducing blade damage having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.
The figures are not to scale. Instead, the thickness of the layers or regions may be enlarged in the drawings. Although the figures show layers and regions with clean lines and boundaries, some or all of these lines and/or boundaries may be idealized. In reality, the boundaries and/or lines may be unobservable, blended, and/or irregular. In general, the same reference numbers will be used throughout the drawing(s) and accompanying written description to refer to the same or like parts. As used in this patent, stating that any part (e.g., a layer, film, area, region, or plate) is in any way on (e.g., positioned on, located on, disposed on, or formed on, etc.) another part, indicates that the referenced part is either in contact with the other part, or that the referenced part is above the other part with one or more intermediate part(s) located therebetween. As used herein, connection references (e.g., attached, coupled, connected, and joined) may include intermediate members between the elements referenced by the connection reference and/or relative movement between those elements unless otherwise indicated. As such, connection references do not necessarily infer that two elements are directly connected and/or in fixed relation to each other. As used herein, stating that any part is in “contact” with another part is defined to mean that there is no intermediate part between the two parts.
During normal engine operation, one or more rotor blades may contact the shroud. The contact (e.g., rubbing) between the rotor blades and the shroud causes eventual wear on the rotor blades and/or the shroud. There is a continuing need to reduce the blade tip rub loss during contact between rotor blades and the shroud during engine operation. Certain examples provide a compliant shroud design with variable stiffness that decreases rubbing, improving durability of the one or more rotor blades, the shroud, and associated engines. Examples disclosed herein increase clearance and reduce blade damage during operation, thus reducing repair costs.
In the following detailed description, reference is made to the accompanying drawings that form a part hereof, and in which is shown by way of illustration specific examples that may be practiced. These examples are described in sufficient detail to enable one skilled in the art to practice the subject matter, and it is to be understood that other examples may be utilized. The following detailed description is therefore provided to describe an example implementation and not to be taken limiting on the scope of the subject matter described in this disclosure. Certain features from different aspects of the following description may be combined to form yet new aspects of the subject matter discussed below.
Descriptors “first,” “second,” “third,” etc. are used herein when identifying multiple elements or components which may be referred to separately. Unless otherwise specified or understood based on their context of use, such descriptors are not intended to impute any meaning of priority, physical order or arrangement in a list, or ordering in time but are merely used as labels for referring to multiple elements or components separately for ease of understanding the disclosed examples. In some examples, the descriptor “first” may be used to refer to an element in the detailed description, while the same element may be referred to in a claim with a different descriptor such as “second” or “third.” In such instances, it should be understood that such descriptors are used merely for ease of referencing multiple elements or components.
The terms “upstream” and “downstream” refer to the relative direction with respect to fluid flow in a fluid pathway. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction to which the fluid flows. As used herein, “vertical” refers to the direction perpendicular to the ground. As used herein, “horizontal” refers to the direction parallel to the centerline of the turbofan 100. As used herein, “lateral” refers to the direction perpendicular to the axial vertical directions (e.g., into and out of the plane of
Various terms are used herein to describe the orientation of features. As used herein, the orientation of features, forces and moments are described with reference to the axial direction, radial direction, and circumferential direction of the vehicle associated with the features, forces and moments. In general, the attached figures are annotated with a set of axes including the axial axis A, the radial axis R, and the circumferential axis C. Additionally or alternatively, the attached figures are annotated with a set of axes including the roll axis R, the pitch axis P, and the yaw axis Y.
“Including” and “comprising” (and all forms and tenses thereof) are used herein to be open ended terms. Thus, whenever a claim employs any form of “include” or “comprise” (e.g., comprises, includes, comprising, including, having, etc.) as a preamble or within a claim recitation of any kind, it is to be understood that additional elements, terms, etc. may be present without falling outside the scope of the corresponding claim or recitation. As used herein, when the phrase “at least” is used as the transition term in, for example, a preamble of a claim, it is open-ended in the same manner as the term “comprising” and “including” are open ended. The term “and/or” when used, for example, in a form such as A, B, and/or C refers to any combination or subset of A, B, C such as (1) A alone, (2) B alone, (3) C alone, (4) A with B, (5) A with C, (6) B with C, and (7) A with B and with C. As used herein in the context of describing structures, components, items, objects and/or things, the phrase “at least one of A and B” is intended to refer to implementations including any of (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing structures, components, items, objects and/or things, the phrase “at least one of A or B” is intended to refer to implementations including any of (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. As used herein in the context of describing the performance or execution of processes, instructions, actions, activities and/or steps, the phrase “at least one of A and B” is intended to refer to implementations including any of (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing the performance or execution of processes, instructions, actions, activities and/or steps, the phrase “at least one of A or B” is intended to refer to implementations including any of (1) at least one A, (2) at least one B, and (3) at least one A and at least one B.
As used herein, singular references (e.g., “a”, “an”, “first”, “second”, etc.) do not exclude a plurality. The term “a” or “an” entity, as used herein, refers to one or more of that entity. The terms “a” (or “an”), “one or more”, and “at least one” can be used interchangeably herein. Furthermore, although individually listed, a plurality of means, elements or method actions may be implemented by, e.g., a single unit or processor. Additionally, although individual features may be included in different examples or claims, these may possibly be combined, and the inclusion in different examples or claims does not imply that a combination of features is not feasible and/or advantageous.
Gas turbine engines include rows of vanes, rows of rotor blades, etc. One or more shrouds may be positioned radially outward from and circumferentially enclose the rows of rotor blades. While example disclosed herein are described with reference to rotor blades in the compressor, the examples disclosed herein can be applied to rotor blades in any section of an engine. It is generally desirable to try to minimize the clearance gap between the one or more shrouds and the rotor blades to minimize leakage of air and/or combustion products. However, if the clearance gap is too small, there is a risk that the rotor blades may rub against the shrouds, which can result in decreased gas turbine efficiency, blade damage, etc.
In some prior examples, a pneumatic or hydraulic system may permit the shroud to move radially outward if the one or more rotor blades contact the shroud to reduce and/or prevent rubbing. However, pneumatic and hydraulic systems are complex and add significant cost and weight to the engine. A shroud that moves radially outward upon contact with a rotor blade and does not require a pneumatic or hydraulic system can increase a clearance benefit and reduce blade damage.
Examples disclosed herein can reduce undesired effects caused by rubbing between the one or more rotor blades and the shroud based on a shroud assembly that moves radially outward upon contact with the rotor blades. By segmenting the shroud of the gas turbine engine to form a shroud with variable stiffness, for example, the rubbing is mitigated. The shroud assembly with variable stiffness can include one or more shroud arms with one or more shroud pads.
Reference now will be made in detail to examples of the present disclosure, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the present disclosure, not limitation of the present disclosure. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present disclosure without departing from the scope or spirit of the present disclosure. For instance, features illustrated or described as part of one example can be used with another example to yield a still further example. Thus, it is intended that the present disclosure covers such modifications and variations as come within the scope of the appended claims and their equivalents.
The core turbine 104 generally includes a substantially tubular outer casing 108 (“turbine casing 108”) that defines an annular inlet 110. The outer casing 108 can be formed from a single casing or multiple casings. The outer casing 108 encloses, in serial flow relationship, a compressor section having a booster or low pressure compressor 112 (“LP compressor 112”) and a high pressure compressor 114 (“HP compressor 114”), a combustion section 116, a turbine section having a high pressure turbine 118 (“HP turbine 118”) and a low pressure turbine 120 (“LP turbine 120”), and an exhaust section 122. A high pressure shaft or spool 124 (“HP shaft 124”) drivingly couples the HP turbine 118 and the HP compressor 114. A low pressure shaft or spool 126 (“LP shaft 126”) drivingly couples the LP turbine 120 and the LP compressor 112. The LP shaft 126 may also couple to a fan spool or shaft 128 of the fan section 106 (“fan shaft 128”). In some examples, the LP shaft 126 may couple directly to the fan shaft 128 (i.e., a direct-drive configuration). In alternative configurations, the LP shaft 126 may couple to the fan shaft 128 via a reduction gearbox 130 (e.g., an indirect-drive or geared-drive configuration).
As shown in
As illustrated in
The combustion gases 160 flow through the HP turbine 118 in which one or more sequential stages of HP turbine stator vanes 162 and HP turbine rotor blades 164 coupled to the HP shaft 124 extract a first portion of kinetic and/or thermal energy from the combustion gases 160. This energy extraction supports operation of the HP compressor 114. The combustion gases 160 then flow through the LP turbine 120 where one or more sequential stages of LP turbine stator vanes 166 and LP turbine rotor blades 168 coupled to the LP shaft 126 extract a second portion of thermal and/or kinetic energy therefrom. This energy extraction causes the LP shaft 126 to rotate, thereby supporting operation of the LP compressor 112 and/or rotation of the fan shaft 128. The combustion gases 160 then exit the core turbine 104 through the exhaust section 122 thereof.
Along with the turbofan 100, the core turbine 104 serves a similar purpose and sees a similar environment in land-based gas turbines, turbojet engines in which the ratio of the first portion 146 of the air 142 to the second portion 148 of the air 142 is less than that of a turbofan, and unducted fan engines in which the fan section 106 is devoid of the nacelle 134. In each of the turbofan, turbojet, and unducted engines, a speed reduction device (e.g., the reduction gearbox 130) may be included between any shafts and spools. For example, the reduction gearbox 130 may be disposed between the LP shaft 126 and the fan shaft 128 of the fan section 106.
In
An example compressor casing or shell 216 circumferentially surrounds the rows 206 of the rotor blades 208 and the rows 210 of the stator vanes 212. The compressor casing 216 may be a unitary (e.g., a single casing for the entire HP compressor 114). Additionally or alternatively, the compressor casing 216 may be segmented such that each segment of the compressor casing 216 surrounds, e.g., a portion of one or more of the rows 206 of the rotor blades 208 of the first stage 202, the rows 206 of the rotor blades 208 of the second stage 204, etc.
The HP compressor 114 includes one or more shroud assemblies 218 that couple to the compressor casing 216. In
In examples disclosed herein, the shroud assembly 218 is segmented in the axial direction. That is, the shroud assembly 218 includes the one or more shroud arms 306. In
During engine operation, the blade tips 214 of the rotor blades 208 may contact the shroud pads 308. Upon contact, one or more of the shroud pads 308 move radially inward into the shroud receiving cavity 302. That is, the shroud arms 306 compress in the radial direction to enable the radially inward movement of the shroud pads 308. For example, the shroud arms 306 cushion and/or absorb the impact of the blade tips 214. Thus, the radially inward movement of the shroud pads 308 reduces the impact between the blade tips 214 and the shroud pads 308.
The illustrated example of
In
The air-damping holes 514 segment the shroud pads 506 into a first shroud pad segment 516, a second shroud pad segment 518, a third shroud pad segment 520, a fourth shroud pad segment 522, a fifth shroud pad segment 524, and a sixth shroud pad segment 526. In some examples, the shroud pad segments 516, 518, 520, 522, 524, 526 have the same axial length (e.g., the air-damping holes 514 are uniformly spaced apart along the axial axis). In some examples, the shroud pad segments 516, 518, 520, 522, 524, 526 do not have the same axial length. The shroud pad segments 516, 518, 520, 522, 524, 526 couple to one or more of the shroud arms 504 (e.g., the solid shroud arm 508 and/or the air-damping shroud arm 510).
The shroud assembly 600 includes shroud pads 616. The shroud pads 616 include a first shroud pad 618, a second shroud pad 620, a third shroud pad 622, a fourth shroud pad 624, a fifth shroud pad 626, and a sixth shroud pad 628. That is, the shroud pads 616 of the shroud assembly 600 are independent shroud pads. Thus, the shroud pads 616 form split lines. For example, the first shroud pad 618 and the second shroud pad 620 form a first split line 630, the second shroud pad 620 and the third shroud pad 622 form a second split line 632, the third shroud pad 622 and the fourth shroud pad 624 form a third split line 634, the fourth shroud pad 624 and the fifth shroud pad 626 form a fourth split line 636, and the fifth shroud pad 626 and the sixth shroud pad 628 form a fifth split line 638. The split lines 630, 632, 634, 636, 638 of the shroud assembly 600 are parallel to the radial axis. That is, the cross-sectional view of the shroud pads 618, 620, 622, 624, 626, 628 are rectangular.
The shroud pads 616 are coupled to the shroud arms 604. For example, the first shroud arm 606 is coupled to the second shroud pad 620, the second shroud arm 608 is coupled to the third shroud pad 622, etc. In
The shroud assembly 700 includes shroud pads 716. The shroud pads 716 include a first shroud pad 718, a second shroud pad 720, a third shroud pad 722, a fourth shroud pad 724, a fifth shroud pad 726, and a sixth shroud pad 728. That is, the shroud pads 716 of the shroud assembly 700 are independent shroud pads. Thus, the shroud pads 716 form split lines. For example, the first shroud pad 718 and the second shroud pad 720 form a first split line 730, the second shroud pad 720 and the third shroud pad 722 form a second split line 732, the third shroud pad 722 and the fourth shroud pad 724 form a third split line 734, the fourth shroud pad 724 and the fifth shroud pad 726 form a fourth split line 736, and the fifth shroud pad 726 and the sixth shroud pad 728 form a fifth split line 738. The split lines 730, 732, 734, 736, 738 of the shroud assembly 700 are not parallel to the radial axis. That is, unlike the shroud assembly 600 of
The shroud pads 716 are coupled to the shroud arms 704. For example, the first shroud arm 706 is coupled to the second shroud pad 720, the second shroud arm 708 is coupled to the third shroud pad 722, etc. In
The shroud assembly 800 includes shroud pads 816. The shroud pads 816 include a first shroud pad 818, a second shroud pad 820, a third shroud pad 822, a fourth shroud pad 824, a fifth shroud pad 826, and a sixth shroud pad 828. That is, the shroud pads 816 of the shroud assembly 800 are independent shroud pads. Thus, the shroud pads 816 form split lines. For example, the first shroud pad 818 and the second shroud pad 820 form a first split line 830, the second shroud pad 820 and the third shroud pad 822 form a second split line 832, the third shroud pad 822 and the fourth shroud pad 824 form a third split line 834, the fourth shroud pad 824 and the fifth shroud pad 826 form a fourth split line 836, and the fifth shroud pad 826 and the sixth shroud pad 828 form a fifth split line 838. The split lines 830, 832, 834, 836, 838 of the shroud assembly 800 are not parallel to the radial axis. That is, unlike the shroud assembly 600 of
The shroud pads 816 are coupled to the shroud arms 804. For example, the first shroud arm 806 is coupled to the second shroud pad 820, the second shroud arm 808 is coupled to the third shroud pad 822, etc. In the illustrated example of
The shroud assembly 900 includes shroud pads 916. The shroud pads 916 include a first shroud pad 918, a second shroud pad 920, a third shroud pad 922, a fourth shroud pad 924, a fifth shroud pad 926, a sixth shroud pad 928, and a seventh shroud pad 930. That is, the shroud pads 916 of the shroud assembly 900 are independent shroud pads. The shroud pads 916 are coupled to the shroud arms 904. For example, the first shroud arm 906 is coupled to the second shroud pad 920, the second shroud arm 908 is coupled to the third shroud pad 922, etc. In
The shroud pads 918, 920, 922, 924, 926, 928, 930 are interlocking with a stepped geometry. For example, the first shroud pad 918 has a shroud pad base 932 and a shroud pad tip 934, the second shroud pad 920 has a shroud pad base 936 and a shroud pad tip 938, the third shroud pad 922 has a shroud pad base 940 and a shroud pad tip 942, the fourth shroud pad 924 has a shroud pad base 944 and a shroud pad tip 946, the fifth shroud pad 926 has a shroud pad base 948 and a shroud pad tip 950, the sixth shroud pad 928 has a shroud pad base 952 and a shroud pad tip 954, and the seventh shroud pad 930 has a shroud pad base 956 and a shroud pad tip 958. The shroud pad bases 932, 940, 948, 956 have a greater axial length than the corresponding shroud pad tips 934, 942, 950, 958. The shroud pad bases 936, 944, 952 have a shorter axial length than the corresponding shroud pad tips 938, 946, 954.
The shroud pads 918, 922, 926, 930 are at a first position and the shroud pads 920, 924, 928 are at a second position. That is, the shroud pad tips 934, 942, 950, 958 of the shroud pads 918, 922, 926, 930 are at a first position 960. The shroud pad tips 938, 946, 954 of the shroud pads 920, 924, 928 are at a second position 962. The second position 962 is located radially inward (e.g., a lower radial position) with respect to the first position 960. Thus, the shroud pad tips 938, 946, 954 may be the first point of contact with rotor blades (not illustrated).
In
During cold assembly, the shroud assembly 218 can be assembled with a larger clearance gap to avoid and/or reduce rub between the shroud assembly 218 and the row 206 of the rotor blades 208 at steady state take off (SSTO). During SSTO, the clearance gap closes and/or reduces in size with few and/or no rubs. During cruise, the manifold may open to pressurize the cavity via the air-damping holes 1534, 1536, 1538, 1540. That is, in response to the increase in pressure, the shroud assembly 218 is deflected radially inward. Thus, the shroud assembly 218 and the rotor blades 208 run line to line at cruise.
The shroud assembly 218, the shroud assembly 400, the shroud assembly 500, the shroud assembly 600, the shroud assembly 700, the shroud assembly 800, and/or the shroud assembly 900 can be combined, divided, re-arranged, etc. For example, the outer wall of the shroud assemblies 218, 500, 600, 700, 800, 900 can be segmented and/or include anti-rotation tabs (e.g., the outer wall segment 420 of
The shroud assembly 218, the shroud assembly 400, the shroud assembly 500, the shroud assembly 600, the shroud assembly 700, the shroud assembly 800, and/or the shroud assembly 900 can prevent and/or reduce shroud and/or airfoil degradation during normal engine operation. At least the shroud arms 306, 404, 504, 604, 704, 804, 904 can be used to implement a means for reducing blade damage. For example, in
In operation, the shroud assembly (e.g., the shroud assembly 218, the shroud assembly 400, the shroud assembly 500, the shroud assembly 600, the shroud assembly 700, the shroud assembly 800, and/or the shroud assembly 900, etc.) of the HP compressor 114 moves radially outwardly upon contact with one or more of the rotor blades 208. This radial movement prevents erosion of the shroud and/or the rotor blades 208. That is, the examples disclosed herein increase reliability/durability of gas turbine engines by decreasing rubbing between the shroud and the rotor blades.
The following claims are hereby incorporated into this Detailed Description by this reference, with each claim standing on its own as a separate embodiment of the present disclosure.
Further aspects of the present disclosure are provided by the subject matter of the following clauses:
Example 1 is a shroud assembly for a gas turbine engine, the shroud assembly comprising: a first shroud arm having a first end and a second end, the first end to couple an outer wall and the second end to couple to a first shroud pad; and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.
Example 2 is the shroud assembly of any preceding clause, wherein the first shroud arm and the second shroud arm have a hairpin structure.
Example 3 is the shroud assembly of any preceding clause, wherein the first shroud pad and the second shroud pad have an air-damping hole.
Example 4 is the shroud assembly of any preceding clause, wherein the first shroud arm has an air-damping hole.
Example 5 is the shroud assembly of any preceding clause, wherein the outer wall has an air-damping hole.
Example 6 is the shroud assembly of any preceding clause, wherein the first shroud arm has a first stiffness and the second shroud arm has a second stiffness.
Example 7 is the shroud assembly of any preceding clause, wherein the first stiffness is less than the second stiffness, the first shroud pad is at a first position and the second shroud pad is at a second position.
Example 8 is the shroud assembly of any preceding clause, wherein the first position is at a lower radial position than the second position.
Example 9 is the shroud assembly of any preceding clause, wherein the first shroud pad is to move radially outward to the second position in response to the rotor blade contacting the first shroud pad.
Example 10 is the shroud assembly of any preceding clause, wherein at least one of the first shroud pad or the second shroud pad is coated.
Example 11 is the shroud assembly of any preceding clause, wherein the first shroud pad and the second shroud pad are to include an anti-rotation tab.
Example 12 is the shroud assembly of any preceding clause, wherein the outer wall is to include a first outer wall segment and a second outer wall segment, the first end of the first arm to couple to the first outer wall segment and the first end of the second arm to couple to the second outer wall segment.
Example 13 is the shroud assembly of any preceding clause, wherein the first outer wall segment and the second outer wall segment are to include an anti-rotation tab and an anti-rotation cavity.
Example 14 is the shroud assembly of any preceding clause, wherein the anti-rotation cavity of the first outer wall segment is to receive the anti-rotation tab of the second outer wall segment.
Example 15 is the shroud assembly of any preceding clause, wherein the first shroud arm and the second shroud arm are 360 degree axial segments.
Example 16 is the shroud assembly of any preceding clause, wherein the first shroud arm and the second shroud arm are circumferentially segmented.
Example 17 is the shroud assembly of any preceding clause, wherein the first shroud pad and the second shroud pad are to form a split line, the split line parallel to the radial axis.
Example 18 is the shroud assembly of any preceding clause, wherein the first shroud pad and the second shroud pad are to form a split line, the split line not parallel to the radial axis.
Example 19 is the shroud assembly of any preceding clause, wherein the first shroud pad is to include a shroud pad base and a shroud pad tip, the second end of the first arm to couple to the shroud pad base.
Example 20 is the shroud assembly of any preceding clause, wherein the shroud pad base has a smaller axial length than the shroud pad tip of the first shroud pad.
Example 21 is the shroud assembly of any preceding clause, wherein the second shroud pad is to include a shroud pad base and a shroud pad tip, the second end of the second arm to couple to the shroud pad base.
Example 22 is the shroud assembly of any preceding clause, wherein the shroud pad base has a greater axial length than the shroud pad tip of the second shroud pad.
Example 23 is the shroud assembly of any preceding clause, wherein the first shroud pad is to include a first shroud pad segment and a second shroud pad segment.
Example 24 is the shroud assembly of any preceding clause, wherein the first shroud pad segment and the second shroud pad segment are to form a split line, the split line parallel to an axial centerline of the gas turbine engine.
Example 25 is the shroud assembly of any preceding clause, wherein the split line is a first split line and the second shroud pad is to include a third shroud pad segment and a fourth shroud pad segment, the third shroud pad segment and the fourth shroud pad segment to form a second split line.
Example 26 is the shroud assembly of any preceding clause, wherein the second split line is not parallel to the axial centerline of the gas turbine engine.
Example 27 is the shroud assembly of any preceding clause, wherein the first split line and the second split line are aligned.
Example 28 is the shroud assembly of any preceding clause, wherein the first split line and the second split line are offset.
Example 29 is a gas turbine engine, comprising: a compressor including a compressor casing and at least one compressor blade; a combustion section; a turbine including a turbine casing and at least one turbine blade; a shaft to rotatably couple the compressor and the turbine; and a shroud assembly for at least one of the compressor or the turbine, the shroud assembly including: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad; and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.
Example 30 is the gas turbine engine of any preceding clause, wherein the first shroud pad is at a first position and the second shroud pad is at a second position, the first position at a lower radial position than the second position.
Example 31 is the gas turbine engine of any preceding clause, wherein the first shroud pad is to move radially outward to the second position in response to the rotor blade contacting the first shroud pad.
Example 32 is a shroud apparatus comprising: first means for reducing blade damage having a first end and a second end, the first end to couple to an outer wall of the shroud assembly and the second end to couple to a first shroud pad; and second means for reducing blade damage having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.
Although certain example methods, apparatus and articles of manufacture have been disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all methods, apparatus and articles of manufacture fairly falling within the scope of the claims of this patent.
The following claims are hereby incorporated into this Detailed Description by this reference, with each claim standing on its own as a separate embodiment of the present disclosure.
Number | Date | Country | |
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Parent | 17343454 | Jun 2021 | US |
Child | 18463970 | US |