Patent ID: 12241376

DETAILED DESCRIPTION OF THE DRAWINGS

For the purposes of promoting an understanding of the principles of the disclosure, reference will now be made to a number of illustrative embodiments illustrated in the drawings and specific language will be used to describe the same.

A turbine assembly24according to a first aspect of the present disclosure is shown inFIGS.2A-7C. A turbine assembly124according to a further aspect of the present disclosure is shown inFIGS.8-9D. A turbine assembly224according to an additional aspect of the present disclosure is shown inFIGS.10-15B.

An illustrative aerospace gas turbine engine10includes an inlet12and an engine core13, the engine core13having a compressor14, a combustor16located downstream of the compressor14, and a turbine18located downstream of the combustor16as shown inFIG.1. A fan21arranged in the inlet is driven by the turbine18and provides thrust for propelling the gas turbine engine10by forcing air15through a bypass duct22. The compressor14compresses and delivers air to the combustor16. The combustor16mixes fuel with the compressed air received from the compressor14and ignites the fuel. The hot, high-pressure products of the combustion reaction in the combustor16are directed into the turbine18to cause the turbine18to rotate about an axis11and drive the compressor14and the fan21.

The turbine18includes at least one turbine wheel assembly19and a turbine shroud20positioned to surround the turbine wheel assembly19as shown inFIG.1. The turbine wheel assembly19includes a plurality of blades19B. The hot, high pressure combustion products from the combustor16are directed toward the blades19B of the turbine wheel assemblies19. The turbine shroud20is coupled to a turbine case23of the gas turbine engine10and extends around the turbine wheel assembly19to block gases from passing over the turbine blades19B during use of the turbine section18in the gas turbine engine10.

The turbine assembly24is adapted for use in the gas turbine engine10ofFIG.1, in particular as a segment of the turbine shroud20of the turbine18. Illustratively, the turbine assembly24includes the turbine case23, a turbine shroud assembly25having a carrier segment26and a blade track segment, and a locating plate34arranged axially forward of the carrier segment26. The locating plate34is configured to be coupled to the turbine case23so as to block axially forward movement of the carrier segment26, prevent separation of the carrier segment26from the turbine case23, and dampen vibrations of the locating plate34.

As shown inFIGS.2A and2B, the turbine assembly24includes the carrier segment26. Illustratively, the carrier segment26is a segmented portion of the turbine shroud20of the turbine18, although a person skilled in the art will understand that a full hoop carrier may be utilized including the same components of the carrier segment26described herein.

The carrier segment26includes an outer wall27arranged circumferentially at least partway around the axis11of the gas turbine engine10. The outer wall27may be curved about the axis11so as to define a first radius of curvature of the outer wall27. The outer wall27may include two hangers28A,28B extending radially outwardly for coupling the carrier segment26to the turbine case23. In some embodiments, the carrier segment26further includes a plurality of flanges29extending radially inwardly.

As can be seen inFIG.2A, a first hanger28A of the carrier segment26may be coupled to a first hook23A of the turbine case23, and a second hanger28B may be coupled to a second hook23B of the turbine case23. The first hanger28A is located axially aft of and spaced apart from the second hanger28B. Similarly, the first hook23A is located axially aft of and spaced apart from the second hook23B. Each hanger28A,28B and each hook23A,23B may extend in the circumferential direction as well, and may extend equal lengths in this direction.

Illustratively, the carrier segment26further includes a blade track segment30arranged circumferentially at least partway around the axis11of the gas turbine engine10, although a person skilled in the art will understand that a full hoop blade track may be utilized including the same components of the blade track segment30described herein. The blade track segment30may be a ceramic matrix composite component configured to directly face the high temperatures of the gases flowing through the gas turbine engine10. The carrier segment26may be a metallic support component configured to interface with other metallic components of the gas turbine engine10to support the blade track segment30to radially locate the bladed track segment30relative to the axis11.

During operation of the gas turbine engine10, the hot, high-pressure products directed into the turbine18from the combustor16flow across a shroud wall31of the blade track segment30. The hot gases flowing across the shroud wall31heat the blade track segment30, which may transfer heat to retainers (not shown) that couple the blade track segment30to the carrier segment26. The shroud wall31may define a portion of a gas path of the turbine assembly24.

In the illustrative embodiment, the turbine shroud20is made up of a number of turbine assemblies24, including the carrier segment26and the locating plate34described in detail below, that each extend circumferentially partway around the axis11and cooperate to surround the turbine wheel assembly19. In other embodiments, the turbine shroud20is annular and non-segmented to extend fully around the axis11and surround the turbine wheel assembly19. In yet other embodiments, certain components of the turbine shroud20are segmented while other components are annular and non-segmented.

Each turbine assembly24further includes the locating plate34, as shown inFIGS.2A-7C. Illustratively, the locating plate34is a segmented portion of the turbine shroud20of the turbine18and is arranged circumferentially at least partway around the axis11. A person skilled in the art will understand that a full hoop locating plate may be utilized including the same components of the locating plate34described herein.

The locating plate34is arranged axially forward of the carrier segment26and includes a main wall36that may be curved about the axis11so as to define a second radius of curvature of the main wall36, as shown inFIGS.2B-3B. In some embodiments, the first radius of curvature of the outer wall27of the carrier segment26is equal to the second radius of curvature of the main wall36. In some embodiments, the first and second radii of curvature of the outer wall27and the main wall36are equal to a third radius of curvature of the turbine case23.

Illustratively, the main wall36extends further in the circumferential direction than the axial direction, and has a relatively small thickness as measured in the radial direction. As can be seen inFIGS.2B-3B, the main wall36includes a main wall upper surface37and a main wall bottom surface38opposite the main wall upper surface37. The main wall36further includes a first circumferential side39and a second circumferential side40opposite the first circumferential side39.

As shown in detail inFIGS.2A-5A,6A,7A, and7B, the locating plate34further includes a raised portion42extending upwardly away from the main wall upper surface37. A person skilled in the art will understand that the usage of the terms “upwardly” or “downwardly” herein correspond to radially outwardly and radially inwardly, respectively, unless otherwise noted. The raised portion42may be generally rectangular and be located centrally along a circumferential extent of the main wall36. In some embodiments, the main wall36may be divided in half by a central, axially extending axis43, and the raised portion42may be arranged exactly centrally on the axis43, as shown inFIG.2B.

The raised portion42may define a raised portion upper surface44that is curved so as to define a fourth radius of curvature, as can be seen in detail inFIGS.4A and4B. In some embodiments, the fourth radius of curvature of the raised portion upper surface44is equal to the first, second, and third radii of curvatures of the outer wall27, the main wall36, and the turbine case23. The raised portion42may include fillets45,46on opposing circumferential sides that extend from the opposing circumferential sides to the main wall upper surface37, as can be seen inFIGS.2B-3B.

The raised portion42may further include a hole48extending radially therethrough, as shown inFIGS.2B,3A-6B, and7C. In some embodiments, the hole48may extend entirely through the raised portion42and entirely through the main wall36continuously. Illustratively, as shown specifically inFIGS.5B,6B, and7C, the main wall36includes a circular recess50formed therein that opens to the main wall bottom surface38. The hole48may open into the circular recess50, and in some embodiments, the diameter of the hole48is smaller than the diameter of the circular recess50.

As shown in detail inFIGS.3A,5A, and6A, the raised portion42may further includes a recess52formed therein. The recess52may open out of an axially aft side41A of the main wall36and extend partially axially forward into the raised portion42. In some embodiments, the recess52terminates axially aft of the hole48.

The locating plate34may further include a first axially aft ledge56extending upwardly away from the main wall upper surface37, as shown in detail inFIG.3A. The first axially aft ledge56may connect to the raised portion42and extend circumferentially away from the raised portion42and connect to a first circumferential ledge60located on the first circumferential side39of the main wall36. Similarly, the locating plate34may further include a second axially aft ledge58extending upwardly away from the main wall upper surface37. The second axially aft ledge58may connect to the raised portion42and extend circumferentially away from the raised portion42and connect to a second circumferential ledge68located on the second circumferential side40of the main wall36.

Each of the first and second axially aft ledges56,58may include a tapered axially aft portion56T,58T. Each of the first and second axially aft ledges56,58may include fillets56F,58F that extend into the main wall upper surface37and connect to the fillets45,46of the raised portion42, as shown inFIG.3B. In some embodiments, a lip76extends downwardly away from the main wall bottom surface38on the axially aft side41A of the main wall36and is flush with the first and second axially aft ledges56,58, as shown inFIGS.3A,5A,6B, andFIGS.7A-7C.

The locating plate34further includes the first and second circumferential ledges60,68arranged on the first and second circumferential sides39,40of the main wall36, as shown inFIGS.2B-5A,6A,7A, and7B. Each of the first and second circumferential ledges60,68extend upwardly away from the main wall upper surface37and also extend axially from the axially aft side41A of the main wall36to an axially forward side41F of the main wall36along the first and second circumferential sides39,40.

In some embodiments, the first and second circumferential ledges60,68may include fillets61,69that extend into the main wall upper surface37and connect to the fillets56F,58F of the first and second axially aft ledges56,58, as shown inFIGS.2B-3B. The first and second circumferential ledges60,68and its fillets61,69, the raised portion42and its fillets45,46, and the first and second axially aft ledges56,58and its fillets56F,58F together form cavities67,74in the locating plate34, as can be seen in detail inFIGS.2B-3B. The cavities67,74are designed to reduce overall weight of the locating plate34.

In the illustrative embodiment, the locating plate34further includes support extensions62,64,70,72extending upwardly away from turbine shroud assembly124, as shown inFIGS.2B-5A,6A,7A, and7B. In particular, first and second support extensions62,64are arranged on the first circumferential ledge60and extend upwardly therefrom. Similarly, third and fourth support extensions70,72are arranged on the second circumferential ledge68and extend upwardly therefrom. Although two support extensions are arranged on the first and second circumferential ledges60,68in the illustrative embodiments, a person skilled in the art will understand that more or fewer than two support extensions may be utilized on the locating plate34, such as one, three, four, or five support extensions arranged on the first and second circumferential ledges60,68.

In some embodiments, the first, second, third, and fourth support extensions62,64,70,72are formed as columnar posts, as shown in detail inFIGS.3A and3B. Illustratively, the first, second, third, and fourth support extensions62,64,70,72are formed as four-sided posts, and the axially aft side64T,72T of the axially aftmost support extensions (shown as the second and fourth support extensions64,72) is tapered.

As shown in2B-5A,6A,7A, and7B, the first and second support extensions62,64are axially spaced apart from each other, and similarly the third and fourth support extensions70,72are axially spaced apart from each other. In some embodiments, the first and third support extensions62,70are arranged on an axially forwardmost end of the circumferential ledges60,68, and the second and fourth support extensions64,72are arranged on an axially aftmost end of the circumferential ledges60,68.

Illustratively, the raised portion42is positioned on the main wall upper surface37circumferentially between the first and second support extensions62,64and the third and fourth support extensions70,72. Specifically, the raised portion42is located centrally on the main wall36, being divided in half by the central, axially extending axis43, as shown inFIG.2B. As such, the first and second support extensions62,64and the third and fourth support extensions70,72are located equidistant from the axis43.

Illustratively, the locating plate34and its components are comprised of metallic materials. In some embodiments, at least the main wall36of the locating plate34is flexible so as to allow some flexion during coupling of the locating plate34to the turbine case23. In other embodiments, the locating plate34and all of its components are flexible. In some embodiments, the locating plate34and all of its components except for the four support extensions62,64,70,72are flexible.

FIG.4Ashows an axially front view of the locating plate34prior to coupling to the turbine case23. As can be seen inFIG.4A, the first and second support extensions62,64extend upwardly by a radial distance62H, as measured from the main wall upper surface37, and the third and fourth support extensions70,72extend upwardly by a radial distance70H, as measured from the main wall upper surface37. Illustratively, the radial distances62H,70H are equal, although a person skilled in the art will understand that the radial distances62H,70H may be different based on the design of the locating plate34, the carrier segment26, the turbine case23, and the other engine10components.

As can also be seen inFIG.4A, the raised portion42extends upwardly a radial distance42H, as measured from the main wall upper surface37. Illustratively, the radial distance42H is less than the radial distances62H,70H. Accordingly, in this first arrangement of the turbine assembly24, a gap42G is formed between the raised portion upper surface44and a radially inwardly facing surface23S of the turbine case23. Thus, prior to coupling of the locating plate34to the turbine case23, the four support extensions62,64,70,72are in contact with the radially inwardly facing surface23S of the turbine case23, while the raised portion upper surface44is not in contact with the radially inwardly facing surface23S. In some embodiments, the turbine case23extends circumferentially around the carrier segment26and the locating plate34and is arranged radially outwardly of the carrier segment26and the locating plate34.

As can be seen inFIG.4B, which shows a second arrangement of the turbine assembly124, the raised portion is coupled to the turbine case23via at least one fastener90extending through a hole92formed in the turbine case23and into the hole48of the raised portion42. The fastener90may be a bolt configured to engage with threads of the holes48,92and may include a nut94so as to couple the locating plate34to the turbine case23. Due to the locating plate34being flexible, as the fastener90is tightened, the raised portion upper surface44is pulled toward the turbine case23and eventually into contact with the radially inwardly facing surface23S of the turbine case23. Because the four support extensions62,64,70,72are already contacting the turbine case23and the locating plate34is pulled into even further contact with the turbine case23via the tightening of the fastener90, secure contact of all four support extensions62,64,70,72with the radially inwardly facing surface23S of the turbine case23can be assured, even if imperfections exist in the support extensions62,64,70,72. Moreover, the contact between the raised portion42and the support extensions62,64,70,72with the turbine case23dampens vibrations of the locating plate34.

Moreover, as can be seen inFIG.2A, under normal operating conditions in which the carrier segment26does not move or only moves axially aft, the locating plate34does not contact the carrier segment26. In the event that forces cause the carrier segment26to move axially forward, the locating plate34will block axially forward movement of the carrier segment26. Additionally, the locating plate34will prevent separation of the hangers28A,28B of the carrier segment26from the hooks23A,23B of the turbine case23.

Another embodiment of a turbine assembly124for use with the gas turbine engine10is shown inFIGS.8-9D. The turbine assembly124is similar to the turbine assembly24shown inFIGS.2A-7C, and described herein. Accordingly, similar reference numbers in the100series indicate features that are common between the turbine assembly124and the turbine assembly24. The description of the turbine assembly24is incorporated by reference to apply to the turbine assembly124, except in instances when it conflicts with the specific description and the drawings of the turbine assembly124.

Similar to the turbine assembly24described above, the turbine assembly124includes a locating plate134for coupling to the turbine case23which is similar to the locating plate34, as shown inFIGS.8-9D. Unlike the locating plate34, the locating plate134of this embodiment does not include support extensions. Instead, the first and second circumferential ledges160,168extend upwardly further than the first and second circumferential ledges60,68described above, and also each include a seal162,170.

Specifically, the first and second circumferential ledges160,168extend from the axially forward side141F of the main wall136to the axially aft side141A of the main wall136, as shown inFIG.8. In other words, the first and second circumferential ledges160,168extend from the axially forward side141F of the main wall136and connect to the first and second axially aft ledges156,158. Accordingly, each of the first and second circumferential ledges160,168includes an upper surface161,169extending along a top side of the axially extending first and second circumferential ledges160,168from the axially forward side141F to the axially aft side141A. Each upper surface161,169includes a groove163,171formed therein that extends along a length of the upper surface161,169for receiving the seals162,170. In some embodiments, the upper surfaces161,169may be planar and flat, and in other embodiments, the upper surfaces161,169may be generally planar and slightly curved to match a contour of turbine case23.

As shown inFIGS.8-9D, each of the first and second circumferential ledges160,168includes a seal162,170arranged within the grooves163,171formed in the upper surface161,169. In some embodiments, the seals162,170may be rope seals, although any seal known to a person skilled in the art may be used. The seals162,170are configured to contact the radially inwardly facing surface23S of the turbine case23. As can be seen inFIGS.9C and9D, the grooves163,171may be formed to be wider or larger than the diameter of the seals162,170to allow compression of the seals162,170when the locating plate134is coupled to the turbine case23(seeFIG.9B).

As can be seen inFIGS.9A and9B, radial distances160H,168H (i.e. radial heights) of the combination of the first and second circumferential ledges160,168and their respective seals162,170are measured between the main wall upper surface137and the top of the seals162,170. As can also be seen inFIG.9A, which shows a first arrangement of the turbine assembly124, the raised portion142extends upwardly a radial distance142H, as measured from the main wall upper surface137. Illustratively, the radial distance142H is less than the radial distances160H,168H. Accordingly, a gap142G is formed between the raised portion upper surface144and the radially inwardly facing surface23S of the turbine case23. Thus, prior to coupling of the locating plate134to the turbine case23, the seals162,170on the first and second circumferential ledges160,168are in contact with the radially inwardly facing surface23S of the turbine case23, while the raised portion upper surface144is not in contact with the radially inwardly facing surface23S.

As can be seen inFIG.9B, which shows a second arrangement of the turbine assembly124, the raised portion is coupled to the turbine case23via the at least one fastener90. Due to the locating plate134being flexible, as the fastener90is tightened, the raised portion upper surface144is pulled toward the turbine case23and eventually into contact with the radially inwardly facing surface23S of the turbine case23. Moreover, the seals162,170are compressed, as shown inFIG.9B.

Because the seals162,170are already contacting the turbine case23and the locating plate134is pulled into even further contact with the turbine case23via the tightening of the fastener90, secure contact of the seals162,170with the radially inwardly facing surface23S of the turbine case23can be assured. Moreover, the contact between the raised portion142and the seals162,170with the turbine case23dampens vibrations of the locating plate134.

Moreover, as can be seen inFIG.2A, under normal operating conditions in which the carrier segment26does not move or only moves axially aft, the locating plate134does not contact the carrier segment26. In the event that forces cause the carrier segment26to move axially forward, the locating plate134will block axially forward movement of the carrier segment26. Moreover, the locating plate134will prevent separation of the hangers28A,28B of the carrier segment26from the hooks23A,23B of the turbine case23.

Another embodiment of a turbine assembly224for use with the gas turbine engine10is shown inFIGS.10A-13. The turbine assembly224is similar to the turbine assemblies24,124shown inFIGS.2A-9D, and described herein. Accordingly, similar reference numbers in the200series indicate features that are common between the turbine assembly224and the turbine assemblies24,124. The descriptions of the turbine assemblies24,124are incorporated by reference to apply to the turbine assembly224, except in instances when they conflict with the specific description and the drawings of the turbine assembly224.

Similar to the turbine assembly24described above, the turbine shroud assembly224includes a locating plate234for coupling to the turbine case23which is similar to the locating plate34, as shown inFIGS.10A,10B,12, and13. Specifically, the locating plate234includes a raised portion242and four support extensions262,264,270,272similar to the locating plate34. Additionally, the locating plate234includes a first anti-rotation extension280extending radially inwardly away from the main wall236, and a second anti-rotation extension284extending radially inwardly away from the main wall236and circumferentially spaced apart from the first anti-rotation extension280that are configured to prevent circumferential rotation of a vane assembly288located radially inwardly of the locating plate234. A person skilled in the art will understand that the anti-rotation extensions280,284can also apply to a locating plate similar to the locating plates34,134described with reference toFIGS.2A-9D.

Illustratively, the first anti-rotation extension280includes a sloped inner surface281and an opposing, first extension surface282that faces a first circumferential direction94, as shown inFIG.12. The sloped inner surface281faces an opposing, second circumferential direction95. Similarly, the second anti-rotation extension284includes a sloped inner surface285and an opposing, second extension surface286that faces the second circumferential direction95. The sloped inner surface285faces the first circumferential direction94. The angles of the slopes of the sloped inner surfaces281,285may be the same or different. In some embodiments, the first and second anti-rotation extensions280,284may each include a stepped axially aft surface283S,287S and a sloped axially forward surface283F,287F, as shown inFIG.10B.

In some embodiments, as shown inFIG.12, the first anti-rotation extension280is circumferentially spaced apart from the central axis243a first distance and the second anti-rotation extension284is circumferentially spaced apart from the central axis243a second distance. Illustratively, the first distance between the extension280and the central axis243is different than the second distance between the extension284and the central axis243, although a person skilled in the art will understand that the first and second distances may be equal based on the design of the turbine assembly224components.

As shown inFIGS.11-13, the turbine assembly224further includes the vane assembly288. Illustratively, the vane assembly288extends partway around the axis11and is segmented. In the illustrative embodiment, a plurality of vane assemblies288each extend circumferentially partway around the axis11and cooperate to form a fully annular vane assembly. In other embodiments, the vane assembly288may be fully annular and not segmented to extend fully around the axis11.

The vane assembly288includes a plurality of vanes289circumferentially spaced apart from each other, as shown inFIG.13. The vane assembly288further includes an inner platform290arranged on a radially inner side of the vanes289, and an outer platform291arranged on a radially outer end of the vanes289. As can be seen inFIGS.11and12, the outer platform291includes a main platform291A, an axially aft flange291B that extends circumferentially along the main platform291A, and an axially forward flange291C that extends circumferentially along the main platform291A and is axially spaced apart from the axially aft flange291B. In some embodiments, a central axis291D of the main platform291A is aligned with the central axis243of the locating plate234. In some embodiments, the main platform291A of the outer platform291is curved so as to define a fifth radius of curvature, as shown inFIG.12. In some embodiments, the first, second, third, and fourth radii of curvature are equal to the fifth radius of curvature of the main platform291A of the outer platform291.

As can be seen in detail inFIGS.11-13, the outer platform291includes first and second anti-rotation protrusions292,295that extend radially outwardly away from a radially outwardly-facing surface291B1of the outer platform291. Specifically, the anti-rotation protrusions292,295extend radially outwardly away from a top surface291B1of the axially aft flange291B of the outer platform291, as can be seen inFIG.11.

Illustratively, the first and second anti-rotation protrusions292,295are formed as block-like structures that extend upwardly from the axially aft flange291B and are circumferentially spaced apart from each other, as shown inFIGS.11-13. The first anti-rotation protrusion292includes a first protrusion surface293that faces the second circumferential direction295and the second anti-rotation protrusion295includes a second protrusion surface296that faces the first circumferential direction94. Each anti-rotation protrusion292,295also includes a radially outer surface294,297that is radially spaced apart from the anti-rotation extensions280,284of the locating plate234, as shown inFIG.12.

Illustratively, the first and second anti-rotation protrusions292,295are circumferentially spaced apart such that they are configured to engage and contact the anti-rotation extensions280,284of the locating plate234, as shown inFIGS.12and13. Specifically, the first and second protrusion surfaces293,296are configured to engage the first and second extension surfaces282,286of the anti-rotation extensions280,284so as to block circumferential movement of the vane assembly288relative to the locating plate234in response to circumferential forces acting on the vane assembly288, as shown inFIG.12. Specifically, the first extension wall282will block circumferential movement of the vane assembly288in the second circumferential direction95, and the second extension wall286will block circumferential movement of the vane assembly288in the first circumferential direction94. In this way, circumferential loads can be transferred from the vane assembly288to the locating plate234, and thus to the turbine case223.

In some embodiments, the first and second anti-rotation protrusions292,295are circumferentially spaced far enough apart such that at least one of the first and second protrusion surfaces293,296is slightly spaced apart from the corresponding extension surface282,286(shown exaggerated inFIGS.12and13). For example, a gap292G exists between the first protrusion surface293and the first extension surface282, while no gap exists between the second protrusion surface296and the second extension surface286, as shown inFIGS.12and13. In some embodiments, a gap exists between both sets of surfaces282,286,293,296. The small gap or gaps allow for thermal expansion of the components of the turbine assembly224or any other incidental movement of the components. The gap or gaps are small enough to allow an extremely small amount of movement in the event the vane assembly288moves circumferentially before being stopped by one of the extension surfaces282,286. In some embodiments, no gap exists between either set of surfaces282,286,293,296such that no movement or expansion of components is permitted.

A method according to the present disclosure includes a first operational step of arranging a turbine case23circumferentially around an axis11, a second operational step of arranging a turbine shroud assembly25including a carrier segment26made of metallic materials circumferentially and a blade track segment30at least partway around the axis11and radially inwardly of the turbine case23, and a third operational step of coupling the blade track segment30to the carrier segment26.

The method can further include a fourth operational step of coupling the carrier segment26to the turbine case23. The method can further include a fifth operational step of arranging, in a first arrangement, a locating plate34with the turbine case23axially forward of the carrier segment26to block axially forward movement of the carrier segment26and prevent separation of the carrier segment26from the turbine case23.

The locating plate includes a main wall36, a raised portion42extending upwardly away from the main wall36a first radial distance62H,70H, a first support extension62,64,70,72extending upwardly away from the main wall36a second radial distance42H and a second support extension62,64,70,72circumferentially spaced apart from the first support extension62,64,70,72and extending upwardly away from the main wall36the second radial distance42H. The first and second support extensions62,64,70,72are circumferentially spaced apart from the raised portion42. The second radial distance42H is greater than the first radial distance62H,70H such that, in the first arrangement, the first and second support extensions62,64,70,72contact the turbine case23and the raised portion42is spaced apart from the turbine case23.

The method can further include a sixth operational step of coupling, in a second arrangement, the locating plate34to the turbine case23such that the first and second support extensions62,64,70,72and the raised portion42simultaneously contact the turbine case23via a fastener90extending through the turbine case23and the raised portion42.

While the disclosure has been illustrated and described in detail in the foregoing drawings and description, the same is to be considered as exemplary and not restrictive in character, it being understood that only illustrative embodiments thereof have been shown and described and that all changes and modifications that come within the spirit of the disclosure are desired to be protected.