JP7146390B2 - Struts for exhaust frames in turbine systems - Google Patents

Description

TECHNICAL FIELD This disclosure relates generally to turbine systems and, more particularly, to support struts for exhaust frames of turbine systems.

In conventional turbine systems, an exhaust housing or frame is typically attached or coupled to the outlet of a turbine component. These exhaust housings are attached to the turbine components to safely direct gases passing through and/or from the turbine components to the environment surrounding the turbine system, or to direct gases for additional processes. Direct the gas to another component (eg, a heat recovery steam generator) that can utilize the Conventional exhaust housings typically include two concentric shells that are directly coupled to turbine components and flow passages for gas defined between the shells.

Additionally, conventional exhaust housings typically include a plurality of support structures disposed between and joining the two shells. These support structures are often called struts. During operation of a turbine system, concentric shells can be subjected to significant stresses and/or loads from the system and its components. For example, movement of turbine components during operation of the turbine system can exert significant stresses, forces or loads on the exhaust housing. Struts are utilized within the exhaust housing to support and/or stabilize the shell during operation of the turbine system.

Conventional struts are made of solid pieces of rigid material (e.g., metal) to ensure support/stabilization and enable the exhaust housing to withstand significant stresses and loads during operation of the turbine system. and is as thick as possible. However, increased strut thickness reduces the operating efficiency of the exhaust housing and ultimately the turbine system. Specifically, multiple substantially thick struts can provide the desired support/stabilization and cover multiple flow areas created by the exhaust housing. As a result, gases flowing from turbine components into the exhaust housing may be blocked and/or diverted around these conventional struts, potentially causing an undesirable increase in pressure within the exhaust housing.

Conventional struts formed from solid rigid materials may experience similar and/or different stresses and loads during operation of the turbine system. These stresses and loads can reduce strut strength over time. The combination of reduced size and strength of these conventional struts makes them susceptible to damage or breakage. If the struts of the exhaust housing are damaged, the concentric shell of the exhaust housing may no longer be supported or stabilized. As a result, the exhaust housing may become loose and/or turbine components may shift, move, or become unstable. This can reduce the overall operating efficiency of the entire turbine system.

A first aspect of the present disclosure provides a strut for an exhaust frame of a turbine system, the strut formed through the body including a leading edge and a trailing edge and extending radially between the leading and trailing edges. an extending aperture, a first section formed between the leading edge and the aperture, and a second section formed between the trailing edge and the aperture and configured to move independently of the first section; Section and.

A second aspect of the present disclosure provides an exhaust frame for a turbine system, the exhaust frame including an inner casing, an outer casing concentrically surrounding the inner casing, and radially extending between the inner casing and the outer casing. a plurality of struts coupled together, each of the plurality of struts having a body including leading and trailing edges; an aperture formed through the body extending radially between the leading and trailing edges; A first section formed between the edge and the opening and a second section formed between the trailing edge and the opening and configured to move independently of the first section.

A third aspect of the present disclosure provides a turbine system including a turbine including a turbine shell, a shaft extending through the turbine, and an exhaust frame positioned adjacent the turbine, the exhaust frame receiving the shaft. an outer casing concentrically surrounding the inner casing and coupled to the turbine shell; and a plurality of radially extending struts coupled between the inner casing and the outer casing. , at least one of the plurality of struts includes a body including a leading edge and a trailing edge, an opening formed through the body extending radially between the leading edge and the trailing edge, and between the leading edge and the opening. and a second section formed between the trailing edge and the opening and configured to move independently of the first section.

Exemplary aspects of the present disclosure solve the problems described herein and/or other problems not discussed.

These and other features of the present disclosure will be more readily understood from the following detailed description of various aspects of the disclosure, taken in conjunction with the accompanying drawings showing various embodiments of the disclosure.

1 is a schematic diagram of a gas turbine system according to an embodiment; FIG. 2 is an isometric view of an exhaust frame including struts of the gas turbine system of FIG. 1, according to an embodiment; FIG. 3 is a side view of a single strut of the exhaust frame of FIG. 2, according to embodiments; FIG. 4 is a cross-sectional bottom view of the strut of FIG. 3 along line 4-4, in accordance with an embodiment; FIG. FIG. 10 is a side view of a single strut including a single aperture, according to embodiments; FIG. 4B is a side view of a single strut including a single aperture, according to another embodiment; FIG. 10 is a side view of a single strut including a single aperture, according to further embodiments; FIG. 4 is a side view of a single strut including multiple openings, according to embodiments; FIG. 10 is a side view of a single strut including multiple openings, according to additional embodiments; FIG. 10 is a side view of a single strut including multiple openings according to further embodiments;

Note that the drawings of the present disclosure are not drawn to scale. The drawings are intended to depict only typical aspects of the disclosure, and therefore should not be considered as limiting the scope of the disclosure. In the drawings, like numbers represent like elements from one drawing to another.

As a first problem, in order to clearly describe the present disclosure, it becomes necessary to select certain terminology when referring to and describing the relevant mechanical components within the scope of the present disclosure. In doing so, where possible, common industry terminology is used and utilized in a manner consistent with its accepted meaning. Unless otherwise indicated, such terminology is to be given a broad interpretation consistent with the context of the present application and the scope of the appended claims. Those of ordinary skill in the art will appreciate that a particular component may often be referred to using several different or overlapping terms. What may be described herein as being of a single component may include and be referred to in another context as being of multiple components. Alternatively, what may be described herein as comprising multiple components may be referred to elsewhere as a single component.

Moreover, some descriptive terms may be used routinely herein and it should prove useful to define these terms at this point. These terms and their definitions are as follows unless otherwise indicated. As used herein, "downstream" and "upstream" refer to the flow of working fluid through a turbine engine or, for example, air flow through a combustor, or coolant through one of the turbine's component systems. A term that indicates the direction of fluid flow. The term "downstream" corresponds to the direction of fluid flow and the term "upstream" refers to the opposite direction of flow. The terms "forward" and "aft" refer to directions, with "forward" referring to the forward or compressor end of the engine and "aft" referring to the aft or turbine end of the engine, unless otherwise specified. Further, the terms "leading" and "following" may be used and/or understood in the same descriptive terms as the terms "forward" and "rearward," respectively. It is often required to describe parts at different radial, axial and/or circumferential positions. The "A" axis represents the axial direction. As used herein, the terms "axial" and/or "axially" refer to the relative motion of bodies along an axis A that is substantially parallel to the axis of rotation of the turbine system (particularly the rotor section). pointing to a specific position/direction. Further, as used herein, the terms "radial" and/or "radially" refer to an axis "R" that is substantially perpendicular to axis A and intersects axis A at only one location. Refers to the relative position/orientation of an object along (eg, FIG. 1). Finally, the term "circumferential" refers to movement or position about axis A (eg, axis "C").

TECHNICAL FIELD The following disclosure relates generally to turbine systems, and more specifically to support struts for exhaust frames of turbine systems.

These and other embodiments are described below with reference to FIGS. 1-10. However, those skilled in the art will readily appreciate that the detailed descriptions given herein with respect to these figures are for purposes of illustration and should not be construed as limiting.

FIG. 1 shows a schematic diagram of a gas turbine system 10 that may be used herein. Gas turbine system 10 may include a compressor 12 . Compressor 12 compresses an incoming flow of air 18 . Compressor 12 channels a flow of compressed air 20 to combustor 22 . Combustor 22 mixes a flow of compressed air 20 with a flow of pressurized fuel 24 and ignites the mixture to produce a flow of combustion gases 26 . Although only a single combustor 22 is shown, gas turbine system 10 may include any number of combustors 22 . The stream of combustion gases 26 is then channeled to a turbine 28 that typically includes a plurality of turbine blades or buckets and stator vanes. The flow of combustion gases 26 drives a turbine 28 to generate mechanical work. Mechanical work produced in turbine 28 drives compressor 12 via shaft 30 extending through turbine 28 and may be used to drive an external load 32 such as a generator.

Gas turbine system 10 may also include an exhaust frame 34 . As shown in FIG. 1 , the exhaust frame 34 may be positioned adjacent the turbine 28 of the gas turbine system 10 . More specifically, the exhaust frame 34 may be positioned adjacent to the turbine 28 and positioned substantially downstream of the turbine 28 and/or the flow of combustion gases 26 flowing from the combustor 22 to the turbine 28 . can do. As discussed herein, a portion of exhaust frame 34 (eg, outer casing) may be directly coupled to enclosure or shell 36 of turbine 28 .

After the combustion gases 26 flow to drive the turbine 28 , the combustion gases 26 may exhaust, enter and/or exit through the exhaust frame 34 in a flow direction (D). In the non-limiting example shown in FIG. 1, the combustion gases 26 may flow in a flow direction (D) through the exhaust frame 34 and be discharged from the gas turbine system 10 (eg, to the atmosphere). In another non-limiting example, where the gas turbine system 10 is part of a combined cycle power plant (e.g., including a gas turbine system and a steam turbine system), the combustion gases 26 are discharged from the exhaust frame 34 in a flow direction ( D) may flow into the heat recovery steam generator of the combined cycle power plant.

FIG. 2 shows an isometric view of an exemplary exhaust frame 34 of gas turbine system 10 . Exhaust frame 34 may include an inner casing 38 and an outer casing 40 . Inner casing 38 may be disposed within, substantially enclosed, and/or concentric with outer casing 40 . As shown in FIG. 2, the inner casing 38 may be substantially annular and may include an opening 42 formed therein. As a non-limiting example, opening 42 in inner casing 38 may be configured to receive a portion of shaft 30 of gas turbine system 10 (see FIG. 1). That is, a portion of the shaft 30 of the gas turbine system 10 may be disposed within and/or pass through the opening 42 of the inner casing 38 of the exhaust frame 34 . In a non-limiting example, shaft 30 is supported by inner casing 38 and is driven within opening 42 when turbine 28 of gas turbine system 10 is driven by the flow of combustion gases 26 as discussed herein. It can rotate freely. In another non-limiting example, the opening 42 of the inner casing 38 includes a shaft support (not shown) that may be secured within the opening 42 of the inner casing 38 and coupled to the shaft 30 of the gas turbine system 10 . can accept. A shaft support secured within an opening 42 in the inner casing 38 of the exhaust frame 34 couples the shaft 30 to the inner casing 38 such that the shaft 30 is supported during operation of the gas turbine system 10 as discussed herein. It can be allowed to rotate freely.

An outer casing 40 of the exhaust frame 34 may be arranged around the inner casing 38 . Specifically, as shown in FIG. 2, the outer casing 40 may concentrically surround the inner casing 38 of the exhaust frame 34 . Similar to inner casing 38, outer casing 40 may be substantially annular and may include an opening 44 formed therein. Openings 44 may define flow regions 46 for combustion gases 26 between outer casing 40 and inner casing 38 . That is, during operation of gas turbine system 10, combustion gases 26 flow in direction (D) (see FIG. 1) into and through flow region 46 and thereafter exhaust frame 34, as discussed herein. can be exhausted from Briefly returning to FIG. 1 and continuing to refer to FIG. A portion of shaft 30 can be substantially and/or concentrically enclosed.

Exhaust frame 34 may also include at least one strut 100 positioned between inner casing 38 and outer casing 40 . As a non-limiting example, exhaust frame 34 may include a plurality of struts 100 circumferentially disposed between inner casing 38 and outer casing 40 . As shown in FIG. 2, each strut 100 of exhaust frame 34 may extend radially between inner casing 38 and outer casing 40 and may be coupled to each of inner casing 38 and outer casing 40 . Struts 100 may be coupled to each of inner casing 38 and outer casing 40 using any suitable coupling technique including, but not limited to, mechanical fastening, welding, brazing, casting, and the like. Additionally, the plurality of struts 100 of the exhaust frame 34 may be positioned within the flow area of the exhaust frame 34 defined between the inner casing 38 and the outer casing 40 . As discussed herein, struts 100 of exhaust frame 34 may couple inner casing 38 and outer casing 40 and support exhaust frame 34 during operation of gas turbine system 10 .

FIG. 3 shows a side view of a single strut 100 of exhaust frame 34 of gas turbine system 10 (see FIG. 1). Strut 100 may include a body 101 and first and second ends 102 and 104 disposed at opposite ends of body 101 . A first end 102 of strut 100 may contact and/or be coupled to outer casing 40 of exhaust frame 34 (see FIG. 2). Additionally, the second end 104 of the strut 100 may contact and/or be coupled to the inner casing 38 of the exhaust frame 34 opposite the first end 102 and/or the outer casing 40 . Body 101 of strut 100 may also include leading edge 106 and trailing edge 108 disposed between first end 102 and second end 104 . Leading edge 106 may be positioned opposite and/or upstream of trailing edge 108 . During operation of gas turbine system 10 , combustion gases 26 flow in direction (D) toward first contact leading edge 106 and over body 101 of strut 100 before being exhausted and/or discharged from exhaust frame 34 . It can flow toward the trailing edge 108 .

Struts 100 of exhaust frame 34 may include at least one opening 110 formed through body 101 . Specifically, strut 100 may include at least one opening 110 formed extending radially into body 101 between leading edge 106 and trailing edge 108 . Additionally, at least one opening 110 may extend radially into body 101 and/or be formed between first end 102 and second end 104 of strut 100 . At least one opening 110 may be formed completely through the body 101 of the strut 100 so that combustion gases 26 flowing over the strut 100 also flow through the openings 110 and/or the body 101 of the strut 100. be able to.

In the non-limiting example shown in FIG. 3, strut 100 can include two separate openings 110A, 110B formed therethrough. The first opening 110A may be located between the leading edge 106 and the trailing edge 108, specifically between the leading edge 106 and the second opening 110B. Additionally, the second opening 110B may be positioned between the leading edge 106 and the trailing edge 108, specifically between the trailing edge 108 and the first opening 110A. As a result, the openings 110A, 110B can be positioned axially adjacent to each other. As shown in the non-limiting example of FIG. 3, the second opening 110B may be positioned axially adjacent to and axially downstream of the first opening 110A. It is understood that the number of openings 110 shown in the figures is merely exemplary. Accordingly, strut 100 may include more or fewer openings 110 than shown and described herein.

Apertures 110 can include various shapes, orientations and/or geometries when formed in strut 100 . The opening 110 and the shape or geometry of the opening 110 change, affect, control and/or effect movement and flexibility of the strut 100 during operation of the gas turbine system 10, as discussed in detail below. be able to. In the non-limiting example shown in FIG. 3, each opening 110A, 110B of strut 100 can be formed as a keyhole slot. Specifically, openings 110A and 110B are double-sided, including radial opening 112 extending radially between two substantially end openings 118 formed at each end of radial opening 112. It can be formed as a keyhole slot. End openings 118 formed at each end of radial openings 112 may be larger and/or have a diameter or width greater than the width of radial openings 112 . As a result, the end openings 118 can extend axially beyond the radial openings 112 in the struts 100 . As shown in the non-limiting example of FIG. 3, the radial openings 112 of the openings 110A, 110B can include substantially uniform widths and/or be substantially linear in shape. can be done.

It is understood that the shapes and/or geometries of the openings 110 shown in the figures are exemplary only. Accordingly, struts 100 may include different shapes and/or geometries of openings 110 than shown and described herein. Further, although shown herein to include similar, mirrored, or identical shapes between apertures 110, it is understood that each aperture 110 formed through strut 100 can be distinguished from one another. be done. As a result, each strut 100 of the exhaust frame 34 may include similarly or identically shaped openings, or may be shaped or shaped differently than the separate openings 110 of the same strut 100 and/or separate struts 100 of the exhaust frame 34 . Apertures 110 having a geometric shape can be included.

Strut 100 can include various portions and sections. That is, the strut 100, and specifically the body 101 of the strut 100, can include various portions and various sections that can be separate from the various portions. As discussed herein, various portions of strut 100 may be defined by features or geometry (eg, axial width and/or circumferential thickness) of body 101 of strut 100 . Conversely, the various sections of strut 100 may be defined by openings 110 formed through body 101 of strut 100, as discussed in more detail below.

Strut 100 may include separate portions axially disposed, formed, and/or radially extending between first end 102 and second end 104 . As shown in FIG. 3, strut 100 includes a first portion 120, a second portion 122, a first portion 120, a second portion 122, formed and/or extending between a first end 102 and a second end 104 of strut 100. and a third portion 124 . Separate portions 120 , 122 , 124 of strut 100 may also be formed and/or positioned between leading edge 106 and trailing edge 108 . Specifically, first portion 120 may be formed between leading edge 106 and second portion 122 . The second portion 122 may be formed axially adjacent and downstream of the first portion 120 . Additionally, a second portion 122 may be formed between the first portion 120 and the third portion 124 . A third portion 124 may be positioned axially adjacent downstream of the second portion 122 and may be formed between the second portion 122 and the trailing edge 108 of the strut 100 . It is understood that the number of parts shown in the figures is merely exemplary. Accordingly, strut 100 may include more or fewer radial portions than shown and described herein. Alternatively, strut 100 may include a single portion extending between first end 102 and second end 104 .

In the non-limiting example shown in FIG. 3, each of first portion 120, second portion 122 and third portion 124 can include axial widths that differ from each other. That is, the axial width of first portion 120 may be different than the axial widths of second portion 122 and third portion 124 . Further, the axial width of second portion 122 may be different than the axial width of third portion 124 . The axial width of each portion of strut 100 may influence, control and/or effect movement and flexibility of strut 100 during operation of gas turbine system 10, as discussed herein. Additionally, as discussed herein, the axial width of each portion of strut 100 also affects (e.g., improves) the function or efficiency (e.g., aerodynamics) of strut 100 during operation of gas turbine system 10 . can do. Although described herein as separate, the axial widths of at least two of first portion 120, second portion 122 and third portion 124 of strut 100 are substantially similar and may also be equal or identical.

In addition to or independently of different axial widths, multiple portions 120, 122, 124 of strut 100 may be defined by varying circumferential thicknesses. Referring briefly to FIG. 4, a cross-sectional bottom view of strut 100 along line 4--4 of FIG. 3 is shown. In the non-limiting example shown in FIG. 4, at least two of the plurality of portions 120, 122, 124 of strut 100 can include distinct circumferential thicknesses (T). Specifically, the first portion 120 of the strut 100 includes a first circumferential thickness (T ₁ ) and the second portion 122 has the first circumferential thickness of the first portion 120 . a second circumferential thickness (T ₂ ) different from or greater than the thickness (T ₁ ); Additionally, as shown in FIG. 4, the third portion 124 can include a third circumferential thickness (T ₃ ). Similar to the first circumferential thickness (T ₁ ), the second circumferential thickness (T ₂ ) is different from the third circumferential thickness (T ₃ ) of the third portion 124. may be different or larger. In a non-limiting example, the third circumferential thickness (T3) of the _third portion 124 is equal to the _first circumferential thickness (T1) of the first portion 120, or It can be different (eg, larger or smaller). The circumferential thickness (T) of each portion of strut 100 influences, controls and/or effects movement and flexibility of strut 100 during operation of gas turbine system 10, as discussed herein. can be done. Additionally, as discussed herein, the circumferential thickness (T) of each portion of strut 100 also has an effect on the function or efficiency (e.g., aerodynamics) of strut 100 during operation of gas turbine system 10. can be given (eg, improved). Although shown as having at least two distinct circumferential thicknesses, it is understood that strut 100 may include more or less thicknesses for multiple portions 120, 122, 124. . Alternatively, the portion of strut 100 formed between first end 102 and second end 104 may be substantially uniform in circumferential thickness, as discussed herein. good.

At least one of the plurality of portions 120 , 122 , 124 of strut 100 may include apertures 110 . Specifically, in the non-limiting example shown in FIG. 3, first opening 110A can be formed through second portion 122 of strut 100 and second opening 110B can be formed through third portion 122 of strut 100. 124 can be formed. As discussed herein, the formation of openings 110 in separate portions 120, 122, 124 of strut 100 affects, controls and/or effects movement and flexibility of strut 100 during operation of gas turbine system 10. can give It is understood that the formation or location of each opening 110 in the separate portions 120, 122, 124 of strut 100 shown in the figures is merely exemplary. Accordingly, apertures 110 may be formed in any or all of portions 120, 122, 124 of strut 100 rather than portions shown and described herein.

Returning to FIG. 3 and continuing to refer to FIG. 4, the struts 100 of the exhaust frame 34 can include multiple sections. The sections may be different than the portions 120, 122, 124 of strut 100. Specifically, the plurality of sections 126 , 128 , 130 may be at least partially defined and/or defined by openings 110 formed in and/or through strut 100 . In a non-limiting example where strut 100 includes openings 110A, 110B, three separate sections 126, 128, 130 may be formed in strut 100. As shown in FIG. As shown in FIGS. 3 and 4, a first section 126 may be formed between the leading edge 106 and the first opening 110A, and a second section 128 may be formed between the first opening 110A and the trailing edge 108. can be formed between More specifically, second section 128 of strut 100 is formed axially adjacent and/or downstream of first section 126 and between first opening 110A and second opening 110B. may be Additionally, a third section 130 of strut 100 may be formed axially adjacent and/or downstream of second section 128 between trailing edge 108 and second opening 110B.

Each of the plurality of sections 126, 128, 130 of strut 100 can include an axial width. The width of each of the plurality of sections 126, 128, 130 is determined by the axial distance between an edge of strut 100 (e.g., leading edge 106, trailing edge 108) and opening 110, and/or two openings 110 ( For example, it can be defined by the axial distance between the first opening 110A, the second opening 110B). As shown in FIG. 3, first section 126 includes a first axial width (W ₁ ), second section 128 includes a second axial width (W ₂ ), and third section 130 includes a second axial width (W 2 ). can include a _third axial width (W3). In the non-limiting example shown in FIG. 3, the first axial width (W ₁ ) of the first section 126 is the second axial width (W ₂ ) of the second section 128 and the third section may be similar or equal to the third axial width (W ₃ ) 130 of the . In other non-limiting examples described herein, the first axial width (W ₁ ) of the first section 126 is the second axial width (W ₂ ) of the second section 128 and /or may be different than the third axial width (W ₃ ) of the third section 130; Additionally, the second axial width (W ₂ ) of the second section 128 may be different than the third axial width (W ₃ ) of the third section 130 . As discussed herein, the width of each section of strut 100 influences, controls and/or effects the movement and flexibility of multiple sections 126, 128, 130 of strut 100 during operation of gas turbine system 10. can give.

As mentioned above, the plurality of portions 120, 122, 124 of strut 100 may be defined by respective widths and/or thicknesses of each section. Conversely, multiple sections 126 , 128 , 130 of strut 100 may be defined by openings 110 formed in strut 100 . Accordingly, portions 120 , 122 , 124 and sections 126 , 128 , 130 of strut 100 may not be aligned with, correspond to, and/or refer to the same region of strut 100 . That is, at least one of the plurality of sections 126, 128, 130 of strut 100 includes and/or extends over (eg, two or more) portions of plurality of portions 120, 122, 124. direction) and vice versa. In the non-limiting example shown in FIGS. 3 and 4, the first opening 110A may be formed in the second portion 122 of the strut 100. As shown in FIG. As a result, first section 126 of strut 100 may include and/or extend axially over portions of first portion 120 and second portion 122 . Further, in the non-limiting example shown in FIGS. 3 and 4, the second opening 110B may be formed in the third portion 124 of the strut 100. As shown in FIG. Accordingly, second section 128 of strut 100 may include and/or extend axially over a portion of second portion 122 and a portion of third portion 124 . Third section 130 of strut 100 may include and/or extend axially over the remainder of third portion 124 not included in second section 128 .

Each of the plurality of sections 126 , 128 , 130 of strut 100 can flex and/or move independently of one another as a result of openings 110 formed through and extending radially above strut 100 . Specifically, in the non-limiting examples shown in FIGS. 3 and 4, first section 126 of strut 100 moves independently of second section 128 and third section 130, respectively. Can be configured. Additionally, second section 128 of strut 100 may be configured to move independently of first section 126 and third section 130 . Finally, third section 130 of strut 100 may be configured to move independently of first section 126 and second section 128 .

By moving each of the plurality of sections 126 , 128 , 130 of strut 100 independently of each other, the loads and/or stresses experienced by exhaust frame 34 and/or strut 100 during operation of gas turbine system 10 are reduced by strut 100 . can be more efficiently distributed and/or more efficiently managed by Improved distribution and/or management of the loads and/or stresses experienced by strut 100 may improve the operation and/or function of strut 100 and exhaust frame 34, and ultimately gas turbine system 10 as a whole. For example, the inclusion of struts 100 in exhaust frame 34 provides the same amount of support and/or load distribution as conventional struts that are stronger and thicker than struts 100 discussed herein. In comparison, thinner struts 100 do not "block" or take up as much space within the flow area 46 of the exhaust frame 34, ultimately resulting in faster and/or easier flow of the combustion gases 26. to flow through the exhaust frame 34 and/or to exhaust the exhaust frame 34 .

In another example, struts 100 take up less space within flow region 46 than conventional stiff/thick struts. These improved functions and/or characteristics may extend the operational life of exhaust frame 34 and/or strut 100 of gas turbine system 10 .

5-10 illustrate side views of additional non-limiting examples of struts 100 that may be included in exhaust frame 34 of gas turbine system 10 (see FIG. 1). It is understood that like-numbered and/or named components may function in substantially the same manner. Redundant descriptions of these components have been omitted for clarity.

As shown in FIG. 5, unlike FIG. 3, the strut 100 can include only a single aperture 110. As shown in FIG. Aperture 110 may be formed in second portion 122 of strut 100 and extend radially between leading edge 106 and trailing edge 108 . Similar to the non-limiting example shown in FIG. 3, the opening 110 formed in the strut 100 shown in FIG. 5 includes a keyhole slot with a radial opening 112 extending between two end openings 118. be able to. In a non-limiting example, strut 100 can include first section 126 and second section 128 configured to move independently from first section 126 . First section 126 of strut 100 may include and/or extend axially over portions of first portion 120 and second portion 122 . Additionally, second section 128 of strut 100 may include and/or extend axially over portions of second portion 122 and third portion 124 . Similarly, as discussed herein, first section 126 and second section 128 of strut 100 each have a first axial width (W ₁ ) and a second axial width (W ₂ ). can contain. As shown in the non-limiting example of FIG. 5, the first axial width (W ₁ ) of the first section 126 is different than the second axial width (W ₂ ) of the second section 128. or less.

In the non-limiting example shown in FIG. 6, strut 100 includes a single opening 110 formed in third portion 124 of strut 100 extending radially between leading edge 106 and trailing edge 108. be able to. Similar to the openings previously described, the opening 110 formed in the strut 100 shown in FIG. 6 can include a keyhole slot with a radial opening 112 extending between two end openings 118 . In a non-limiting example, strut 100 can include first section 126 and second section 128 configured to move independently from first section 126 . First section 126 of strut 100 may include and/or extend axially over portions of first portion 120 , second portion 122 and third portion 124 . Additionally, second section 128 of strut 100 may include and/or extend axially over the remainder of third portion 124 . As shown in the non _- limiting example of FIG. 6, and unlike the example shown in FIG. It may be different or greater _than the directional width (W2).

Compared to the struts 100 discussed herein with respect to FIGS. 3 and 4, the non-limiting example of struts 100 shown in FIG. A portion can include a single or uniform thickness. As a result, the strut 100 shown in FIG. 7 may include only a single or first portion 120. As shown in FIG. An opening 110 (eg, keyhole slot) may be formed in strut 100 (eg, first portion 120 ) and extend radially between leading edge 106 and trailing edge 108 . Similar to the examples shown in FIGS. 5 and 6, the strut 100 shown in FIG. 7 can include a first section 126 and a second section 128, with the second section 128 independent of the first section 126. configured to move First section 126 and second section 128 of strut 100 may include and/or extend axially over separate portions of first portion 120 of strut 100 . As shown in the non-limiting example of FIG. 7, the first axial width (W ₁ ) of the first section 126 is substantially the same as the second axial width (W ₂ ) of the second section 128. may be similar to or equal to .

The strut 100 shown in FIG. 8 may be substantially similar to the non-limiting struts (eg, openings 110A, 110B) shown and described herein with respect to FIGS. However, the openings 110A, 110B of strut 100 shown in FIG. 8 may be different than those shown in FIGS. Specifically, as shown in FIG. 8, the first openings 110A and the second openings 110B can include only linear openings 112 formed through the struts 100. As shown in FIG. By eliminating end openings 118 (see FIG. 3) and/or not forming keyhole slot openings, the non-limiting example strut 100 shown in FIG. More stiffness and/or support may be provided to portions of struts 100 formed adjacent respective ends 104 of the struts 100 . Further, as a result of the shape or geometry of openings 110A, 110B formed in strut 100 shown in FIG. 8, each section of strut 100 (eg, first section 126, second section 128) is a gas During operation of turbine system 10 (see FIG. 1), mobility and/or flexibility may be reduced or reduced.

In the non-limiting example shown in FIG. 9, first opening 110A and second opening 110B can include additional unique shapes or geometries. Specifically, first opening 110A and second opening 110B can include substantially curved openings 132 extending radially between end openings 118 . Specifically, the curved opening 132 of the first opening 110A is formed to extend axially (eg, concavely) toward the leading edge 106 of the strut 100, and the curved opening 132 of the second opening 110B. Aperture 132 may be formed (eg, convex) to extend axially toward trailing edge 108 . Accordingly, the curved openings 132 of the first opening 110A and the second opening 110B can also extend axially away from each other. As shown in FIG. 9, the first aperture 110A and the second aperture 110B may be (axial) mirror images of each other.

As a result of the curved opening 132 forming part of the opening 110, the multiple sections 126, 128, 130 of the strut 100 can include varying thicknesses. As shown in the non-limiting example of FIG. 9, the thicknesses of first section 126 and third section 130 are such that each section is at an end of strut 100 (e.g., first end 102, second end 102, second section 130). may become smaller (eg, radially converge) as one moves radially from the edge 104 of the curved opening 132 toward the radial center point of the curved opening 132 . The thickness of second section 128 can have an inverse relationship to first section 126 and third section 130 . That is, the thickness of second section 128 increases from the ends of strut 100 (e.g., first end 102, second end 104) toward the radial center point of opening 132 where the section is curved. It can become larger (radially spread out) as it moves radially. In another non-limiting example, curved opening 132 of first opening 110A is formed to extend axially away from leading edge 106, and curved opening 132 of second opening 110B is formed to: It may be formed to extend axially away from the trailing edge 108 . In this non-limiting example, the thickness relationships of the plurality of sections 126, 128, 130 described above may be reversed (eg, the thickness of the second section 128 radially converges).

FIG. 10 shows additional non-limiting examples regarding the shape or geometry of the first opening 110A and the second opening 110B of the strut 100. FIG. That is, the first opening 110A and the second opening 110B can include variable width openings 134 that extend radially between the end openings 118 . The width of the variable width openings 134 may converge or become smaller as the variable width openings 134 move radially away from each end opening 118 . Specifically, the variable width openings 134 of the first opening 110A and the second opening 110B are adjacent to each end opening 118 more than the width adjacent to the radial center point of the variable width openings 134. can have a greater width.

As a result of the variable width opening 134 forming part of the opening 110, the multiple sections 126, 128, 130 of the strut 100 can include varying thicknesses. As shown in the non-limiting example of FIG. 10, the thicknesses of first section 126, second section 128 and third section 130 are such that each section is at an end (e.g., first end) of strut 100. It can become larger (radially widening) as one moves radially from the portion 102, second end 104) toward the radial center point of the variable width opening 134. FIG. In another non-limiting example, the variable width openings 134 of the opening 110 radially widen or become larger as the variable width openings 134 move radially away from each end opening 118. can be formed as In this non-limiting example, the thickness relationships of the sections 126, 128, 130 described above may be reversed (e.g., the thicknesses of the sections 126, 128, 130 may radially converge). do).

In various embodiments, components described as being “fluidly coupled” or “in fluid communication with” each other can be joined along one or more interfaces. In some embodiments, these interfaces may include joints between separate components; in others, these interfaces may be rigidly and/or integrally formed mutual Can contain connections. That is, in some cases, components that are "bonded" together can be formed simultaneously to define a single continuous member. However, in other embodiments, these bonded components can be formed as separate members and then joined by known processes (eg, fastening, ultrasonic welding, gluing).

When an element or layer is said to be “overlying,” “engaging,” “connected to,” or “coupled to” another element, it is directly related to the other element. There may be intervening elements overlying, engaging, connected or otherwise coupled to. In contrast, an element is "directly overlying," "directly engaging," "directly connected to," or "directly coupled to" another element. , there may be no intervening elements or layers present. Interpret other words used to describe relationships between elements in a similar fashion (e.g., "between" vs. "directly between," "adjacent" vs. "directly adjacent," etc.) should. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. As used herein, the singular forms "a," "an," and "the" are intended to include plural forms as well, unless expressly stated otherwise. The terms "comprises" and/or "comprising" as used herein indicate the presence of the stated features, integers, steps, acts, elements and/or components It will be further understood that does not exclude the presence or addition of one or more other features, integers, steps, acts, elements, components, and/or groups thereof.

This written description is intended to disclose the invention, including the best mode, and to practice the invention, including making and using any device or system, and performing any incorporated method. The examples are used to enable the trader. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other embodiments, if having structural elements that do not differ from the language of the claims, or if they contain equivalent structural elements that do not substantially differ from the language of the claims, may not be patentable. It is intended to be within the scope of the claims.
[Embodiment 1]
A strut (100) for an exhaust frame (34) of a turbine system (10), said strut (100) comprising:
a body (101) including a leading edge (106) and a trailing edge (108);
an aperture (110) formed through said body (101) and extending radially between said leading edge (106) and said trailing edge (108);
a first section (126) formed between said leading edge (106) and said opening (110);
a second section (128) formed between said trailing edge (108) and said opening (110) and configured to move independently from said first section (126); (100).
[Embodiment 2]
further comprising separate openings (110A, 110B) formed through said body (101) axially adjacent said opening (110), said separate openings (110A, 110B) extending from said leading edge (106); and said trailing edge (108);
A strut (100) according to claim 1.
[Embodiment 3]
3. The strut (100) of embodiment 2, wherein said second section (128) is formed between said opening (110) and said separate openings (110A, 110B).
[Embodiment 4]
formed through the body (101) between the trailing edge (108) and the separate openings (110A, 110B);
a third section (130) configured to move independently of said first section (126) and said second section (128);
4. The strut (100) of embodiment 3, further comprising:
[Embodiment 5]
The axial width of said first section (126) is
equal to the axial width of said second section (128) and said third section (130);
A strut (100) according to embodiment 4.
[Embodiment 6]
2. The embodiment of claim 1, wherein said first section (126) comprises a _first axial width (W1) that is different than a _second axial width (W2) of said second section (128). strut (100).
[Embodiment 7]
2. The strut (100) of embodiment 1, wherein said opening (110) comprises a keyhole slot.
[Embodiment 8]
An exhaust frame (34) for a turbine system (10), said exhaust frame (34) comprising:
an inner casing (38);
an outer casing (40) concentrically surrounding said inner casing (38);
a plurality of struts (100) radially extending and coupled between the inner casing (38) and the outer casing (40), each of the plurality of struts (100) comprising:
a body (101) including a leading edge (106) and a trailing edge (108);
an aperture (110) formed through said body (101) and extending radially between said leading edge (106) and said trailing edge (108);
a first section (126) formed between said leading edge (106) and said opening (110);
a second section (128) formed between said trailing edge (108) and said opening (110) and configured to move independently from said first section (126). Frame (34).
[Embodiment 9]
at least one of the plurality of struts (100) comprising:
further comprising separate openings (110A, 110B) formed through said body (101) axially adjacent said opening (110), said separate openings (110A, 110B) extending from said leading edge (106); and said trailing edge (108);
An exhaust frame (34) according to claim 8.
[Embodiment 10]
10. The exhaust frame (34) of embodiment 9, wherein said second section (128) is formed between said opening (110) and said separate openings (110A, 110B).
[Embodiment 11]
formed between the trailing edge (108) and the separate openings (110A, 110B);
a third section (130) configured to move independently of said first section (126) and said second section (128);
11. The exhaust frame (34) of embodiment 10, further comprising:
[Embodiment 12]
The axial width of said first section (126) is
equal to the axial width of said second section (128) and said third section (130);
12. An exhaust frame (34) according to claim 11.
[Embodiment 13]
9. Claimed in embodiment 8, wherein said first section (126) comprises a _first axial width (W1) that is different than a _second axial width (W2) of said second section (128). exhaust frame (34).
[Embodiment 14]
9. The exhaust frame (34) of embodiment 8, wherein the opening (110) of each of the plurality of struts (100) comprises a keyhole slot.
[Embodiment 15]
a turbine (28) including a turbine shell (36);
a shaft (30) extending through the turbine (28);
an exhaust frame (34) positioned adjacent to the turbine (28), the exhaust frame (34) comprising:
an inner casing (38) configured to receive said shaft (30);
an outer casing (40) concentrically surrounding said inner casing (38) and coupled to said turbine shell (36);
a plurality of struts (100) radially extending and coupled between the inner casing (38) and the outer casing (40), at least one of the plurality of struts (100) comprising:
a body (101) including a leading edge (106) and a trailing edge (108);
an aperture (110) formed through said body (101) and extending radially between said leading edge (106) and said trailing edge (108);
a first section (126) formed between said leading edge (106) and said opening (110);
a second section (128) formed between said trailing edge (108) and said opening (110) and configured to move independently from said first section (126). system (10).
[Embodiment 16]
at least one of the plurality of struts (100) comprising:
further comprising separate openings (110A, 110B) formed through said body (101) axially adjacent said opening (110), said separate openings (110A, 110B) extending from said leading edge (106); and said trailing edge (108);
16. The turbine system (10) according to embodiment 15.
[Embodiment 17]
17. The turbine system (10) according to embodiment 16, wherein said second section (128) is formed between said opening (110) and said separate openings (110A, 110B).
[Embodiment 18]
formed between the trailing edge (108) and the separate openings (110A, 110B);
a third section (130) configured to move independently of said first section (126) and said second section (128);
18. The turbine system (10) according to embodiment 17, further comprising:
[Embodiment 19]
The axial width of said first section (126) is
equal to the axial width of said second section (128) and said third section (130);
19. The turbine system (10) according to embodiment 18.
[Embodiment 20]
16. Claimed in embodiment 15, wherein said first section (126) comprises a _first axial width (W1) that is different than a _second axial width (W2) of said second section (128). of the turbine system (10).

10 gas turbine system 12 compressor 18 air 20 compressed air 22 combustor 24 fuel 26 combustion gases 28 turbine 30 shaft 32 external load 34 exhaust frame 36 turbine shell 38 inner casing 40 outer casing 42 opening 44 opening 46 flow field 100 strut 101 body 102 first end 104 second end 106 leading edge 108 trailing edge 110 opening 110A first opening 110B second opening 112 radial opening 118 end opening 120 first portion 122 Second portion 124 Third portion 126 First section 128 Second section 130 Third section 132 Curved opening 134 Variable width opening A Axial axis C Circumferential axis R Radial axis W ₁ first axial width W ₂ second axial width

Claims (10)

A strut (100) for an exhaust frame (34) of a turbine system (10) , the strut (100) comprising:
a leading edge (106) and a trailing edge (108) axially opposite the leading edge (106) and a first end (102) and a second radially opposite the first end (102); a body (101) comprising an end (104) of
an opening (110, 110A) formed through said body (101) extending radially between a first end (102) and a second end (104) and extending at a leading edge (106); ) and the trailing edge ( 108 ) ;
a first section (126) formed between the leading edge (106) and said openings (110 , 110A );
A second section (128) formed between the trailing edge (108) and the openings (110 , 110A ) , the second section (128) configured to move independently from the first section (126). A strut (100) comprising a section (128) of The strut ( 100 ) further includes a separate opening (110B) formed through the body (101) axially adjacent to the opening ( 110A ), the separate opening (110B) ) extends radially between the first end (102) and the second end (104) and is formed between the leading edge (106) and the trailing edge (108) . A strut (100) according to Claim 1. A strut (100) according to claim 2, wherein a second section (128) is formed between said opening (110A) and said separate opening ( 110B ). A third section (130) formed through the body (101) between the trailing edge (108) and the separate opening (110B) , the third section (130) comprising a first section (126) and a second section ( 4. The strut (100) of claim 3, further comprising a third section (130) configured to move independently from 128). The strut (100) of claim 4, wherein the axial width of the first section (126) is equal to the axial width of the second section (128) and the third section (130). 5. Claims 1-4, wherein the first section (126) comprises a _first axial width (W1) that is different than the _second axial width (W2) of the second section (128). A strut (100) according to any one of the preceding claims. A strut (100) according to any of the preceding claims , wherein said apertures (1101 , 110A ) comprise keyhole slots. Said openings (110, 110A) define a radial opening (112) extending radially between two end openings (118) formed at each end of the radial opening (112). 8. A strut (100) according to claim 7, formed as a double keyhole slot with. Said discrete opening (110B) defines a radial opening (112) extending radially between two end openings (118) formed at each end of the radial opening (112). 6. A strut (100) according to any one of claims 2 to 5, formed as a double keyhole slot comprising: An exhaust frame (34) for a turbine system (10) , the exhaust frame (34) comprising:
an inner casing (38);
an outer casing (40) concentrically surrounding said inner casing (38);
A plurality of struts (100) extending radially between and coupled to said inner casing (38) and said outer casing (40) , each of said plurality of struts (100) comprising: An exhaust frame (34) comprising a plurality of struts (100), which are struts (100) according to any one of claims 1 to 9 .

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