EP3336318B1

EP3336318B1 - Struts for exhaust frames of turbine systems

Info

Publication number: EP3336318B1
Application number: EP17205620.2A
Authority: EP
Inventors: Przemyslow Michal JAKUBCZAK; Wojciech DROZDZIK; Robert JAMIOLKOWSKI; Jakub PUTOWSKI
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2016-12-16
Filing date: 2017-12-06
Publication date: 2020-06-17
Anticipated expiration: 2037-12-06
Also published as: JP7146390B2; EP3336318A1; CN108204255A; PL419827A1; JP2018115656A; CN108204255B

Description

BACKGROUND OF THE INVENTION

The disclosure relates generally to turbine systems, and more particularly, to support struts for exhaust frames of turbine systems.
In conventional turbine systems exhaust housings or frames are typically attached or coupled to an outlet of a turbine component. These exhaust housings are attached to the turbine component to safely direct gases passing through and/or from the turbine component into the environment surrounding the turbine system, or alternatively, to direct the gases to another component that may utilize the gases for additional processes (e.g., a heat recovery steam generator). Conventional exhaust housings typically include two concentric shells coupled directly to the turbine component, and a flow path for the gases defined between the shells.
Additionally, conventional exhaust housings typically include a plurality of support structures positioned between and coupling the two shells. These support structures are often referred to as struts. During operation of the turbine system, the concentric shells may experience high stress and/or loads from the system and its components. For example, movement of the turbine component during operation of the turbine system may provide a high stress, force or load on the exhaust housing. The struts are utilized within the exhaust housing to support and/or stabilize the shells during operation of the turbine system.
To ensure support/stabilization and to ensure the exhaust housing can withstand the high stresses and loads during operation of the turbine system, conventional struts are made of a solid piece of rigid material (e.g., metal), that is as thick as possible. However, as the thickness of the struts increases, the operational efficiency of the exhaust housing, and ultimately the turbine system, decreases. Specifically, a plurality of substantially thick struts may provide the desired support/stabilization, but may in turn cover a large amount of the flow area formed by the exhaust housing. As a result, the gases flowing from the turbine component into the exhaust housing may be blocked and/or diverted around these conventional struts, which may cause an undesirable increase is pressure within the exhaust housing.
The conventional struts formed from the solid, rigid material may experience similar and/or distinct stresses and loads during operation of the turbine system. These stresses and loads may decrease the strength of the struts over time. The combination of the size of these conventional struts and the decrease in strength, make conventional struts susceptible to damage or failure. When a strut of the exhaust housing becomes damaged, the concentric shells of the exhaust housing may no longer be supported or stabilized. As a result, the exhaust housing may become loose and/or cause the turbine component to shift, move or become unstable. This in turn may decrease the entire operational efficiency of the entire turbine system.
US 2011/052373 A1 discloses a high-turning strut in a diffuser of a turbine engine, the strut having at least one slot located proximate the leading edge and extending through the turning strut. US6139259 , EP1149987 and EP1548231 disclose further strut bodies of gas turbine engines.

BRIEF DESCRIPTION OF THE INVENTION

A first aspect of the disclosure provides an exhaust frame strut of a turbine system according to claim 1.
A second aspect of the disclosure provides an exhaust frame for a turbine system according to claim 8.
A third aspect of the disclosure provides a turbine system according to claim 15.
The illustrative aspects of the present disclosure solve the problems herein described and/or other problems not discussed.

BRIEF DESCRIPTION OF THE DRAWINGS

These and other features of this disclosure will be more readily understood from the following detailed description of the various aspects of the disclosure taken in conjunction with the accompanying drawings that depict various embodiments of the disclosure, in which:

FIG. 1 depicts a schematic diagram of a gas turbine system according to embodiments.
FIG. 2 depicts an isometric view of an exhaust frame including struts for the gas turbine system of FIG. 1, according to embodiments.
FIG. 3 depicts a side view of a single strut of the exhaust frame of FIG. 2, according to embodiments.
FIG. 4 depicts a cross-section bottom view of the strut of FIG. 3 taken along line 4-4, according to embodiments.
FIG. 5 depicts a side view of a single strut including a single aperture, according to embodiments.
FIG. 6 depicts a side view of a single strut including a single aperture, according to another embodiment.
FIG. 7 depicts a side view of a single strut including a single aperture, according to further embodiments.
FIG. 8 depicts a side view of a single strut including a plurality of apertures, according to embodiments.
FIG. 9 depicts a side view of a single strut including a plurality of apertures, according to additional embodiments.
FIG. 10 depicts a side view of a single strut including a plurality of apertures, according to further embodiments.

It is noted that the drawings of the disclosure are not 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 numbering represents like elements between the drawings.

DETAILED DESCRIPTION OF THE INVENTION

As an initial matter, in order to clearly describe the current disclosure it will become necessary to select certain terminology when referring to and describing relevant machine components within the scope of this disclosure. When doing this, if possible, common industry terminology will be used and employed in a manner consistent with its accepted meaning. Unless otherwise stated, such terminology should 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 often a particular component may be referred to using several different or overlapping terms. What may be described herein as being a single part may include and be referenced in another context as consisting of multiple components. Alternatively, what may be described herein as including multiple components may be referred to elsewhere as a single part.
In addition, several descriptive terms may be used regularly herein, and it should prove helpful to define these terms at the onset of this section. These terms and their definitions, unless stated otherwise, are as follows. As used herein, "downstream" and "upstream" are terms that indicate a direction relative to the flow of a fluid, such as the working fluid through the turbine engine or, for example, the flow of air through the combustor or coolant through one of the turbine's component systems. The term "downstream" corresponds to the direction of flow of the fluid, and the term "upstream" refers to the direction opposite to the flow. The terms "forward" and "aft," without any further specificity, refer to directions, with "forward" referring to the front or compressor end of the engine, and "aft" referring to the rearward or turbine end of the engine. Additionally, the terms "leading" and "trailing" may be used and/or understood as being similar in description as the terms "forward" and "aft," respectively. It is often required to describe parts that are at differing radial, axial and/or circumferential positions. The "A" axis represents an axial orientation. As used herein, the terms "axial" and/or "axially" refer to the relative position/direction of objects along axis A, which is substantially parallel with the axis of rotation of the turbine system (in particular, the rotor section). As further used herein, the terms "radial" and/or "radially" refer to the relative position/direction of objects along an axis "R" (see, FIG. 1), which is substantially perpendicular with axis A and intersects axis A at only one location. Finally, the term "circumferential" refers to movement or position around axis A (e.g., axis "C").
The following disclosure relates generally to a turbine system, and more particularly, to support struts for exhaust frames of turbine systems.
These and other embodiments are discussed below with reference to FIGs. 1-10. However, those skilled in the art will readily appreciate that the detailed description given herein with respect to these Figures is for explanatory purposes only and should not be construed as limiting.
FIG. 1 shows a schematic view of gas turbine system 10 as may be used herein. Gas turbine system 10 may include a compressor 12. Compressor 12 compresses an incoming flow of air 18. Compressor 12 delivers a flow of compressed air 20 to a combustor 22. Combustor 22 mixes the flow of compressed air 20 with a pressurized flow of fuel 24 and ignites the mixture to create 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 flow of combustion gases 26 is in turn delivered to a turbine 28, which typically includes a plurality of turbine blades or buckets and stator vanes. The flow of combustion gases 26 drives turbine 28 to produce mechanical work. The mechanical work produced in turbine 28 drives compressor 12 via a shaft 30 extending through turbine 28, and may be used to drive an external load 32, such as an electrical generator and/or the like.
Gas turbine system 10 may also include an exhaust frame 34. As shown in FIG. 1, exhaust frame 34 may be positioned adjacent turbine 28 of gas turbine system 10. More specifically, exhaust frame 34 may be positioned adjacent to turbine 28 and may be positioned substantially downstream of turbine 28 and/or the flow of combustion gases 26 flowing from combustor 22 to turbine 28. As discussed herein, a portion (e.g., outer casing) of exhaust frame 34 may be coupled directly to an enclosure or shell 36 of turbine 28.
Subsequent to combustion gases 26 flowing through and driving turbine 28, combustion gases 26 may be exhausted, flow-through and/or discharged through exhaust frame 34 in a flow direction (D). In the non-limiting example shown in FIG. 1, combustion gases 26 may flow through exhaust frame 34 in the flow direction (D) and may be discharged from gas turbine system 10 (e.g., to the atmosphere). In another non-limiting example where gas turbine system 10 is part of a combined cycle power plant (e.g., including gas turbine system and a steam turbine system), combustion gases 26 may discharge from exhaust frame 34, and may flow in the flow direction (D) into a heat recovery steam generator of the combined cycle power plant.
FIG. 2 depicts an isometric view of an example 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 positioned within, substantially surrounded by and/or concentric with outer casing 40. As shown in FIG. 2, inner casing 38 may be substantially annular and may include an opening 42 formed therein. In a non-limiting example, opening 42 of 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 shaft 30 of gas turbine system 10 may be positioned within and/or pass through opening 42 of inner casing 38 of exhaust frame 34. In the non-limiting example, shaft 30 may be supported by inner casing 38 and may be free to rotate within opening 42 as turbine 28 of gas turbine system 10 is driven by the flow of combustion gases 26, as discussed herein. In another non-limiting example, opening 42 of inner casing 38 may receive a shaft support (not shown) that may be fixed within opening 42 of inner casing 38 and may be coupled to shaft 30 of gas turbine system 30. The shaft support fixed within the opening 42 in inner casing 38 of exhaust frame 34 may couple shaft 30 to inner casing 38 and may allow shaft 30 to freely rotate during operation of gas turbine system 10, as discussed herein.
Outer casing 40 of exhaust frame 34 may be positioned around inner casing 38. Specifically, and as shown in FIG. 2, outer casing 40 may concentrically surround inner casing 38 of exhaust frame 34. Similar to inner casing 38, outer casing 40 may be substantially annular and may include an opening 44 formed therein. Opening 44 may define a flow area 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 may flow in a direction (D) (see, FIG. 1) into and through flow area 46, and may be subsequently exhausted from exhaust frame 34, as discussed herein. Briefly returning to FIG. 1, and with continued reference to FIG. 2, outer casing 40 may be coupled directly to shell 36 of turbine 28 and may substantially and/or concentrically surround a portion of shaft 30 positioned within or received by inner casing 38.
Exhaust frame 34 may also include at least one strut 100 positioned between inner casing 38 and outer casing 40. In 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 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 exhaust frame 34 may be positioned within flow area of exhaust frame 34, defined between inner casing 38 and outer casing 40. As discussed herein, struts 100 of exhaust frame 34 may couple inner casing 38 and outer casing 40, and may provide support to exhaust frame 34 during operation of gas turbine system 10.
FIG. 3 depicts a side view of a single strut 100 of exhaust frame 34 for gas turbine system 10 (see, FIG. 1). Strut 100 may include a body 101, a first end 102 and a second end 104 positioned on opposite ends of body 101. First end 102 of strut 100 may contact and/or may be coupled to outer casing 40 of exhaust frame 34 (see, FIG. 2). Additionally, second end 104 of strut 100 may contact and/or may be coupled to inner casing 38 of exhaust frame 34 opposite first end 102 and/or outer casing 40. Body 101 of strut 100 may also include a leading edge 106 and a trailing edge 108 positioned 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 may flow in a direction (D) to first contact leading edge 106, and flow over body 101 of strut 100 toward trailing edge 108, before being exhausted and/or discharged from exhaust frame 34.
Strut 100 of exhaust frame 34 includes at least one aperture 110 formed through body 101. Specifically, strut 100 includes at least one aperture 110 extending radially and formed in body 101, between leading edge 106 and trailing edge 108.
Additionally, the at least one aperture 110 extends or is formed in body 101, between first end 102 and second end 104 of strut 100. The at least one aperture 110 may be formed completely through body 101 of strut 100 such that combustion gases 26 flowing over strut 100 may also flow through aperture 110 and/or body 101 of strut 100.
In a non-limiting example shown in FIG. 3, strut 100 may include two distinct apertures 110A, 110B formed there through. First aperture 110A may be positioned between leading edge 106 and trailing edge 108, and specifically, between leading edge 106 and second aperture 110B. Additionally, second aperture 110B may be positioned between leading edge 106 and trailing edge 108, and specifically, between trailing edge 108 and first aperture 110A. As a result, apertures 110A, 110B may be positioned axially adjacent one another. As shown in the non-limiting example of FIG. 3, second aperture 110B maybe positioned axially adjacent and axially downstream of first aperture 110A. It is understood that the number of apertures 110 shown in the figures is merely illustrative. As such, strut 100 may include more or less apertures 110 than the number depicted and discussed herein.
Aperture 110 may include various shapes, orientations and/or geometries when formed within strut 100. Apertures 110, and the shape or geometry of apertures 110, may alter, influence, control and/or effect the movement and flexibility of strut 100 during operation of gas turbine system 10, as discussed in detail below. In a non-limiting example shown in FIG. 3, each aperture 110A, 110B of strut 100 may be formed as a keyhole slot. Specifically, apertures 110A, 110B may be formed as a double keyhole slot include a radial opening 112 extending radially between two substantially end openings 118 formed on each end of radial opening 112. End openings 118 formed on each end of radial opening 112 may be larger and/or may have a diameter or width that is greater than the width of radial opening 112. As a result, end openings 118 may extend axially beyond radial opening 112 within strut 100. As shown in the non-limiting example of FIG. 3, radial opening 112 of apertures 110A, 110B may include a substantially uniform width and/or may be substantially linear in shape.
It is understood that the shapes and/or geometries of apertures 110 shown in the figures is merely illustrative. As such, strut 100 may include distinct shapes and/or geometries for apertures 110 than those depicted and discussed herein. Additionally, although shown herein to include similar, mirroring, or identical shapes between the apertures 110, it is understood that each aperture 110 formed through strut 100 may be distinct from one another. As a result, each strut 100 of exhaust frame 34 may include similarly or identically-shaped apertures, or alternatively, may include apertures 110 having distinct shapes or geometries from distinct aperture(s) 110 in the same strut 100 and/or distinct struts 100 of exhaust frame 34.
Strut 100 may include various portions and sections. That is, strut 100, and specifically body 101 of strut 100, may include various portions, and various sections that may be distinct from the various portions. As discussed herein, the various portions of strut 100 may be defined by the features or geometries (e.g., axial width and/or circumferential thickness) of body 101 of strut 100. Conversely, and as detailed below, the various sections of strut 100 may be defined by apertures 110 formed through body 101 of strut 100.
Strut 100 may include distinct portions axially disposed, formed and/or radially extending between first end 102 and second end 104. As shown in FIG. 3, strut 100 may include a first portion 120, a second portion 122, and a third portion 124 formed and/or extending between first end 102 and second end 104 of strut 100. Distinct 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. Second portion 122 may be formed axially adjacent and downstream of first portion 120. Additionally, second portion 122 may be formed between first portion 120 and third portion 124. Third portion 124 may be positioned axially adjacent and downstream of second portion 122, and may be formed between second portion 122 and trailing edge 108 of strut 100. It is understood that the number of portions shown in the figures is merely illustrative. As such, strut 100 may include more or less radially portions than the number depicted and discussed 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 may include distinct axial widths from each other. That is, an axial width of first portion 120 may be distinct from an axial width of second portion 122 and third portion 124. Additionally, the axial width of second portion 122 may be distinct from the axial width of third portion 124. The axial width of each portion of strut 100 may influence, control and/or effect the movement and flexibility of strut 100 during operation of gas turbine system 10, as discussed herein. Additionally, and as discussed herein the axial width of each portion of strut 100 may also effect (e.g., improve) the function or efficiency (e.g., aerodynamics) of strut 100 during operation of gas turbine system 10. Although discussed herein as being distinct, it is understood that the axial widths of at least two of first portion 120, second portion 122 and third portion 124 of strut 100 may be substantially similar, equal or identical.
In addition to, or independent from, the distinct axial widths, the plurality of portions 120, 122, 124 of strut 100 may be defined by varying circumferential thicknesses. Briefly turning to FIG. 4, a cross-sectional bottom view of strut 100 taken 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 may include distinct circumferential thicknesses (T). Specifically, first portion 120 of strut 100 includes a first circumferential thickness (T₁) and second portion 122 includes a second circumferential thickness (T₂) that may be distinct, or larger than, the first circumferential thickness (T₁) of first portion 120. Additionally as shown in FIG. 4, third portion 124 may include a third circumferential thickness (T₃). Similar to first circumferential thickness (T₁), second circumferential thickness (T₂) may be distinct, or larger than, the third circumferential thickness (T₃) of third portion 124. In non-limiting examples, third circumferential thickness (T₃) of third portion 124 may be equal to or distinct (e.g., larger, smaller) from the first circumferential thickness (T₁) of first portion 120. The circumferential thickness (T) of each portion of strut 100 may influence, control and/or effect the movement and flexibility of strut 100 during operation of gas turbine system 10, as discussed herein. Additionally, and as discussed herein the circumferential thickness (T) of each portion of strut 100 may also effect (e.g., improve) the function or efficiency (e.g., aerodynamics) of strut 100 during operation of gas turbine system 10. Although shown to have at least two distinct circumferential thicknesses, it is understood that strut 100 may include more or less thicknesses for the plurality of portions 120, 122, 124. Alternatively, the portion(s) of strut 100 formed between first end 102 and second end 104 may be substantially uniform in circumferential thickness, as discussed herein.
At least one of the plurality of portions 120, 122, 124 of strut 100 may include aperture(s) 110. Specifically in the non-limiting example shown in FIG. 3, first aperture 110A may be formed through second portion 122 of strut 100, while second aperture 110B may be formed through third portion 124 of strut 100. As discussed herein, the formation of apertures 110 within distinct portions 120, 122, 124 of strut 100 may influence, control and/or effect the movement and flexibility of strut 100 during operation of gas turbine system 10. It is understood that the formation or position of each aperture 110 in a distinct portion 120, 122, 124 of strut 100 shown in the figures is merely illustrative. As such, aperture(s) 110 may be formed in any or all of the plurality of portions 120, 122, 124 of strut 100 than the portions depicted and discussed herein.
Returning to FIG. 3, and with continued reference to FIG. 4, strut 100 of exhaust frame 34 may include a plurality of sections. The plurality of sections may be distinct from the plurality of portions 120, 122, 124 of strut 100. Specifically, the plurality of sections 126, 128, 130 may be formed and/or defined, at least partially, by apertures 110 formed within and/or through strut 100. In the non-limiting example where 100 strut includes apertures 110A, 110B, three distinct sections 126, 128, 130 maybe formed in strut 100. As shown in FIGs. 3 and 4, a first section 126 may be formed between leading edge 106 and first aperture 110A, and a second section 128 may be formed between first aperture 110A and trailing edge 108. More specifically, second section 128 of strut 100 may be formed between first aperture 110A and second aperture 110B, axially adjacent and/or downstream of first section 126. Additionally, a third section 130 of strut 100 may be formed between trailing edge 108 and second aperture 110B, axially adjacent and/or downstream of second section 128.
Each of the plurality of sections 126, 128, 130 of strut 100 may include an axial width. The width of each of the plurality of sections 126, 128, 130 may be defined by the axial distance between an edge (e.g., leading edge 106, trailing edge 108) and an aperture 110 of strut 100, and/or the axial distance between two apertures 110 (e.g., first aperture 110A, second aperture 110B). As shown in FIG. 3, first section 126 may include a first axial width (W₁), second section 128 may include a second axial width (W₂) and third section 130 may include a third axial width (W₃). In the non-limiting example shown in FIG. 3, the first axial width (W₁) of first section 126 may be similar or equal to the second axial width (W₂) of second section 128 and the third axial width (W₃) of third section 130. In other non-limiting example discussed herein, the first axial width (W₁) of first section 126 maybe distinct from the second axial width (W₂) of second section 128 and/or the third axial width (W₃) of third section 130. Additionally, the second axial width (W₂) of second section 128 may be distinct from the third axial width (W₃) of third section 130. As discussed herein, the width of each section of strut 100 may influence, control and/or effect the movement and flexibility of the plurality of sections 126, 128, 130 of strut 100 during operation of gas turbine system 10.
As discussed above, the plurality of portions 120, 122, 124 of strut 100 may be defined by the respective widths and/or thicknesses of each section. Conversely, the plurality of sections 126, 128, 130 of strut 100 may be defined by apertures 110 formed in strut 100. As such, the plurality of portions 120, 122, 124 and the plurality of sections 126, 128, 130 of strut 100 may not be aligned, correspond and/or refer to the same area of strut 100. That is, at least one section of the plurality of sections 126, 128, 130 of strut 100 may include and/or span (axially) across multiple (e.g., two or more) portions of the plurality of portions 120, 122, 124; and vice versa. In the non-limiting example shown in FIGs. 3 and 4, first aperture 110A may formed in second portion 122 of strut 100. As a result, first section 126 of strut 100 may include and/or axially span over first portion 120 and a part of second portion 122. Additionally in the non-limiting example shown in FIGs. 3 and 4, second aperture 110B may be formed in third portion 124 of strut 100. As such, second section 128 of strut 100 may include and/or axially span over a part of second portion 122 and a part of third portion 124. Third section 130 of strut 100 may include and/or axially span over the remaining part of third portion 124 not included in second section 128.
Each of the plurality of sections 126, 128, 130 of strut 100 may flex and/or move independent of each other as a result of aperture(s) 110 being formed through and radially extending over strut 100. Specifically in the non-limiting example shown in FIGs. 3 and 4, first section 126 of strut 100 may be configured to move independent of second section 128 and third section 130, respectively. Additionally, second section 128 of strut 100 may be configured to move independent of first section 126 and third section 130. Finally, third section 130 of strut 100 may be configured to move independent of first section 126 and second section 128.
By allowing each of the plurality of sections 126, 128, 130 of strut 100 to move independent from each other, a load and/or stress experienced by exhaust frame 34 and/or strut 100 during operation of gas turbine system 10 may be distributed more efficiently through and/or managed more effectively by strut 100. The improved distribution and/or managing of the load and/or stress experienced by strut 100 may improve the operation and/or function of strut 100 and exhaust frame 34, and ultimately the gas turbine system 10 as a whole. For example, the inclusion of struts 100 in an exhaust frame 34 may provide the same amount of support and/or load distribution as a conventional strut that is solid and thicker than the strut 100 discussed herein. By comparison, thinner strut 100 may not "block" or occupy as much space in flow area 46 of exhaust frame 34, which may ultimately allow for combustion gases 26 to flow through and/or exit exhaust frame 34 quicker and/or with more ease.
In another example, strut 100 occupies less space in flow area 46 than a conventional, solid/thicker strut. These improved functions and/or characteristics may extend the operational life of exhaust frame 34 and/or strut 100 of gas turbine system 10.
FIGs. 5-10 depict side views of additional non-limiting examples of strut 100 that may be included in exhaust frame 34 of gas turbine system 10 (see, FIG. 1). It is understood that similarly numbered and/or named components may function in a substantially similar fashion. Redundant explanation of these components has been omitted for clarity.
As shown in FIG. 5, and distinct from FIG. 3, strut 100 may include only a single aperture 110. Aperture 110 may be formed in second portion 122 of strut 100, and may extend radially between leading edge 106 and trailing edge 108. Similar to the non-limiting example shown in FIG. 3, aperture 110 formed in strut 100 shown in FIG. 5 may include a keyhole slot having a radial opening 112 extending between two end openings 118. In the non-limiting example, strut 100 may include first section 126 and second section 128, configured to move independent from first section 126. First section 126 of strut 100 may include and/or axially span over first portion 120 and a part of second portion 122. Additionally, second section 128 of strut 100 may include and/or axially span over part of second portion 122 and third section 124. Similarly as discussed herein, first section 126 and second section 128 of strut 100 may include a first axial width (W₁) and a second axial width (W₂), respectively. As shown in the non-limiting example of FIG. 5, the first axial width (W₁) of first section 126 may be distinct or smaller than the second axial width (W₂) of second section 128.
In the non-limiting example shown in FIG. 6, strut 100 may include a single aperture 110 formed in third portion 124 of strut 100, and may extend radially between leading edge 106 and trailing edge 108. Similar to previously discussed apertures, aperture 110 formed in strut 100 shown in FIG. 6 may include a keyhole slot having a radial opening 112 extending between two end openings 118. In the non-limiting example, strut 100 may include first section 126 and second section 128, configured to move independent from first section 126. First section 126 of strut 100 may include and/or axially span over first portion 120, second portion 122 and a part of third portion 124. Additionally, second section 128 of strut 100 may include and/or axially span over the remaining part of third portion 124. As shown in the non-limiting example of FIG. 6, and distinct form the example shown in FIG. 5, the first axial width (W₁) of first section 126 may be distinct or greater than the second axial width (W₂) of second section 128.
Compared to strut 100 discussed herein with respect to FIGs. 3 and 4, the non-limiting example of strut 100 shown in FIG. 7 may include a single or uniform thickness in the portion of strut 100 formed between leading edge 106 and trailing edge 108. As a result, strut 100 shown in FIG. 7 may only include a single or first portion 120. Aperture 110 (e.g., keyhole slot) may be formed in strut 100 (e.g., first portion 120), and may extend radially between leading edge 106 and trailing edge 108. Similar to the examples shown in FIGs. 5 and 6, strut 100 shown in FIG. 7 may include first section 126 and second section 128, the latter configured to move independent from first section 126. First section 126 and second section 128 of strut 100 may include and/or axially span over distinct parts of first portion 120 of strut 100. As shown in the non-limiting example of FIG. 7, the first axial width (W₁) of first section 126 may be substantially similar or equal to the second axial width (W₂) of second section 128.
Strut 100 depicted in FIG. 8 may be substantially similar to the non-limiting strut shown and discussed herein with respect to FIGs. 3 and 4 (e.g., apertures 110A, 110B). However, apertures 110A, 110B of strut 100 depicted in FIG. 8 may be distinct from those apertures depicted in FIGs. 3 and 4. Specifically, and as shown in FIG. 8, first aperture 110A and second aperture 110B may only include linear opening 112 formed through strut 100. By excluding end openings 118 (see, FIG. 3) and/or not forming a keyhole slot aperture, the non-limiting example of strut 100 depicted in FIG. 8 may provide more stiffness and/or support toward the portions of strut 100 formed adjacent first end 102 and second end 104, respectively. Additionally, as a result of the shape or geometry of apertures 110A, 110B formed in strut 100 depicted in FIG. 8, each section (e.g., first section 126, second section 128) of strut 100 strut 100 may have reduced or less movement-capabilities and/or flexibility for during operation of gas turbine system 10 (see, FIG. 1).
In the non-limiting example shown in FIG. 9, first aperture 110A and second aperture 110B may include additional, unique shapes or geometries. Specifically, first aperture 110A and second aperture 110B may include a substantially curved opening 132 extending radially between end openings 118. Specifically, curved opening 132 of first aperture 110A may be formed to extend axially toward leading edge 106 of strut 100 (e.g., concave), and curved opening 132 of second aperture 110B may be formed to extend axially toward trailing edge 108 (e.g., convex). As such, curved openings 132 of first aperture 110A and second aperture 110B may also extend axially away from each other. As shown in FIG. 9, first aperture 110A and second aperture 110B maybe a (axial) mirror image of each other.
As a result of curved openings 132 forming part of apertures 110, the plurality of sections 126, 128, 130 of strut 100 may include varying thickness. As shown in the non-limiting example of FIG. 9, the thickness of first section 126 and third section 130 may become smaller (e.g., radially converge) as the respective section radial moves from the ends (e.g., first end 102, second end 104) of strut 100 toward a radial central point of curved openings 132. The thickness of second section 128 may have an opposite relationship as first section 126 and third section 130. That is, the thickness of second section 128 may become larger (radially diverge) as the section radial moves from the ends (e.g., first end 102, second end 104) of strut 100 toward a radial central point of curved openings 132. In another non-limiting example, curved opening 132 of first aperture 110A may be formed to extend axially away from leading edge 106 and curved opening 132 of second aperture 110B may be formed to extend axially away from trailing edge 108. In this non-limiting example, the thickness relationship for the plurality of sections 126, 128, 130 discussed above may be the opposite (e.g., thickness of second section 128 radially converges).
FIG. 10 depicts additional non-limiting examples for the shape or geometry of first aperture 110A and second aperture 110B of strut 100. That is, first aperture 110A and second aperture 110B may include a varying-width opening 134 extending radially between end openings 118. The width of varying-width opening 134 may converge or get smaller as varying-width opening 134 radially moves away from each end opening 118. Specifically, varying-width opening 134 of first aperture 110A and second aperture 110B may have a greater width adjacent each end opening 118 than a width adjacent a radial central point of varying-width opening 134.
As a result of varying-width opening 134 forming part of apertures 110, the plurality of sections 126, 128, 130 of strut 100 may include varying thickness. As shown in the non-limiting example of FIG. 10, the thickness of first section 126, second section 128 and third section 130 may become larger (radially diverge) as each section radial moves from the ends (e.g., first end 102, second end 104) of strut 100 toward a radial central point of varying-width opening 134. In another non-limiting example, varying-width opening 134 of apertures 110 may be formed to radially diverge or get larger as varying-width opening 134 radially moves away from each end opening 118. In this non-limiting example, the thickness relationship for the plurality of sections 126, 128, 130 discussed above may be the opposite (e.g., thickness of the plurality of sections 126, 128, 130 radially converges).
In various embodiments, components described as being "fluidly coupled" to or "in fluid communication" with one another can be joined along one or more interfaces. In some embodiments, these interfaces can include junctions between distinct components, and in other cases, these interfaces can include a solidly and/or integrally formed interconnection. That is, in some cases, components that are "coupled" to one another can be simultaneously formed to define a single continuous member. However, in other embodiments, these coupled components can be formed as separate members and be subsequently joined through known processes (e.g., fastening, ultrasonic welding, bonding).
When an element or layer is referred to as being "on", "engaged to", "connected to" or "coupled to" another element, it may be directly on, engaged, connected or coupled to the other element, or intervening elements may be present. In contrast, when an element is referred to as being "directly on," "directly engaged to", "directly connected to" or "directly coupled to" another element, there may be no intervening elements or layers present. Other words used to describe the relationship between elements should be interpreted in a like fashion (e.g., "between" versus "directly between," "adjacent" versus "directly adjacent," etc.). 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 the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.
This written description uses examples to disclose the invention and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.

Claims

An exhaust frame (34) strut (100) of a turbine (28) system, the strut (100) comprising:
a body (101) including a leading edge (106) and a trailing edge (108);

an aperture (110, 110A, 110B) formed through the body (101), the aperture (110, 110A, 110B) extending radially between the leading edge (106) and the trailing edge (108);

a first section (126) formed between the leading edge (106) and the aperture (110, 110A, 110B); and

a second section (128) formed between the trailing edge (108) and the aperture (110, 110A, 110B), characterized in that

the or each aperture (110, 110A, 110B) extends radially between a first end (102) and a second end (104) of body (101), and as a result of the aperture

the second section (128) is able to move independent from the first section (126).
The strut (100) of claim 1, further comprising:
a distinct aperture (110, 110A, 110B) formed through the body (101) axially adjacent the aperture (110, 110A, 110B), the distinct aperture (110, 110A, 110B) extending radially between the leading edge (106) and the trailing edge (108).
The strut (100) of claim 2, wherein the second section (128) is formed between the aperture (110, 110A, 110B) and the distinct aperture (110, 110A, 110B).
The strut (100) of claim 3, further comprising:
a third section (130) formed through the body (101) between the trailing edge (108) and the distinct aperture (110, 110A, 110B), the third section (130) configured to move independent from:
the first section (126); and

the second section (128).
The strut (100) of claim 4, wherein an axial width of the first section (126) is equal to an axial width of:
the second section (128); and

the third section (130).
The strut (100) of any preceding claim, wherein the first section (126) includes a first axial width distinct from a second axial width of the second section (128).
The strut (100) of any preceding claim, wherein the aperture (110, 110A, 110B) includes a keyhole slot.
An exhaust frame (34) for a turbine (28) system, the exhaust frame (34) comprising:
an inner casing (38);

an outer casing (40) concentrically surrounding the inner casing (38); and

a plurality of struts (100) extending radially between and coupled to the inner casing (38) and the outer casing (40), each of the plurality of struts (100) including:
a body (101) including a leading edge (106) and a trailing edge (108);

an aperture (110, 110A, 110B) formed through the body (101), the aperture (110, 110A, 110B) extending radially between the leading edge (106) and the trailing edge (108);

a first section (126) formed between the leading edge (106) and the aperture (110, 110A, 110B); and

a second section (128) formed between the trailing edge (108) and the aperture (110, 110A, 110B), characterized in that

the or each aperture (110, 110A, 110B) extends radially between a first end (102) and a second end (104) of body (101), and as a result of the aperture

the second section (128) is able to move independent from the first section (126).
The exhaust frame (34) of claim 8, wherein at least one of the plurality of struts (100) further includes:
a distinct aperture (110, 110A, 110B) formed through the body (101) axially adjacent the aperture (110, 110A, 110B), the distinct aperture (110, 110A, 110B) extending radially between the leading edge (106) and the trailing edge (108).
The exhaust frame (34) of claim 9, wherein the second section (128) is formed between the aperture (110, 110A, 110B) and the distinct aperture (110, 110A, 110B).
The exhaust frame (34) of claim 10, further comprising:
a third section (130) formed between the trailing edge (108) and the distinct aperture (110, 110A, 110B), the third section (130) configured to move independent from:
the first section (126); and

the second section (128).
The exhaust frame (34) of claim 11, wherein an axial width of the first section (126) is equal to an axial width of:
the second section (128); and

the third section (130).
The exhaust frame (34) of any of claims 8 to 12, wherein the first section (126) includes a first axial width distinct from a second axial width of the second section (128).
The exhaust frame (34) of any of claims 8 to 13, wherein the aperture (110, 110A, 110B) of the each of the plurality of struts (100) includes a keyhole slot.
A turbine system comprising:
a turbine including a turbine shell;

a shaft extending through the turbine; and

an exhaust frame as claimed in any of claims 8 to 14 positioned adjacent the turbine, wherein the inner casing of the exhaust frame is configured to receive the shaft; and the outer casing of the exhaust frame is coupled to the turbine shell.