Annular segment assembly in a gas turbine engine

Abstract

The ring segment assembly (200) includes a ring segment (202) including an impact pocket (318) having an impact surface (320), a plurality of prong portions (402) extending from the impact surface (320), and an impact plate (204) spaced a non-zero distance (702) from the impact surface (320). The plurality of prong portions (402) are arranged to define a plurality of prong-free impact areas (404). The impact plate (204) has a plurality of protrusions (602) and a plurality of valleys (604). The impact plate (204) defines a plurality of impact apertures (606). Each of the plurality of impact apertures (606) is formed in one of the valleys (604) of the plurality of valleys (604) and is positioned opposite one of the plurality of prong-free impact areas (404).

Description

Technical Field

[0001] This invention relates to an annular segment assembly in a gas turbine engine. Background Technology

[0002] A gas turbine engine typically includes a compressor section, a turbine section, and a combustion section disposed therebetween. The compressor section includes multi-stage rotating compressor blades and stationary compressor guide vanes. The combustion section typically includes multiple burners. The turbine section includes multi-stage rotating turbine blades and stationary turbine guide vanes. The turbine blades and guide vanes typically operate at high temperatures and are internally cooled. The burners may include fuel injectors for supplying fuel that will be mixed with compressed air from the compressor section, and ignition sources for igniting the mixture to form hot exhaust gas for the turbine section. Summary of the Invention

[0003] In one aspect, the annular segment assembly includes: an annular segment including an impact cavity having an impact surface; a plurality of puncture portions extending from the impact surface, the plurality of puncture portions being arranged to define a plurality of non-puncture impact regions; and an impact plate spaced from the impact surface at a non-zero distance, the impact plate having a plurality of protrusions and a plurality of valleys, the impact plate defining a plurality of impact holes, each of the plurality of impact holes being formed in one of the valleys and positioned opposite one of the plurality of non-puncture impact regions.

[0004] In one aspect, the annular segment assembly includes: an annular segment comprising an impact cavity having an impact surface; a plurality of puncture portions extending from the impact surface; and an impact plate spaced from the impact surface at a non-zero distance, the impact plate having a plurality of protrusions and a plurality of valleys arranged in an array of a plurality of rows and a plurality of columns, each of the plurality of protrusions and each of the plurality of valleys alternating with each other in each of the plurality of rows and each of the plurality of columns, the impact plate defining a plurality of impact holes, each of the plurality of impact holes being formed in one of the plurality of valleys. Attached Figure Description

[0005] To facilitate identification of any particular element or action in discussion, one or more of the most significant digits in the reference numerals refer to the drawing number in which the element was first introduced.

[0006] Figure 1 This is a longitudinal cross-sectional view of a gas turbine engine 100 taken along a plane containing a longitudinal axis or a central axis.

[0007] Figure 2 Show Figure 1 A perspective view of the ring segment component used.

[0008] Figure 3 Show Figure 2 A perspective view of the annular segment in the image.

[0009] Figure 4 Show Figure 2 A top view of a portion of the ring segment.

[0010] Figure 5 Show Figure 2 The cross-sectional view of the annular segment in the diagram better illustrates the puncture site.

[0011] Figure 6 Show Figure 2 A perspective view of the impact plate in the image.

[0012] Figure 7 Show Figure 2 A cross-sectional view of the annular segment component. Detailed Implementation

[0013] Before explaining any embodiment of the invention in detail, it should be understood that the application of the invention is not limited to the details of the construction and arrangement of the components set forth in this specification or illustrated in the following drawings. The invention can have other embodiments and can be practiced or carried out in various ways. Furthermore, it should be understood that the wording and terminology used herein are for descriptive purposes and should not be considered limiting.

[0014] Various techniques relating to the systems and methods will now be described with reference to the accompanying drawings, wherein the same reference numerals always denote the same elements. The drawings discussed below, as well as the various embodiments used to describe the principles of this disclosure in this patent document, are merely illustrative and should not be construed in any way as limiting the scope of this disclosure. Those skilled in the art will understand that the principles of this disclosure can be implemented in any suitably arranged device. It should be understood that functions described as being performed by certain system elements can be performed by multiple elements. Similarly, for example, elements can be configured to perform functions described as being performed by multiple elements. Many of the innovative teachings of this application will be described with reference to exemplary, non-limiting embodiments.

[0015] Furthermore, it should be understood that the words or phrases used herein should be interpreted broadly, unless explicitly limited in some examples. For example, the terms “comprising,” “having,” and “including,” and their derivatives, mean including but not limited to. The singular forms “a,” “an,” and “the” are also intended to include the plural forms, unless the context explicitly indicates otherwise. Additionally, the term “and / or,” as used herein, refers to and covers any and all possible combinations of one or more of the associated listed items. The term “or” is inclusive and means “and / or,” unless the context explicitly indicates otherwise. The phrases “associated with” and “associated with,” and their derivatives, may mean including, contained within, interconnected with, contained in, contained in, connected to or connected with, linked to or connected with, connectable to, cooperate with, intertwined, juxtaposed, proximate, bound to or combined with, having, having characteristics of, etc. Furthermore, while multiple embodiments or constructions may be described herein, any features, methods, steps, components, etc., described with respect to one embodiment are equally applicable to other embodiments where no specific statement to the contrary exists.

[0016] Furthermore, although the terms “first,” “second,” “third,” etc., may be used herein to refer to various elements, information, functions, or actions, these elements, information, functions, or actions should not be limited by these terms. Rather, these numerical adjectives are used to distinguish different elements, information, functions, or actions from one another. For example, without departing from the scope of this disclosure, a first element, information, function, or action may be referred to as a second element, information, function, or action, and similarly, a second element, information, function, or action may be referred to as a first element, information, function, or action.

[0017] Furthermore, in the specification, the terms "axial" or "axially located" refer to the direction along the longitudinal axis of the gas turbine engine. The terms "radial" or "radially located" refer to the direction perpendicular to the longitudinal axis of the gas turbine engine. The terms "downstream" or "rear" refer to the direction along the flow direction. The terms "upstream" or "forward" refer to the direction opposite to the flow direction.

[0018] Furthermore, the term "proximate" may mean that an element is relatively close to but does not contact another element, or that the element is in contact with another part, unless the context clearly indicates otherwise. Additionally, the phrase "based on" is intended to mean "at least partially based on," unless otherwise clearly stated. The terms "about" or "substantially" or similar terms are intended to cover variations in values ​​within normal industrial manufacturing tolerances for that dimension. If no industry standard is available, then unless otherwise stated, twenty percent of the variation will fall within the meaning of these terms.

[0019] Figure 1 An example of a gas turbine engine 100 is illustrated, comprising a compressor section 102, a combustion section 104, and a turbine section 106 arranged along a central axis 112. The compressor section 102 includes multiple compressor stages 114, each compressor stage 114 including a set of fixed guide vanes 116 or adjustable guide vanes and a set of rotating blades 118. A rotor 134 supports the rotating blades 118 for rotation about the central axis 112 during operation. In some configurations, a single integral rotor 134 extends the length of the gas turbine engine 100 and is supported for rotation by bearings at either end. In other configurations, the rotor 134 is assembled from several separate spools attached to each other, or may include multiple disc sections attached via bolts or bolts.

[0020] The compressor section 102 is in fluid communication with the inlet section 108 to allow the gas turbine engine 100 to draw atmospheric air into the compressor section 102. During operation of the gas turbine engine 100, the compressor section 102 draws in atmospheric air and compresses it for delivery to the combustion section 104. The illustrated compressor section 102 is an example of one compressor section 102, while other arrangements and designs are possible.

[0021] In the described configuration, the combustion section 104 includes a plurality of independent burners 120, each burner operating to mix a fuel stream with compressed air from the compressor section 102 and burn the air-fuel mixture to produce a stream of high-temperature, high-pressure combustion gases or exhaust gas 122. Of course, many other arrangements of the combustion section 104 are possible.

[0022] The turbine section 106 includes multiple turbine stages 124, each turbine stage 124 including multiple fixed turbine guide vanes 126 and multiple rotating turbine blades 128. The turbine stages 124 are arranged to receive exhaust gas 122 from the combustion section 104 at a turbine inlet 130 and to expand the gas to convert thermal and pressure energy into rotational or mechanical work. The turbine section 106 is connected to the compressor section 102 to drive the compressor section 102. For a gas turbine engine 100 used for power generation or as a prime mover, the turbine section 106 is also connected to a generator, pump, or other device to be driven. Similar to the compressor section 102, other designs and arrangements of the turbine section 106 are possible.

[0023] Exhaust section 110 is located downstream of turbine section 106 and is arranged to receive the expanded exhaust 122 flow from the final turbine stage 124 in turbine section 106. Exhaust section 110 is arranged to effectively guide exhaust 122 away from turbine section 106 to ensure efficient operation of turbine section 106. Many variations and design differences are possible in exhaust section 110. Therefore, the exhaust section 110 described is merely one example of those variations.

[0024] The control system 132 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and control various operations of the gas turbine engine 100. In a preferred configuration, the control system 132 is typically microprocessor-based and includes memory devices and data storage devices for collecting, analyzing, and storing data. Furthermore, the control system 132 provides output data to various devices, including monitors, printers, indicators, etc., which allow users to interact with the control system 132 to provide inputs or adjustments. In the example of a power generation system, a user can input a power output setpoint, and the control system 132 can adjust various control inputs to achieve that power output efficiently.

[0025] The control system 132 can control various operating parameters, including but not limited to the position of the variable inlet guide vanes, fuel flow rate and pressure, engine speed, valve position, generator load, and generator excitation. Of course, other applications may have fewer or more controllable devices. The control system 132 also monitors various parameters to ensure proper operation of the gas turbine engine 100. Some of the monitored parameters may include inlet air temperature, compressor outlet temperature and pressure, burner outlet temperature, fuel flow rate, generator power output, bearing temperature, etc. Many of these measurements are displayed to the user and recorded for subsequent review if necessary.

[0026] Figure 2 Instructions for Figure 1 A perspective view of the annular segment assembly 200 of the gas turbine engine 100. The annular segment assembly 200 is disposed adjacent to the tip of the rotating turbine blade 128, with a gap therebetween. A plurality of annular segment assemblies 200 are arranged circumferentially and are disposed around a plurality of rotating turbine blades 128 in the gas turbine engine 100.

[0027] The annular segment assembly 200 includes an annular segment 202 and an impact plate 204 fixedly connected to the annular segment 202. The annular segment 202 can be welded to the annular segment 202. Other connection methods may also be used to connect the impact plate 204 to the annular segment 202.

[0028] Figure 3 illustrate Figure 2The diagram shows a perspective view of the annular segment 202. The annular segment 202 has a generally rectangular shape and a curved shape in the circumferential direction. The annular segment 202 has a first side 302 facing away from the rotating turbine blade 128 and a second side 304 opposite to the first side 302 and facing the rotating turbine blade 128. The annular segment 202 has a front side 310 and a rear side 312 relative to the flow direction of the exhaust 122. The annular segment 202 has a first mating surface side 314 and a second mating surface side 316, each facing an adjacent annular segment assembly 200. The annular segment 202 has a front rail 306 extending radially from the first side 302 and circumferentially along the front side 310. The annular segment 202 has a rear rail 308 extending radially from the first side 302 and circumferentially along the rear side 312.

[0029] The annular segment 202 includes an impact recess 318 defined between the front rail 306, the rear rail 308, the first mating surface side 314, and the second mating surface side 316. The impact recess 318 has an opening on the first side 302, which is obstructed by the impact plate 204 when assembled to form the annular segment assembly 200. Figure 2 (As shown in the diagram) Cover. The impact recess 318 has a generally rectangular shape and a curved shape in the circumferential direction. The impact recess 318 has an impact surface 320. A plurality of supports 322 extend from the impact surface 320 in the radial direction. The supports 322 may have a cylindrical shape, a conical shape, a cubic shape, etc. A plurality of cooling holes 324 are arranged along the edge of the impact recess 318.

[0030] Figure 4 illustrate Figure 2 The diagram shows a top view of a portion of the annular segment 202. The annular segment 202 includes a plurality of pins 402 extending radially from the impact surface 320. The plurality of pins 402 are arranged in an array having a plurality of rows along the X direction and a plurality of columns along the Y direction. The plurality of pins 402 in adjacent rows and columns are offset from each other, thereby defining an interleaved arrangement. Specifically, the illustrated configuration includes pins 402 in adjacent rows or columns positioned such that each pin 402 in a row or column is offset by half the distance between two pins 402 in adjacent rows or columns. In other configurations, the plurality of pins 402 may be offset from each other only in adjacent rows or columns, or aligned with each other in rows and / or columns. Furthermore, other arrangements are possible.

[0031] In an advantageous embodiment, the puncture portion 402 can be used to generate more turbulence, but is not limited thereto, thereby increasing the heat transfer coefficient and / or increasing the heat transfer area, thereby improving heat transfer on the annular segment 202, as will be described in detail below.

[0032] Multiple spiked portions 402 are arranged to form multiple non-spiked impact regions 404 on the impact surface 320. Each of the multiple non-spiked impact regions 404 is a region on the impact surface 320 that does not include the spiked portions 402. The edge of each of the multiple non-spiked impact regions 404 is formed by the multiple spiked portions 402.

[0033] Multiple non-spiked impact regions 404 are arranged in rows along the X direction and columns along the Y direction. At least one spiked portion 402 is placed between two adjacent non-spiked impact regions 404 in a row. At least one spiked portion 402 is placed between two adjacent non-spiked impact regions 404 in a column. A portion of the non-spiked impact region 404 has a hexagonal shape defined by the arrangement of the spiked portions 402 surrounding the non-spiked impact region 404. The remaining portion of the non-spiked impact region 404 has a parallelogram shape, also defined by the arrangement of the spiked portions 402 surrounding the non-spiked impact region 404. The non-spiked impact regions 404 have the same shape in the same row and / or the same column. The non-spiked impact regions 404 with hexagonal shapes are located in the same row and column, as are the non-spiked impact regions 404 with parallelogram shapes. The rows and columns alternate, and the non-spiked impact regions 404 of adjacent rows and columns are offset from each other in a manner similar to that described for the rows and columns of the spiked portion 402. In other configurations, the non-spiked impact regions 404 may have any other different shapes or be arranged in any other different manner.

[0034] Figure 5 for Figure 2A cross-sectional view of the annular segment 202 is shown, which better illustrates the puncture portion 402. Each of the plurality of puncture portions 402 is solid and has a generally conical shape, having a puncture tip 510 and a puncture base 512. The puncture base 512 is attached to the impact surface 320, with the puncture tip 510 located opposite the puncture base 512. The space between the puncture tip 510 and adjacent puncture portions 402 is circular. In the illustrated arrangement, the space between the puncture tip 510 and adjacent puncture portions 402 has the same radius 508. The radius 508 is greater than or equal to 0.5 mm. The puncture portion 402 tapers gradually from the puncture base 512 to the puncture tip 510, with a puncture sidewall 514 in between. The puncture sidewall 514 is conical and has an angle 518 relative to the puncture base 512. Angle 518 is less than or equal to 85°. The maximum puncture width 506 is defined at the bottom 512 of the puncture portion. The maximum puncture width 506 is greater than or equal to 1 mm. The puncture height 504 is defined from the bottom 512 of the puncture portion to the tip 510 of the puncture portion. The ratio of the puncture height 504 to the maximum puncture width 506 is less than or equal to 2. The puncture portions 402 are arranged such that there is a puncture distance 502 between the centers of two adjacent puncture portions 402 in a row and column. The ratio of the puncture distance 502 to the maximum puncture width 506 is greater than or equal to 2. The annular segment 202 has an annular segment thickness 516 defined between the second side 304 and the impact surface 320. The ratio of the annular segment thickness 516 to the puncture height 504 is greater than or equal to 1.25.

[0035] The dimensions described above illustrate some possible arrangements of the poking portion 402, while other configurations are possible. In other configurations, the poking portion 402 may have different dimensions.

[0036] Figure 6 illustrate Figure 2 The impact plate 204 shown is a perspective view. The impact plate 204 has a generally rectangular shape and a curved shape in the circumferential direction.

[0037] The impact plate 204 includes a plurality of protrusions 602 and a plurality of valleys 604. The valleys 604 extend from the impact plate 204 toward the impact surface 320 of the impact cavity 318. The protrusions 602 extend from the impact plate 204 in a direction opposite to that of the valleys 604. The protrusions 602 and valleys 604 are arranged in an array having a plurality of rows along the X direction and a plurality of columns along the Y direction. The protrusions 602 and valleys 604 alternate with each other in each row and column. The protrusions 602 and valleys 604 are offset in each row and column, thus defining an alternating arrangement. The protrusions 602 and valleys 604 provide a negative Poisson's ratio structure for the impact plate 204. Poisson's ratio is a measure of the Poisson effect, where a material expands in a direction perpendicular to the compression direction. Materials characterizing this behavior are defined as having a positive Poisson's ratio structure. On the other hand, materials with a negative Poisson's ratio structure expand in the direction perpendicular to the expansion direction. Materials with a negative Poisson's ratio structure also contract in the direction perpendicular to the compression direction.

[0038] The impact plate 204 includes a plurality of impact holes 606. Each of the plurality of impact holes 606 is formed in an associated valley 604 of a plurality of valleys 604.

[0039] Figure 7 illustrate Figure 2 A cross-sectional view of the annular segment assembly 200. An impact plate 204 is fixedly connected to the annular segment 202 and covers the impact cavity 318. The impact plate 204 is spaced apart from the impact surface 320 of the impact cavity 318 by a non-zero distance 702. Multiple supports 322 ( Figure 3 As shown, it extends between and contacts the impact surface 320 and the impact plate 204 to support the impact plate 204 and maintain a non-zero distance 702 therebetween.

[0040] Multiple impact holes 606 are formed in every other row and every other column of multiple recesses 604. Each impact hole 606 is formed in an associated recess 604 at a location closest to the impact surface 320. Each impact hole 606 is positioned opposite to and associated with a non-puncture impact region 404. Each impact hole 606 defines a central axis 704 perpendicular to the impact surface 320 and passing through the associated non-puncture impact region 404. In the illustrated configuration, the central axis 704 passes through the center of the associated non-puncture impact region 404. In other configurations, the central axis 704 may pass through the associated non-puncture impact region 404 offset from the center.

[0041] In operation, the cooling flow 706 passes through each impact hole 606 and impacts each non-punctured impact region 404 on the impact surface 320. The cooling flow 706 travels the shortest distance from the impact plate 204 to the impact surface 320, which enhances heat transfer. The non-punctured impact regions 404 allow for undisturbed impact from the cooling flow 706 onto the non-punctured impact regions 404. The undisturbed impact improves heat transfer at the non-punctured impact regions 404. The cooling flow 706 is disturbed by multiple punctures 402. The punctures 402 generate turbulence, which improves the heat transfer coefficient and increases the heat transfer area. The enhanced heat transfer reduces the demand on the cooling flow 706 and thus improves the performance of the gas turbine engine 100. The cooling flow 706 exits the impact recess 318 through multiple cooling holes 324 arranged at the edges of the impact recess 318. The annular segment 202 with the dotted portion 402 can be manufactured by conventional casting technology or by other technologies, such as selective laser melting (SLM) printing or electrical discharge machining (EDM).

[0042] Impact plate 204 is fixedly connected to annular segment 202 to cover impact cavity 318. Impact plate 204 is welded around the edge of impact cavity 318. Impact plate 204 has a negative Poisson's ratio structure provided by protrusions 602 and valleys 604. The negative Poisson's ratio structure allows impact plate 204 to expand in both directions under tension that reduces stress at the welded area. The fixed connection of impact plate 204 to annular segment 202 reduces leakage of cooling flow 706 in impact cavity 318, which improves cooling effect.

[0043] Although exemplary embodiments of the present disclosure have been described in detail, those skilled in the art will understand that various changes, substitutions, variations and modifications may be made to the disclosure without departing from the spirit and scope of the broadest form of the disclosure.

[0044] The descriptions in this application should not be taken as implying that any particular element, step, action, or function is an essential element that must be included within the scope of the claims: the scope of the patent subject matter is defined only by the granted claims. Furthermore, none of these claims are intended to invoke a device plus function, unless the exact phrase "device, which is used for" is followed by a participle.

[0045] List of Components in the Attachment

[0046] 100: Gas turbine engine

[0047] 102: Compressor Section

[0048] 104: Combustion Part

[0049] 106: Turbine Section

[0050] 108: Entrance Section

[0051] 110: Exhaust section

[0052] 112: Central Axis

[0053] 114: Compressor stage

[0054] 116: Fixed guide vane

[0055] 118: Rotating blade

[0056] 120: Burner

[0057] 122: Exhaust

[0058] 124: Turbo stage

[0059] 126: Fixed turbine guide vanes

[0060] 128: Rotary turbine blades

[0061] 130: Turbine Inlet

[0062] 132: Control System

[0063] 134: Rotor

[0064] 200: Circular segment assembly

[0065] 202: Circular segment

[0066] 204: Impact plate

[0067] 302: First side

[0068] 304: Second side

[0069] 306: Front Rail

[0070] 308: Rear Rail

[0071] 310: Front

[0072] 312: Rear side

[0073] 314: First mating surface side

[0074] 316: Second mating surface side

[0075] 318: Impact depression

[0076] 320: Impact Surface

[0077] 322: Pillar

[0078] 324: Cooling holes

[0079] 402: Puncture point

[0080] 404: No point-piercing impact area

[0081] 502: Distance between the puncture site and the injection site

[0082] 504: Height of the puncture site

[0083] 506: Maximum width of the puncture site

[0084] 508: Radius

[0085] 510: Tip of the puncture site

[0086] 512: Bottom of the puncture site

[0087] 514: Lateral wall of the puncture site

[0088] 516: Thickness of the annular segment

[0089] 518: Angle

[0090] 602: Protrusion

[0091] 604: concave valley

[0092] 606: Impact Hole

[0093] 702: Non-zero distance

[0094] 704: Central Axis

[0095] 706: Cooling Flow

Claims

1. A ring segment assembly (200), comprising: An annular segment (202) including an impact cavity (318) with an impact surface (320); A plurality of puncture portions (402) extending from the impact surface (320) are arranged to define a plurality of non-puncture impact regions (404). and An impact plate (204) spaced from the impact surface (320) by a non-zero distance (702), the impact plate (204) having a plurality of protrusions (602) and a plurality of valleys (604), the impact plate (204) defining a plurality of impact holes (606), each of the plurality of impact holes (606) being formed in one of the plurality of valleys (604) and positioned opposite to one of the plurality of non-puncture impact regions (404). A portion of the plurality of non-puncture impact regions (404) comprises a hexagonal shape, and the remaining portion of the plurality of non-puncture impact regions (404) comprises a parallelogram shape.

2. The ring segment assembly (200) of claim 1, wherein, The impact plate (204) includes a negative Poisson's ratio structure and is fixedly connected to the annular segment (202).

3. The annular segment assembly (200) as claimed in claim 1, wherein, The plurality of non-spiked impact regions (404) are arranged in an array having a plurality of rows and a plurality of columns, wherein the plurality of non-spiked impact regions (404) having the hexagonal shape and the plurality of non-spiked impact regions (404) having the parallelogram shape alternate in each of the plurality of rows and each of the plurality of columns.

4. The annular segment assembly (200) as claimed in claim 1, wherein, Each of the plurality of impact holes (606) is associated with one of the plurality of non-puncture impact regions (404) and defines a central axis (704), wherein the central axis (704) is perpendicular to the impact surface (320) and passes through the associated non-puncture impact region (404).

5. The annular segment assembly (200) as claimed in claim 4, wherein, The central axis (704) passes through the center of the associated non-puncture impact area (404).

6. The annular segment assembly (200) as claimed in claim 1, wherein, The plurality of protrusions (602) and the plurality of concave valleys (604) are arranged in an array having a plurality of rows and a plurality of columns, wherein the plurality of protrusions (602) and the plurality of concave valleys (604) alternate with each other in each of the plurality of rows and in each of the plurality of columns.

7. The annular segment assembly (200) as claimed in claim 6, wherein, The plurality of impact holes (606) are arranged in every other row of the plurality of rows and in every other column of the plurality of columns.

8. The annular segment assembly (200) as claimed in claim 1, wherein, The plurality of punctures (402) are arranged in an array having a plurality of rows and a plurality of columns, wherein the plurality of punctures (402) are staggered in each of the plurality of rows and in each of the plurality of columns.

9. The annular segment assembly (200) as claimed in claim 1, wherein, It also includes a plurality of struts (322) that extend between and contact each of the impact surface (320) and the impact plate (204) and are operable to maintain the non-zero distance (702) therebetween.

Images