Turbine engine combustor with combustion chamber heat shield

Abstract

A turbine engine includes a compressor section, a combustion section, and a turbine section. The combustion section includes a combustor liner defining a combustion chamber. At least one fuel nozzle and at least one heat shield are located in the combustion chamber. The at least one heat shield includes an inner air flow passage and a pin set.

Description

[0001] Cross-reference to related applications

[0002] This application claims priority and benefit to Polish patent application No. P441103, filed May 5, 2022, the entire contents of which are incorporated herein by reference. Technical Field

[0003] This disclosure generally relates to a turbine engine having a combustor, and more specifically, to a combustor having a heat shield for the combustion chamber of the combustor. Background Technology

[0004] A turbine engine, particularly a gas or combustion turbine engine, is a rotating engine that extracts energy from a stream of combustion gases that passes through the engine and flows over multiple airfoils, which include fixed impeller blades and rotating turbine blades.

[0005] The combustor of a gas turbine engine is configured to burn fuel in a combustion chamber. This configuration can impose significant thermal loads on the combustor structure. Priorities in this environment can include improved cooling or control of the airflow. Attached Figure Description

[0006] In the specification with reference to the accompanying drawings, a complete and feasible disclosure, including its best mode, is set forth for those skilled in the art, wherein:

[0007] Figure 1 This is a schematic diagram of a turbine engine with a compression section, a combustion section and a turbine section, based on the various aspects described in this article.

[0008] Figure 2 It is based on the various aspects described in this article along Line II-II. Figure 1 A cross-sectional view of the combustion zone.

[0009] Figure 3 Based on the various aspects described in this article, it is possible to... Figure 2 A cross-sectional view of the burner used in the combustion section.

[0010] Figure 4 This is based on exemplary embodiments of the present disclosure. Figure 2 An enlarged cross-sectional view of at least a portion of the heat shield.

[0011] Figure 5 It is in accordance with exemplary embodiments of this disclosure Figure 4 The cross-sectional view taken at line VV further shows the pin assembly of the heat shield.

[0012] Figure 6 This is based on exemplary embodiments of the present disclosure. Figure 5The pin assembly further illustrates the airflow.

[0013] Figure 7 This is a cross-sectional view of the pin assembly of a heat shield according to another exemplary embodiment of the present disclosure.

[0014] Figure 8 This is a cross-sectional view of the pin assembly of a heat insulation cover according to yet another exemplary embodiment of the present disclosure. Detailed Implementation

[0015] The aspects of this disclosure described herein are generally directed to a turbine engine with a combustor having a defined combustion chamber. Multiple fuel cups or fuel-air mixers, such as fuel nozzles integrated with a swirl diffuser, discharge the fuel-air mixture into a volume defined as the combustion chamber by a combustor liner. That is, the combustion chamber receiving the fuel-air mixture can be defined at least partially by the combustor liner. For example, a heat shield can be located between adjacent fuel-air mixers or between a fuel-air mixer and a combustor liner to provide separation, barrier, or shielding between components. The heat shield can absorb, guide, or otherwise provide a temperature difference between a first surface and a second surface. The heat shield has an internal airflow passage fluidly connected to cooling air. For example, the cooling air can be provided by a compressor section. Pin groups are located in the internal airflow passage to increase the heat transfer coefficient of the heat shield. The pin group can include multiple subsets of pins. Depending on the observation point, the pin group or multiple subsets of pins can be organized in columns or rows. At least one subset or column of pins has an elongated oval cross-sectional shape. The shape and arrangement of the pins prevent air from flowing linearly through the internal airflow channels. Because air lacks a linear path, it must traverse a longer path to reach more of the pin assembly, thus absorbing more heat. This increased path length, or non-linear path, improves the cooling efficiency of the heat shield. Increased cooling efficiency can reduce the amount of air required to cool the heat shield, allowing the same amount of air to provide improved cooling, or a combination thereof.

[0016] Optionally, the air exiting the internal airflow passage and entering the combustion chamber may have an outlet flow path that interacts with or supplements the swirl. Alternatively, the outlet flow path may transfer supplemental tangential momentum to the swirl of the fuel-air mixture. Yet another alternative is that the air exiting the internal airflow passage may create an air curtain around at least a portion of the fuel-air mixture between adjacent fuel nozzles, or between the fuel nozzle and the burner liner.

[0017] For illustrative purposes, this disclosure will be described in relation to a combustion section or combustor for an aircraft turbine engine. However, it will be understood that the aspects of this disclosure described herein are not limited thereto and can have general applicability in engines including compressors and power generation turbines, as well as in non-aircraft applications such as other mobile applications and non-mobile industrial, commercial, automotive, and residential applications.

[0018] Reference will now be made in detail to the combustor architecture, particularly the heat shield located within the combustion chamber of the turbine engine, one or more examples of which are shown in the accompanying drawings. Detailed descriptions use numbers and letter reference numerals to denote features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to denote similar or analogous portions of this disclosure.

[0019] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0020] The terms "front" and "rear" refer to relative positions within a turbine engine or carrier, and to the normal operating posture of the turbine engine or carrier. For example, in the context of a turbine engine, "front" refers to the position closer to the engine inlet, and "rear" refers to the position closer to the engine nozzle or exhaust port.

[0021] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the fluid flow. As may be used herein, the terms "front" or "forward" mean in front of something, and "back" or "rear" means behind something. For example, when used for fluid flow, front / forward can mean upstream, and back / rear can mean downstream.

[0022] The term "fluid" can refer to either a gas or a liquid. As is available in this document, "fluid connectivity" means that a fluid is able to establish a connection between specified areas.

[0023] Furthermore, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to the direction along a ray extending between the engine's central longitudinal axis and the engine's outer perimeter.

[0024] The singular forms “a,” “an,” and “the” include plural references unless the context clearly specifies otherwise. Furthermore, as used herein, the term “group” or “set” of elements can be any number of elements, including only one.

[0025] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, front, rear, etc.) are for identification purposes only to aid the reader in understanding this disclosure and should not be construed as limiting, in particular, with respect to the location, orientation, or use of aspects of the disclosure described herein. Connecting references (e.g., attachment, connection, joint, and engagement) are to be interpreted broadly and may include intermediate elements between sets of elements and relative movement between elements, unless otherwise indicated. Therefore, connecting references do not necessarily imply that two elements are directly connected and in a fixed relationship with each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying figures may vary.

[0026] Figure 1 This is a schematic diagram of a turbine engine 10. As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16. The compressor section 12, combustion section 14, or turbine section 16 may be arranged in an axially flowing configuration. The compressor section 12, combustion section 14, or turbine section 16 may define an axially extending engine centerline. A drive shaft 18 rotatably connects the compressor section 12 and the turbine section 16 such that rotation of one affects rotation of the other, and defines a rotation axis 20 for the turbine engine 10.

[0027] Compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 that are fluidly connected in series with each other. Turbine section 16 may include an HP turbine 26 and an LP turbine 28 that are fluidly connected in series with each other. Drive shaft 18 may operatively connect the LP compressor 22, HP compressor 24, HP turbine 26, and LP turbine 28 together. Alternatively, drive shaft 18 may include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft may connect the LP compressor 22 to the LP turbine 28, and the HP drive shaft may connect the HP compressor 24 to the HP turbine 26. The LP spool may be defined as a combination of the LP compressor 22, LP turbine 28, and LP drive shaft, such that rotation of the LP turbine 28 may apply a driving force to the LP drive shaft, which in turn may rotate the LP compressor 22. The HP spool may be defined as a combination of the HP compressor 24, HP turbine 26, and HP drive shaft, such that rotation of the HP turbine 26 may apply a driving force to the HP drive shaft, which in turn may rotate the HP compressor 24.

[0028] Compressor section 12 may include multiple axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. The compressor blades for a stage of compressor section 12 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of compressor section 12 may be mounted to a housing that may extend circumferentially around turbine engine 10. It will be understood that the representation of compressor section 12 is merely illustrative and any number of stages may be possible. Furthermore, it is contemplated that any other number of components may be present within compressor section 12.

[0029] Similar to compressor section 12, turbine section 16 may include multiple axially spaced stages, each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Turbine blades for one stage of turbine section 16 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of the turbine section may be circumferentially mounted to the housing. It should be noted that any number of blades, blades, and turbine stages can be present, as the illustrated turbine section is merely schematic. Furthermore, it is contemplated that any other number of components may be present within turbine section 16.

[0030] Combustion section 14 may be arranged in series between compressor section 12 and turbine section 16. Combustion section 14 may be fluidly coupled to at least a portion of compressor section 12 and turbine section 16, such that combustion section 14 at least partially fluidly couples compressor section 12 to turbine section 16. As a non-limiting example, combustion section 14 may be fluidly coupled to HP compressor 24 at its upstream end and to HP turbine 26 at its downstream end.

[0031] During operation of the turbine engine 10, ambient air or atmospheric air is drawn into the compressor section 12 via a fan (not shown) upstream of the compressor section 12, where the air is compressed to define pressurized air. This pressurized air can then flow into the combustion section 14, where it mixes with fuel, ignites, and burns to generate combustion gases. The HP turbine 26 extracts some work from these combustion gases, driving the HP compressor 24. The combustion gases are discharged into the LP turbine 28, which extracts additional work to drive the LP compressor 22, and the exhaust gases are ultimately discharged from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 28 drives the LP spool to rotate the fan (not shown) and the LP compressor 22. The pressurized airflow and combustion gases together define the working airflow flowing through the fan, compressor section 12, combustion section 14, and turbine section 16 of the turbine engine 10.

[0032] Figure 2 Depicting along Figure 1 The image shows a cross-sectional view of combustion section 14 along line II-II. Combustion section 14 may include a burner 30 having an annular arrangement of fuel cups, premixers, fuel-air mixers, or fuel nozzles 31 arranged around the centerline or axis of rotation 20 of the turbine engine 10. It should be understood that the annular arrangement of fuel cups or fuel nozzles 31 may be one or more fuel nozzles, and one or more of the fuel nozzles 31 may have different characteristics. Depending on the type of engine in which the burner 30 is located, the burner 30 may have a canister-shaped, canister-annular, or annular arrangement. In a non-limiting example, the burner 30 may have a combined arrangement positioned together with the engine housing 32.

[0033] The burner 30 may be at least partially defined by a burner liner 34. The burner liner 34 may be a burner housing, a flame tube, or may include multiple layers of housing or liner. That is, the burner liner 34 may define at least a portion of the combustion chamber or volume for a canister-shaped, canister-annular, or annularly arranged burner.

[0034] In some examples, the burner liner 34 may include an outer liner 33 and an inner liner 35, which are concentric with each other and arranged in a ring around the engine centerline or axis of rotation 20. In some examples, the burner liner 34 may have a ring-shaped structure around the burner 30. In some examples, the burner liner 34 may include multiple segments or portions that collectively form the burner liner 34. The dome assembly 36, together with the burner liner 34, may at least partially define a combustion chamber 40 arranged in a ring around the axis of rotation 20. The compressed air passage 42 may be at least partially defined by both the burner liner 34 and the housing 32.

[0035] Figure 3 A cross-sectional view depicting a portion of a combustion section suitable for use in combustion section 14, located between compressor section 12 and turbine section 16 of the turbine engine 10. Figure 1 Between ), the burner axis 38 may extend in the axial direction and is defined by the burner 30.

[0036] The compressed air passage 42, at least partially defined by the burner liner 34 and the housing 32, can receive compressed air from the compressor section 12. Optionally, a cooling circuit, such as, but not limited to, a porous, fusion-null orifice, or dilution orifice 44 as shown in the dashed line, may be included in the burner liner 34. The cooling circuit or dilution orifice 44 can fluidly connect the compressed air passage 42 to the combustion chamber 40.

[0037] As an example, at least one or more fuel nozzles 31 are illustrated as a first fuel nozzle 50 and a second fuel nozzle 52. A first fuel outlet 54 and a second fuel outlet 56 fluidly connect the first fuel nozzle 50 and the second fuel nozzle 52 to the combustion chamber 40, respectively. It should be understood that the annularly arranged fuel nozzles 31 can be one or more fuel nozzles, wherein one or more of the fuel nozzles can have different characteristics, because the first fuel nozzle 50 and the second fuel nozzle 52 are shown for illustrative purposes only and are not intended to be limiting.

[0038] The first fuel nozzle 50 and the second fuel nozzle 52 may be coupled to or disposed within the dome assembly 36. At least one fuel supply line 58, as shown by the dashed line, may connect the fuel injectors 60 of the first fuel nozzle 50 and the second fuel nozzle 52 to the fuel supply assembly or fuel tank 61, as shown by the dashed line. A vortex 63 may be provided to cause the incoming air to swirl near the fuel injector 60. The vortex 63 may be included in or coupled to at least one fuel nozzle 31.

[0039] The burner liner 34 may have an outer surface 62 and an inner surface 64 that at least partially defines the combustion chamber 40. The burner liner 34 may be made from a single continuous integral part, or it may be multiple integral parts assembled together to define the burner liner 34. As a non-limiting example, the outer surface 62 may define a first piece, while the inner surface 64 may define a second piece, which, when assembled together, form the burner liner 34. As described herein, the burner liner 34 may include at least one cooling circuit, which, as an example, is shown as a dilution orifice 44. Further, it is contemplated that the burner liner 34 may be of any type, including but not limited to double-walled liners or ceramic tile liners. The igniter 66 may be fluidly coupled to the combustion chamber 40 at any location, and as a non-limiting example, is fluidly coupled to the combustion chamber 40 downstream of the dilution orifice 44.

[0040] Optionally, at least one retaining component 68 may attach the burner liner 34 to the housing 32. As shown by the dashed line, the at least one retaining component 68 may be in any position and may include additional structural or mechanical fasteners securing at least a portion of the housing 32 and the burner liner 34. Alternatively, multiple portions of the burner liner 34 may be integrally formed with the housing 32.

[0041] At least one heat shield can extend from the dome assembly 36 into the combustion chamber 40. As an example, at least one heat shield is shown as a first heat shield 70, a second heat shield 72, and a third heat shield 74. The first heat shield 70, the second heat shield 72, and the third heat shield 74 each include a first surface 76 and a second surface 78.

[0042] As shown in the figure, as a non-limiting example, the first heat shield 70 is adjacent to and separated from the burner liner 34. Although the figure shows a gap between the burner liner 34 and the first heat shield 70, it is contemplated that a portion of the first heat shield 70 may contact a portion of the burner liner 34. The first heat shield 70 is also shown adjacent to the first fuel nozzle 50. That is, the first heat shield 70 may be radially positioned between the first fuel outlet 54 of the first fuel nozzle 50 and the burner liner 34.

[0043] As a non-limiting example, the second heat shield 72 is shown radially positioned between the first fuel outlet 54 of the first fuel nozzle 50 and the second fuel outlet 56 of the second fuel nozzle 52. That is, the first heat shield 70 and the second heat shield 72 may be located on radially opposite sides of the first fuel outlet 54 of the first fuel nozzle 50. The second heat shield 72 may provide a barrier between the first fuel outlet 54 and the second fuel outlet 56, or otherwise separate the first fuel outlet 54 and the second fuel outlet 56.

[0044] As a non-limiting example, the third heat shield 74, as shown, is adjacent to the burner liner 34. The third heat shield 74 is also shown adjacent to the second fuel nozzle 52. That is, the third heat shield 74 may be radially positioned between the second fuel outlet 56 of the second fuel nozzle 52 and the burner liner 34. The second heat shield 72 and the third heat shield 74 may be located on radially opposite sides of the second fuel outlet 56 of the second fuel nozzle 52. Although a gap is shown between the burner liner 34 and the third heat shield 74, it is contemplated that a portion of the third heat shield 74 may contact a portion of the burner liner 34.

[0045] Although the illustration shows two fuel nozzles and three heat shields, any number of fuel nozzles and heat shields are expected. Further, it is anticipated that each fuel nozzle outlet has a heat shield located radially outside or adjacent to the outlet, and another heat shield located radially inside or adjacent to the outlet.

[0046] The internal airflow passage 80 may be at least partially defined by the first surface 76 and the second surface 78 of the first heat shield 70, the second heat shield 72, and the third heat shield 74. The internal airflow passage 80 includes an air inlet 82 and an air outlet 84. A portion of the compressed air from the compressor section 12 may flow through the internal airflow passage 80 to the combustion chamber 40, as indicated by the flow path arrow 86. That is, a portion of the compressed air from the compressor section 12 may flow into the air inlet 82, through the internal airflow passage 80, and exit the air outlet 84 into the combustion chamber 40.

[0047] Multiple pins, referred to herein as pin group 90, are located within the internal airflow passage 80. The pins in pin group 90 may extend from either a first surface 76 or a second surface 78. It is contemplated that at least one subset of pins in pin group 90 extends between or is integrally formed with the first surface 76 and the second surface 78. That is, at least one subset of pin group 90 connects the first surface 76 to the second surface 78. Although illustrated generally linearly, the first surface 76 or the second surface 78 may be curved or include curved or angled portions.

[0048] Furthermore, it is anticipated that a subset of pins in pin assembly 90 may extend from the first surface 76 toward the second surface 78 without being engaged or connected to the second surface 78. Alternatively, a subset of pins in pin assembly 90 may extend from the second surface 78 toward the first surface 76 without being engaged or connected to the first surface 76.

[0049] It is further anticipated that the pin assembly 90 may bend horizontally or vertically along the flow path (along the columns currently described). That is, the pin assembly 90 may include at least one subset of pins that are angled or bent as they extend from the first surface 76 or the second surface 78.

[0050] Figure 4 This is an enlarged cross-sectional view of at least a portion of the first heat shield 70. The centerline 92 of the airflow channel extends downstream from the air inlet 82 of the internal airflow channel 80 to the air outlet 84. Multiple openings 88 may appear between the pins. That is, the pin assembly 90 extending from the first surface 76 to the second surface 78 may define multiple openings 88. The multiple openings 88 show portions of the internal airflow channel 80, further indicated by dashed lines, where airflow within the internal airflow channel 80 may flow into or out of the page around the pin assembly 90 as airflow proceeds from the air inlet 82 to the air outlet 84.

[0051] The first heat shield 70 may include a cavity 94 upstream of and fluidly connected to the air inlet 82. Specifically, curved, wavy, or linear portions of the first surface 76 and the second surface 78 upstream of the internal airflow passage 80 may define the cavity 94. The heat shield inlet 96 may receive air from the compressor section 12 (… Figure 3 Compressed gas from HP compressor 24. Alternatively, the heat shield inlet 96 can receive compressed gas from HP compressor 24. Figure 1 The upstream air intake.

[0052] Alternatively, the flow deflector 98, as shown by the dashed line, may be located in or adjacent to the air inlet 82 of the internal airflow passage 80. Although illustrated as a protrusion, the flow deflector 98 may be a recess or other known structure for redirecting, turning, or swirling the airflow from the cavity 94 before it enters the internal airflow passage 80.

[0053] The first channel height 100 can be measured at the air inlet 82 of the internal airflow channel 80. The second channel height 102 can be measured at the channel outlet or air outlet 84. The ratio of the first channel height 100 to the second channel height 102 can be equal to 1:1 and 3:1 or between 1:1 and 3:1. That is, the effective area of ​​the internal airflow channel 80 from the air inlet 82 to the air outlet 84 can be uniform or tapered. It is anticipated that the ratio of the first channel height 100 to the second channel height 102 will be between 1.5:1 and 2:1. Even after the airflow contacts and flows around the pins on its way through the pin assembly 90, the uniform or tapered effective area of ​​the internal airflow channel 80 can maintain the effective area and / or velocity of the air flowing through the internal airflow channel 80.

[0054] As shown in the figure, as an example, the second airflow channel wall 79 adjacent to the second surface 78 tapers towards the airflow channel centerline 92 in the downstream direction. However, it is anticipated that, alternatively, the first airflow channel wall 77 adjacent to the first surface 76 may taper towards the airflow channel centerline 92. As an example, through Figure 3 The second heat shield 72 further anticipates and illustrates that the first airflow channel wall adjacent to the first surface 76 and the second airflow channel wall adjacent to the second surface 78 can taper in the downstream direction toward the centerline 92 of the airflow channel.

[0055] Figure 5 A schematic cross-section of the pin assembly 90 is further shown. As an example, the pin assembly 90 is illustrated as having eight rows of pins located within the internal airflow passage 80. However, any number of pins or rows of pins is contemplated.

[0056] Pin group 90 may include one or more subsets of pins, such as first subset 104, second subset 106, or third subset 108. Although shown to have the same shape or size, it is contemplated that subsets may include any number of consecutive or discontinuous pin groups with different sizes or shapes.

[0057] Although shown as having an elongated oval cross-sectional shape, or more specifically, a stadium-shaped or track-shaped cross-section, it is contemplated that one or more pins in pin group 90 may have cross-sectional shapes of different shapes. As a non-limiting example, one or more pins or subsets of pins in pin group 90 may have elliptical, oval, rounded rectangular, teardrop-shaped, or V-shaped cross-sections. It is contemplated that the cross-sectional shape of one or more subsets of pins may include at least one axis of symmetry.

[0058] Pin subsets 104, 106, and 108 may include multiple pins, which may be arranged in any number of columns or other configurations, such as, but not limited to, geometric structures. As an example, exemplary columns are illustrated as a first pin column 110, a second pin column 114, and a third pin column 118.

[0059] For example, a first pin column 110 may define a first column centerline 112. A second pin column 114 may define a second column centerline 116. The second column centerline 116 may be spaced apart from the first column centerline 112. As a non-limiting example, the second column centerline 116 is axially spaced downstream of the first column centerline 112, wherein the general direction downstream is indicated by the flow direction arrow 123. The first pin column 110 and the second pin column 114 are spaced apart relative to each other such that the non-circular cross-sections combining at least one subset of pins from the pin group 90 do not have a linear path through the pin group 90 in the downstream direction. Although illustrated herein as linear, it is contemplated that the columns may be non-linear.

[0060] The third pin column 118 may define a third column center line 120. The third column center line 120 may be spaced apart from the first column center line 112 and the second column center line 116. As a non-limiting example, the third column center line 120 is axially spaced apart from the first column center line 112 and the second column center line 116 and is downstream of the first column center line 112 and the second column center line 116.

[0061] Pin columns 110, 114, and 118 can be groups of adjacent pins. For example, adjacent pins in the same column are illustrated as first pin 118a, second pin 118b, third pin 118c, fourth pin 118d, fifth pin 118e, and sixth pin 118f. Alternatively, adjacent pins in this column can have the same cross-sectional shape or the same orientation.

[0062] The first column centerline 112 can form a first column angle 122 relative to the airflow channel centerline 92. That is, the first column angle 122 can be measured counterclockwise from the airflow channel centerline 92 to the first column centerline 112.

[0063] The second column angle 124 can be measured counterclockwise from the centerline 92 of the airflow channel to the centerline 116 of the second column. The third column angle 126 can be measured counterclockwise from the centerline 92 of the airflow channel to the centerline 120 of the third column.

[0064] Although shown as identical, it is anticipated that the first column centerline 112, the second column centerline 116, or the third column centerline 120 can form any angle relative to the airflow channel centerline 92. It is further anticipated that the angle measured clockwise from the airflow channel centerline 92 to any column centerline can be greater than zero and less than 180 degrees.

[0065] Each pin in pin group 90, such as pins 118a, 118b, 118c, 118d, 118e, and 118f, has a length or long body axis with the largest cross-sectional dimension. The width or short body axis can be measured in a cross-sectional plane substantially perpendicular to the length or long body axis, wherein the term "substantially perpendicular" is defined as an angle equal to or between 85 and 95 degrees. Alternatively, the width or short body axis can be measured in a cross-sectional plane at any angle relative to the length or long body axis.

[0066] At least one pin in the first pin column 110 includes a first length 130 and a first width 132. A first pin angle 134 can be measured between the first length 130 and the center line 112 of the first column.

[0067] The second long body axis or second length 140 and the second short body axis or second width 142 can be measured in the cross-sectional plane of at least one pin in the second pin column 114. The second pin angle 144 can be measured between the second length 140 and the center line 116 of the second column. The second pin angle 144 can be substantially equal to the first pin angle 134; however, it is contemplated that the second pin angle 144 can be between 0 degrees and 180 degrees. It is further contemplated that the difference between the first pin angle and the second pin angle 144 is 90 degrees.

[0068] At least one pin in the third pin column 118 includes a third length 150 and a third width 152. A third pin angle 154 can be measured between the third length 150 and the center line 120 of the third column. The third pin angle 154 can be substantially equal to the first pin angle 134 or the second pin angle 144; however, it is anticipated that the third pin angle 154 can be between 0 degrees and 180 degrees. It is further anticipated that the difference between the first pin angle 134 or the second pin angle 144 and the third pin angle 154 is 90 degrees.

[0069] The ratio of the first length 130 to the first width 132, the ratio of the second length 140 to the second width 142, or the ratio of the third length 150 to the third width 152 can be between 1.1:1 and 4:1. However, it is anticipated that the ratios of the first, second, or third lengths 130, 140, 150 to the first, second, or third widths 132, 142, 152 will be between 1.5:1 and 3:1, respectively.

[0070] It is further anticipated that the ratio of the first length 130 to the first width 132 is equal to 1.1:1 and 2:1 or between 1.1:1 and 2:1, the ratio of the second length 140 to the second width 142 is greater than 2:1, and the ratio of the third length 150 to the third width 152 is equal to 1:1 and 2:1 or between 1:1 and 2:1.

[0071] As an example, the first length 130 can be less than the second length 140. Alternatively, the first length 130 can be equal to or greater than the second length 140. The second length 140 can be greater than the third length 150. Alternatively, the second length 140 can be equal to or less than the third length 150. The first length 130 can be equal to the third length 150. Alternatively, the first length 130 can be greater than or less than the third length 150.

[0072] The ratio remains the same or decreases. Increases then decreases.

[0073] The first width 132, the second width 142, or the third width 152 may be substantially equal, wherein the term "substantially equal" indicates that the values ​​are within 5% of each other. Alternatively, the values ​​or measurements of the first width 132, the second width 142, or the third width 152 may be different. That is, the values ​​or measurements of the first width 132, the second width 142, or the third width 152 may not be equal.

[0074] The first length 130 and the first width 132 can indicate the first pin column 110 or the first subset 104. That is, when determining the first length 130 or the first width 132, the lengths and widths of the multiple pins constituting the column or subset can be taken into account. The mean, median, mode, or other algebraic combination of the lengths of each of the multiple pins constituting the first pin column 110 or the first subset 104 can be used to determine the first length 130. Similarly, the mean, median, mode, or other algebraic combination of the widths of each of the multiple pins constituting the first pin column 110 or the first subset 104 can be used to determine the first width 132.

[0075] It is also anticipated that the second length 140, the second width 142, the third length 150 or the third width 152 may indicate the second pin column 114, the second subset 106, the third pin column 118, or the third subset 108.

[0076] The gap or column distance 155 can be the distance measured between two pins, where each pin is in an adjacent pin column. That is, the column distance 155 can be measured as the shortest distance between two adjacent pins from an adjacent pin column. The column distance 155 can vary between one or more pairs of adjacent pin columns. It is anticipated that the column distance 155 can be within 0% to 20% of the first width 132, the second width 142, or the third width 152.

[0077] Optionally, column distance 155 can be equal within subsets 104, 106, and 108 of pin group 90. It is anticipated that column distance 155 can vary among subsets 104, 106, and 108 of pin group 90. Further, it is anticipated that column distance 155 can be equal across pin group 90.

[0078] The pin distance 156 can be measured between adjacent pins in the same column. That is, the pin distance 156 can be measured as the shortest distance between two adjacent pins in the same pin column. The pin distance 156 can vary between one or more pairs of adjacent pins. It is expected that the pin distance 156 can be within 0% to 20% of the first width 132, the second width 142, or the third width 152.

[0079] Optionally, the pin distance 156 can be equal within subsets 104, 106, and 108 of pin group 90. It is also anticipated that the pin distance 156 can vary among subsets 104, 106, and 108 of pin group 90. Furthermore, it is anticipated that the pin distance 156 can be equal across pin group 90.

[0080] Although illustrated as non-overlapping, it is anticipated that one or more adjacent pins may overlap. That is, a line drawn parallel to the center line of a column may pass through or intersect two adjacent pins from different columns. In other words, pin group 90 may include subgroups of pins that overlap in the radial or axial direction.

[0081] Furthermore, it is anticipated that one or more adjacent pins may overlap, while the centerlines of one or more adjacent pins may remain discrete or non-overlapping. That is, although the centerlines of one or more adjacent pins may not overlap, a line drawn parallel to the column centerline may pass through two adjacent pins from different columns or intersect with two adjacent pins from different columns.

[0082] Figure 6 This further illustrates a schematic cross-section of the airflow through pin assembly 90. As an example, a first nonlinear airflow path 158 illustrates an example of a serpentine, tortuous, or nonlinear airflow path capable of flowing through at least a portion of pin assembly 90. The first nonlinear airflow path 158 fluidly connects air inlet 82 to air outlet 84.

[0083] The second nonlinear airflow path 160 is another example of a serpentine, tortuous, or nonlinear airflow path that splits into a first split flow 160a and a second split flow 160b. As shown, the first split flow 160a and the second split flow 160b can re-merge. Alternatively, it is also contemplated that the first split flow 160a or the second split flow 160b can receive or merge with other airflows (not shown) or exit the pin group 90 between different sets of adjacent pins.

[0084] A linear flow path is any flow path that directly connects air inlet 82 and air outlet 84 via the shortest distance. Air cannot flow through pin group 90 in a linear path. The elongated or non-circular cross-sectional shape of at least one subset or column of pins, and the axial spacing of the subset or column of pins, prevent the air flow path from being linear. The first linear flow path 162 is shown in dashed lines because it is practically impossible for air to follow or flow along the first linear flow path 162. The second linear flow path 164 and the third linear flow path 166 are also shown in dashed lines to further illustrate what is considered a linear flow path. In other words, there is no straight line through which fluid can flow from air inlet 82 to air outlet 84. Any such attempt at a linear flow path is blocked or otherwise impeded by at least one subset of pins from pin group 90. All possible air flow paths through pin group 90 when flowing from air inlet 82 to air outlet 84 include at least a turn or bend. That is, any air flow path connecting air inlet 82 and air outlet 84 includes at least a serpentine or curved portion.

[0085] During operation, compressed air comes from compressor section 12 or from HP compressor 24 ( Figure 1 The upstream exhaust gas is supplied to the first, second, and third heat shields 70, 72, and 74. Figure 3 The internal airflow passage 80, defined by the first, second, and third heat shields 70, 72, and 74, connects compressed air from the compressor section 12 or bleed air from upstream of the HP compressor 24 to the combustion chamber 40. Figure 3 ).

[0086] When air flows into the air inlet 82 and through the internal air flow channel 80, air heat conduction occurs from portions of the first and second surfaces 76, 78 that define the internal air flow channel 80 and the pin assembly 90. Figure 3 and Figure 4 The heat of the pin assembly ( ). The pin group 90 includes at least one subset of pins, the cross-section of which has an elongated or non-circular cross-sectional shape. The shape of the pin subset and the axial spacing of the pin rows ensure that no linear path passes through the pin group ( ). Figures 5-8 (Refer to again) Figure 6As an example, the first nonlinear airflow path 158 illustrates at least a partially serpentine, curved, tortuous, or zigzag airflow path from air inlet 82 through pin assembly 90 to air outlet 84. Due to the absence of a linear path, the time length is increased, and thus the heat conducted by the air increases. Additionally, pin assembly 90 includes pins with non-circular cross-sections. Pin assembly 90 having at least one subset of pins with non-circular cross-sections can be compared to pin assembly consisting only of pins with circular cross-sections. This takes into account the case where circular and non-circular cross-sections have the same short body axis or width. The surface area in contact with air flowing through pin assembly with pins having non-circular cross-sections is greater than the surface area in contact with air flowing through pin assembly with pins having only circular cross-sections. The increase in the surface area of ​​pins with non-circular cross-sections can increase the overall heat transfer coefficient of the heat insulation shroud compared to the heat transfer coefficient of a shroud consisting only of pins with circular cross-sections.

[0087] The flow in the second nonlinear airflow path 160 is likely to separate at one pin and reattach at another to ensure “contact” of the flowing medium. Compared to the heat transfer coefficient of a heat shield that only includes pins with circular cross-sections, the second nonlinear airflow path 160 exhibits improved heat pick-up and thus increases the overall heat transfer coefficient of the heat shield.

[0088] During discharge, air from the first, second, or third heat shields 70, 72, 74 may have an outlet flow path, which is connected to the combustion chamber 40. Figure 3 The swirling interaction of the fuel-air mixture in the combustion chamber 40, or supplemental combustion chamber 40 Figure 3 The swirling of the fuel-air mixture within the combustion chamber. Alternatively, the outlet flow path may transfer supplemental tangential momentum to the swirling of the fuel-air mixture. Yet another alternative is that air exiting the internal airflow passage 80 may surround at least a portion of the fuel-air mixture, between adjacent fuel nozzles 50, 52, or between the fuel nozzles 50, 52 and the burner liner 34. Figure 3 An air curtain is created between them.

[0089] Figure 7 A cross-section of another exemplary pin assembly 190 is shown. Pin assembly 190 and... Figure 5 The similarity is similar to that of pin group 90, so similar parts will be identified by similarity numbers increased by 100. It should be understood that, unless otherwise stated, the description of similar parts of pin group 90 applies to pin group 190.

[0090] Pin group 190 may include one or more subsets of pins, such as a first subset 204, a second subset 206, and a third subset 208. A fourth subset 205 may be located downstream of the first subset 204 and upstream of the second subset 206. A fifth subset 207 may be located between the second subset 206 and the third subset 208. A sixth subset 209 may be located downstream of the third subset 208. The first, second, third, fourth, fifth, or sixth subsets 204, 205, 206, 207, 208, and 209 may consist of multiple pins. The multiple pins may be arranged in any number of columns or other configurations.

[0091] As a non-limiting example, the pins in each of the first, second, third, fourth, fifth, and sixth subsets 204, 205, 206, 207, 208, and 209 can be grouped based on size and shape. For example, the pins in the first subset 204 have the same size and shape, but can have different angles or orientations relative to the flow direction arrow 123.

[0092] The pins in the first, second, and third subsets 204, 206, and 208 may have first, second, and third lengths of 230, 240, and 250, respectively, and widths of the first, second, and third lengths of 232, 242, and 252, respectively. The fourth, fifth, and sixth subsets 205, 207, and 209 may include pins having fourth, fifth, and sixth lengths of 215, 217, and 219, respectively, and widths of the fourth, fifth, and sixth lengths of 225, 227, and 229, respectively.

[0093] The ratios of lengths 215, 217, 219, 230, 240, 250 to widths 225, 227, 229, 232, 242, 252 can be equal to 1:1 and 4:1, or between 1:1 and 4:1. However, it is anticipated that the ratios of the first, second, third, fourth, and fifth lengths 215, 217, 230, 240, 250 to the first, second, third, fourth, and fifth widths 225, 227, 232, 242, 252 will be between 1.1:1 and 3:1. Optionally, the ratio of the sixth length 219 to the sixth width 229 can be 1:1. That is, the pins in the sixth subset 209 can have, but are not limited to, a circular cross-sectional shape.

[0094] The values ​​or measures of the widths 225, 227, 229, 232, 242, 252 of the pins used for each of the subsets 204, 205, 206, 207, 208, 209 can be different. As shown in the figure, as a non-limiting example, the widths 225, 227, 229, 232, 242, 252 of each subset 204, 205, 206, 207, 208, 209 can decrease in the airflow direction, as indicated by the flow direction arrow 123. Alternatively, the widths 225, 227, 229, 232, 242, 252 can be substantially equal, where the term "substantially equal" indicates values ​​within 5% of each other. It is also contemplated that the widths 225, 227, 232, 242, 252 can be substantially equal to and greater than or less than the sixth width 229.

[0095] The column distance 255 can be the distance measured between two adjacent pins, for example, the distance measured between the first pin 291a and the second pin 291b. That is, the column distance 255 can be measured as the shortest distance between two adjacent pins from adjacent pin columns. The column distance 255 can be equal across pin groups 190. Alternatively, the column distance 255 can vary between one or more pairs of adjacent pin columns. It is contemplated that the column distance 255 can be within 0% to 20% of the first width 232, the second width 242, the third width 252, the fourth width 225, the fifth width 227, or the sixth width 229.

[0096] The pin distance 256 can be measured between adjacent pins in the same column, for example, between the second pin 291b and the third pin 291c. That is, the pin distance 256 can be measured as the shortest distance between two adjacent pins from adjacent pin columns.

[0097] As an example, airflow path 258 is shown having at least a partially serpentine, tortuous, or non-linear portion 258a. Optionally, in addition to the non-linear portion 258a, airflow path 258 may include a linear portion 258b. Airflow path 258 fluidly connects air inlet 82 to air outlet 84. It is also contemplated that different pin sizes or cross-sectional shapes can be combined to provide various flow paths through pin assembly 190 or to separate the linear and non-linear portions of the flow paths.

[0098] Figure 8 The illustration shows a cross-section of another exemplary pin assembly 290. Pin assembly 290 and... Figure 7 The similarity is similar to that of pin group 190. Therefore, similar parts will be identified by a similarity number further increased by 100. It should be understood that, unless otherwise stated, the description of the similar parts of pin group 190 applies to pin group 290.

[0099] Pin group 290 may include one or more pin subsets, such as first subset 303, second subset 306, third subset 308 and fourth subset 309.

[0100] As a non-limiting example, the pins in each of the first, second, third, and fourth subsets 303, 306, 308, and 309 may be grouped based on size, shape, or orientation relative to the flow direction arrow 123.

[0101] The pins in the first, second, third, and fourth subsets 303, 306, 308, and 309 can have first, second, third, and fourth lengths 339, 340, 350, and 351, and first, second, third, and fourth widths 341, 342, 352, and 353, respectively.

[0102] The ratio of lengths 339, 340, 350, 351 to widths 341, 342, 352, 353 can be equal to 1:1 and 4:1 or between 1:1 and 4:1.

[0103] The values ​​or measures of the lengths 339, 340, 350, 351 or the widths 341, 342, 352, 353 of the pins used for each of the subsets 303, 306, 308, 309 may differ between subsets or between pins within each subset 303, 306, 308, 309. Alternatively, the lengths 339, 340, 350, 351 or the widths 341, 342, 352, 353 may be substantially equal between two or more pins or between two or more subsets 303, 306, 308, 309.

[0104] It is further anticipated that the lengths 339, 340, 350, and 351 may be roughly equal to one or more widths 341, 342, 352, and 353, or within 5% of one or more widths 341, 342, 352, and 353.

[0105] As an example, the ratio of the first length 339 to the first width 341 can be 1:1, and the overall cross-sectional shape of at least one pin in the pin group 290 can be oblong or non-circular. In other words, the cross-sectional shape of at least one subset of pins in the pin group 290 can be teardrop-shaped or V-shaped.

[0106] As an example, a nonlinear airflow path 372 is shown flowing from air inlet 82 to air outlet 84. However, the nonlinear airflow path 372 may include a linear portion 372a, and at least a portion 372b of the nonlinear airflow path 372 may be curved, zigzag, serpentine, or otherwise change direction. It is also contemplated that different pin sizes or cross-sectional shapes may be combined to provide various flow paths through pin assembly 290 or to separate the linear and nonlinear portions of the flow paths.

[0107] Benefits associated with this disclosure, as described herein, include increasing the length of time a given amount of air takes to pass through the heat shield in the combustion chamber. The pin assembly in the internal airflow passage of the heat shield comprises at least one subset of pins having an elongated or non-circular cross-section. The cross-sectional shape of the pin subset and the position of the pins disrupt what was previously a linear path through the internal airflow passage. This increased time in the internal airflow passage allows the air to conduct more heat than it would in a shorter time within the internal airflow passage. This can improve thermal performance or reduce the amount of air required to achieve the same thermal effect.

[0108] Another benefit is that the air exiting the internal airflow passages of the heat exchanger and entering the combustion chamber can have an outlet flow path that interacts with or supplements the swirling flow of the fuel-air mixture in the combustion chamber. Alternatively, the outlet flow path can transfer supplementary tangential momentum to the swirling flow of the fuel-air mixture. The interaction between the air exiting the heat shield and the swirling flow of the fuel-air mixture, or the transfer of supplementary tangential momentum, can provide acoustic benefits.

[0109] Another benefit is that air exiting the internal airflow passage can create an air curtain around at least a portion of the fuel-air mixture, between adjacent fuel nozzles, or between the fuel nozzles and the burner liner. More specifically, air exiting the internal airflow passage can create an air curtain around at least a portion of the fuel-air mixture. The airflow exiting the internal airflow passage can also provide an air curtain between adjacent fuel nozzles or between the fuel nozzles and the burner liner.

[0110] Within the scope not yet described, various features and structures of different aspects may be combined or substituted for each other as needed. The fact that a feature is not illustrated in all examples does not mean that it cannot be illustrated in this way, but rather that it is done for the sake of brevity. Therefore, various features of different aspects may be mixed and matched as needed to form new aspects, regardless of whether the new aspects are explicitly described. All combinations or substitutions of the features described herein are covered by this disclosure.

[0111] This written description uses examples to illustrate aspects of the disclosure described herein, including best practices, and also enables any person skilled in the art to practice aspects of this disclosure, including making and using any apparatus or system and performing any incorporated methods. The patentable scope of aspects of this disclosure is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0112] Further aspects of this disclosure are provided by the subject matter of the following provisions:

[0113] A turbine engine includes: a compressor section, a combustion section, and a turbine section arranged in a tandem flow configuration, the combustion section including: a combustor liner defining a combustion chamber; at least one fuel nozzle having a fuel outlet fluidly connected to the combustion chamber; at least one heat shield located near the fuel outlet of the fuel nozzle and extending into the combustion chamber, the at least one heat shield including: an internal airflow passage having an air inlet and an air outlet fluidly connected to the combustion chamber, and a centerline of the airflow passage extending downstream from the air inlet to the air outlet; and a pin assembly located within the internal airflow passage and having a first pin column defining a first column of centerlines forming a first angle relative to the centerline of the airflow passage, and a second pin column defining a second column of centerlines forming a second angle relative to the centerline of the airflow passage, the second column of centerlines being spaced downstream of the first column of centerlines, the first pin column and the second pin column having different cross-sectional shapes, wherein the first pin column or the second pin column comprises an oblong cross-sectional shape.

[0114] According to the foregoing provisions, the first and second pin rows define a portion of one or more airflow paths that flow through the pin group in the downstream direction and fluidly connect the air inlet to the air outlet, and the one or more airflow paths include at least a serpentine or curved portion.

[0115] The turbine engine according to any one of the foregoing clauses, wherein the first channel height of the air inlet and the second channel height of the air outlet have a ratio of the first channel height to the second channel height equal to 1:1, 3:1, or between 1:1 and 3:1.

[0116] The turbine engine according to any one of the foregoing clauses, wherein the ratio of the first channel height to the second channel height is between 1.5:1 and 2:1.

[0117] In the turbine engine according to any one of the foregoing clauses, the cross-section of one or more pins in the first pin column or the second pin column includes at least one axis of symmetry.

[0118] In the turbine engine according to any one of the foregoing clauses, the cross-section of one or more pins in at least one pin subgroup of the pin group is stadium-shaped, elliptical, oval, rounded rectangle, teardrop-shaped, or V-shaped.

[0119] According to any one of the preceding clauses, in the turbine engine, the cross-section of one or more pins in the at least one pin subset of the pin group is stadium-shaped, the stadium shape having a length and a width, wherein the ratio of the length to the width is between 1.1:1 and 4:1.

[0120] The turbine engine according to any one of the foregoing clauses, wherein the ratio of the length to the width is between 1.5:1 and 3:1.

[0121] According to any one of the preceding clauses, in the turbine engine, the first pin column or first pin subset of the pin group includes a first length and a first width, and the second pin column or second pin subset of the pin group includes a second length and a second width, wherein the first length and the second length are different.

[0122] The turbine engine according to any one of the foregoing clauses, wherein the pin group further includes a third pin column or a third pin subset of the pin group, the third pin column or the third pin subset of the pin group having a third length and a third width.

[0123] The turbine engine according to any one of the foregoing clauses, wherein the first width and the second width are within 5% of the third width.

[0124] The turbine engine according to any one of the foregoing clauses, wherein the ratio of the first length to the first width is between 1.1:1 and 2:1, the ratio of the second length to the second width is greater than 2:1, and the ratio of the third length to the third width is between 1.1:1 and 2:1.

[0125] The turbine engine according to any one of the foregoing clauses, wherein the ratio of the first length to the first width is between 1.1:1 and 2:1, the ratio of the second length to the second width is greater than 2:1, and the ratio of the third length to the third width is equal to 1:1.

[0126] The turbine engine according to any one of the foregoing clauses, wherein the at least one heat shield is at least two heat shields extending from opposite sides of the at least one fuel nozzle.

[0127] The turbine engine according to any one of the foregoing clauses, wherein the at least one heat shield is at least a first heat shield, a second heat shield and a third heat shield, and wherein the at least one fuel nozzle is a first fuel nozzle having a first outlet and a second fuel nozzle having a second outlet, the second outlet being positioned radially adjacent to the first outlet.

[0128] The turbine engine according to any one of the foregoing clauses, wherein the first heat shield or the third heat shield is radially located between the burner liner and the first outlet or the second outlet.

[0129] The turbine engine according to any one of the foregoing clauses, wherein the second heat shield is radially located between the first outlet and the second outlet.

[0130] A turbine engine includes: a compressor section, a combustion section, and a turbine section arranged in a tandem flow configuration, the combustion section including: a combustor liner defining a combustion chamber; at least one fuel nozzle having an outlet fluidly connected to the combustion chamber; and at least one heat shield adjacent to the outlet of the fuel nozzle and extending into the combustion chamber, the at least one heat shield including: an internal airflow passage having an air inlet and an air outlet fluidly connected to the combustion chamber; and a pin assembly located within the airflow passage, a subset of pins having a non-circular cross-section.

[0131] The turbine engine according to any one of the foregoing clauses, wherein the non-circular cross-section of the pin subset is stadium-shaped, the stadium shape having a length and a width, wherein the ratio of the length to the width is between 1.1:1 and 4:1.

[0132] The turbine engine according to any one of the foregoing clauses, wherein the pin set includes at least a first pin subset and a second pin subset, the first pin subset having a first length and a first width, the second pin subset being downstream of the first pin subset having a second length and a second width, wherein the first length is greater than the second length.

[0133] The turbine engine according to any one of the foregoing clauses, wherein the at least one heat shield includes a first surface and a second surface, the first surface and the second surface at least partially defining the airflow passage.

[0134] In any of the preceding clauses, the pins or subsets of pins in the pin group extend from the first surface or the second surface without engaging or connecting the first surface to the second surface.

[0135] In any of the preceding clauses, the pins or subsets of pins in the pin group connect the first surface and the second surface.

[0136] The turbine engine according to any one of the foregoing clauses, wherein a subset of pins from the pin group defines a plurality of openings between the pins.

[0137] The turbine engine according to any one of the foregoing clauses further includes a cavity upstream of the internal airflow passage.

[0138] The turbine engine according to any one of the foregoing clauses, wherein the first length is less than the second length and greater than or equal to the third length.

[0139] The turbine engine according to any one of the foregoing clauses, wherein the pin set includes at least a first pin subset and a second pin subset, the first pin subset having a first length and a first width, the second pin subset being downstream of the first pin subset having a second length and a second width, wherein the first length is greater than the second length.

[0140] The turbine engine according to any one of the foregoing clauses, wherein the pin assembly includes sub-pins overlapping in the axial direction.

Claims

1. A turbine engine, characterized in that, include: A compressor section, a combustion section, and a turbine section are arranged in a series flow configuration, wherein the combustion section includes: A burner liner that defines a combustion chamber; At least one fuel nozzle having a fuel outlet fluidly connected to the combustion chamber; At least one heat shield, located near the fuel outlet of the fuel nozzle and extending into the combustion chamber, the heat shield comprising: An internal airflow passage having an air inlet and an air outlet, the air outlet being fluidly connected to the combustion chamber, and the centerline of the airflow passage extending downstream from the air inlet to the air outlet; and A pin assembly located within the internal airflow channel, having a first pin column defining a first column of center lines forming a first angle relative to the center line of the airflow channel, and a second pin column defining a second column of center lines forming a second angle relative to the center line of the airflow channel, the second column of center lines being spaced downstream of the first column of center lines, the first pin column and the second pin column having different cross-sectional shapes, wherein the first pin column or the second pin column includes an oblong cross-sectional shape; The first pin column includes a first length and a first width, and the second pin column includes a second length and a second width, wherein the pin group further includes a third pin column having a third length and a third width, wherein the first width and the second width are within 5% of the third width.

2. The turbine engine according to claim 1, characterized in that, The airflow path that flows through the pin assembly in the downstream direction and connects the air inlet fluid to the air outlet includes at least a serpentine or curved portion.

3. The turbine engine according to claim 1, characterized in that, The height of the first channel of the air inlet and the height of the second channel of the air outlet have a ratio of the height of the first channel to the height of the second channel equal to 1:1, 3:1, or between 1:1 and 3:

1.

4. The turbine engine according to claim 3, characterized in that, The ratio of the height of the first channel to the height of the second channel is between 1.5:1 and 2:

1.

5. The turbine engine according to claim 1, characterized in that, The cross-section of the first or second pin column includes at least one axis of symmetry.

6. The turbine engine according to any one of claims 1-5, characterized in that, The cross-section of at least one subset of pins in the pin group is stadium-shaped, elliptical, oval, rounded rectangle, teardrop-shaped, or V-shaped.

7. The turbine engine according to claim 6, characterized in that, The at least one subset of pins in the pin group is stadium-shaped, the stadium shape having a length and a width, wherein the ratio of the length to the width is between 1.1:1 and 4:

1.

8. The turbine engine according to claim 7, characterized in that, The ratio of the length to the width is between 1.5:1 and 3:

1.

9. The turbine engine according to any one of claims 1-5, characterized in that, The first length and the second length are different.

10. The turbine engine according to claim 1, characterized in that, The ratio of the first length to the first width is equal to 1.1:1, 2:1, or between 1.1:1 and 2:1; the ratio of the second length to the second width is greater than 2:1; and the ratio of the third length to the third width is equal to 1:1, 2:1, or between 1:1 and 2:

1.

11. The turbine engine according to claim 1, characterized in that, The ratio of the first length to the first width is equal to 1.1:1, 2:1, or between 1.1:1 and 2:1, the ratio of the second length to the second width is greater than 2:1, and the ratio of the third length to the third width is equal to 1:

1.

12. The turbine engine according to any one of claims 1-5, characterized in that, The at least one heat shield is at least two heat shields extending from opposite sides of the at least one fuel nozzle.

13. The turbine engine according to any one of claims 1-5, characterized in that, The at least one heat shield is at least a first heat shield, a second heat shield, and a third heat shield, and the at least one fuel nozzle is a first fuel nozzle having a first outlet and a second fuel nozzle having a second outlet, the second outlet being positioned radially adjacent to the first outlet.

14. The turbine engine according to claim 13, characterized in that, The first heat shield or the third heat shield is located radially between the burner liner and the first outlet or the second outlet.

15. The turbine engine according to claim 14, characterized in that, The second heat shield is located radially between the first outlet and the second outlet.

16. A turbine engine, characterized in that, include: A compressor section, a combustion section, and a turbine section are arranged in a series flow configuration, wherein the combustion section includes: A burner liner that defines a combustion chamber; At least one fuel nozzle, the at least one fuel nozzle having an outlet fluidly connected to the combustion chamber; and At least one heat shield, said heat shield being adjacent to the outlet of said fuel nozzle and extending into said combustion chamber, said heat shield comprising: An internal airflow passage having an air inlet and an air outlet, the air outlet being fluidly connected to the combustion chamber; and A pin group, the pin group being located within the airflow channel, wherein a subset of pins in the pin group has a non-circular cross-section; The pin set includes at least a first pin subset and a second pin subset, the first pin subset having a first length and a first width, the second pin subset being downstream of the first pin subset having a second length and a second width, and the pin set further including a third pin subset having a third length and a third width, wherein the first width and the second width are within 5% of the third width.

17. The turbine engine according to claim 16, characterized in that, The non-circular cross-section of the pin subset is stadium-shaped, having a length and a width, wherein the ratio of the length to the width is between 1.1:1 and 4:

1.

18. The turbine engine according to any one of claims 16-17, characterized in that, The first length is greater than the second length.

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