Burner Dilution with Vortex Generating Turbulators

Abstract

A combustor for a gas turbine engine. The combustor has a combustor liner including a vortex turbulence generator. The vortex turbulence generator has a flow passage extending therethrough and a plurality of vortex generating turbulators disposed on a wall, the flow passage being defined by the wall surrounding the periphery of the flow passage, each of the plurality of vortex generating turbulators including a protrusion extending from a surface of the wall into the flow passage, and generating vortex turbulence of an oxidant from a cold surface side of the combustor liner through the flow passage to a hot surface side of the combustor liner.

Description

Technical Field

[0001] The present disclosure relates to dilution of combustion gases in a combustion chamber of a gas turbine engine. More specifically, the present disclosure relates to dilution vortex turbulence generators in a combustor liner to generate dilution gas turbulence entering the combustor to increase turbulence and mixing with the combustion gases. Background Art

[0002] In conventional gas turbine engines, it is known to provide a dilution air flow into a combustion chamber downstream of a primary combustion zone. Conventionally, an annular combustor may include an inner liner and an outer liner, forming a combustion chamber between them. The inner combustion liner and the outer combustion liner may include dilution holes through the liner, which provide an air flow from a passage around the annular combustor into the combustion chamber. Some applications are known to use circular holes, while other applications are known to use dilution holes of different shapes to provide a dilution air flow to the combustion chamber. Other applications are known to use angled dilution holes aligned axially through the liner. The angled dilution holes are typically aligned in the flow direction from upstream to downstream to provide a dilution air flow to the combustion chamber. Some other applications may include a trumpet-shaped outlet on the inner part of the hole to provide greater dilution air diffusion near the hole outlet. Still other applications may use a raised inlet or bracket around the dilution hole. The bracket is typically aligned perpendicular to the surface of the liner to provide a dilution air flow directly into the combustion chamber. The air flow through the dilution holes in a conventional combustor is typically perpendicular to the surface of the liner and is typically close to the surface of the liner. The conventional dilution air flow close to the surface of the liner helps cool the liner. Summary of the invention

[0003] In order to solve the problems in the conventional technology, the inventors have designed a technology for inducing turbulence in the air flow passing through the dilution holes. According to one aspect, the present disclosure relates to a combustor for a gas turbine engine. The combustor has: a combustor liner having a cold surface side and a hot surface side; a combustion chamber arranged on the hot surface side of the combustor liner; and a vortex turbulence generator arranged on the combustor liner. The vortex turbulence generator includes a turbulence generator flow channel extending from the cold surface side of the combustor liner through the combustor liner to the hot surface side of the combustor liner. The turbulence generator flow channel is defined by a turbulence generator wall surrounding the periphery of the turbulence generator flow channel, and a plurality of vortex generating turbulents are arranged on the turbulence generator wall. Each of the plurality of vortex generating turbulents includes a protruding portion extending from the surface of the turbulence generator wall into the turbulence generator flow channel, and generates vortex turbulence of an oxidant from the cold surface side of the combustor liner through the turbulence generator flow channel to the hot surface side of the combustor liner.

[0004] Another aspect of the present disclosure relates to a dilution vortex turbulence generator for a combustor of a gas turbine engine. The dilution vortex turbulence generator may be in the form of an insert to be installed in a combustor liner, for example. Thus, the dilution vortex turbulence generator may include: a substrate having a cold surface side and a hot surface side; a turbulence generator flow channel extending from the cold surface side through the substrate to the hot surface side, wherein the turbulence generator flow channel is defined by a turbulence generator wall surrounding the periphery of the turbulence generator flow channel. A plurality of vortex generating turbulators are disposed on the turbulence generator wall, each of the plurality of vortex generating turbulators including a protruding portion extending from a surface of the turbulence generator wall into the turbulence generator flow channel, and generating vortex turbulence of an oxidant from the cold surface side of the substrate through the turbulence generator flow channel to the hot surface side of the substrate.

[0005] Additional features, advantages and embodiments of the present disclosure are set forth or apparent by consideration of the following detailed description, drawings and claims. In addition, it should be understood that the foregoing summary and the following detailed description are exemplary and intended to provide further explanation without limiting the scope of the present disclosure as claimed. BRIEF DESCRIPTION OF THE DRAWINGS

[0006] The foregoing and other features and advantages will become apparent from the following more particular description of various exemplary embodiments as illustrated in the accompanying drawings, in which like reference numerals generally indicate identical, functionally similar, and / or structurally similar elements.

[0007] Figure 1 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine according to an embodiment of the present disclosure.

[0008] Figure 2 is a cross-sectional side view of an exemplary combustion section according to an embodiment of the present disclosure.

[0009] Figure 3 is a cross-sectional view of a vortex turbulence generator according to an embodiment of the present disclosure.

[0010] Figure 4 is a perspective cross-sectional view of a vortex turbulence generator according to an embodiment of the present disclosure.

[0011] Figure 5A Example embodiments of turbulators according to embodiments of the present disclosure are depicted.

[0012] Figure 5B Example embodiments of turbulators according to embodiments of the present disclosure are depicted.

[0013] Figure 5C Example embodiments of turbulators according to embodiments of the present disclosure are depicted.

[0014] Figure 5D Example embodiments of turbulators according to embodiments of the present disclosure are depicted.

[0015] Figure 6 is a plan view of another example vortex turbulence generator according to an embodiment of the present disclosure.

[0016] Figure 7 is a cross-sectional view of another vortex turbulence generator according to an embodiment of the present disclosure.

[0017] Figure 8 is a perspective cross-sectional view of another vortex turbulence generator according to an embodiment of the present disclosure.

[0018] Fig. 9 is an example of an extended horn for a vortex turbulence generator according to an embodiment of the present disclosure.

[0019] Fig.10 is an example of an offset vortex turbulence generator according to the present disclosure. DETAILED DESCRIPTION

[0020] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0021] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0022] The terms "upstream" and "downstream" refer to relative directions relative to the flow of a fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing.

[0023] Some conventional dilution holes are simple holes through the liner that provide an air flow perpendicular to the surface of the liner. One purpose of the dilution air flow is to cool the combustion gases before they enter the turbine section. Another purpose of the dilution air flow is to provide surface cooling of the liner. However, conventional dilution holes do not provide turbulence from the dilution holes into the combustion chamber, which results in poor mixing with the combustion gases. In addition, the non-turbulent air leaving the conventional dilution holes stagnates at the trailing edge of the dilution holes, which increases the temperature of the combustor liner in the stagnant zone. Therefore, there is a need to provide better mixing and reduce the stagnant zone caused by conventional dilution holes. Therefore, the inventors have found that it is necessary to induce turbulence in the dilution air flow through the dilution holes in order to provide better mixing of the dilution air and the combustion gases and reduce the stagnant zone.

[0024] The present disclosure generally relates to providing a dilution air flow into a dilution zone of a combustor. When the dilution air flow enters the combustion chamber via the dilution holes, it mixes with the hot combustion gases flowing through the combustion chamber at the liner surface. One purpose of the dilution air flow is to cool the combustion gases before they enter the turbine section. Another purpose of the dilution air flow is to provide surface cooling of the liner. However, when the air flow is perpendicular to the surface and is generally not turbulent, the air flow remains close to the surface of the liner. As a result, high temperature gases accumulate on the downstream edge and surface of the hole, thereby reducing the reliability of the liner. In addition, if the dilution air flow remains close to the liner surface, it cannot provide effective mixing and cooling of the combustion gases away from the liner surface. Therefore, a method for reducing NOx emissions in the dilution zone is needed. By providing better mixing of the dilution air flow with the combustion gases, NOx emissions in the dilution zone can be reduced, and higher reliability of the combustor liner around the dilution holes can be achieved.

[0025] According to the present disclosure, a vortex turbulence generator is formed at a dilution hole in a dilution zone of a combustor. Air flowing in an outer chamber on the cold side of a combustor liner flows through a vortex turbulence generator into the combustion chamber to provide mixing with the combustion gas and provide cooling of the liner surface. The vortex turbulence generator according to the present disclosure includes a flow channel in the form of a hole in the liner, wherein the wall of the hole is lined with a turbulator. The turbulator is a protrusion extending from the wall into the hole and is shaped to generate a vortex in the air flow passing through the turbulator. The turbulator can be in the form of a conical protrusion extending from the wall, wherein the base of the cone is attached to the wall. When air flows over the surface of the turbulator, a vortex is generated in the air flow. The turbulator can also be arranged on the wall, which also generates a vortex air flow around the hole. For example, the turbulator can be placed along the wall in a spiral manner so that when the air flows through the hole, a vortex around the circumference of the hole can also be generated. In some embodiments, the central portion of the hole is usually open to allow some air to flow freely through the open portion without flowing through the turbulator. This has the effect of forming a main jet of relatively non-turbulent air flow through the middle of the hole surrounded by the turbulent vortices generated by the turbulators. In other embodiments, a main jet structure may be included in the center of the hole to separate the air flow in the hole into a generally non-turbulent jet air flow through the ejector and vortex turbulence around the ejector in the turbulator portion of the hole. The flow from the ejector then mixes with the turbulent air flow in the combustion chamber.

[0026] Due to the turbulent air flow surrounding the main jet air flow, deeper penetration of the dilution air into the combustion chamber can be achieved. In addition, when the turbulent air flow leaves the hole, the turbulent air flow provides for the dilution air to be present in the wake of the bulk flow on the downstream side of the hole. This provides a cooler temperature on the liner surface at the downstream portion of the hole, thereby improving the reliability of the liner.

[0027] Now referring to the accompanying drawings, Figure 11 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine 10 (referred to herein as "engine 10") that may incorporate various embodiments of the present disclosure. Although further described below with reference to a turbofan engine, the present disclosure is also applicable to turbomachinery in general, including turbojets, turbopropellers, and turboshaft gas turbine engines, including marine and industrial turbine engines and auxiliary power units. Figure 1 As shown, the engine 10 has a longitudinal or axial centerline axis 12 extending therethrough from an upstream end 98 to a downstream end 99 for reference. Generally, the engine 10 may include a fan assembly 14 and a core engine 16 disposed downstream of the fan assembly 14.

[0028] The core engine 16 may generally include a substantially tubular casing 18 defining an annular inlet 20. The casing 18 surrounds or at least partially forms, in serial flow relationship: a compressor section having a boost or low pressure (LP) compressor 22, a high pressure (HP) compressor 24; a combustion section 26; a turbine section including a high pressure (HP) turbine 28, a low pressure (LP) turbine 30; and an ejection exhaust nozzle section 32. A high pressure (HP) rotor shaft 34 drivingly connects the HP turbine 28 to the HP compressor 24. A low pressure (LP) rotor shaft 36 drivingly connects the LP turbine 30 to the LP compressor 22. The LP rotor shaft 36 may also be connected to a fan shaft 38 of the fan assembly 14. In certain embodiments, as shown in FIG. Figure 1 As shown, LP rotor shaft 36 may be connected to fan shaft 38 via reduction gear 40, for example in an indirect drive or gear drive configuration. In other embodiments, although not shown, engine 10 may also include an intermediate pressure (IP) compressor and a turbine rotatable with the IP shaft.

[0029] like Figure 1 As shown, fan assembly 14 includes a plurality of fan blades 42 coupled to and extending radially outward from fan shaft 38. An annular fan casing or nacelle 44 circumferentially surrounds fan assembly 14 and / or at least a portion of core engine 16. In one embodiment, nacelle 44 may be supported relative to core engine 16 by a plurality of circumferentially spaced outlet guide vanes or struts 46. In addition, at least a portion of nacelle 44 may extend over an outer portion of core engine 16 to define a bypass airflow passage 48 therebetween.

[0030] Figure 2 Yes Figure 1 A cross-sectional side view of an exemplary combustion section 26 of the core engine 16 is shown. Figure 2As shown, the combustion section 26 may generally include an annular combustor assembly 50 having an annular inner liner 52, an annular outer liner 54, and a baffle wall 56 that together define a combustion chamber 62. The combustion chamber 62 may more specifically define an area that defines a primary combustion zone 62(a) where an initial chemical reaction of a fuel-oxidant mixture 72 and / or recirculation of combustion gases 86 may occur prior to flowing further downstream to a dilution zone 62(b) where mixing and / or recirculation of combustion products and air may occur prior to flowing to the HP turbine 28 and the LP turbine 30. The baffle wall 56 and the dome assembly 57 each extend radially between upstream ends 58, 60 of the radially spaced inner and outer liners 52, 54, respectively. The dome assembly 57 is disposed downstream of the baffle wall 56 adjacent the generally annular combustion chamber 62 defined between the dome assembly 57, the inner liner 52, and the outer liner 54. In particular embodiments, the inner liner 52 and / or the outer liner 54 may be formed at least partially or entirely from a metal alloy or a ceramic matrix composite (CMC) material.

[0031] like Figure 2 As shown, the inner liner 52 and the outer liner 54 may be enclosed within a diffuser or outer shell 64. An outer flow channel 66 may be defined around the inner liner 52 and / or the outer liner 54. The inner liner 52 and the outer liner 54 may extend from the baffle wall 56 toward the turbine nozzle or inlet 68 to the HP turbine 28 ( Figure 1 ), thereby at least partially defining a hot gas path between the combustor assembly 50 and the HP turbine 28. The outer surface of the liner 52 adjacent to the outer flow channel 66 may be referred to as the cold surface side 52(a), and the outer surface of the outer liner 54 adjacent to the outer flow channel 66 may be referred to as the cold surface side 54(a). The inner surface of the liner 52 adjacent to the hot gas path may be referred to as the hot surface side 52(b), and the inner surface of the outer liner 54 adjacent to the hot gas path may be referred to as the hot surface side 54(b).

[0032] like Figure 2 As further shown, each of the inner liner 52 and the outer liner 54 of the combustor assembly 50 may include a plurality of dilution vortex turbulence generators 90. As will be described in greater detail below, the dilution vortex turbulence generators 90 provide a flow of compressed air 82(c) therethrough and into the combustion chamber 62. Thus, the flow of compressed air 82(c) may be used to cool a portion of the inner liner 52 and the outer liner 54, as well as to cool the combustion gases 86 downstream of the primary combustion zone 62(a) so as to cool the flow of combustion gases 86 entering the turbine section.

[0033] During operation of the engine 10, as Figure 1 and Figure 2As shown collectively, a quantity of air, schematically indicated by arrows 74, enters engine 10 from upstream end 98 through nacelle 44 and / or associated inlet 76 of fan assembly 14. As air 74 passes through fan blades 42, a portion of the air, schematically indicated by arrows 78, is directed or directed into bypass airflow passage 48, while another portion of the air, schematically indicated by arrows 80, is directed or directed into low pressure compressor 22. Air 80 is progressively compressed as it flows through LP compressor 22 and HP compressor 24 toward combustion section 26. Figure 2 As shown, the compressed air now flows through the compressor exit guide vanes (CEGV) 67 as schematically indicated by arrows 82 and enters the diffuser cavity 84 of the combustion section 26 through the prediffuser 65 .

[0034] The compressed air 82 pressurizes the diffuser cavity 84. A first portion of the compressed air 82, as schematically indicated by arrow 82(a), flows from the diffuser cavity 84 into the combustion chamber 62 where it mixes with the fuel injected from the fuel nozzle 70 to form the fuel / air mixture 72 that is combusted, thereby generating combustion gases 86, as schematically indicated by arrow 86, within the primary combustion zone 62(a) of the combustor assembly 50. Typically, the LP compressor 22 and the HP compressor 24 provide more compressed air to the diffuser cavity 84 than is required for combustion. Thus, a second portion of the compressed air 82, as schematically indicated by arrow 82(b), may be used for various purposes other than combustion. For example, Figure 2 As shown, the compressed air 82(b) may be directed into the outer flow passage 66 to provide cooling to the inner liner 52 and the outer liner 54. A portion of the compressed air 82(b) may be directed through a dilution vortex turbulence generator 90 (schematically shown as compressed air 82(c)) and into the dilution zone 62(b) of the combustion chamber 62 to provide cooling to the inner liner 52 and the outer liner 54. The compressed air 82(c) may also provide cooling to the combustion gases 86 in the dilution zone 62(b) and may also provide turbulence to the flow of the combustion gases 86 to provide better mixing of the diluent oxidant gas (compressed air 82(c)) with the combustion gases 86. Additionally, or in the alternative, at least a portion of the compressed air 82(b) may be directed out of the diffuser cavity 84. For example, a portion of the compressed air 82(b) may be directed through various flow passages to provide cooling air to at least one of the HP turbine 28 or the LP turbine 30.

[0035] Return to common reference Figure 1 and Figure 2 The combustion gases 86 generated in the combustion chamber 62 flow from the combustor assembly 50 into the HP turbine 28, thereby causing the HP rotor shaft 34 to rotate, thereby supporting the operation of the HP compressor 24. Figure 1As shown, combustion gases 86 are then directed through LP turbine 30, thereby causing LP rotor shaft 36 to rotate, thereby supporting operation of LP compressor 22 and / or rotation of fan shaft 38. Combustion gases 86 are then exhausted through jet exhaust nozzle section 32 of core engine 16 to provide propulsion at downstream end 99.

[0036] Figure 3 is Figure 2 An enlarged view of a section of outer liner 54 as seen at detail 3-3. Figure 3 , a cross-section of a dilution vortex turbulence generator according to one embodiment of the present disclosure is depicted. Figure 3 The dilution vortex turbulence generator may be formed as an insert to be installed in the inner liner 52 or the outer liner 54. Alternatively, the dilution vortex turbulence generator may be formed integrally with the inner liner 52 and the outer liner 54. Figure 3 An example of a dilution vortex turbulence generator as an insert is depicted, while Figure 4 Dilution vortex turbulence generators are depicted which may be integral to the inner liner 52 or the outer liner 54. Figure 3 , it can be seen that the dilution vortex turbulence generator element 100 includes a substrate 106. The shape of the substrate 106 can be generally cylindrical so as to fit into a corresponding hole of the inner liner 52 or the outer liner 54. The substrate 106 includes a cold surface side 54 (a) and a hot surface side 54 (b). When installed in the outer liner 54, the cold surface side 54 (a) is adjacent to the outer flow channel 66, and the hot surface side 54 (b) is adjacent to the combustion chamber 62. Formed by the substrate 106 is an oxidant flow channel 108, which allows the compressed air 82 (c) flow of the oxidant to enter the combustion chamber 62 from the outer flow channel 66. The flow channel 108 includes a wall 102. The wall 102 can be cylindrical over the entire length of the flow channel 108 from the cold surface side 54 (a) of the substrate 106 to the hot surface side 54 (b) of the substrate 106. Alternatively, a portion of the wall 102 may be cylindrical along a portion of the axial length of the flow channel 108, while another portion (102a) of the wall 102 may be conical. In another embodiment, the entire flow channel 108 may be conical. In either case, the large diameter D1 of the conical surface 102a of the flow channel 108 is disposed toward the cold surface side 54(a) of the substrate 106, while the small diameter D2 of the conical surface 102a is disposed toward the hot surface side 54(b) of the substrate 106.

[0037] Reference again Figure 3 and Figure 4, it can be seen that a plurality of vortex generating turbulators 104 are attached to the wall 102 and include a protruding portion 104a extending from the wall 102 into an opening portion of the flow channel 108. Each vortex generating turbulator is formed with an aerodynamic shape so that when the oxidant (air) flow crosses the turbulator, vortices are generated in the flow by the turbulator. As shown, multiple rows of turbulators 104 may be arranged around the wall 102, wherein a first row of turbulators 104 may be located closer to the cold surface side 54(a) and a second row of turbulators 104 may be located closer to the hot surface side 54(b). Where multiple rows of turbulators 104 are provided, the turbulators 104 in one row may be staggered in rotation around the wall 102 about a centerline axis 168 of the flow channel 108, such as in Figure 4 108. The turbulators 104 are shown in two staggered rows. Alternatively, a single row of turbulators 104 may be included instead, or more than two rows of turbulators 104 may be included. In addition, an arrangement may be implemented in which the turbulators 104 extend in a spiral pattern along the wall from the cold surface side 54(a) to the hot surface side 54(b). One purpose of the turbulators 104 is to generate eddy turbulence of the oxidant (air) flowing through the flow channel 108. More specifically, the turbulators 104 are arranged so that a vortex or turbulence is generated at the outlet where the oxidant flow leaves the flow channel 108 and enters the hot surface side 54(b) of the combustion chamber 62.

[0038] exist Figure 3 and 4 104, it can be seen that the turbulator 104 is generally conical or pyramidal in shape, with a base portion 170 of the conical / pyramidal turbulator connected to the wall 102 and an apex portion 172 of the conical / pyramidal turbulator extending into the open portion of the flow channel 108. One surface 110 of the conical / pyramidal shape is arranged to be directly exposed to the air flow through the flow channel 108. For example, Figure 3 As shown, the turbulator 104 can be a part of a cone, wherein the outer conical surface 110 faces the cold surface side to receive the incoming air flow. When the air flow passes through the surface of the conical shape, vortices are generated in the air flow by the turbulator 104. For the description herein, the surface 110 (and the corresponding other surfaces described below) will generally be considered as the primary flow interface surface. That is, the surface 110 will be considered as the main aerodynamic surface of the turbulator, which generally provides interaction with the incoming oxidant flow through the flow channel 108.

[0039] Reference now Figures 5A to 5D , which depicts some arrangements of turbulators 104 that may be implemented in various embodiments of the present disclosure. Figures 5A to 5D Each turbulator 104 shown in FIG. 1 may be similar to Figure 3 and 4 The turbulators shown in FIG. 1 are arranged on the wall 102 . Figure 5AA generally pyramidal turbulator 104 is depicted including a primary flow interfacing surface that is a generally triangular surface 112. Figure 5B In FIG. 1 , turbulator 104 is also generally pyramidal in shape and includes Figure 5A The triangular surface 112 is similar to the primary flow interfacing surface 114, but has rounded edges on the sides extending from the wall 102 into the opening portion of the flow passage 108. Figure 5C In the example, surface 116 is similar to Figure 5A The triangular surface 112 is divided into two triangles, forming a cavity 118 therebetween. Figure 5D Similar to Figure 5C , but includes three triangular cross-sections of surface 120.

[0040] Regardless of the shape of the turbulator 104 implemented, it will be appreciated that the attachment of the turbulator to the wall 102 may be adjusted based on the shape employed in order to provide a desired aerodynamic flow across the surface. Figure 4 As shown, the conical turbulator 104 can be mounted on the wall so that the conical surface 110 is generally perpendicular to the incoming flow. However, the turbulator 104 can be rotated about the conical axis so that the conical surface 110 is at a desired angle relative to the incoming flow. Such an angle can be used to generate vortex turbulence leaving the conical surface 110, as well as to direct a portion of the incoming air flow to deflect away from the conical surface 110 in a tangential direction around the circumference of the wall 102. Therefore, this can provide an overall vortex within the flow channel 108.

[0041] exist Figure 3 and Figure 4 108 can be opened to allow free air flow therethrough. That is, the length of the turbulators 104 can be such that they do not extend from the wall 102 through the centerline axis of the flow channel 108, thereby allowing an unobstructed hole between the tips of the turbulators 104, as seen in the plan view (not shown) from the cold surface side 54 (a). Thus, this arrangement allows a substantially non-turbulent main jet of the airflow to pass through the open portion, while the turbulators 104 generate turbulent vortices around the central main jet. When leaving the vortex turbulence generator on the hot surface side, the main jet will have a higher speed than the slower turbulent flow. The main jet can then penetrate deeper into the combustion chamber, while the surrounding turbulence can provide dilution air around the outlet, particularly in the downstream wake portion of the flow (described in more detail below).

[0042] Figures 6 to 8 Another embodiment of a dilution vortex turbulence generator according to the present disclosure is depicted. For example, Figure 6 is a plan view of the dilution vortex turbulence generator taken from the cold surface side 54 ( a ) of the outer liner 54 . Figure 7 is along Figure 6 A cross-sectional view taken along plane 7-7 is shown, and Figure 8 is a stereogram of a cross section taken along plane 7-7. Figures 6 to 8 In this embodiment, the dilution vortex turbulence generator includes a similar Figure 3 and Figure 4 The eddy turbulence generating part 139 also includes a dilution flow main ejector 130 disposed therein. Figures 6 to 8 As shown, this embodiment includes a wall 102 and a Figure 3 and Figure 4 104, thereby forming a turbulence generating portion. Figure 3 and Figure 4 In comparison, we can see Figure 7 The wall 102 in FIG. 1 is a cone extending from the cold surface side 54(a) to the hot surface side 54(b). The large diameter portion 180 of the conical wall is located on the cold surface side 54(a), and the small diameter portion 182 of the conical wall is located on the hot surface side 54(b). Thus, the wall 102 forms a converging air flow therethrough. Attached to the wall 102 is a turbulator 104, which may include any of the turbulator embodiments previously described. In addition, similar to Figure 3 and Figure 4 , Figures 6 to 8 The present embodiment shown includes two rows of turbulators around the wall 102. Thus, the aforementioned wall and turbulators define the turbulence generating portion of the present embodiment.

[0043] In the present embodiment, the dilution flow main ejector 130 is included within the turbulence generating portion 139. The main ejector 130 extends from the cold surface side 54(a) of the liner to the hot surface side 54(b) of the liner. The main ejector 130 is depicted in the figures as a generally conical wall 102 and is shown as being located approximately centrally relative to the wall 102 in the opening portion of the flow channel with a gap 144 between the main ejector 130 and the wall 102. However, the main ejector 130 need not be conical and other arrangements may be implemented instead. In addition, the main ejector 130 need not be centrally located relative to the wall 102, but may be offset. For the conical main ejector depicted in these figures, the large diameter portion 184 can be seen adjacent to the cold surface side 54(a) of the liner, while the small diameter portion 186 can be seen adjacent to the hot surface side 54(b) of the liner.

[0044] It can be seen that the main ejector 130 has a main ejector flow channel 132 therethrough. The main ejector flow channel 132 provides an oxidant flow through the main ejector from the cold surface side of the liner to the hot surface side. It can be seen that the main ejector is formed by a conical ejector wall 134 having an inner surface 136 and an outer surface 138 that define the main ejector flow channel 132. The inner surface 136 can be relatively smooth so as to provide a relatively non-turbulent flow of the oxidant entering the combustion chamber 62 through the main ejector flow channel 132. Alternatively, the inner surface 136 can also include turbulators. The outer surface 138 can also be smooth, or, as shown, can include turbulators 142 attached thereto and extending into a gap 144 between the outer surface 138 and the wall 102. The turbulators 142 can be the same type as the turbulators 104 on the wall 102, or they can be different types.

[0045] It can be seen that the main ejector 130 is supported by ribs 140. Figures 6 to 8 In FIG. 1 , the main ejector 130 is shown to be supported by four ribs 140, but more than four ribs or less than four ribs may be implemented to support the main ejector 130. In addition, Figures 6 to 8 The ribs 140 are depicted on the cold surface side 54(a) of the primary ejector 130, and the ribs 140 are not depicted on the hot surface side of the primary ejector 130. However, it is understood that the ribs 140 may also be provided on the hot surface side of the primary ejector, or may be provided at any location between the cold surface side and the hot surface side, connecting the outer surface 138 to the wall 102. In addition, although not shown in the figure, the ribs 140 may also include turbulators 104 attached thereto.

[0046] Figures 6 to 8 The dilution vortex turbulence generator depicted in FIG. 1 generally provides an oxidant flow from the cold surface side 52 (a) of the liner 52 to the hot surface side 52 (b) of the liner 52, or from the cold surface side 54 (a) to the hot surface side 54 (b) of the outer liner 54, through the main injector 130 and the turbulence generating portion 139 surrounding the main injector 130. Therefore, as Figure 7 As shown, a relatively smooth main jet 150 of oxidant is provided to the combustion chamber 62 by the main injector 130, while a turbulent flow 152 of oxidant is provided to the combustion chamber via the turbulence generator portion. At the outlet of the vortex turbulence generator in the combustion chamber (i.e., at the hot surface side 54 (b)), the main jet 150 and the turbulent flow 152 mix with each other. As will be described later, this arrangement reduces hot combustion gases on the downstream portion of the outlet on the liner, thereby reducing NOx emissions and providing better liner durability.

[0047] Fig. 9 Another embodiment of a vortex turbulence generator according to the present disclosure is depicted. Fig. 9In the embodiment, the extension trumpet 154 is disposed on the cold surface side 54(a) of the combustor liner. The extension trumpet 154 extends from the cold surface side 54(a) to the outer flow channel 66( Figure 2 ). The extended horn 154 includes a proximal end 156 and a distal end 158 at the cold surface side 54 (a). Similar to Figure 3 and 4 , vortex turbulence generators are disposed in the extension horn 154 and may extend from the distal end 158 through the flow passage 108 to the hot surface side 54(b). Thus, the vortex generating turbulators 104 are disposed about the inner flow passage 108 through the length of the extension horn 154. The vortex generating turbulators 104 may be arranged about the circumference in a spiral pattern along the length of the flow passage 108, thereby generating a vortex (generally depicted as 159) that exits the flow passage 108 and enters the combustion chamber 62.

[0048] exist Fig.10 In another embodiment according to the present disclosure, similar to Figures 6 to 8 The turbulence generator / primary ejector configuration shown in can be implemented in a non-concentric manner. Fig.10 The example plane diagram is generally depicted, where the turbulence generating part is not as Figures 6 to 8 , but may generally have a teardrop shape. That is, a first portion 160 of the wall 102 forming the flow channel 108 may be substantially concentric with the primary ejector 130. A second portion 162 forming the wall 102 may not be concentric with the primary ejector 130 and may be a larger size (e.g., diameter) than the first portion 160. In this arrangement, the first portion 160 and the primary ejector 130 are positioned toward the upstream end 98 of the vortex generator, while the second portion 162 may be positioned toward the downstream end 99 of the vortex generator. It can be seen that the wall 102 forming the second portion 162 includes a turbulator 104, while the first portion 160 may not include a turbulator 104. Therefore, the second portion 162 of the turbulator may generate turbulence of the oxidant on the downstream side of the outlet entering the combustion chamber, while the primary ejector 130 provides a smooth flow (non-turbulent flow) of the oxidant upstream of the turbulence. This arrangement helps to provide better turbulence at the downstream end of the flow, thereby reducing the temperature on the downstream side of the vortex generator.

[0049] In a comparison of the present disclosure with conventional dilution holes, in conventional dilution holes, the combustion gases flow downstream and the dilution air reaches the combustion chamber through the dilution holes. A higher temperature of the gas exists at the mixing location behind the hole, where the dilution air mixes with the combustion gases, leaving the dilution hole. The higher temperature in the conventional dilution hole is due to the lack of turbulent mixing of the combustion gases and the dilution air. In addition, the conventional dilution hole has a small wake region at the downstream edge of the dilution hole. The small wake results in a higher concentration of hot gases at the downstream edge. As a result, the higher temperature at the gas wall is concentrated at the downstream edge of the dilution hole, thereby reducing the life of the liner.

[0050] In contrast, for the vortex turbulence generator of the present disclosure, as the turbulent air mixes with the hot combustion gases, the gas temperature at the mixing location behind the hole is lower, thereby reducing NOx emissions. In addition, the dilution air is present in the wake of the dilution flow, which reduces the temperature at the edge of the dilution hole on the downstream side and diffuses the hot gas further downstream. The lower temperature and diffusion of the dilution air provide better liner reliability.

[0051] As a further comparison between conventional dilution holes and the vortex turbulence generators of the present disclosure, the vortex turbulence generators of the present disclosure provide a lower velocity flow on the downstream side of the dilution air than the higher velocity flow in the conventional dilution holes. The lower velocity represents turbulent flow from the vortex turbulence generators into the combustion chamber.

[0052] As a further comparison of turbulent kinetic energy (TKE) in a combustion chamber, in a conventional dilution hole, turbulence is typically concentrated near the dilution hole as the jet leaves the hole. In contrast, in the vortex turbulence generator of the present disclosure, turbulence is diffused further downstream, resulting in better mixing with the combustion gases and lower NOx emissions.

[0053] The present disclosure also provides a method for providing a dilution flow of an oxidant in a combustor of a gas turbine engine. According to the present disclosure, an oxidant flow is provided on the cold surface side of a combustor liner. The oxidant flow from the cold surface side of the combustor liner is provided to a vortex turbulence generator within the combustor liner. The vortex turbulence generator generates vortex turbulence of the oxidant, and outputs the generated vortex turbulence to a combustion chamber on the hot surface side of the combustor liner. Generating turbulence in the vortex turbulence generator involves passing the oxidant flow through the vortex generating surface of the vortex turbulent generator, the vortex turbulent generator is disposed on the flow channel wall, the flow channel wall extends through the vortex turbulence generator and defines an oxidant flow channel therethrough. The vortex turbulent extends from the flow channel wall into the opening portion of the flow channel, and the vortex generating surface of the vortex turbulent generator generates a vortex of the oxidant passing through the surface of the vortex turbulent generator within the vortex turbulence generator. The vortex turbulence generator may have a plurality of vortex turbulators disposed on the flow channel wall, and the plurality of vortex turbulators further generate vortices of the oxidant around the flow channel within the vortex turbulence generator. Further, the vortex turbulence generator is arranged to provide a non-turbulent oxidant flow jet from the cold surface side of the combustor liner to the hot surface side of the combustor liner through a central portion of the vortex turbulence generator, and the non-turbulent oxidant flow jet is output into the combustion chamber together with the vortex turbulence of the oxidant, and the vortex turbulence is output around the non-turbulent oxidant flow jet.

[0054] Although the foregoing description generally relates to gas turbine engines, it can be readily appreciated that gas turbine engines can be implemented in a variety of environments. For example, the engine can be implemented in an aircraft, but can also be implemented in non-aircraft applications such as power plants, marine applications, or oil and gas production applications. Therefore, the present disclosure is not limited to use in aircraft.

[0055] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0056] A combustor for a gas turbine, comprising: a combustor liner, the combustor liner having a cold surface side and a hot surface side; a combustion chamber, the combustion chamber being arranged on the hot surface side of the combustor liner; a vortex turbulence generator, the vortex turbulence generator being arranged on the combustor liner, the vortex turbulence generator comprising: a turbulence generator flow channel, the turbulence generator flow channel extending from the cold surface side of the combustor liner through the combustor liner to the hot surface side of the combustor liner, the turbulence generator flow channel extending from the cold surface side of the combustor liner through the combustor liner to the hot surface side of the combustor liner A turbulence generator flow channel is defined by a turbulence generator wall surrounding the periphery of the turbulence generator flow channel; and a plurality of vortex generating turbulators, the plurality of vortex generating turbulators are arranged on the turbulence generator wall, each of the plurality of vortex generating turbulators includes a protrusion extending from the surface of the turbulence generator wall into the turbulence generator flow channel, and generates vortex turbulence of the oxidant from the cold surface side of the combustor liner through the turbulence generator flow channel to the hot surface side of the combustor liner.

[0057] A combustor according to any preceding clause, wherein at least a portion of the turbulence generator wall is a conical surface, the major diameter of the conical surface being disposed toward the cold surface side of the combustor liner and the minor diameter of the conical surface being disposed toward the hot surface side of the combustor liner.

[0058] A combustor according to any preceding clause, wherein the plurality of vortex generating turbulators comprises a plurality of rows of vortex generating turbulators arranged on the turbulator wall, a first row of the plurality of rows of vortex generating turbulators being arranged adjacent to the cold surface side of the combustor liner, and a second row of the plurality of rows of vortex generating turbulators being arranged adjacent to the hot surface side of the combustor liner.

[0059] A combustor as in any preceding clause, wherein the vortex generating turbulators in the first row are rotationally staggered on the turbulator wall relative to the vortex generating turbulators in the second row about a central axis of the turbulator flow passage.

[0060] A combustor as claimed in any preceding clause, wherein each of the vortex generating turbulators is a conical element having a base portion disposed on the turbulator wall and an apex portion extending into the turbulator flow channel.

[0061] A combustor according to any preceding clause, wherein the vortex turbulence generator further includes an extension horn having a proximal end at the cold surface side of the combustor liner and a distal end extending from the cold surface side of the combustor liner, wherein the turbulence generator flow channel further extends from the proximal end through the extension horn to the distal end.

[0062] A combustor according to any of the preceding clauses, wherein the vortex turbulence generator further includes a main injector, the main injector including an injector wall, the injector wall having a main injector flow channel passing therethrough, the injector wall having an injector wall inner surface and an injector wall outer surface defining the main injector flow channel, wherein the main injector extends from the cold surface side of the combustor liner to the hot surface side of the combustor liner, and wherein the main injector is arranged in the turbulence generator flow channel with a gap between the turbulence generator wall and the injector wall outer surface.

[0063] A combustor according to any preceding clause, further comprising a plurality of vortex generating turbulators disposed on the injector wall outer surface and extending into the gap.

[0064] A combustor according to any preceding clause, wherein the turbulence generator wall, the ejector wall inner surface and the ejector wall outer surface each include conical surfaces arranged radially with respect to each other, the large diameter portion of each conical surface being disposed on the cold surface side of the combustor liner, and the small diameter portion of each conical surface being disposed on the hot surface side of the combustor liner.

[0065] A combustor according to any preceding clause, wherein the primary injector provides a non-turbulent flow of the oxidant into the combustion chamber, and wherein the turbulence generator provides a turbulent vortex of the oxidant into the combustion chamber, the turbulent vortex surrounding the non-turbulent flow at the hot surface side of the combustor liner.

[0066] A burner according to any preceding clause, wherein the turbulence generator wall comprises a first portion which is concentric with the main injector and a second portion which is not concentric with the main injector, wherein the first portion is on the upstream side of the vortex turbulence generator and the second portion is on the downstream side of the vortex turbulence generator and has a larger radius than the first portion.

[0067] A combustor as in any preceding clause, wherein the plurality of turbulators provided on the wall of the turbulator are provided on the second portion and not on the first portion.

[0068] A combustor according to any preceding clause, further comprising a plurality of vortex generating turbulators disposed on an inner surface of the ejector wall.

[0069] Further aspects of the disclosure are provided by the subject matter of the following further clauses.

[0070] A dilution vortex turbulence generator for a combustor of a gas turbine, the generator comprising: a substrate having a cold surface side and a hot surface side; a turbulence generator flow channel, the turbulence generator flow channel extending from the cold surface side through the substrate to the hot surface side, the turbulence generator flow channel being defined by a turbulence generator wall surrounding the periphery of the turbulence generator flow channel; and a plurality of vortex generating turbulents, the plurality of vortex generating turbulents being arranged on the turbulence generator wall, each of the plurality of vortex generating turbulents comprising a protrusion extending from a surface of the turbulence generator wall into the turbulence generator flow channel, and generating vortex turbulence of an oxidant from the cold surface side of the substrate through the turbulence generator flow channel to the hot surface side of the substrate.

[0071] A dilution vortex turbulence generator according to any preceding clause, wherein at least a portion of the turbulence generator wall is a conical surface, the major diameter of the conical surface is arranged towards the cold surface side of the substrate, and the minor diameter of the conical surface is arranged towards the hot surface side of the substrate.

[0072] A dilution vortex turbulence generator according to any preceding clause, wherein the plurality of vortex generating turbulators comprises a plurality of rows of the vortex generating turbulators arranged on the turbulator wall, a first row of the plurality of rows being arranged adjacent to the cold surface side of the substrate, and a second row of the plurality of rows being arranged adjacent to the hot surface side of the substrate.

[0073] A dilution vortex turbulence generator as claimed in any preceding clause, wherein the vortex generating turbulators in the first row are rotationally staggered on the turbulence generator wall about a central axis of the turbulence generator flow channel relative to the vortex generating turbulators in the second row.

[0074] A dilution vortex turbulence generator according to any preceding clause, wherein each of the vortex generating turbulators is a conical element having a base portion disposed on the turbulator wall and an apex portion extending into the turbulator flow channel.

[0075] The dilution vortex turbulence generator according to any preceding clause, further comprising an extension horn having a proximal end at the cold surface side of the substrate and a distal end extending from the cold surface side of the substrate, wherein the turbulence generator flow channel further extends from the proximal end through the extension horn to the distal end.

[0076] The dilution vortex turbulence generator according to any of the preceding clauses further comprises a main ejector, the main ejector comprising an ejector wall, the ejector wall having a main ejector flow channel passing therethrough, the ejector wall having an ejector wall inner surface and an ejector wall outer surface defining the main ejector flow channel, wherein the main ejector extends from the cold surface side of the substrate to the hot surface side of the substrate, and wherein the main ejector is disposed within the turbulence generator flow channel with a gap between the turbulence generator wall and the ejector wall outer surface.

[0077] A dilution vortex turbulence generator according to any preceding clause, further comprising a plurality of vortex generating turbulators disposed on the ejector wall outer surface and extending into the gap.

[0078] A dilution vortex turbulence generator according to any preceding clause, further comprising a plurality of vortex generating turbulators arranged on the inner surface of the ejector wall.

[0079] A dilution vortex turbulence generator according to any of the preceding clauses, wherein the turbulence generator wall, the ejector wall inner surface and the ejector wall outer surface each include conical surfaces arranged radially with respect to each other, the large diameter portion of each conical surface being arranged on the cold surface side of the substrate, and the small diameter portion of each conical surface being arranged on the hot surface side of the substrate.

[0080] A dilution vortex turbulence generator according to any of the preceding clauses, wherein the surface of the turbulence generator wall includes a first portion that is concentric with the main ejector and a second portion that is not concentric with the main ejector, the first portion being on the upstream side of the dilution vortex turbulence generator and the second portion being on the downstream side of the dilution vortex turbulence generator and having a larger radius than the first portion.

[0081] A dilution vortex turbulence generator as claimed in any preceding clause, wherein the plurality of turbulators provided on the turbulence generator wall are provided on the second portion and are not provided on the first portion.

[0082] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0083] A method for providing a dilution flow of an oxidant in a combustor of a gas turbine, the method comprising: providing an oxidant flow on a cold surface side of a combustor liner; providing the oxidant flow from the cold surface side of the combustor liner to a vortex turbulence generator in the combustor liner; generating vortex turbulence of the oxidant in the vortex turbulence generator and outputting it from the vortex turbulence generator to a combustion chamber on the hot surface side of the combustor liner, wherein the vortex turbulence of the oxidant is generated in a generating step, wherein the generating step comprises: passing the oxidant flow through a vortex generating surface of a vortex turbulent generator, the vortex turbulent generator being disposed on a flow channel wall, the flow channel wall extending through the vortex turbulence generator and defining an oxidant flow channel therethrough, wherein the vortex turbulent generator extends from the flow channel wall into an opening portion of the flow channel, and wherein the vortex generating surface of the vortex turbulent generator generates vortices of the oxidant, the vortices of the oxidant passing through the surface of the vortex turbulent generator in the vortex turbulence generator.

[0084] A method according to any preceding clause, wherein the vortex turbulence generator comprises a plurality of vortex turbulators disposed on the flow channel wall, wherein the plurality of vortex turbulators further generate a vortex of the oxidant around the flow channel within the vortex turbulence generator.

[0085] A method according to any preceding clause, wherein the vortex turbulence generator is arranged to provide a non-turbulent oxidant flow jet from the cold surface side of the combustor liner through the central portion of the vortex turbulence generator to the hot surface side of the combustor liner, and wherein, in the output, the non-turbulent oxidant flow jet is output into the combustion chamber together with the vortex turbulence of the oxidant, and the vortex turbulence is output around the non-turbulent oxidant flow jet.

[0086] Although the foregoing description is directed to some exemplary embodiments of the present disclosure, it should be noted that other changes and modifications will be apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, the features described in conjunction with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A burner for a gas turbine, It is characterized in that include: a combustor liner having a cold surface side and a hot surface side; a combustion chamber disposed on the hot surface side of the combustor liner; A vortex turbulence generator, wherein the vortex turbulence generator is arranged on the combustor liner, and the vortex turbulence generator comprises: a turbulence generator flow passage extending through the combustor liner from the cold surface side of the combustor liner to the hot surface side of the combustor liner, the turbulence generator flow passage being defined by a turbulence generator wall surrounding a periphery of the turbulence generator flow passage; and a plurality of vortex generating turbulators disposed on the turbulence generator wall, each of the plurality of vortex generating turbulators including a protrusion extending from a surface of the turbulence generator wall into the turbulence generator flow passage and generating vortex turbulence of an oxidant from the cold surface side of the combustor liner through the turbulence generator flow passage to the hot surface side of the combustor liner; The vortex turbulence generator further comprises a main ejector, the main ejector comprises an ejector wall, the ejector wall has a main ejector flow channel passing therethrough, the ejector wall has an ejector wall inner surface defining the main ejector flow channel and an ejector wall outer surface, wherein the main injector extends from the cold surface side of the combustor liner to the hot surface side of the combustor liner, and The main ejector is arranged in the turbulence generator flow channel, and there is a gap between the turbulence generator wall and the outer surface of the ejector wall. The turbulence generator wall includes a first portion that is concentric with the main ejector and a second portion that is not concentric with the main ejector, wherein the first portion is on the upstream side of the vortex turbulence generator, and the second portion is on the downstream side of the vortex turbulence generator and has a larger radius than the first portion. The plurality of vortex generating turbulators provided on the wall of the vortex turbulence generator are provided on the second portion but not on the first portion.

2. The burner according to claim 1, It is characterized in that in, At least a portion of the turbulence generator wall is a conical surface having a major diameter disposed toward the cold surface side of the combustor liner and a minor diameter disposed toward the hot surface side of the combustor liner.

3. The burner according to claim 1, It is characterized in that in, The plurality of vortex generating turbulators include a plurality of rows of vortex generating turbulators disposed on the turbulator wall, a first row of the plurality of rows of vortex generating turbulators being disposed adjacent to the cold surface side of the combustor liner, and a second row of the plurality of rows of vortex generating turbulators being disposed adjacent to the hot surface side of the combustor liner.

4. The burner according to claim 3, It is characterized in that in, The vortex generating turbulators in the first row are rotationally staggered on the turbulator wall about a central axis of the turbulator flow channel relative to the vortex generating turbulators in the second row.

5. The burner according to claim 1, It is characterized in that in, Each of the plurality of vortex generating turbulators is a conical element having a base portion disposed on the turbulator wall and an apex portion extending into the turbulator flow channel.

6. The burner according to claim 1, It is characterized in that in, The vortex turbulence generator further includes an extension horn having a proximal end at the cold surface side of the combustor liner and a distal end extending from the cold surface side of the combustor liner, Wherein the turbulence generator flow channel further extends from the proximal end through the extension horn to the distal end.

7. The burner according to claim 1, It is characterized in that Further included is a plurality of vortex generating turbulators disposed on the outer surface of the ejector wall and extending into the gap.

8. The burner according to claim 1, It is characterized in that in, The turbulence generator wall, the ejector wall inner surface and the ejector wall outer surface each include conical surfaces arranged radially with respect to each other, a large diameter portion of each conical surface being disposed on the cold surface side of the combustor liner, and a small diameter portion of each conical surface being disposed on the hot surface side of the combustor liner.

9. The burner according to claim 1, It is characterized in that in, The primary injector provides a non-turbulent flow of the oxidant into the combustion chamber, and wherein the vortex turbulence generator provides a turbulent vortex of the oxidant into the combustion chamber, the turbulent vortex surrounding the non-turbulent flow at the hot surface side of the combustor liner.

10. The burner according to claim 1, It is characterized in that Further comprising a plurality of vortex generating turbulators disposed on the inner surface of the ejector wall.

11. A dilution vortex turbulence generator for a combustor of a gas turbine, It is characterized in that The generator comprises: a substrate having a cold surface side and a hot surface side; a turbulence generator flow channel extending through the substrate from the cold surface side to the hot surface side, the turbulence generator flow channel being defined by a turbulence generator wall surrounding a periphery of the turbulence generator flow channel; and a plurality of vortex generating turbulators disposed on the turbulence generator wall, each of the plurality of vortex generating turbulators including a protrusion extending from a surface of the turbulence generator wall into the turbulence generator flow channel and generating vortex turbulence of an oxidant from the cold surface side of the substrate through the turbulence generator flow channel to the hot surface side of the substrate; The vortex turbulence generator further comprises a main ejector, the main ejector comprises an ejector wall, the ejector wall has a main ejector flow channel passing therethrough, the ejector wall has an ejector wall inner surface defining the main ejector flow channel and an ejector wall outer surface, wherein the main injector extends from the cold surface side of the combustor liner to the hot surface side of the combustor liner, and The main ejector is arranged in the turbulence generator flow channel, and there is a gap between the turbulence generator wall and the outer surface of the ejector wall. The turbulence generator wall includes a first portion that is concentric with the main ejector and a second portion that is not concentric with the main ejector, wherein the first portion is on the upstream side of the vortex turbulence generator, and the second portion is on the downstream side of the vortex turbulence generator and has a larger radius than the first portion. The plurality of vortex generating turbulators provided on the wall of the vortex turbulence generator are provided on the second portion but not on the first portion.

12. The dilution vortex turbulence generator according to claim 11, It is characterized in that in, At least a portion of the turbulence generator wall is a conical surface with a large diameter disposed toward the cold surface side of the substrate and a small diameter disposed toward the hot surface side of the substrate.

13. The dilution vortex turbulence generator according to claim 11, It is characterized in that in, The plurality of vortex generating turbulators include a plurality of rows of the vortex generating turbulators disposed on the turbulator wall, a first row of the plurality of rows disposed adjacent to the cold surface side of the substrate, and a second row of the plurality of rows disposed adjacent to the hot surface side of the substrate.

14. The dilution vortex turbulence generator according to claim 13, It is characterized in that in, The vortex generating turbulators in the first row are rotationally staggered on the turbulator wall about a central axis of the turbulator flow channel relative to the vortex generating turbulators in the second row.

15. The dilution vortex turbulence generator according to claim 11, It is characterized in that in, Each of the vortex generating turbulators is a conical member having a base portion disposed on the turbulator wall and an apex portion extending into the turbulator flow channel.

16. The dilution vortex turbulence generator according to claim 11, It is characterized in that Further included are a plurality of vortex generating turbulators disposed on the outer surface of the ejector wall and extending into the gap.

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