Combustor deflector assembly

Abstract

A deflector assembly for a combustor defining a flow of operating fluid. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extend through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. One or more cooling holes are positioned around the one or more fastening mechanisms to operably direct cooling air around the one or more fastening mechanisms at the downstream surface.

Description

[0001] This application is a divisional application of the invention patent application filed on June 14, 2022, with application number 202210671613.2 and invention title "Burner Deflector Assembly". Technical Field

[0002] This disclosure relates to a burner deflector assembly. Background Technology

[0003] A gas turbine engine may include a combustion section with a combustor that produces hot combustion gases that are discharged into a turbine section of the engine. The combustor section may include a deflector assembly to protect portions of the combustor section from the hot combustion gases. The deflector assembly may include cooling arrangements to cool portions of the deflector assembly. Attached Figure Description

[0004] The features and advantages of this disclosure will be apparent from the following description of various exemplary embodiments, as shown in the accompanying drawings, wherein similar reference numerals generally denote the same, functionally similar, or structurally similar elements.

[0005] Figure 1 This is a schematic partial cross-sectional view of a portion of an exemplary combustor section having a deflector assembly used in a gas turbine engine system, according to one aspect of this disclosure.

[0006] Figure 2A This is based on one aspect of the disclosure. Figure 1 A front view of the upstream surface of an exemplary panel of the deflector component.

[0007] Figure 2B It is part of an exemplary panel surrounding the area of ​​the fastening mechanism, according to one aspect of this disclosure. Figure 2A The enlarged front view cropped at detail 2B.

[0008] Figure 2C It is part of an exemplary panel according to one aspect of this disclosure, in Figure 2B A schematic cross-sectional view taken at point 2C in the details.

[0009] Figure 3A This is an enlarged front view of a portion of another exemplary panel surrounding the area of ​​the fastening mechanism, according to one aspect of this disclosure.

[0010] Figure 3B It is part of an exemplary panel according to one aspect of this disclosure, in Figure 3A A schematic cross-sectional view taken at detail 3B.

[0011] Figure 4AThis is an enlarged front view of a portion of another exemplary panel surrounding the area of ​​the fastening mechanism, according to one aspect of this disclosure.

[0012] Figure 4B It is based on one aspect of this disclosure Figure 4A A schematic cross-sectional view taken at detail 4B.

[0013] Figure 5 This is a schematic front view of the upstream surface of another exemplary panel according to one aspect of this disclosure.

[0014] Figure 6A This is a schematic cross-sectional view of a portion of another exemplary panel according to an embodiment of the present disclosure.

[0015] Figure 6B The head of the fastening mechanism according to one aspect of this disclosure and Figure 6A A schematic front view of one or more cooling holes on the panel.

[0016] Figure 7 This is a schematic front view of another embodiment of the head and one or more cooling holes of the fastening mechanism according to one aspect of this disclosure.

[0017] Figure 8 This is a schematic cross-sectional view of a portion of another exemplary panel surrounding the fastening mechanism, according to one aspect of this disclosure.

[0018] Figure 9 This is a schematic front view of the upstream surface of another embodiment of a panel including one or more pins according to one aspect of this disclosure.

[0019] Figure 10 This is a schematic front view of the upstream surface of another exemplary panel, including one or more pins, according to one aspect of this disclosure.

[0020] Figure 11 This is a schematic front view of the upstream surface of another exemplary panel, including one or more pins, according to one aspect of this disclosure.

[0021] Figure 12 This is a schematic front view of the upstream surface of another exemplary panel, including one or more pins, according to one aspect of this disclosure. Detailed Implementation

[0022] The features, advantages, and embodiments of this disclosure will be set forth or become apparent from consideration of the following detailed description, drawings, and claims. Furthermore, it should be understood that the following detailed description is exemplary and intended to provide further explanation, and does not limit the scope of the claimed disclosure.

[0023] Various embodiments are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the art will recognize that other components and constructions can be used without departing from the spirit and scope of this disclosure.

[0024] 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 components.

[0025] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, while "downstream" refers to the direction from which the fluid flows.

[0026] The terms “connection,” “fixation,” “attachment,” “linkage,” etc., refer to both direct connection, fixation, attachment, or linking, and indirect connection, fixation, attachment, or linking through one or more intermediate components or features, unless otherwise specified herein.

[0027] The singular forms “one,” “a,” and “the” include plural references unless the context clearly indicates otherwise.

[0028] The approximate language used throughout the specification and claims is applied to modify any quantitative expression that may allow variation without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “about,” “approximate,” “usually,” and “substantially” are not limited to specified precise values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture a component or system. For example, approximate language may refer to a margin of one percent, two percent, four percent, ten percent, fifteen percent, or twenty percent at the endpoints of a single value, a range of values, or a defined range of values.

[0029] The deflector assembly disclosed herein may include a bolted arrangement of one or more bolts positioned around the deflector assembly. The deflector assembly may be attached to or otherwise mounted to the dome of a combustor in an aircraft engine via the bolted arrangement of one or more bolts. When the deflector assembly and the dome are assembled, the head portions of the bolts may be exposed to hot combustion gases. Therefore, due to the proximity of the head portions to the hot combustion gases, some bolted arrangements of the deflector assembly may experience thermal damage around the bolts. In some cases, thermal damage around the bolts may cause fatigue, failure, or wear of a portion of the deflector assembly around the bolt area. Therefore, embodiments of this disclosure provide an improved cooling arrangement around the bolts of a deflector assembly to improve the durability and life cycle of such a deflector assembly compared to deflector assemblies without the benefits of this disclosure.

[0030] Embodiments of this disclosure can provide cooling on both the cold and hot sides of a deflector assembly around a bolt. The deflector assembly may include one or more cooling holes to operatively direct cooling air radially or tangentially to the bolt head on the hot side of the deflector assembly. For example, the cooling holes may be radially inwardly angled to direct cooling air radially toward the bolt head. The cooling air can act as an air “curtain,” providing a cooling insulation layer around the bolt to reduce or prevent heat transfer from hot combustion gases to the bolt. Pins or ribs on the cold side of the deflector assembly provide structural support to the deflector assembly when mounted to a dome. The pins or ribs can promote turbulence of the cooling air around the pins and provide a larger surface area for heat transfer to improve cooling. Cooling arrangements of this disclosure may include retracted bolts with a surrounding cooling pattern to reduce thermal damage to the bolt head due to combustion gases during aircraft engine operation. For example, the deflector assembly may include a recessed area from which the bolt is inserted or otherwise extends. In this sense, the bolt can be recessed from the hot side of the deflector assembly. In some examples, cooling holes are located in the recessed area of ​​the deflector assembly. The cooling holes can be angled to operatively direct cooling air tangentially to the head of the bolt on the hot side of the deflector assembly.

[0031] The bolt may include cooling holes passing through it, allowing cooling air to flow through the bolt to further reduce heat damage around the bolt head. Pins may be arranged in various patterns around the deflector assembly to increase the residence time of cooling air in the area of ​​the pin. The pin may include a drilled hole through its center to provide a substantially axial cooling flow around the bolt. For example, the axial cooling flow can act as an additional air curtain, allowing a cooling insulating layer of air to be operatively guided around the bolt to reduce or prevent heat transfer from hot combustion gases to the bolt. The shape and size of the pin can be designed for effective heat dissipation. Furthermore, a semi-circular slit may be provided between the bolt and the fuel / air cyclone on the deflector assembly to provide an air curtain within the deflector assembly, further protecting the bolt from hot combustion gases.

[0032] Therefore, the cooling arrangement of this disclosure can promote heat dissipation and reduce thermal damage around the bolts of the deflector assembly. Consequently, compared to cooling arrangements of deflector assemblies without the benefits of this disclosure, the cooling arrangement of this disclosure can increase the durability and lifespan of the deflector assembly.

[0033] Now refer to the attached diagram, Figure 1This is a schematic partial cross-sectional view of a portion of an exemplary combustion section 26 having a deflector assembly 160 used in a gas turbine engine system, as can be incorporated into various embodiments of this disclosure. The gas turbine engine system may include any suitable configuration, such as, but not limited to, a turbofan, turboprop, turbine shaft, turbojet, or propeller fan configuration for aviation, marine, or power generation purposes. Furthermore, other suitable configurations may include steam turbine engines or other Brayton cycle machines. Various embodiments of combustion section 26 may further specifically define a rich-burner combustor. However, other embodiments may define a lean-burner combustor configuration. In an exemplary embodiment, combustion section 26 includes an annular combustor. Those skilled in the art will understand that the combustor may be any other combustor, including but not limited to single or double annular combustors, can combustors, or can-annular combustors.

[0034] like Figure 1 As shown, combustion section 26 defines an axial direction A and a radial direction R perpendicular to the axial direction A. Combustion section 26 includes an outer bushing 102 and an inner bushing 104 disposed between an outer burner housing 106 and an inner burner housing 108. The outer bushing 102 and the inner bushing 104 are radially spaced apart from each other, such that a combustion chamber 110 is defined therebetween. The outer bushing 102 and the outer burner housing 106 form an outer channel 112 therebetween, and the inner bushing 104 and the inner burner housing 108 form an inner channel 114 therebetween.

[0035] Combustion section 26 may also include a burner assembly 118, which includes an annular dome assembly 120 mounted upstream of combustion chamber 110. The burner assembly 118 is configured to connect to the front ends of outer bushing 102 and inner bushing 104. More specifically, the burner assembly 118 includes an inner annular dome 122 attached to the front end of inner bushing 104 and an outer annular dome 124 attached to the front end of outer bushing 102.

[0036] Combustion section 26 may be configured to receive an annular flow of compressor exhaust air 126 from the exhaust outlet of a high-pressure compressor (not shown) of a gas turbine engine system. To aid in guiding the compressed air, the annular dome assembly 120 may also include an inner shroud 128 and an outer shroud 130, which may be coupled to the upstream ends of the inner bushing 104 and outer bushing 102, respectively. In this respect, an annular opening 132 formed between the inner shroud 128 and the outer shroud 130 allows compressed fluid to enter combustion section 26 through a diffusion opening in a direction generally indicated by the flow direction 134. Compressed air may enter a cavity 136 defined at least partially by the annular dome assembly 120. In various embodiments, cavity 136 is more specifically defined by an inner annular dome 122 and an outer annular dome 124 and between the inner shroud 128 and the outer shroud 130. As will be discussed in more detail below, a portion of the compressed air in cavity 136 may be used for combustion, while another portion may be used to cool combustion section 26.

[0037] In addition to directing air into cavity 136 and combustion chamber 110, inner shroud 128 and outer shroud 130 can direct a portion of the compressed air around the exterior of combustion chamber 110 to facilitate cooling of outer liner 102 and inner liner 104. For example, as Figure 1 As shown, a portion of the compressor exhaust air 126 can flow around the combustion chamber 110, as indicated by the outer passage flow direction 138 and the inner passage flow direction 140, to provide cooling air to the outer passage 112 and the inner passage 114, respectively.

[0038] In some exemplary embodiments, the inner annular dome 122 may be integrally formed as a single annular component, and similarly, the outer annular dome 124 may also be integrally formed as a single annular component. In yet other embodiments, the inner annular dome 122 and the outer annular dome 124 may be formed together as a single integral component. In various embodiments, an annular dome assembly 120 including one or more of the inner annular dome 122, the outer annular dome 124, the outer bushing 102, or the inner bushing 104 may be formed as a single integral component. In other exemplary embodiments, the inner annular dome 122 or the outer annular dome 124 may alternatively be formed from one or more components joined in any suitable manner. For example, with respect to the outer annular dome 124, in some exemplary embodiments, the outer cover 130 may be formed separately from the outer annular dome 124 and attached to the front end of the outer annular dome 124 using, for example, welding, mechanical fasteners, adhesives or bonding agents, or composite lamination processes. Alternatively or additionally, the inner annular dome 122 may have a similar construction.

[0039] The combustor assembly 118 further includes a plurality of mixer assemblies 142 spaced circumferentially between the outer annular dome 124 and the inner annular dome 122. In this respect, the annular dome assembly 120 defines an opening in which a cyclone separator, cyclone separator, or mixer assembly 142 is mounted, attached, or otherwise integrated to introduce an air / fuel mixture into the combustion chamber 110. Notably, compressed air can be directed from the combustion section 26 into or through one or more mixer assemblies 142 to support combustion in the upstream end of the combustion chamber 110.

[0040] Liquid or gaseous fuel is delivered to combustion section 26 via a fuel distribution system (not shown), and introduced into combustion section 26 in the form of a highly atomized spray from a fuel nozzle at the front end of the burner. In an exemplary embodiment, each mixer assembly 142 may define an opening for receiving fuel injectors 146 (details omitted for clarity). Fuel injectors 146 may inject fuel in a generally axial direction A and a generally radial direction R, wherein the fuel may vortex with incoming compressed air. Thus, each mixer assembly 142 receives compressed air from an annular opening 132 and fuel from the corresponding fuel injector 146. The fuel and pressurized air vortex and mix together through the mixer assembly 142, and the resulting fuel / air mixture is discharged into combustion chamber 110 for combustion.

[0041] Combustion section 26 may further include an ignition assembly (e.g., one or more igniters extending through outer bushing 102) suitable for igniting the fuel-air mixture. For clarity, in Figure 1 Details of the fuel injectors and ignition assembly are omitted. Upon ignition, the resulting hot combustion gases can flow in a generally axial direction A through the combustion chamber 110 and through the turbine section of the engine, where a portion of the thermal or kinetic energy from the hot combustion gases is extracted via a sequential stage of turbine stator blades and turbine rotor blades. More specifically, the hot combustion gases can flow into an annular, first-stage turbine nozzle 148. As generally understood, the first-stage turbine nozzle 148 can be defined by an annular flow channel comprising a plurality of radially extending, circularly spaced nozzle blades 150 that deflect the gases so that they flow at an angle and impinge on the first-stage turbine blades (not shown) of the high-pressure turbine (not shown) of the gas turbine engine system.

[0042] Still referencing Figure 1 Multiple mixer assemblies 142 are circumferentially arranged within the annular dome assembly 120. Fuel injectors 146 are disposed in each mixer assembly 142 to supply fuel and support the combustion process.

[0043] Each dome has a heat shield, such as deflector assembly 160, which thermally insulates the annular dome assembly 120 from the extremely high temperatures (e.g., from hot combustion gases) generated in the combustion chamber 110 during engine operation. The inner annular dome 122, outer annular dome 124, and deflector assembly 160 may define a plurality of openings 144 for receiving the mixer assembly 142. As shown, in one embodiment, the plurality of openings 144 are circular. In other embodiments, the openings 144 are ovular, elliptical, polygonal, rectangular, or other non-circular cross-sections. The deflector assembly 160 is mounted on the combustion chamber side (e.g., downstream side) of the annular dome assembly 120. The deflector assembly 160 may include a plurality of panels 200 (one of which is in…) Figure 2A (As shown in the text), further detailed below.

[0044] Compressed air (e.g., compressor exhaust air 126) flows into the annular opening 132, where a portion of the compressor exhaust air 126 is used to mix with fuel for combustion, while another portion is used to cool the deflector assembly 160. The compressed air can flow around the fuel injector 146 and through mixing impellers surrounding the circumference of the mixer assembly 142, where it mixes with fuel and is directed into the combustion chamber 110. Another portion of the air enters a cavity 136 defined by the annular dome assembly 120, the inner shroud 128, and the outer shroud 130. The compressed air in cavity 136 is at least partially used to cool the annular dome assembly 120 and the deflector assembly 160, as further detailed below.

[0045] Figure 2A This is a front view of the first upstream surface 202 of an exemplary panel 200 of the deflector assembly 160. Figure 2A As shown, each panel 200 includes a first upstream surface 202 and a first downstream surface 204 opposite to the first upstream surface 202 (e.g., Figure 2C (As shown). Each panel 200 may further include a circumferentially outer side 206 and a circumferentially inner side 208, which define a predetermined arc relative to the circumference of the panel 200. Each panel 200 may include a first radially extending side 210 and a second radially extending side 212, each extending from the circumferentially outer side 206 to the circumferentially inner side 208. Each panel 200 further includes an opening 144 extending between a first upstream surface 202 and a first downstream surface 204 for receiving a corresponding one of the mixer assemblies 142, as detailed above.

[0046] Multiple panels 200 may be together to form different segments or sections of the deflector assembly 160. For example, each of the multiple panels 200 may be constructed together to form a ring or similar ring structure defining the deflector assembly 160. In some embodiments, each of the multiple panels 200 may be formed from a separate component, and each panel 200 (e.g., each separate component) may be attached or otherwise connected together to form the deflector assembly 160. In some embodiments, the multiple panels 200 may be formed from a single or integral structure defining a ring or ring structure defining the deflector assembly 160. The shape or size of the multiple panels 200, and therefore the shape or size of the deflector assembly 160, may include any shape or size as needed to provide thermal insulation for the annular dome assembly 120.

[0047] Each panel 200 includes one or more fastening mechanisms 214 for fastening each panel 200, and thus the deflector assembly 160, to the annular dome assembly 120. The one or more fastening mechanisms 214 may include any type of fastening mechanism, such as studs, threaded bolts, screws, nuts, rivets, etc. Although four fastening mechanisms 214 are shown on the panel 200 in the exemplary embodiment, each panel 200 may include any number of fastening mechanisms 214 as needed. The one or more fastening mechanisms 214 may each be located, near, or adjacent to a corresponding corner, edge, perimeter, etc., of the respective panel 200. As needed, the one or more fastening mechanisms 214 may be located at any position along the circumferential or radial direction of the respective panel 200.

[0048] Each panel 200 includes one or more pins 222 (only one is labeled in each corresponding figure) associated with each fastening mechanism 214. The one or more pins 222 can provide a larger surface area for heat transfer to improve cooling of each panel 200 around the one or more fastening mechanisms 214, as further detailed below. The one or more pins 222 can also promote turbulence in the cooling airflow. For example, the one or more pins 222 can disrupt the cooling airflow, making it irregular and improving heat transfer around the one or more pins 222. The one or more pins 222 can also provide additional structural support between the deflector assembly 160 and the annular dome assembly 120 around the region of the fastening mechanism 214.

[0049] exist Figure 2A In the example, one or more pins 222 may include a generally cylindrical shape and may be arranged in a generally circular pattern around the corresponding fastening mechanism 214. One or more pins 222 may include other shapes or sizes and may be arranged in other patterns, as described below. Figures 9 to 12Further details are provided below. Each of the one or more pins 222 may include one or more cooling holes 224 extending therethrough (only one is labeled in each respective figure). For example, the one or more cooling holes 224 may extend axially through each of the one or more pins 222, as further detailed below.

[0050] Figure 2B Is Figure 2A An enlarged front view of a portion of the exemplary panel 200, cropped at detail 2B, surrounding the area of ​​the fastening mechanism 214. (See also...) Figure 2B As shown, each panel 200 includes a recessed portion 218 in a region surrounding each of one or more fastening mechanisms 214. The recessed portion 218 comprises a portion of the respective panel 200 that is recessed relative to the first downstream surface 204, as described below regarding... Figure 2C Further details are provided. The corresponding fastening mechanism 214 can be located at the center of the recessed portion 218, such that the corresponding fastening mechanism 214 is recessed or otherwise retracted relative to the first downstream surface 204. The corresponding fastening mechanism 214 can be located anywhere within the recessed portion 218 as needed. Furthermore, although... Figure 2B The recessed portion 218 shown is generally circular in shape, but the recessed portion 218 surrounding each fastening mechanism 214 may include any shape or size as needed. The recessed portion 218 may include one or more cooling holes 220 extending therethrough. The one or more cooling holes 220 may extend from a first upstream surface 202 of the recessed portion 218 to a first downstream surface 204, as further detailed below.

[0051] Figure 2C Is Figure 2B A schematic cross-sectional view of a portion of the exemplary panel 200, taken at detail 2C. Figure 2C As shown, when multiple panels 200 are mounted or otherwise attached to the annular dome assembly 120, a cavity 211 can be defined between the annular dome assembly 120 and the deflector assembly 160. One or more fastening mechanisms 214 can be inserted through a corresponding center hole 213 of each panel 200 (in Figure 2C A central hole 213 is shown in the diagram. Each central hole 213 may be located in the central region of the recess 218, such that a corresponding fastening mechanism 214 is located at the center of the recess 218, as detailed above. One or more fastening mechanisms 214 may protrude from or otherwise extend from the first upstream surface 202 of the respective panel 200 and may be inserted into the corresponding hole 215 (in the diagram). Figure 2CThis is illustrated in other mounting configurations of the annular dome assembly 120 (with a hole 215 shown). In some embodiments, one or more fastening mechanisms 214 may be integrally formed with the respective panel 200, such that the center hole 213 may not be necessary.

[0052] When one or more fastening mechanisms 214 are disposed on or through the panel 200, the head 216 of the corresponding fastening mechanism 214 may be disposed at, near or adjacent to, the first downstream surface 204 of the recessed portion 218 of the corresponding panel 200. Figure 2C In this configuration, the head 216 of each of one or more fastening mechanisms 214 is configured to be flush with the first downstream surface 204 of the recessed portion 218 of the corresponding panel 200. However, the head 216 of the corresponding fastening mechanism 214 may be axially recessed relative to the first downstream surface 204.

[0053] During burner operation, one or more fastening mechanisms 214 may be exposed to hot combustion gases at a first downstream surface 204 of each panel 200. Therefore, one or more fastening mechanisms 214 may experience thermal damage due to the hot combustion gases, as detailed above. Embodiments of this disclosure provide improved cooling around one or more fastening mechanisms 214 to reduce thermal gradients and improve the durability of the deflector assembly 160, as further detailed below.

[0054] exist Figure 2CWhen the corresponding panel 200 is mounted to the annular dome assembly 120, the recessed portion 218 can retract from the first downstream surface 204 toward the annular dome assembly 120 in the axial proximal direction. For example, the recessed portion 218 can define an angled portion of the corresponding panel 200 relative to the first downstream surface 204. For example, the recessed portion 218 can retract from the first downstream surface 204 at an angle (θ) of approximately forty-five degrees (45°) to facilitate the placement and alignment of the cooling holes 220 (e.g., for ease of manufacture), so that the cooling holes 220 provide an effective "curtain" of cooling air 223 around the corresponding fastening mechanism 214, as detailed below. Of course, the recessed portion 218 can retract from the first downstream surface 204 at any angle (θ) greater than zero degrees (0°) and less than or equal to ninety degrees (90°). In some cases, if the angle (θ) is greater than 60 degrees, a sharp edge may form between the first downstream surface 204 and the recessed portion 218, and the thermal and mechanical stresses at the edge may increase due to the sharp edge. Furthermore, if the angle (θ) is less than 30 degrees, the head 216 of the corresponding fastening mechanism 214 can be positioned closer to the hot combustion gases, resulting in higher thermal stresses on the fastening mechanism 214 compared to a larger angle (θ). Therefore, preferably, the angle (θ) relative to the first downstream surface 204 can be greater than or equal to 30 degrees (30°) and less than or equal to 60 degrees (60°). Such a range provides a desired range to balance the placement of the head 216 of the fastening mechanism 214 away from the hot combustion gases while reducing or minimizing the thermal or mechanical stresses formed at the edge between the first downstream surface 204 and the recessed portion 218.

[0055] One or more cooling holes 220 are disposed in the area of ​​the panel 200 surrounding the respective fastening mechanism 214. Each of the one or more cooling holes 220 may include a longitudinal axis 270 relative to each respective cooling hole 220 (for clarity, only...). Figure 2C (Seen on one of the cooling holes 220). The longitudinal axis 270 of each of the one or more cooling holes 220 may be relative to the longitudinal axis 272 of the corresponding fastening mechanism 214 (only shown on one of the cooling holes 220 for clarity). Figure 2CThe fastening mechanism 214 (shown on the fastening mechanism 214) extends at an axial angle (an angle in the axial direction). The longitudinal axis 270 of one or more cooling holes 220 may extend at an axial angle between +15 degrees (+15°) and -105 degrees (-105°) relative to the longitudinal axis 272 of the corresponding fastening mechanism 214. In other words, the longitudinal axis 270 of one or more cooling holes 220 may extend at an angle between +60 degrees (±60°) relative to the normal of the recess 218 (e.g., perpendicular to the axis of the recess 218). Compared with other or alternative angles, this axial angle or angle relative to the normal of the recess 218 provides convenience for manufacturing one or more cooling holes 220 while providing an effective curtain of cooling air 223 through one or more cooling holes 220 and around the head 216 of the corresponding fastening mechanism 214. For example, the effective curtain of cooling air 223 provides a cooling insulation layer of air around the fastening mechanism 214 to reduce or prevent heat transfer of hot combustion gases to the corresponding fastening mechanism 214. Other or alternative angles of one or more cooling holes 220 may not provide an effective curtain of air, so that the cooling air 223 through one or more cooling holes 220 may not completely reduce or prevent the heat transfer of hot combustion gases to the corresponding fastening mechanism 214.

[0056] The longitudinal axis 270 of one or more cooling holes 220 may also extend at a circumferential angle (e.g., an angle in the circumferential direction) relative to the longitudinal axis 272 of the corresponding fastening mechanism 214. The longitudinal axis 270 of one or more cooling holes 220 may extend at a circumferential angle between zero and ninety degrees relative to the longitudinal axis 272 of the corresponding fastening mechanism 214 to provide an effective curtain of cooling air 223 around the head 216 of the corresponding fastening mechanism 214 compared to other or alternative circumferential angles, as detailed above. Thus, one or more cooling holes 220 may extend through the recess 218 to operably guide cooling air 223 around the head 216 of the corresponding fastening mechanism 214 in a radial or tangential direction relative to the longitudinal axis 303 of the fastening mechanism 214, as further detailed below.

[0057] One or more cooling holes 220 may be positioned around the corresponding fastening mechanism 214. Therefore, the one or more cooling holes 220 may operably guide cooling fluid or cooling air 223 from the cavity 211 to the region surrounding the head 216 of the corresponding fastening mechanism 214. Thus, cooling air 223 may provide a curtain of cooling air around the corresponding fastening mechanism 214, as detailed above. The cooling air 223 can therefore reduce thermal damage to the corresponding fastening mechanism 214 by providing a cooling insulation layer around the fastening mechanism 214 to reduce or prevent heat transfer of hot combustion gases to the corresponding fastening mechanism 214. Figures 2A to 2CIn the example, one or more cooling holes 220 include a plurality of cooling holes 220 in a circular pattern around the recessed portion 218. Such a pattern can realize a circular curtain of cooling air 223 around the respective fastening mechanism 214, which creates a cooling insulation layer of cooling air 223 around the entire circumference of the head 216 of the respective fastening mechanism 214 to reduce or prevent heat transfer of hot combustion gases to the area surrounding the head of the fastening mechanism 214.

[0058] In some cases, hot combustion gases (e.g., in combustion chamber 110) may be trapped within a curtain of cooling air 223 surrounding the corresponding fastening mechanism 214. Therefore, refer below... Figures 3A to 3B and Figures 4A to 4B Other embodiments of panel 200 are provided and described in detail.

[0059] One or more pins 222 extend between a first end and a second end opposite the first end. One or more pins 222 may be attached at the first end to or otherwise connected to a first upstream surface 202 of a respective panel 200, and may be attached at the second end to or otherwise connected to a second downstream surface 205 of the annular dome assembly 120. When each panel 200 is mounted or otherwise connected to the annular dome assembly 120, one or more pins 222 may extend from the first upstream surface 202 of the respective panel 200 to the second downstream surface 205 of the annular dome assembly 120.

[0060] One or more cooling holes 224 may include a longitudinal axis 274 (in Figure 2C (Only shown on one cooling hole 224), the longitudinal axis 274 can be relative to the longitudinal axis of one or more pins 222 (with Figure 2C The longitudinal axis 274 (coaxial) extends at a certain angle. Figure 2C In this configuration, one or more cooling holes 224 may extend at an angle of zero degrees relative to the longitudinal axis of one or more pins 222. The one or more cooling holes 224 may each extend at an angle between ±10 degrees relative to the longitudinal axis of one or more pins 222 to provide an effective curtain of cooling air 225 around the head 216 of the respective fastening mechanism 214, as detailed above. In this way, the one or more cooling holes 224 may be angled to guide cooling air 225 radially outward, radially inward, or axially relative to the head 216 or longitudinal axis 272, respectively.

[0061] When one or more pins 222 are installed between the annular dome assembly 120 and the corresponding panel 200, one or more cooling holes 224 can be substantially aligned with corresponding holes 226 of the annular dome assembly 120 and holes 228 of the corresponding panel 200. Holes 226 can extend from a second upstream surface 203 of the annular dome assembly 120 to a second downstream surface 205. Holes 228 can extend from a first upstream surface 202 to a first downstream surface 204. In this way, cooling air 225 from the cavity 136 can flow through holes 226, through one or more cooling holes 224, and out of holes 228. Therefore, the cooling air 225 through one or more pins 222 can provide an additional curtain around the corresponding fastening mechanism 214 to further protect the head 216 from hot combustion gases. Holes 226 and 228 can be angled substantially similarly to the cooling holes 224 through one or more pins 222. The corresponding hole 226, the corresponding cooling hole 224 and the corresponding hole 228 can together form a single cooling hole to provide a single path through which cooling air 225 can flow.

[0062] Figure 3A This is an enlarged front view of a portion of another exemplary panel 300 surrounding the region of the fastening mechanism 214 according to another embodiment. Panel 200 is substantially the same as panel 200 and includes many of the same or similar components and functions. Figure 3A As shown, panel 300 includes a fastening mechanism 314 having one or more cooling holes 319.

[0063] Figure 3B It is part of the exemplary panel 300, in Figure 3A A schematic cross-sectional view taken at detail 3B. Panel 300 includes one or more fastening mechanisms 314 disposed within the recessed portion 218, similar to... Figures 2A to 2C The embodiment described herein. A corresponding fastening mechanism 314 includes one or more cooling holes 319 extending therethrough. The one or more cooling holes 319 extend from an upstream surface of the one or more fastening mechanisms 314 and through a head 316 of the one or more fastening mechanisms 314. The one or more cooling holes 319 operatively guide cooling air 321 from the cavity 136 to a downstream side of the one or more fastening mechanisms 314. The cooling air 321 can reduce or prevent the accumulation of recirculated hot combustion air bubbles around the head 316 of the corresponding fastening mechanism 314. That is, the one or more cooling holes 319 can operatively guide cooling air 321 to flush out hot combustion gases or prevent hot combustion gases from becoming trapped around the corresponding fastening mechanism 314.

[0064] One or more cooling holes 319 may each include a longitudinal axis 374. The longitudinal axis 374 of one or more cooling holes 319 may extend at an axial angle (an angle in the axial direction) relative to the longitudinal axis of the corresponding fastening mechanism 314 (coaxial with the longitudinal axis 374 in FIG. 3). The longitudinal axis 374 of one or more cooling holes 319 may extend at an axial angle between ±10 degrees (±10°) relative to the longitudinal axis of the corresponding fastening mechanism 314 to provide an effective angle for cooling air 321 to reduce or prevent the accumulation of recirculated bubbles of hot combustion gases around the head 316 of the corresponding fastening mechanism 314. Preferably, the axial angle at which one or more cooling holes 319 extend may be zero degrees (0°) to more effectively reduce or prevent recirculated bubbles of hot combustion gases compared to other axial angles. The longitudinal axis 374 of one or more cooling holes 319 may also extend at a circumferential angle (e.g., an angle in the circumferential direction) relative to the longitudinal axis 374 of the corresponding fastening mechanism 314. The longitudinal axis 374 of one or more cooling holes 319 may extend at a circumferential angle between zero and ninety degrees relative to the longitudinal axis of the corresponding fastening mechanism 314 to effectively reduce or prevent recirculation bubbles of hot combustion gases compared to other circumferential angles.

[0065] Figure 4A This is an enlarged front view of a portion of another exemplary panel 400 surrounding the area of ​​the fastening mechanism 214 according to another embodiment. Panel 400 is substantially identical to panel 200 and includes many of the same or similar components and functions. Figure 4A As shown, panel 400 includes a recessed portion 418, which includes cooling holes 420 in a semi-circular pattern surrounding fastening mechanism 214.

[0066] Figure 4B It is part of the exemplary panel 400, in Figure 4A A schematic cross-sectional view taken at detail 4B. Panel 400 includes a recessed portion 418 in the area surrounding one or more fastening mechanisms 214 and one or more cooling holes 420, similar to... Figures 2A to 2C The embodiments described herein. Figure 4B In one embodiment, one or more cooling holes 420 comprise a plurality of cooling holes 420 in a semi-circular pattern surrounding only a portion (e.g., the radially outer half) of the recessed portion 418. Such a pattern enables a semi-circular curtain of cooling air 223 surrounding the respective fastening mechanism 214, while reducing or preventing the formation of recirculated air bubbles around the head 216 of the respective fastening mechanism 214. That is, Figure 4BThe cooling holes 420 are configured to flush out hot combustion gases or prevent hot combustion gases from becoming trapped around the corresponding fastening mechanism 214. One or more cooling holes 420 may be arranged in any pattern around the fastening mechanism 214 as needed to reduce or prevent recirculation bubbles from forming around the head 216 of the corresponding fastening mechanism 214.

[0067] Figure 5 This is a front view of the first upstream surface 202 of another exemplary panel 500 according to one aspect of this disclosure. Fastening mechanism 214 and one or more pins 222 are... Figure 5 The diagram is schematically shown, and for clarity, only three pins 222 are shown around the circumference of each fastening mechanism 214. One or more pins 222 may include more than three pins 222 arranged in various patterns, as detailed above. Furthermore, although one or more cooling holes 224 of one or more pins 222 are not shown... Figure 5 As shown in the image, but Figure 5 One or more pins 222 may include one or more cooling holes 224, as detailed above.

[0068] like Figure 5 As shown, each panel 500 may also include one or more slits 501 extending through the respective panel 500. Figure 5 (Only one is marked in the text). For example, one or more slits 501 may extend from a first upstream surface 202 of a respective panel 500 to a first downstream surface 204. Each of the one or more slits 501 may be radially and circumferentially positioned between a respective fastening mechanism 214 and an opening 144 of the respective panel 500. Thus, the one or more slits 501 may operatively guide additional cooling air from the cavity 136 between the fastening mechanism 214 and the respective mixer assembly 142 in the opening 144.

[0069] like Figure 5 As further shown, one or more slits 501 may comprise a generally arcuate or C-shaped structure. One or more slits 501 may comprise any size or shape as needed to provide additional cooling air. The size or shape of one or more slits 501 may be configured as a function of the distance from the corresponding fastening mechanism 214 to the opening 144. For example, one or more slits 501 may comprise a larger area for fastening mechanisms 214 closer to the opening 144 than the area for fastening mechanisms 214 further away from the opening 144. In some embodiments, one or more slits 501 may be associated only with fastening mechanisms 214 closer to the opening 144. For example, Figure 5 Fastening mechanisms 214 further away from opening 144 (e.g., fastening mechanism 214 in the upper half of panel 500) may not have one or more slits 501 associated with them. While a slit 501 is associated with... Figure 5 Each fastening mechanism 214 is associated with a pin 222, but any number of slits 501 (e.g., multiple slits 501) may be associated with, or positioned relative to or near, each fastening mechanism 214. In some embodiments, a slit 501 may be positioned between a respective fastening mechanism 214 and a respective pin 222.

[0070] Figure 6A This is a schematic cross-sectional view of a portion of a panel 600 surrounding a fastening mechanism 614, according to another embodiment of the present disclosure. Figure 6B This is a schematic front view of the head 616 of the fastening mechanism 614 and one or more cooling holes 620. Although Figure 6A and 6B The embodiments shown herein illustrate an unretracted fastening mechanism 614 (e.g., panel 600 does not include a recessed portion), however, the embodiments described herein can be combined to include a recessed portion, such that... Figure 6A and 6B The fastening mechanism 614 retracts (as per reference). Figure 2B-2C (As shown and explained). Panel 600 includes a first upstream surface 602 and a first downstream surface 604. Fastening mechanism 614 includes a head 616 configured to be substantially flush with the first downstream surface 604. Fastening mechanism 614 includes a longitudinal axis 672 defined therethrough. When fastening mechanism 614 is disposed in panel 600, the longitudinal axis 672 of fastening mechanism 614 extends substantially axially.

[0071] Panel 600 includes one or more cooling holes 620. The one or more cooling holes 620 are disposed around the fastening mechanism 614. The one or more cooling holes 620 are angled radially inward relative to the fastening mechanism 614 to operably guide cooling air 223 radially toward the head 616 of the fastening mechanism 614 (e.g., ...). Figure 6B (as shown), similar to Figure 2A-2C An embodiment. In this manner, one or more cooling holes 620 can operatively direct cooling flow around the head 616 of the fastening mechanism 614, as detailed above.

[0072] Figure 7 This is a schematic front view of the head 616 of a fastening mechanism 614 according to another embodiment and one or more cooling holes 720. The cooling holes 720 are also circumferentially angled to operatively guide cooling air 623 to the head 616 of the fastening mechanism 614. For example, one or more cooling holes 720 extend at a circumferential angle (e.g., an angle in the circumferential direction) relative to the longitudinal axis 672 of the fastening mechanism 614. In this way, the cooling holes 720 tangentially supply cooling air 223 to the head 616 of the fastening mechanism 614.

[0073] Figure 8 This is a schematic cross-sectional view of a portion of a panel 800 surrounding a fastening mechanism 814, according to another embodiment of this disclosure. Although Figure 8 The embodiments shown herein illustrate an unretracted fastening mechanism 814 (e.g., panel 800 does not include a recessed portion), however, the embodiments described herein can be combined to include a recessed portion, such that... Figure 8 The fastening mechanism 814 retracts (as per reference). Figure 2B-2C (Shown and explained). Panel 800 includes a first upstream surface 802 and a first downstream surface 804. Fastening mechanism 814 includes a head 816 configured to be substantially flush with the first downstream surface 804. Fastening mechanism 814 includes a longitudinal axis 872 defined therethrough. When fastening mechanism 814 is disposed in panel 800, the longitudinal axis 872 of fastening mechanism 814 extends substantially axially.

[0074] Panel 800 includes one or more cooling holes 820. The one or more cooling holes 820 are disposed around the fastening mechanism 814. The one or more cooling holes 820 are angled radially inward relative to the fastening mechanism 814 to operably guide cooling air 223 radially toward the head 816 of the fastening mechanism 814, similar to... Figure 2A-2C An embodiment. In this manner, one or more cooling holes 820 can operatively direct cooling flow around the head 816 of the fastening mechanism 814, as detailed above. Figure 8 As shown, the cooling hole 820 may also include a groove 830 for providing or otherwise generating eddies around the fastening mechanism 814. The groove 830 may include an inward surface 832 extending at an angle from the first downstream surface 804. The inward surface 832 may extend at any angle between zero degrees (0°) and sixty degrees (60°) relative to the first downstream surface 804 to generate eddies around the fastening mechanism 814. Thus, the groove 830 may further direct cooling air 823 toward the head 816 of the fastening mechanism 814, or at least toward a portion of the head 816 that is not flush with the inward surface 832, to provide additional heat transfer protection and dissipation around the fastening mechanism 814. The groove 830 may include any size or shape to generate eddies and facilitate the flow of cooling air 223 toward the head 816 of the fastening mechanism 814.

[0075] Figure 9 This is a front view of the first upstream surface 202 of another embodiment of a panel 900 including one or more pins 922 according to aspects of this disclosure. The one or more pins 922 may include an elongated shape such that a first end and a second end of each of the one or more pins 922 are elongated. (As described above...) Figure 2A-2CCompared to the generally cylindrical shape of one or more pins 222, the elongated shape of one or more pins 922 provides a larger surface area at both the first and second ends. Figure 9 In this configuration, one or more pins 922 may include an elongated rectangular shape and each pin 922 may be tangentially positioned relative to the fastening mechanism 214.

[0076] Figure 10 This is a front view of the first upstream surface 202 of another embodiment of a panel 1000 including one or more pins 1022 according to aspects of this disclosure. Figure 10 In this context, one or more pins 1022 may include various generally arcuate shapes and may be positioned in a circular pattern around each corresponding fastening mechanism 214.

[0077] Figure 11 This is a front view of the first upstream surface 202 of another embodiment of a panel 1100 including one or more pins 1122 according to aspects of this disclosure. Figure 11 In this configuration, one or more pins 1122 may include various generally arcuate shapes and may be positioned in a semi-circular pattern around each respective fastening mechanism 214. The semi-circular pattern of one or more pins 1122 may be located on the side of the fastening mechanism 214 away from the opening 144. For example, the semi-circular pattern may be located between the respective fastening mechanism 214 and the circumferential outer side 206, the circumferential inner side 208, the first radial extension side 210, or the second radial extension side 212.

[0078] Figure 12 This is a front view of the first upstream surface 202 of another embodiment of a panel 1200 including one or more pins 1222, according to aspects of this disclosure. Figure 12 In this configuration, the semi-circular pattern of one or more pins 1222 may be located on the side of the fastening mechanism 214 closer to the opening 144. For example, the semi-circular pattern of one or more pins 1222 may be substantially located between the fastening mechanism 214 and the opening 144. Figures 10 to 12 In this design, one or more pins 222 may each include an elongated portion extending between a first end and a second end. The first and second ends may be angled such that the ends of the one or more pins 222 extend at an angle relative to the elongated portions of the one or more pins 222. For example, the first and second ends may not be perpendicular to the elongated portions. The angled first and second ends may promote air vortices between the respective pins 222 to provide additional cooling in the region surrounding the one or more pins 222.

[0079] Compared to deflector components that do not offer the benefits of this disclosure, Figures 9 to 12Embodiments of pins 922, 1022, 1122, and 1222 may each provide increased surface area or increased turbulence generation to achieve increased heat transfer and dissipation in the area surrounding one or more pins on the panel. As detailed above, pins 922, 1022, 1122, and 1222 may include any size or shape and may be arranged in any pattern around the corresponding fastening mechanism 214 as needed to provide improved heat transfer and dissipation.

[0080] Further aspects of this disclosure are provided by the subject matter of the following clauses.

[0081] A deflector assembly for a burner. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extend through the deflector assembly. One or more cooling holes extend from the upstream surface through the deflector assembly to the downstream surface. The one or more cooling holes are positioned around the one or more fastening mechanisms to operably guide cooling air around the one or more fastening mechanisms at the downstream surface.

[0082] According to any one of the preceding clauses, in the deflector assembly, one or more cooling holes are positioned in a circular pattern around each of the one or more recessed portions.

[0083] According to any one of the preceding clauses, in the deflector assembly, one or more cooling holes are positioned in a semi-circular pattern around each of the one or more recessed portions.

[0084] According to any one of the preceding clauses, in the deflector assembly, one or more cooling holes are radially angled relative to one or more fastening mechanisms to operably guide cooling air radially around one or more fastening mechanisms at a downstream surface.

[0085] According to any one of the preceding clauses, in the deflector assembly, one or more cooling holes are circumferentially angled relative to one or more fastening mechanisms to operatively guide cooling air around one or more fastening mechanisms at a downstream surface.

[0086] According to any one of the preceding clauses, in the deflector assembly, one or more cooling holes include grooves configured to generate vortices of cooling air in a region surrounding one or more fastening mechanisms on a downstream surface.

[0087] According to any one of the preceding clauses, in the deflector assembly, one or more cooling holes are first cooling holes, and one or more fastening mechanisms include one or more second cooling holes extending through one or more fastening mechanisms to operably guide cooling air through one or more fastening mechanisms of the deflector assembly at a downstream surface.

[0088] The deflector assembly according to any one of the preceding clauses further includes one or more slits positioned between one or more fastening mechanisms and a central opening of the deflector assembly to provide cooling air at a downstream surface through the one or more slits.

[0089] The deflector assembly according to any one of the preceding clauses further includes one or more recessed portions retracting from the downstream surface. One or more fastening mechanisms extend from the one or more recessed portions such that the one or more fastening mechanisms are retracted relative to the downstream surface.

[0090] According to any one of the preceding clauses, in the deflector assembly, one or more recessed portions retract from the downstream surface at an angle greater than zero degrees and less than or equal to ninety degrees.

[0091] According to any one of the preceding clauses, in the deflector assembly, one or more first cooling holes extend through one or more recessed portions.

[0092] The deflector assembly according to any one of the preceding clauses further includes one or more pins extending from the upstream surface of the deflector assembly, the one or more pins being positioned around one or more fastening mechanisms.

[0093] According to any one of the preceding clauses, each of the one or more pins includes one or more third cooling holes passing through it to provide cooling air around one or more fastening mechanisms at a downstream surface.

[0094] According to any one of the preceding clauses, in the deflector assembly, one or more pins include an elongated surface connected to the upstream surface of one or more panels.

[0095] According to any one of the preceding clauses, in the deflector assembly, one or more pins are tangentially positioned relative to one or more fastening mechanisms.

[0096] According to any one of the preceding clauses, in the deflector assembly, one or more pins are positioned in a circular pattern around each of the one or more fastening mechanisms.

[0097] According to any one of the preceding clauses, in the deflector assembly, one or more pins are positioned in a semi-circular pattern around each of the one or more fastening mechanisms.

[0098] A method for operatively flowing cooling air through a deflector assembly of a burner. The method includes flowing cooling air through one or more cooling orifices from an upstream surface of the deflector assembly to a downstream surface of the deflector assembly. The method further includes exiting the cooling air at the downstream surface from one or more cooling orifices around one or more fastening mechanisms of the deflector assembly.

[0099] The method according to any one of the preceding clauses further includes causing cooling air to exit one or more cooling holes in a circular pattern around one or more fastening mechanisms.

[0100] The method according to any one of the preceding clauses further includes causing cooling air to exit one or more cooling holes in a semi-circular pattern around one or more fastening mechanisms.

[0101] The method according to any one of the preceding clauses further includes causing cooling air to flow radially through one or more cooling holes relative to one or more fastening mechanisms, and causing the cooling air to exit radially from one or more cooling holes at a downstream surface around one or more fastening mechanisms.

[0102] The method according to any one of the preceding clauses further includes causing cooling air to flow circumferentially through one or more cooling holes relative to one or more fastening mechanisms, and causing the cooling air to exit tangentially from one or more cooling holes at a downstream surface around one or more fastening mechanisms.

[0103] The method according to any one of the preceding clauses further includes generating vortices of cooling air at the downstream surface by means of grooves in one or more cooling holes in the region surrounding one or more fastening mechanisms.

[0104] According to any one of the preceding clauses, the method comprises one or more cooling holes being first cooling holes, the method further comprising causing cooling air to flow through one or more second cooling holes extending through one or more fastening mechanisms, and causing the cooling air to exit the one or more second cooling holes at a downstream surface via one or more fastening mechanisms.

[0105] The method according to any one of the preceding clauses further includes causing cooling air to flow at a downstream surface through one or more slits of the deflector assembly, the one or more slits being located between one or more fastening mechanisms and a central opening of the deflector assembly.

[0106] According to any one of the preceding clauses, in the method, one or more first cooling holes extend through a recessed portion of the deflector assembly, the recessed portion retracting from the downstream surface, and one or more fastening mechanisms extend from the recessed portion such that the one or more fastening mechanisms retract relative to the downstream surface.

[0107] The method according to any one of the preceding clauses further includes allowing cooling air to flow through one or more third cooling holes of one or more pins of the deflector assembly, the one or more pins being positioned around one or more fastening mechanisms.

[0108] While the foregoing description is directed toward preferred embodiments, other variations and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of this disclosure. Furthermore, features described in connection with one embodiment may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A deflector assembly for defining the flow of operating fluid in a burner, characterized in that, The deflector assembly includes: The upstream surface and the downstream surface opposite the upstream surface; One or more fastening mechanisms, each extending through the deflector assembly; and One or more cooling holes extending from the upstream surface through the deflector assembly to the downstream surface, the one or more cooling holes being positioned around the one or more fastening mechanisms to operably guide cooling air around the one or more fastening mechanisms at the downstream surface.

2. The deflector assembly according to claim 1, characterized in that, in, The one or more cooling holes include a plurality of cooling holes positioned in a circular pattern around the one or more fastening mechanisms.

3. The deflector assembly according to claim 1, characterized in that, in, The one or more cooling holes include a plurality of cooling holes positioned in a semi-circular pattern around the one or more fastening mechanisms.

4. The deflector assembly according to claim 1, characterized in that, in, The one or more cooling holes are radially angled relative to the one or more fastening mechanisms to operably guide cooling air radially around the one or more fastening mechanisms at the downstream surface.

5. The deflector assembly according to claim 1, characterized in that, in, The one or more cooling holes are circumferentially angled relative to the one or more fastening mechanisms to operably guide cooling air around the one or more fastening mechanisms at the downstream surface.

6. The deflector assembly according to claim 1, characterized in that, in, The one or more cooling holes include grooves configured to generate vortices of cooling air in the region surrounding the one or more fastening mechanisms on the downstream surface.

7. The deflector assembly according to claim 1, characterized in that, It further includes one or more slits positioned between the one or more fastening mechanisms and the central opening of the deflector assembly to operably guide cooling air through the one or more slits at the downstream surface.

8. The deflector assembly according to claim 7, characterized in that, It further includes one or more pins extending from the upstream surface of the deflector assembly, the one or more pins being positioned between the one or more fastening mechanisms and the one or more slits.

9. The deflector assembly according to claim 1, characterized in that, It further includes one or more pins extending from the upstream surface of the deflector assembly, the one or more pins being positioned around the one or more fastening mechanisms.

10. The deflector assembly according to claim 9, characterized in that, in, Each of the one or more pins includes one or more third cooling holes passing through it to provide cooling air around the one or more fastening mechanisms at the downstream surface.

Images