Turbomachinery Impingement Cooling Module

Abstract

To provide an improved system for cooling turbomechanical combustors. [Solution] An impingement module (200) for localized cooling of a high-temperature gas path component (66) of a turbomachinery (10) includes a plurality of impingement orifices (216). The impingement module is arranged such that the plurality of impingement orifices are oriented toward the outer surface (67) of the high-temperature gas path component. Thus, the impingement module is configured to receive a flow of pressurized air and guide the pressurized air through the impingement orifices (216) to collide with the outer surface (67) of the high-temperature gas path component (66).

Description

Technical Field

[0001] The present disclosure generally relates to high temperature gas path components for turbomachinery, such as combustors. More particularly, the present disclosure relates to systems for cooling such components. The invention claimed herein relates to the subject matter recited in the appended claims.

Background Art

[0002] Turbomachinery is utilized in various industries and applications for energy transfer purposes. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of the working fluid entering the gas turbine engine and supplies this compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed within the combustion section and burned within a combustion chamber to produce high pressure and high temperature combustion gases. The combustion gases flow from the combustion section to the turbine section, where they expand to produce work. For example, the expansion of the combustion gases in the turbine section can rotate a rotor shaft connected to, for example, a generator to produce electricity. The combustion gases then exit the gas turbine through the exhaust section.

[0003] In many turbomachinery combustors, the combustion gases pass through a high temperature gas path at least partially defined by a combustion liner that extends downstream from a fuel nozzle and terminates at an inlet to the turbine section towards the inlet of the turbine section of the gas turbine engine. Thus, the high combustion gas temperature within the turbine section generally corresponds to a greater heat and kinetic energy transfer between the combustion gases and the turbine, thereby improving the overall output of the turbomachinery. However, the high combustion gas temperature can cause erosion, creep, and / or low cycle fatigue in various components of the combustor, thereby potentially limiting the overall durability of the combustor.

[0004] Therefore, turbomachinery components located along high-temperature gas paths, such as combustion liners, need to be cooled. For example, cooling of a combustion liner is typically achieved by delivering a cooling medium, such as compressed working fluid from the compressor section, through a cooling flow annular section or channel defined between the liner and the flow sleeve and / or impingement sleeve surrounding the liner. For example, the flow of the cooling medium in the channel between the liner and the sleeve can be turbulent, and therefore the contact between the cooling medium and the high-temperature gas path surface to be cooled, e.g., the outer surface of the combustion liner, is inconsistent in direction and / or duration. Thus, such cross-flow or turbulence can result in reduced cooling of the high-temperature gas path surface. In addition, variations in the flow and / or concentration of high-temperature combustion gases, as well as variations in the structure of the high-temperature gas path components (for example, if a portion of the high-temperature gas path component is downwind of other components, such as on the leeward side of a multi-staged fuel injector in the axial direction), can lead to localized heat concentration, e.g., the occurrence of hot spots, where the temperature of the high-temperature gas path component can be significantly higher than that of adjacent areas.

[0005] Therefore, improved systems for cooling turbomechanical combustors are desired in the art. In particular, systems that provide localized cooling at one or more hot spots and / or impingement cooling with a controlled, uniform flow to minimize or avoid cross-flows would be useful. [Overview of the project]

[0006] The inventions claimed herein relate to the subject matter described in the claims. The aspects and advantages of the systems described herein are partially described in the following description, may become apparent from the description, or can be learned through the practice of the art.

[0007] According to one embodiment, a turbomachinery is disclosed. The turbomachinery includes a compressor, a combustor, and a turbine downstream of the combustor. The compressor extends from an intake to a discharge. The discharge of the compressor directly supplies a flow of high-pressure air to a high-pressure plenum defined within the outer casing of the turbomachinery. The combustor includes a head end, a liner that at least partially defines a hot gas path, a flow sleeve that circumferentially surrounds at least a portion of the liner, and an impingement module. The flow sleeve is separated from the liner to form a cooling flow annular section between the liner. The cooling flow annular section is in fluid communication with the high-pressure plenum, thereby allowing air from the high-pressure plenum to flow into the cooling flow annular section and from the cooling flow annular section to the head end. The impingement module extends into the cooling flow annular section with a plurality of impingement orifices oriented toward the outer surface of the liner. Therefore, the impingement module is configured to guide the airflow from the high-pressure plenum through the impingement orifice so that it strikes the outer surface of the liner.

[0008] According to another embodiment, an impingement module for cooling high-temperature gas path components of a turbomachinery is disclosed. The impingement module has a plurality of impingement orifices. The impingement module is arranged such that the plurality of impingement orifices are directed toward the surface of the high-temperature gas path components. Thus, the impingement module is configured to receive a flow of pressurized air and guide the pressurized air through the impingement orifices so as to collide with the surface of the components.

[0009] In a further embodiment, a flow sleeve for a combustor is disclosed. The combustor includes a liner that at least partially defines a hot gas path. The flow sleeve is configured to be attached to the combustor so that it surrounds at least a portion of the liner circumferentially and is separated from the liner so that it forms a cooling flow annular section between the liner. The flow sleeve includes a feed pipe extending inward toward the liner and an impingement module coupled to the feed pipe. The impingement module has a plurality of impingement orifices. The impingement module is positioned such that the plurality of impingement orifices are directed toward the outer surface of the liner. Thus, the impingement module is configured to guide an airflow through the impingement orifices to impact the outer surface of the liner.

[0010] These and other features, aspects, and advantages of this assembly will be better understood by referring to the following description and the appended claims. The appended drawings are incorporated herein and constitute part of this specification and illustrate embodiments of the art and, together with the description, help to illustrate the principles of the art.

[0011] A full and implementable disclosure of the System, including best modes of fabrication and use of the Assembly, directed to those skilled in the art, is described herein with reference to the accompanying drawings. [Brief explanation of the drawing]

[0012] [Figure 1] This is a schematic diagram of a turbomachinery according to an exemplary embodiment of the present disclosure. [Figure 2] This shows a cross-sectional side view of a portion of an exemplary turbomachine, including an exemplary combustor, which may encompass various embodiments of the present disclosure. [Figure 3] The image shows a cross-sectional perspective view of a portion of a combustor for a turbomachinery, including an impingement cooling module, according to one or more exemplary embodiments of the present disclosure. [Figure 4]The image shows a cross-sectional view of a portion of a combustor equipped with an impingement cooling module for use in a turbomachinery, according to one or more exemplary embodiments of the present disclosure. [Figure 5] Figure 4 provides an enlarged view of the impingement module from a portion of the combustor shown. [Figure 6] The image shows perspective views of multiple impingement modules arranged around the combustor liner for a turbomachinery (without flow sleeves) according to one or more additional exemplary embodiments of the present disclosure. [Figure 7] Figure 6 provides a view looking upstream from the rear end of the liner. [Figure 8] A side view of the liner is provided in Figure 6. [Figure 9] Figure 1 shows a perspective view of an impingement module according to one or more exemplary embodiments of the present disclosure, which may be incorporated into a turbomachinery such as the exemplary turbomachinery shown. [Figure 10] Figure 9 provides a partial cross-sectional perspective view of the impingement module. [Figure 11] Figure 9 provides another cross-sectional perspective view of the impingement module shown. [Figure 12] The image shows an end view of another exemplary embodiment of an impingement module for a turbomachinery, according to one or more additional exemplary embodiments of the present disclosure. [Figure 13] The image shows an end view of yet another exemplary embodiment of an impingement module for a turbomachinery, according to one or more additional exemplary embodiments of the present disclosure. [Modes for carrying out the invention]

[0013] Hereinafter, embodiments of the System are given in detail, one or more examples of which are shown in the drawings. Each example is provided for illustrative purposes of the Art and is not intended to limit the Art. Indeed, it will be apparent to those skilled in the art that modifications and changes can be made in the Art without departing from the scope or spirit of the claimed Art. For example, features illustrated or described as part of one embodiment can also be used in conjunction with another embodiment to bring about further embodiments. Thus, this disclosure is intended to include modifications and changes that fall within the scope of the appended claims and their equivalents.

[0014] Detailed descriptions use numerals and letters to refer to features in the drawings. Similar or identical reference numerals in the drawings and descriptions are used to refer to similar or identical parts of the invention. As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to imply the location or importance of any individual component.

[0015] As used herein, the terms “upstream” (or “forward”) and “downstream” (or “backward”) refer to relative directions of fluid flow in a fluid path. For example, “upstream” refers to the direction from which the fluid has flowed, and “downstream” refers to the direction from which the fluid has flowed. The term “radially” refers to a relative direction substantially perpendicular to the axial centerline of a particular component; the term “axially” refers to a relative direction substantially parallel and / or coaxial with the axial centerline of a particular component; and the term “circumferentially” refers to a relative direction extending around the axial centerline of a particular component. Approximate terms such as “generally” or “about” include values ​​within plus or minus 10 percent of the stated value. When used in the context of angles or directions, such terms include values ​​within plus or minus 10 degrees of the stated angle or direction. For example, “generally perpendicular” includes directions within 10 degrees from perpendicular, e.g., clockwise or counterclockwise.

[0016] Referring now to the drawings, FIG. 1 shows a schematic view of one embodiment of a turbomachine, which in the illustrated embodiment is a gas turbine engine 10. Although industrial or land-based gas turbines are shown and described herein, the present disclosure is not limited to industrial or land-based gas turbines unless specifically recited in the claims. For example, the systems described herein can be used in any type of turbomachine including, but not limited to, steam turbines, aircraft gas turbines, or marine gas turbines.

[0017] As shown, the gas turbine engine 10 generally includes an inlet section 12, a compressor section 14 disposed downstream of the inlet section 12, a plurality of combustors 50 (one example of which is shown in FIG. 2) within a combustor section 16 disposed downstream of the compressor section 14, a turbine section 18 (e.g., an expansion turbine section) disposed downstream of the combustor section 16, and an exhaust section 20 disposed downstream of the turbine section 18. Additionally, the gas turbine engine 10 may include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18.

[0018] The compressor section 14 may generally include a plurality of rotor disks 24 (one of which is shown) and a plurality of rotor blades 26 extending radially outward from each rotor disk 24 and connected to each rotor disk 24. Each rotor disk 24 may then be coupled to a portion of the shaft 22 extending through the compressor section 14 or may form a portion of the shaft 22.

[0019] The turbine section 18 can generally include a plurality of rotor disks 28 (one of which is shown) and a plurality of rotor blades 30 that extend radially outward from each rotor disk 28 and are interconnected to each rotor disk 28. Each rotor disk 28 may then be coupled to a portion of a shaft 22 that extends through the turbine section 18 or may form a portion of the shaft 22. The turbine section 18 further includes an outer casing 31 that circumferentially surrounds a portion of the shaft 22 and the rotor blades 30, thereby at least partially defining a hot gas path 32 through the turbine section 18.

[0020] During operation, an operating fluid such as air flows into the compressor section 14 through the inlet section 12, and the air is gradually compressed in the compressor section 14, so that pressurized air is supplied to the combustors of the combustor section 16. The pressurized air is mixed with fuel and burned in each combustor to produce combustion gas 34. The combustion gas 34 flows from the combustor section 16 into the turbine section 18 through the hot gas path 32, where energy (kinetic and / or thermal) is transferred from the combustion gas 34 to the rotor blades 30, causing the shaft 22 to rotate. The mechanical rotational energy can then be used to drive the compressor section 14 and / or to generate electrical power. The combustion gas 34 exiting the turbine section 18 can be discharged from the gas turbine engine 10 via the exhaust section 20.

[0021] Figure 2 provides a cross-sectional side view of a portion of an exemplary gas turbine engine 10, including an exemplary combustor 50, which may be, for example, one of several cannula-type combustors provided in the combustor section 16 shown in Figure 1 and described above. The illustrated exemplary combustor 50 may encompass various embodiments of the present disclosure. As illustrated, the combustor 50 is at least partially surrounded by an outer casing 52 (such as a compressor discharge casing 54 located downstream of the compressor 14) and / or an outer turbine casing 56. The outer casing 52 is in fluid communication with the compressor 14 and at least partially defines a high-pressure plenum 58 that surrounds at least a portion of the combustor 50. An end cover 60 is coupled to the outer casing 52 at one end of the combustor 50.

[0022] As shown in Figure 2, the combustor 50 generally includes at least one axially extending fuel nozzle 62 extending downstream from the end cover 60, an annular cap assembly 64 extending radially and axially within the outer casing 52 downstream from the end cover 60, an annular hot gas path duct or combustion liner 66 extending downstream from the cap assembly 64, and an annular flow sleeve 68 surrounding at least a portion of the combustion liner 66. The combustion liner 66 defines a hot gas path 70 for delivering combustion gases 34 through the combustor 50 (the hot gas path 70 may be continuous with, for example, the hot gas path 32 in the turbine section 18 described above). The combustor section hot gas path 70 and the turbine section hot gas path 32 may also collectively define the overall hot gas path of the turbine engine 10. The end cover 60 and the cap assembly 64 define at least partially the head end plenum 72 of the combustor 50.

[0023] The cap assembly 64 generally includes a front end 74 located downstream of the end cover 60, a rear end 76 located downstream of the front end 74, and one or more annular shrouds 78 extending at least partially between them. The combustion liner 66 defines a combustion chamber 86 within the combustor 50, and the combustion chamber 86 is bounded at its front end by a cap plate defining the rear end 76 of the cap assembly 64. In certain embodiments, an axially extending fuel nozzle 62 extends at least partially through the cap assembly 64 to supply a first combustible mixture 80, mainly composed of fuel and a portion of the compressed working fluid 19 from the compressor 14, such as air, to the combustion chamber 86 defined within the combustion liner 66 downstream of the rear end 76 of the cap assembly 64.

[0024] In some embodiments, the combustor 50 may further include one or more radially extending fuel injectors 84 (also known as axial multi-stage fuel injectors or downstream lean fuel injectors) extending through the flow sleeve 68 and combustion liner 66 at a point downstream of at least one axially extending fuel nozzle 62.

[0025] As shown in the exemplary embodiment of Figure 2, the combustion liner 66 extends downstream to the rear frame 130, where it terminates. A mounting bracket 131 may be coupled to the rear frame 130. In some embodiments, the rear frame 130 and / or the mounting bracket 131 may be coupled to the outer turbine casing 56, and a mounting flange 112 may be connected to the compressor discharge casing 54. In other embodiments (not shown), the combustion liner 66 may be integrated with the first-stage turbine nozzle in a structure that may be known as an integrated outlet component or transition nozzle.

[0026] For example, as seen in Figures 2 and 3, the flow sleeve 68 can surround at least a portion of the liner 66 circumferentially, and the flow sleeve 68 may be separated from the liner 66 to form a cooling flow annular section 90 (Figure 3) between the liner 66. The compressed working fluid 19 (Figure 2) from the compressor discharge plenum 58 flows along the outside of the liner 66 through the cooling flow annular section 90 to supply convective cooling to the liner 66, and can be redirected to flow through the head end plenum 72 and the axially extending fuel nozzle 62 (Figure 2).

[0027] In some embodiments, one or more impingement modules 200 may be provided, for example, as shown in Figure 3. The impingement modules 200 may be provided in any suitable number and / or locations as desired to provide impingement cooling to the surface of the hot gas path component, such as the outer surface 67 of the liner 66. For example, in some embodiments, multiple impingement modules 200 may be provided over all or most of the liner 66. In additional embodiments, the impingement modules 200 may be provided in more limited areas, for example, to provide localized cooling in one or more hot spots within the component to be cooled, for example, in the liner 66. In embodiments where localized cooling is provided, the impingement modules 200 may be provided, for example, individually or in groups of two, three, or four impingement modules 200, as needed, depending on the location and size of the hot spot.

[0028] When two or more impingement modules 200 are provided, adjacent impingement modules 200 can be superimposed, and each impingement module 200 may include an extension or flap that can be positioned to contact, for example, the corresponding flap of the nearest adjacent impingement module 200, and to overlap with it, as shown in Figures 3, 4, and 5. In additional embodiments, the impingement modules 200 may be spaced apart from each other, or may not be in direct contact with each other.

[0029] For example, as seen in Figures 3, 4, and 5, the impingement module 200 (or, if more than one impingement module is provided, each impingement module 200) may extend to the cooling flow annular section 90, for example, the impingement module 200 may extend from the flow sleeve 68 toward the liner 66, for example, from the flow sleeve 68 toward the cooling flow annular section 90, without contacting the liner 66. Thus, the impingement module 200 can supply a cooling medium, for example, a flow of air from the compressor discharge plenum 58, to the liner 66 of the combustor 50 by directly impacting it at a specific location. The impingement module 200 may be used in various parts or sections of the turbomachinery 10. For example, the impingement module 200 may be positioned in close proximity to any surface of a component to be cooled, such as a hot gas path component, to cool such a surface. When the impingement module 200 is positioned in such a manner and connected to a source of pressurized air (and / or other cooling medium) with a pressure difference sufficient (i.e., sufficiently large) to allow an impingement flow through the impingement module 200, the impingement module 200 provides localized impingement cooling to the surface of the component. Thus, the description herein of cooling the liner 66 is merely one example of the many possible implementations for the impingement module 200, and it will be understood that the impingement module 200 can be used, for example, with any high-temperature gas path component to provide cooling to the surface of such component.

[0030] For example, as seen in Figures 3, 4, and 5, the impingement module 200 is generally defined between a supply pipe 202 and one or more impingement orifices 216, so that the cooling medium flows into the impingement module 200 at the inlet 204 of the supply pipe 202 and exits the impingement module 200 at one or more impingement orifices 216 positioned in close proximity to and directed toward the surface to be cooled, such as the outer surface 67 of the liner 66.

[0031] The supply pipe 202 may be generally oriented radially, for example, generally along a direction perpendicular to the longitudinal axis of the component to be cooled, such as the combustion liner 66, and may extend from an inlet 204 to an outlet 206. In some embodiments, the inlet 204 of the supply pipe 202 may be coplanar with the outer surface 69 of the flow sleeve 68. The outlet 206 of the supply pipe 202 may be coupled to the body of the impingement module 200, thereby allowing the cooling medium to flow directly into the internal plenum within the impingement module 200 via the supply pipe 202. For example, the impingement module 200 may include a distribution channel 208 that overlaps on and is in fluid communication with the multiple impingement orifices 216 to facilitate uniform distribution of the cooling medium flow among the multiple impingement orifices 216, and the outlet 206 of the supply pipe 202 may be directly coupled to the distribution channel 208. For example, the distribution channel 208 may include a collar 210, and the outlet 206 of the supply pipe 202 may be received by the collar 210 of the distribution channel 208.

[0032] The distribution channel 208 may be provided in a variety of shapes, for example, it may be elongated as shown in the figure, or it may be rounded, for example, circular, oval, and / or dome-shaped, or it may be any other suitable shape that spans multiple impingement orifices 216 (for example, the shape of the distribution channel 208 may vary depending on the number and arrangement of the impingement orifices 216). The distribution channel 208 may include an internal volume, the internal volume of the distribution channel 208 may define a distribution plenum 212 within the impingement module 200, at least in part.

[0033] In some embodiments, the cooling medium may flow directly from the distribution plenum 212 to one or more impingement orifices 216. In additional embodiments, the impingement orifices 216 may be located within and along one or more impingement channels 214, for example, as shown. The number of impingement orifices 216 within each impingement channel 214 may vary, such as at least two impingement orifices 216 per impingement channel 214 and up to four impingement orifices 216 per impingement channel 214. For example, by providing four or fewer impingement orifices 216 per impingement channel 214, cross-flow between impingement orifices 216 within the same impingement channel 214 can be reduced or eliminated. In such embodiments, the distribution channel 208 and the distribution plenum 212 may extend across each of the impingement channels 214 (for example, if two or more impingement channels 214 are provided). For example, in some embodiments, the distribution channel 208 may be generally perpendicular to the impingement channel 214. For example, the distribution channel 208 may be generally oriented circumferentially, for example, the longitudinal axis of the distribution channel 208 may be generally parallel to the circumferential direction extending around the liner 66, and the impingement channel 214 may be generally oriented axially, for example, the longitudinal axis of each impingement channel 214 may be generally parallel to the central axis of the liner 66 and / or the direction of combustion gas flow through the liner 66.

[0034] The impingement module 200 may be positioned close to the surface to be cooled, for example, the outer surface 67 of the liner 66, such that each impingement orifice 216 is spaced a certain distance, for example, a height Z (Figure 5), from the surface to be cooled. In some embodiments, the height Z at some impingement orifices 216 may differ from the height Z at other impingement orifices 216, as seen, for example, in Figure 5, and the impingement module 200 is generally linear, while the liner 66 is curved. In additional embodiments, the impingement module 200 may be curved in one or more directions (for example, axially and / or circumferentially) to match the outer shape of the surface to be cooled, so that the height Z at each impingement orifice 216 may be generally the same, as seen, for example, in Figures 6, 7, 8, 12, and 13. For example, the curvature of the high-temperature gas path components to be cooled may vary, for example, the high-temperature gas path components are combustion liners such as the exemplary combustion liner 66 shown in Figures 6 to 8. For example, the curvature of the high-temperature gas path component, for example, the liner 66, may vary along the longitudinal dimension of the high-temperature gas path component from the rear end to the front end. In such embodiments, for example, multiple impingement modules may be provided with varying degrees of curvature from one impingement module to another in order to complement the various curvatures of the high-temperature gas path components and thereby maintain a generally constant height Z. For example, as shown in Figure 12, some impingement modules may have a relatively high degree of curvature (small radius), while other impingement modules may have a relatively low degree of curvature (large radius) to complement the various curvatures of the high-temperature gas path components to be cooled, for example, as shown in Figure 13. In various embodiments, each impingement orifice 216 is located at the bottom surface of the impingement channel 214 closest to the outer surface 67 of the combustion liner 66.

[0035] The impingement orifices 216 may be sized to supply a jet of cooling medium, for example, the impingement orifices 216 may have a relatively small cross-sectional area to supply a faster flow of cooling medium to the surface to be cooled. For example, the impingement orifices 216 may be cylindrical, for example, each having a circular cross-section, and the diameter D of each impingement orifice 216 (Figure 5) may be sized to supply such a flow. Each impingement orifice 216 may have approximately the same diameter D. The impingement module 200 may be sized and arranged such that the ratio of the height Z at each impingement orifice 216 to the diameter D of each impingement orifice 216 (e.g., height across diameter, or Z / D) is about 1 to about 5, for example, about 2 to about 4, for example, about 3 or about 3.5. For example, in embodiments where the impingement module 200 is not precisely parallel to the surface to be cooled, as shown in Figure 5, for example, the Z / D ratio may be smaller in some impingement orifices 216 and larger in other nearby impingement orifices 216 of the impingement module 200, with each instance of the Z / D ratio falling within the range described above, for example, Z / D may be 3 in one impingement orifice 216 and 3.5 in another impingement orifice 216.

[0036] Each impingement channel 214 may include the surface of the impingement module 200 closest to the bottom surface, for example, the surface to be cooled. The impingement module 200 may have one or more return channels 218 (Figure 4) formed between adjacent impingement channels 214. The number of impingement channels 214 and return channels 218 can vary, including, but not limited to, two impingement channels 214 with one return channel 218 in between, three impingement channels 214 with two return channels 218 in between, five impingement channels 214 with four return channels 218 in between, and up to eight impingement channels 214 with seven return channels 218, for example, as shown, four impingement channels 214 and three return channels 218, five impingement channels 214 with four return channels 218 in between, and so on.

[0037] For example, the bottom of the impingement module 200 may be corrugated, as shown in the figure, so that impingement channels 214, particularly impingement orifices 216 defined at the bottom of each impingement channel 214, can extend below the return channels 218. That is, the return channels 218 can be formed between and above adjacent impingement channels 214 (radially outward). Thus, during operation, the cooling medium can flow from the impingement module 200 through the impingement orifices 216, collide with the surface 67 to be cooled, thereby absorbing thermal energy from the surface 67 (e.g., cooling), and then, after absorbing thermal energy, the cooling medium can rise (e.g., by convection) and flow away from the surface 67, for example, in a direction generally opposite to the impingement cooling flow from the impingement orifices 216 of the impingement module 200. Therefore, the return channel 218 above the impingement orifice 216 provides a passage for such a return flow of heated air (and / or other medium) that is separated from and away from the impingement cooling flow from the impingement orifice 216, thereby avoiding or reducing cross-flow between the impingement jet from the impingement orifice 216 and the warmer return air. In this way, the impingement flow remains directed generally directly and generally perpendicularly from the impingement orifice 216 to the surface. In addition, by separating adjacent impingement channels 214 from each other by the return channel 218 between them, cross-flow between the impingement orifices 216 of adjacent impingement channels 214 can be avoided or reduced.

[0038] As shown in Figures 9 and 10, the impingement module 200 may include two collars 210 coupled to their respective supply pipes 202. The impingement module 200 further includes a pair of distribution channels 208 that distribute cooling air to the impingement channels 214. As shown in Figures 6 to 8, the distribution channels 208 generally extend circumferentially, and the impingement channels 214 generally extend axially, with the circumferential and axial directions being relative to the longitudinal axis of the combustor 50. To facilitate the installation of impingement modules 200 and adjacent impingement modules 200 (as shown in Figures 6 to 8), the first peripheral edge 232 of the first impingement module 200 may be oriented upward (i.e., extending radially outward from the longitudinal axis of the combustor 50) so that it overlaps with the second peripheral edge 234 of the second impingement module 200 which is circumferentially adjacent to the first impingement module 200, and the opposite second peripheral edge 234 may be oriented downward (i.e., extending radially inward toward the longitudinal axis of the combustor 50). Alternatively, or in addition, the first axial edge 242 of the first impingement module 200 may be oriented upward, and the second axial edge 244 may be oriented downward, such that the first axial edge 242 of the first impingement module 200 overlaps with the second axial edge 244 of the second impingement module 200 which is axially adjacent to the first impingement module 200.

[0039] Figure 11 provides a bottom perspective view of the impingement module 200, showing an exemplary number and arrangement of impingement orifices 216. While each impingement channel 214 is shown with two impingement orifices 216, it should be understood that other numbers of impingement orifices 216 may be used instead, including arrangements in which the impingement orifices 216 are asymmetrically spaced within one impingement channel 214 compared to another impingement channel 214, or in which the number is asymmetrical. In Figure 11, the impingement module 200 is shown with a single collar 210 and its respective supply pipe 202, as an alternative to embodiments having two collars 210 as shown in Figures 9 and 10.

[0040] This specification discloses the invention in best mode and uses examples to enable those skilled in the art to practice the invention, including the manufacture and use of any device or system, and the execution of any incorporated method. The scope of the invention claimed herein is defined by the appended claims and may include other examples conceivable by those skilled in the art.

[0041] Further aspects of the present invention are provided by the subject matter of the following clauses.

[0042] A turbomachinery comprising a compressor extending from an intake to a discharge section, the discharge section of which supplies a flow of high-pressure air directly to a high-pressure plenum defined within an outer casing of the turbomachinery; a combustor at least partially enclosed by the outer casing; and a turbine downstream of the combustor, the combustor comprising a head end; a liner at least partially defining a high-temperature gas path; and a flow sleeve circumferentially surrounding at least a portion of the liner, the flow sleeve being separated from the liner to form a cooling flow annular section between the liner and the cooling flow A turbomachinery in which an annular section is in fluid communication with a high-pressure plenum, and air from the high-pressure plenum flows into the cooling flow annular section and from the cooling flow annular section to the head end, and an impingement module is provided with a plurality of impingement orifices, and the impingement module extends into the cooling flow annular section with the plurality of impingement orifices directed toward the outer surface of the liner, thereby the impingement module is configured to guide the airflow from the high-pressure plenum through the impingement orifices so as to collide with the outer surface of the liner.

[0043] The impingement module comprises a supply pipe, the supply pipe extending at least partially through a flow sleeve, thereby the inlet of the supply pipe being positioned and directed to receive airflow from a high-pressure plenum, as described in one or more of these clauses.

[0044] The supply pipe inlet is coplanar with the outer surface of the flow sleeve in one or more of the systems described in these clauses.

[0045] An impingement module comprises multiple impingement channels, and multiple impingement orifices are defined in the impingement channels, as described in one or more of these clauses.

[0046] The impingement module is a system according to one or more of these clauses, further comprising one or more return channels defined between adjacent impingement channels among a plurality of impingement channels.

[0047] One or more return channels are located above multiple impingement orifices in the system described in one or more of these clauses.

[0048] An impingement module is a system described in one or more of these clauses, comprising distribution channels upstream of multiple impingement orifices.

[0049] A system according to one or more of these clauses, in which each impingement orifice of a plurality of impingement orifices is spaced a certain height away from the outer surface of the liner, each impingement orifice of the plurality of impingement orifices defines a diameter, and the height at each impingement orifice is between 1 and 5 times the diameter of each impingement orifice.

[0050] An impingement module comprising multiple impingement channels, wherein multiple impingement orifices are evenly distributed among the impingement channels, as described in one or more of these clauses.

[0051] The impingement module comprises a distribution channel, the distribution channel is upstream of a plurality of impingement channels, the plurality of impingement channels are generally parallel to one another, and the distribution channel is generally oriented perpendicular to the plurality of impingement channels, according to one or more of these clauses of the system.

[0052] The impingement module comprises a supply pipe coupled to a distribution channel, the supply pipe extending at least partially from the distribution channel through a flow sleeve, as described in one or more of these clauses.

[0053] Further aspects of the present invention are provided by the subject matter of the following clauses.

[0054] An impingement module for localized cooling of a hot gas path component of a turbomachinery, comprising multiple impingement orifices, wherein the impingement module is arranged such that the multiple impingement orifices are oriented toward the outer surface of the hot gas path component, thereby the impingement module is configured to receive a flow of pressurized air and guide the pressurized air through the impingement orifices to collide with the outer surface of the component.

[0055] The system described in one or more of these clauses further comprises a supply pipe, the inlet of which is positioned and directed to receive a flow of pressurized air.

[0056] A system further comprising multiple impingement channels, wherein multiple impingement orifices are defined in the impingement channels, as described in one or more of these clauses.

[0057] A system according to one or more of these clauses, further comprising one or more return channels defined between adjacent impingement channels among a plurality of impingement channels.

[0058] One or more return channels are located above multiple impingement orifices in the system described in one or more of these clauses.

[0059] A system as described in one or more of these clauses, further comprising distribution channels upstream of multiple impingement orifices.

[0060] Further aspects of the present invention are provided by the subject matter of the following clauses.

[0061] A flow sleeve for a combustor, wherein the combustor comprises a liner that defines at least partially a hot gas path, the flow sleeve is configured to be attached to the combustor so as to surround at least a portion of the liner circumferentially and is separated from the liner so as to form a cooling flow annular portion between the liner, the flow sleeve comprises a supply pipe extending inward toward the liner and an impingement module coupled to the supply pipe, the impingement module comprising a plurality of impingement orifices, the impingement module being positioned such that the plurality of impingement orifices are oriented toward the outer surface of the liner, the impingement module being configured to guide an airflow through the impingement orifices so as to collide with the outer surface of the liner.

[0062] An impingement module comprises multiple impingement channels, and multiple impingement orifices are defined in the multiple impingement channels, as described in one or more of these clauses.

[0063] A system according to one or more of these clauses, in which each impingement orifice of a plurality of impingement orifices is spaced a certain height away from the outer surface of the liner, each impingement orifice of the plurality of impingement orifices defines a diameter, and the height at each impingement orifice is between 1 and 5 times the diameter of each impingement orifice. [Explanation of Symbols]

[0064] 10. Gas turbine engines, turbine engines, turbomachinery 12 Entrance Section 14 Compressor section, compressor 16. Combustor Section 18. Turbine section, turbine 19 Working fluid 20 Exhaust Section 22 shafts 24 Rotor Discs 26 rotor blades 28 Rotor Discs 30 rotor blades 32 High-temperature gas pathway 34 Combustion gases 50 Combustors 52 Outer casing 54 Compressor discharge casing 56. Outer turbine casing 58 High-pressure plenum, compressor discharge plenum 60 End cover 62 Fuel Nozzle 64 Cap Assembly 66 Combustion liner, liner, high-temperature gas path components 67 External surface, surface 68 Flow Sleeve 69 Exterior 70 High-temperature gas pathway 72 Headend Plenum 74 Front end 76 Rear end 78 Ring Shroud 80. First flammable mixture 84 Fuel Injector 86 Combustion Chamber 90 Cooling flow annular section 112 Mounting flange 130 Rear frame 131 Mounting bracket 200 impingement module, first impingement module, second impingement module 202 Supply pipe 204 Entrance 206 Exit 208 distribution channels 210 Colors 212 Distribution Plenum 214 Impingement Channels 216 Impingement orifice 218 Return Channel 232 First peripheral portion 234 Second peripheral area 242 First axial edge 244 Second axial edge D diameter Z Height

Claims

1. An impingement module (200) for localized cooling of a high-temperature gas path component (66) of a turbomachinery (10), wherein the impingement module (200) is An impingement module (200) comprising a plurality of impingement orifices (216), wherein the plurality of impingement orifices (216) are arranged such that they are directed toward the surface (67) of the high-temperature gas path component (66), and the impingement module (200) is configured to receive a flow of pressurized air and guide the pressurized air through the plurality of impingement orifices (216) so as to collide with the surface (67) of the high-temperature gas path component (66).

2. The impingement module (200) according to claim 1, further comprising a supply pipe (202), wherein the inlet (204) of the supply pipe (202) is configured to receive the flow of the pressurized air.

3. The impingement module (200) according to claim 1 or 2, further comprising a plurality of impingement channels (214), wherein the plurality of impingement orifices (216) are defined by penetrating the walls of the plurality of impingement channels (214).

4. The impingement module (200) according to any one of claims 1 to 3, wherein the plurality of impingement orifices (216) are evenly distributed among the plurality of impingement channels (214).

5. The impingement module (200) according to claim 3 or 4, further comprising one or more return channels (218) defined between adjacent impingement channels (214) among the plurality of impingement channels (214).

6. The impingement module (200) according to claim 5, wherein the one or more return channels (218) are positioned above the plurality of impingement orifices (216).

7. The impingement module (200) according to any one of claims 1 to 6, further comprising a distribution channel (208) upstream of the plurality of impingement orifices (216).

8. An impingement module (200) according to claim 7 as dependent on claim 3, or any other claim dependent on claim 3, wherein the plurality of impingement channels (214) are substantially parallel to one another, and the distribution channel (208) is oriented substantially perpendicular to the plurality of impingement channels (214).

9. An impingement module (200) according to claim 7 or 8, as dependent on claim 2, or any other claim dependent on claim 2, wherein the supply pipe (202) is fluidly coupled to the distribution channel (208).

10. A flow sleeve (68) for a combustor (50), wherein the flow sleeve (68) is configured to be attached to the combustor (50) so as to surround at least a portion of the liner (66) of the combustor (50) in a circumferential manner, and the flow sleeve (68) is separated from the liner (66) so as to form a cooling flow annular portion (90) between the liner (66), and the flow sleeve (68) comprises an impingement module (200) according to any one of claims 1 to 9, wherein the impingement module (200) is arranged and configured to guide airflow through an impingement orifice (216) so as to collide with the outer surface (67) of the liner (66) when the flow sleeve (68) is attached to the liner (66).

11. The flow sleeve (68) according to claim 10, wherein the impingement module (200) is positioned radially inward of the flow sleeve (68).

12. The flow sleeve (68) according to claim 10 or 11, wherein the supply pipe (202) extends at least partially through the flow sleeve (68), the impingement module (200) is fluidly coupled to the supply pipe (202), and the supply pipe (202) is in particular the supply pipe for the impingement module according to claim 2, or any other of claims 3 to 8 dependent on claim 2.

13. The flow sleeve (68) according to claim 12, wherein the inlet (204) of the supply pipe (202) is coplanar with the outer surface of the flow sleeve (68).

14. A turbomachinery (10), A compressor (14) extending from an intake to a discharge, wherein the discharge of the compressor (14) is configured to directly supply a flow of high-pressure air to a high-pressure plenum (58) defined within the outer casing (52) of the turbomachinery (10), The combustor (50) is at least partially surrounded by the outer casing (52), The turbine (18) downstream of the combustor (50) and The combustor is equipped with, Head end and A liner (66) that at least partially defines the high-temperature gas path (32), A flow sleeve (68) according to any one of claims 10 to 13 surrounds at least a portion of the liner (66) in the circumferential direction. The flow sleeve (68) is separated from the liner (66) to form a cooling flow annular portion (90) between the liners (66), the cooling flow annular portion (90) is in fluid communication with the high-pressure plenum (58), and the cooling flow annular portion (90) is arranged and configured to provide airflow from the high-pressure plenum (58) to the cooling flow annular portion (90) and from the cooling flow annular portion (90) to the head end. Turbomachinery (10), an impingement module (200) having a plurality of impingement orifices (216) extending to the cooling flow annular portion (90) with the liner (66) facing the outer surface (67), thereby the impingement module (200) is arranged and configured to guide the airflow from the high-pressure plenum (58) through the plurality of impingement orifices (216) to collide with the outer surface (67) of the liner (66).

15. The turbomachinery (10) according to claim 14, wherein each of the plurality of impingement orifices (216) is spaced apart from the outer surface (67) of the liner (66) by a height (Z), each of the plurality of impingement orifices (216) defines a diameter (D), and the height (Z) of each impingement orifice (216) is 1 to 5 times the diameter (D) of each impingement orifice (216).

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