IMPACT COOLING MODULES FOR TURBOMACHES

Abstract

A baffle module (200) for localized cooling of a hot gas path component (66) of a turbomachine (10) includes a plurality of baffle openings (216). The baffle module is positioned such that the plurality of baffle openings are directed towards an outer surface (67) of the hot gas path component. Thus, the baffle module is configured to receive a compressed air flow and direct the compressed air through the baffle openings (216) to impinge on the outer surface (67) of the hot gas component (66).

Description

AREA

[0001] The present disclosure relates generally to hot gas path components, e.g., combustion chambers, for turbomachinery. In particular, the present disclosure relates to systems for cooling such components. The invention claimed herein relates to the subject matter set out in the accompanying claims. STATE OF THE ART

[0002] Turbomachinery is used in a variety of industries and applications for power transmission. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section progressively increases the pressure of a working fluid entering the gas turbine engine and delivers this compressed working fluid to the combustion section. The compressed working fluid and a fuel (e.g., natural gas) mix within the combustion section and burn in a combustion chamber to produce combustion gases at high pressure and temperature. The combustion gases flow from the combustion section into 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, which, for example,It is connected to a generator to produce electricity. The combustion gases then leave the gas turbine via the exhaust section.

[0003] In many turbomachinery combustion chambers, combustion gases are routed to the turbine inlet of the gas turbine engine through a hot gas path, which is at least partially defined by a combustion lining extending downstream from a fuel nozzle and terminating at the turbine inlet. Accordingly, high combustion gas temperatures in the turbine section generally correspond to greater thermal and kinetic energy transfer between the combustion gases and the turbine, thereby increasing the overall power output of the turbomachine. However, these high combustion gas temperatures can lead to erosion, creep, and / or cyclic fatigue of the various combustion chamber components, thus limiting the overall service life of the combustion chamber.

[0004] Therefore, it is necessary to cool the turbomachine components located along the hot gas path, such as the combustion lining. Cooling of the combustion lining is typically achieved by passing a cooling medium, such as the compressed working fluid from the compressor section, through a cooling flow ring or channel defined between the lining and a flow sleeve and / or an impact sleeve surrounding the lining. The coolant flow in the flow channel, e.g., between the lining and the sleeve, can become turbulent, resulting in uneven contact between the cooling medium and the hot gas path surface to be cooled, e.g., the outer surface of the combustion lining, in terms of direction and / or duration. Such crossflow or turbulent flow can thus lead to reduced cooling of the hot gas path surface.In addition, fluctuations in the flow and / or concentration of high-temperature combustion gases, as well as fluctuations in the structure of the hot gas path components (e.g., such that sections of the hot gas path component are located on the leeward side of other components, such as on the leeward side of axially stepped fuel injection nozzles), can lead to the development of local heat concentrations, e.g., hot spots, where the temperature of the hot gas path component can be significantly higher than in adjacent areas.

[0005] Consequently, there is a need in engineering for an improved system for cooling a turbomachine combustion chamber. In particular, a system that provides localized cooling, e.g., at one or more hotspots, and / or impingement cooling with controlled and uniform flow to minimize or avoid crossflows would be beneficial. SHORT DESCRIPTION

[0006] The invention claimed herein relates to the subject matter set forth in the claims. Aspects and advantages of the system according to the present disclosure are partly set forth in the following description, or may be apparent from the description, or may be determined by a practical implementation of the invention.

[0007] According to one embodiment, a turbomachine is disclosed. The turbomachine comprises a compressor, a combustion chamber, and a turbine downstream of the combustion chamber. The compressor extends from an inlet to an outlet. The compressor outlet provides a high-pressure airflow directly into a high-pressure chamber defined within an outer casing of the turbomachine. The combustion chamber includes a head end, a lining that at least partially defines a hot gas path, a flow sleeve that circumferentially surrounds at least a section of the lining, and an impact module. The flow sleeve is spaced apart from the lining to form a cooling flow ring between them. The cooling flow ring is in fluid communication with the high-pressure chamber, causing air to flow from the high-pressure chamber into the cooling flow ring and from the cooling flow ring to the head end.The impact module extends into the cooling flow ring, with the multitude of impact openings oriented towards an outer surface of the lining. Thus, the impact module is configured to direct an airflow from the high-pressure chamber through the impact openings so that it impacts the outer surface of the lining.

[0008] According to a further embodiment, an impact module for cooling a hot gas path component of a turbomachine is disclosed. The impact module has a plurality of impact openings. The impact module is positioned such that the plurality of impact openings are directed towards a surface of the hot gas path component. Thus, the impact module is configured to receive a compressed air flow and guide the compressed air through the impact openings so that it impacts the surface of the component.

[0009] According to a further embodiment, a flow sleeve for a combustion chamber is disclosed. The combustion chamber includes a lining that defines at least a partial hot gas path. The flow sleeve is configured for mounting on the combustion chamber, whereby the flow sleeve circumferentially surrounds at least a section of the lining, being spaced apart from the lining to form a cooling flow ring between them. The flow sleeve includes a feed pipe extending inward toward the lining and an impact module coupled to the feed pipe. The impact module has a plurality of impact openings. The impact module is positioned such that the plurality of impact openings are directed toward an outer surface of the lining. Thus, the impact module is configured to guide an airflow through the impact openings so that it impacts the outer surface of the lining.

[0010] These and other features, aspects, and advantages of the present arrangements will be better understood with reference to the following description and the accompanying claims. The accompanying drawings, which are integrated into and form part of this patent specification, illustrate embodiments of the technology and, together with the description, serve to explain the principles of the technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] A complete and enabling disclosure of the present system, including its best method of manufacture and use of the present arrangements, which is directed to a person skilled in the art, is set forth in the description which refers to the accompanying figures, wherein: Fig. 1 is a schematic illustration of a turbomachine according to exemplary embodiments of the present disclosure. Fig. 2 illustrates a cross-sectional side view of a section of an exemplary turbomachine, including an exemplary combustion chamber, which may comprise various embodiments of the present disclosure. Fig. Figure 3 illustrates a perspective sectional view of a section of a combustion chamber for a turbomachine, which includes impact cooling modules, according to one or more exemplary embodiments of the present disclosure. Fig. Figure 4 illustrates a sectional view of a section of a combustion chamber with impact cooling modules for use in a turbomachine according to one or more exemplary embodiments of the present disclosure. Fig. 5 an enlarged view of an impact module from the in Fig. 4 provides an illustrated section of the combustion chamber. Fig. 6 illustrates a perspective view of a plurality of impact modules arranged around a lining of a combustion chamber for a turbomachine (omitting a flow sleeve), according to one or more additional exemplary embodiments of the present disclosure. Fig. 7 a view positioned in front of a rear end of the in Fig. 6 illustrated linings are provided. Fig. 8 a side view of the in Fig. 6 illustrated linings are provided. Fig. Figure 9 illustrates a perspective view of an impact module according to one or more exemplary embodiments of the present disclosure, which is incorporated into a turbomachine, such as the exemplary turbomachine of Fig. 1, can be integrated. Fig. 10 a partially cropped perspective view of the in Fig. 9 illustrated impact module provided. Fig. 11 another perspective sectional view of the in Fig. 9 illustrated impact module provided. Fig. 12 illustrates an end view of a further exemplary embodiment of an impact module for a turbomachine according to one or more additional exemplary embodiments of the present disclosure. Fig. Figure 13 illustrates an end view of a further exemplary embodiment of an impact module for a turbomachine according to one or more additional exemplary embodiments of the present disclosure. DETAILED DESCRIPTION

[0012] Reference is now made in detail to embodiments of the present systems, one or more examples of which are illustrated in the drawings. Each example is provided to illustrate the technology, not to limit it. Indeed, it will be obvious to those skilled in the art that modifications and deviations can be made to the present technology without departing from the scope of protection or the spirit of the claimed technology. For example, features illustrated or described as part of one embodiment can be used with another embodiment to produce yet another embodiment. It is therefore intended that the present disclosure covers such modifications and deviations, insofar as they fall within the scope of protection of the accompanying claims and their equivalents.

[0013] In the detailed description, numerical and letter designations are used to refer to features in the drawings. Identical or similar designations in the drawings and the description have been used to refer to identical or similar 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 indicate the location or importance of the individual components.

[0014] In the sense used herein, the terms "upstream" (or "front") and "downstream" (or "backward") refer to the relative direction with respect to fluid flow in a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction in which the fluid flows. The term "radial" refers to the relative direction that is substantially perpendicular to an axial centerline of a given component; the term "axial" refers to the relative direction that is substantially parallel and / or coaxial to an axial centerline of a given component; and the term "circumferential" refers to the relative direction that extends around the axial centerline of a given component. Approximation terms such as "general" or "about" include values ​​within ten percent greater or less than the stated value.When used in the context of an angle or direction, such terms include values ​​within ten degrees greater or lesser than the stated angle or direction. For example, "generally vertical" includes directions within ten degrees vertical in any direction, such as clockwise or counterclockwise.

[0015] Now illustrated with reference to the drawings Fig. 1 A schematic representation of an embodiment of a turbomachine, which in the illustrated embodiment is a gas turbine engine 10. Although an industrial or land-based gas turbine is shown and described herein, the present disclosure is not limited to an industrial and / or land-based gas turbine unless otherwise specified in the claims. For example, the systems described herein may be used in any type of turbomachine, including, but not limited to, a steam turbine, an aircraft gas turbine, or a marine gas turbine.

[0016] As shown, the gas turbine engine 10 generally includes an inlet section 12, a compressor section 14 arranged downstream of the inlet section 12, a plurality of combustion chambers 50 (an example of which is shown in Fig. (as illustrated in Figure 2) within a combustion chamber section 16 arranged downstream of the compressor section 14, a turbine section 18 arranged downstream of the combustion chamber section 16, and an exhaust gas section 20 arranged downstream of the turbine section 18. Additionally, the gas turbine engine 10 can include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18.

[0017] The compressor section 14 can 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 of them. Each rotor disk 24 can in turn be coupled to, or form a section of, the shaft 22 extending through the compressor section 14.

[0018] 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 extending radially outward from each rotor disk 28 and connected to each of them. Each rotor disk 28 can, in turn, be coupled to or form a section of the shaft 22 extending through the turbine section 18. The turbine section 18 further includes an outer casing 31 circumferentially surrounding the section of the shaft 22 and the rotor blades 30, thereby defining at least a part of a hot gas path 32 through the turbine section 18.

[0019] During operation, a working fluid, such as air, flows through the inlet section 12 and into the compressor section 14, where the air is progressively compressed, providing compressed air to the combustion chambers of the combustion chamber section 16. The compressed air is mixed with fuel and burned in each combustion chamber to produce combustion gases 34. The combustion gases 34 flow through the hot gas path 32 from the combustion chamber section 16 into the turbine section 18, where energy (kinetic and / or thermal) is transferred from the combustion gases 34 to the rotor blades 30, causing the shaft 22 to rotate. The mechanical rotational energy can then be used to power the compressor section 14 and / or generate electricity. The combustion gases 34 exiting the turbine section 18 can then be expelled from the gas turbine engine 10 via the exhaust section 20.

[0020] Fig. Figure 2 provides a cross-sectional side view of a section of an exemplary gas turbine engine 10, which includes an exemplary combustion chamber 50, which may be, for example, one of several can-ring combustion chambers that are in the Fig. The combustion chamber section 16 illustrated in Figure 1 and described above is provided. The illustrated exemplary combustion chamber 50 can comprise various embodiments of the present disclosure. As shown, the combustion chamber 50 is at least partially surrounded by an outer casing 52 (such as a compressor outlet 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 chamber 58 that surrounds at least a section of the combustion chamber 50. An end cover 60 is coupled to the outer casing 52 at one end of the combustion chamber 50.

[0021] As in Fig. As shown in Figure 2, the combustion chamber 50 generally includes at least one axially extending fuel nozzle 62 extending downstream of the end cover 60, an annular cap assembly 64 extending radially and axially within the outer casing 52 downstream of the end cover 60, an annular hot gas path channel or combustion lining 66 extending downstream of the cap assembly 64, and an annular flow sleeve 68 surrounding at least a portion of the combustion lining 66. The combustion lining 66 defines a hot gas path 70 for guiding the combustion gases 34 through the combustion chamber 50 (the hot gas path 70 may, for example, be contiguous with the hot gas path 32 described above in the turbine section 18). Furthermore, the combustion section hot gas path 70 and the turbine section hot gas path 32 may together define an overall hot gas path of the turbine engine 10.The end cover 60 and the cap arrangement 64 define at least partially a head end chamber 72 of the combustion chamber 50.

[0022] The cap assembly 64 generally includes a front end 74 positioned downstream of the end cover 60, a rear end 76 arranged downstream of the front end 74, and one or more annular sheaths 78 extending at least partially between them. The combustion lining 66 defines a combustion chamber 86 within the combustion chamber 50, which is bounded at its front end by a cap plate that defines the rear end 76 of the cap assembly 64. In certain embodiments, the axially extending fuel nozzle(s) 62 extend at least partially through the cap assembly 64 to supply a first combustible mixture 80, consisting mainly of fuel and a portion of the compressed working fluid 19, e.g., air, from the compressor 14, to the combustion chamber 86, which is defined within the combustion lining 66 downstream of the rear end 76 of the cap assembly 64.

[0023] In some embodiments, the combustion chamber 50 may further include one or more radially extending fuel injection nozzles 84 (also known as axially stepped fuel injection nozzles or late lean mixture fuel injection nozzles) which extend through the flow sleeve 68 and the combustion lining 66 at a point which is downstream of the at least one axially extending fuel nozzle 62.

[0024] As in the exemplary embodiment in Fig. As shown in Figure 2, the combustion liner 66 extends downstream to and terminates at a rear frame 130. 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 outlet 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 or transition nozzle.

[0025] For example, in the Fig. 2 and Fig. As can be seen in Figure 3, the flow sleeve 68 can surround at least a section of the lining 66, and the flow sleeve 68 can be spaced apart from the lining 66 to allow a cooling flow ring 90 between them ( Fig. 3) to form. The condensed working fluid 19 ( Fig. 2) from the compressor outlet chamber 58 can flow through the cooling flow ring 90 along the outside of the lining 66 to provide convective cooling to the lining 66 before the direction of movement is reversed to flow through the head end chamber 72 and the axially extending fuel nozzle 62 ( Fig. 2) to flow.

[0026] In some embodiments, such as in Fig. As illustrated in Figure 3, one or more impact modules 200 can be provided. The impact modules 200 can be provided in any suitable number and / or position to provide impact cooling to a surface of a hot gas path component, such as an outer surface 67 of the lining 66. For example, in some embodiments, a plurality of impact modules 200 can be provided over all or a large part of the lining 66. In additional embodiments, the impact modules 200 can be provided in more limited areas to provide, for example, localized cooling, e.g., at one or more hotspots in the component to be cooled, such as in the lining 66. In embodiments where localized cooling is provided, the impact module 200 can, for example, be provided individually or in groups of two, three, or four impact modules 200 where required, e.g.,depending on the position and size of the hotspot.

[0027] If more than one impact module 200 is provided, adjacent impact modules 200 can be arranged in an overlapping manner, wherein, for example, each impact module 200 can include extensions or flaps that can be brought into contact with the corresponding flap of the nearest adjacent impact module 200, e.g. by overlapping, as in the Fig. 3, Fig. 4 and Fig. Figure 5 illustrates this. In additional embodiments, the impact modules 200 can be spaced apart from each other or otherwise not in direct contact.

[0028] For example, in the Fig. 3, Fig. 4 and Fig. As can be seen in Figure 5, the impact module 200 (or each impact module 200 if more than one is provided) can extend into the cooling flow ring 90, allowing the impact module 200 to extend from the flow sleeve 68 towards the lining 66, e.g., from the flow sleeve 68 into the cooling flow ring 90, without contacting the lining 66. Thus, the impact module 200 can deliver a coolant flow, e.g., air from the compressor outlet chamber 58, directly to the lining 66 of the combustion chamber 50 at a specific position, causing it to impact. The impact module 200 can be used in various sections or areas of the turbomachine 10. For example, the impact module 200 can be positioned near any surface of a component to be cooled, such as a hot gas path component, to cool that surface.When the impact module 200 is positioned as described and then connected to a compressed air source (and / or another cooling medium) with a sufficient (i.e., sufficiently large) pressure differential to drive the impact flow through the impact module 200, the impact module 200 provides localized impact cooling for the surface of the component. Accordingly, it is understood that the present description of the cooling of the lining 66 is only one example of many possible implementations of the impact module 200 and that the impact module 200 can be used with any hot gas path component, for example, to cool a surface of such a component or components.

[0029] For example, in the Fig. 3, Fig. 4 and Fig. As can be seen in Figure 5, the impact module 200 is generally defined between a supply pipe 202 and one or more impact openings 216, whereby the cooling medium flows into the impact module 200 at an inlet 204 of the supply pipe 202 and exits the impact module 200 at the one or more impact openings 216, which are positioned near and oriented towards the surface to be cooled, e.g. the outer surface 67 of the lining 66.

[0030] The supply pipe 202 can generally be radially oriented, e.g., generally along a direction perpendicular to a longitudinal axis of the component to be cooled, e.g., the combustion lining 66, and extend from the inlet 204 to an outlet 206. In some embodiments, the inlet 204 of the supply pipe 202 can be flush with an outer surface 69 of the flow sleeve 68. The outlet 206 of the supply pipe 202 can be coupled to a main body of the baffle module 200, whereby cooling medium flows directly into an internal chamber within the baffle module 200 via the supply pipe 202. For example, the impact module 200 can include a distribution channel 208 that superimposes several impact openings 216 and is in fluid communication with them to promote a uniform distribution of the coolant flow between the several impact openings 216, and the outlet 206 of the supply pipe 202 can be directly coupled to the distribution channel 208.For example, the distribution channel 208 can include a collar 210, and the outlet 206 of the supply pipe 202 can be incorporated into the collar 210 of the distribution channel 208.

[0031] The distribution channel 208 can be provided in various shapes, e.g., it can be elongated, as illustrated, or it can be rounded, e.g., circular, oblong, and / or dome-shaped, or it can have any other suitable shape extending over several impact openings 216 (e.g., the shape of the distribution channel 208 can vary based on the number and arrangement of the impact openings 216). The distribution channel 208 can include an internal volume, and the internal volume of the distribution channel 208 can at least partially define a distribution chamber 212 within the impact module 200.

[0032] In some embodiments, the cooling medium can flow directly from the distribution chamber 212 to one or more baffle openings 216. In further embodiments, the baffle openings 216 can be arranged in or along one or more baffle channels 214, as illustrated. The number of baffle openings 216 in each baffle channel 214 can vary, from a minimum of two baffle openings 216 per baffle channel 214 to a maximum of four baffle openings 216 per baffle channel 214. For example, providing no more than four baffle openings 216 per baffle channel 214 can reduce or eliminate cross-flow between baffle openings 216 in the same baffle channel 214. In such embodiments, the distribution channel 208 and the distribution chamber 212 can extend over each of the impact channels 214 (e.g., if more than one impact channel 214 is provided).For example, in some embodiments, the distribution channel 208 can generally run perpendicular to the impact channels 214. For example, the distribution channel 208 can generally be oriented circumferentially, such that a longitudinal axis of the distribution channel 208 is generally parallel to a circumferential direction extending around the lining 66, and the impact channels 214 can generally be axially oriented, with, for example, a longitudinal axis of each of the impact channels 214 generally running parallel to a central axis of the lining 66 and / or a flow direction of combustion gases through the lining 66.

[0033] The impact module 200 can be positioned near the surface to be cooled, e.g. the outer surface 67 of the lining 66, so that each impact opening 216 is spaced a distance, e.g. a height Z, from the surface to be cooled ( Fig. 5) In some embodiments, the height Z at some impact openings 216 may differ from the height Z at other impact openings 216, as for example in Fig. Figure 5 shows that the impact modulus 200 is generally linear and the lining 66 is curved. In additional embodiments, the impact modulus 200 can be curved in one or more directions (e.g., axially and / or circumferentially) to conform to the profile of the surface to be cooled, thereby making the height Z at each impact opening 216 generally the same, as shown in the Fig. 6, Fig. 7, Fig. 8, Fig. 12 and Fig. 13 can be seen. For example, the curvature of the hot gas path component to be cooled can vary, e.g., if the hot gas path component is a combustion lining, such as the one shown in the Fig. Figure 6-8 illustrated an exemplary combustion lining 66. For example, the curvature of the hot gas path component, e.g., the lining 66, can vary along a longitudinal extension of the hot gas path component from a rear end to a front end. In such embodiments, a plurality of impact modules can be provided, with different degrees of curvature from one impact module to another, e.g., to complement the varying curvature of the hot gas path component and thereby maintain a generally constant height Z. For example, as shown in Fig. Figure 12 illustrates that some impact modules have a relatively high degree of curvature (small radius), while other impact modules, e.g., as in Fig. Figure 13 illustrates that they have a comparatively low degree of curvature (large radius) to complement the varying curvature of the hot gas path component to be cooled. In various embodiments, each baffle opening 216 is arranged in a lower surface of the baffle channel 214 that is closest to the outer surface 67 of the combustion lining 66.

[0034] The baffle openings 216 can be dimensioned to provide jets of the cooling medium, for example, the baffle openings 216 can have a relatively small cross-sectional area to provide a higher flow velocity of the cooling medium to the surface to be cooled. For example, the baffle openings 216 can be cylindrical, e.g., they can each have a circular cross-section, and the diameter D ( Fig. 5) Each baffle opening 216 can be dimensioned to provide such a flow. The baffle openings 216 can each have approximately the same diameter D. The baffle module 200 can be dimensioned and positioned such that a ratio of the height Z at each baffle opening 216 to the diameter D of the respective baffle opening 216 (e.g., height versus diameter or ZD) between approximately one and approximately five, as between approximately two and approximately four, as between approximately three or approximately three and a half. For example, in embodiments in which the impact modulus 200 is not exactly parallel to the surface to be cooled, as e.g. in Fig. 5 illustrates the relationship ZD at some impact openings 216 may be smaller and at other adjacent impact openings 216 of the impact modulus 200 may be larger, with each example of the ratio ZD lies within the aforementioned areas, so that, for example ZD at one impact opening 216 three (3) and at another impact opening 216 three and a half (3.5) may be.

[0035] The impact channels 214 can each enclose a lower surface, e.g., the surface of the impact module 200 that is closest to the surface to be cooled. The impact channels 218 can each enclose a lower surface, e.g., the surface of the impact module 200 that is closest to the surface to be cooled. The number of impact channels 214 and return channels 218 can vary, such as two impact channels 214 with one return channel 218 between them, three impact channels 214 with two return channels 218 between them, four impact channels 214 and three return channels 218, as illustrated, five impact channels 214 with four return channels 218 between them, and so on, up to and including eight impact channels 214 with seven return channels 218.

[0036] For example, the base of the impact module 200 can be corrugated, as illustrated, so that the impact channels 214, and in particular the impact openings 216 defined in the base of each impact channel 214, can extend below the return channels 218. That is, the return channels 218 can be formed between and above (radially outside) adjacent impact channels 214. Accordingly, during operation, the cooling medium can flow from the impact module 200 through the impact openings 216, impact the surface 67 to be cooled, and thereby absorb thermal energy from it (i.e., cool it). The cooling medium can then, after absorbing the thermal energy, rise (e.g., by convection) and flow away from the surface 67, generally in a direction opposite to the impact cooling flow from the impact openings 216 of the impact module 200.Accordingly, the return channels 218 above the baffle openings 216 can provide a flow path for such a return flow of heated air (and / or another medium) that is separate from and removed from the impact cooling flow from the baffle openings 216, thereby preventing or reducing, for example, crossflow between impact jets from the baffle openings 216 and warmer return air. In this way, the impact flow generally remains directed towards the surface of the baffle openings 216 and generally perpendicular to it. Additionally, the spacing between adjacent baffle channels 214, provided by the intervening return channels 218, can prevent or reduce crossflow between the baffle openings 216 of adjacent baffle channels 214.

[0037] As in Fig. 9 and Fig. As shown in Figure 10, the impact module 200 can include two collars 210, which are coupled to respective supply pipes 202. The impact module 200 further includes a pair of distribution channels 208, which distribute the cooling air to the impact channels 214. As shown in the Fig. As illustrated in Figures 6-8, the distribution channels 208 extend in a generally circumferential direction, while the impact channels 214 extend in a generally axial direction, the circumferential and axial directions being relative to the longitudinal axis of the combustion chamber 50. To facilitate the installation of the impact modules 200 with adjacent impact modules 200 (as shown in Figures 6-8), Fig. To facilitate (as shown in Figures 6-8), a first circumferential edge 232 can be bent upwards (i.e., extending radially outwards from the longitudinal axis of the combustion chamber 50), while an opposing second circumferential edge 234 can be bent downwards (i.e., extending radially inwards in the direction of the longitudinal axis of the combustion chamber 50), such that the first circumferential edge 232 of a first impact module 200 overlaps the second circumferential edge 234 of a second impact module 200, which is circumferentially adjacent to the first impact module 200. Alternatively or additionally, a first axial edge 242 can be bent upwards and a second axial edge 244 can be bent downwards, such that the first axial edge 242 of a first impact module 200 overlaps the second axial edge 244 of a second impact module 200, which is axially adjacent to the first impact module 200.

[0038] Fig. Figure 11 provides a perspective bottom view of the impact module 200, illustrating an exemplary number and arrangement of the impact openings 216. Although each distribution channel 214 is shown with two impact openings 216, it is obvious that a different number of impact openings 216 can also be used, including arrangements in which the impact openings 216 in one distribution channel 214 are asymmetrically spaced or asymmetrically numbered compared to another distribution channel 214. Fig. 11 is the impact module 200 with a single collar 210 and a respective supply pipe 202 as an alternative to the one in Fig. 9 and Fig. The embodiment shown in Figure 10 is illustrated with two collars 210.

[0039] This written description uses examples to disclose the invention, including best practices, and also to enable a person skilled in the art to apply the invention, including the manufacture and use of any devices or systems and the performance of any methods contained herein. The scope of protection of the invention as claimed herein is defined by the accompanying claims and may include further examples that are obvious to a person skilled in the art.

[0040] Further aspects of the invention are provided by the subject matter of the following paragraphs: A turbomachine comprising a compressor extending from an inlet to an outlet, wherein the outlet of the compressor provides a high-pressure air flow directly into a high-pressure chamber defined within an outer casing of the turbomachine, a combustion chamber at least partially surrounded by the outer casing, and a turbine downstream of the combustion chamber, wherein the combustion chamber has a head end, a lining at least partially defining a hot gas path, a flow sleeve circumferentially surrounding at least a section of the lining, the flow sleeve being spaced from the lining to form a cooling flow ring between them, the cooling flow ring being in fluid communication with the high-pressure chamber, whereby air flows from the high-pressure chamber into the cooling flow ring and from the cooling flow ring to the head end, and an impingement module comprising a plurality of impingement openings.wherein the impact module extends into the cooling flow ring, wherein the plurality of impact openings is oriented towards an outer surface of the lining, thereby configuring the impact module to direct an airflow from the high-pressure chamber through the impact openings to impact the outer surface of the lining.

[0041] The system according to one or more of these paragraphs, wherein the impact module comprises a supply tube, the supply tube extending at least partially through the flow sleeve, whereby an inlet of the supply tube is positioned and oriented to receive the airflow from the high-pressure chamber.

[0042] The system according to one or more of these paragraphs, wherein the inlet of the supply pipe is flush with an outer surface of the flow sleeve.

[0043] The system according to one or more of these paragraphs, wherein the impact module comprises a plurality of impact channels, the plurality of impact openings being defined in the impact channels.

[0044] The system according to one or more of these paragraphs, wherein the impact module further comprises one or more return channels defined between adjacent impact channels of the plurality of impact channels.

[0045] The system according to one or more of these paragraphs, wherein the one or more return channels are positioned above the plurality of impact openings.

[0046] The system according to one or more of these paragraphs, wherein the impact module comprises a distribution channel upstream of the plurality of impact openings.

[0047] The system according to one or more of these paragraphs, wherein each of the plurality of impact openings is spaced a height away from the outer surface of the lining, wherein each of the plurality of impact openings defines a diameter, and wherein the height at each impact opening is between one and five times the diameter of the respective impact opening.

[0048] The system according to one or more of these paragraphs, wherein the impact module comprises a plurality of impact channels, wherein the plurality of impact openings is evenly distributed among the impact channels.

[0049] The system according to one or more of these paragraphs, wherein the impact module comprises a distribution channel, wherein the distribution channel is upstream of the plurality of impact channels, wherein the plurality of impact channels are generally parallel to each other and the distribution channel is generally oriented perpendicular to the plurality of impact channels.

[0050] The system according to one or more of these paragraphs, wherein the impact module comprises a feed pipe coupled to the distribution channel, the feed pipe extending from the distribution channel and at least partially through the flow sleeve.

[0051] Further aspects of the invention are provided by the subject matter of the following paragraphs: An impact module for localized cooling of a hot gas path component of a turbomachine, comprising a plurality of impact openings, wherein the impact module with the plurality of impact openings is positioned towards an outer surface of the hot gas path component, thereby configuring the impact module to receive a compressed air flow and direct the compressed air through the impact openings to impact the outer surface of the component.

[0052] The system according to one or more of these paragraphs, further comprising a supply pipe, wherein an inlet of the supply pipe is positioned and oriented to receive the flow of compressed air.

[0053] The system according to one or more of these paragraphs, further comprising a plurality of impact channels, wherein the plurality of impact openings in the impact channels is defined.

[0054] The system according to one or more of these paragraphs, further comprising one or more return channels defined between adjacent impact channels of the plurality of impact channels.

[0055] The system according to one or more of these paragraphs, wherein the one or more return channels are positioned above the plurality of impact openings.

[0056] The system according to one or more of these paragraphs, further comprising a distribution channel upstream of the multitude of impact openings.

[0057] Further aspects of the invention are provided by the subject matter of the following paragraphs: Flow sleeve for a combustion chamber, wherein the combustion chamber comprises a lining that defines at least a partial hot gas path, wherein the flow sleeve is configured for mounting on the combustion chamber, the flow sleeve circumferentially surrounding at least a section of the lining, the flow sleeve being spaced from the lining to form a cooling flow ring between them, the flow sleeve comprising a feed tube extending inwards towards the lining and an impact module coupled to the feed tube, the impact module comprising a plurality of impact openings, the impact module being positioned such that the plurality of impact openings are oriented towards an outer surface of the lining, the impact module being configured to direct an airflow through the impact openings to impinge on the outer surface of the lining.

[0058] The system according to one or more of these paragraphs, wherein the impact module comprises a plurality of impact channels, wherein the plurality of impact openings is defined in the plurality of impact channels.

[0059] The system according to one or more of these paragraphs, wherein each of the plurality of impact openings is spaced a height away from the outer surface of the lining, wherein each of the plurality of impact openings defines a diameter, and wherein the height at each impact opening is between one and five times the diameter of the respective impact opening.

Claims

[1] Impact module (200) for localized cooling of a hot gas path component (66) of a turbomachine (10), wherein the impact module comprises: a plurality of impact openings (216), wherein the impact module is configured to be positioned with the plurality of impact openings towards a surface (67) of the hot gas path component (66), whereby the impact module is configured to receive a flow of compressed air and to direct the compressed air through the impact openings to impact the surface of the hot gas path component. [2] Impact module according to claim 1, further comprising a supply pipe (202), an inlet (204) of the supply pipe configured to receive the flow of compressed air. [3] Impact module according to a preceding claim, further comprising a plurality of impact channels (214), wherein the plurality of impact openings (216) are defined by walls of the impact channels. [4] Impact module according to any of the preceding claims, wherein the plurality of impact openings is uniformly distributed on the impact channels. [5] Impact module according to one of claims 3 or 4, further comprising one or more return channels (218) defined between adjacent impact channels (214) of the plurality of impact channels. [6] Impact module according to the preceding claim, wherein the one or more return channels (218) are positioned above the plurality of impact openings. [7] Impact module according to one of the preceding claims, further comprising a distribution channel (208) upstream of the plurality of impact openings (216). [8] Impact module according to the preceding claim, if it depends on claim 3 or any other claim dependent on claim 3, wherein the plurality of impact channels (214) are generally parallel to each other and the distribution channel (208) is generally oriented perpendicular to the plurality of impact channels. [9] Impact module according to one of the two preceding claims, if it depends on claim 2 or on another claim dependent on claim 2, wherein the feed pipe (202) is fluidically coupled to the distribution channel (208). [10] Flow sleeve (68) for a combustion chamber (50), wherein the flow sleeve is configured for mounting on the combustion chamber, the flow sleeve circumferentially surrounding at least a section of a lining (66) of the combustion chamber, the flow sleeve being spaced apart from the lining to form a cooling flow ring (90) between them, the flow sleeve comprising an impact module (200) according to any one of the preceding claims, the impact module being arranged and configured to direct an airflow through the impact openings (216) to impinge on the outer surface (67) of the lining (66) when the flow sleeve is mounted on the lining. [11] Flow sleeve according to the preceding claim, wherein the impact module (200) is arranged on a radially inner side of the flow sleeve (68). [12] Flow sleeve according to one of the two preceding claims, wherein a feed pipe (202) extends at least partially through the flow sleeve, wherein the impact module (200) is fluidically coupled to the feed pipe, wherein the feed pipe is in particular the feed pipe of an impact module according to claim 2 or one of claims 3 to 8 depending on claim 2. [13] Flow sleeve according to the preceding claim, wherein the inlet (204) of the supply pipe (202) is flush with an outer surface of the flow sleeve (68). [14] Turbomachine (10), comprising: a compressor (14) extending from an inlet to an outlet, the outlet of the compressor being configured to provide a high-pressure airflow directly into a high-pressure chamber (58) defined within an outer casing (52) of the turbomachine; a combustion chamber (50) which is at least partially surrounded by the outer casing (52); and a turbine (18) downstream of the combustion chamber (50), the combustion chamber includes: a head end; a lining (66) that defines at least part of a hot gas path (32); a flow sleeve (68) according to any one of claims 9 to 11, which circumferentially surrounds at least a section of the lining, wherein the flow sleeve (68) is spaced apart from the lining (66) to form a cooling flow ring (90) between them, wherein the cooling flow ring is in fluid communication with the high-pressure chamber (58), and wherein the cooling flow ring is arranged and configured to cause an airflow from the high-pressure chamber into the cooling flow ring and from the cooling flow ring to the head end; and wherein the impact module (200) extends into the cooling flow ring (90), wherein the plurality of impact openings (216) is aligned to an outer surface (67) of the lining (66), thereby arranging and configuring the impact module to direct an airflow from the high pressure chamber through the impact openings to impact the outer surface of the lining. [15] Turbomachine according to the preceding claim, wherein each impact opening (216) of the plurality of impact openings is spaced apart from the outer surface (67) of the lining (66) by a height (Z), wherein each impact opening of the plurality of impact openings defines a diameter (D), and wherein the height (Z) at each impact opening (216) is between one and five times the diameter (D) of the respective impact opening (216).

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