Apparatus and method for thermal manipulation in a cap of a gas turbine combustor

Abstract

Device comprising: a turbine engine (10) comprising: a combustion chamber (16) having a head end (32); a base plate (72) arranged in the head end (32); and a combustion chamber cap (36) connected to the base plate (72), the base plate (72) and the combustion chamber cap (36) having a fuel nozzle receptacle (64), the combustion chamber cap (36) having a plurality of segments (50, 52, 54) arranged around the fuel nozzle receptacle (64), each segment (50, 52, 54) having a plurality of air effusion channels (66); wherein each segment (50, 52, 54) has a plurality of bolts (74) connected to the base plate (72), the bolts (74) projecting in an axial direction (71) through slots in the base plate (72) extending in a radial direction (81) and / or a circumferential direction (83) to axially retain the segments (50, 52, 54) relative to the base plate (72) while allowing movement of the segments (50, 52, 54) in the radial direction (81) and / or in the circumferential direction (83) relative to the base plate (72); wherein an air gap (70) is present between adjacent segments (52, 54) of the plurality of segments (50, 52, 54), the air gap (70) being configured to allow a flow of cooling air.

Description

BACKGROUND OF THE INVENTION

[0001] The subject matter disclosed herein relates to an apparatus and method for thermal manipulation in a cap of a gas turbine combustor.

[0002] A gas turbine engine contains a compressor, a combustor, and a turbine. The combustor receives compressed air from a compressor along with a fuel and burns a fuel-air mixture to produce hot combustion gases. The hot gases flow through the turbine, driving the turbine blades. As intended, the combustor generates a significant amount of heat. Unfortunately, this heat can cause thermal expansion of various components, which, without proper cooling or appropriate relief, can lead to thermal cracking or other problems. For example, heat in a combustor head end can cause significant thermal expansion in a cap assembly.

[0003] WO 92 / 21919 A1 discloses a gas turbine combustion chamber with an air-atomizing fuel injector. The combustion chamber has a combustion chamber cap with a plurality of openings, each accommodating a fuel injector. The combustion chamber cap has a heat shield spaced apart from a base plate of the combustion chamber cap and having a plurality of cooling holes. The heat shield can be constructed from sector-shaped segments that adjoin one another in the circumferential direction. Each segment has an opening for the fuel injector.

[0004] US 5,524,438 A shows a combustion chamber cap that can be constructed from sector-shaped segments arranged side by side in the circumferential direction. A similar combustion chamber cap is also described in US 2010 / 0058766 A1.

[0005] US 5 357 745 A shows a combustion chamber cap with an annular base plate and has a plurality of cooling openings.

[0006] US 2005 / 0 022 531 A1 describes a double-walled combustion chamber with an inner lining and an outer lining. The outer lining can have several segments interspersed with air effusion channels. The segments can be arranged at a distance from one another, forming an air gap.

[0007] A combustion chamber with several wall segments arranged at a distance from one another to form a gap is also known from US 2009 / 0 013 694 A1 and US 2005 / 0034461 A1. BRIEF DESCRIPTION OF THE INVENTION

[0008] The invention relates to a device having the features of patent claim 1.

[0009] Certain embodiments are summarized below. These embodiments are not intended to limit the scope of the claimed invention; rather, these embodiments are intended to provide a brief summary of possible embodiments of the invention. Indeed, the invention may encompass a variety of embodiments that may be similar to or different from the embodiments described below. SHORT DESCRIPTION OF THE DRAWING

[0010] These and other features, aspects and advantages of the present invention will be better understood when the following detailed description is read with reference to the accompanying drawings, in which like reference characters represent like parts throughout the drawings, in which: Fig. 1 is a block diagram of a turbine apparatus having a fuel nozzle connected to a combustor in accordance with an embodiment of the present invention; Fig. 2 a sectional side view of the Fig. 1, having a plurality of fuel nozzles connected to an end cover in accordance with an embodiment of the present invention; Fig. 3 is a front view of a burner cap assembly in accordance with an embodiment of the present invention; Fig. 4 a detailed representation of the combustion chamber cap arrangement according to Fig. 3 according to line 4-4 in Fig. 3 in accordance with an embodiment of the present invention, Fig. 5 a cross section along the line 5-5 to Fig. 3 is in accordance with an embodiment of the present invention; Fig. 6 is a perspective exploded view from the rear of the combustion chamber cap assembly according to Fig. 3 is in accordance with an embodiment of the present invention; A perspective exploded view from the front of the combustion chamber cap assembly according to Fig. 3 is in accordance with an embodiment of the present invention; Fig. 8 a partial view from the front of the base plate arrangement according to Fig. 7 according to line 8-8 in Fig. 7 is in accordance with an embodiment of the present invention; Fig. 9 is a perspective view of a combustor cap assembly with an associated base plate assembly in accordance with an embodiment of the present invention; Fig. 10 is a perspective view of a combustion chamber cap assembly taken along line 10-10 of Fig. 3 and Fig. 9 in accordance with an embodiment of the present invention; and Fig. 11 is a perspective view of a combustion chamber cap assembly taken along line 10-10 of Fig. 3 and Fig. 9 in accordance with an embodiment of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0011] One or more specific embodiments of the present invention are described below. In an effort to provide a concise description of the embodiments, not all features of the actual implementation can be described in the description. It will be understood that in developing any such implementation, as in any engineering or design project, many implementation-specific decisions must be made to achieve the designer's particular goals, such as compliance with system and economic constraints that may vary from one implementation to another. Further, it will be understood that such a development effort may be complex and time-consuming, but may nonetheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill in the art given this disclosure.

[0012] When introducing elements of the various embodiments of the present invention, the indefinite articles are to be understood as meaning that one or more of these elements may be present. The terms "include," "comprise," and "comprising" are to be understood as meaning that further elements may be present in addition to the elements mentioned.

[0013] As explained in detail below, embodiments of the turbine combustor cap may include a plurality of segments configured to reduce thermal stresses due to the generation of heat in a gas turbine combustor. For example, the plurality of segments may include multiple segments per fuel nozzle. In some embodiments, each fuel nozzle is surrounded by 2, 3, 4, 5, or more segments, rather than having a closed structure around a perimeter of the fuel nozzle. Together, the plurality of segments describe a plate-like geometry with one or more fuel nozzle receptacles. For example, each fuel nozzle receptacle may be defined by curved edges of two or more segments of the turbine combustor cap, which together define a circular opening for the fuel nozzle.

[0014] In certain embodiments, the segments may form air gaps between each other to facilitate air cooling while also allowing for a certain degree of thermal expansion relative to the fuel nozzles. Additionally, embodiments of the segments may include a mechanism to allow movement, e.g., in the radial and / or circumferential directions, to provide relief for thermal expansion. Thus, the air gaps and mechanism may significantly reduce the occurrence of thermal stresses and cracks in the turbine combustor cap.

[0015] The disclosed embodiments may also include a base plate connected to the plurality of segments, wherein the base plate guides against the rejection of the segments. For example, the segments may be axially spaced from the back plate to form an intermediate cooling chamber. The base plate may include air channels configured to direct air jets against the back of the segments to provide temper cooling of the segments. In certain embodiments, the segments may be connected to the base plate via bolts, wherein the bolts are disposed through slots aligned in a radial direction. The engagement of the bolts in the slots may enable movement (e.g., radially and / or circumferentially) of the segments relative to the base plate, providing relief for thermal expansion as noted above.

[0016] In certain embodiments, the segments may have openings (e.g., perforations) to facilitate effusion cooling. For example, the openings may extend axially through the segments from a rear side to a front side. These openings may be oriented at a variety of angles relative to the front side, for example, from 20 to 90 degrees. In certain embodiments, the openings may direct the airflow in a converging manner toward the fuel nozzles. However, any suitable configuration of the openings is within the scope of the described embodiments.

[0017] With reference to the drawing and first to Fig. 1, a block diagram of one embodiment of a turbine device 10 is shown. The diagram includes fuel nozzles 12, a fuel supply 14, and a combustor 16. As described, the fuel supply 14 supplies a liquid fuel or a gaseous fuel, such as natural gas, to the turbine device 10 via a fuel nozzle 12 into the combustor 16. After mixing with compressed air, illustrated by arrow 18, ignition occurs in the combustor 16, and the resulting exhaust gas causes the blades within the turbine 20 to rotate. The connection between the blades in the turbine 20 and the shaft 22 causes rotation of the shaft 22, which is also connected to some components within the turbine device 10 as illustrated. For example, the illustrated shaft 22 is drivingly connected to a compressor 24 and a load 26.It will be understood that the load 26 may be any suitable device capable of generating power via the rotating output of the turbine device 10, such as a power generator or a vehicle.

[0018] The air supply may direct air via conduits to the air inlet 28, which then directs the air into the compressor 24. The compressor 24 has a plurality of vanes drivingly connected to the shaft 22, with air from the air inlet 28 being compressed and delivered to the fuel nozzles 12 and the combustion chamber 16, as shown by arrows 29. The fuel nozzles 12 may then mix the compressed air and fuel, as shown by reference numeral 18, to produce an optimal mixture ratio for combustion, for example, combustion that burns the fuel more completely to avoid wasting fuel or causing high emissions. The exhaust gas exits the device at the exhaust outlet 30 after passing through the turbine 20.As explained in detail below, one embodiment of the combustor 16 includes a combustor cap assembly segmented around each fuel nozzle 12, providing relief for thermal expansion within the combustor 16.

[0019] Fig. 2 shows a cross-sectional side view of one embodiment of the combustor 16 including a plurality of fuel nozzles 12. In certain embodiments, a head end 32 of a combustor 16 includes an end cap 34. Additionally, the head end 32 of the combustor 16 may include a combustor cap assembly 36 that closes the combustion chamber and houses the fuel nozzles 12. The fuel nozzles 12 deliver fuel, air, and other fluids into the combustion chamber 16. A plurality of fuel nozzles 12 are shown attached to the end cap 34 near the base of the combustion chamber 16 and extend through the combustor cap assembly 36. For example, the combustor cap assembly 36 houses one or more fuel nozzles 12 and provides combustion containment.Each fuel nozzle 12 facilitates the mixing of compressed air and fuel and directs the mixture through the combustor cap assembly 36 into a combustion chamber 38 of the combustion chamber 16. The air-fuel mixture can then combust within the combustion chamber 38, producing hot, compressed exhaust gas. The compressed exhaust gas drives the rotation of the blades within the turbine 20. The combustion chamber 16 includes a flow sleeve 40 and a combustion chamber wall 42 that define the combustion chamber 38. In certain embodiments, the flow sleeve 40 and the wall 42 are coaxial or concentric with each other to form a hollow annular space 44 that allows the passage of air for cooling and entry into the combustion zone 38 (e.g., through perforations in the wall 52 and / or fuel nozzles 12). The configuration of the wall 42 allows for optimal flow of the air-fuel mixture to the transition part 46 (e.g.,converging section) along the exhaust path 48 to the turbine 20. For example, the fuel nozzles 12 may deliver a compressed air-fuel mixture into the combustion chamber 38, where combustion of the mixture occurs. The resulting exhaust gas flows through the transition piece 46 along the exhaust path 48 into the turbine 20, causing the blades of the turbine 20 to rotate along with the shaft 22.

[0020] During this process, the combustor cap assembly 36 may experience stress as combustion occurs. In particular, the compressed air may have a temperature of approximately 650 to 1300°F, causing thermal expansion of the combustor cap assembly. Fuel may have a temperature of approximately 50 to 350°F, causing thermal expansion of the nozzle 12 that is of a lesser magnitude compared to the thermal expansion of the combustor cap assembly 36. The nozzle 12 and the combustor cap assembly 36 may be composed of the same or different materials, such as stainless steel, an alloy, or another suitable material. Further, the combustion may expose the combustor cap assembly 36 to temperatures ranging from approximately 2000 to 3000°F or more.The combustion chamber cap assembly 36 may experience significant thermal stress or strain as a result of exposure to these various temperatures.

[0021] As described in detail below, segmenting the combustor cap assembly 36 may provide stress relief for stresses that may be caused, for example, by thermal expansion of various components of the combustor cap assembly 36.

[0022] Fig. 3 illustrates a front view of one embodiment of a combustor cap assembly 36. The combustor cap assembly 36 may include a plurality of effusion plate segments 50, 52, and 54. The segments 50, 52, and 54 may be combined in a repeatable pattern to form a side 56 of the combustor cap assembly 36. For example, the side 56 of the combustor cap assembly 36 may have a circular shape with a diameter 58 of approximately 12 to 28 inches.

[0023] Each segment of the plurality of segments 50, 52, and 54 may have a front side 60, a back side, and a plurality of edges 62. Each of the plurality of edges 62 of the plurality of segments 50, 52, and 54 may define a nozzle combustion tube 63 surrounding a fuel nozzle receptacle 64. The nozzle combustion tube 63 may, for example, provide fluid flow between a fuel nozzle receptacle 64 and a fuel nozzle 12 passing through the receptacle, for example, to block fluid leakage.

[0024] As illustrated, segment 50 may have three edges 62, each adjacent to a separate fuel nozzle receptacle 64. Segment 52 may have two edges 62, each adjacent to a separate fuel nozzle receptacle 64, and segment 54 may have five edges 62, each adjacent to a separate fuel nozzle receptacle 64. In this way, each segment 50, 52, 54 has edges 62 that are adjacent to at least two fuel nozzle receptacles 64 without completely enclosing any one fuel nozzle receptacle 64. In other words, each fuel nozzle 12 is enclosed by multiple segments rather than a continuous structure.Therefore, the combustor cap assembly 36 may include a first set of cap segments 50 and 52 disposed along an outer periphery of the turbine combustor cap and a second set of cap segments 54 disposed in a central region of the turbine combustor cap, the first set of cap segments completely surrounding the second set of cap segments.

[0025] Furthermore, segments 50 and 52 may be arranged in a repeating pattern along the outer perimeter of the outer surface 56 of the combustor cap assembly 36, with segments 50 and 52 arranged circumferentially alternately adjacent to one another. Furthermore, segments 54 may be repeatably arranged around a central region and spaced radially inwardly from the outer surface 56 of the combustor cap 36, adjacent to the above-described repeatedly arranged segments 50 and 52.

[0026] Each of the segments 50, 52, 54 may allow a fluid, such as air, to flow through the surface of the segments 50, 52 and 54 via effusion channels 66 ( Fig. 4). In this way, segments 50, 52, and 54 can be combined to form an effusion plate 59, i.e., a plate that allows fluid to flow through the channels in the plate. Fig. Figure 4 illustrates a partial plan view, indicated by curved lines 4-4, of the front surface 60 of any one of the segments 50, 52, or 54.

[0027] As in Fig. 4, the front side 60 has a plurality of effusion channels 66, for example, approximately 100 to 5000 channels 66. Each of the segments 50, 52, and 54 may have approximately 10 to 500 effusion channels 66. For example, each of the segments 50, 52, and 54 may have at least approximately 50, 100, 150, 200, 250, 300, 350, or 400 effusion channels 66. In one embodiment, the effusion plate 49 of the combustor assembly 36 may be interspersed with approximately a total of 100 effusion channels 66. Additionally, each effusion channel 66 may have a diameter of approximately 4 to 100, 10 to 100, 20 to 40, 20 to 80, 20 to 35, or 50 to 60 thousandths of an inch. For example, each effusion channel 66 may be at least less than about 20, 30, 40, 50, 60, 70, 80, 90, or 100 thousandths of an inch in diameter.In one embodiment, each segment 50, 52 and 54 may have at least about 100 air effusion channels, each effusion channel being at least less than about 100 thousandths of an inch in diameter.

[0028] As described above, the effusion channels 66 allow fluid to pass through the segments 50, 52, and 54 to assist in cooling the segments 50, 52, and 54. Therefore, the effusion channels 66 may extend axially from the rear side through the respective segments 50, 52, or 54 and exit the effusion plate 49 of the combustor assembly 36. Further, the effusion channels 66 may be angled relative to the front side 60 of each of the segments 50, 52, and 54. For example, the effusion channels 66 may discharge the fluid from the effusion channels 66 at an angle of approximately 90, 80, 70, 60, 50, 40, 30, and / or 20° relative to the front side 60 of each of the segments 50, 52, and 54. In another embodiment, the effusion channels 66 may be arranged at an angle of less than about 45° with respect to the front side 60 of each segment 50, 52 and 54.Alternatively, each effusion channel 66 may be arranged at an angle of approximately between 20 and 60° relative to the front side 60 of each segment 50, 52, and 54. Furthermore, the effusion channels 66 may be arranged parallel or non-parallel, converging or divergent to one another. In one embodiment, the effusion channels 66 may converge toward the fuel nozzles 12. The effusion channels 66 may also be arranged in a regular pattern or in a random pattern.

[0029] Coming back to Fig. 3, segments 50, 52, and 54 may each have edges 62 that adjoin separate fuel nozzle receptacles 64. Additionally, segments 50, 52, and 54 may also have a plurality of land ports 68. These land ports 68 may be the portions of segments 50, 52, and 54 that adjoin one another. For example, segment 50 may have four land ports 68 (one land port 68 to each of the two segments 52 and one land port 68 to each of the two segments 54), while segment 52 may have three land ports 68 (one land port 68 to each of the two segments 52 and one land port 68 to a single segment 54). Likewise, the segment 54 may have five web connections 68 (one web connection 68 to each of the two segments 50, one web connection 68 to a single segment 52, and one web connection 68 to each of the two segments 54).

[0030] The web connections 68 may each contain an air gap 70. Therefore, the segments 50, 52 and 54 may each be separated from each other by an air gap 70. This air gap is in Fig. 5, which shows a cross-section of the combustion chamber assembly 36 along the line 5-5 in Fig. 3. The air gap 70 may, for example, have a width of about 0.03 to 0.3 inches. As shown, the air gap 70 may also allow air flow between the segments 52 and 54 along an axial path, which is illustrated by the pillar 71. Referring to the Fig. 3 and Fig. 5, the effusion plate 49 is connected to a base plate 72 via a plurality of connecting means, for example, threaded bolts or bolts 74 and nuts 76. In the illustrated embodiment, each bolt 74 may include a spacer means, for example, one or more washers 78, axially disposed between the nut 76 and the base plate 72. In particular, the effusion plate 49 (e.g., segments 50, 52, and 54) is axially spaced from the base plate 72 via a spacer means 69 to form an intermediate cooling chamber 77 to enhance the blow-off cooling of the back surface 79 of the effusion plate 49. Therefore, the intermediate cooling chamber 77 may be disposed between the base plate 72 and the plurality of segments 50, 52, and 54 such that the base plate 72 has a plurality of blowing passages aligned with the (inner) rear side 79 of each of the plurality of segments 50, 52, and 54.

[0031] The base plate 72 also includes one or more air passages or blow-off cooling channels 80 configured to direct air jets into the intercooling chamber 77 and directly against the rear side 79 of the segments 50, 52, and 54 of the effusion plate 49. In this manner, the base plate 72 cooperates with the effusion plate 79 to provide blow-off cooling of the individual segments 50, 52, and 54. The air flow can, in turn, pass through the segments 50, 52, and 54 via the effusion channels 66 in an axial direction 71, as well as between adjacent segments 50, 52, and 54 via the air gaps 70. The air flow can also pass between the segments 50, 52, and 54 and the fuel nozzles 12. The effusion cooling via the channels 66, the intercooling via the air gaps 70 and the blow cooling via the channels 80 together cool the combustion chamber cap assembly 36 considerably, while the segmentation (e.g.segments 50, 52 and 54) reduces thermal stresses by allowing a certain degree of unhindered thermal expansion.

[0032] The air gap 70 and the land connections 68 can allow thermal expansion of each of the existing segments 50, 52, or 54. That is, certain nozzles 12 can heat up to a greater extent than other nozzles 12 in the combustion chamber 16, whereby each edge 62 of the segments 50, 52, and 54 located adjacent to the fuel nozzle receptacle 64 of the hotter nozzle 62 thermally expands in a radial direction illustrated by arrows 81 to a greater extent than the remaining segments 50, 52, and 54. By providing an air gap 70 between the segments 50, 52, and 54, each segment 50, 52, and 54 exposed to this higher heat intensity can thermally expand without abutting an adjacent segment 50, 52, and 54.This may result in reduced forces exerted on the combustor cap assembly 36 as a whole because the segments 50, 52, and 54 may thermally expand in the radial direction 81 without coming into contact with each other, which could otherwise result in, for example, segment cracking due to contact stresses between the segments 50, 52, and 54. For example, the air gap may decrease by approximately 40, 50, 60, 70, 80, or 90% when subjected to thermal stress conditions.

[0033] Fig. 6 is an exploded perspective view from the rear of one embodiment of the combustion chamber cap assembly 36, while Fig. 7 is a front perspective exploded view of an embodiment of the combustion chamber cap assembly. Referring to the Fig. 6 and Fig. 7, effusion plate 49 is connected to base plate 72 via a plurality of bolts 74 and nuts 76. As described above, base plate 72 cooperates with effusion plate 49 to achieve blow-off cooling of the individual segments 50, 52, and 54.

[0034] As further stated in the Fig. 6 and Fig. 7, the base plate 72 may be configured to allow movement of the segments 50, 52, and 54 in a radial direction 81 and / or circumferential direction 83. For example, the bolts 74 may extend in the axial direction 71 through slots in the base plate 72 extending in the radial direction 81 and / or circumferential direction 83 to axially retain the segments 50, 52, and 54 relative to the base plate 72 while allowing a certain amount of radial and / or circumferential movement of the segments 50, 52, and 54 relative to the base plate 72. These slots may also be described with reference to Fig. 8, the partial top view of the base plate arrangement according to Fig. 7 within line 8-8 in Fig. 7 illustrates.

[0035] In one embodiment, the base plate 72 may include at least one circular stud receptacle 73 and at least one elongated stud receptacle 75. For example, the base plate 72 may include the circular stud receptacle 73 in a central region of each segment 50, 52, and 54 such that the stud 74 substantially centers the respective segment around the stud receptacle 73. Therefore, the size of the circular stud receptacle 73 may be set with relatively close tolerances relative to the stud 74 to block movement of the segment 50, 52, or 54 at the central stud 74. In contrast, the base plate 72 may include a plurality of elongated stud receptacles 75 at peripheral locations spaced from the central region of each segment 50, 52, and 54 such that each stud 74 can move along the length 85 of its corresponding elongated stud receptacle 75 to provide relief for thermal expansion.In certain embodiments, the elongated bolt receptacles 75 may be oriented only in radial directions 81. However, some embodiments may have elongated bolt receptacles 75 oriented in radial directions 81 and circumferential directions 83, or only in circumferential directions 83. As described above, each bolt 74 engages a corresponding nut 76 to axially secure the segments 50, 52, and 54 to the base plate 72. In certain embodiments, the nut 76 on the central bolt 74 disposed in the circular bolt receptacle 73 may be fully tightened to limit movement of the central bolt 74, while the other nuts of the peripheral bolts 74 disposed in elongated bolt receptacles 75 are less than fully tightened to facilitate peripheral thermal expansion of each segment 50, 52, or 54.Alternatively, the peripheral bolts 74 may include axial spacing means (e.g., sleeves) to limit axial compression between the segments 50, 52, and 54 and the base plate 72. Therefore, a central bolt 74 may be rigidly connected to the base plate 72 to center the segments 50, 52, and 54, and the radially inner and outer bolts 74 are secured to the base plate 72 with a clearance or range of motion to allow for thermal expansion relative to the central bolt 74. It should also be noted that the peripheral bolts 74 may have an elongated shape adapted to the elongated bolt receptacles 75, allowing movement of the peripheral bolts 74 along the length 85 of each elongated bolt receptacle 75.

[0036] Fig. 9 shows an exploded front view of another embodiment of the combustor cap assembly 36. Again, the combustor cap assembly 36 has the outer surface 56, the diameter 58, the front surface 60, the edges 62, the fuel nozzle receptacles 64, the land connections 68 and the air gaps 70 as described above with reference to FIG. Fig. 3, Fig. 5, Fig. 6 and Fig. 7. However, in the illustrated embodiment, the effusion plate 49 has a different set of segments 84 and 86 compared to the segments 50, 52 and 54 of the Fig. 3, Fig. 4 and Fig. 5.

[0037] Additionally, segments 84 and 86 may be arranged in a repeatable pattern along the outer perimeter of the outer surface 56 of the fuel cap assembly 82, with segments 84 and 86 being arranged alternately next to one another. As illustrated, segments 84 extend from the outer surface 56 to the central region of the combustor cap assembly 36 around a central fuel nozzle assembly 64. Segments 86 extend only partially from the outer edge 56 to the central region of the combustor cap assembly 36 such that segments 86 do not reach the central fuel nozzle receptacle 64. In the illustrated embodiment, effusion plate 49 is formed by four segments 84 and four segments 86 in an alternating symmetrical pattern. In this manner, segments 84 and 86 combine to cover the entire outer surface 56 of the combustor cap assembly 36.Thus, the combustor cap assembly 36 may include a first set of cap segments 86 disposed only along an outer periphery of the combustor cap 36, and a second set of cap segments 84 disposed both along a central region of the turbine combustor cap and along the outer periphery of the turbine combustor cap.

[0038] Corresponding to segments 50, 52 and 54, segments 84 and 86 also include a plurality of threaded bolts or studs 88 adapted to engage stud receptacles 90 of base plate 72. As described above, stud receptacles 90 may include circular stud receptacles 73 and elongated stud receptacles 75 similar to those shown in Fig. 8. The circular bolt receptacles 73 may be configured to secure the respective segments 84 and 86, while the elongated bolt receptacles 75 may be configured to permit movement of the segments 84 and 86 in the radial direction 81 and / or circumferential direction 83. For example, the circular bolt receptacles 73 may be disposed at a central location of each segment 84 and 86 such that retaining the central bolt 88 (e.g., by means of a nut) substantially maintains a centered position of the segments 84 and 86 during thermal expansion or thermal contraction. In contrast, the elongated bolt receptacles 75 permit movement of the bolts 88 along the length of the elongated bolt receptacles 75, providing unloading or relief for thermal expansion or contraction.

[0039] Additionally, the combustor cap assembly 36 includes a plurality of passages and gaps to assist cooling and thermal expansion. For example, the effusion plate 49 Fig. 5 web connections 68 and air gaps 70. The air gaps 70 allow both thermal expansion and cooling air flow between adjacent segments 84 and 86 along the web connections 68. For example, the segments 84 and 86 may have different thermal expansion coefficients than the fuel nozzles 12 or other components of the combustor cap assembly 36. Therefore, the components may expand or contract at different rates. The air gaps 70 allow some room for this geometry change while also allowing the direct cooling of the edges 62 of the segments 84 and 86 by cooling air. Examples of fluid flow into the air gaps 70 for cooling the edges 62 of the segments 84 and 86 are shown in the Fig. 10 and Fig. 11 illustrates.

[0040] In Fig. 10 is a partial perspective view of one embodiment of the combustion chamber cap 36 taken within the arcuate line 10-10 in FIGS. Fig. 3 and Fig. 9 shown. Fig. 10 shows two fuel nozzle receptacles 64, an air gap 70, a base plate 72 and a segment 92. It is understood that the segment 92 is one of the segments 50, 52 or 54 according to the Fig. 3, Fig. 6 and Fig. 7 or one of the segments 84 and 86 according to the Fig. 9. The segment 92 is attached to the base plate 72 to form a cavity or intermediate chamber 94 for a cooling flow (e.g. air flow) corresponding to the intermediate cooling chamber 77 of Fig. 5. For example, the intermediate chamber 94 may have a width of less than about 0.04 to 0.2 inches. As described above, the cooling flow (e.g., air) may be directed into the intermediate chamber 94 through the passages 80 (e.g., Fig. 5) in the base plate 72 and directly impinge on the back surface 79 of the segment 92. In this way, the airflow provides blow-on cooling of the segment 92. Additionally, the segment 92 may include the effusion channels 66 to effect effusion cooling of the segment 92. However, the segment 92 may also be used without an effusion channel 66, with all air passing through one or more edge outlets 96, as described below.

[0041] The segment 92 includes one or more edge outlets 96 (e.g., cooling jet outlet) that discharge one or more cooling jets 98 in a direction illustrated by arrow 100. Each outlet 96 may have an opening of at least approximately 10, 20, 30, 40, 50, 60, 70, 80, 90, or 100% of the area of the outlet side 93 of the segment 92. Further, the outlet 96 may include a splitter 102 that splits the cooling jets 98. The splitter 102 may be used to direct the flow of the cooling jets 98 into the air gap 70 for cooling along the air gap 70 between adjacent segments 92. In certain embodiments, the splitter 102 may split the airflow and diverge outward toward opposing fuel nozzle receptacles 64.

[0042] Fig. 11 is a partial perspective view of an embodiment of the combustion chamber cap 36 taken within the curved line 10-10 in FIGS. Fig. 3 and Fig. 9. According to the embodiment according to Fig. 10 contains the execution according to Fig. 11 two fuel nozzle receptacles 64, an air gap 70, a base plate 72 and a segment 92. It is understood that the segment 92 is one of the segments 50, 52 or 54 as in Fig. 3, Fig. 6 and Fig. 7 or one of the segments 84 and 86 as shown in Fig. 9. The segment 92 is attached to the base plate 72 to form an intermediate chamber 94 ( Fig. 19) which provide a blow-on cooling flow (air flow) from the passages 80 (e.g. Fig. 5) and discharges the cooling flow through effusion channels. Furthermore, segment 92 may also be used without an effusion channel 66, with all air passing through one or more edge outlets 104, as described below.

[0043] In addition, segment 92 contains Fig. 11 one or more edge outlets 104 (e.g., a cooling jet outlet) that discharges one or more cooling jets 98 in a direction indicated by arrow 100. The outlets 104, which may be openings in a side surface 106, may have a size that is at least approximately 5, 10, 20, 30, 40, 50, 60, 70, or 80% of the height of the side surface 106. The side surface 106 may be used to direct the flow of the cooling air jets 98 into the air gap 70 for cooling along the air gap 70 between two adjacent segments 92. In this way, the outlets 104 operate in substantially the same manner as the outlets 96 described above with reference to Fig. 10. In fact, the outlets 104 may be used in conjunction with or instead of the outlets 96, as appropriate for cooling adjacent segments.

[0044] The description uses examples to disclose the invention in order to describe advantageous embodiments and to enable a person of ordinary skill in the art to carry out the invention. The scope of the invention is defined by the claims and may also include further embodiments that occur to a person of ordinary skill in the art. Such further embodiments are to be understood as falling within the scope of the claims if they contain elements that do not deviate from the literal meaning of the claims or if they contain elements that have equivalent structural elements without substantial differences from the literal meaning of the claims.

[0045] An apparatus includes a turbine engine 10 having a combustion chamber 16 with a head end 32, a base plate disposed at the head end 32, and a combustion chamber cap 36 connected to the base plate 72, the base plate 72 and the combustion chamber cap 36 including a fuel nozzle receptacle 64. Additionally, the combustion chamber cap 36 includes a plurality of segments 50, 52, 54 disposed around the fuel nozzle receptacle 64, and each segment 50, 52, 54 includes a plurality of air effusion channels 66. List of reference symbols: 10 Turbine device 12 Fuel nozzle 14 Fuel supply 16 Combustion chamber 18 Arrow 20 turbines 22 Wave 24 Compressor 26 Last 27 Air supply 28 Air intake 29 Arrow 30 Exhaust outlet 32 headboard 34 End cover 36 Combustion chamber cap assembly 38 combustion chamber 40 Flow cuff 42 Combustion chamber wall 44 Hollow annulus 46 Transition part 48 Export Directive 49 Effusion plate 50 effusion plate segment 52 Effusion plate segment 54 Effusion plate segment 56 pages 58 diameter 60 Front 62 edge 63 Nozzle combustion tube 64 Fuel nozzle holder 66 Effusion channel 68 bridge connection 70 air gap 71 Axial direction 72 base plate 74 bolts 76 Mother 77 Cooling chamber 78 Washer 79 Back 80 cooling channel 81 Radial direction 82 Cooling cap arrangement 83 Circumferential direction 84 cap segment 85 length 86 cap segment 88 bolts 90 bolt holder 92 segments 94 Intermediate chamber 96 edge outlet 98 Cooling jet 100 arrows 102 dividers 104 Outlet 106 side surface

Claims

[1] Device comprising: a turbine engine (10) comprising: a combustion chamber (16) having a head end (32); a base plate (72) arranged in the head end (32); and a combustion chamber cap (36) connected to the base plate (72), the base plate (72) and the combustion chamber cap (36) having a fuel nozzle receptacle (64), the combustion chamber cap (36) having a plurality of segments (50, 52, 54) arranged around the fuel nozzle receptacle (64), each segment (50, 52, 54) having a plurality of air effusion channels (66); wherein each segment (50, 52, 54) has a plurality of bolts (74) connected to the base plate (72), the bolts (74) projecting in an axial direction (71) through slots in the base plate (72) extending in a radial direction (81) and / or a circumferential direction (83) to axially retain the segments (50, 52, 54) relative to the base plate (72) while allowing movement of the segments (50, 52, 54) in the radial direction (81) and / or in the circumferential direction (83) relative to the base plate (72); wherein an air gap (70) is present between adjacent segments (52, 54) of the plurality of segments (50, 52, 54), the air gap (70) being configured to allow a flow of cooling air. [2] The apparatus of claim 1, wherein a plurality of segments (50, 52, 54) includes a first set of cap segments (86) disposed along an outer periphery of the combustion chamber cap (36) and a second set of cap segments (84) disposed at a central region of the combustion chamber cap (36). [3] The device (10) of claim 1, wherein each segment (50, 52, 54) has a hollow interior facing the base plate (72). [4] The apparatus of claim 1, wherein the plurality of bolts (74) on each segment (50, 52, 54) includes a central bolt, a radially inner bolt, and a radially outer bolt, the central bolt being fixedly mounted to the base plate (72) to center the segment (50, 52, 54) and the radially inner and outer bolts being mounted to the base plate (72) with a range of motion to allow for thermal expansion relative to the central bolt. [5] The apparatus (10) of claim 1, comprising an intermediate cooling chamber (94) between the base plate (72) and the plurality of segments (50, 52, 54), the base plate (72) having a blowing passage to an inner side (79) of each segment (50, 52, 54) of the plurality of segments (50, 52, 54). [6] The apparatus (10) of claim 1, wherein each segment (50, 52, 54) has at least about 100 air effusion channels (66) and each air effusion channel (66) has a diameter of at least less than about 80 thousandths of an inch. [7] The device (10) of claim 1, wherein the plurality of segments (50, 52, 54) each have a front side (60), a back side (79) and edges (62), the edges (62) being arranged around the fuel nozzle receptacle (64), and each of the plurality of segments (50, 52, 54) having a plurality of air effusion channels (66) extending from the back side (79) through each of the plurality of segments (50, 52, 54) and opening out of the front side (60). [8] The device of claim 7, comprising an air gap (70) between adjacent segments (52, 54) in the plurality of segments (50, 52, 54), the size of the air gap (70) being set to allow thermal expansion of each of the two segments (50, 52) without them coming into contact with each other.

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