Integrated combustion nozzle with integral head

Abstract

The present invention provides an integrated combustion nozzle (100) and a turbine (10). The integrated combustion nozzle (100) includes an integrated head end (200) coupled to a combustion liner (110). The integrated head end (200) includes a first fuel nozzle (202) and a second fuel nozzle (204) disposed at a front end portion of the combustion liner (110). A fuel plenum (248) is defined between the first fuel nozzle (202) and the second fuel nozzle (204). The fuel plenum (206) extends from the first fuel nozzle (202) and into an opening (170, 172) in a first wall of the combustion liner (110), such that the fuel plenum (206) forms a continuous surface with the first wall. The integrated head end (200) also includes a second liner portion (208) extending from the second fuel nozzle (204) and into the opening (170, 172) of the second wall of the combustion liner (110) such that the second liner portion (208) forms a continuous surface with the second wall.

Description

Technical Field

[0001] The present disclosure generally relates to integrated combustion nozzles for gas turbine engines. More particularly, the present disclosure relates to a compact integrated combustion nozzle having an integrated two-stage combustion system. Background Art

[0002] Turbines are used in various industries and applications for energy transfer purposes. For example, a gas turbine engine typically 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 the compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed in the combustion section and burned in a combustion chamber to generate high-pressure and high-temperature combustion gases. From the combustion section, the combustion gases flow 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 connected to, for example, a generator to generate electricity. The combustion gases then leave the gas turbine via the exhaust section.

[0003] Turbine combustion systems typically burn hydrocarbon fuels and produce air polluting emissions such as nitrogen oxides (NOx) and carbon monoxide (CO). The oxidation of molecular nitrogen in a turbine depends on the temperature of the gas in the combustor and the residence time of the reactants in the highest temperature region within the combustor. Therefore, the amount of NOx produced by a turbine can be reduced or controlled by maintaining the combustor temperature below the NOx generation temperature or by limiting the residence time of the reactants in the combustor.

[0004] A method for controlling the temperature of a combustor involves premixing fuel and air to produce a fuel-air mixture prior to combustion. The method may include axial staging of fuel injectors, wherein a first fuel-air mixture is injected and ignited at a first, or primary, combustion zone of the combustor to produce a primary stream of high-energy combustion gases, and wherein a second fuel-air mixture is injected into and mixed with the primary stream of high-energy combustion gases via a plurality of radially oriented and circumferentially spaced fuel injectors or an axially staged fuel injector assembly positioned downstream of the primary combustion zone. Injecting the second fuel-air mixture into the secondary combustion zone is sometimes referred to as a "cross-flow jet" arrangement.

[0005] Axially staged injection increases the likelihood of complete combustion of available fuel, which in turn reduces air polluting emissions. However, conventional axially staged fuel injection combustion systems have multiple components with complex geometries that are difficult and time-consuming to assemble. Consequently, scaling an axially staged combustor (e.g., from a large combustor to a smaller one) can be difficult due to the space required for assembly. Therefore, an improved gas turbine combustion system that includes axially staged fuel injection and is fully scalable would be useful to the industry. Summary of the Invention

[0006] Aspects and advantages of the integrated combustion nozzle and turbine according to the present disclosure will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the technology.

[0007] According to one embodiment, an integrated combustion nozzle is provided. The integrated combustion nozzle includes a combustion liner extending radially between an inner liner section and an outer liner section. The combustion liner includes a forward portion axially separated from an aft portion. The combustion liner also includes a first sidewall and a second sidewall. The aft portion of the combustion liner defines a turbine nozzle. The first sidewall and the second sidewall each define an axially and radially extending opening. The integrated combustion nozzle also includes an integrated head end coupled to the combustion liner. The integrated head end is in fluid communication with a fuel supply source. The integrated head end includes a first fuel nozzle and a second fuel nozzle disposed at the forward portion of the combustion liner. A fuel plenum is defined between the first and second fuel nozzles. A first liner portion extends from the first fuel nozzle and enters an opening in the first wall, such that the first liner portion forms a continuous surface with the first wall of the combustion liner. The integrated head end also includes a second liner portion that extends from the second fuel nozzle and enters an opening in the second wall, such that the second liner portion forms a continuous surface with the second wall of the combustion liner.

[0008] According to another embodiment, a turbine is provided. The turbine includes a compressor section and a compressor discharge casing disposed downstream of the compressor section. A turbine section is disposed downstream of the compressor discharge casing. The turbine also includes an annular combustion system disposed within the compressor discharge casing. The annular combustion system includes a plurality of integrated combustion nozzles arranged in an annular array about an axial centerline of the turbine. Each integrated combustion nozzle includes a combustion liner extending radially between an inner liner section and an outer liner section. The combustion liner includes a forward portion axially separated from an aft portion. The combustion liner also includes a first sidewall and a second sidewall. The aft portion of the combustion liner defines a turbine nozzle. The first sidewall and the second sidewall each define an axially and radially extending opening. The integrated combustion nozzle also includes an integrated head end coupled to the combustion liner. The integrated head end is in fluid communication with a fuel supply source. The integrated head end includes a first fuel nozzle and a second fuel nozzle disposed at the forward portion of the combustion liner. A fuel plenum is defined between the first fuel nozzle and the second fuel nozzle. The first liner portion extends from the first fuel nozzle and enters the opening in the first wall, so that the first liner portion forms a continuous surface with the first wall of the combustion liner. The integrated head end also includes a second liner portion extending from the second fuel nozzle and enters the opening in the second wall, so that the second liner portion forms a continuous surface with the second wall of the combustion liner.

[0009] These and other features, aspects and advantages of the integrated combustion nozzle and turbine of the present invention will become better understood with reference to the following description and appended claims.The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the technology and, together with the description, serve to explain the principles of the technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] This specification sets forth a complete and enabling disclosure of the integrated combustion nozzle and turbine of the present invention, including the best mode of making and using the systems and methods of the present invention, as will be apparent to one skilled in the art with reference to the accompanying drawings, wherein:

[0011] Figure 1 is a schematic diagram of a turbine according to an embodiment of the present disclosure;

[0012] Figure 2 is an upstream view of an exemplary combustion section of a turbomachine according to an embodiment of the present disclosure;

[0013] Figure 3 is an upstream cross-sectional view of a portion of a combustion section of a turbine according to an embodiment of the present disclosure;

[0014] Figure 4 is a cross-sectional perspective view of a portion of a combustion section of a turbine according to an embodiment of the present disclosure;

[0015] Figure 5 is a perspective view of a portion of a compressor discharge casing according to an embodiment of the present disclosure;

[0016] Figure 6 is a perspective view of an integrated combustion nozzle viewed from a first side according to an embodiment of the present disclosure;

[0017] Figure 7 is a perspective view of an integrated combustion nozzle viewed from a second side according to an embodiment of the present disclosure;

[0018] Figure 8 is a perspective view of an integrated combustion nozzle according to an embodiment of the present disclosure, the integrated combustion nozzle being shown with an exploded integral head end;

[0019] Figure 9 is a cross-sectional view of an integrated combustion nozzle taken along a circumferential direction C of a gas turbine according to an embodiment of the present disclosure; and

[0020] Figure 10 is a cross-sectional perspective view of an integrated combustion nozzle according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0021] Reference will now be made in detail to embodiments of the integrated combustion nozzle and turbine of the present invention, one or more examples of which are shown in the accompanying drawings. Each example is provided by way of explanation of the present invention technology and not as a limitation thereof. In fact, it will be apparent to those skilled in the art that modifications and variations can be made in the present invention technology without departing from the scope or spirit of the present invention technology protected by the claims. For example, features shown or described as part of one embodiment can be used in another embodiment to produce yet another embodiment. Therefore, the present disclosure is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents.

[0022] The detailed description uses numerical and letter designations to refer to features in the drawings. Similar or analogous designations in the drawings and the description have been used to refer to similar or analogous components of the present invention. As used herein, the terms "first," "second," and "third" are used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of each component.

[0023] As used herein, the terms "upstream" (or "upward") and "downstream" (or "downward") refer to relative directions relative to the flow of fluid in a fluid pathway. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction towards which the fluid is flowing. The term "radial" refers to a relative direction that is substantially perpendicular to the axial centerline of a particular component, the term "axially" refers to a relative direction that is substantially parallel and / or coaxially aligned with the axial centerline of a particular component, and the term "circumferentially" refers to a relative direction that extends around the axial centerline of a particular component. Terms indicating approximation, such as "substantially," "substantially," or "approximately" include values ​​that are within ten percent greater or less than the specified value. When used in the context of an angle or direction, such terms include values ​​that are within ten degrees greater or less than the angle or direction. For example, "substantially vertical" includes directions that are within ten degrees of vertical in any direction (e.g., clockwise or counterclockwise).

[0024] Referring now to the accompanying drawings, Figure 1 A schematic diagram of one embodiment of a turbine is shown, which in the illustrated embodiment is a gas turbine 10. Although an industrial or land-based gas turbine is shown and described herein, the present disclosure is not limited to land-based and / or industrial gas turbines unless otherwise indicated in the claims. For example, the present invention as described herein can be used with any type of turbine, including but not limited to steam turbines, aircraft gas turbines, or marine gas turbines.

[0025] As shown, the gas turbine 10 generally includes an inlet section 12, a compressor 14 disposed downstream of the inlet section 12, a combustion section 16 disposed downstream of the compressor 14, a turbine 18 disposed downstream of the combustion section 16, and an exhaust section 20 disposed downstream of the turbine 18. Furthermore, the gas turbine 10 may include one or more shafts 22 coupling the compressor 14 to the turbine 18.

[0026] During operation, air 24 flows through the inlet section 12 and into the compressor 14, where it is gradually compressed, providing compressed air 26 to the combustion section 16. At least a portion of the compressed air 26 is mixed with fuel 28 within the combustion section 16 and combusted to produce combustion gases 30. From the combustion section 16, the combustion gases 30 flow into the turbine 18, where energy (kinetic and / or thermal) is transferred from the combustion gases 30 to rotor blades (not shown), thereby rotating the shaft 22. The mechanical rotational energy can then be used for various purposes, such as powering the compressor 14 and / or generating electricity. The combustion gases 30 exiting the turbine 18 can then be exhausted from the gas turbine 10 via the exhaust section 20.

[0027] Figure 1 Also shown is the axial centerline 38 ( Figure 2 ) coincides with the axis 22. The axial centerline 38 defines an axial direction substantially parallel to and / or along the axial direction A, a radial direction R perpendicular to the axial direction A, and a circumferential direction C extending about the axial direction A.

[0028] Figure 2 An upstream view of the combustion section 16 is provided according to various embodiments of the present disclosure. Figure 2 As shown, the combustion section 16 may be at least partially surrounded by an outer or compressor discharge casing 32. The compressor discharge casing 32 may at least partially define a high pressure chamber 34 that at least partially surrounds various components of the combustor 16. The high pressure chamber 34 may be connected to the compressor 14 ( Figure 1 ) is fluidly connected to receive compressed air 26 from the compressor. In various embodiments, as Figure 2 As shown in , the combustion section 16 includes a segmented annular combustion system 36 including a plurality of integrated combustion nozzles 100 circumferentially arranged about an axial centerline 38 of the gas turbine 10 , which may coincide with the gas turbine shaft 22 .

[0029] Figure 3 1 shows a cross-sectional view of a portion of the combustor section 16 when viewed from the axial direction A of the gas turbine 10 according to an embodiment of the present disclosure. Figure 3 As shown in FIG, each integrated combustion nozzle 100 (three of which are in Figure 3) can be coupled together to form a local combustion zone 101 that is isolated from one another and disposed in the turbine section 18 (eg, a primary combustion zone 102 and a secondary combustion zone 104 ( Figure 6 and Figure 7 ))Upstream. Although Figure 3 Three integrated combustion nozzles 100 are shown, but the combustion section 16 may include enough integrated combustion nozzles 100 to circumferentially surround the axial centerline 38 ( Figure 2 ).

[0030] In an exemplary embodiment, Figure 3 As shown in FIG, each of the integrated combustion nozzles 100 may include a combustion liner 110 and an integrated head end 200 coupled to a forward end of the combustion liner 110. As discussed in more detail below, each integrated head end 200 may be coupled to a fuel supply source 224 ( Figure 4 ) are fluidically connected and may include a first fuel nozzle 202, a second fuel nozzle 204, and a fuel injection assembly 213 positioned downstream of the first fuel nozzle 202 and the second fuel nozzle 204. As shown, the first fuel nozzle 202 of each integrated head end 200 may be positioned proximate to and in contact with the second fuel nozzle 204 of the adjacent integrated head end 200 to inject a first combustible mixture of fuel and air into the local combustion zone 101. In various embodiments, the fuel injection assembly 213 may include a first group of fuel injectors 214 and a second group of fuel injectors 216 disposed downstream of the fuel nozzles 202, 204, and may be operable to inject a second combustible stream of fuel and air into two separate local combustion zones 101.

[0031] In many embodiments, the first group of fuel injectors 214 and the second group of fuel injectors 216 may be oriented relative to each other such that they each extend through opposite ends of the integrated head end 200 and into corresponding local combustion zones 101 so as to inject a second combustible mixture of fuel and air into two separate adjacent local combustion zones 101.

[0032] like Figures 3 to 8As shown in common, the integrated head end 200 may also include a first liner portion 206 and a second liner portion 208 extending from the first fuel nozzle 202 and the second fuel nozzle 204, respectively. In many embodiments, the first liner portion 206 may define a pressure side injection outlet 210 through which a first set of fuel injectors 214 extend to inject a second fuel and air flow into the local combustion zone 101. Similarly, the second liner portion 208 may define a suction side injection outlet 212 through which a second set of fuel injectors 216 extend to inject a second fuel and air flow into the local combustion zone 101. In this way, the first set of fuel injectors 214 of the integrated head end 200 and the second set of fuel injectors 216 of the immediately adjacent integrated head end 200 may extend into a common local combustion zone 101.

[0033] Figure 4 A cross-sectional perspective view of a portion of the combustion section 16 is shown. As shown, a support tube 218 may couple the integrated combustion nozzle 100 to the compressor discharge casing 32. In particular embodiments, the support tube 218 may be a hollow body that surrounds at least one fuel conduit. For example, in many embodiments, the support tube 218 may be coupled to the front end 220 of the integrated head end 200. In various embodiments, the support tube 218 may extend from the front end 220 of the integrated head end 200 through the compressor discharge casing 32 to provide an extended, protected path for the fuel supply conduit 222. In some embodiments, a flange 238 may couple the support tube 218 to the outer surface 33 of the compressor discharge casing 32. In an exemplary embodiment, the support tube 218 may surround at least one fuel supply conduit 222. The at least one fuel supply conduit 222 may be fluidly coupled to the front end 220 of the head end assembly 200, such as to a fuel nozzle inlet 226 or a fuel injector inlet 228 ( Figure 9 ).

[0034] In many embodiments, the liquid fuel cartridge 240 may extend through one of the first fuel nozzle 202 or the second fuel nozzle 204. For example, Figure 4As shown in the figure, the liquid fuel cartridge 240 extends through the second fuel nozzle 204 to inject the liquid fuel stream into the local combustion zone 101. In certain embodiments, the liquid fuel cartridge can extend from an inlet 242 through the compressor discharge casing 32 and one of the first fuel nozzle 202 or the second fuel nozzle 204 to an outlet 244 disposed within the local combustion zone 101. As shown, the liquid fuel cartridge 240 can be coupled to the compressor discharge casing 32 via a mounting flange 246. In certain embodiments, the liquid fuel cartridge 240 can be coupled to the outer surface 33 of the compressor discharge casing 32 via a mounting flange 246. In some embodiments, as shown, the liquid fuel cartridge 240 can be in fluid communication with a liquid fuel supply 225 to deliver the liquid fuel stream to the combustion chamber. In other embodiments, the liquid fuel cartridge can be in fluid communication with a fuel supply 224.

[0035] Figure 5 A perspective view of a portion of the combustion section 16 according to an embodiment of the present disclosure is shown. As shown, each of the liquid fuel cartridges 240 can be circumferentially spaced apart from one another and coupled to the compressor discharge casing 32 such that each extends through the compressor discharge casing 32 and into a corresponding localized combustion zone 101. Similarly, each of the support tubes 218 can be circumferentially spaced apart from one another and coupled to the compressor discharge casing via flanges 238 such that each extends from the compressor discharge casing to a corresponding integrated combustion nozzle 100. In this manner, each of the support tubes 218 can provide a protected path for at least one fluid supply conduit 222, which advantageously protects the conduit from the heat of the combustion section 16.

[0036] Figure 6 A perspective view of the integrated combustion nozzle 100 is provided as viewed from a first side. Figure 7 A perspective view of an integrated combustion nozzle 100 from a second side is provided according to an embodiment of the present disclosure. Figure 2 、 Figure 3 and Figure 4 As shown collectively, the segmented annular combustion system 36 includes a plurality of integrated combustion nozzles 100. As further described herein, each combustor nozzle 100 includes a first sidewall 116 and a second sidewall 118. In a particular embodiment, the first sidewall is a pressure sidewall and the second sidewall is a suction sidewall based on the integration of the sidewalls with the corresponding pressure and suction sides of a downstream turbine nozzle 120. It should be understood that any reference herein to pressure and suction sidewalls represents a particular embodiment, such references are for convenience of discussion, and such references are not intended to limit the scope of any embodiment unless the specific context dictates otherwise.

[0037] like Figure 6 and Figure 7As shown in FIG, each circumferentially adjacent pair of combustor nozzles 100 defines a corresponding primary combustion zone 102 and a corresponding secondary combustion zone 104 therebetween, thereby forming an annular array of primary combustion zones 102 and secondary combustion zones 104. The primary combustion zone 102 and the secondary combustion zone 104 are circumferentially separated or fluidically isolated from adjacent primary combustion zones 102 and secondary combustion zones 104, respectively, by combustion liners 110.

[0038] Each combustor nozzle 100 includes an inner liner segment 106, an outer liner segment 108, and a hollow or semi-hollow combustion liner 110 extending between the inner liner segment 106 and the outer liner segment 108. It is contemplated that more than one (e.g., 2, 3, 4, or more) combustion liners 110 may be positioned between the inner liner segment 106 and the outer liner segment 108, thereby reducing the number of joints between adjacent inner liner segments that need to be sealed. For ease of discussion herein, reference will be made to an integrated combustion nozzle 100 having a single combustion liner 110 between the respective inner liner segment 106 and outer liner segment 108, although a liner segment to combustion liner ratio of 2:1 is not required. Figure 6 and Figure 7 As shown in FIG, each combustion liner 110 includes a front end portion or upstream end portion 112, an aft end portion or downstream end portion 114, Figure 6 In the particular example embodiment shown, the first side wall 116 is the pressure side wall and Figure 7 In the particular example embodiment shown, the second side wall 118 is a suction side wall.

[0039] In the exemplary embodiment, the integrated combustion nozzle 100 further includes an integrated head end 200 coupled to the combustion liner 110 at the forward end 112. In the illustrated exemplary embodiment, the integrated head end 200 includes a first fuel injector 202 and a second fuel injector 204. As shown, the integrated head end 204 is configured to be mounted in the forward end portion 112 of the corresponding combustion liner 110. Figure 3 As shown in FIG, when the integrated combustion nozzle 100 is installed in the combustion section 16, the first fuel injector 202 may contact the second fuel injector 204 of the adjacent integrated combustion nozzle 100 to jointly form the upstream end of the local combustion zone 101. The first fuel injector 202 and the second fuel injector 204 may be referred to as "bundle tube fuel nozzles." However, the fuel nozzles 202, 204 may include or comprise any type of fuel nozzle or combustor (such as a swirl fuel nozzle or a swirl nozzle), and unless specifically recited as such, the claims should not be limited to bundle tube fuel nozzles.

[0040] Each of the fuel nozzles 202, 204 may extend at least partially circumferentially between two circumferentially adjacent combustion liners 110 and / or extend at least partially radially between the respective inner and outer liner segments 106, 108 of the respective combustor nozzle 100. During axially staged fuel injection operation, the fuel nozzles 202, 204 each provide a flow of premixed fuel and air (i.e., a first combustible mixture) to the respective primary combustion zone 102.

[0041] In at least one embodiment, Figure 6 and Figure 7 As shown in FIG, the downstream end portion 114 of one or more of the combustion liners 110 transitions into a generally airfoil-type turbine nozzle 120 that directs and accelerates the flow of combustion products toward the turbine blades. Thus, the downstream end portion 114 of each combustion liner 110 can be considered an airfoil without a leading edge. When the integrated combustion nozzle 100 is installed within the combustion section 16, the turbine nozzle 120 can be positioned immediately upstream of a stage of turbine rotor blades of the turbine 18.

[0042] As used herein, the term "integrated combustion nozzle" refers to a seamless structure that includes a combustion liner 110, a turbine nozzle 120 located downstream of the combustion liner, an inner liner segment 106 (embodied by the turbine nozzle 120) extending from a forward end 112 to an aft end 114 of the combustion liner 110, and an outer liner segment 108 (embodied by the turbine nozzle 120) extending from the forward end 112 to the aft end 114 of the combustion liner 110. In at least one embodiment, the turbine nozzle 120 of the integrated combustion nozzle 100 serves as a first-stage turbine nozzle and is positioned upstream of a first stage of turbine rotor blades.

[0043] As described above, one or more integrated combustion nozzles 100 are formed as a unitary or monolithic structure or body including an inner liner segment 106, an outer liner segment 108, a combustion liner 110, and a turbine nozzle 120. The integrated combustion nozzle 100 may be made as an integrated or seamless component via casting, additive manufacturing (such as 3D printing), or other manufacturing techniques. By forming the combustor nozzle 100 as a monolithic or integrated component, the need for seals between various features of the combustor nozzle 100 may be reduced or eliminated, part count and cost may be reduced, and assembly steps may be simplified or eliminated. In other embodiments, the combustor nozzle 100 may be manufactured, such as by welding, or may be formed by different manufacturing techniques, wherein components made by one technique are joined to components made by the same or another technique.

[0044] In certain embodiments, at least a portion or all of each integrated combustion nozzle 100 may be formed from a ceramic matrix composite (CMC) or other composite material. In other embodiments, a portion or all of each integrated combustion nozzle 100 (more specifically, the turbine nozzle 120 or its trailing edge) may be made from a highly oxidation-resistant material (e.g., coated with a thermal barrier coating).

[0045] In another embodiment (not shown), at least one of the combustion liners 110 may taper to a trailing edge aligned with the longitudinal (axial) axis of the combustion liner 110. That is, the combustion liners 110 may not be integrated with the turbine nozzle 120. In these embodiments, it may be desirable to have an uneven number of combustion liners 110 and turbine nozzles 120. Conical combustion liners 110 (i.e., those without integrated turbine nozzles 120) may be used alternately with combustion liners 110 with integrated turbine nozzles 120 (i.e., integrated combustion nozzles 100) or in some other pattern.

[0046] In certain embodiments, Figure 6 and Figure 7 As shown in FIG, the integrated head end 200 may further include a first liner portion 206 and a second liner portion 208. The first liner portion 206 and the second liner portion 208 may each extend generally axially from the integrated head end 200 and at least partially form the primary combustion zone 102. For example, the first liner portion 206 may extend from the first fuel nozzle 202 such that it is aligned with and forms a continuous surface with the pressure sidewall 116. Similarly, the second liner portion 208 may extend from the second fuel nozzle 204 such that it is aligned with and forms a continuous surface with the suction sidewall 118.

[0047] In many embodiments, such as Figure 6 As shown in , the first liner portion 206 of each integrated head end 200 may define one or more pressure side injection outlets 210 through which a first set of fuel injectors 214 may extend to inject a second combustible mixture of fuel and air into the secondary combustion zone 104. Similarly, as Figure 7 As shown in , the second liner portion 208 of each integrated head end 200 may define one or more suction side injection outlets 212 through which a second set of fuel injectors 216 may extend to inject a second combustible mixture of fuel and air into the secondary combustion zone 104. Each respective primary combustion zone 102 is defined upstream of corresponding pressure side injection outlets 210 and / or suction side injection outlets 212 of a pair of circumferentially adjacent integrated combustion nozzles 100. Each secondary combustion zone 104 is defined downstream of corresponding pressure side injection outlets 210 and / or suction side injection outlets 212 of the pair of circumferentially adjacent integrated combustion nozzles 100.

[0048] Although the pressure side injection outlet 210 is Figure 6 and Figure 7 10 as residing in a common radial or injection plane relative to the axial centerline of the integrated combustion nozzle 100, or at a common axial distance from the downstream end portion 114 of the combustion liner 110, but in certain embodiments, one or more of the pressure side injection outlets 210 may be axially staggered relative to radially adjacent pressure side injection outlets 210, thereby offsetting the axial distance of the pressure side injection outlet 210 from the downstream end portion 114 for a particular pressure side injection outlet 210. Similarly, although Figure 7 The suction side injection outlets 212 are shown in a common radial or injection plane or at a common axial distance from the downstream end portion 114 of the combustion liner 110 , but in particular embodiments, one or more of the suction side injection outlets 212 may be axially staggered relative to radially adjacent suction side injection outlets 212 , thereby offsetting the axial distance of the pressure side injection outlet 212 from the downstream end portion 114 for a particular suction side injection outlet 212 .

[0049] Figure 8 A perspective view of an integrated combustion nozzle 100 according to an embodiment of the present disclosure is shown, with the combustion liner 110 exploded from the integrated head end 200. As shown, the combustion liner 110 can define openings 170 and 172 to facilitate coupling of the integrated head end 200 to the openings 170 and 172 and partially define the primary combustion zone 102 and the secondary combustion zone 104. More specifically, the pressure sidewall 116 can define the opening 170, which can be a generally rectangular cutout corresponding to the shape of the first liner portion 206. Similarly, the suction sidewall 118 can define the opening 172, which can be a generally rectangular cutout corresponding to the shape of the second liner portion 208. In many embodiments, the first liner portion 206 can be slidably received by the opening 170 of the pressure sidewall 116, and the second liner portion 208 can be slidably received by the opening 172 of the suction sidewall 118.

[0050] When the integrated head end 200 is in the installed position ( Figure 6 and Figure 7), the first liner portion 206 can form a continuous surface with the pressure sidewall 116 such that there is no abrupt change in profile between the pressure sidewall 116 and the first liner portion 206. In many embodiments, the first liner portion 206 can be a substantially flat plate that extends radially and axially and corresponds to the shape of the opening 170. For example, the first liner portion can fill the opening 170 so as to partially define both the primary combustion zone 102 and the secondary combustion zone 104. Similarly, when the integrated head end 200 is in the installed position, the second liner portion 208 can form a continuous surface with the suction sidewall 118 such that there is no abrupt change in profile between the suction sidewall 118 and the second liner portion 208. In many embodiments, the second liner portion 208 can be a substantially flat plate that extends radially and axially and corresponds to the shape of the opening 172. For example, the second liner portion 208 can fill the opening 172 so as to partially define both the primary combustion zone 102 and the secondary combustion zone 104.

[0051] Figure 9 shows a cross-sectional view of the integrated combustion nozzle 100 taken along the circumferential direction C of the gas turbine 10 (circumferentially between the pressure side wall 116 and the suction side wall 118), and Figure 10 1 shows a cross-sectional view of an integrated combustion nozzle 100 taken along a radial direction R according to an embodiment of the present disclosure. Figure 9 and Figure 10 As shown therein, fuel injection assembly 213 may be positioned downstream of first fuel nozzle 202 and second fuel nozzle 204 such that the fuel injection assembly advantageously provides a second fuel and air flow into the combustion chamber.

[0052] In many embodiments, the integrated head end 200 can further define a fuel plenum 248 axially between the front end 220 of the integrated head end 200 and the fuel injection assembly 213. In many embodiments, the fuel plenum 248 can be defined in the circumferential direction C between the first fuel nozzle 202 and the second fuel nozzle 204.

[0053] In various embodiments, such as Figure 9 As shown in the figure, the at least one fuel supply conduit 222 may include a first fuel nozzle supply conduit 230 connected to the fuel nozzle inlet 226 at the front end 220 of the integrated head end 200, a second fuel nozzle supply conduit 232 connected to another fuel nozzle inlet 226 at the front end 220 of the integrated head end 200, a first fuel injector supply conduit 234 connected to the fuel injector inlet 228 at the front end 220 of the integrated head end 200, and a second fuel injector supply conduit 236 connected to another fuel injector inlet 228 at the front end 220 of the integrated head end 200.

[0054] In many embodiments, the support tube 218 can surround each of the conduits 230, 232, 234, 236 such that the support tube 218 provides a thermal barrier between the high-temperature compressed air 26 in the high-pressure plenum 34 and the conduits 230, 232, 234, 236 containing the cool-temperature fuel. In an exemplary embodiment, each of the conduits 230, 232, 234, 236 can be a solid hollow tube, i.e., they do not include conformal bellows, which advantageously reduces component cost and assembly time.

[0055] like Figure 9 As shown in FIG, the fuel nozzle inlet 226 can be defined by the integrated head end 200. In many embodiments, the fuel nozzle inlet 226 can be in fluid communication with both the fuel supply source 224 and the fuel plenum 248, such that fuel from the fuel supply source 224 is delivered to the fuel plenum 248 via the fuel inlet 226. Figure 9 and Figure 10 As shown, a first plurality of fuel ports 250 may extend between the fuel plenum 248 and the first fuel nozzle 202, such that the first fuel nozzle 202 is in fluid communication with the fuel plenum 248 via the first plurality of fuel ports 250. Similarly, a second plurality of fuel ports 252 may extend between the fuel plenum 248 and the second fuel nozzle 204, such that the second fuel nozzle 204 is in fluid communication with the fuel plenum 248 via the second plurality of fuel ports 252.

[0056] In an exemplary embodiment, Figure 9 and Figure 10 As shown in FIG, the integrated head end 200 may define at least one fuel circuit 254 in fluid communication with a fuel supply source 224 and a fuel injection assembly 213. As shown, the at least one fuel circuit 224 may extend from a fuel injector inlet 228 through a fuel plenum to the fuel injection assembly. Figure 9 and Figure 10 In the embodiment shown in FIG, the integrated head end 200 includes two fuel circuits 254 that provide fluid communication between the fuel supply 224 and the fuel injection assembly 213. For example, one fuel circuit 254 can deliver fuel to the first group of fuel injectors 214, while the other fuel circuit 254 delivers fuel to the second group of fuel injectors 216. In other embodiments (not shown), the integrated head end 200 can include more or fewer fuel circuits, depending on the number of fuel injectors.

[0057] In many embodiments, the integrated head end can be formed as a single component as a whole. That is, each of the subcomponents (e.g., fuel nozzles 202, 204, liner portions 206, 208, fuel injection assembly 213, and any other subcomponents of the integrated head end 200) can be manufactured together as a single body. In an exemplary embodiment, this can be accomplished by utilizing an additive manufacturing system. However, in other embodiments, other manufacturing techniques, such as casting or other suitable techniques, can be used. In this regard, utilizing additive manufacturing methods, each integrated head end 200 can be formed as a single piece of continuous metal as a whole, and therefore can include fewer subcomponents and / or joints compared to existing designs. Integrating each integrated head end 200 through additive manufacturing can advantageously improve the overall assembly process. For example, integral formation reduces the number of separate parts that must be assembled, thereby reducing the associated time and overall assembly costs. In addition, existing problems such as leakage, joint quality between separate parts, and overall performance can be advantageously reduced.

[0058] The integrated head end 200 described herein defines both a primary form of fuel / air delivery to the combustion zone and a secondary form of fuel / air delivery to the combustion zone. Specifically, the integrated head end 200 may define fuel nozzles 202, 204, a fuel injection assembly 213, and a means for delivering fuel from a fuel supply source 224 to the fuel nozzles 202, 204, and the fuel injection assembly 213. Thus, due at least to the reduction in separate individual components, the overall integrated combustion nozzle 100 may be relatively simple and quick to assemble compared to existing designs. Furthermore, because the integrated head end 200 is a single component, the integrated burner nozzle 100 may be scalable to a much more compact size than in previous designs due to the ease of assembly. For example, rather than including multiple individual components that require space to assemble relative to one another, the integrated head end 100 may comprise a single component that requires only a few assembly steps.

[0059] Furthermore, the support tube 218 advantageously provides a thermally protective barrier for the fuel supply conduit 222, thereby allowing the use of a solid hollow tube (rather than a bellows), which reduces part and assembly costs. Additionally, the support tube 218 may define one or more air inlets 280. For example, the one or more air inlets 280 may be defined on the support tube 218 within the compressor discharge casing 32 (at a location proximate the flange 238) such that compressed air flows into the support tube 218 at the one or more air inlets 280. The one or more air inlets 280 may be in fluid communication with the high pressure plenum 34. Compressed air may flow through the support tube 218 and exit at an outlet or outlet tube 282 (e.g., Figure 10). An outlet tube 282 may extend from support tube 218 through one of first fuel nozzle 202 or second fuel nozzle 204 to combustion zone 101. In this manner, purge air may flow from air inlet 280 through the interior of support tube 218 to air outlet tube 282 and be injected at combustion zone 101, which may advantageously purge or sweep away any fuel that leaks from fuel supply conduit 222 into combustion zone 101.

[0060] This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any combined methods. The patentable scope of the invention is defined by the claims and may include other examples that occur to those skilled in the art. If these other examples include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims, then these other examples are intended to be within the scope of the claims.

Claims

1. An integrated combustion nozzle (100), comprising: a combustion liner (110) extending in a radial direction (R) between an inner liner segment (106) and an outer liner segment (108), the combustion liner (110) including a first sidewall (116), a second sidewall (118), and a forward portion axially separated from an aft portion, the aft portion of the combustion liner (110) defining a turbine nozzle, wherein the first sidewall (116) and the second sidewall (118) each define a respective opening (170, 172) extending axially and radially; An integrated head end (200) coupled to the combustion liner (110), the integrated head end (200) being in fluid communication with a fuel supply (224), wherein the integrated head end (200) comprises: a first fuel nozzle (202) and a second fuel nozzle (204), the first fuel nozzle and the second fuel nozzle being disposed at the forward end portion of the combustion liner (110), wherein a fuel plenum (248) is defined between the first fuel nozzle (202) and the second fuel nozzle (204); a first liner portion (206) extending from the first fuel nozzle (202) and into the corresponding openings (170, 172) of the first sidewall (116) such that the first liner portion (206) forms a continuous surface with the first sidewall (116) of the combustion liner (110); A second liner portion (208) extends from the second fuel nozzle (204) and into the corresponding openings (170, 172) of the second sidewall (118) such that the second liner portion (208) forms a continuous surface with the second sidewall (118) of the combustion liner (110).

2. The integrated combustion nozzle (100) of claim 1, further comprising a fuel injection assembly (213) positioned downstream of the first fuel nozzle (202) and the second fuel nozzle (204).

3. The integrated combustion nozzle (100) of claim 2, wherein the fuel injection assembly (213) includes a first set of fuel injectors (214) extending through the first liner portion (206) of the integrated head end (200) and a second set of fuel injectors (216) extending through the second liner portion (208) of the integrated head end (200).

4. The integrated combustion nozzle (100) of claim 2, wherein the integrated head end (200) defines at least one fuel circuit (254) in fluid communication with the fuel supply source (224) and the fuel injection assembly (213), the at least one fuel circuit (254) extending from a fuel injector inlet (228) through the fuel plenum (248) to the fuel injection assembly (213).

5. The integrated combustion nozzle (100) of claim 1, wherein the integrated head end (200) defines a fuel nozzle inlet (226) in fluid communication with a fuel supply (224) and the fuel plenum (248). The integrated combustion nozzle (100) of any preceding claim, further comprising a support tube (218) coupling the integrated combustion nozzle (100) to a compressor discharge casing (32).

7. The integrated combustion nozzle (100) of claim 6, wherein the support tube (218) surrounds at least one fuel supply source (224) conduit, the fuel supply source (224) conduit being fluidly coupled to one of a fuel nozzle inlet (226) or a fuel injector inlet (228) at a forward end of the integrated head end.

8. The integrated combustion nozzle (100) of claim 7, wherein the support tube (218) defines at least one air inlet in fluid communication with a high-pressure plenum defined within the compressor discharge casing (32), wherein an air outlet tube extends from the support tube (218) through one of the first fuel nozzle (202) or the second fuel nozzle (204) to a combustion zone, and wherein purge air flows from the one or more air inlets to the air outlet tube through an interior of the support tube (218).

9. The integrated combustion nozzle (100) of claim 1, further comprising a liquid fuel cartridge extending through one of the first fuel nozzle (202) or the second fuel nozzle (204).

10. The integrated combustion nozzle (100) of claim 9, wherein the liquid fuel cartridge is coupled to the compressor discharge casing (32) via a mounting flange.

11. A turbine (10), comprising: compressor section (14); a compressor discharge casing (32) disposed downstream of the compressor section (14); a turbine section (18) disposed downstream of the compressor discharge casing (32); An annular combustion system (36) disposed within the compressor discharge casing (32), the annular combustion system (36) comprising a plurality of integrated combustion nozzles (100) disposed in an annular array about an axial centerline of the turbine (10), wherein each integrated combustion nozzle (100) comprises: a combustion liner (110) extending in a radial direction (R) between an inner liner segment (106) and an outer liner segment (108), the combustion liner (110) including a first sidewall (116), a second sidewall (118), and a forward portion axially separated from an aft portion, the aft portion of the combustion liner (110) defining a turbine nozzle, wherein the first sidewall (116) and the second sidewall (118) each define a respective opening (170, 172) extending axially and radially; An integrated head end (200) coupled to the combustion liner (110), the integrated head end (200) being in fluid communication with a fuel supply (224), wherein the integrated head end (200) comprises: a first fuel nozzle (202) and a second fuel nozzle (204), the first fuel nozzle and the second fuel nozzle being disposed at the forward end portion of the combustion liner (110), wherein a fuel plenum (248) is defined between the first fuel nozzle (202) and the second fuel nozzle (204); a first liner portion (206) extending from the first fuel nozzle (202) and into the corresponding opening (170, 172) of the first sidewall (216) such that the first liner portion (206) forms a continuous surface with the first sidewall (216) of the combustion liner (110); A second liner portion (208) extends from the second fuel nozzle (204) and into the corresponding opening (170, 172) of the second sidewall (218) such that the second liner portion (208) forms a continuous surface with the second sidewall (218) of the combustion liner (110).

12. The turbomachine (10) of claim 11, further comprising a fuel injection assembly (213) positioned downstream of the first fuel nozzle (202) and the second fuel nozzle (204).

13. The turbine (10) of claim 12, wherein the fuel injection assembly (213) includes a first set of fuel injectors (214) extending through the first liner portion (206) of the integrated head end (200) and a second set of fuel injectors (216) extending through the second liner portion (208) of the integrated head end (200).

14. The turbine (10) of claim 12, wherein the integrated head end (200) defines at least one fuel circuit (254) in fluid communication with the fuel supply (224) and the fuel injection assembly (213), the at least one fuel circuit (254) extending from a fuel injector inlet (228) through the fuel plenum (248) to the fuel injection assembly (213).

15. The turbine (10) of claim 11, wherein the integrated head end (200) defines a fuel nozzle inlet (226) in fluid communication with a fuel supply (224) and the fuel plenum (248).

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