Transfer channel with improved cooling for a turbomachine

Abstract

Turbine system (10), comprising: a transfer channel (50) with an inlet (52) and an outlet (54) and a channel passage (56) extending between the inlet (52) and the outlet (54) and defining a longitudinal axis (90), a radial axis (94) and a tangential axis (92), wherein the outlet (54) of the transfer channel (50) is offset relative to the inlet (52) along the longitudinal axis (90) and the tangential axis (92), wherein the channel passage (56) includes an upstream section (172) extending from the inlet (52) and a downstream section (174) extending from the outlet (54); a rib (160) extending from an outer surface (192) of the channel passage (56) and around an entire circumference of the outer surface (192), wherein the rib (160) divides the channel passage (56) into the upstream section (172) and the downstream section (174) and defines and fluidically separates an upstream cavity (162) and a downstream cavity (164), wherein the upstream cavity (162) extends continuously around the upstream section (172) of the channel passage (56) from the rib (160) to a first end surrounding the inlet (52) of the transfer channel (50) to allow a first fraction (182) of a working fluid to be directed to the first end,wherein the downstream cavity (164) extends continuously around the downstream section (174) of the channel passage (56) from the rib (160) to a second end surrounding the outlet (54) of the transfer channel (50) to allow a second portion (184) of the working fluid to be directed towards the second end.

Description

AREA OF INVENTION

[0001] The subject of the invention described here is generally turbomachinery, such as gas turbine systems and in particular transfer channels with improved cooling properties in turbomachinery. BACKGROUND OF THE INVENTION

[0002] Turbine systems are just one example of turbomachinery widely used in fields such as power generation. For instance, a conventional gas turbine system contains a compressor section, a burner section, and at least one turbine section. The compressor section is designed to compress air as it flows through it. The air then flows from the compressor section to the burner section, where it is mixed with fuel and combusted, producing a hot gas stream. This hot gas stream is delivered to the turbine section, which utilizes it to extract energy and drive the compressor, an electric generator, and various other loads.

[0003] The burner sections of turbine systems generally contain pipes or channels to direct the combusted hot gas to the turbine section(s). More recently, burner sections have been introduced that incorporate channels which redirect the flow of hot gas, for example, by accelerating and rotating the hot gas stream.

[0004] For example, channels have been introduced for burner sections which, although they allow the hot gas to flow longitudinally, additionally shift the flow radially or tangentially, resulting in different angular components. These designs offer several advantages by eliminating first-stage guide nozzles from the turbine sections. Previously used to shift the hot gas flow, the first-stage guide nozzles are no longer strictly necessary due to the design of these channels. Eliminating the first-stage guide nozzles can reduce associated pressure drops and increase the efficiency and power output of the turbine system.

[0005] Various design and operating parameters influence the design and operation of burner sections. For example, higher combustion gas temperatures generally improve the thermodynamic efficiency of the burner section. However, such elevated temperatures necessitate improved cooling of the various turbine system components to reduce the risk of damage to these components due to exposure to high temperatures. However, there are several problems with known cooling techniques for turbine systems. For instance, cooling air leakage reduces cooling efficiency and also results in less air being supplied to the combustion chamber. Additionally, current designs for cooling various components make inefficient use of the cooling air, leading to further inefficiencies.These design and operating parameters are of particular importance when using channels that, as discussed above, shift the flow of hot gas within them, due to the high temperatures and heat transfer coefficients generated in the channels, and especially in the downstream sections of the channels.

[0006] JP S58-182 034 A discloses a turbine system comprising a transfer duct with an inlet, an outlet, and a channel extending between them. The outlet of the transfer duct is offset relative to the inlet along both the longitudinal and radial axes. An impact sleeve with a plurality of impact cooling openings surrounds the transfer duct in a spaced arrangement. The turbine system further includes several T-shaped ribs spaced along the longitudinal axis, extending outward from an outer surface of the channel and attached in U-shaped sections formed on the inner surface of the impact sleeve. The ribs define a series of spaces between the transfer duct and the impact sleeve, into which compressor discharge air can be introduced through the impact cooling openings to cool the respective sections of the transfer duct by impact cooling.The used impact cooling air is then discharged directly into the hot gas path through holes in the transfer duct.

[0007] US Patent 7,181,914 B2 discloses a gas turbine engine comprising, in serial flow connection, an air inlet, a fan, a medium-pressure compressor, a high-pressure compressor, a combustion chamber assembly, a high-pressure turbine, a medium-pressure turbine, a low-pressure turbine, and an exhaust nozzle. The combustion chamber assembly is fluidically connected to the high-pressure turbine via a transfer channel.

[0008] JP 2000-146 186 A discloses an arrangement of a gas turbine combustion chamber with a transfer channel and a flow sleeve surrounding the transfer channel, the two defining a gap between them for supplying compressor air to the combustion chamber. One or more rows of guide vanes spaced circumferentially and longitudinally are attached to the inner surface of the flow sleeve, extending partially through the gap towards the transfer channel. The guide vanes serve to direct the airflow in the gap and to make it more uniform along the circumference in order to reduce local flow and cooling variations.

[0009] US 7 721 547 B2 discloses a transfer channel for directing a gas flow from a combustion chamber to a first stage of a turbine section in a combustion turbine, comprising an inlet, an outlet and a channel passage extending between them, wherein the outlet is offset relative to the inlet along the longitudinal, radial and tangential axes.

[0010] Therefore, improved burner areas for turbomachinery, such as turbine systems, would be desirable in this field. In particular, burner areas with improved cooling designs would be advantageous. BRIEF DESCRIPTION OF THE INVENTION

[0011] Aspects and advantages of the invention are presented in the following description or may be apparent from the description or can be recognized through the practical implementation of the invention.

[0012] In one embodiment, a turbine system is provided. The turbine system includes a transfer channel with an inlet and an outlet, and a channel passage extending between the inlet and the outlet, defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transfer channel is offset relative to the inlet along the longitudinal and tangential axes. The channel passage comprises an upstream section extending from the inlet and a downstream section extending from the outlet.The turbine system further includes a rib extending from an outer surface of the channel and around its entire circumference, the rib dividing the channel into an upstream and a downstream section, defining and fluidically separating an upstream and a downstream cavity. The upstream cavity extends continuously around the upstream section of the channel from the rib to a first end surrounding the inlet of the transfer channel, to allow a first fraction of a working fluid to be directed to that first end.The downstream cavity extends continuously around the downstream section of the channel passage from the rib to a second end surrounding the outlet of the transfer channel to allow a second portion of the working fluid to be directed to the second end.

[0013] The turbine system can further comprise a flow sleeve substantially surrounding the transfer channel, wherein the flow sleeve has an upstream outlet, a downstream outlet and a flow sleeve passage extending between the upstream outlet and the downstream outlet, wherein the sleeve passage has an upstream section extending from the upstream outlet and a downstream section extending from the downstream outlet, and wherein the rib further divides the upstream section of the flow sleeve and the downstream section of the flow sleeve.

[0014] The upstream sections of the transfer channel and flow sleeve of each of the aforementioned turbine systems can define an upstream cavity between them, while the downstream sections of the transfer channel and flow sleeve can define a downstream cavity between them, with the rib essentially isolating the upstream cavity and the downstream cavity from each other.

[0015] The flow sleeve of each of the aforementioned turbine systems can be an impact sleeve.

[0016] The rib of each of the aforementioned turbine systems can be formed in one piece with the passage.

[0017] Several film cooling holes can be defined in the downstream section of the channel passage of each of the aforementioned turbine systems.

[0018] The outlet of the transfer channel of each of the aforementioned turbine systems may be offset relative to the inlet along the radial axis.

[0019] The downstream section may also have several internal pins.

[0020] The turbine system of each of the aforementioned types may further comprise a turbine section in conjunction with the transfer channel, wherein the turbine section may comprise a rotor blade assembly of a first stage.

[0021] In one embodiment of the aforementioned turbine system, no guide nozzles are arranged upstream of the rotor blade assembly of the first stage.

[0022] In a further embodiment, a turbine system is provided. The turbine system comprises a transfer channel with an inlet, an outlet, and a channel passage extending between the inlet and the outlet, defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transfer channel is offset relative to the inlet along the longitudinal and tangential axes. The turbine system further comprises a flow sleeve substantially surrounding the transfer channel, the flow sleeve having an upstream outlet, a downstream outlet, and a sleeve passage extending between the upstream and downstream outlets.The turbine system further comprises a cavity defined between the transfer channel and the flow sleeve, wherein the cavity has an upstream cavity and a downstream cavity, and a rib positioned between the transfer channel and the flow sleeve, wherein the rib divides the upstream cavity and the downstream cavity.

[0023] The rib of the aforementioned turbine system can essentially isolate the upstream cavity and the downstream cavity from each other.

[0024] The rib of each of the aforementioned turbine systems can extend from an outer surface of the transfer channel.

[0025] The flow sleeve of each of the aforementioned turbine systems can be an impact sleeve.

[0026] Several film cooling holes can be defined in the downstream section of the channel passage of each of the aforementioned turbine systems.

[0027] The outlet of the transfer channel of each of the aforementioned turbine systems may also be offset relative to the inlet along the radial axis.

[0028] Each of the aforementioned turbine systems may further comprise a turbine section in conjunction with the transfer channel, wherein the turbine section may comprise a rotor blade assembly of a first stage.

[0029] Optionally, no guide nozzles are arranged upstream of the first stage's impeller assembly.

[0030] These and other features, aspects, and advantages of the present invention will be better understood by reference to the following description and the accompanying claims. The accompanying drawings, which are included in and form part of this patent specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] A complete and fundamental disclosure of the present invention, including its best embodiment, to the person skilled in the art, is described below in the remainder of the patent specification with reference to the accompanying drawings, in which: Fig. 1 a schematic view of a gas turbine system according to an embodiment of the present disclosure; Fig. 2 a cross-sectional view of various sections of a gas turbine system according to an embodiment of the present disclosure; Fig. 3 a perspective view of an annular arrangement of transfer channels and associated impact sleeves according to an embodiment of the present disclosure; Fig. 4 a rear perspective view from above of several transfer channels and associated impact sleeves according to an embodiment of the present disclosure; Fig. 5 a rear perspective view from above of several transfer channels, wherein associated impact sleeves have been removed, according to an embodiment of the present disclosure; Fig. 6 a cross-sectional view of sections of a transfer channel and an associated impact sleeve according to an embodiment of the present disclosure; Fig. 7 a cross-sectional view of sections of a transfer channel and an associated impact sleeve according to a further embodiment of the present disclosure; Fig. Figure 8 shows a cross-sectional view of a turbine area of ​​a gas turbine system according to a further embodiment of the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0032] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is given within the context of an explanation of the invention and not a limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variants of the present invention can be made without derogating from the scope of protection or the inventive concept of the invention. For example, features shown or described as part of one embodiment can be used with another embodiment to give yet another embodiment of the invention. Thus, the present invention is intended to include such modifications and variants insofar as they fall within the scope of protection of the appended claims and their equivalents.

[0033] Fig. Figure 1 is a schematic representation of a turbomachine, which in the illustrated embodiment is a gas turbine system 10. It should be understood that the turbine system 10 of this disclosure need not be a gas turbine system 10, but can instead be any suitable turbine system 10, such as a steam turbine system or another suitable system. Furthermore, it should be understood that the turbomachine according to this disclosure need not be a turbine system, but can instead be any other suitable turbomachine. The gas turbine system 10 can include a compressor section 12, a burner section 14, which can contain several burners 15 as discussed below, and a turbine section 16. The compressor section 12 and turbine section 16 can be connected via a shaft 18. The shaft 18 can consist of a single shaft or of several shaft segments coupled together to form the shaft 18.The shaft 18 can further be connected to a generator or other suitable energy storage device, or can, for example, be directly connected to an electrical grid. An inlet section 19 can supply an airflow to the compressor section 12, and exhaust gases can be discharged from the turbine section 16 through an exhaust section 20 and / or discharged and / or utilized in the system 10 or in another suitable system, discharged to the atmosphere, or recycled by a heat recovery steam generator.

[0034] In Fig. Figure 2 is a simplified drawing showing several sections of a gas turbine system 10. The in Fig. The gas turbine system 10 shown in Figure 2 has a compressor section 12 for pressurizing a working fluid, which is essentially pressurized air, but could also be any other suitable fluid flowing through the system 10. The pressurized working fluid discharged from the compressor section 12 flows into a burner section 14, which may contain several burners 15 (of which only one is in Fig. (as shown in Figure 2), which are arranged in a ring-shaped configuration around an axis of the system 10. The working fluid entering the burner section 14 is mixed with fuel, such as natural gas or another suitable liquid or gas, and combusted. Hot combustion gases flow from each burner 15 to a turbine section 16 to drive the system 10 and generate electricity.

[0035] A burner 15 in the gas turbine 10 can contain a variety of components for mixing and burning the working fluid and the fuel. For example, the burner 15 can contain a housing 21, such as a compressor outlet housing 21. A variety of sleeves, which can be axially extending annular sleeves, can be arranged at least partially in the housing 21. The in Fig. The two sleeves shown extend axially along a substantially longitudinal axis 98, such that the inlet of a sleeve is aligned axially with the outlet. For example, a burner insert 22 can substantially define a combustion zone 24 therein. The combustion of the working fluid, fuel, and an optional oxidizer can substantially take place in the combustion zone 24. The resulting hot combustion gases can flow substantially axially downstream along the longitudinal axis 98 through the combustion insert 22 into a transition piece 26 and then substantially axially along the longitudinal axis 98 through the transition piece 26 and into the turbine region 16.

[0036] The burner 15 may further include one or more fuel nozzles 40. Fuel may be supplied to the fuel nozzles 40 by one or more distributors (not shown). As discussed below, the fuel nozzle or nozzles 40 may supply the fuel and, optionally, the working fluid to the combustion zone 24 for combustion.

[0037] According to the presentation in the Fig. According to the present description, a burner 15 can include one or more transfer channels 50, as described in sections 3 to 6. The transfer channels 50 described in this description can be provided in place of various axially extending sleeves of other burners. For example, a transfer channel 50 can replace the axially extending adapter 26 and, optionally, the burner insert 22 of a burner 15. Thus, the transfer channel can extend from the fuel nozzles 40 or from the burner insert 22. As discussed below, the transfer channel 50 can provide several advantages over the axially extending burner inserts 22 and adapters 26 for allowing working fluid to flow through and to the turbine area 16.

[0038] As shown, the multiple transfer channels 50 can be arranged in an annular configuration around a longitudinal axis 90. Furthermore, each transfer channel 50 can extend between one or more fuel nozzles 40 and the turbine section 16. For example, each transfer channel 50 can extend from the fuel nozzles 40 of the turbine section 16. Thus, the working fluid can flow essentially from the fuel nozzles 40 through the transfer channel 50 to the turbine section 16. In some embodiments, the transfer channels 50 can advantageously allow the omission of the first-stage guide nozzles in the turbine section, which can reduce or eliminate an associated pressure loss and increase the efficiency and output power of the system 100.

[0039] Each transfer channel 50 can have an inlet 52 and an outlet 54, with a passage 56 between them. The passage 56 defines a combustion chamber 58 through which the hot combustion gases flow. The inlet 52 and outlet 54 of a transfer channel 50 can have substantially circular or oval cross-sections, rectangular cross-sections, triangular cross-sections, or any other suitable polygonal cross-section. Furthermore, it should be understood that the inlet 52 and outlet 54 of a transfer channel 50 need not have similarly shaped cross-sections. For example, in one embodiment, the inlet 52 can have a substantially circular cross-section, while the outlet 54 can have a substantially rectangular cross-section.

[0040] Furthermore, the passage 56 can be substantially tapered between the inlet 52 and the outlet 54. For example, in an exemplary embodiment, at least one section of the passage 56 can be substantially conical. Additionally or alternatively, however, the passage 56 or any section thereof can have a substantially rectangular cross-section, a triangular cross-section, or any other suitable polygonal cross-section. It should be understood that the cross-sectional shape of the passage 56 can change over the entire passage 56 or any section thereof as the passage 56 tapers towards the relatively smaller outlet 54.

[0041] The outlet 54 of each of the multiple transfer channels 50 can be offset relative to the inlet 52 of the corresponding transfer channel 50. The term "offset," as used herein, means arranged at a distance along the specified coordinate direction. The outlet 54 of each of the multiple transfer channels 50 can be offset longitudinally relative to the inlet 52 of the corresponding transfer channel 50, for example, along the longitudinal axis 90.

[0042] Additionally, in exemplary embodiments, the outlet 54 of each of the multiple transfer channels 50 can be offset tangentially to the inlet 52 of the corresponding transfer channel 50, for example along a tangential axis 92. Since the outlet 54 of each of the multiple transfer channels 50 is offset tangentially to the inlet 52 of the corresponding transfer channel 50, the transfer channels 50 can advantageously utilize the tangential component of the working fluid flow through the transfer channels 50 to eliminate the need for guide nozzles for the first stage in the turbine section 16, as discussed below.

[0043] Furthermore, in exemplary embodiments, the outlet of each of the multiple transfer channels 50 can be offset radially relative to the inlet 52 of the corresponding transfer channel 50, for example along a radial axis 94. Since the outlet 54 of each of the multiple transfer channels 50 is offset radially relative to the inlet 52 of the corresponding transfer channel 50, the transfer channels 50 can advantageously utilize the radial component of the working fluid flow through the transfer channels 50, thereby eliminating the need for guide nozzles of a first stage in the turbine region 16, as discussed below.

[0044] It should be understood that the tangential axis 92 and the radial axis 94 are individually defined for each transition channel 50 with respect to the annular arrangement of the transition channels as shown in the figure. Fig. 3 defined perimeter, and that the axes 92 and 94 vary for each transfer channel 50 around the perimeter based on the number of transfer channels 50 arranged in a ring-shaped arrangement around the longitudinal axis 90.

[0045] As discussed below, after hot combustion gases flow through the transfer channel 50, they can flow from the transfer channel 50 into the turbine section 16. As shown in Fig. According to the present description, a turbine section 16 can contain a shroud 102 which can define a hot gas path 104. The shroud 102 can be formed from several shroud blocks 106. The shroud blocks 106 can be arranged in one or more annular arrangements, each of which can define a section of the hot gas path 104 therein.

[0046] The turbine section 16 can further comprise several rotor blades 112 and several guide nozzles 114. Each of the several rotor blades 112 and guide nozzles 114 can be arranged at least partially in the hot gas path 104. Furthermore, the several rotor blades 112 and the several guide nozzles 114 can be arranged in one or more annular arrangements, each of which can define a section of the hot gas path 104.

[0047] The turbine section 16 can contain several turbine stages. Each stage can contain several rotor blades 112 arranged in an annular arrangement and several guide nozzles 114 arranged in an annular arrangement. For example, in one embodiment, the turbine section 16 can contain three stages as shown in Fig. 8. For example, a first stage of the turbine section 16 can include a (not shown) first-stage guide nozzle assembly and a first-stage rotor blade assembly 122. The guide nozzle assembly can include several guide nozzles 114 arranged and mounted circumferentially around the shaft 18. The rotor blade assembly 122 can include several rotor blades 112 arranged circumferentially around the shaft 18 and connected to the shaft 18. However, in exemplary embodiments in which the turbine section is connected to the burner section 14, which has several transfer channels 50, the first-stage guide nozzle assembly can be omitted, so that no guide nozzles are arranged upstream of the first first-stage rotor blade assembly 122. Upstream can be defined with respect to the flow of hot combustion gases through the hot gas path 104.

[0048] A second stage of the turbine section 16 can include a second-stage guide nozzle assembly 123 and a second-stage rotor blade assembly 124. The guide nozzles 114 contained in the guide nozzle assembly 123 can be arranged circumferentially around the shaft 18 and fixed. The rotor blades 112 contained in the rotor blade assembly 124 can be arranged circumferentially around the shaft 18 and connected to the shaft 18. The second-stage guide nozzle assembly 123 is thus arranged between the first-stage rotor blade assembly 122 and the second-stage rotor blade assembly 124 along the hot gas path 104. A third stage of the turbine section 16 can include a third-stage guide nozzle assembly 125 and a third-stage rotor blade assembly 126. The guide nozzles 114 contained in the guide nozzle arrangement 125 can be arranged and fixed circumferentially around the shaft 18.The rotor blades 112 contained in the rotor blade assembly 126 can be arranged circumferentially around the shaft 18 and connected to the shaft 18. The guide nozzle assembly 125 of the third stage is thus arranged between the rotor blade assembly 124 of the second stage and the rotor blade assembly 126 of the third stage along the hot gas path 104.

[0049] It should be understood that the turbine section 16 is not limited to three stages, but that instead any number of stages is within the scope of protection and inventive concept of the present disclosure.

[0050] As in the Fig. 4, Fig. 6 and Fig. As shown in Figure 7, in exemplary embodiments a flow sleeve 140 can substantially surround a transfer channel 50 in a substantially comprehensive manner. A flow sleeve 140 surrounding a transfer channel 50 circumferentially can define a cavity 142 between them. Compressed working fluid 146 from the housing 21 can flow through the cavity 142 to provide convection cooling for the transfer channel 50. Furthermore, in some embodiments the flow sleeve 140 can be an impact sleeve. In these embodiments, impact holes 144 can be defined in the sleeve 140 as shown. Compressed working fluid 146 from the housing 21 can flow through the impact holes 144 and impinge on the transfer channel 50 before flowing through the cavity 142, thus providing additional impact cooling of the transfer channel.

[0051] Each flow sleeve 140 can have an upstream outlet 152, a downstream outlet 154, and a passage 156 between them. Each flow sleeve 140 can extend between one or more fuel nozzles 40 and the turbine section 16, thus surrounding at least a section of the associated transfer channel 50. Therefore, similar to the transfer channels 50 discussed above, the downstream outlet 154 of each of the multiple flow sleeves 140 can be offset longitudinally, radially, and / or tangentially relative to the upstream outlet 152 of the corresponding flow sleeve 140.

[0052] As discussed, the working fluid 146 can flow through the cavity 142 defined between the transfer channel 50 and the flow sleeve 140. This working fluid 146 can cool the transfer channel 50 during operation of the turbomachine. As discussed above, it is desirable that the working fluid 146 be used efficiently for cooling the transfer channel 50. Thus, in exemplary embodiments, a rib 160 can be included in the cavity 142 of one or more transfer channels 50 and the associated flow sleeves 140. The rib 160 can be positioned between the transfer channel 50 and the flow sleeve 140 and can divide the cavity 142 into an upstream cavity 162 and a downstream cavity 164.Thus, the transfer channel 50 as well as its passage 56 can be divided by the rib 160 into an upstream section 172 and a downstream section 174, and the flow sleeve 140 can be similarly divided by the rib 160 into an upstream section 176 and a downstream section 178.

[0053] By dividing the cavity 142 and the associated transition channel 50 and the flow sleeve 140, the rib 160 can allow a portion 182 of the working fluid 146 in the upstream cavity 162 to advantageously provide the flow and cooling properties required for that cavity, while allowing a portion 184 of the working fluid 146 in the downstream cavity 164 to provide separate advantageous flow and cooling properties required for that cavity. For example, as shown in the Fig. 6 and Fig. As shown in Figure 7, the portion 184 in the downstream cavity 164 flows essentially downstream, advantageously cooling the downstream section 174 of the passage 56. In particular, the flow 186 of the hot combustion gases through the downstream section 174 can have relatively higher Mach numbers due to the design of the transfer channel 50 and its passage 56, and the heat transfer coefficients in the downstream section 174 can be relatively larger. The use of fins 160 according to the present description can advantageously provide targeted cooling of the downstream section 174. Furthermore, in exemplary embodiments, the downstream section 174 of the passage 56 can contain several film cooling passages 190 defined therein, which extend between an outer surface 192 and an inner surface 194 of the passage 56.Each film cooling passage 190 can transfer a film cooling fraction 196 of the downstream part 184 of the working fluid 146 to the combustion chamber 58 of the transfer channel 50. This film cooling fraction 196 can flow essentially downstream along the inner surface 194 of the passage 56 and thereby provide further cooling of the downstream section 174.

[0054] What next in the Fig. 6 and Fig. As shown in Figure 7, the portion 182 in the upstream cavity 162 can flow essentially upstream, thereby advantageously cooling the upstream section 172 of the passage 56. Such a flow can cool the upstream section 172 while simultaneously supplying this portion 182 to the fuel nozzles 40 for mixing with fuel and combustion. The use of fins 160 according to the present description can thus advantageously provide targeted cooling of the upstream section 172 while simultaneously efficiently supplying a portion 182 of the working fluid 146 for combustion.

[0055] In exemplary embodiments, the rib 160 can essentially isolate the upstream cavity 162 and the downstream cavity 164 (and various sections thereof) from each other. In these embodiments, the rib 160 effectively seals the upstream cavity 162 and the downstream section of cavity 164 from each other in such a way that no or only a minimal proportion 182 of the working fluid 146 can flow from the upstream cavity 162 past the rib 160 into the downstream cavity 164, and no or only a minimal proportion 184 of the working fluid 146 can flow from the downstream cavity 164 past the rib 160 into the upstream cavity 162. Insulating the cavities 162, 164 increases the cooling efficiency and the utilization of the working fluid 146.

[0056] A rib 160 according to the present description extends substantially circumferentially around the circumference of a transfer channel 50, thus dividing the transfer channel 50 into the upstream section 172 and the downstream section 174, and dividing the flow sleeve 140 into the upstream section 176 and the downstream section 178. The rib 160 can consist of a single component or of several components positioned between the transfer channel 50 and the flow sleeve 140 to provide such a division. In exemplary embodiments, a rib 160 extends from the outer surface 192 of the passage 56. The rib 160 can be formed in one piece with the passage 56 as shown in the illustration. Fig. 6. For example, the rib 160 and the passage 56 can be cast as a single component. Alternatively, the rib 160 can be attached to the passage 56, for example, by welding, brazing, bolting, etc. Additionally or alternatively, the rib 160 can extend from an inner surface 198 of the flow sleeve 140 and can be formed in one piece with or attached to the flow sleeve 140.

[0057] The use of a fin 160 as described above can thus provide improved cooling for transfer channels 50 and the turbomachines using the transfer channels 50. Such cooling can, as described above, be particularly targeted and effectively cool the transfer channels 50 while simultaneously reducing leakage and providing sufficient working fluid 146 for combustion.

[0058] As further explained in Fig. As shown in Figure 7, a transfer channel 50 according to the present description can contain several internal pins 200, which further facilitate its cooling. In these embodiments, the passage 56 or a section thereof can be substantially hollow and define an interior region 202 between the outer surface 192 and the inner surface 194. In some embodiments, the pins 200 can be arranged in the interior region 202 in one or more substantially circumferential rows, extending substantially between the outer surface 192 and the inner surface 194. Access holes 204 can be defined in the outer surface 192 such that the working fluid 146, or a portion thereof, such as the portion 184, flows through the access holes 204 into the interior region 202. In exemplary embodiments, the access holes 204 can be arranged upstream of the pins 202.This working fluid 146, or a portion thereof, can then flow past the pins 200, cooling the pins 200 and the transfer channel 50. Film cooling passages 206 or other suitable outlet holes can be defined in the inner surface 194 such that the working fluid 146, or a portion thereof, can then be discharged from the interior 202 into the combustion chamber 58 of the transfer channel 50, to flow essentially downstream, for example along the inner surface 194 of the passage 56, in the combustion chamber 58, thereby providing further cooling at the passage 56. In exemplary embodiments, film cooling passages 206 or other suitable outlet holes can be arranged downstream of the pins 200.

[0059] In exemplary embodiments, as shown, pins 200 can be provided only in the downstream section 174 of the transfer channel 50. Additionally or alternatively, however, pins 200 can be included in the upstream section 172. Furthermore, it should be understood that the use of pins 200 according to this description is not limited to the illustrated embodiments, but can instead be used in any suitable transfer channel 50.

[0060] Additionally, in some embodiments where pins 200 are used, various sections of the flow sleeve 140 may not be required. For example, as in Fig.As shown in Figure 7, the flow sleeve 140, due to the use of pins 200 in the downstream section 174 of the transfer channel 50, contains only the upstream section 176 and not the downstream section 178. Alternatively, however, the downstream section 174 may be included. Furthermore, any suitable section of the flow sleeve 140 may or may not be included when the pins 200 are used.

[0061] This description uses examples to disclose the invention, including its best embodiment, and to enable anyone skilled in the art to put the invention into practice, including the manufacture and use of all elements and systems and the execution of all processes involved. The patentable scope of the invention is defined by the claims and may include further examples that are apparent to a person skilled in the art. Such further examples shall be included in the scope of the invention if they have structural elements that do not differ from the wording of the claims or if they contain equivalent structural elements with insignificant modifications compared to the wording of the claims.

[0062] Turbine systems are provided. In one embodiment, the turbine system comprises a transfer channel with an inlet and an outlet, and a channel passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transfer channel is offset relative to the inlet along the longitudinal axis and the tangential axis. The channel passage comprises an upstream section extending from the inlet and a downstream section extending from the outlet. The turbine system further comprises a rib extending from an outer surface of the channel passage, the rib dividing the upstream section and the downstream section. REFERENCE MARK LIST: 10 turbine systems 12 Compressor area 14 Burner area 15 burners 16 Turbine area 18 wave 19 Entrance area 20 Exhaust area 21 cases 22 burner insert 24 combustion zone 26 Transition piece 30 Flow sleeve 32 Flow path 34 Impact sleeve 36 Flow path 38 external annular space 40 Fuel nozzle 50 Transfer channel 52 Admission 54 Outlet 56 Passage 58 Combustion chamber 90 longitudinal axis 92 tangential axis 94 radial axis 98 longitudinal axis 102 Cover band 104 Hot gas path 106 Cover block 112 Running blade 114 Guide nozzle 122 First stage impeller arrangement 123 Second-stage guide nozzle arrangement 124 Second-stage impeller arrangement 125 Third-stage guide nozzle arrangement 126 Third-stage guide vane arrangement 140 Flow / impact sleeve 142 cavity 144 Impact Hole 146 Working fluid 152 Outlet 154 Outlet 156 Passage 160 rib 162 upstream cavity 164 downstream cavity 172 Upstream section (diversion channel) 174 downstream section (diversion channel) 176 Upstream section (flow sleeve) 178 downstream section (flow sleeve) 182 Fraction of working fluid (upstream) 184 Fraction of working fluid (downstream) 186 Hot gas 190 film cooling passage 192 Outer surface (transfer channel) 194 Inner surface (conveyor channel) 196 Film cooling component (working fluid) 198 Inner surface (flow sleeve) 200 pens 202 Interior 204 Access hole 206 Film cooling passage

Claims

[1] Turbine system (10) comprising: a transfer channel (50) with an inlet (52) and an outlet (54) and a channel passage (56) extending between the inlet (52) and the outlet (54) and defining a longitudinal axis (90), a radial axis (94) and a tangential axis (92), wherein the outlet (54) of the transfer channel (50) is offset relative to the inlet (52) along the longitudinal axis (90) and the tangential axis (92), wherein the channel passage (56) includes an upstream section (172) extending from the inlet (52) and a downstream section (174) extending from the outlet (54); a rib (160) extending from an outer surface (192) of the channel passage (56) and around an entire circumference of the outer surface (192), wherein the rib (160) divides the channel passage (56) into the upstream section (172) and the downstream section (174) and defines and fluidically separates an upstream cavity (162) and a downstream cavity (164), wherein the upstream cavity (162) extends continuously around the upstream section (172) of the channel passage (56) from the rib (160) to a first end surrounding the inlet (52) of the transfer channel (50) to allow a first fraction (182) of a working fluid to be directed to the first end,wherein the downstream cavity (164) extends continuously around the downstream section (174) of the channel passage (56) from the rib (160) to a second end surrounding the outlet (54) of the transfer channel (50) to allow a second portion (184) of the working fluid to be directed towards the second end. [2] Turbine system (10) according to claim 1, further comprising a flow sleeve (140) substantially surrounding the transfer channel (50), wherein the flow sleeve (140) has an upstream outlet (152), a downstream outlet (154) and a flow sleeve passage (156) extending between the upstream outlet (152) and the downstream outlet (154), wherein the flow sleeve (140) has an upstream section (176) extending from the upstream outlet (152) and a downstream section (178) extending from the downstream outlet (154), and wherein the rib (160) further comprises the upstream section (176) of the flow sleeve (140) and the downstream section (178). The horizontal section (178) divides the flow sleeve (140). [3] Turbine system (10) according to claim 2, wherein the upstream sections (172, 176) of the transfer channel (50) and the flow sleeve (140) define the upstream cavity (162) between them, wherein the downstream sections (174, 178) of the transfer channel (50) and the flow sleeve (140) define the downstream cavity (164) between them, and wherein the rib (160) substantially isolates the upstream cavity (162) and the downstream cavity (164) from each other. [4] Turbine system (10) according to claim 2, wherein the flow sleeve (140) is an impact sleeve. [5] Turbine system (10) according to claim 1, wherein the rib (160) is formed in one piece with the channel opening (56). [6] Turbine system (10) according to claim 1, wherein several film cooling passages (190) are defined in the downstream section (174) of the channel passage (56). [7] Turbine system (10) according to claim 1, wherein the outlet (54) of the transfer channel (50) is further offset relative to the inlet (52) along the radial axis (94) and / or wherein the downstream section (174) further comprises several internal pins (200). [8] Turbine system (10) according to claim 1, which further comprises a turbine section (16) in conjunction with the transfer channel (50), wherein the turbine section (16) comprises a rotor blade arrangement (122) of a first stage. [9] Turbine system (10) according to claim 8, wherein no guide nozzles are arranged upstream of the rotor blade assembly (122) of the first stage. [10] Turbine system (10) comprising: a transfer channel (50) with an inlet (52), an outlet (54) and a channel passage (56) extending between the inlet (52) and the outlet (54) and defining a longitudinal axis (90), a radial axis (94) and a tangential axis (92), wherein the outlet (54) of the transfer channel (50) is offset relative to the inlet (52) along the longitudinal axis (90) and the tangential axis (92); a flow sleeve (140) substantially surrounding the transfer channel (50), wherein the flow sleeve (140) has an upstream outlet (152), a downstream outlet (154) and a flow sleeve passage (156) extending between the upstream outlet (152) and the downstream outlet (154); a cavity (142) defined between the transfer channel (50) and the flow sleeve (140), wherein the cavity (142) has an upstream cavity (162) and a downstream cavity (164) separated from each other in terms of flow; and a rib (160) positioned between the transfer channel (50) and the flow sleeve (140), extending from an outer surface (192) of the channel opening (56) and around its entire circumference, the rib (160) dividing the upstream cavity (162) and the downstream cavity (164), the upstream cavity (162) extending from the rib (160) to a first end surrounding the inlet (52) of the transfer channel (50) to allow a first portion (182) of a working fluid to be directed to the first end, the downstream cavity (164) extending continuously from the rib (160) to a second end surrounding the outlet (54) of the transfer channel (50) to allow a second to enable the proportion (184) of the working fluid to flow towards the second end.

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