Turbine guide vanes in a gas turbine engine

Abstract

A turbine vane (200) in a gas turbine engine includes an inner platform (202), an outer platform (204), and a vane airfoil (206) positioned therebetween. The vane airfoil includes a first cooling passage (212) extending between the outer platform and the inner platform, and a second cooling passage (214) extending between the outer platform and the inner platform. The second cooling passage is arranged downstream of the first cooling passage with respect to a flow direction. The turbine vane includes a crossover pipe (300) disposed between the second cooling passage and the inner platform. The crossover pipe includes an inlet (304), an outlet (306), and a pipe wall (302) enclosing a hollow interior. The inlet is positioned a distance within the second cooling passage. The outlet is positioned at least partially through an aperture of the inner platform.

Description

Background Technology

[0001] Industrial gas turbine engines typically consist of a compressor section, a turbine section, and a combustion section located between them. The compressor section includes multi-stage rotary compressor blades and stationary compressor guide vanes. The combustion section typically includes multiple burners.

[0002] The turbine section consists of multiple stages of rotating turbine blades and stationary turbine guide vanes. Turbine blades and guide vanes often operate in high-temperature environments and are internally cooled. Summary of the Invention

[0003] A turbine guide vane in a gas turbine engine includes: an inner platform having an orifice; an outer platform; and a guide vane airfoil positioned between the inner and outer platforms. The guide vane airfoil includes: a first cooling passage extending between the outer and inner platforms; and a second cooling passage extending between the outer and inner platforms. The second cooling passage is arranged downstream of the first cooling passage relative to the flow direction. The turbine guide vane includes a jumper tube disposed between the second cooling passage and the inner platform. The jumper tube includes an inlet, an outlet, and a tube wall enclosing a hollow interior. The inlet is positioned at a distance within the second cooling passage. The outlet is positioned to at least partially pass through the orifice of the inner platform. The turbine guide vane includes a cover plate attached to the jumper tube and the inner platform.

[0004] A turbine guide vane in a gas turbine engine includes: an inner platform having an orifice; an outer platform; and a guide vane airfoil positioned between the inner and outer platforms. The guide vane airfoil includes: a first cooling passage extending between the outer and inner platforms; and a second cooling passage extending between the outer and inner platforms. The second cooling passage is arranged downstream of the first cooling passage relative to the flow direction. The guide vane airfoil includes a third cooling passage arranged downstream of the second cooling passage relative to the flow direction. The turbine guide vane includes a cross-connector having an inlet positioned at a distance within the second cooling passage and an outlet positioned to at least partially pass through the orifice of the inner platform and fluidly communicate with the outside of the inner platform. The first cooling passage guides a first flow of cooling air from the first cooling passage to the third cooling passage. The cross-connector guides a second flow of cooling air from the second cooling passage to the outside of the inner platform. Attached Figure Description

[0005] To facilitate identification of any particular element or action being discussed, one or more of the most significant digits in the reference numerals refer to the drawing number in which the element was first introduced.

[0006] Figure 1 It is a longitudinal cross-sectional view of a gas turbine engine taken along a plane containing the longitudinal axis or central axis.

[0007] Figure 2 It is a cross-sectional view of the turbine guide vane taken along a plane parallel to the flow direction.

[0008] Figure 3 This is a perspective view of the cross-pipeline.

[0009] Figure 4 yes Figure 2 An enlarged view of a portion of the turbine guide vanes.

[0010] Figure 5 yes Figure 4 Different views of the turbine guide vanes. Detailed Implementation

[0011] Before explaining any embodiments of the invention in detail, it will be understood that the invention is not limited in its application to the details of the construction and the arrangement of components set forth in this specification or illustrated in the following drawings. The invention is capable of having other embodiments and can be practiced or implemented in various ways. Moreover, it will be understood that the wording and terminology used herein are for descriptive purposes and should not be considered limiting.

[0012] Various techniques relating to systems and methods will now be described with reference to the accompanying drawings, wherein similar reference numerals denote similar elements throughout. The drawings discussed below, as well as the various embodiments used to describe the principles of this disclosure in this patent document, are merely illustrative and should not be construed in any way as limiting the scope of this disclosure. Those skilled in the art will understand that the principles of this disclosure can be implemented in any suitably arranged device. It will be understood that functions described as being implemented by certain system elements can be performed by multiple elements. Similarly, for example, an element may be configured to perform functions described as being implemented by multiple elements. Many of the inventive teachings of this application will be described with reference to exemplary, non-limiting embodiments.

[0013] Furthermore, it should be understood that, unless explicitly limited in some examples, the words or phrases used herein should be interpreted broadly. For example, the terms “comprising,” “having,” and “including,” and their derivatives, mean inclusion without limitation. The singular forms “a,” “an,” and “the” are intended to also include the plural forms, unless the context explicitly indicates otherwise. Additionally, the term “and / or,” as used herein, refers to and covers any and all possible combinations of one or more of the associated listed items. The term “or” is inclusive, meaning and / or, unless the context explicitly indicates otherwise. The phrases “associated with” and “associated with,” and their derivatives, may mean including, encompassing, interconnected with, containing, contained within, connected to or connected with, linked to or connected to, connectable to, cooperate with, interleaved, juxtaposed, proximate, combined with or combined with, having, possessing the properties of, etc. Furthermore, while multiple embodiments or constructions may be described herein, any features, methods, steps, components, etc., described with respect to one embodiment are equally applicable to other embodiments without specific statements to the contrary.

[0014] Furthermore, although the terms “first,” “second,” “third,” etc., may be used herein to refer to various elements, information, functions, or actions, these elements, information, functions, or actions should not be limited by these terms. Rather, these numerical adjectives are used to distinguish different elements, information, functions, or actions from one another. For example, without departing from the scope of this disclosure, a first element, information, function, or action may be referred to as a second element, information, function, or action, and similarly, a second element, information, function, or action may be referred to as a first element, information, function, or action.

[0015] Additionally, the term "adjacent" may mean: one element is relatively close to another element but does not contact it; or the element is in contact with another part, unless the context clearly indicates otherwise. Furthermore, unless otherwise clearly stated, the phrase "based on" is intended to mean "at least partially based on". The terms "approximately" or "roughly" or similar terms are intended to cover variations in values ​​within normal industry manufacturing tolerances for that dimension. In the absence of an available industry standard, unless otherwise stated, twenty percent of the variation will fall within the meaning of these terms.

[0016] Figure 1An example of a gas turbine engine 100 is illustrated, comprising a compressor section 102, a combustion section 104, and a turbine section 106 arranged along a central axis 112. The compressor section 102 includes multiple compressor stages 114, each compressor stage 114 including a set of rotating blades 116 and a set of fixed guide vanes 118 or adjustable guide vanes. A rotor 134 supports the rotating blades 118 for rotation about the central axis 112 during operation. In some configurations, a single one-piece rotor 134 extends the length of the gas turbine engine 100 and is supported at either end by a bearing for rotation. In other configurations, the rotor 134 is assembled from several individual spools attached to each other or may include multiple disc sections attached via one or more bolts.

[0017] The compressor section 102 is in fluid communication with the inlet section 108 to allow the gas turbine engine 100 to draw atmospheric air into the compressor section 102. During operation of the gas turbine engine 100, the compressor section 102 draws in atmospheric air and compresses it for delivery to the combustion section 104. The illustrated compressor section 102 is an example of a compressor section 102, and other arrangements and designs are possible.

[0018] In the illustrated configuration, the combustion section 104 includes a plurality of individual burners 120, each of which operates to mix a fuel stream with compressed air from the compressor section 102 and to burn the air-fuel mixture to produce a stream of high-temperature, high-pressure combustion gases or exhaust gases 122. Of course, many other arrangements of the combustion section 104 are possible.

[0019] Turbine section 106 includes multiple turbine stages 124, each turbine stage 124 including a plurality of rotating turbine blades 126 and a plurality of stationary turbine guide vanes 128. Turbine stages 124 are arranged to receive exhaust gas 122 from combustion section 104 at turbine inlet 130 and expand the gas to convert thermal and pressure energy into rotational or mechanical work. Turbine section 106 is connected to compressor section 102 to drive compressor section 102. For a gas turbine engine 100 used for power generation or as a prime mover, turbine section 106 may also be connected to a generator, pump, or other device to be driven. Similar to compressor section 102, other designs and arrangements of turbine section 106 are possible.

[0020] The exhaust section 110 is located downstream of the turbine section 106 and is arranged to receive the flow of expanded exhaust gas 122 from the final turbine stage 124 in the turbine section 106. The exhaust section 110 is arranged to efficiently guide the exhaust gas 122 away from the turbine section 106 to ensure efficient operation of the turbine section 106. Many variations and design differences are possible in the exhaust section 110. Therefore, the exhaust section 110 illustrated is only one example of those variations.

[0021] The control system 132 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and control various operations of the gas turbine engine 100. In a preferred configuration, the control system 132 is typically microprocessor-based and includes memory devices and data storage devices for collecting, analyzing, and storing data. Additionally, the control system 132 provides output data to various devices, including monitors, printers, indicators, etc., which allow users to interact with the control system 132 to provide inputs or adjustments. In the example of a power generation system, a user can input a power output setpoint, and the control system 132 can adjust various control inputs to achieve that power output efficiently.

[0022] The control system 132 is capable of controlling various operating parameters, including but not limited to the position of the variable inlet guide vanes, fuel flow rate and pressure, engine speed, valve position, generator load, and generator excitation. Of course, other applications may have fewer or more controllable devices. The control system 132 also monitors various parameters to ensure the proper operation of the gas turbine engine 100. Some of the monitored parameters may include inlet air temperature, compressor outlet temperature and pressure, combustor outlet temperature, fuel flow rate, generator power output, bearing temperature, etc. Many of these measurements are displayed to the user and recorded for subsequent review if necessary.

[0023] In this specification, the term "axial" or "axially" refers to the direction along the longitudinal axis of the gas turbine engine. The term "radial" or "radially" refers to the direction perpendicular to the longitudinal axis of the gas turbine engine. The term "downstream" or "aft" refers to the direction along the flow direction. The term "upstream" or "front" refers to the direction opposite to the flow direction.

[0024] Figure 2 The turbine guide vane 200 is parallel to the exhaust gas 122 (in Figure 1The image shows a cross-sectional view taken from a plane along the flow direction 228. The turbine guide vane 200 is one of a plurality of turbine guide vanes 200 arranged circumferentially adjacent to each other in the gas turbine engine 100 to define a row of fixed turbine guide vanes 200. The turbine guide vane 200 can be one of the fixed turbine guide vanes 126 used in the gas turbine engine 100.

[0025] The turbine guide vane 200 includes an inner platform 202, an outer platform 204, and a guide vane airfoil 206 positioned between the inner platform 202 and the outer platform 204. The inner platform 202 has an orifice 230. The guide vane airfoil 206 includes a leading edge 208 and a trailing edge 210 relative to the flow direction 228 of the exhaust gas 122.

[0026] The turbine guide vane 200 includes a plurality of cooling channels disposed within the airfoil portion 206. The plurality of cooling channels extend between the inner platform 202 and the outer platform 204. The plurality of cooling channels include a first cooling channel 212 disposed at or near the leading edge 208, a second cooling channel 214 disposed downstream of the first cooling channel 212 relative to the flow direction 228, a third cooling channel 216 disposed downstream of the second cooling channel 214, and a trailing edge cooling channel 218. The first cooling channel 212 and the second cooling channel 214 form a front cooling circuit 224. The third cooling channel 216 and the trailing edge cooling channel 218 form a rear cooling circuit 226. Figure 2 In the configuration shown, the turbine guide vane 200 has two cooling circuits: a front cooling circuit 224 and a rear cooling circuit 226. However, in other configurations, the turbine guide vane 200 may have any number of cooling circuits. It is also possible that each cooling circuit may have any number of cooling channels.

[0027] Turbulence ribs 220 are arranged in each of the cooling channels. Figure 2In the configuration shown, turbulence ribs 220 are disposed in the first cooling channel 212, the second cooling channel 214, the third cooling channel 216, and the trailing edge cooling channel 218. The turbulence ribs 220 may be uniformly distributed between the inner platform 202 and the outer platform 204 along the first cooling channel 212, the second cooling channel 214, the third cooling channel 216, and the trailing edge cooling channel 218. The turbulence ribs 220 are oriented at an angle relative to the flow direction of the cooling air 222. For example, the turbulence ribs 220 may be oriented at a 45-degree angle relative to the flow direction of the cooling air 222. Alternatively, the turbulence ribs 220 may be oriented at any desired angle relative to the flow direction of the cooling air 222, as defined by the design of the gas turbine engine 100. Furthermore, it is possible that one or more of the first cooling channel 212, the second cooling channel 214, the third cooling channel 216, and the trailing edge cooling channel 218 may omit the turbulence ribs 220 wholly or partially.

[0028] The turbine guide vane 200 includes a cross-connector 300 disposed between the inner platform 202 and the second cooling channel 214. One end of the cross-connector 300 is positioned at a certain distance within the second cooling channel 214. The other end of the cross-connector 300 is positioned to at least partially pass through an orifice 230 of the inner platform 202 and is in fluid communication with the outside of the inner platform 202.

[0029] Figure 3 yes Figure 2 The diagram shows a perspective view of the crosspipe 300. The crosspipe 300 has a generally hollow cuboid shape. The crosspipe 300 has curved edges at the corners of adjacent side surfaces. The crosspipe 300 has a pipe wall 302 enclosing its hollow interior. The crosspipe 300 has an inlet 304 and an outlet 306. The inlet 304 has a generally rectangular shape. The outlet 306 has a generally rectangular shape. Of course, in practice, the inlet 304 and the outlet 306 can have any shape as desired. The area of ​​the outlet 306 is different from the area of ​​the inlet 304. Figure 3 In the configuration shown, the area of ​​outlet 306 is larger than the area of ​​inlet 304. It is possible that the area of ​​outlet 306 is smaller than or the same as the area of ​​inlet 304.

[0030] The pipe wall 302 has a curved shape such that the minimum area of ​​the cross-connector 300 is not at the inlet 304 or the outlet 306, but between the inlet 304 and the outlet 306. The pipe wall 302 has a smooth curved shape. The pipe wall 302 is curved at the four side surfaces of the cross-connector 300. The curvature of the pipe wall 302 is different at the different side surfaces. The portion of the pipe wall 302 facing the outlet 306 may have a straight shape. Of course, in practice, the pipe wall 302 may have any shape as desired.

[0031] The jumper pipe 300 has a throttling plate 308. The throttling plate 308 is attached to the inner surface 310 of the jumper pipe 300 and extends around the inner periphery of the jumper pipe 300. The throttling plate 308 may be welded to the inner periphery of the jumper pipe 300 or formed as part of the jumper pipe 300. The throttling plate 308 is positioned at a distance from the outlet 306. This distance may be designed to allow welding to be performed. It is possible that the throttling plate 308 is attached to the inner surface 310 of the jumper pipe 300 by any method known in the industry. It is also possible that the throttling plate 308 is positioned at the outlet 306.

[0032] exist Figure 3 In the configuration shown, the bridging pipe 300 has a generally hollow cuboid shape. However, in other configurations, the bridging pipe 300 may have any desired shape, such as a hollow cylindrical shape, a hollow conical shape, a hollow elliptical shape, etc. It is also possible that the area of ​​the outlet 306 may be equal to or smaller than the area of ​​the inlet 304. It is also possible that the pipe wall 302 may be curved at two opposite side surfaces of the bridging pipe 300. It is also possible that the curvature of the pipe wall 302 may be the same at different side surfaces. It is also possible that the pipe wall 302 may be straight between the inlet 304 and the outlet 306.

[0033] Figure 4 yes Figure 2 An enlarged view of a portion of the turbine guide vane 200 viewed in a direction perpendicular to the flow direction 228. Figure 5 yes Figure 4 Different views of the turbine guide vane 200 viewed in a direction parallel to the flow direction 228.

[0034] refer to Figure 4 Along the direction parallel to the flow direction 228, the size of the inlet 304 is smaller than the size of the outlet 306. Alternatively, along the direction parallel to the flow direction 228, the size of the inlet 304 may be larger than or the same as the size of the outlet 306.

[0035] refer to Figure 5 Along the direction perpendicular to the flow direction 228, the size of the inlet 304 is larger than the size of the outlet 306. Alternatively, along the direction perpendicular to the flow direction 228, the size of the inlet 304 may be smaller than or the same as the size of the outlet 306.

[0036] refer to Figure 4 and Figure 5The outlet 306 of the cross-connector 300 is positioned as an opening 230 through the inner platform 202. A cover plate 402 is attached to the outer surface 404 of the cross-connector 300 and extends around the outer periphery of the cross-connector 300. The cover plate 402 is positioned near the outlet 306 of the cross-connector 300. The cover plate 402 is also attached to the outer surface of the inner platform 202 facing away from the outer platform 204. Thus, the cross-connector 300 is secured to the inner platform 202 via the cover plate 402. The cover plate 402 may be welded, brazed, or otherwise attached to the cross-connector 300 and the inner platform 202. The outlet 306 of the cross-connector 300 may protrude from the inner platform 202 by a certain distance. This distance is selected to allow welding to be performed. However, it is possible that the cover plate 402 may be attached to the cross-connector 300 and the inner platform 202 using any attachment technique known in the industry.

[0037] The inlet 304 of the cross-connector 300 is located at a certain distance within the second cooling channel 214. The inlet 304 of the cross-connector 300 is located at at least a portion of the span length of the second cooling channel 214. For example, the inlet 304 of the cross-connector 300 may be located between 3% and 20% of the span length of the guide vane airfoil 206. Alternatively, the cross-connector 300 may be located within the second cooling channel 214 at any desired percentage of the span length of the guide vane airfoil 206, such as between 4% and 18%, or between 5% and 15%, etc.

[0038] The second cooling channel 214 has a hoop 406 disposed at its inner periphery. The hoop 406 is a protrusion extending away from the inner periphery of the second cooling channel 214. The inlet 304 of the cross-connector 300 is configured to be adjacent to or abut against the hoop 406. However, in other configurations, the hoop 406 may be omitted from the second cooling channel 214.

[0039] During assembly, the crosspipe 300 is inserted through the inner platform 202 into the second cooling channel 214 until the inlet 304 of the crosspipe 300 contacts the hoop 406. The crosspipe 300 can then be pulled away from the hoop 406 a distance to allow for thermal growth of the crosspipe 300 during operation of the gas turbine engine 100. This distance may be, for example, between 0.5 mm and 1 mm, or any desired distance.

[0040] In the operation of the gas turbine engine 100, refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5Cooling air 222 is discharged from the compressor section 102 to the turbine section 106. A first flow of cooling air 222 is fed into a first cooling passage 212, and a second flow of cooling air 222 is fed in parallel through the outer platform 204 into a second cooling passage 214. Cooling air 222 flows from the outer platform 204 to the inner platform 202 in the first cooling passage 212 and the second cooling passage 214 to cool the guide vane airfoil section 206.

[0041] refer to Figure 2 The first stream of cooling air 222 exits the first cooling channel 212 at the inner platform 202 and passes through the flow area 502 (e.g., Figure 5 (As illustrated in the diagram) The airflow 222 flows around the outer periphery of the cross-connector 300 and enters the third cooling passage 216. The flow region 502 is defined between the inner surface of the guide vane airfoil 206 and the outer periphery of the cross-connector 300. The first flow of cooling air 222 flows from the inner platform 202 to the outer platform 204 in the third cooling passage 216 to cool the guide vane airfoil 206. The first flow of cooling air 222 exits the third cooling passage 216 at the outer platform 204 and meanders to the trailing edge cooling passage 218. The first flow of cooling air 222 flows from the outer platform 204 to the inner platform 202 in the trailing edge cooling passage 218 and exits the turbine guide vane 200 at the trailing edge 210. The profile of the tube wall 302 is selected to guide the first flow of cooling air 222 from the first cooling passage 212 through the flow region 502 and around the outer periphery of the cross-connector 300 to the third cooling passage 216, while reducing pressure loss when it turns into the third cooling passage 216 at the inner platform 202.

[0042] A second stream of cooling air 222 exits the second cooling passage 214 and enters the cross-connector 300 at the inlet 304. This second stream of cooling air 222 flows through the cross-connector 300 and exits the turbine guide vane 200 from the outlet 306 of the cross-connector 300 to the outside of the inner platform 202. The cross-connector 300 guides the cooling air 222 from the second cooling passage 214 to the outside of the inner platform 202. The cooling air 222 exiting the turbine guide vane 200 provides cooling to other components of the gas turbine engine 100, such as the interstage sealing housing (not shown). The size of the throttle plate 308 is selected to control the amount of cooling air 222 vented from the turbine guide vane 200 to meet the cooling requirements of the interstage sealing housing.

[0043] The temperature of the cooling air 222 at the outlet of the first cooling channel 212 and the second cooling channel 214 is higher than the temperature of the cooling air 222 at the inlet of the first cooling channel 212 and the second cooling channel 214. Since the first cooling channel 212 is located at the leading edge 208 or closer to the leading edge than the second cooling channel 214, the temperature of the cooling air 222 at the outlet of the first cooling channel 212 is higher than the temperature of the cooling air 222 at the outlet of the second cooling channel 214.

[0044] By placing the transimpedance pipe 300 between the inner platform 202 and the second cooling passage 214, cooler cooling air 222 exiting the second cooling passage 214 enters the transimpedance pipe 300 without mixing with the hotter cooling air 222 exiting the first cooling passage 212. This arrangement allows the cooler second stream of cooling air 222 from the second cooling passage 214 to exit the turbine guide vanes 200 at a slightly cooler temperature than it would have if mixed with the first stream of cooling air 222 exiting the first cooling passage 212, thus better cooling other components of the gas turbine engine 100, such as the interstage sealing housing. This arrangement improves the cooling of the gas turbine engine 100 during operation.

[0045] Although exemplary embodiments of the present disclosure have been described in detail, those skilled in the art will understand that various changes, substitutions, modifications and improvements disclosed herein may be made without departing from the spirit and scope of the present disclosure in its broadest form.

[0046] Nothing described in this application should be construed as implying that any particular element, step, action, or function is an essential element that must be included within the scope of the claims: the scope of the patent subject matter is defined only by the granted claims. Furthermore, none of these claims are intended to refer to a means-plus-function claim construction, unless the exact phrase "device for..." is followed by a participle.

Claims

1. A turbine guide vane in a gas turbine engine, the turbine guide vane comprising: The inner platform has openings; External platforms; The guide vane airfoil is positioned between the inner platform and the outer platform, and the guide vane airfoil includes: A first cooling channel extends between the outer platform and the inner platform; A second cooling channel extends between the outer platform and the inner platform, and the second cooling channel is arranged downstream of the first cooling channel relative to the flow direction; A cross-connector, disposed between the second cooling channel and the inner platform, includes an inlet, an outlet, and a wall enclosing the hollow interior. The inlet is located at a certain distance within the second cooling channel, and the outlet is positioned to at least partially pass through an opening in the inner platform. A cover plate, which is attached to the cross-connector and the inner platform, The inlet is located at a portion of the span length of the second cooling channel, such that a gap is defined within the second cooling channel between the inlet and the outer platform.

2. The turbine guide vane according to claim 1, wherein, The pipe wall has a curved shape.

3. The turbine guide vane according to claim 1, wherein, The cross-connector has a generally hollow cuboid shape.

4. The turbine guide vane according to claim 1, wherein, The area of ​​the outlet of the crosspipe is different from the area of ​​the inlet of the crosspipe.

5. The turbine guide vane according to claim 1, wherein, The minimum area of ​​the crosspipe is between the inlet and the outlet of the crosspipe.

6. The turbine guide vane according to claim 1, wherein, The cross-connector includes a throttling plate attached to the inner surface of the cross-connector and extending around the inner periphery of the cross-connector.

7. The turbine guide vane according to claim 1, wherein, The cover plate is attached to the outer surface of the cross-connector and extends around the outer periphery of the cross-connector.

8. The turbine guide vane according to claim 1, wherein, The cover plate is attached to the outer surface of the inner platform.

9. The turbine guide vane according to claim 1, wherein, The second cooling channel includes a hoop disposed on the inner surface of the second cooling channel.

10. The turbine guide vane according to claim 9, wherein, The inlet of the cross-connector is positioned adjacent to the hoop.

11. A turbine guide vane in a gas turbine engine, the turbine guide vane comprising: The inner platform has openings; External platforms; The guide vane airfoil is positioned between the inner platform and the outer platform, and the guide vane airfoil includes: A first cooling channel extends between the outer platform and the inner platform; A second cooling channel extends between the outer platform and the inner platform, and the second cooling channel is arranged downstream of the first cooling channel relative to the flow direction; A third cooling channel is arranged downstream of the second cooling channel relative to the flow direction; and A cross-connector has an inlet located at a distance within the second cooling channel and an outlet located at least partially through the inner platform and in fluid communication with the outside of the inner platform. The first cooling channel guides a first flow of cooling air from the first cooling channel to the third cooling channel, and the cross-connector guides a second flow of cooling air from the second cooling channel to the outside of the inner platform. The inlet is located at a portion of the span length of the second cooling channel, such that a gap is defined within the second cooling channel between the inlet and the outer platform.

12. The turbine guide vane according to claim 11, wherein, The cross-connector has a generally hollow cuboid shape.

13. The turbine guide vane according to claim 11, wherein, The area of ​​the outlet of the crosspipe is different from the area of ​​the inlet of the crosspipe.

14. The turbine guide vane according to claim 11, wherein, The minimum area of ​​the crosspipe is between the inlet and the outlet of the crosspipe.

15. The turbine guide vane according to claim 11, wherein, The cross-connector includes a throttling plate attached to the inner surface of the cross-connector and extending around the inner periphery of the cross-connector.

16. The turbine guide vane of claim 11, further comprising a cover plate attached to the cross-connector and the inner platform.

17. The turbine guide vane according to claim 16, wherein, The cover plate is attached to the outer surface of the cross-connector and extends around the outer periphery of the cross-connector.

18. The turbine guide vane according to claim 16, wherein, The cover plate is attached to the outer surface of the inner platform.

19. The turbine guide vane according to claim 11, wherein, The second cooling channel includes a hoop disposed on the inner surface of the second cooling channel.

20. The turbine guide vane according to claim 19, wherein, The inlet of the cross-connector is positioned adjacent to the hoop.

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