Guide vane in a gas turbine engine

Abstract

A guide vane (200, 300, 400, 500, 700) in a gas turbine engine (100) includes an inner platform (202), an outer platform (204), and an airfoil (206) extending therebetween. Side surfaces (302, 304) of the inner and outer platforms between the guide vane (300) and an adjacent guide vane define a first seal slot (310, 318), a second seal slot (312, 320), and a third seal slot (314, 322) forming a closed loop with three corners (316, 324). At least one of the corners is rounded. The guide vane (500, 600) includes a spoiler rib (504) and a peg fin (506, 604) disposed in an interior portion (406) of the airfoil. The peg fin (604) is disposed in a region of a trailing edge (212). The inner platform defines a film cooling hole (410) disposed at an outer surface (408) facing the airfoil. The film cooling hole is arranged in a scalloped shape. An inner surface (804) of the inner platform and an outer surface (704) of the outer platform include impingement cooling ribs (802, 702). The inner platform projects further upstream in a flow direction than the outer platform.

Description

BACKGROUND

[0001] Industrial gas turbine engines generally include a compressor section, a turbine section, and a combustion section disposed therebetween. The compressor section includes multiple stages of rotating compressor blades and stationary compressor vanes. The combustion section generally includes a plurality of combustors.

[0002] The turbine section includes multiple stages of rotating turbine blades and stationary turbine vanes. The turbine blades and vanes generally operate in a high temperature environment and are internally cooled. SUMMARY

[0003] A guide vane in a gas turbine engine includes an inner platform including an outer surface, an inner surface, and a side surface; an outer platform including an outer surface, an inner surface, and a side surface, the side surface of the outer platform defining a first outer seal slot, a second outer seal slot, and a third outer seal slot; an airfoil extending between the inner platform and the outer platform, the airfoil including a pressure side wall and a suction side wall intersecting at a leading edge and a trailing edge, the pressure side wall and the suction side wall defining an airfoil interior. The second outer seal slot is spaced apart from the first outer seal slot and intersects the first outer seal slot. The third outer seal slot extends between the first outer seal slot and the second outer seal slot. The first outer seal slot, the second outer seal slot, and the third outer seal slot form a closed loop with three outer corners at the outer platform.

[0004] A guide vane in a gas turbine engine includes an airfoil extending between an inner platform and an outer platform, the airfoil including a pressure side wall and a suction side wall intersecting at a leading edge and a trailing edge, the pressure side wall and the suction side wall defining an airfoil interior; and a plurality of pin fins disposed in the airfoil interior, the plurality of pin fins arranged in rows extending between the leading edge and the trailing edge and in columns extending between the inner platform and the outer platform for cooling the airfoil interior.

[0005] A guide vane in a gas turbine engine includes an airfoil extending between an inner platform and an outer platform, the airfoil including a pressure side wall and a suction side wall intersecting at a leading edge and a trailing edge, the pressure side wall and the suction side wall defining an airfoil interior; an outer rib disposed at the outer surface of the outer platform configured to enable impingement cooling of the outer platform; and an inner rib disposed at the inner surface of the inner platform configured to enable impingement cooling of the inner platform.

[0006] A guide vane in a gas turbine engine includes an outer platform including an outer surface, an inner surface, and a side surface, an inner platform including an outer surface, an inner surface, and a side surface, an airfoil extending between the inner platform and the outer platform, the airfoil including a pressure side wall and a suction side wall intersecting at a leading edge and a trailing edge, the pressure side wall and the suction side wall defining an airfoil interior. The outer surface of the inner platform defines a plurality of film cooling holes for cooling the inner platform. BRIEF DESCRIPTION OF DRAWINGS

[0007] To readily identify the discussion of any particular element or act, the most significant digit or digits in any given reference number refer to the figure number in which that element is first introduced.

[0008] Figure 1 is a longitudinal sectional view of a gas turbine engine taken along a plane containing a longitudinal or central axis.

[0009] Figure 2 is a longitudinal sectional view of a guide vane.

[0010] Figure 3 is a front view of a guide vane.

[0011] Figure 4 is a perspective view of a guide vane.

[0012] Figure 5 is a perspective cutaway view of a portion of a guide vane.

[0013] Figure 6 is a transparent front view of a portion of a guide vane.

[0014] Figure 7 is a perspective top view of a guide vane.

[0015] Figure 8 is a perspective bottom view of a guide vane. DETAILED DESCRIPTION

[0016] Before any embodiments of the application are explained in detail, it is to be understood that the application is not limited in its application to the details of construction and the arrangement of components set forth in the following description or illustrated in the following drawings. The application is capable of other embodiments and of being practiced or being carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and not of limitation.

[0017] Various techniques relating to systems and methods will now be described with reference to the drawings, wherein like reference numerals refer to like elements throughout. The drawing in which the discussion is easiest to understand is usually the first figure. The following drawings discussed herein are not drawn to scale and are intended to be merely illustrative and not limiting of the scope of the disclosure. Those skilled in the art will understand that the principles of the disclosure can be implemented in any suitably arranged device. It should be understood that functions described as being performed by certain system elements can be performed by multiple elements. Similarly, for example, an element can be configured to perform functions described as being performed by multiple elements. Many of the innovative teachings of the present application will be described with reference to exemplary, non-limiting embodiments.

[0018] Moreover, it should be understood that the words or phrases used herein in reference to particular embodiments are intended to be broad and inclusive and are not intended to limit or confine the scope of the inventive principles. Furthermore, unless otherwise expressly specified, it is in no way intended that any method or aspect of the inventive principles be construed as requiring any particular order of steps. Also, as used herein, "or" is intended to mean any one or more of the items in the list of which it is used, for example, "A or B" means A or B or both. Furthermore, as used herein, "and" is intended to mean both "and" as well as "or," for example, "A and / or B" means A and / or B. In addition, unless otherwise indicated, singular articles and / or single reference numerals are also intended to address one or more items unless the context clearly dictates otherwise. For example, the term "a" or "an" entity can mean one or more entities. Unless otherwise indicated, the terms "coupled" and / or "connected," as well as terms like "first" and "second," are used broadly and encompass both direct and indirect couplings, connections, and / or rankings, unless otherwise indicated.

[0019] Moreover, while the terms "first," "second," "third," etc. can be used herein to describe various elements, information, functions or acts, the elements, information, functions or acts should not be limited by these terms. Rather, these terms are used merely to distinguish one element, information, function or act from another. For example, a first element, information, function or act could be termed a second element, information, function or act, and, similarly, a second element, information, function or act could be termed a first element, information, function or act, without departing from the scope of the present disclosure.

[0020] Further, the term "adjacent" can mean that an element is relatively near to, but not touching, another element, or that an element is touching another part, unless the context clearly indicates otherwise. Further, the phrase "based on" is intended to mean "based, at least in part, on" unless explicitly stated otherwise. The term "about" or "substantially" or similar terms are intended to cover variations in a value for that dimension that can result from normal industry manufacturing tolerances. If no industry standard is available, then a variation of twenty percent will fall into the meaning of these terms unless otherwise stated.

[0021] Figure 1 An example of a gas turbine engine 100 is shown that includes a compressor section 102, a combustion section 104, and a turbine section 106 arranged along a central axis 112. The compressor section 102 includes a plurality of compressor stages 114, with each compressor stage 114 including a set of rotating blades 116 and a set of stationary vanes 118 or adjustable guide vanes. A rotor 134 supports the rotating blades 116 for rotation about the central axis 112 during operation. In some constructions, a single, one-piece rotor 134 extends the length of the gas turbine engine 100 and is supported for rotation at either end by bearings. In other constructions, the rotor 134 is assembled from a plurality of separate spools attached to one another, or can include a plurality of disk sections attached via one or more bolts.

[0022] The compressor section 102 is in fluid communication with an 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 atmospheric air and compresses the air for delivery to the combustion section 104. The illustrated compressor section 102 is an example of one compressor section 102, with other arrangements and designs possible.

[0023] In the illustrated construction, the combustion section 104 includes a plurality of individual combustors 120 that each operate to mix a flow of fuel with compressed air from the compressor section 102 and to combust the air-fuel mixture to produce a flow of high-temperature, high-pressure combustion gases or exhaust 122. Of course, many other arrangements of the combustion section 104 are possible.

[0024] The turbine section 106 includes a plurality of turbine stages 124, with each turbine stage 124 including a plurality of rotating turbine blades 126 and a plurality of stationary turbine vanes 128. The turbine stages 124 are arranged to receive exhaust gas 122 from the combustion section 104 at a turbine inlet 130 and expand the gas to convert thermal and pressure energy into rotational or mechanical work. The turbine section 106 is connected to the compressor section 102 to drive the compressor section 102. For a gas turbine engine 100 used for power generation or as a prime mover, the turbine section 106 is also connected to a generator, pump, or other device to be driven. As with the compressor section 102, other designs and arrangements of the turbine section 106 are possible.

[0025] The exhaust section 110 is positioned downstream of the turbine section 106 and is arranged to receive the expanded flow of exhaust gas 122 from the last turbine stage 124 in the turbine section 106. The exhaust section 110 is arranged to effectively direct the exhaust gas 122 away from the turbine section 106 to ensure efficient operation of the turbine section 106. There can be many variations and design differences in the exhaust section 110. Thus, the illustrated exhaust section 110 is merely one example of these variations.

[0026] The control system 132 is coupled to the gas turbine engine 100 and is operative 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. In addition, the control system 132 provides output data to various devices including monitors, printers, indicators, etc. that allow a user to interact with the control system 132 to provide input 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 in an efficient manner.

[0027] The control system 132 can control various operating parameters including, but not limited to, variable inlet guide vane position, fuel flow rate and pressure, engine speed, valve position, generator load, and generator excitation. Of course, other applications can have fewer or more controllable devices. The control system 132 also monitors various parameters to ensure that the gas turbine engine 100 is operating correctly. Some of the parameters that are monitored can 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 later review if such review is necessary.

[0028] Figure 2is a longitudinal cross-sectional view of a guide vane 200. The guide vane 200 is one of a number of guide vanes 200 arranged in a circumferential direction to define a row of stationary guide vanes 200. The guide vane 200 interfaces with the combustor 120 and is disposed proximate a turbine inlet 130 of a turbine section 106 in the gas turbine engine 100. Exhaust gas 122 from the combustor 120 passes through the guide vane 200 into the turbine section 106.

[0029] The guide vane 200 includes an inner platform 202, an outer platform 204, and an airfoil 206 extending between the inner platform 202 and the outer platform 204 in a radial direction 208. The airfoil 206 includes a leading edge 210 and a trailing edge 212 in a longitudinal direction 214 parallel to a flow direction of the exhaust gas 122. The inner platform 202 protrudes further toward the combustor 120 than the outer platform 204. The further protruding inner platform 202 interfaces to the combustor 120 to reduce leakage of the exhaust gas 122 from the combustor 120.

[0030] Figure 3 is a front view of a guide vane 300. The guide vane 300 has an upstream side 306 and a downstream side 308 in a longitudinal direction 214 generally parallel to a flow direction of the exhaust gas 122. The inner platform 202 includes a side surface 302. The outer platform 204 includes a side surface 304. The side surface 302 of the inner platform 202 and the side surface 304 of the outer platform 204 are surfaces between adjacent guide vanes 300 arranged in a circumferential direction.

[0031] The side surface 302 of the inner platform 202 extends between the upstream side 306 and the downstream side 308 in the longitudinal direction 214. The side surface 302 includes a first inner seal groove 310 extending between the upstream side 306 and the downstream side 308. The side surface 302 includes a second inner seal groove 312 extending between the upstream side 306 and the downstream side 308. The second inner seal groove 312 intersects the first inner seal groove 310 at the upstream side 306. The side surface 302 includes a third inner seal groove 314 extending between the second inner seal groove 312 and the first inner seal groove 310 at the downstream side 308. The first inner seal groove 310, the second inner seal groove 312, and the third inner seal groove 314 form a closed loop. A seal strip can be placed in the first inner seal groove 310, the second inner seal groove 312, and the third inner seal groove 314 to form a seal between adjacent guide vanes 300.

[0032] At least one of the first inner seal groove 310, the second inner seal groove 312, and the third inner seal groove 314 has a straight-line shape to place a straight-line shaped seal strip. At least one of the first inner seal groove 310, the second inner seal groove 312, and the third inner seal groove 314 has a curved shape. As Figure 3As shown in the middle, the second inner seal groove 312 and the third inner seal groove 314 can be straight. The first inner seal groove 310 can be curved. It is possible that the first inner seal groove 310, the second inner seal groove 312, and the third inner seal groove 314 can have any suitable configuration.

[0033] The first inner seal groove 310 has a constant width in the length direction. The second inner seal groove 312 has a constant width in the length direction. The third inner seal groove 314 has a constant width in the length direction. The width of the first inner seal groove 310, the width of the second inner seal groove 312, and the width of the third inner seal groove 314 are the same. In other configurations, the width of the first inner seal groove 310, the width of the second inner seal groove 312, and the width of the third inner seal groove 314 can be different. It is also possible that at least one of the first inner seal groove 310, the second inner seal groove 312, and the third inner seal groove 314 has a width that is variable along the length direction. The width of the first inner seal groove 310, the width of the second inner seal groove 312, and the width of the third inner seal groove 314 are designed to place a seal strip with a high temperature difference to make the seal strip durable.

[0034] Three inner corners 316 are formed at the intersections between the first inner seal groove 310 and the second inner seal groove 312, between the second inner seal groove 312 and the third inner seal groove 314, and between the third inner seal groove 314 and the first inner seal groove 310. At least one of the three inner corners 316 is rounded. The inner corner 316 can be rounded on both sides, such as a side facing the interior of the closed loop and a side facing away from the interior of the closed loop. It is possible that the inner corner 316 is rounded on only one side. The inner corner 316 defines a width that is greater than the width of the first inner seal groove 310, the second inner seal groove 312, and the third inner seal groove 314, which results in a variable width of each of the first inner seal groove 310, the second inner seal groove 312, and the third inner seal groove 314. The variable width of each of the first inner seal groove 310, the second inner seal groove 312, and the third inner seal groove 314 allows the guide vane 300 to tilt during a transient period and reduces damage to the seal strip in the first inner seal groove 310, the second inner seal groove 312, and the third inner seal groove 314.

[0035] The side surface 304 of the outer platform 204 extends in the longitudinal direction 214 between an upstream side 306 and a downstream side 308. The side surface 304 includes a first outer seal groove 318 extending between the upstream side 306 and the downstream side 308. The side surface 304 includes a second outer seal groove 320 extending between the upstream side 306 and the downstream side 308. The second outer seal groove 320 intersects the first outer seal groove 318 at the upstream side 306. The side surface 304 includes a third outer seal groove 322 extending between the second outer seal groove 320 and the first outer seal groove 318 at the downstream side 308. The first outer seal groove 318, the second outer seal groove 320, and the third outer seal groove 322 form a closed loop. A seal strip can be placed in the first outer seal groove 318, the second outer seal groove 320, and the third outer seal groove 322 to form a seal between adjacent guide vanes 300.

[0036] At least one of the first outer seal groove 318, the second outer seal groove 320, and the third outer seal groove 322 has a straight shape to place a seal strip having a straight shape. At least one of the first outer seal groove 318, the second outer seal groove 320, and the third outer seal groove 322 has a curved shape. As shown in FIG. 3, the first outer seal groove 318 and the third outer seal groove 322 are straight. The second outer seal groove 320 is curved. It is possible that the first outer seal groove 318, the second outer seal groove 320, and the third outer seal groove 322 can have any suitable configuration. Figure 3

[0037] The first outer seal groove 318 has a constant width in the length direction. The second outer seal groove 320 has a constant width in the length direction. The third outer seal groove 322 has a constant width in the length direction. The width of the first outer seal groove 318, the width of the second outer seal groove 320, and the width of the third outer seal groove 322 are the same. In other configurations, the width of the first outer seal groove 318, the width of the second outer seal groove 320, and the width of the third outer seal groove 322 can be different. It is also possible that at least one of the first outer seal groove 318, the second outer seal groove 320, and the third outer seal groove 322 has a width that is variable along the length direction. The width of the first outer seal groove 318, the width of the second outer seal groove 320, and the width of the third outer seal groove 322 are designed to place a seal strip having a high temperature difference so as to make the seal strip durable.

[0038] ​Three outer corners 324 are formed at the intersections between the first outer seal slot 318 and the second outer seal slot 320, the second outer seal slot 320 and the third outer seal slot 322, and the third outer seal slot 322 and the first outer seal slot 318. At least one of the three outer corners 324 is more rounded. The outer corners 324 can be rounded on both sides, for example, a side facing the interior of the closed loop and a side facing away from the interior of the closed loop. It is possible that the outer corners 324 are rounded on only one side. The outer corners 324 define a width that is greater than the width of the first outer seal slot 318, the second outer seal slot 320, and the third outer seal slot 322, which results in a variable width of each of the first outer seal slot 318, the second outer seal slot 320, and the third outer seal slot 322. The variable width of each of the first outer seal slot 318, the second outer seal slot 320, and the third outer seal slot 322 allows the guide vane 300 to tilt during transients and reduces damage to the seal strips in the first outer seal slot 318, the second outer seal slot 320, and the third outer seal slot 322.

[0039] Figure 4 is a perspective view of a guide vane 400. Figure 4 may be a guide vane 300 as shown in Figure 3 is a perspective view of a guide vane 300 as shown in

[0040] The inner platform 202 has an outer surface 408 facing the outer platform 204. The outer surface 408 includes a plurality of film cooling holes 410. The plurality of film cooling holes 410 are arranged in a plurality of rows 412. The plurality of rows 412 are arranged in a fan shape. The fan shape has an outer diameter towards the airfoil 206. The fan shaped film cooling holes 410 provide cooling of the inner platform 202.

[0041] The outer platform 204 can have a similar configuration as the inner platform 202. The outer platform 204 has an inner surface 414 facing the inner platform 202. The inner surface 414 can include a plurality of film cooling holes 410 arranged in a plurality of rows 412 (not shown in Figure 4 The plurality of rows 412 are arranged in a fan shape. The fan shape has an outer diameter towards the airfoil 206. The fan shaped film cooling holes 410 provide cooling of the outer platform 201.

[0042] Figure 5 is a perspective cutaway view of a portion of a guide vane 500. The guide vane 500 includes a partition wall 502 disposed in the airfoil interior 406. The partition wall 502 extends between the inner platform 202 and the outer platform 204 and is spaced apart from each other in the longitudinal direction 214. Figure 5Two partition walls 502 are shown. The partition walls 502 are coupled to the pressure side wall 402 and the suction side wall 404. Figure 5 (Not shown in the image). The internal cooling channel 508 is defined within the airfoil interior 406 by a partition wall 502, a pressure side wall 402, and a suction side wall 404. Figure 5 Only one internal cooling channel 508 of the guide vane 500 is shown. The guide vane 500 includes a plurality of partition walls 502 between the leading edge 210 and the trailing edge 212, which define a plurality of internal cooling channels 508 therebetween.

[0043] At least one spoiler rib 504 is disposed inside the airfoil 406. The spoiler rib 504 extends longitudinally 214 between the partition walls 502. Figure 5 As shown, multiple spoiler ribs 504 are disposed between partition walls 502. The spoiler ribs 504 are spaced apart from each other in the radial direction 208. The spoiler ribs 504 improve cooling in the internal cooling channels 508.

[0044] Multiple nail-shaped fins 506 are disposed within the airfoil 406. The nail-shaped fins 506 are disposed on the inner surface of the suction sidewall 404. The nail-shaped fins 506 are also disposed on the inner surface of the pressure sidewall 402. Figure 5 (Not shown in the image). The spiked fins 506 are arranged in rows extending in the longitudinal direction 214 between spaced-apart partition walls 502 and in columns extending in the radial direction 208 between the inner platform 202 and the outer platform 204. The combination of the spiked fins 506 and the spoiler ribs 504 improves cooling in the internal cooling channel 508.

[0045] Figure 6 This is a transparent front view of a portion of the guide vane 600. The guide vane 600 includes an internal cooling channel 508 in the region of the trailing edge 212. Multiple spoiler ribs 602 are disposed in the internal cooling channel 508 in the region of the trailing edge 212. The spoiler ribs 602 are disposed downstream of the partition wall 502 and extend toward the trailing edge 212. The spoiler ribs 602 have different configurations. For example, some of the spoiler ribs 602 extend further toward the trailing edge 212. It is possible that the spoiler ribs 602 may have the same configuration or any suitable configuration.

[0046] A plurality of pin fins 604 are disposed in the inner cooling passage 508 in the region of the trailing edge 212. The pin fins 604 are arranged in more than one row 606. The rows 606 extend toward the trailing edge 212. Each row 606 includes a plurality of pin fins 604 that extend between the inner platform 202 and the outer platform 204 and are spaced apart from one another, thereby forming more than one column. Each pin fin 604 in a row 606 can have the same configuration or can have different configurations as desired. For example, some pin fins 604 can have a different diameter than other pin fins 604 in the same row 606. Pin fins 604 in different rows 606 can have different configurations. Pin fins 604 in adjacent rows 606 can be arranged in a staggered arrangement in the radial direction 208. The combination of the pin fins 604 and the spoiler ribs 602 improves cooling in the inner cooling passage 508 in the region of the trailing edge 212.

[0047] Figure 7 is a perspective top view of a guide vane 700. The guide vane 700 includes external ribs 702 disposed on an outer surface 704 of the outer platform 204. The external ribs 702 can have different configurations, such as different lengths, widths, heights, or orientations relative to one another. Some of the external ribs 702 are arranged in rows and parallel to one another. The external ribs 702 provide impingement cooling to the outer platform 204.

[0048] Figure 8 is a perspective bottom view of a guide vane 800. The guide vane 800 includes internal ribs 802 disposed on an inner surface 804 of the inner platform 202. The internal ribs 802 can have different configurations, such as different lengths, widths, heights, or orientations relative to one another. Some of the internal ribs 802 are arranged in rows and parallel to one another. The internal ribs 802 provide impingement cooling to the inner platform 202.

[0049] It should be noted that, Figures 1-8 Many of the features of the guide vanes are shown, and these features can be used together or separately from one another on any guide vane. Thus, it is not required that a guide vane include any or all of the features described, and there is no limitation on the combination of features for a particular design.

[0050] While exemplary embodiments of the disclosure have been described in detail, those skilled in the art will understand that various changes, substitutions, variations, and improvements can be made to what is disclosed herein without departing from the spirit and scope of the disclosure in its broadest form.

[0051] The description herein is not to be interpreted as implying any particular element, step, action, or function is a requirement of the patentable subject matter: the scope of the patent subject matter is defined only by the claims. Moreover, none of the claims are intended to invoke 35 U.S.C. § 112 (6) unless the exact phrase "means for" follows the transitional word "means" and no such claim is meant to be given its broadest interpretation.

[0052] List of reference signs

[0053] 100 gas turbine engine

[0054] 102 compressor section

[0055] 104 combustion section

[0056] 106 turbine section

[0057] 108 inlet section

[0058] 110 exhaust section

[0059] 112 center axis

[0060] 114 compressor stage

[0061] 116 rotating blade

[0062] 118 stationary vane

[0063] 120 combustor

[0064] 122 exhaust

[0065] 124 turbine stage

[0066] 126 rotating turbine blade

[0067] 128 stationary turbine vane

[0068] 130 turbine inlet

[0069] 132 control system

[0070] 134 rotor

[0071] 200 guide vane

[0072] 202 inner platform

[0073] 204 outer platform

[0074] 206 airfoil

[0075] 208 radial direction

[0076] 210 leading edge

[0077] 212 trailing edge

[0078] 214 longitudinal direction

[0079] 300 guide vane

[0080] 302 side surface

[0081] 304 side surface

[0082] 306 upstream side

[0083] 308 downstream side

[0084] 310 first inner seal groove

[0085] 312 second inner seal groove

[0086] 314 third inner seal groove

[0087] 316 inner corner

[0088] 318 first outer seal groove

[0089] 320 second outer seal groove

[0090] 322 third outer seal groove

[0091] 324 outer corner

[0092] 400 guide vane

[0093] 402 pressure side wall

[0094] 404 suction side wall

[0095] 406 airfoil interior

[0096] 408 outer surface

[0097] 410 film cooling hole

[0098] 412 row

[0099] 414 inner surface

[0100] 500 guide vane

[0101] 502 partition wall

[0102] 504 spoiler rib

[0103] 506 peg fin

[0104] 508 internal cooling passage

[0105] 600 guide vane

[0106] 602 spoiler ribs

[0107] 604 pin fins

[0108] 606 rows

[0109] 700 guide vanes

[0110] 702 outer ribs

[0111] 704 outer surface

[0112] 800 guide vanes

[0113] 802 inner ribs

[0114] 804 inner surface

Claims

1. A guide vane in a gas turbine engine, the guide vane comprising: The inner platform includes an outer surface, an inner surface, and side surfaces; An outer platform includes an outer surface, an inner surface, and a side surface, wherein the side surface of the outer platform defines a first outer sealing groove, a second outer sealing groove, and a third outer sealing groove; An airfoil extending between the inner platform and the outer platform, the airfoil including a pressure sidewall and a suction sidewall intersecting at its leading and trailing edges, the pressure sidewall and the suction sidewall defining the interior of the airfoil. The second outer sealing groove is spaced apart from and intersects with the first outer sealing groove. Wherein, the third outer sealing groove extends between the first outer sealing groove and the second outer sealing groove, and The first outer sealing groove, the second outer sealing groove, and the third outer sealing groove form a closed loop with three outer corners at the outer platform. The width defined by the outer corner is greater than the width of the first outer sealing groove, the second outer sealing groove and the third outer sealing groove, which results in a variable width for each of the first outer sealing groove, the second outer sealing groove and the third outer sealing groove.

2. The guide vane according to claim 1, wherein, At least one of the three outer corners at the outer platform is circular.

3. The guide vane according to claim 1, wherein, The side surface of the inner platform defines a first inner sealing groove, a second inner sealing groove, and a third inner sealing groove, wherein the second inner sealing groove is spaced apart from and intersects with the first inner sealing groove, wherein the third inner sealing groove extends between the first inner sealing groove and the second inner sealing groove, and wherein the first inner sealing groove, the second inner sealing groove, and the third inner sealing groove form a closed loop with three inner corners at the inner platform.

4. The guide vane according to claim 3, wherein, At least one of the three inner corners at the inner platform is rounded.

5. The guide vane according to claim 1, wherein, The outer surface of the inner platform defines film cooling holes.

6. The guide vane according to claim 5, wherein, The membrane cooling holes are arranged in a fan shape.

7. The guide vane of claim 6, wherein the fan-shaped shape has an outer diameter facing the airfoil.

8. The guide vane according to claim 1, wherein the airfoil includes spiked fins and at least one spoiler rib.

9. The guide vane according to claim 8, wherein, The spiked fins form an array having rows extending between the leading edge and the trailing edge and columns extending between the inner platform and the outer platform.

10. The guide vane according to claim 1, wherein, The airfoil includes spike-shaped fins disposed in the region of the trailing edge.

11. The guide vane according to claim 1, wherein, The outer surface of the outer platform includes at least one external rib.

12. The guide vane according to claim 1, wherein, The inner surface of the inner platform includes at least one internal rib.

13. The guide vane according to claim 1, wherein, The inner platform protrudes further upstream in the flow direction than the outer platform.

14. The guide vane according to claim 1, wherein the guide vane comprises: Multiple nail-shaped fins are disposed inside the airfoil and arranged in rows extending between the leading edge and the trailing edge and in columns extending between the inner platform and the outer platform for cooling the interior of the airfoil.

15. The guide vane of claim 14, wherein the plurality of nail-shaped fins are disposed in the region of the trailing edge.

16. The guide vane according to claim 1, wherein the guide vane comprises: External ribs are disposed on the outer surface of the outer platform and are configured to enable impact cooling of the outer platform. as well as Internal ribs are disposed on the inner surface of the inner platform and are configured to enable shock cooling of the inner platform.

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