CN115653696B - Cooling structure of turbine stator blade - Google Patents
Cooling structure of turbine stator blade Download PDFInfo
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- CN115653696B CN115653696B CN202211090578.1A CN202211090578A CN115653696B CN 115653696 B CN115653696 B CN 115653696B CN 202211090578 A CN202211090578 A CN 202211090578A CN 115653696 B CN115653696 B CN 115653696B
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Abstract
The invention discloses a cooling structure of a turbine stator blade, which comprises the turbine stator blade and a baffle plate, wherein the turbine stator blade comprises an upper edge plate, a lower edge plate and a blade profile, the baffle plate is a thin-wall sheet metal which is consistent with the front section of the turbine stator blade in shape, and the front sections of the upper edge plate, the lower edge plate and the blade profile are wrapped to form a slit cavity. The upper edge plate, the lower edge plate and the blade profile are respectively provided with a plurality of ribs and air holes at the front section of the upper edge plate, the lower edge plate and the blade profile at certain intervals. According to the invention, the thin-wall baffle plate structure is designed, so that a certain slit cavity is formed between the thin-wall baffle plate structure and the turbine stationary blade, cooling airflow fully exchanges heat in the cavity, the metal temperature of the blade-shaped front section of the stationary blade and the front section of the flange plate is reduced, and when gas flows out through the slit, a high-efficiency air film can be covered on the side wall surface of the stationary blade gas, so that the side wall surface of the stationary blade gas is protected, and the utilization efficiency of cold air is improved. Meanwhile, the front section of the stator blade profile which is most easily damaged in the traditional design is transferred to the thin-wall baffle plate, so that the stator blade is protected from being damaged.
Description
Technical Field
The invention relates to the field of turbine blade cooling structures, in particular to a cooling structure of a turbine stator blade.
Background
The gas engine is one kind of internal combustion engine, and it produces power to do work through burning natural gas, and may be used in driving automobile and ship to walk or may be burnt to drive generator to generate power. The advantages are cleaner and environment-friendly than diesel engine or petrol engine. The gas engine can replace diesel engines and gasoline engines, and is widely applied to the fields of public transportation, oilfield power generation and the like. As known from a simple circulation mode of the gas turbine, the initial temperature of the gas at the inlet of the turbine is increased, the power and the performance of the gas turbine can be improved, but at the same time, the bearing temperature of the turbine blades is increased, the severe degree of the service environment is aggravated, and the initial temperature of the gas of the F-stage gas turbine is about 1400 ℃, and the bearing limit of metal of the blades is far exceeded. Therefore, advanced cooling structure designs for turbine blades are critical to safe operation of the gas turbine.
The typical turbine stator blade adopts a hollow structure, and the effect of reducing the temperature is realized by taking away the heat of the blade through the combination of a plurality of cooling modes such as impact cooling, convection cooling, air film cooling and the like of cooling air at the positions such as the inner cavity of the blade, the air hole of the blade body, the outer wall surface of the blade and the like. The front section of the stator blade profile is directly flushed by upstream fuel gas, so that the environment is more severe, and the front section is one of the common parts of stator blade damage, and is mainly characterized by coating peeling, metal bulge, burning-through, even fracture and the like. In order to control the metal temperature of the front section of the stator blade profile within an allowable range, a common cooling structure is that air is extracted from a compressor to enter a cavity of the front section of the stator blade profile, then flows out through air film holes densely distributed on the wall surface of the front section of the stator blade profile, covers the outer wall surface of the front section of the stator blade profile under the action of fuel gas to realize air film cooling, and is matched with a ceramic heat-insulating coating on the outer wall surface of the stator blade to realize double protection.
For example, in chinese patent application publication No. CN 114396316A and application publication No. 2022.04.26, a turbine stator blade and a turbine stator blade are disclosed, which include a blade body, the blade body has a front edge side and a rear edge side, a first cavity and a second cavity are disposed in the blade body, the first cavity and the second cavity are sequentially disposed along a direction from the front edge side to the rear edge side, a slit is disposed on the rear edge side of the blade body, the slit communicates the second cavity with the outside of the blade body, and the blade body is provided with a plurality of film cooling holes, which communicate the first cavity, the second cavity with the outside of the blade body.
The invention discloses a turbine guide cooling blade in China patent application publication No. CN 111485956A and application publication No. 2020.08.04, which comprises a main body, a first partition plate and a plurality of air film holes, wherein the main body comprises a front edge and a tail edge, the first partition plate is arranged in the main body to form a first cavity and a second cavity which are independent in each other, the first cavity is positioned at one side of the main body, which is close to the front edge, the second cavity is positioned at one side of the main body, which is close to the tail edge, an air vent is arranged on the first partition plate, the first cavity and the second cavity are communicated through the air vent, the air film holes are all arranged on the main body and are respectively communicated with the first cavity and the second cavity, the air film holes are first through holes, and a first divergent opening is formed in the direction from the middle part of each air film hole to the outer surface of the main body.
For traditional stator blade profile front section and flange plate front section cooling structure design, the following disadvantages mainly exist:
Firstly, the air film cooling effect of the front section of the stator blade type is poor. The vane front section of the stator blade is directly flushed by high-speed fuel gas, and is limited by the curvature shape of the vane front section, and the gas film Kong Chuqi at the vane front section is used for flushing fuel gas, only the wall surface is covered in a small range near the gas film hole, even the wall surface cannot be covered, the gas film is poor in covering effect, the effect of isolating the fuel gas is not ideal, and therefore dense gas film hole arrangement is needed.
Secondly, the gas film hole at the front section of the stator blade type is difficult to be discharged and even has gas backflow. The gas stagnation area exists in the front section area of the stator blade profile, the pressure of the area is not different from the pressure of cooling air in the stator blade cavity from the air compressor, the power of the cooling air flowing outwards is insufficient, even the gas flows backwards to the inner cavity of the blade, the temperature of a blade matrix is increased due to the fact that the gas invades the interior of the blade, and oxidative corrosion, cracks, bulges and the like are generated, so that the service life of the stator blade is seriously shortened or the damage to operation safety is caused.
Thirdly, the air film holes are very densely arranged at the front section of the stator blade type, so that the strength of the stator blade is greatly reduced. Because the air film cooling effectiveness of the front section of the stator blade profile is low, if an ideal air film cooling effect is to be realized, the arrangement interval of air film holes must be reduced, so that the air film holes of the front section of the blade profile are arranged very densely, the removal amount of the material of the front section of the blade profile is increased, and the strength of the blade is reduced.
Fourthly, the front section of the stator blade profile is easy to damage during operation, and the maintenance and replacement costs of the blade are high and the period is long. The temperature of the fuel gas near the front section of the stator blade profile is higher, the temperature of the cooling air introduced into the inner cavity of the stator blade is far lower than that of the fuel gas, the huge temperature difference of the cooling air and the fuel gas causes high concentration of metal thermal stress of the front section of the stator blade profile, the high concentration of metal thermal stress is a cause of extremely easy damage to the front section of the stator blade profile, the repair difficulty after the damage is high, more commonly, the whole stator blade is directly replaced, and the cost is very high.
Fifthly, in order to ensure the air film covering effect, the air film holes of the static blade edge plates need a certain angle along the air flow direction, so that the air film holes cannot be arranged at the forefront section of the blade edge plates, and the front section metal of the edge plates is directly heated by fuel gas, cannot be cooled and is easy to oxidize and corrode.
Disclosure of Invention
In order to overcome the problems in the prior art, the invention provides a cooling structure of a turbine stator blade, wherein a thin-wall metal plate baffle structure which is consistent with the shapes of a vane type front section and a flange plate front section is independently designed on the vane type front section and the upper flange plate front section and the lower flange plate front section of the stator blade, a slit cavity for cooling gas is formed, after the cooling gas flows in the cavity for fully exchanging heat, the metal temperature of the vane type front section and the flange plate front section is reduced to be within an allowable range, and then, when the gas flows out through the slit, a high-efficiency air film can be realized to cover the side wall surface of the stator blade, the protection of the side wall surface of the stator blade gas is realized, and the utilization efficiency of cold air is improved.
The cooling structure of the turbine stator blade comprises the turbine stator blade and a baffle, wherein the turbine stator blade comprises an upper edge plate, a lower edge plate and a blade profile, the baffle is a thin-wall sheet metal which is consistent with the front section of the turbine stator blade in shape, and the front sections of the upper edge plate, the lower edge plate and the blade profile are wrapped to form a slit cavity.
By adopting the technical scheme, the front section of the stator blade profile which is most easily damaged in the traditional design is transferred to the thin-wall baffle, so that the stator blade is protected from being damaged, the replacement baffle is simpler and easier and the cost is reduced compared with the prior art in which the whole stator blade is required to be maintained and replaced, and meanwhile, the front section of the flange plate which is difficult to be cooled in the traditional scheme is cooled and protected, and meanwhile, an air film is formed through a slit to cover.
The invention further provides that the front section of the upper edge plate is provided with a plurality of upper edge plate ribs at certain intervals along the circumferential direction, and the upper edge plate is also provided with a plurality of upper edge plate air holes.
The invention further provides that the front section of the lower edge plate is provided with a plurality of lower edge plate ribs at certain intervals along the circumferential direction, and the lower edge plate is also provided with a plurality of lower edge plate air holes.
The invention further provides that the outer wall surface of the front section of the blade profile is provided with a plurality of blade profile ribs at certain intervals along the radial direction, and a plurality of blade profile air holes are arranged along the wall thickness direction.
The invention is further provided with an air supply cavity on the blade profile.
The invention further provides that when the baffle is mounted on the turbine stator blade, the upper flange plate rib, the lower flange plate rib and the blade profile rib are positioned between the baffle and the upper flange plate, between the baffle and the lower flange plate and between the baffle and the blade profile, and an upper flange plate slit chamber, a lower flange plate slit chamber and a blade profile slit chamber are formed on the turbine stator blade.
By adopting the technical scheme, the cooling air from the upper side of the front section of the upper edge plate enters the slit chamber of the upper edge plate through the air holes of the upper edge plate, flows in the slit chamber, and flows out of the chamber through the slit along the flowing direction of the fuel gas to enter the main fuel gas;
cooling air from the lower side of the front section of the lower edge plate enters the slit chamber of the lower edge plate through the air holes of the lower edge plate, and after flowing in the slit chamber, the cooling air flows out of the chamber through the slit along the flowing direction of the fuel gas to enter the main stream fuel gas.
Cooling air from the air supply chamber passes through the airfoil air holes into the airfoil slit chamber. The cooling air is divided into two directions in the chamber, flows out of the chamber through the pressure surface and suction surface slits respectively, and enters the main flow fuel gas.
The invention further provides that the upper edge plate, the lower edge plate and the blade profile are integrally cast and formed with the upper edge plate rib, the lower edge plate rib and the blade profile rib.
The invention further provides that the outer wall surface of the baffle plate is sprayed with a TBC thermal barrier coating with a certain thickness for resisting high-temperature gas impact.
By adopting the technical scheme, the blade-shaped front-section baffle is formed by adopting metal plates, so that the original pneumatic appearance is ensured, the thin-wall metal plates can be deformed to release the internal stress when heated, the peeling of the TBC coating on the surface due to the overlarge internal stress is avoided, and the service life of the coating is prolonged. TBC thermal-insulation coating is sprayed on the outer surface of the baffle plate, and the TBC thermal-insulation coating is matched with impact holes arranged on blades on the inner surface and cold air in the slit to flow and exchange heat, so that the coating itself bears a large temperature gradient, and the metal temperature of the baffle plate can be reduced in the allowable temperature of the service life of the baffle plate metal material.
In summary, the technical scheme of the invention has the following beneficial effects:
1. A thin-wall metal plate baffle structure is independently designed on the front section of the stator blade profile of the turbine and the front sections of the upper and lower edge plates to form a cooling gas slit cavity, after the cooling gas flows in the cavity to exchange heat fully, the metal temperature of the front section of the stator blade profile and the front section of the edge plates is reduced, and then when the gas flows out through the slit, an efficient gas film can be covered on the side wall surface of the stator blade gas, so that the side wall surface of the stator blade gas is protected, and the utilization efficiency of the cold gas is improved.
2. The formed slit cavity is filled with cooling gas, so that the metal of the front section of the blade profile is wrapped by cold gas and is not directly flushed by gas, the metal thermal stress of the area is reduced, the front section of the blade profile does not need to be densely provided with air holes, the number of the air holes is reduced, the strength of the area of the front section of the blade profile is improved, high-temperature gas is not directly flushed with cooling gas flow of a conventional air film hole of the front section of the blade profile of a static blade, and the risk of backflow of the gas is avoided.
3. The stator blade body is integrally molded by casting, the baffle plate is formed by stamping by adopting metal plates, two processes and two materials are adopted, the stator blade body material mainly focuses on bearing force and takes bearing heat into consideration, and the metal plate material mainly meets the requirements of heat resistance, oxidation resistance and bearing force and has various emphasis aspects.
4. The invention transfers the front section of the stator blade profile which is most easily damaged in the traditional design to the thin-wall baffle plate, thereby protecting the stator blade from being damaged, and the replacement of the baffle plate is relatively easy and the cost is reduced compared with the maintenance and the replacement of the whole stator blade.
5. The sheet metal part of the front edge baffle of the static blade bears extremely small airflow force and is mainly used for bearing heat, the thin-wall sheet metal baffle adopted in the scheme covers the area, a TBC heat insulation layer is sprayed on the gas side of the thin-wall sheet metal baffle, efficient impact cooling and flow heat exchange are arranged on the back side matched blade, and the temperature gradient can be mainly concentrated on the coating, so that the metal temperature of the sheet metal of the protective baffle meets the use requirement.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed for the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a partial cross-sectional view of the present invention;
FIG. 3 is a cross-sectional view taken at the A-A position of FIG. 2;
FIG. 4 is a cross-sectional view of the B-B position of FIG. 2;
Fig. 5 is a schematic view of a baffle structure according to the present invention.
In the drawings, the list of components represented by the various numbers is as follows:
10-baffle, 20-turbine stator blade, 21-upper edge plate, 22-lower edge plate, 23-blade profile, 31-upper edge plate front section, 32-lower edge plate front section, 33-blade profile front section, 41-upper edge plate rib, 42-lower edge plate rib, 43-blade profile rib, 51-upper edge plate air hole, 52-lower edge plate air hole, 53-blade profile air hole, 60-blade profile front section air supply cavity, 61-upper edge plate slit cavity, 62-lower edge plate slit cavity, 63-blade profile slit cavity.
Detailed Description
In order to make the technical solution of the present application better understood by those skilled in the art, the technical solution of the present application will be clearly and completely described in the following with reference to the accompanying drawings, and based on the embodiments of the present application, other similar embodiments obtained by those skilled in the art without making any inventive effort should be included in the scope of protection of the present application. In addition, directional words such as "upper", "lower", "left", "right", and the like, as used in the following embodiments are merely directions with reference to the drawings, and thus, the directional words used are intended to illustrate, not to limit, the application.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the description of the application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application.
Examples:
The invention will be further described with reference to the drawings and preferred embodiments.
As shown in FIG. 1 and FIG. 2, the cooling structure of the turbine stator blade comprises the turbine stator blade 20, wherein the turbine stator blade 20 comprises an upper edge plate 21, a lower edge plate 22 and a blade profile 23, and is characterized by further comprising a baffle plate 10, wherein the baffle plate 10 is a thin-wall sheet metal consistent with the shape of the front section of the turbine stator blade 20, and is wrapped on the front sections of the upper edge plate 21, the lower edge plate 22 and the blade profile 23 to form a slit cavity.
The upper edge plate 21 is provided with a plurality of upper edge plate ribs 41 at a certain interval along the circumferential direction at the front section, and the upper edge plate 21 is also provided with a plurality of upper edge plate air holes 51.
The lower rim plate 22 is provided with a plurality of lower rim plate ribs 42 at a certain interval along the circumferential direction at the front section thereof, and the lower rim plate 22 is also provided with a plurality of lower rim plate air holes 52.
The outer wall surface of the front section of the vane pattern 23 is provided with a plurality of vane pattern ribs 43 at regular intervals along the radial direction, and a plurality of vane pattern air holes 53 are provided along the wall thickness direction. The blade profile 23 is also provided with an air supply chamber 60.
When the baffle 10 is mounted on the turbine stator blade 20, the upper flange plate rib 41, the lower flange plate rib 42 and the blade profile rib 43 are positioned between the baffle 10 and the upper flange plate 21, the lower flange plate 22 and the blade profile 23, and an upper flange plate slit chamber 61, a lower flange plate slit chamber 62 and a blade profile slit chamber 63 are formed on the turbine stator blade 20.
The upper flange plate 21, the lower flange plate 22 and the blade profile 23 are integrally cast with the upper flange plate rib 41, the lower flange plate rib 42 and the blade profile rib 43.
As shown in fig. 4, the baffle 10 is a follow-up curved surface sheet metal structure of an upper edge plate front section 31, a lower edge plate front section 32 and a blade-shaped front section 33, no cooling air holes are formed on the wall surface, and the baffle 10 is connected with the front end surface and the outer circular surface of the upper edge plate front section 31 and the front end surface and the inner circular surface of the lower edge plate front section 32 to realize connection and fixation between the baffle and the stationary blade body 20.
By adopting the technical scheme, the cooling air from the upper side of the front section 31 of the upper edge plate can enter the slit chamber 61 of the upper edge plate through the air holes 51 of the upper edge plate, and after flowing in the slit chamber, the cooling air flows out of the chamber through the slit along the flowing direction of the fuel gas to enter the main fuel gas;
Cooling air from the underside of the lower platform front section 32 enters the lower platform slot chamber 62 through the platform air holes 52, flows within the slot chamber, and then flows out of the chamber through the slots in the direction of gas flow into the main stream gas.
As shown in fig. 3, the cooling air from the air supply chamber 60 passes through the vane-type air holes 53 into the vane-type slit chamber 63. The cooling air is divided into two directions in the chamber, flows out of the chamber through the pressure surface and suction surface slits respectively, and enters the main flow fuel gas.
As shown in fig. 5, the baffle 10 is covered by a TBC ceramic coating on the outer side wall surface of the baffle, so that direct scouring of high-temperature fuel gas can be resisted, the vane type front section and the flange plate front section area are isolated from the fuel gas, the heat transfer effect of the fuel gas on the metal in the area is greatly reduced, and the thermal stress is reduced;
A chamber with a certain impact distance is formed between the inner wall of the baffle 10 and the outer side wall surface of the turbine stator blade 20, so that the inner side and the outer side of the vane type front section 33 are both positioned in cooling gas, and the phenomenon of heat stress concentration caused by huge temperature difference in the area of the vane type front section 33 in the traditional design is greatly reduced. The baffle 10 sheet metal part bears the extremely small air current force, mainly is used for carrying heat, and the thin wall sheet metal baffle 10 that this scheme adopted covers this region, and its gas side spraying has TBC insulating layer, and the efficient impingement cooling and the heat transfer that flow that set up on the back side cooperation blade can make the temperature gradient mainly concentrate on the coating to the metal temperature of protection baffle panel beating satisfies the operation requirement.
In summary, the structure of the following thin-wall sheet metal baffle 10 is independently designed at the front section of the turbine stator blade 20 to form the cooling gas slit cavity, after the cooling air flows in the cavity to exchange heat fully, the metal temperatures of the stator blade type front section 33, the upper edge plate front section 31 and the lower edge plate front section 32 are reduced to be within the allowable range, the cooling gas after passing through the convection heat exchange of the cavity between the baffle 10 and the body of the turbine stator blade 20 sufficiently takes away the heat of the baffle 10 and the stator blade to raise the temperature, then flows out of the cavity through the slit, the flowing direction of the cooling gas is consistent with the flowing direction of the fuel gas, and the cooling gas flows out through the following slit, so that the cooling gas can be well covered on the wall surface of the blade to form an effective air film cover, and the temperature difference between the air film cooling gas and main stream fuel gas is relatively reduced, thereby reducing the mixing loss between the cooling gas and realizing the efficient covering protection effect of the cooling gas on the side wall surface of the turbine stator blade.
The formed slit cavity is filled with cooling gas, so that the metal of the front section 33 of the blade profile is wrapped by cold gas and is not directly washed by the gas, the metal thermal stress of the area is greatly reduced, the front section 33 of the blade profile does not need to be densely covered with air holes, the number of the air holes is greatly reduced, the strength of the area of the front section 33 of the blade profile is greatly improved, high-temperature gas is not directly washed by the cooling gas flow of the air film holes of the front section 33 of the traditional blade profile, the risk of backflow of the gas is avoided, the front section 33 of the blade profile which is most easily damaged in the traditional design is transferred onto the thin-wall baffle plate 10 by using the baffle plate structure, the blade profile is protected from being damaged, and if damage occurs and needs to be replaced, the baffle plate 10 can be directly replaced to keep the blade profile body, so that the replacement maintenance period and the cost are greatly reduced.
The technical features of the above-described embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above-described embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above examples, and all technical solutions belonging to the concept of the present invention belong to the protection scope of the present invention. It should be noted that modifications and adaptations to the present invention may occur to one skilled in the art without departing from the principles of the present invention and are intended to be within the scope of the present invention.
Claims (7)
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211090578.1A CN115653696B (en) | 2022-09-07 | 2022-09-07 | Cooling structure of turbine stator blade |
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| CN202211090578.1A CN115653696B (en) | 2022-09-07 | 2022-09-07 | Cooling structure of turbine stator blade |
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| CN115653696A CN115653696A (en) | 2023-01-31 |
| CN115653696B true CN115653696B (en) | 2025-01-10 |
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| CN118622393B (en) * | 2024-07-01 | 2025-09-16 | 北京航空航天大学 | Oil-cooled turbine stator blade adopting layered structure |
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| GB0117110D0 (en) * | 2001-07-13 | 2001-09-05 | Siemens Ag | Coolable segment for a turbomachinery and combustion turbine |
| US8322988B1 (en) * | 2009-01-09 | 2012-12-04 | Florida Turbine Technologies, Inc. | Air cooled turbine airfoil with sequential impingement cooling |
| US10612385B2 (en) * | 2016-03-07 | 2020-04-07 | Rolls-Royce Corporation | Turbine blade with heat shield |
| US10450873B2 (en) * | 2017-07-31 | 2019-10-22 | Rolls-Royce Corporation | Airfoil edge cooling channels |
| CN114439553B (en) * | 2022-03-04 | 2024-07-05 | 中国航发沈阳发动机研究所 | Low thermal stress turbine cooling guide vane |
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