CN114017133B - Cooled variable geometry low pressure turbine guide vane - Google Patents
Cooled variable geometry low pressure turbine guide vane Download PDFInfo
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- CN114017133B CN114017133B CN202111341295.5A CN202111341295A CN114017133B CN 114017133 B CN114017133 B CN 114017133B CN 202111341295 A CN202111341295 A CN 202111341295A CN 114017133 B CN114017133 B CN 114017133B
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- air flow
- cold air
- flow path
- pressure turbine
- variable geometry
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application belongs to the field of aeroengine turbine guide vanes, and particularly relates to a cooling variable geometry low pressure turbine guide vane. Comprising the following steps: an upper rotating shaft (1), an upper rotating table (2), a blade body (3), a lower rotating table (4) and a lower rotating shaft (5) which are sequentially connected from the upper end to the lower end, wherein a cold air inlet (6) is formed in the side wall of the upper rotating shaft (1), an air collecting cavity (17) is formed in the upper rotating shaft (1), and a plurality of orifices (7) are formed in the bottom plate of the lower side of the upper rotating shaft (1); the inner parts of the upper rotary table (2), the blade body (3), the lower rotary table (4) and the lower rotary shaft (5) are respectively provided with an air flow channel, the inner parts of the upper rotary table (2) and the blade body (3) are provided with a first partition rib and a second partition rib, and the first partition rib and the second partition rib divide the whole air flow channel into three cold air flow channels. The variable geometry low-pressure turbine guiding vane cooling device can realize cooling of the variable geometry low-pressure turbine guiding vane, and has the multi-aspect requirements of vane cooling, disk cavity air supply, end wall sealing, producibility and the like.
Description
Technical Field
The application belongs to the field of aeroengine turbine guide vanes, and particularly relates to a cooling variable geometry low pressure turbine guide vane.
Background
With the development of aeronautical technology, the aeronautical engines are required to give consideration to high thrust units in supersonic, fight and maneuvering flight conditions, as well as low consumption flow rates for subsonic cruising, standby and air patrol. This trend has prompted researchers to propose the concept of variable cycle engines, which designers have adjusted the throat area of the turbine guide to vary the air flow through it by rotating the guide vanes to meet different engine operating conditions in order to maximize the performance and efficiency of the variable cycle engine throughout subsonic and supersonic flight. In order to realize the rotation of the guide vane, the vane body of the low-pressure turbine guide vane is separated from the upper and lower edge plates, and the rotating shafts are added at the upper and lower ends of the vane body to form the variable geometry low-pressure turbine guide vane. Because the blade body is separated from the upper edge plate and the lower edge plate, and the cooling structure of the inner cavity of the blade is more difficult to design due to the limitation of the rotating shaft.
The low-pressure turbine guide vane with a conventional structure adopts a single-cavity cooling structure, an impact guide pipe piece is arranged in a cavity, cold air enters an impact guide pipe from an upper edge plate, and most of the cold air is discharged into a disk cavity of a lower edge plate after passing through the impact guide pipe to balance the axial force of a rotor; a small amount of gas flows out through the impact holes on the impact guide pipe to form impact cooling on a local high-temperature area of the blade, heat exchange is enhanced, the impacted cooling gas flows to the tail edge and is discharged into the main channel from the tail edge gas film hole to form gas film cooling. The variable cycle engine belongs to a pre-research technology, and the domestic research is just started, and the variable geometry low pressure turbine guide vane matched with the variable cycle engine has no mature technical proposal and application case. Compared with the conventional low-pressure turbine guide vane, the external structure of the variable geometry low-pressure turbine guide vane is changed significantly, and the cooling structure form commonly adopted in the conventional low-pressure turbine guide vane cannot be continuously applied to the variable geometry low-pressure turbine guide vane. Meanwhile, the temperature before the turbine of the variable cycle engine is further improved, and the cooling structure type commonly adopted at present cannot meet the cooling requirement of the blades.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a cooled variable geometry low pressure turbine guide vane that solves at least one problem of the prior art.
The technical scheme of the application is as follows:
a cooled variable geometry low pressure turbine guide vane comprising: an upper rotating shaft, an upper rotating table, a blade body, a lower rotating table and a lower rotating shaft which are sequentially connected from the upper end to the lower end,
a cold air inlet is formed in the side wall of the upper rotating shaft, an air collecting cavity is formed in the upper rotating shaft, and a plurality of orifices are formed in a bottom plate on the lower side of the upper rotating shaft;
the inside of going up the revolving stage, the leaf body, the revolving stage down and the pivot down all is provided with the air current passageway, go up the revolving stage with the inside of leaf body is provided with first barrier rib and second barrier rib, first barrier rib with the second barrier rib separates holistic air current passageway into three air conditioning flow paths, includes:
the first cold air flow path is of a rotary channel structure, and comprises an air flow channel at the front side of the upper rotary table and an air flow channel at the front edge position of the blade body, cold air enters the first cold air flow path from the throttle hole and passes through the rotary channel and is discharged from a first through hole at the tail end of the rotary channel and a blade back air film hole at the front edge of the blade body;
the second cold air flow path, cold air enters the second cold air flow path from the throttle hole, and is discharged into the disc cavity after sequentially passing through the air flow channel in the middle of the upper rotary table, the air flow channel in the middle of the blade body, the air flow channel of the lower rotary table and the air flow channel of the lower rotary shaft;
the third cold air flow path is of a rotary channel structure and comprises an air flow channel at the rear side of the upper rotary table and an air flow channel at the tail edge position of the blade body, cold air enters the third cold air flow path from the throttle hole, passes through the rotary channel and is discharged from a second through hole at the tail end of the rotary channel and a blade basin air film hole at the tail edge of the blade body.
In at least one embodiment of the present application, the side wall of the upper rotating shaft is uniformly provided with 4 cool air inlets along the circumferential direction.
In at least one embodiment of the present application, the first cold air flow path is provided inside with a first spoiler rib.
In at least one embodiment of the present application, the blade front edge is provided with a cyclone cavity, and the cold air in the first cold air flow path enters the cyclone cavity through the impact hole provided at the blade front edge and then is discharged through the blade back air film hole.
In at least one embodiment of the present application, the jet angle of the cold air in the impingement holes is tangential to the swirl chamber.
In at least one embodiment of the present application, a third partition rib is further disposed inside the blade body, and the third partition rib partitions the air flow passage in the middle of the blade body into two cold air flow paths.
In at least one embodiment of the present application, the second cold air flow path is internally provided with a second spoiler rib.
In at least one embodiment of the present application, the third cold air flow path is provided inside with a third spoiler rib.
The invention has at least the following beneficial technical effects:
the cooling type variable geometry low-pressure turbine guide vane has the advantages that the requirements on multiple aspects such as vane cooling, disk cavity air supply, end wall sealing, producibility and the like are met, and on the basis of meeting the vane cooling requirement, a disk cavity air supply flow path with adjustable flow area is designed, so that the disk cavity air supply requirement can be met; the cold air outlet holes are designed at the end wall positions of the blades so as to achieve a certain sealing effect; the blade has low technological difficulty and good casting manufacturability.
Drawings
FIG. 1 is a diagram of a conventional structure in comparison to a variable geometry guide vane according to one embodiment of the present application;
FIG. 2 is a schematic view of a cooled variable geometry low pressure turbine guide vane according to an embodiment of the present application;
FIG. 3 is a cross-sectional view of a cooled variable geometry low pressure turbine guide vane according to an embodiment of the application;
FIG. 4 is a view A-A of FIG. 2;
FIG. 5 is a view C-C of FIG. 2;
fig. 6 is an enlarged view of region I of fig. 5.
Wherein:
1-an upper rotating shaft; 2-an upper turntable; 3-leaf body; 4-a lower turntable; 5-a lower rotating shaft; 6-cool air inlet; 7-an orifice; 8-a first through hole; 9-a second through hole; 10-a first cool air flow path; 11-a second cool air flow path; 12-a third cool air flow path; 13-leaf back air film holes; 14-an impingement hole; 15-leaf basin air film holes.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application. Embodiments of the present application are described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of protection of the present application.
The present application is described in further detail below with reference to fig. 1-6.
The present application provides a cooled variable geometry low pressure turbine guide vane comprising: an upper rotating shaft 1, an upper rotating table 2, a blade body 3, a lower rotating table 4 and a lower rotating shaft 5 which are sequentially connected from the upper end to the lower end.
As shown in fig. 1, the low-pressure turbine guide vane of a conventional structure structurally comprises an upper edge plate a, a lower edge plate B and a vane body C, and the vane is hung on a casing and belongs to stator components. In order to realize the integral adjustment of the blade, the blade body C of the variable geometry low-pressure turbine guide blade is separated from the upper edge plate and the lower edge plate, only the upper edge plate A is hung on the casing, and the blade body C is a rotating piece. In order to realize the rotation of the blade body C, an upper rotating shaft 1, a lower rotating shaft 5, an upper rotating table 2 and a lower rotating table 4 are added at the upper end and the lower end, wherein the upper rotating shaft 1 and the lower rotating shaft 5 are the axes of blade suspension rotation, the upper rotating table 2 and the lower rotating table 4 are used for furthest containing blade shapes, and reducing the exposure of end walls, so that the gas leakage quantity of an end wall gap is reduced, and meanwhile, the upper rotating table 2 and the lower rotating table 4 are matched with an upper edge plate A and a lower edge plate B, and the gas leakage of a main channel is avoided. The dimensions of the shaft and turntable are significantly less than the chord length of She Shenduan, so that the vane cavities are in a semi-closed state. The variable geometry low pressure turbine guide vane does not have the condition that the vane inner cavity is designed to be similar to the open type structure of the low pressure turbine guide vane with the conventional structure, and the auxiliary cooling structure such as the cold air duct D and the like cannot be installed in the vane inner cavity, so that the difficulty in the design of the vane cooling structure is greatly increased.
As shown in figures 2-3, the side wall of the upper rotating shaft 1 is provided with a cold air inlet 6, the inside of the upper rotating shaft 1 is provided with an air collecting cavity 17, and the lower side bottom plate of the upper rotating shaft 1 is provided with a plurality of orifices 7; the inside of going up revolving stage 2, blade body 3, lower revolving stage 4 and lower pivot 5 all is provided with the air current passageway, and the inside of going up revolving stage 2 and blade body 3 is provided with first barrier rib and second barrier rib, and first barrier rib and second barrier rib separate holistic air current passageway into three air conditioning flow paths, include: a first cold air flow path 10, a second cold air flow path 11, and a third cold air flow path 12.
The first cool air flow path 10 is in a rotary channel structure, the first cool air flow path 10 comprises an air flow channel at the front side of the upper rotary table 2 and an air flow channel at the front edge position of the blade body 3, cool air enters the first cool air flow path 10 from the throttle hole 7, passes through the rotary channel and is discharged from the first through hole 8 at the tail end of the rotary channel and the blade back air film hole 13 at the front edge of the blade body 3; a second cool air flow path 11, cool air enters the second cool air flow path 11 from the throttle hole 7, and is discharged into the disc cavity after sequentially passing through the air flow channel in the middle of the upper rotary table 2, the air flow channel in the middle of the blade body 3, the air flow channel of the lower rotary table 4 and the air flow channel of the lower rotary shaft 5; the third cool air flow path 12 is a rotary channel structure, the third cool air flow path 12 comprises an air flow channel at the rear side of the upper rotary table 2 and an air flow channel at the tail edge position of the blade body 3, cool air enters the third cool air flow path 12 from the throttle hole 7, passes through the rotary channel and is discharged from the second through hole 9 at the tail end of the rotary channel and the blade basin air film hole 15 at the tail edge of the blade body 3.
According to the cooling type variable geometry low pressure turbine guide vane, according to the structural characteristics of the variable geometry low pressure turbine guide vane, cooling air enters the air collection cavity 17 in the upper rotating shaft 1 from the cold air inlet 6 in the upper rotating shaft 1, so that the pressure in the air collection cavity 7 is ensured. In this embodiment, 4 cool air inlets 6 are uniformly distributed on the side wall of the upper rotating shaft 1 along the circumferential direction. In the inner cavity of the blade, the cold air flow paths are designed according to the cooling requirement and other functional requirements, and according to the heat load distribution condition of the blade, the front edge and the tail edge are two areas with higher heat load of the blade, and the two areas are provided with two independent cold air flow paths for cooling. An independent cold air flow path is designed in the middle of the blade to supply air to the disc cavity, so that the axial force of the engine is balanced, and meanwhile, the cooling of the middle area of the blade is considered. The whole guide vane has 3 independent cold air flow paths. The cooling gas flows into each flow path through the orifice 7 in the gas collection chamber 17, and the orifice 7 serves to regulate the pressure and flow rate of each flow path. The orifice 7 is shown in fig. 4.
The first cool air flow path 10 of the cooled variable geometry low pressure turbine turning vane of the present application is used to cool the high temperature region of the leading edge of the vane. Cool air enters through the throttle hole 7 and is discharged from the first through hole 8 and the vane back air film hole 13 at the tail end of the rotary channel. Because the leading edge position is far away from the cold air inlet, the first cold air flow path 10 adopts a rotary channel structure, the structure can avoid a large expansion angle in the flow path, and reduce flow loss, and meanwhile, under the condition that the inlet and outlet pressure and the throttling area are certain, the rotary channel can obviously reduce the flow area in the channel, increase the gas flow rate, enhance the internal heat exchange, and the first turbulence rib is also arranged in the first cold air flow path 10 to strengthen the surface heat exchange. In order to increase the cooling effect of the end of the rotary channel in the first cold air flow path 10, the first through hole 8 of the air outlet is added at the end of the rotary channel to ensure the fluidity of the cold air at the end, and meanwhile, the cold air discharged from the first through hole 8 can also play a certain role in pneumatic sealing. Preferably, in this embodiment, the front edge of the blade body 3 is provided with a swirl chamber 16, and after approaching the front edge through the rotation channel, the cool air enters the front edge swirl chamber 16 through the impact hole 14 near the front edge of the blade body 3, and finally is discharged through the blade back air film hole 13. Preferably, in this embodiment, as shown in fig. 6, the jet angle of the cold air in the impact hole 14 is tangential to the cyclone cavity 16, the cold air flows close to the wall after entering the cyclone cavity 16, and washes the inner wall surface of the cyclone cavity 16 to cool the inner wall surface of the cyclone cavity, and then the cold air is discharged through the back air film hole 13 on the back side of the cyclone cavity 16, and the discharged cold air covers the back side of the blade to form air film cooling on the back of the blade.
The cooling type variable geometry low-pressure turbine guide vane is characterized in that the second cold air flow path 11 is a disk cavity air-entraining flow path, the cooling requirement of the vane is considered, and air is mainly led into the disk cavity from an outer ring of the engine to balance the axial force of the engine, and meanwhile, the vane is cooled by the cold air passing through the flow path. Cool air enters through the throttle hole 7 and is discharged into the disc cavity through the outlet of the lower rotating shaft 5. Advantageously, in this embodiment, the third partition rib is further disposed in the blade body 3, and divides the airflow channel in the middle of the blade body 3 into two cold air channels, that is, the blade section of the second cold air channel 11 forms two branches of the channels, and a partition rib is designed in the middle of the channels, so that the problem of possible insufficient strength caused by too wide channels can be avoided. In this embodiment, the second cooling air flow path 11 is further provided with a second turbulence rib, which plays a role in enhancing heat exchange. The flow path is designed in the area with the largest blade profile thickness, and compared with other flow paths, the flow path has larger flow area, and more cold air flows to obtain the heat exchange effect equivalent to other flow paths, so the flow path is designed as a disc cavity air supply flow path, the heat exchange strength of the flow path is improved by utilizing the characteristic of large disc cavity air supply amount, and the throttle hole 7 plays a role of adjusting flow rate of the flow path.
The cooled variable geometry low pressure turbine guide vane of the present application, the third cool air flow path 12 is primarily used to cool the high temperature region of the trailing edge location. The cool air enters the third cool air flow path 12 from the throttle hole 7, reaches the high temperature area of the tail edge of the blade through the rotary channel, and is discharged from the second through hole 9 at the tail end of the channel and the blade basin air film hole 15. Similar to the first cool air flow path 10, the reason for this flow path using the turn-around passage is that the high temperature region of the trailing edge is far from the cool air inlet. Because the flow path is close to the tail edge of the blade, the thickness of the blade profile is thinner, compared with other flow paths, the flow area is smaller under the condition of the same flow path width, the cooling of the blade is more facilitated, the third turbulence rib is arranged in the third cold air flow path 12 to strengthen heat exchange, and the tail end of the flow path is provided with the air outlet hole-second ventilation hole 9, so that the fluidity of the tail end cold air is ensured. And a gas film hole is designed in the area with the strongest heat exchange at the tail edge, gas film cooling is formed on the side surface of the leaf basin, the cold air outflow can generate a suction effect on the flow path 12, and the fluidity of the cold air in the flow path mainly depends on the air outlet quantity of the second through hole 9 and the gas film hole 15 of the leaf basin.
The cooling type variable geometry low pressure turbine guide vane can realize cooling of the variable geometry low pressure turbine guide vane. The structure gives consideration to the requirements of blade cooling, disc cavity air supply, end wall sealing, producibility and the like, and on the basis of meeting the requirements of blade cooling, a disc cavity air supply flow path with adjustable flow area is designed, so that the disc cavity air supply requirement can be met; the cold air outlet holes are designed at the end wall positions of the blades so as to achieve a certain sealing effect; the blade has low technological difficulty and good casting manufacturability.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A cooled variable geometry low pressure turbine guide vane comprising: an upper rotating shaft (1), an upper rotating table (2), a blade body (3), a lower rotating table (4) and a lower rotating shaft (5) which are sequentially connected from the upper end to the lower end,
a cold air inlet (6) is formed in the side wall of the upper rotating shaft (1), an air collecting cavity (17) is formed in the upper rotating shaft (1), and a plurality of orifices (7) are formed in the lower bottom plate of the upper rotating shaft (1);
the utility model provides a fan blade, including upper rotary table (2), blade (3), lower rotary table (4) and the inside of lower pivot (5) all is provided with air current passageway, upper rotary table (2) and the inside of blade (3) is provided with first separating rib and second separating rib, first separating rib and the second separating rib separates holistic air current passageway into three air conditioning flow path, include:
the first cold air flow path (10), the first cold air flow path (10) is a rotary channel structure, the first cold air flow path (10) comprises an air flow channel at the front side of the upper rotary table (2) and an air flow channel at the front edge position of the blade body (3), cold air enters the first cold air flow path (10) through the throttle hole (7), passes through the rotary channel and is discharged through a first through hole (8) at the tail end of the rotary channel and a blade back air film hole (13) at the front edge of the blade body (3);
the second cold air flow path (11), the cold air enters the second cold air flow path (11) from the throttle hole (7), and is discharged into the disc cavity after sequentially passing through the air flow channel in the middle of the upper rotary table (2), the air flow channel in the middle of the blade body (3), the air flow channel of the lower rotary table (4) and the air flow channel of the lower rotary shaft (5);
the third cold air flow path (12), the third cold air flow path (12) is a rotary channel structure, the third cold air flow path (12) comprises an air flow channel at the rear side of the upper rotary table (2) and an air flow channel at the tail edge position of the blade body (3), cold air enters the third cold air flow path (12) through the throttle hole (7), passes through the rotary channel, and is discharged through a second through hole (9) at the tail end of the rotary channel and a blade basin air film hole (15) at the tail edge of the blade body (3).
2. The cooled variable geometry low pressure turbine turning vane of claim 1 wherein 4 cold air inlets (6) are circumferentially and evenly distributed on the side wall of the upper shaft (1).
3. The cooled variable geometry low pressure turbine turning vane of claim 1 wherein the first cold gas flow path (10) is internally provided with first turbulating ribs.
4. A cooled variable geometry low pressure turbine guide vane according to claim 3, characterised in that the leading edge of the vane body (3) is provided with a swirl chamber (16), and the cold air in the first cold air flow path (10) enters the swirl chamber (16) through an impingement hole (14) provided in the leading edge of the vane body (3) and is discharged through a vane back film hole (13).
5. The cooled variable geometry low pressure turbine turning vane of claim 4 wherein the angle of the jet of cold air in the impingement holes (14) is tangential to the swirl chamber (16).
6. The cooled variable geometry low pressure turbine turning vane of claim 1 wherein a third barrier rib is also provided within the blade body (3) and divides the flow path in the middle of the blade body (3) into two cold air flow paths.
7. The cooled variable geometry low pressure turbine turning vane of claim 6 wherein said second cold gas flow path (11) is internally provided with second turbulating ribs.
8. The cooled variable geometry low pressure turbine turning vane of claim 1 wherein the third cold gas flow path (12) is internally provided with third turbulator ribs.
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| CN202111341295.5A CN114017133B (en) | 2021-11-12 | 2021-11-12 | Cooled variable geometry low pressure turbine guide vane |
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| CN202111341295.5A CN114017133B (en) | 2021-11-12 | 2021-11-12 | Cooled variable geometry low pressure turbine guide vane |
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| CN114017133B true CN114017133B (en) | 2023-07-07 |
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| CN112780354A (en) * | 2021-02-03 | 2021-05-11 | 上海交通大学 | Tail edge crack-splitting cooling structure and method suitable for turbine blade and turbine blade |
| CN112922676A (en) * | 2021-02-04 | 2021-06-08 | 大连理工大学 | Internal back basin rotary cooling channel of turbine blade |
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| US20180223681A1 (en) * | 2017-02-09 | 2018-08-09 | General Electric Company | Turbine engine shroud with near wall cooling |
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| JPH06185301A (en) * | 1993-08-16 | 1994-07-05 | Toshiba Corp | Blade of turbine |
| EP1262634A2 (en) * | 2001-05-29 | 2002-12-04 | General Electric Company | Integral nozzle and shroud |
| US7806659B1 (en) * | 2007-07-10 | 2010-10-05 | Florida Turbine Technologies, Inc. | Turbine blade with trailing edge bleed slot arrangement |
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| CN114017133A (en) | 2022-02-08 |
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