CN114017133A - Cooled variable-geometry low-pressure turbine guide vane - Google Patents
Cooled variable-geometry low-pressure turbine guide vane Download PDFInfo
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- CN114017133A CN114017133A CN202111341295.5A CN202111341295A CN114017133A CN 114017133 A CN114017133 A CN 114017133A CN 202111341295 A CN202111341295 A CN 202111341295A CN 114017133 A CN114017133 A CN 114017133A
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- cold air
- flow path
- blade
- pressure turbine
- rotating shaft
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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 turbine guide blades of aircraft engines, and particularly relates to a cooling type variable-geometry low-pressure turbine guide blade. The method comprises the following steps: the air conditioner comprises an upper rotating shaft (1), an upper rotary table (2), a blade body (3), a lower rotary 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 throttling holes (7) are formed in a bottom plate on 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 all provided with airflow channels, the inner parts of the upper rotary table (2) and the blade body (3) are provided with first partition ribs and second partition ribs, and the first partition ribs and the second partition ribs divide the whole airflow channels into three cold air flow paths. This application can realize becoming how much low pressure turbine guide vane's cooling, compromise blade cooling, dish chamber air feed, many-sided requirements such as end wall obturage and producibility.
Description
Technical Field
The application belongs to the field of turbine guide blades of aircraft engines, and particularly relates to a cooling type variable-geometry low-pressure turbine guide blade.
Background
With the development of aviation technology, an aircraft engine is required to combine high unit thrust in supersonic, combat and maneuver flight states and low consumption flow rate in subsonic cruising, standby and air patrol. This trend has prompted researchers to come up with the concept of a variable cycle engine that, in order to maximize its performance and efficiency throughout subsonic and supersonic flight, designers have varied the air flow through the turbine nozzle by rotating the guide vanes to adjust the throat area of the nozzle to meet different engine operating conditions. 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 rotating shafts are additionally arranged 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 and lower edge plates and the limit of the rotating shaft, the design of the cooling structure of the inner cavity of the blade is more difficult.
The low-pressure turbine guide vane with the conventional structure is generally of a single-cavity cooling structure, an impact guide duct piece is arranged in a cavity, cold air enters an impact guide pipe from an upper edge plate, most of the cold air is discharged into a disc cavity of a lower edge plate after passing through the impact guide pipe, and the axial force of a rotor is balanced; 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 strengthened, the impacted cooling gas flows to the tail edge and is discharged into the main channel from the tail edge gas film holes to form gas film cooling. The variable-cycle engine belongs to a pre-research technology, the domestic research is just started, and no mature technical scheme and application case exist for the variable-geometry low-pressure turbine guide vane matched with the variable-cycle engine. Compared with the conventional low-pressure turbine guide vane, the appearance structure of the variable-geometry low-pressure turbine guide vane is obviously changed, and the cooling structure form commonly adopted in the conventional-structure low-pressure turbine guide vane cannot be continuously applied to the variable-geometry low-pressure turbine guide vane. Meanwhile, the front temperature of the turbine of the variable-cycle engine is further increased, and the currently commonly adopted cooling structure cannot meet the requirement of blade cooling.
Accordingly, a technical solution is desired to overcome or at least alleviate 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 to address at least one of the problems 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 platform, a blade body, a lower rotating platform and a lower rotating shaft which are connected in sequence from the upper end to the lower end, wherein,
a cold air inlet is formed in the side wall of the upper rotating shaft, a gas collecting cavity is formed in the upper rotating shaft, and a plurality of throttling holes are formed in a bottom plate on the lower side of the upper rotating shaft;
go up the revolving stage the blade body down the revolving stage and the inside of pivot all is provided with airflow channel down, go up the revolving stage and the inside of blade body is provided with first rib and second rib that separates, first rib that separates and the second rib that separates is three air conditioning flow paths with holistic airflow channel, include:
the first cold air flow path is of a rotary channel structure and comprises an air flow channel on the front side of the upper rotary table and an air flow channel at the front edge position of the blade body, and cold air enters the first cold air flow path through the throttle hole, 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 cold air enters the second cold air flow path through the throttling hole, sequentially passes through the airflow channel in the middle of the upper rotary table, the airflow channel in the middle of the blade body, the airflow channel of the lower rotary table and the airflow channel of the lower rotary shaft and then is discharged into the disc cavity;
the third air conditioning flow path, the third air conditioning flow path is gyration channel structure, the third air conditioning flow path include the air current passageway of last revolving stage rear side and the air current passageway of the trailing edge position of blade body, air conditioning by the orifice gets into the third air conditioning flow path is through gyration channel, by the second through-hole that is located gyration channel end and the blade basin air film hole of blade body trailing edge discharges.
In at least one embodiment of this application, along the circumference equipartition 4 cold air intakes have been gone up to the lateral wall of pivot.
In at least one embodiment of the present application, a first spoiler rib is provided inside the first cold air flow path.
In at least one embodiment of this application, the blade leading edge is provided with the whirl chamber, and the air conditioning in the first air conditioning flow path is discharged through the blade back air film hole after the jump hole that the blade leading edge set up gets into the whirl chamber.
In at least one embodiment of the present application, a jet angle of the cold air in the impingement hole 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 divides the airflow channel in the middle of the blade body into two cold air flow paths.
In at least one embodiment of the present application, a second flow disturbing rib is provided inside the second cold air flow path.
In at least one embodiment of the present application, a third spoiler rib is provided inside the third cold air flow path.
The invention has at least the following beneficial technical effects:
the cooling type variable geometry low-pressure turbine guide vane meets the requirements of vane cooling, disc cavity air supply, end wall sealing, producibility and the like, and on the basis of meeting the requirement of vane cooling, a disc cavity air supply flow path with adjustable flow area is designed, so that the requirement of disc cavity air supply can be met; a cold air outflow hole is designed at the end wall of the blade to achieve a certain sealing effect; the blade has low process difficulty and good casting manufacturability.
Drawings
FIG. 1 is a comparison of a conventional configuration of one embodiment of the present application with a variable geometry guide vane;
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 of an embodiment of the present 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 in fig. 5.
Wherein:
1-an upper rotating shaft; 2-upper rotating platform; 3-leaf body; 4-lower turntable; 5-lower rotating shaft; 6-a cold air inlet; 7-orifice; 8-a first via; 9-a second via; 10-a first cold air flow path; 11-a second cold air flow path; 12-a third cold air flow path; 13-leaf back air film hole; 14-impingement holes; 15-leaf basin air film hole.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the 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 a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 6.
The application provides a cooled becomes how much low pressure turbine guide vane, includes: the upper rotary shaft 1, the upper rotary table 2, the blade body 3, the lower rotary table 4 and the lower rotary shaft 5 are sequentially connected from the upper end to the lower end.
As shown in fig. 1, the guide vane of the low pressure turbine of the conventional structure is structurally composed of an upper flange a, a lower flange B and a blade body C, and the vane is hung on a casing and belongs to a stator member. In order to realize the integral adjustment of the blades, 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 part. In order to realize the rotation of the blade body C, the upper rotating shaft 1, the lower rotating shaft 5, the upper rotating platform 2 and the lower rotating platform 4 are additionally arranged at the upper end and the lower end of the blade body C, wherein the upper rotating shaft 1 and the lower rotating shaft 5 are the axes of the suspended rotation of the blades, the upper rotating platform 2 and the lower rotating platform 4 are used for containing the blade profile to the maximum extent, the exposure of the end wall is reduced, and therefore the gas leakage amount in the gap of the end wall is reduced, meanwhile, the upper rotating platform 2 and the lower rotating platform 4 are matched with the upper edge plate A and the lower edge plate B, and the gas leakage of a main channel is avoided. The size of the rotating shaft and the rotating platform is obviously smaller than the chord length of the blade body section, so that the inner cavity of the blade is in a semi-closed state. The variable geometry low-pressure turbine guide blade does not have the condition that the inner cavity of the blade is designed to be a low-pressure turbine guide blade open type structure similar to a conventional structure, auxiliary cooling structures such as a cold air duct D and the like cannot be installed in the inner cavity of the blade, and the difficulty in designing a blade cooling structure is greatly increased.
As shown in fig. 2-3, the side wall of the upper rotating shaft 1 is provided with a cold air inlet 6, a gas collecting cavity 17 is arranged inside the upper rotating shaft 1, and a lower bottom plate of the upper rotating shaft 1 is provided with a plurality of throttle holes 7; go up revolving stage 2, blade 3, down the inside of revolving stage 4 and lower pivot 5 and all be provided with airflow channel, the inside of going up revolving stage 2 and blade 3 is provided with first partition rib and second partition rib, and first partition rib and second partition rib separate holistic airflow channel for 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 cold air flow path 10 is a rotary channel structure, the first cold air flow path 10 comprises an air flow path on the front side of the upper rotary table 2 and an air flow path at the front edge position of the blade body 3, and cold air enters the first cold air flow path 10 through the throttle hole 7, passes through the rotary channel and is discharged through 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; the cold air enters the second cold air flow path 11 through the throttling hole 7, sequentially passes through the airflow channel in the middle of the upper rotary table 2, the airflow channel in the middle of the blade body 3, the airflow channel of the lower rotary table 4 and the airflow channel of the lower rotary shaft 5 and then is discharged into the disc cavity; the third cold air flow path 12 is a rotary channel structure, the third cold air flow path 12 comprises an air flow path at the rear side of the upper rotary table 2 and an air flow path at the tail edge position of the blade body 3, and cold air enters the third cold air flow path 12 through the throttle hole 7, passes through the rotary channel, and is discharged through 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.
The utility model provides a cooling type becomes how much low pressure turbine guide vane, according to becoming how much low pressure turbine guide vane's structural feature, the cooling gas gets into the gas collection chamber 17 of pivot 1 inside from the air conditioning import 6 of last pivot 1, for guaranteeing the inside pressure of gas collection chamber 7. In this embodiment, 4 cold air inlets 6 are uniformly distributed on the side wall of the upper rotating shaft 1 along the circumferential direction. In the blade inner cavity, a cold air flow path is designed according to cooling requirements and other functional requirements, according to the thermal load distribution condition of the blade, the front edge and the tail edge are two areas with high thermal load of the blade, and need to be intensively cooled, 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, balance the axial force of the engine and simultaneously consider the cooling of the middle area of the blade. 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 collecting chamber 17, and the orifice 7 is used 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 guide vane of the present application is used to cool the high temperature region of the leading edge of the vane. Cold air enters from the throttling hole 7 and is discharged from the first through hole 8 and the blade back air film hole 13 at the tail end of the rotary channel. Because the front 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, the flow loss is reduced, 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, the gas flow rate is increased, the internal heat exchange is enhanced, and the first turbulence rib is further arranged inside the first cold air flow path 10 to enhance the surface heat exchange. In addition, in order to increase the cooling effect of the tail end of the rotary channel in the first cold air flow path 10, the first through hole 8 of the air outlet hole is added at the tail end of the rotary channel so as to ensure the fluidity of the cold air at the tail end, and meanwhile, the cold air discharged from the first through hole 8 can also play a certain pneumatic sealing role. Preferably, in this embodiment, a swirl chamber 16 is disposed at the leading edge of the blade body 3, and after the leading edge approaches through the revolving channel, the cold air enters the leading edge swirl chamber 16 through the impact holes 14 near the leading edge of the blade body 3, and finally is discharged through the blade back film holes 13. Preferably, in this embodiment, as shown in fig. 6, a jet angle of the cold air in the impact hole 14 is tangent to the swirl chamber 16, the cold air flows against the wall after entering the swirl chamber 16, and washes an inner wall surface of the swirl chamber to cool the inner wall surface of the swirl chamber 16, and then the cold air is discharged through the blade back air film hole 13 on the back side of the swirl chamber 16, and the discharged cold air covers the blade back side to form air film cooling on the blade back.
The utility model provides a cooled becomes how much low pressure turbine guide vane, second air conditioning flow path 11 are dish chamber bleed air flow path, compromise the blade cooling needs, are mainly responsible for introducing the dish chamber with gaseous by the engine outer loop for balanced engine axial force, utilize the air conditioning through this flow path to cool off the blade simultaneously. The cold air enters from the throttling hole 7 and is discharged into the disc cavity from the outlet of the lower rotating shaft 5. Advantageously, in this embodiment, a third partition rib is further disposed inside the blade body 3, and the third partition rib divides the airflow channel in the middle of the blade body 3 into two cold air flow paths, that is, the blade section of the second cold air flow path 11 forms two flow path branches, and a partition rib is designed in the middle of the flow path, so that the problem of possible insufficient strength due to too wide flow path can be avoided. In this embodiment, a second turbulence rib is further disposed in the second cold air flow path 11 to enhance heat exchange. The flow path is designed in the area with the largest blade profile thickness, has larger flow area compared with other flow paths, and needs more cold air to flow through 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 intensity of the flow path is improved by utilizing the characteristic of large air supply quantity of the disc cavity, and the throttling hole 7 plays a role in adjusting the flow rate of the flow path.
In the cooling type variable geometry low pressure turbine guide vane of the present application, the third cooling air flow path 12 is mainly used for cooling the high temperature region at the trailing edge position. The cold air enters the third cold air flow path 12 from the throttle hole 7, passes through the rotary channel to reach the high temperature zone at the tail edge of the blade, and is discharged from the second through hole 9 and the blade basin air film hole 15 at the tail end of the channel. Similar to the first cold air flow path 10, the reason for this path is that the high temperature zone of the trailing edge is farther from the cold air inlet. The flow path is close to the tail edge of the blade, the blade profile is thin, 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, a 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 an air outlet hole-a second vent hole 9 to ensure the fluidity of tail end cold air. The film holes are designed in the area with the strongest heat exchange at the tail edge to form film cooling on the side surface of the blade basin, the cold air outflow can generate suction effect on the flow path 12, and the fluidity of the cold air in the flow path is mainly determined by the air outlet quantity of the second through holes 9 and the blade basin film holes 15.
The application discloses cooling formula becomes geometry low pressure turbine guide vane can realize becoming geometry low pressure turbine guide vane's cooling. The structure gives consideration to the requirements of various aspects such as blade cooling, disc cavity air supply, end wall sealing, producibility and the like, and on the basis of meeting the requirement of blade cooling, a disc cavity air supply flow path with adjustable flow area is designed, so that the requirement of disc cavity air supply can be met; a cold air outflow hole is designed at the end wall of the blade to achieve a certain sealing effect; the blade has low process difficulty and good casting manufacturability.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within 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 rotary table (2), a blade body (3), a lower rotary table (4) and a lower rotating shaft (5) which are connected in sequence 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), a gas collecting cavity (17) is formed in the upper rotating shaft (1), and a plurality of throttling holes (7) are formed in a bottom plate on the lower side of the upper rotating shaft (1);
go up revolving stage (2), blade (3) down revolving stage (4) and the inside of pivot (5) all is provided with airflow channel down, go up revolving stage (2) and the inside of blade (3) is provided with first rib and second and separates the rib, first rib and the second separates the rib and separates holistic airflow channel for three air conditioning flow paths, include:
the first cold air flow path (10) is of a rotary channel structure, the first cold air flow path (10) comprises an air flow channel on the front side of the upper rotary table (2) and an air flow channel at the front edge position of the blade body (3), and 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 cold air enters the second cold air flow path (11) through the throttling hole (7), sequentially passes through the airflow channel in the middle of the upper rotary table (2), the airflow channel in the middle of the blade body (3), the airflow channel of the lower rotary table (4) and the airflow channel of the lower rotary shaft (5) and then is discharged into the disc cavity;
third air conditioning flow path (12), third air conditioning flow path (12) are gyration channel structure, third air conditioning flow path (12) include the air current passageway of revolving stage (2) rear side and the air current passageway of the trailing edge position of blade (3), cold air by orifice (7) get into third air conditioning flow path (12), through gyration channel, by be located gyration channel terminal second through-hole (9) and blade basin air film hole (15) of blade (3) trailing edge discharge.
2. The cooled variable-geometry low-pressure turbine guide vane as claimed in claim 1, wherein 4 cold air inlets (6) are uniformly distributed on the side wall of the upper rotating shaft (1) along the circumferential direction.
3. The cooled variable geometry low pressure turbine guide vane as claimed in claim 1, characterized in that a first turbulator rib is provided inside the first cold air flow path (10).
4. The cooled variable geometry low pressure turbine guide vane as claimed in claim 3, wherein a swirl chamber (16) is provided at the leading edge of the blade body (3), and the cool air in the first cool air flow path (10) enters the swirl chamber (16) through the impact holes (14) provided at the leading edge of the blade body (3) and is discharged through the film holes (13) at the blade back.
5. The cooled variable geometry low pressure turbine guide vane as claimed in claim 4, wherein the jet angle of the cold air in the impingement hole (14) is tangential to the swirl chamber (16).
6. The cooled variable geometry low pressure turbine guide vane as claimed in claim 1, characterized in that the blade body (3) is provided with a third partition rib inside, which divides the air flow passage in the middle of the blade body (3) into two cold air flow paths.
7. The cooled variable geometry low pressure turbine guide vane as claimed in claim 6, characterized in that a second turbulator rib is provided inside the second cold air flow path (11).
8. The cooled variable geometry low pressure turbine guide vane as claimed in claim 1, wherein a third turbulator rib is provided inside the third cold gas flow path (12).
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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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| 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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2021
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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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| CN114017133B (en) | 2023-07-07 |
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