CN110863862A - Blade tip structure and turbine - Google Patents
Blade tip structure and turbine Download PDFInfo
- Publication number
- CN110863862A CN110863862A CN201911234798.5A CN201911234798A CN110863862A CN 110863862 A CN110863862 A CN 110863862A CN 201911234798 A CN201911234798 A CN 201911234798A CN 110863862 A CN110863862 A CN 110863862A
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- blade tip
- side rib
- blade
- tip structure
- cavity
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a blade tip structure and a turbine, and belongs to the technical field of engines. Wherein the apex structure includes: the top of the rotating blade is provided with a concave cavity, and two sides of the concave cavity are respectively provided with a concave cavity suction surface side rib plate and a concave cavity pressure surface side rib plate; and a guide hole is formed in the side rib plate of the suction surface of the cavity. The casing is located at the top of the rotating blade of the blade tip structure, and a blade tip gap exists between the casing and the top support of the rotating blade. According to the blade tip structure provided by the embodiment of the invention, the side rib plate of the concave cavity suction surface at the top of the rotating blade in the blade tip structure is perforated to guide and control the fluid flowing through the blade tip and change the difference between the speed and the angle of the jet flow of the blade tip and the main flow, so that the leakage vortex strength of the blade tip is reduced, the loss is reduced and the efficiency of a turbine is improved.
Description
Technical Field
The invention belongs to the technical field of engines, and particularly relates to a blade tip structure and a turbine.
Background
Modern turbine buckets have a large pressure differential between the bucket face and the bucket back, which drives the flow of air through the tip clearance, leaking from the bucket face to the bucket back. Due to the small gap and the large pressure differential, this jet tends to reach supersonic velocities. When this supersonic jet leaks through the tip clearance and enters the blade back side, it has a high velocity shear with the main flow in the channel, and thus a strong leakage vortex is formed at the blade tip back side. In addition, a part of the leakage fluid is deflected to the surface of the blade under the action of the main flow pressure gradient and is converged into the upper end wall channel vortex, so that the upper end wall channel vortex is strengthened. The generation and enhancement of these two vortices causes a significant deterioration in turbine performance. Since the loss of the turbine above 1/3 is caused by the tip clearance leakage flow, and the reduction of the loss and the improvement of the efficiency are important problems that must be solved by the turbine component, the research of adopting corresponding control measures to reduce the clearance leakage flow loss is a main subject of the turbine tip clearance research in recent years.
Therefore, the technical problem that the leakage loss of the turbine blade tip cannot be effectively reduced exists in the conventional blade tip structure.
Disclosure of Invention
The embodiment of the invention provides a blade tip structure and a turbine, and at least solves some technical problems.
In a first aspect, an embodiment of the present invention provides a blade tip structure, including:
the top of the rotating blade is provided with a concave cavity, and two sides of the concave cavity are respectively provided with a concave cavity suction surface side rib plate and a concave cavity pressure surface side rib plate;
and a guide hole is formed in the side rib plate of the suction surface of the cavity.
Optionally, there is a point of maximum thickness on the cavity suction side rib;
the guide hole opens in a region between the point of maximum thickness and the trailing edge of the rotating blade on the suction surface side rib of the pocket.
Optionally, the maximum thickness point on the cavity suction surface side rib plate is a tangent point between an inscribed circle between the cavity suction surface side rib plate and the cavity pressure surface side rib plate and the cavity suction surface side rib plate.
Optionally, the aperture of the guide hole is 0.5 to 1 time of the blade tip clearance between the rotary blade and the top casing.
Optionally, the number of the guide holes transversely formed in the rib plate on the suction surface side of the cavity ranges from 3 to 6.
Optionally, the hole pitch between adjacent guide holes is 3 times to 5 times of the hole diameter of the guide hole.
Optionally, the guide hole has an opening angle of 30 ° to 50 ° on the suction side rib of the cavity.
In a second aspect, embodiments of the present invention provide a turbine including a casing and the tip structure of any one of the first aspects, wherein the casing is located at the top of a rotating blade of the tip structure, and the casing has a tip clearance from a top support of the rotating blade.
The blade tip structure and the turbine provided by the embodiment of the invention comprise: the top of the rotating blade is provided with a concave cavity, and two sides of the concave cavity are respectively provided with a concave cavity suction surface side rib plate and a concave cavity pressure surface side rib plate; and a guide hole is formed in the side rib plate of the suction surface of the cavity. According to the blade tip structure provided by the embodiment of the invention, the side rib plate of the concave cavity suction surface at the top of the rotating blade in the blade tip structure is perforated to guide and control the fluid flowing through the blade tip and change the difference between the speed and the angle of the jet flow of the blade tip and the main flow, so that the leakage vortex strength of the blade tip is reduced, the loss is reduced and the efficiency of a turbine is improved.
Drawings
FIG. 1 is a schematic structural view of a blade tip structure according to an embodiment of the present invention;
FIG. 2 is another schematic structural view of a blade tip structure provided in accordance with an embodiment of the present invention;
FIG. 3 is a schematic view of the operation of a blade tip structure according to an embodiment of the present invention;
FIG. 4 is a schematic view of a blade tip structure according to an embodiment of the present invention;
FIG. 5 is a schematic view of a point of maximum thickness for a blade tip structure provided by an embodiment of the present invention.
Summary of reference numerals:
the rotor blade comprises a rotor blade 1, a casing 2, a rib plate on the suction surface side of a blade cavity-3, a guide hole-4, a cavity on the top of the blade-5, a cavity pressure surface-6, a cavity suction surface-7 and a gap-8 between the rotor blade 1 and the casing 2.
Detailed Description
The present invention will be described in further detail with reference to the following embodiments.
Referring to fig. 1, a schematic structural diagram of a blade tip structure according to an embodiment of the present invention is shown. As shown in fig. 1, the blade tip structure mainly includes:
the rotary blade comprises a rotary blade 1, wherein the top of the rotary blade 1 is provided with a cavity 5, and two sides of the cavity 5 are respectively provided with a suction surface side rib plate 3 and a pressure surface side rib plate 6 of the cavity 5;
the cavity 5 is provided with a guide hole 4 on the suction surface side rib plate 3.
The blade tip structure provided in the present embodiment is generally applied to a turbine, and as shown in fig. 1 and fig. 2, a casing 2 is disposed on the top of the blade tip structure, and a blade tip gap 8 exists between the blade tip structure and the casing 2. As shown in fig. 1, a guide hole 4 is formed in a suction surface side rib 3 of a cavity 5 formed in the top of a rotary blade 1. As shown in fig. 3, 13 is a leakage vortex formed by the airflow on the pressure surface side rib 66 side of the cavity 5 leaking to the suction surface side rib 37 side of the cavity 5 through the tip clearance 88, and 14 is the airflow passing through the guide hole 4. As shown in fig. 4, 15 is the air flow around the suction side rib 37 of the cavity 5.
As shown in fig. 3 and 4, the leakage vortex is purged by the gas flow passing through the guide hole 4, so that the size of the leakage vortex is reduced, and the loss is reduced.
The difference between the flow angle of the air flow 14 passing through the guide holes 44 and the air flow 15 flowing around the suction surface 7 is reduced, so that the mixing between the air flow 14 and the air flow 15 is reduced, and the loss is reduced.
The strength of the tip leakage vortex is directly related to the tip loss, the tip jet is a direct reason for generating the tip leakage vortex, and the turbine movable blade inevitably has the tip jet due to the pressure difference on two sides of the tip, so the tip jet is guided and controlled, the tip loss can be effectively reduced, and the turbine efficiency is improved. This can be accomplished by perforating the suction side of the blade tip. On one hand, the airflow jetted out of the guide hole 4 is controlled, the difference between the direction and the angle of the jet flow and the main flow is reduced, the leakage vortex strength is effectively reduced, on the other hand, the partial airflow in the blade tip concave cavity 5 flows out of the hole, the airflow jetted out of the upper side of the blade tip ribbed plate is reduced, the flow speed is also reduced, and the blade tip leakage vortex strength is also reduced. The jet flow passing through the holes can be effectively controlled by adjusting the positions, the number, the diameters and the angles of the holes, so that the flow and the speed of the air flow jetted from the upper part of the ribbed plate of the blade tip are also influenced, the flowing effective control of the blade tip is achieved, the leakage vortex strength of the blade tip is reduced, the leakage loss of the blade tip is reduced, and the efficiency of the turbine is improved.
Optionally, there is a point of maximum thickness on the suction side rib 3 of said cavity 5;
the guide hole 4 opens in the area between the point of maximum thickness on the suction side rib 3 of the cavity 5 and the trailing edge of the rotor blade 1.
Optionally, the maximum thickness point on the suction side rib 3 of the cavity 5 is a tangent point between an inscribed circle between the suction side rib 3 and the pressure side rib 6 of the cavity 5 and the suction side rib 3 of the cavity 5.
As shown in fig. 5, 9 is a contour line of the pressure surface 6 in a plan view direction, 10 is a contour line of the suction surface 7 in a plan view direction, 11 is a circle having the largest diameter among circles which are tangent to the contour lines of the pressure surface and the suction surface at the same time, and 12 is an angle between the center line of the guide hole 4 and the contour line of the local suction surface. It is ensured that the strength of the side ribs is not affected by the guide holes 4 and that the guide holes 4 are located in a better air flow guiding area.
Optionally, the aperture of the guide hole 4 is 0.5 to 1 times of the tip clearance 8 between the rotary blade 1 and the top casing 2.
Optionally, the number of the guide holes 4 transversely formed on the suction surface side rib plate 3 of the cavity 5 ranges from 3 to 6.
Optionally, the hole pitch between adjacent guide holes 4 is 3 times to 5 times the hole diameter of the guide hole 4.
Optionally, the opening angle of the guide hole 4 on the suction side rib 3 of the cavity 5 is 30 ° to 50 °.
And the air flow guiding effect of the blade tip structure is comprehensively optimized by limiting relevant parameters of the guide hole 4. Parameters such as the number, the position, the aperture and the angle of the guide holes 4 can be changed along with different flow fields of the blade tips, and the parameters can be changed according to the flow fields and requirements to guide and control jet flow of the blade tips.
In a specific example, the number of the guide holes 4 on the suction side rib plate 3 of the cavity 5 provided with the blade tip structure is 5, the hole diameter is 0.8mm, and the included angle β between the central line of the 5 holes and the X axis is 35 degrees.
In summary, in the blade tip structural scheme provided in the embodiment of the present invention, the guide hole is formed to guide the airflow entering the cavity, so that part of the airflow in the cavity flows out of the guide hole on the suction surface side rib plate of the cavity, part of the airflow flows out of the opening at the trailing edge of the cavity, and the remaining airflow is ejected from the upper side of the suction surface side rib plate of the cavity. By adjusting the position, the direction, the aperture and other parameters of the guide hole, the airflow in the cavity can be guided according to the blade profile and the working condition, the flow of the airflow ejected from the hole and the speed difference and the angle difference between the airflow and the main flow are adjusted, the shearing effect of the airflow and the main flow is reduced, the tip leakage vortex strength can be effectively reduced, the flow of the airflow ejected from the upper part of the rib plate on the suction surface side of the tip is also reduced, and the effect of reducing the tip leakage vortex strength is also achieved. The provided turbine movable blade tip structure can reduce tip leakage vortex strength, reduce tip leakage loss and improve turbine efficiency by more than 0.3%. In addition, only the ribbed plate on the suction surface side of the concave cavity of the blade tip is punched, so that the processing is convenient to realize.
In addition, the embodiment of the invention also provides a turbine which comprises a casing 2 and a blade tip structure. The casing 2 is located at the top of the rotating blade 1 of the blade tip structure, and a blade tip gap 8 exists between the casing 2 and a top bracket of the rotating blade 1. The tip structure may be the tip structure described above with reference to any of fig. 1-5.
According to the turbine provided by the embodiment of the invention, the fin plate on the suction surface side of the concave cavity at the top of the rotating blade in the blade tip structure is perforated, so that the fluid flowing through the blade tip is guided and controlled, and the difference between the jet flow speed and the main flow speed and angle of the blade tip is changed, thereby reducing the leakage vortex strength of the blade tip, reducing the loss and improving the efficiency of the turbine. The specific implementation process of the turbine provided in this embodiment may refer to the specific implementation process of the threaded connection structure shown in fig. 1 to 5, and details are not repeated herein.
The above description is only for the specific embodiments of the present disclosure, but the scope of the present disclosure is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present disclosure, and all the changes or substitutions should be covered within the scope of the present disclosure. Therefore, the protection scope of the present disclosure should be subject to the protection scope of the claims.
Claims (8)
1. A blade tip structure, comprising:
the top of the rotating blade is provided with a concave cavity, and two sides of the concave cavity are respectively provided with a concave cavity suction surface side rib plate and a concave cavity pressure surface side rib plate;
and a guide hole is formed in the side rib plate of the suction surface of the cavity.
2. The blade tip structure of claim 1 wherein a point of maximum thickness exists on the pocket suction side rib;
the guide hole opens in a region between the point of maximum thickness and the trailing edge of the rotating blade on the suction surface side rib of the pocket.
3. The blade tip structure as defined in claim 2, wherein the point of greatest thickness at the pocket suction side rib is a tangent between an inscribed circle between the pocket suction side rib and the pocket pressure side rib and the pocket suction side rib.
4. The blade tip structure according to any one of claims 1 to 3 wherein the aperture of the guide hole is 0.5-1 times the tip clearance between the rotating blade and the top case.
5. The blade tip structure as defined in claim 4 wherein said guide holes formed transversely in said cavity suction side ribs range in number from 3 to 6.
6. The blade tip structure of claim 5 wherein the hole pitch between adjacent guide holes is between 3 and 5 times the hole diameter of the guide hole.
7. The blade tip structure of claim 6 wherein the angle of the opening of the guide holes in the concave suction side rib is between 30 ° and 50 °.
8. A turbine comprising a casing and the tip structure of any one of claims 1 to 7, the casing being located at the top of a rotating blade of the tip structure, the casing being in tip clearance with a top shelf of the rotating blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911234798.5A CN110863862B (en) | 2019-12-05 | 2019-12-05 | Blade tip structure and turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911234798.5A CN110863862B (en) | 2019-12-05 | 2019-12-05 | Blade tip structure and turbine |
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| Publication Number | Publication Date |
|---|---|
| CN110863862A true CN110863862A (en) | 2020-03-06 |
| CN110863862B CN110863862B (en) | 2022-12-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911234798.5A Active CN110863862B (en) | 2019-12-05 | 2019-12-05 | Blade tip structure and turbine |
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| Country | Link |
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| CN (1) | CN110863862B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111379594A (en) * | 2020-04-06 | 2020-07-07 | 中国航发沈阳发动机研究所 | Turbine rotor blade groove-shaped blade top structure and design method thereof |
| CN114876693A (en) * | 2022-06-13 | 2022-08-09 | 西安理工大学 | Through-flow turbine device with curved groove |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101131096A (en) * | 2006-08-21 | 2008-02-27 | 通用电气公司 | Flared tip turbine blade |
| US20080118367A1 (en) * | 2006-11-21 | 2008-05-22 | Siemens Power Generation, Inc. | Cooling of turbine blade suction tip rail |
| US8708645B1 (en) * | 2011-10-24 | 2014-04-29 | Florida Turbine Technologies, Inc. | Turbine rotor blade with multi-vortex tip cooling channels |
| CN105179022A (en) * | 2015-09-30 | 2015-12-23 | 北京大学 | Turbine blade of blade top rib wing structure |
| CN105937410A (en) * | 2015-03-04 | 2016-09-14 | 通用电气公司 | Turbine rotor blade |
| CN106089313A (en) * | 2015-04-29 | 2016-11-09 | 通用电气公司 | There is the rotor blade extending out tip |
| CN207554113U (en) * | 2017-03-31 | 2018-06-29 | 中国航发商用航空发动机有限责任公司 | Aero-turbine rotor assembly and its blade |
-
2019
- 2019-12-05 CN CN201911234798.5A patent/CN110863862B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101131096A (en) * | 2006-08-21 | 2008-02-27 | 通用电气公司 | Flared tip turbine blade |
| US20080118367A1 (en) * | 2006-11-21 | 2008-05-22 | Siemens Power Generation, Inc. | Cooling of turbine blade suction tip rail |
| US8708645B1 (en) * | 2011-10-24 | 2014-04-29 | Florida Turbine Technologies, Inc. | Turbine rotor blade with multi-vortex tip cooling channels |
| CN105937410A (en) * | 2015-03-04 | 2016-09-14 | 通用电气公司 | Turbine rotor blade |
| CN106089313A (en) * | 2015-04-29 | 2016-11-09 | 通用电气公司 | There is the rotor blade extending out tip |
| CN105179022A (en) * | 2015-09-30 | 2015-12-23 | 北京大学 | Turbine blade of blade top rib wing structure |
| CN207554113U (en) * | 2017-03-31 | 2018-06-29 | 中国航发商用航空发动机有限责任公司 | Aero-turbine rotor assembly and its blade |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111379594A (en) * | 2020-04-06 | 2020-07-07 | 中国航发沈阳发动机研究所 | Turbine rotor blade groove-shaped blade top structure and design method thereof |
| CN114876693A (en) * | 2022-06-13 | 2022-08-09 | 西安理工大学 | Through-flow turbine device with curved groove |
| CN114876693B (en) * | 2022-06-13 | 2024-03-22 | 西安理工大学 | Through-flow turbine device with curved groove |
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| Publication number | Publication date |
|---|---|
| CN110863862B (en) | 2022-12-06 |
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