CN111852574A - Turbine blade and gas turbine comprising same - Google Patents
Turbine blade and gas turbine comprising same Download PDFInfo
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- CN111852574A CN111852574A CN202010734234.4A CN202010734234A CN111852574A CN 111852574 A CN111852574 A CN 111852574A CN 202010734234 A CN202010734234 A CN 202010734234A CN 111852574 A CN111852574 A CN 111852574A
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- cooling
- turbine blade
- blade
- flow
- channel
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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
A turbine blade and a gas turbine comprising the same, wherein a cooling channel is arranged inside the turbine blade; the turbine blade comprises a clapboard and a flow deflector; the partition plate is arranged in the cooling channel inside the turbine blade and used for enabling the cooling channel to form a serpentine channel cooling structure; wherein the cooling channel at the end of the separator is defined as a turn zone; and the flow deflector is arranged in a turning area in the cooling channel and used for distributing at least three strands of cooling air in the turning area. According to the invention, under the condition of not increasing the total cooling air quantity, the flow of the cooling air in the turning area of the serpentine channel is more accurately controlled, so that the distribution of the cooling air on the cross section of the channel in the turning area is more reasonable and controllable, thereby reducing the pressure loss of the cooling air in the turning area of the blade cooling channel and improving the overall temperature distribution and the thermal stress level of the blade.
Description
Technical Field
The invention relates to the technical field of gas turbine design, in particular to a turbine blade and a gas turbine comprising the same.
Background
With the gradual improvement of economic requirements of gas turbine users, the further enhancement of relevant emission requirements of the gas turbine by environmental protection departments, the gradual improvement of the compressor pressure ratio and the combustion temperature of the gas turbine, and the cooling design of hot-end components of the gas turbine, especially turbine blades, face higher and higher challenges. In order to ensure safe and reliable operation of the turbine blade, it is necessary to design the turbine blade with a complex cooling system to maintain the temperature and stress distribution of the blade body at a reasonable level.
In the design process of turbine blade cooling, the serpentine channel cooling structure is often adopted in a large amount as a carrier of cooling methods such as convection cooling and film cooling. Can cool off the high temperature blade at the inside continuous arrangement cooling structure of blade through snakelike access structure to guarantee that the blade is in reasonable temperature level. In a bucket cooling design, achieving maximum heat exchange at minimum pressure loss is often the goal sought by cooling designers. However, in the turning area of the serpentine channel cooling structure, due to the low reynolds number effect, the viscous effect of the cooling air is strong, the boundary layer of the cooling air is thick and easy to separate, the cooling air is often unevenly distributed on the cross section of the channel under the action of centrifugal force, and strong secondary vortex flow is formed, so that the rapid loss of the cooling air pressure and the reduction of the heat exchange effect are caused. In the prior art, the pressure loss is reduced by arranging a flow deflector structure in the area, but the effect is not ideal.
Disclosure of Invention
In view of the above, the main object of the present invention is to provide a turbine blade and a gas turbine including the same, which are intended to at least partially solve at least one of the above technical problems.
In order to achieve the purpose, the scheme of the invention is as follows:
as an aspect of the present invention, there is provided a turbine blade provided with a cooling passage inside; the turbine blade comprises a clapboard and a flow deflector; wherein the content of the first and second substances,
a partition plate disposed in the cooling channel inside the turbine blade for forming the cooling channel into a serpentine channel cooling structure; wherein the cooling channel at the end of the separator is defined as a turn zone;
and the flow deflector is arranged in a turning area in the cooling channel and used for distributing at least three strands of cooling air in the turning area.
As another aspect of the present invention, there is also provided a gas turbine including the turbine blade as described above.
Based on the technical scheme, compared with the prior art, the turbine blade provided by the invention has at least one of the following beneficial effects:
(1) in the turning area close to the blade cooling channel, the cooling air is divided into at least three branches by the flow deflectors, so that the flow state is more reasonable, the generation of secondary flow is reduced, and the flow separation is reduced, thereby effectively reducing the pressure loss;
(2) the distribution of cooling air in the turning area of the cooling channel on the cross section of the cooling channel can be adjusted through the position of the flow deflector, so that the flowing heat exchange is more uniform, and the thermal stress level of the turbine blade can be effectively reduced;
(3) the cooling air in the turning area of the cooling channel is divided into at least three branches, so that the pressure loss is smaller, and the cooling can be carried out by using lower pressure, and the overall thermal efficiency of the gas turbine is improved;
(4) by applying the invention, the rapid change of the wall thickness of the cooling channel is avoided, and the loose defect of the blade in the use process is reduced.
Drawings
FIG. 1 is a perspective view of a turbine rotor blade of a gas turbine engine of an embodiment of the present invention;
FIG. 2 is a schematic cross-sectional view of a turbine rotor blade internal cooling passage of a gas turbine engine according to an embodiment of the present invention;
FIG. 3 is a schematic cross-sectional view A-A of FIG. 2;
FIG. 4 is a perspective view of a turbine stator blade of a gas turbine engine of an embodiment of the present invention;
FIG. 5 is a schematic cross-sectional view of a turbine stator blade internal cooling passage of a gas turbine engine according to an embodiment of the present invention;
FIG. 6 is a schematic cross-sectional view B-B of FIG. 5;
FIG. 7 is an enlarged partial schematic view of region C of FIG. 2 or FIG. 5;
fig. 8 is a partially enlarged view of the region C of the other embodiment of fig. 2 or 5.
In the above drawings, the reference numerals have the following meanings:
1-root cooling channel inlet; 11-blade root; 12-a blade platform; 13-blade body; 14-a vane lower endwall; 15-a vane upper endwall; 20-cooling channel partitions; 21-turn zone entrance; 22-turn zone exit; 23-a first cooling channel; 24-a second cooling channel; 25-a third cooling channel; 30-profile camber line; 31-suction surface; 32-pressure side; 33-blade leading edge; 34-the trailing edge of the blade; 35- "U" type guide vane; 36. 37-guide vanes; 38-end fillets; 41-fin structure; 42-jet through hole.
Detailed Description
According to the turbine blade provided by the invention, under the condition that the total cooling air amount is not increased, the flow of the cooling air in the turning area of the serpentine channel is more accurately controlled, so that the distribution of the cooling air on the cross section of the channel in the area is more reasonable and controllable, the pressure loss of the cooling air in the turning area of the blade cooling channel is reduced, and the overall temperature distribution and the thermal stress level of the blade are improved.
In order that the objects, technical solutions and advantages of the present invention will become more apparent, the present invention will be further described in detail with reference to the accompanying drawings in conjunction with the following specific embodiments.
As an aspect of the present invention, there is provided a turbine blade, an inside of which is provided with a cooling passage; the turbine blade comprises a clapboard and a flow deflector; wherein the content of the first and second substances,
the clapboard is arranged in the cooling channel inside the turbine blade and is used for enabling the cooling channel to form a serpentine channel cooling structure; wherein the cooling channel at the end of the separator is defined as a turn zone;
and the guide vane is arranged in a turning area in the cooling channel and used for distributing at least three strands of cooling air in the turning area.
In an embodiment of the invention, the guide vanes comprise a first guide vane and a second guide vane;
the first flow deflector is of a U-shaped structure and is arranged on the periphery of the tail end of the partition board in the turning area;
the second guide vanes comprise a plurality of first guide vanes which are arranged at intervals on the periphery of the first guide vanes in the turning area.
In an embodiment of the present invention, the first guide vane is a smooth and continuous U-shaped structure.
In an embodiment of the invention, the first guide vane is a discontinuous U-shaped structure of at least 2 segments.
In an embodiment of the present invention, the second guide vanes include 2 guide vanes, and the 2 guide vanes are symmetrically disposed around the partition plate in the turning area.
In the embodiment of the invention, 2 second guide vanes are arranged in a group, and a plurality of groups of the second guide vanes are arranged at the periphery of the first guide vanes in the turning area in a stacking mode at intervals.
In an embodiment of the present invention, the second guide vane has a shape of a circular arc, a triangle, or an airfoil.
In an embodiment of the invention, the ends of the baffle are provided in a rounded configuration.
In embodiments of the present invention, the fillet configuration is circular, elliptical, or other streamlined shape.
As another aspect of the present invention, there is also provided a gas turbine including the turbine blade as described above.
The technical solution of the present invention is further described below with reference to specific examples, but it should be noted that the following examples are only for illustrating the technical solution of the present invention, but the present invention is not limited thereto.
As shown in FIG. 1, a turbine rotor blade includes a blade airfoil 13, a blade root 11, and a blade platform 12 between the blade airfoil 13 and the blade root 11. The internal configuration of the blade may be obtained by cutting the blade along the profile camber line 30, as shown in fig. 2. The blade interior has a plurality of cooling channels for the flow of cooling gas.
There are at least 1 independent serpentine cooling flow paths inside the blade to provide cooling air to the blade, as shown in fig. 2, 3, fig. 3 is a schematic cross-sectional view a-a of fig. 2, including: the cooling air enters from the root cooling channel inlet 1 and sequentially passes through the first cooling channel 23, the second cooling channel 24 and the third cooling channel 25 along the radial direction, the wall surfaces of the cooling channels are provided with fin structures 41 for enhancing heat exchange, and the cooling air is discharged from the tail edge injection through hole 42 after heat exchange.
The turning regions of the first cooling passage 23, the second cooling passage 24, and the third cooling passage 25, as partially enlarged in the region C shown in fig. 7, employ the cooling structure of the present invention. After reaching the inlet 21 of the turning area, the cooling air from the first cooling channel 23 first reaches the inlet of the "U" shaped guide vane 35, which is divided into two sections a1 and a2 by the "U" shaped guide vane 35, wherein the widths of a1 and a2 can be adjusted according to actual needs to ensure that the flow rates into the regions a2 and a1 meet the expected target. The cooling fluid entering the region a2 turns to the turn region outlet 22 and smoothly enters the second cooling passage 24 by the cooperation of the "U" shaped guide plate 35 and the end fillet 38 of the cooling passage partition plate 20. The outlet areas a3 and a4 of the "U" shaped guide vanes 35 are adjustable in width to ensure that the cooling air flow rate at the turn zone outlet 22 meets the desired target.
The cooling air entering the a1 zone reaches the inlet of the guide vane 36, which is divided into two sections b1 and b2 by the guide vane 36, wherein the widths of b1 and b2 can be adjusted according to actual needs to ensure that the flow entering the b2 and b1 regions meets the expected target. The outlet areas b3 and b4 of the guide vanes 36 are adjustable in width to ensure that the cooling air flow rate at the outlet of the guide vanes 36 meets the desired objective.
The cooling air entering the a1 zone enters the guide vane 37 after passing through the guide vane 36, the inlet is divided into two sections c1 and c2 by the guide vane 37, wherein the widths of c1 and c2 can be adjusted according to actual needs to ensure that the flow entering the areas c2 and c1 meets the expected target. The outlet areas c3 and c4 of the guide vanes 37 are adjustable in width to ensure that the cooling air flow rate at the outlet of the guide vanes 37 meets the desired objective.
Figure 4 shows another embodiment of the present invention. As shown in fig. 4, the turbine stator blade includes a blade body 13, a blade lower end wall 14, and a blade upper end wall 15. The internal configuration of the blade may be obtained by cutting the blade along the profile camber line 30, as shown in fig. 5. The blade interior has a plurality of cooling channels for the flow of cooling gas.
There are at least 1 independent serpentine cooling flow paths inside the blade to provide cooling air to the blade, as shown in fig. 5, 6, fig. 6 is a schematic cross-sectional view a-a of fig. 5, including: the cooling air enters from the root cooling channel inlet 1 and sequentially passes through the first cooling channel 23, the second cooling channel 24 and the third cooling channel 25 along the radial direction, the wall surfaces of the cooling channels are provided with fin structures 41 for enhancing heat exchange, and the cooling air is discharged from the tail edge injection through hole 42 after heat exchange.
The turning regions of the first cooling passage 23, the second cooling passage 24, and the third cooling passage 25, as partially enlarged in the region C shown in fig. 7, employ the cooling structure of the present invention. After reaching the inlet 21 of the turning area, the cooling air from the first cooling channel 23 first reaches the inlet of the "U" shaped guide vane 35, which is divided into two sections a1 and a2 by the "U" shaped guide vane 35, wherein the widths of a1 and a2 can be adjusted according to actual needs to ensure that the flow rates into the regions a2 and a1 meet the expected target. The cooling fluid entering the region a2 turns to the turn region outlet 22 and smoothly enters the second cooling passage 24 by the cooperation of the "U" shaped guide plate 35 and the end fillet 38 of the cooling passage partition plate 20. The outlet areas a3 and a4 of the "U" shaped guide vanes 35 are adjustable in width to ensure that the cooling air flow rate at the turn zone outlet 22 meets the desired target.
The cooling air entering the a1 zone reaches the inlet of the guide vane 36, which is divided into two sections b1 and b2 by the guide vane 36, wherein the widths of b1 and b2 can be adjusted according to actual needs to ensure that the flow entering the b2 and b1 regions meets the expected target. The outlet areas b3 and b4 of the guide vanes 36 are adjustable in width to ensure that the cooling air flow rate at the outlet of the guide vanes 36 meets the desired objective.
The cooling air entering the a1 zone enters the guide vane 37 after passing through the guide vane 36, the inlet is divided into two sections c1 and c2 by the guide vane 37, wherein the widths of c1 and c2 can be adjusted according to actual needs to ensure that the flow entering the areas c2 and c1 meets the expected target. The outlet areas c3 and c4 of the guide vanes 37 are adjustable in width to ensure that the cooling air flow rate at the outlet of the guide vanes 37 meets the desired objective.
The turning regions of the first cooling passage 23, the second cooling passage 24 and the third cooling passage 25, which employ at least two guide vanes 36 and at least two guide vanes 37, are another embodiment of the cooling structure of the present invention as shown in the partially enlarged view of the region C in fig. 8.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A turbine blade having a cooling passage provided therein; wherein the turbine blade comprises a diaphragm and a guide vane; wherein the content of the first and second substances,
a partition plate disposed in the cooling channel inside the turbine blade for forming the cooling channel into a serpentine channel cooling structure; wherein the cooling channel at the end of the separator is defined as a turn zone;
and the flow deflector is arranged in a turning area in the cooling channel and used for distributing at least three strands of cooling air in the turning area.
2. The turbine blade of claim 1, wherein the flow fence comprises a first flow fence and a second flow fence;
the first flow deflector is of a U-shaped structure and is arranged on the periphery of the tail end of the partition board in the turning area;
the second flow deflectors comprise a plurality of second flow deflectors which are arranged at intervals on the periphery of the first flow deflectors in the turning area.
3. The turbine blade of claim 2 wherein said first vane is a smooth, continuous U-shaped structure.
4. The turbine blade of claim 2, wherein the first flow deflector is a discontinuous U-shaped structure of at least 2 segments.
5. The turbine blade according to claim 2, wherein the second guide vane includes 2 guide vanes symmetrically disposed around the diaphragm at the periphery of the first guide vane in the turning region.
6. The turbine blade of claim 5 wherein said second vanes, 2 in one set, are provided in multiple sets spaced apart and stacked about the periphery of said first vane in said turning region.
7. The turbine blade of claim 2, wherein the second flow deflector is in the shape of a circular arc, a triangle, or an airfoil.
8. The turbine blade of claim 1 wherein said bulkhead end is provided in a radiused configuration.
9. A turbine blade according to claim 8, wherein said fillet configuration is circular, elliptical or other streamlined shape.
10. A gas turbine comprising a turbine blade according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010734234.4A CN111852574A (en) | 2020-07-27 | 2020-07-27 | Turbine blade and gas turbine comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010734234.4A CN111852574A (en) | 2020-07-27 | 2020-07-27 | Turbine blade and gas turbine comprising same |
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| Publication Number | Publication Date |
|---|---|
| CN111852574A true CN111852574A (en) | 2020-10-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010734234.4A Pending CN111852574A (en) | 2020-07-27 | 2020-07-27 | Turbine blade and gas turbine comprising same |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102668653B1 (en) * | 2021-10-27 | 2024-05-22 | 두산에너빌리티 주식회사 | Airfoil for turbine, turbine including the same |
-
2020
- 2020-07-27 CN CN202010734234.4A patent/CN111852574A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102668653B1 (en) * | 2021-10-27 | 2024-05-22 | 두산에너빌리티 주식회사 | Airfoil for turbine, turbine including the same |
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