CN215633158U - Turbine cooling blade of gas turbine - Google Patents
Turbine cooling blade of gas turbine Download PDFInfo
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- CN215633158U CN215633158U CN202122032810.3U CN202122032810U CN215633158U CN 215633158 U CN215633158 U CN 215633158U CN 202122032810 U CN202122032810 U CN 202122032810U CN 215633158 U CN215633158 U CN 215633158U
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- blade
- ribs
- cooling
- partition plate
- gas turbine
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Abstract
The utility model discloses a gas turbine cooling blade which comprises a blade body, a blade root platform, a cooling cavity, a partition plate channel, a turbulent flow rib inner channel, an airflow outflow structure and the like. The novel cooling structure increases local cooling strengthening of the positions of the partition plates and the turbulence ribs, so that the surface temperature of the blade is more uniform, and the local temperature gradient of the surface of the blade is further reduced.
Description
Technical Field
The utility model relates to a turbine blade of a gas turbine, in particular to a turbine cooling blade of the gas turbine.
Background
The spoiler enhanced heat exchange is to disturb a fully developed boundary layer through a spoiler on a wall surface, so that the thickness of a thermal boundary layer is reduced, and the convective heat exchange coefficient is increased. The turbulent flow rib is the most classical turbulent flow structure in the intensified heat exchange, and the rib spoiler not only increases the effective heat exchange area of the blade cooling channel, but also causes the intensive mixing of fluids in different areas in the channel, and disturbs the development of a boundary layer, thereby improving the heat exchange effect. The fins are arranged in the channel to enhance the heat exchange efficiency, but the flow resistance of the cold air is increased along with the insertion of the fins, and the development of a novel turbulence rib structure with better comprehensive cooling and flowing characteristics has important theoretical research significance and engineering application value.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a cooling blade of a gas turbine, which enables a part of cooling air to flow through the interior of a turbulence rib positioned on a pressure surface and a suction surface by opening an air inlet on the wall of a middle partition plate and establishing a cooling channel in the partition plate and the turbulence rib when the cooling air flow entering from the air inlet at the lower part of a blade root flows through the blade root platform, thereby improving the cooling effect of the turbulence rib and the partition plate.
The method is realized by adopting the following technical scheme:
a gas turbine cooling blade comprises an integrally formed blade body and a blade root platform, wherein an internal cooling cavity is arranged inside the blade body, and is formed by enclosing a pressure surface and a suction surface of the blade body, a front edge and a tail edge, a plurality of front edge air film cooling holes are formed in the front edge, a plurality of tail edge air outlet holes are formed in the tail edge, a top plate is arranged at the top of the blade body, and a plurality of blade top air film cooling holes are formed in the top plate;
the inner surface of the pressure surface of the blade body is connected with the inner surface of the suction surface through a plurality of partition plates arranged at intervals longitudinally, and the first partition plate arranged in the cooling chamber divides the air inlet at the lower part of the blade root platform into a plurality of parts arranged according to the number of the air inlets at the bottom of the blade; other partition plates for limiting the area of the airflow flow channel and the walking path are arranged between the first partition plate and the front edge and the tail edge; the most front side partition plate is provided with impact holes, and airflow enters the most front edge cavity through the impact holes and then enters main flow through the front edge air film cooling holes;
a first partition plate channel for conveying a cooling medium to the front edge direction and a second partition plate channel for conveying the cooling medium to the tail edge are arranged in the first partition plate;
a plurality of turbulence ribs which are arranged in parallel are arranged on the inner surface of the pressure surface and the inner surface of the suction surface of the blade body between two adjacent partition plates and between the rightmost partition plate and the tail edge; the interior of each turbulence rib is of a hollow structure, the channels in the ribs and the partition plate channels are of a communicated structure, and the other partition plates except the first partition plate are provided with third partition plate channels for connecting the channels in the turbulence ribs on the two sides of the partition plate; the air flow in the turbulence ribs enters the front edge cavity through the channel after passing through the last row of turbulence ribs close to the front edge direction, enters the region where the turbulence device is arranged after passing through the last row of turbulence ribs close to the tail edge direction, and then enters the main flow through the tail edge air outlet hole.
A further development of the utility model is that the gas flow enters the first and second separator channels through first and second orifice inlets which enclose an acute angle with the gas flow direction.
The utility model is further improved in that the turbulence ribs are ribs having a set included angle with the flow direction of the airflow, and the included angle ranges from 30 degrees to 45 degrees.
The utility model is further improved in that the spoiler rib is a W-shaped rib.
The utility model is further improved in that the turbulence ribs are V-shaped ribs.
A further improvement of the utility model is that the turbulator ribs are interrupted V-shaped ribs.
The utility model has the further improvement that the turbulence ribs are arranged along the rib height direction according to the die drawing direction, and the fillets are rounded at the connecting parts of the turbulence ribs and the inner wall surface of the blade and are rounded at the tops of the turbulence ribs.
The utility model has the further improvement that when the blade is in operation, after cooling airflow enters from the air inlet at the lower part of the blade root, part of the airflow is conveyed to the top of the blade near the platform height of the blade root through the internal channel of the middle partition plate which is longitudinally arranged, and the airflow is diffused towards the front edge and the tail edge through the internal channel of the turbulence rib which is connected with the internal channel of the turbulence rib, so that the secondary cooling of the partition plate and the vicinity of the turbulence rib is formed.
The utility model has at least the following beneficial technical effects:
according to the gas turbine cooling blade provided by the utility model, the micro cooling channels are arranged in the internal partition plate and the turbulence ribs of the blade, part of cooling air flow can flow through each turbulence rib after entering from the air inlet of the middle partition plate, and finally enters the main flow from the front edge and the tail edge respectively, so that the local cooling enhancement at the positions of the partition plate and the turbulence ribs is increased, the surface temperature of the blade is more uniform, and the local temperature gradient of the surface of the blade is further reduced.
Drawings
FIG. 1 is a longitudinal cross-sectional view of a gas turbine blade of the present invention;
FIG. 2 is a schematic view of the flow of the passages within the gas turbine blade barrier of the present invention;
FIG. 3 is a schematic view of the flow of the last row of turbulator rib cold air outlets of a gas turbine blade of the present invention near the leading edge into the impingement chamber;
FIG. 4a is a schematic view of a turbulator rib arrangement for a gas turbine blade in accordance with the present invention, the turbulator rib being a discontinuous V-shaped rib;
FIG. 4b is a schematic view of a turbulator rib arrangement for a gas turbine blade in accordance with the present invention, the turbulator rib being a V-shaped rib;
FIG. 4c is a schematic view of a turbulator rib arrangement of the gas turbine blade of the present invention, the turbulator rib being a W-shaped rib.
Detailed Description
The utility model is described in further detail below with reference to the attached drawing figures:
as shown in fig. 1, the gas turbine cooling blade provided by the present invention includes an integrally formed blade body 1 and a blade root platform 2, an internal cooling chamber 3 is disposed inside the blade body 1, the cooling chamber 3 is defined by a pressure surface and a suction surface of the blade body 1, a leading edge 4 and a trailing edge 5, a plurality of leading edge air film cooling holes 401 are disposed on the leading edge 4, a plurality of trailing edge air outlet holes 501 are disposed on the trailing edge 5, a top plate 6 is disposed on the top of the blade body 1, and a plurality of blade tip air film cooling holes 601 are disposed on the top plate 6.
The inner surface of the pressure surface of the blade body 1 is connected with the inner surface of the suction surface through a plurality of partition plates arranged at intervals longitudinally, and the first partition plate 7 arranged in the cooling chamber 3 divides the air inlets at the lower part of the blade root platform 2 into a plurality of parts arranged according to the number of the air inlets at the bottom of the blade; other partition plates for limiting the airflow channel area and the walking path are arranged between the first partition plate 7 and the front edge 4 and the tail edge 5; the most front side partition plate is provided with impact holes 9, airflow enters a most front edge cavity 10 through the impact holes 9 and then enters main flow through a front edge air film cooling hole 401, a first partition plate channel 701 for conveying cooling media to the front edge direction and a second partition plate channel 702 for conveying cooling media to the tail edge are arranged in the first partition plate 7, and a plurality of turbulence ribs 8 which are arranged in parallel are arranged on the inner surface of the pressure surface and the inner surface of the suction surface of the blade body 1 between every two adjacent partition plates and between the most right side partition plate and the tail edge 5; the interior of the turbulence rib 8 is of a hollow structure, the channels in the rib and the partition plate channels are of a communicated structure, and the other partition plates except the first partition plate are provided with third partition plate channels 705 for connecting the channels in the turbulence ribs on the two sides of the partition plate; the air flow in the turbulence ribs enters the front edge cavity 10 through the channel 12 after passing through the last row of turbulence ribs in the direction close to the front edge 4, enters the region where the turbulence device 11 is arranged after passing through the last row of turbulence ribs in the direction close to the tail edge 5, and then enters the main flow through the tail edge air outlet 501.
After the blade cooling scheme is adopted, cooling airflow enters from the air inlet at the lower part of the blade root, partial airflow is conveyed to the top of the blade through the internal channel of the middle partition plate longitudinally arranged near the platform height of the blade root, and the partial airflow is diffused towards the front edge and the tail edge through the internal channel of the turbulence rib connected with the internal channel of the turbulence rib, so that the secondary cooling of the partition plate and the vicinity of the turbulence rib is formed.
Preferably, the gas flow enters the first and second baffle passages 701, 702 through first and second hole inlets 703, 704 that are at an acute angle to the direction of gas flow.
Preferably, the turbulence ribs 8 are fins having an included angle with the flow direction of the air flow, and the included angle ranges from 30 ° to 45 °.
Preferably, the spoiler rib 8 is a W-shaped rib or a V-shaped rib or an interrupted V-shaped rib.
Preferably, the spoiler rib 8 is set up along the rib height direction according to the pattern drawing direction, and is rounded at the connection part with the inner wall surface of the blade, and is rounded at the top of the spoiler rib.
While FIG. 1 is merely one form of internal structure that may be designed without departing from the intent of the present invention, other types of internal structures are possible, and there are not limited to only two cooling cavities within the blade, and when other cooling cavities are present, there are also baffle inner channel inlets located at the inlet channel of each cooling cavity near the platform height to deliver baffle channel airflow up to each adjacent turbulator rib. The turbulator ribs may also have variations in shape, of which fig. 4a, 4b and 4c are only three.
When introducing elements of various embodiments of the present invention, the articles "a," "an," "the," and "said" are intended to mean that there are one or more of the elements, that "include," "include," and "have" are intended to be inclusive, and that there may be additional elements other than the listed elements.
The embodiments of the present invention are only intended to be limited by the embodiments of the present invention, and other equivalent modifications can be made within the scope of the present invention.
Claims (8)
1. A gas turbine cooling blade is characterized by comprising an integrally formed blade body (1) and a blade root platform (2), wherein an internal cooling cavity (3) is arranged inside the blade body (1), the cooling cavity (3) is formed by enclosing a pressure surface and a suction surface of the blade body (1), a front edge (4) and a tail edge (5), a plurality of front edge air film cooling holes (401) are formed in the front edge (4), a plurality of tail edge air outlet holes (501) are formed in the tail edge (5), a top plate (6) is arranged at the top of the blade body (1), and a plurality of blade top air film cooling holes (601) are formed in the top plate (6);
the inner surface of the pressure surface of the blade body (1) is connected with the inner surface of the suction surface through a plurality of longitudinally spaced partition plates, and the air inlets at the lower part of the blade root platform (2) are divided into a plurality of parts according to the number of the air inlets at the bottom of the blade by the first partition plate (7) arranged in the cooling chamber (3); other partition plates for limiting the airflow channel area and the walking path are arranged among the first partition plate (7), the front edge (4) and the tail edge (5); the most front side partition plate is provided with impact holes (9), airflow enters a most front edge cavity (10) through the impact holes (9) and then enters main flow through a front edge air film cooling hole (401);
a first separator channel (701) for conveying a cooling medium to the front edge direction and a second separator channel (702) for conveying the cooling medium to the tail edge are arranged in the first separator (7);
a plurality of turbulence ribs (8) which are arranged in parallel are arranged on the inner surface of the pressure surface and the inner surface of the suction surface of the blade body (1) between two adjacent partition plates and between the rightmost partition plate and the tail edge (5); the inner part of each turbulence rib is of a hollow structure, the channels in the ribs and the partition plate channels are of a communicated structure, and the other partition plates except the first partition plate are provided with third partition plate channels (705) used for connecting the channels in the turbulence ribs on the two sides of the partition plate; the air flow in the turbulence ribs enters the front edge cavity (10) through the channel (12) after passing through the last row of turbulence ribs close to the front edge (4) direction, enters the region where the turbulence device (11) is arranged after passing through the last row of turbulence ribs close to the tail edge (5) direction, and then enters the main flow through the tail edge air outlet hole (501).
2. A gas turbine cooling blade according to claim 1, characterised in that the gas flow enters the first (701) and second (702) diaphragm channels through a first (703) and second (704) orifice inlet openings at an acute angle to the gas flow direction.
3. A gas turbine cooling blade according to claim 1, wherein the turbulator ribs (8) are fins having a set angle with the flow direction of the gas stream, the angle being in the range of 30 ° to 45 °.
4. A gas turbine cooling blade according to claim 1, characterised in that the turbulator ribs (8) are W-shaped ribs.
5. Gas turbine cooling blade according to claim 1, wherein the turbulator ribs (8) are V-shaped ribs.
6. A gas turbine cooling blade according to claim 1, characterised in that the turbulator ribs (8) are interrupted V-shaped ribs.
7. The gas turbine cooling blade as claimed in claim 1, wherein the turbulator ribs (8) are set up in the direction of rib height according to the draft direction, and are rounded at the junction with the inner wall surface of the blade, and are rounded at the top of the turbulator ribs.
8. The gas turbine cooling blade of claim 1, wherein during operation, after cooling airflow enters from the inlet at the lower portion of the blade root, a portion of the airflow is delivered to the top of the blade near the platform height of the blade root through the longitudinally disposed internal channels of the intermediate partition, and is diffused toward the leading edge and the trailing edge through the internal channels of the turbulation ribs connected thereto, thereby forming a re-cooling of the partition and the vicinity of the turbulation ribs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122032810.3U CN215633158U (en) | 2021-08-26 | 2021-08-26 | Turbine cooling blade of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122032810.3U CN215633158U (en) | 2021-08-26 | 2021-08-26 | Turbine cooling blade of gas turbine |
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| CN215633158U true CN215633158U (en) | 2022-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202122032810.3U Active CN215633158U (en) | 2021-08-26 | 2021-08-26 | Turbine cooling blade of gas turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114876581A (en) * | 2022-05-12 | 2022-08-09 | 中国航发沈阳发动机研究所 | Turbine blade trailing edge enhanced heat exchange semi-split seam cooling structure |
-
2021
- 2021-08-26 CN CN202122032810.3U patent/CN215633158U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114876581A (en) * | 2022-05-12 | 2022-08-09 | 中国航发沈阳发动机研究所 | Turbine blade trailing edge enhanced heat exchange semi-split seam cooling structure |
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