CN113623010B - Turbine blade - Google Patents
Turbine blade Download PDFInfo
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- CN113623010B CN113623010B CN202110791499.2A CN202110791499A CN113623010B CN 113623010 B CN113623010 B CN 113623010B CN 202110791499 A CN202110791499 A CN 202110791499A CN 113623010 B CN113623010 B CN 113623010B
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- rib
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- ribs
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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
- F01D5/141—Shape, i.e. outer, aerodynamic form
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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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- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a turbine blade which comprises a shell, a first rib component, a second rib component and a plurality of ribs, wherein the shell comprises an outer layer blade and an inner layer blade, the outer layer blade surrounds the outer peripheral side of the inner layer blade, an installation cavity is formed between the outer layer blade and the inner layer blade, the installation cavity comprises a first cavity, a second cavity, a third cavity and a fourth cavity, the shell is provided with a first end and a second end, the first cavity is arranged at the first end of the shell, the fourth cavity is arranged at the second end of the shell, the first rib component and the second rib component both comprise a plurality of rib layers, each rib layer comprises a plurality of ribs which are arranged in parallel at intervals, the extending directions of the ribs of two adjacent rib layers form an included angle, the first rib component is arranged in the second cavity and the fourth cavity, the second rib component is arranged in the third cavity and the fourth cavity, the plurality of ribs are arranged in the first cavity, and the plurality of ribs are arranged in parallel at intervals along the extending direction of the first cavity. The turbine blade has the advantages of simple structure, long service life, high heat dissipation efficiency and the like.
Description
Technical Field
The invention relates to the technical field of cooling of turbine blade laminates, in particular to a turbine blade.
Background
The cooling technology of the hot end part of the aero-engine is one of important bottleneck technologies for restricting the development of the aero-engine industry in China, the temperature of gas at the inlet of a turbine is far higher than the temperature resistance limit of materials used by the turbine blade, and effective cooling measures must be used for protecting the turbine blade so as to prevent the turbine blade from being corroded and damaged by high temperature.
In the related technology, the cooling structure of the cooling channel with the turbulence column is mainly adopted for cooling the interior of the turbine blade, the heat exchange area of the cooling structure of the cooling channel of the turbulence column is small, the turbulence degree is not high, and the convective heat transfer coefficient is small.
Disclosure of Invention
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art.
Therefore, the embodiment of the invention provides the turbine blade which is simple in structure, large in heat exchange area and high in turbulence.
A turbine blade according to an embodiment of the present invention is characterized by comprising: the shell comprises an outer-layer blade and an inner-layer blade, the outer-layer blade surrounds the outer peripheral side of the inner-layer blade, an installation cavity is formed between the outer-layer blade and the inner-layer blade, the installation cavity comprises a first cavity, a second cavity, a third cavity and a fourth cavity, the shell is provided with a first end and a second end, the first cavity is arranged at the first end of the shell, the fourth cavity is arranged at the second end of the shell, the third cavity and the fourth cavity are oppositely arranged, the second cavity is arranged between the first cavity and the fourth cavity, and the third cavity is arranged between the first cavity and the fourth cavity; the first rib group and the second rib group respectively comprise a plurality of rib layers, each rib layer comprises a plurality of ribs which are arranged in parallel at intervals, the extending directions of the ribs of two adjacent rib layers form an included angle, the first rib group is arranged in the second cavity and the fourth cavity, and the second rib group is arranged in the third cavity and the fourth cavity; the fins are arranged in the first cavity and are arranged in parallel at intervals along the extending direction of the first cavity.
According to the turbine blade provided by the embodiment of the invention, through the arrangement of the first rib component, the second rib component and the plurality of ribs, the heat exchange area is increased, the turbulence degree of airflow is enhanced, and the heat exchange effect in the blade is obviously enhanced, so that the heat dissipation efficiency of the turbine blade is improved, and the service life of the turbine blade is prolonged.
In some embodiments, the rib layers of the first rib assembly and the rib layers of the second rib assembly are stacked within the fourth cavity.
In some embodiments, the multi-layer rib layer comprises: first rib layer, first rib layer is including a plurality of first ribs, and is a plurality of first rib is established the interior circumferencial side of inlayer blade, and is a plurality of first rib is followed the circumference interval of inlayer blade sets up, second rib layer is including a plurality of second ribs, and is a plurality of the second rib is established the interior circumferencial side of outer blade, and is a plurality of the second rib is followed the circumference interval of outer blade sets up.
In some embodiments, the angle between the direction of extension of the first rib and the direction of extension of the second rib is 90 °.
In some embodiments, the extending direction of the first rib intersects with one end of the inner blade at a point a, and the included angle between the extending direction of the first rib and the tangent of the point a of the inner blade is 45 °.
In some embodiments, the rib cross-sectional shape of each of the rib layers is rectangular.
In some embodiments, the ribs of adjacent two of the rib layers are of equal thickness.
In some embodiments, the spacing between two adjacent ribs in the rib layer is 4mm to 4.1mm.
In some embodiments, the cross-sectional shape of the rib is rectangular, and the rib extends in the height direction of the housing.
In some embodiments, the turbine blade further comprises a concave vortex generator and a circumferential flow post, the concave vortex generator and circumferential flow post disposed within the first cavity.
Drawings
FIG. 1 is a schematic structural view of a turbine blade according to an embodiment of the present invention.
FIG. 2 is a top view of a turbine blade of an embodiment of the present invention.
FIG. 3 is a schematic structural view of a first rib assembly and an inner blade with the outer blade removed according to an embodiment of the present invention.
FIG. 4 is a schematic structural view of a second rib assembly and an inner blade with the outer blade removed according to an embodiment of the present invention.
FIG. 5 is an elevation view of a second rib assembly and an inner blade with the outer blade removed according to an embodiment of the present invention.
Reference numerals are as follows:
a turbine blade 100;
a housing 1; an outer blade 11; the inner blade 12; a cooling chamber 121; a blade leading edge 13; a first cavity 131; a pressure side wall 14; a second chamber 141; a suction sidewall 15; a third chamber 151; the blade trailing edge 16; a fourth chamber 161; a first rib assembly 2; a second rib member 3; a rib 4; a rib layer 5; a first rib layer 51; the first rib 511; a second rib layer 52; and a second rib 521.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
A turbine blade according to an embodiment of the present invention is described below with reference to fig. 1-4.
As shown in fig. 1 to 4, a turbine blade according to an embodiment of the present invention includes a housing 1, a first rib assembly 2, a second rib assembly 3, and a plurality of ribs 4.
The casing 1 includes outer blade 11 and inner blade 12, outer blade 11 encircles the periphery side at inner blade 12, and form the installation cavity between outer blade 11 and the inner blade 12, the installation cavity includes first chamber 131, second chamber 141, third chamber 151 and fourth chamber 161, casing 1 has first end and second end, first chamber 131 establishes the first end (the left end as shown in fig. 1) at casing 1, fourth chamber 161 establishes the second end (the right end as shown in fig. 1) at casing 1, third chamber 151 and fourth chamber 161 are arranged relatively, and second chamber 141 establishes between first chamber 131 and fourth chamber 161, third chamber 151 establishes between first chamber 131 and fourth chamber 161.
Specifically, as shown in fig. 1, each of the outer blade 11 and the inner blade 12 includes a pressure sidewall 14, a blade leading edge 13, a suction sidewall 15, and a blade trailing edge 16, which are connected in sequence. In operation, the casing 1 is subjected to a relatively high fluid pressure, referred to as the pressure side wall 14, and a relatively low fluid pressure, referred to as the suction side wall 15, the pressure side wall 14 being curved concave towards the suction side wall 15, the suction side wall 15 being curved convex away from the pressure side wall 14, and the first chamber 131 being located in the blade leading edge 13, the second chamber 141 being located in the pressure side wall 14, the third chamber 151 being located in the suction side wall 15, and the fourth chamber 161 being located in the blade trailing edge 16.
Specifically, a plurality of ribs are arranged in parallel at intervals to form first cooling channels, the first cooling channels between two adjacent rib layers 5 form staggered cooling channels, the ribs of the two adjacent rib layers 5 are closely connected and do not interfere with each other, and the size and the number of the ribs of the rib layers 5 are flexibly changed according to the size of the turbine blade 100.
A plurality of ribs 4 are provided in the first chamber 131, and the plurality of ribs 4 are arranged in parallel at intervals along the extending direction of the first chamber 131. Specifically, the plurality of fins 4 are disposed in the first cavity 131, and the plurality of fins 4 are disposed at intervals along the inner circumferential surface of the first cavity 131, and two adjacent fins 4 form a second cooling channel, so that the cooling air can pass through the second cooling channel to cool the blade leading edge 13.
According to the turbine blade 100 of the embodiment of the invention, through the arrangement of the first rib assembly 2 and the second rib 521, the traditional turbulent flow column is replaced by the plurality of rib layers 5, and the staggered cooling channels are formed in the cavities of the pressure side wall 14, the suction side wall 15 and the blade tail edge 16, so that when cooling airflow flows into the staggered cooling channels, the cooling airflow between two adjacent rib layers 5 has certain mixing, converging and diverging conditions, the heat exchange area is greatly increased, the flow channel area is smaller, the flow speed in the channels is accelerated, the turbulence degree is increased, and the convective heat exchange of the inner surfaces of the pressure side wall 14 and the suction side wall 15 of the blade is obviously enhanced.
According to the turbine blade 100 of the embodiment of the present invention, the plurality of ribs 4 are arranged in parallel and at intervals along the extending direction of the first cavity 131, the cooling air flow from the first rib assembly 2 and the second rib assembly 3 will impinge on the position of the blade leading edge 13 and the blade trailing edge 16, the cooling air flow is mixed with the air flow in the plurality of ribs 4, the flow turbulence is enhanced, and thus the cooling effect on the blade leading edge 13 is enhanced, and in addition, when the cooling air flow from the first rib assembly 2 and the second rib assembly 3 impinges on the two outermost ribs 4 of the plurality of ribs 4, the cooling air flow is turned back and returned to the first rib assembly 2 or the second rib assembly 3, the flow turbulence of the first rib assembly 2 and the second rib assembly 3 is further enhanced, and the cooling efficiency of the pressure side wall 14 and the suction side wall 15 is enhanced.
It is understood that the rib 4 in the first cavity 131 in the blade leading edge 13 of the turbine blade 100 may be replaced by the first rib member 2 or the second rib member 3, and the outer peripheral surface of the inner blade 12 defines the cooling cavity 121, whereby the cooling cavity 121 not only facilitates the passage of the cooling air flow, thereby improving the cooling efficiency of the turbine blade 100, but also saves the material of the turbine blade 100.
In some embodiments, each rib layer 5 of the first rib assembly 2 and each rib layer 5 of the second rib assembly 3 are stacked within the fourth cavity 161. Specifically, as shown in FIGS. 1-4, the cross-section of the ribs of the first rib 4 assembly and the cross-section of the ribs of the second rib assembly 3 within the fourth cavity 161 gradually decrease from left to right such that the first rib assembly 2 and the second rib assembly 3 conform to the blade trailing edge 16 shape such that the first rib assembly 2 and the second rib assembly 3 may meet at the trailing edge location. Therefore, the flow turbulence degree at the position of the blade tail edge 16 is stronger, the heat exchange of the high-temperature area of the blade tail edge 16 is enhanced, and the structure of the blade tail edge 16 is more stable.
In some embodiments, the multi-layer rib layer 5 includes a first rib layer 51 and a second rib layer 52.
The first rib layer 51 includes a plurality of first ribs 511, the plurality of first ribs 511 are provided on the inner circumferential side of the inner blade 12, and the plurality of first ribs 511 are provided at intervals in the circumferential direction of the inner blade 12, the second rib layer 52 includes a plurality of second ribs 521, the plurality of second ribs 521 are provided on the inner circumferential side of the outer blade 11, and the plurality of second ribs 521 are provided at intervals in the circumferential direction of the outer blade 11.
Specifically, as shown in fig. 3 to 4, a first rib layer 51 is provided on an inner circumferential surface of the inner blade 12, the first rib layer 51 includes a plurality of first ribs 511, the plurality of first ribs 511 are provided at intervals in a circumferential direction of the inner blade 12, a second rib layer 52 is provided on an inner circumferential surface of the outer blade 11, the second rib layer 52 includes a plurality of second ribs 521, the plurality of second ribs 521 are provided at intervals in a circumferential direction of the outer blade 11, the outer blade 11 and the inner blade 12 are connected by the first rib layer 51 and the second rib layer 52, the first rib layer 51 and the second rib layer 52 both play a supporting role and also form staggered first cooling channels to enhance heat exchange, and when a cooling air flow flows in the staggered channels, the cooling air flows between the first rib layer 51 and the second rib layer 52 have a certain mixing, converging and diverging situations, thereby enhancing the heat dissipation capability of the turbine blade 100.
In some embodiments, the angle between the direction of extension of the first rib 511 and the direction of extension of the second rib 521 is 90 °. Specifically, as shown in fig. 3 to 4, the ribs of the first rib layer 51 and the ribs of the second rib layer 52 are arranged alternately, and the ribs of the first rib layer 51 and the ribs of the second rib layer 52 are arranged perpendicular to each other. Therefore, the first rib layer 51 and the second rib layer 52 are provided with the staggered and vertical first cooling channels, so that the cooling air flows in the first cooling channels in a staggered and rapid mode, and the cooling efficiency is improved.
In some embodiments, the extending direction of the first rib 511 intersects with one end of the inner blade 12 at the point a, and the angle between the extending direction of the first rib 511 and the tangent of the point a of the inner blade 12 is 45 °. Specifically, as shown in fig. 5, the upper end of the first rib 511 intersects with the upper end surface of the inner blade 12 at a point a, and the included angle between the tangent line passing through the point a and the first rib 511 is 45 °. That is to say, in the projection plane of the inner blade 12, the included angle between the first rib 511 and the up-down direction is substantially 45 °, and the included angle between the second rib 521 and the up-down direction is substantially 45 ° in reverse.
In some embodiments, the rib cross-sectional shape of each rib layer 5 is rectangular. Specifically, the rib cross-sectional shape is rectangular, thereby facilitating the fixing of the multilayer rib layer 5 between the inner blade 12 and the outer blade 11, and also improving the stability of the multilayer rib layer 5, thereby improving the service life of the turbine blade 100.
In some embodiments, the width of the rib section is 1mm, and the length of the rib is set on the inner blade 12 according to the shape of the blade and the arrangement of the ribs, wherein the shortest rib length is controlled to be 10.0-10.1mm, and the longest rib length is controlled by the overall size of the blade, thereby making the rib setting more reasonable.
In some embodiments, the ribs of two adjacent rib layers 5 are of equal thickness. Specifically, the thicknesses of the first rib 511 and the second rib 521 are equal, and the thicknesses of the first rib 511 and the second rib 521 are both half of the thickness of the mounting cavity. Thereby, the first rib 511 and the second rib 521 are arranged between the outer blade 11 and the inner blade 12.
In some embodiments, the spacing between two adjacent ribs in the rib layer 5 is 4mm to 4.1mm. Therefore, the airflow channel formed by two adjacent ribs in the rib layer 5 is 4mm-4.1mm, the flow speed of cooling airflow cannot be ensured due to the overlarge airflow channel, and the installation and the manufacture are troublesome due to the undersize airflow channel.
In some embodiments, the cross-sectional shape of the rib 4 is rectangular, and the rib 4 extends in the height direction (up and down direction as shown in fig. 1) of the housing 1. Specifically, the fins 4 are straight plates, and the cross-sectional shapes of the fins 4 are rectangular, so that the fins 4 are conveniently mounted and fixed on the outer-layer blades 11 and the inner-layer blades 12, and the fins 4 also provide support for the outer-layer blades 11 and the inner-layer blades 12, so that the connection of the turbine blade 100 is more stable, and the fins 4 extend along the height direction of the shell 1, namely the fins 4 do not interfere with the flow direction of cooling air, so that the heat exchange effect of the blade front edge 13 is ensured.
It can be understood that: the number of the fins 4 may be designed to be matched according to the size of the turbine blade 100 and the working environment.
In some embodiments, the turbine blade 100 further includes a concave vortex generator (not shown) and a circumferential flow column (not shown) disposed within the first cavity 131. Specifically, the recessed vortex generators and the streaming pillars are provided between two adjacent fins 4, thereby improving the heat dissipation capability of the blade leading edge 13 and improving the heat dissipation effect of the blade leading edge 13.
When the turbine blade 100 according to the embodiment of the present invention is used, the specific cooling process of the turbine blade 100 is as follows:
during the use of the turbine blade 100, the turbine blade 100 is surrounded by an external hot gas stream, and the compressor supplies the turbine blade 100 with a cooling gas flow, which enters the mounting cavity from the lower inlet of the mounting cavity, and flows in the mounting cavity from top to bottom, and the cooling gas flow is divided into three parts and flows out of the mounting cavity, taking the flow of the cooling gas flow in the fins 4 and the first rib assembly 2 as an example.
The first part of the cooling air flow flows directly from the second cooling channel formed by the fins 4, from bottom to top, out of the first cavity 131 of the turbine blade 100.
The second portion of the cooling gas enters the second cavity 141 from the first cooling channel between the first rib assemblies 2, a part of the second portion of the cooling gas is merged into the first portion of the cooling gas flow in the leading edge 13 of the blade and then flows out of the blade directly, and another part of the second portion of the cooling gas flows into the adjacent first cooling channel of the first rib assembly 2 and then flows out of the second cavity 141.
A third portion of the cooling gas enters the third chamber 151 from the channels between the second rib assemblies 3, a portion of the third portion of the cooling gas merges into the first portion of the cooling gas flow in the leading edge 13 of the blade and flows directly out of the blade, and another portion of the third portion of the cooling gas flows into the adjacent first cooling channel of the second rib assembly 3 and then flows out of the second chamber 141 and then flows out of the third chamber 151.
The flows of the second part of cooling air flow and the third part of cooling air flow in the second cavity 141 and the third cavity 151 are complicated, mixing, converging or splitting is performed between all the cooling air flows, the air flows between two adjacent rib layers 5 are mixed between the ribs, and the specific flows are related to the flow velocity of the cooling air flow and other factors. These mixing, merging and splitting conditions all enhance the turbulence of the cooling air flow, and the narrow passages of the two adjacent rib layers 5 also increase the flow velocity of the cooling air flow.
In summary, compared with the turbine blade 100 of the conventional laminated plate cooling structure only suitable for the enhanced heat exchange of the spoiler column, the turbine blade 100 of the embodiment of the present invention has a higher convective heat exchange coefficient and a better cooling effect of the turbine blade 100.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, but are not intended to indicate or imply that the device or element so referred to must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and are not to be construed as limiting the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise explicitly stated or limited, the terms "mounted," "connected," "fixed," and the like are to be construed broadly, e.g., as being permanently connected, detachably connected, or integral; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "above," and "over" a second feature may be directly on or obliquely above the second feature, or simply mean that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (6)
1. A turbine blade, comprising:
the shell comprises an outer-layer blade and an inner-layer blade, the outer-layer blade surrounds the outer peripheral side of the inner-layer blade, an installation cavity is formed between the outer-layer blade and the inner-layer blade, the installation cavity comprises a first cavity, a second cavity, a third cavity and a fourth cavity, the shell is provided with a first end and a second end, the first cavity is arranged at the first end of the shell, the fourth cavity is arranged at the second end of the shell, the third cavity and the fourth cavity are oppositely arranged, the second cavity is arranged between the first cavity and the fourth cavity, and the third cavity is arranged between the first cavity and the fourth cavity; cooling air flow enters the installation cavity from an inlet below the installation cavity, and the cooling air flow flows in the installation cavity from bottom to top;
the first rib group and the second rib group respectively comprise a plurality of rib layers, each rib layer comprises a plurality of ribs which are arranged in parallel at intervals, the extending directions of the ribs of two adjacent rib layers form an included angle, the first rib group is arranged in the second cavity and the fourth cavity, and the second rib group is arranged in the third cavity and the fourth cavity;
the fins are arranged in the first cavity and are arranged in parallel at intervals along the extending direction of the first cavity;
each rib layer of the first rib assembly and each rib layer of the second rib assembly are arranged in an overlapping manner in the fourth cavity;
the multi-layer rib layer includes: the first rib layer comprises a plurality of first ribs, the first ribs are arranged on the inner peripheral side of the inner-layer blades and are arranged along the circumferential interval of the inner-layer blades, the second rib layer comprises a plurality of second ribs, the second ribs are arranged on the inner peripheral side of the outer-layer blades and are arranged along the circumferential interval of the outer-layer blades;
the extending direction of first rib with the extending direction's of second rib contained angle is 90, the extending direction of first rib with the one end of inlayer blade is handed over in point A, the extending direction of first rib with contained angle between the radial tangent line of inlayer blade point A is 45.
2. The turbine blade of claim 1, wherein a rib cross-sectional shape of each of said rib layers is rectangular.
3. The turbine blade as in any one of claims 1-2, wherein the ribs of adjacent two of said rib layers are of equal thickness.
4. The turbine blade as in any one of claims 1-2, wherein a spacing between adjacent two of said ribs in said rib layer is 4mm-4.1mm.
5. The turbine blade as in any one of claims 1-2, wherein the cross-sectional shape of the rib is rectangular and the rib extends along the height of the housing.
6. The turbine blade of any one of claims 1-2, further comprising a trapped vortex generator and a bypass flow column, said trapped vortex generator and bypass flow column being disposed within said first cavity.
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| CN202110791499.2A CN113623010B (en) | 2021-07-13 | 2021-07-13 | Turbine blade |
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| CN202110791499.2A CN113623010B (en) | 2021-07-13 | 2021-07-13 | Turbine blade |
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| CN113623010B true CN113623010B (en) | 2022-11-29 |
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| CN114991878B (en) * | 2022-05-30 | 2023-07-07 | 哈尔滨工业大学 | Turbine pressure side half split joint cooling seal beard tail edge blade and forming method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2378073A1 (en) * | 2010-04-14 | 2011-10-19 | Siemens Aktiengesellschaft | Blade or vane for a turbomachine |
| US8070441B1 (en) * | 2007-07-20 | 2011-12-06 | Florida Turbine Technologies, Inc. | Turbine airfoil with trailing edge cooling channels |
| WO2012036850A1 (en) * | 2010-09-17 | 2012-03-22 | Siemens Energy, Inc. | Turbine component cooling channel mesh with intersection chambers |
| CN104791020A (en) * | 2015-04-23 | 2015-07-22 | 华能国际电力股份有限公司 | Gas turbine blade with longitudinal crossed rib cooling structure |
| CN109026173A (en) * | 2018-10-18 | 2018-12-18 | 哈尔滨电气股份有限公司 | A kind of cooling structure of the combustion engine second level movable vane suitable for 20-30MW grade |
| CN111577397A (en) * | 2020-05-28 | 2020-08-25 | 中国航发湖南动力机械研究所 | Turbine blade and aircraft engine |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1000225B1 (en) * | 1997-07-29 | 2002-06-05 | Siemens Aktiengesellschaft | Turbine blade and a method for the production thereof |
| CN101158292A (en) * | 2007-07-13 | 2008-04-09 | 北京航空航天大学 | Ladder type interleaving rib cooling blade suitable for gas-turbine unit |
| CN100557199C (en) * | 2007-07-13 | 2009-11-04 | 北京航空航天大学 | A kind ofly be applicable to the gradually wide type slot staggered rib passage in the cold parts in the turbine blade etc. |
| US9133716B2 (en) * | 2013-12-02 | 2015-09-15 | Siemens Energy, Inc. | Turbine endwall with micro-circuit cooling |
| CN105649681A (en) * | 2015-12-30 | 2016-06-08 | 中国航空工业集团公司沈阳发动机设计研究所 | Crossed rib of guide blade of gas turbine |
| JP6906332B2 (en) * | 2017-03-10 | 2021-07-21 | 川崎重工業株式会社 | Turbine blade cooling structure |
| JP6860383B2 (en) * | 2017-03-10 | 2021-04-14 | 川崎重工業株式会社 | Turbine blade cooling structure |
| JP2018150828A (en) * | 2017-03-10 | 2018-09-27 | 川崎重工業株式会社 | Cooling structure for turbine blade |
| KR102038513B1 (en) * | 2018-04-24 | 2019-10-31 | 한국중부발전(주) | Structure of partion in the matrix cooling channel to increase the thermal performance of internal passage of turbine blade |
| CN109812301A (en) * | 2019-03-06 | 2019-05-28 | 上海交通大学 | A kind of turbo blade double wall cooling structure with horizontal communication hole |
| KR102160298B1 (en) * | 2019-04-01 | 2020-09-25 | 연세대학교 산학협력단 | Impinging jets in the matrix cooling channel of turbine blade to enhance thermal performance |
| JP2021050688A (en) * | 2019-09-26 | 2021-04-01 | 川崎重工業株式会社 | Turbine blade |
| US11268392B2 (en) * | 2019-10-28 | 2022-03-08 | Rolls-Royce Plc | Turbine vane assembly incorporating ceramic matrix composite materials and cooling |
| CN112576316B (en) * | 2020-11-16 | 2023-02-21 | 哈尔滨工业大学 | Turbine blade |
-
2021
- 2021-07-13 CN CN202110791499.2A patent/CN113623010B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8070441B1 (en) * | 2007-07-20 | 2011-12-06 | Florida Turbine Technologies, Inc. | Turbine airfoil with trailing edge cooling channels |
| EP2378073A1 (en) * | 2010-04-14 | 2011-10-19 | Siemens Aktiengesellschaft | Blade or vane for a turbomachine |
| WO2012036850A1 (en) * | 2010-09-17 | 2012-03-22 | Siemens Energy, Inc. | Turbine component cooling channel mesh with intersection chambers |
| CN104791020A (en) * | 2015-04-23 | 2015-07-22 | 华能国际电力股份有限公司 | Gas turbine blade with longitudinal crossed rib cooling structure |
| CN109026173A (en) * | 2018-10-18 | 2018-12-18 | 哈尔滨电气股份有限公司 | A kind of cooling structure of the combustion engine second level movable vane suitable for 20-30MW grade |
| CN111577397A (en) * | 2020-05-28 | 2020-08-25 | 中国航发湖南动力机械研究所 | Turbine blade and aircraft engine |
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