CN112145234B - Omega type gyration chamber plywood cooling structure - Google Patents
Omega type gyration chamber plywood cooling structure Download PDFInfo
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- CN112145234B CN112145234B CN202011014722.4A CN202011014722A CN112145234B CN 112145234 B CN112145234 B CN 112145234B CN 202011014722 A CN202011014722 A CN 202011014722A CN 112145234 B CN112145234 B CN 112145234B
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- 238000001816 cooling Methods 0.000 title claims abstract description 56
- 239000011120 plywood Substances 0.000 title description 8
- 238000005452 bending Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 13
- 239000007789 gas Substances 0.000 description 19
- 239000000112 cooling gas Substances 0.000 description 8
- 238000013461 design Methods 0.000 description 7
- 230000001965 increasing effect Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000004088 simulation Methods 0.000 description 4
- 230000001154 acute effect Effects 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 230000035900 sweating Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 238000004378 air conditioning Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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Classifications
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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
- F01D5/186—Film cooling
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to the technical field of cooling of aero-engines and gas turbine turbines, and relates to a omega-shaped rotary cavity layer plate cooling structure. The cooling structure is composed of a plurality of unit bodies with the same shape, and the structural elements of each unit body comprise an air inlet hole positioned on the air inlet plate, an air film hole positioned on the air outlet plate, a turbulence column and an omega-shaped rotary cavity. The omega-shaped rotary cavity can be divided into an air inlet cavity and an air outlet cavity, flow disturbing columns are respectively arranged at the respective centers, and the shape of each flow disturbing column is consistent with the outline shape of the cavity. The center of the air inlet cavity and the center of the air outlet cavity of the omega-shaped rotary cavity are respectively provided with a turbulence column, the two cavities are communicated as smooth as possible through a section of v-shaped channel, and the cooling channel is in an approximate omega shape in overlooking. The invention reduces the air flow resistance and loss, enhances the blade cooling effect, further improves the load resistance of the turbine blade, and improves the space utilization rate compared with the quadrilateral array arrangement of the prior laminate structure.
Description
Technical Field
The invention belongs to the technical field of cooling of aero-engines and gas turbine turbines, and relates to a omega-shaped rotary cavity layer plate cooling structure.
Background
In order to increase the performance level of aircraft engines, the turbine inlet temperature is constantly increasing, with a consequent progressive deterioration of the operating environment of the hot-end components of the turbine. These turbine components operating in high temperature environments are subjected to high temperature thermal loads, as well as loads caused by high rotational speeds, high pressures, large vibrations, and the like. In such a harsh operating environment, one effective measure is to ensure the normal, reliable and long-term operation of the turbine. The principle of cooling is to use the least amount of cold air to carry away as much heat as possible, to protect the components at a lower average temperature, and to have a smaller temperature gradient. The laminated plate cooling structure organically couples heat conduction, convection cooling, impact cooling, air film cooling and the like together, approaches to porous medium sweating type cooling in the heat exchange effect due to abundant inner cavity turbulence and pore structures, avoids the defect that the sweating type cooling is easy to block, can adapt to the cooling requirements of the prior aeroengine and gas turbine on hot end components, and has wide application prospect.
For a laminate cooling structure, the design of a turbulence column and a cavity of an inner cavity of the laminate cooling structure is a main characteristic for distinguishing different types of laminates and is also a main factor for influencing the flowing and heat exchange performance of the laminates. The invention provides a laminate structure with an inner cavity cooling channel rotating in an omega shape. This structure can avoid the mutual impact between the inside air current of plywood, mixing, avoids appearing backward flow, series flow scheduling problem simultaneously to reduce flow resistance and flow loss, still can synthesize reinforcing plywood heat transfer ability and anti load capacity through extension air conditioning flow distance in addition, and improve plywood inner space utilization.
Disclosure of Invention
In order to solve the problems, the invention provides a laminated plate structure suitable for cooling hot end parts of aero-engines and gas turbines, which is typically applied to a new generation of high-performance turbine blades and contributes to improving the performance and reliability of the whole turbine.
The technical scheme of the invention is as follows:
the utility model provides a omega type gyration chamber plywood cooling structure, comprises a plurality of unit bodies that the shape is the same, and the constitutional element of every unit body includes the inlet port that is located the air inlet plate, is located the air film hole of air outlet plate, vortex post and is omega type gyration chamber. The omega-shaped rotary cavity can be divided into an air inlet cavity and an air outlet cavity, flow disturbing columns are respectively arranged at the respective centers, and the shape of each flow disturbing column is consistent with the outline shape of the cavity. Wherein the shape of the unit body can be approximately considered to be formed by juxtaposing two regular hexagons, squares or circles with the same size.
Take the shape of a unit body as two parallel regular hexagons as an example. The centers of the two regular hexagons, namely the centers of the air inlet cavity and the air outlet cavity of the omega-shaped rotary cavity, are respectively provided with a turbulence column, the two cavities are communicated as smooth as possible through a section of v-shaped channel, and the cooling channel is in an approximate omega shape in overlooking.
Furthermore, the cross section of the cooling channel is elliptical at all positions along the cooling channel.
Further, the ratio of the length of the major axis to the minor axis of the cross-sectional oval shape of the cooling channel may be between 1.2 and 2, where a typical value may be 2.
In each unit body, an air inlet cavity is connected with an air inlet hole, and an air outlet cavity is connected with an air film hole. In the section perpendicular to the surface of the unit body, the central lines of the air inlet hole and the air film hole are in S-shaped curves. The included angle between the tangential direction of the central line of the air inlet hole at the outer surface of the air inlet plate and the plate surface is an incident angle & lt A1, the included angle between the tangential direction of the central line of the air film hole at the outer surface of the air outlet plate and the plate surface is an emergent angle & lt A2, the included angles of & lt A1 and & lt A2 are acute angles, the included angles can be 30-50 degrees, and the typical value can be 30 degrees.
Furthermore, the cross section of the air inlet hole and the air film hole are elliptical, and the air inlet hole and the air film hole are smoothly connected with a channel in the omega-shaped rotary cavity by adopting an arc-shaped slideway.
Furthermore, the central lines of the air inlet hole and the air film hole are respectively composed of two tangent circular arcs, the radiuses of the two circular arcs are respectively R1 and R2, and the bending directions are opposite. The starting end of the circular arc with the radius of R1 is tangent to the central axis of the laminate, and the included angle formed by the tangent line at the intersection point of the circular arc with the radius of R2 and the surface of the air inlet/outlet plate and the plate surface is the air inlet/outlet angle of the hole, namely the air inlet/outlet angle.
The whole laminate can be considered to be formed by a plurality of such unit bodies which are arranged closely according to the periodicity.
The invention has the advantages that:
1. reduction of air flow resistance and losses
Compared with a typical laminated plate structure, the invention has the beneficial effects that the flow resistance and loss of cooling gas are reduced by about 7-11%, and the overall efficiency of the engine is further improved.
As shown in FIG. 2, compared with a typical structure that the units in the laminate are communicated with each other, the units of the present invention are arranged independently from each other, so that the cooling airflows entering from different air inlets are prevented from impacting and mixing in the same unit body, and the situations of backflow, series flow and the like are also avoided, thereby reducing the flow resistance and the flow loss.
From the turning angle when the cooling air enters and exits the cavity, the incident angle A1 of the air inlet hole and the emergent angle A2 of the air film hole are acute angles, and compared with a typical laminate structure, the turning of 90 degrees of the cooling air flow in a narrow channel for multiple times and the turning of about 140 degrees of the partial cooling air flow entering the air outlet hole are avoided, and the flow resistance loss is greatly reduced.
According to the change of the on-way cross section of the cavity, compared with the traditional rectangular cross section, the design of the on-way elliptical cross section of the whole rotary cavity greatly reduces the change of the cold air channel cross section and reduces the flow loss while ensuring the heat exchange area in the channel. In addition, the rotary cavity is smoothly connected with the air inlet and the air film hole, and the cross section area is not obviously changed, so that the phenomena of sudden expansion and throttling cannot occur in the process of air flow flowing in the laminate, the energy loss caused by the flowing is reduced, and the resistance of the laminate is small.
2. Enhancing blade cooling effect
Compared with a typical laminated plate structure, the cooling gas consumption is reduced by about 15% in order to achieve the same cooling effect.
As shown in figure 3, the S-shaped gas film hole can reduce the included angle between the outflow of the gas film and the plate surface in the limited space, so that the cooling gas adherence effect is better, the gas film hole with the approximate elliptical cross section has a better gas film covering effect on the gas plate compared with the traditional circular gas film hole, and the gas film cooling effect is enhanced.
Different with the porous complete UNICOM structure of typical plywood, relatively independent gyration chamber design makes cooling air flow can flow longer route in the plywood, and especially the design of two vortex columns makes flow path more single vortex column design increase about 50%, lets the cooling gas obtain more abundant utilization, improves the heat transfer effect.
Compared with a typical laminate, the design of the omega-shaped rotary cavity enables cooling air to realize accelerated heat exchange by utilizing the rotation of the cavity, and airflow generates oscillation inside the cavity to damage a boundary layer and improve the cooling effect. By taking the regular hexagon omega-shaped rotary cavity as an example, the design also enables cooling airflow to form 13 times of impact on the wall surface, and the impact is increased by more than 1 time compared with the omega-shaped rotary structure, so that the disturbance is enhanced, and the cooling effect is improved.
After the unit bodies are periodically arranged, a partition wall structure is formed between the adjacent unit bodies, as shown in fig. 4, the heat exchange strengthening function of the middle turbulent flow column structure can be effectively supplemented, so that the heat conduction area between the cold and hot walls and the heat exchange area of the inner cavity are increased.
3. Increasing the load resistance of a turbine blade
The turbine blades are subjected in operation mainly to the following loads: centrifugal loads caused by high-speed rotation, aerodynamic loads exerted by the gas flow, vibratory loads due to vibrations, which exert a tendency to deform in tension, torsion and bending on the blade base body and to generate corresponding stresses, and thermal stresses due to thermal expansion non-uniformities. These stresses couple together and beyond the limits that the material can withstand, damage can occur. The periodic arrangement mode of the unit bodies enables a reticular supporting rib structure to be formed in the laminate, in addition, the double-turbulence-column omega-shaped rotary cavity enables the supporting ribs and the turbulence columns to be connected more tightly, referring to fig. 4, compared with the original condition that the inlet/outlet air plates (similar to point support) are connected by the turbulence columns to bear load, the integral bending resistance and torsion load resistance of the structure are improved in all directions, the amplitude reaches more than 18%, and the integral safety and reliability of the engine are improved.
4. Optimized laminate layout structure
The unit bodies are designed to be periodically and tightly arranged, as shown in fig. 5, so that the space utilization rate is improved compared with the quadrilateral array arrangement of the existing laminate structure, and the number of structural elements in unit area can be increased by about 15%.
Drawings
FIG. 1 is a schematic diagram of a layer plate structure of an omega-type rotation cavity.
FIG. 2(a) is a three-dimensional numerical simulation result diagram of the flow of cooling gas in the interior of a conventional laminate.
FIG. 2(b) is a diagram of a three-dimensional numerical simulation result of cooling gas flow in an inner cavity of a laminate of an omega-shaped rotary cavity.
FIG. 3 is a comparison graph of the air film covering effect of the air outlet holes of the conventional laminate and the laminate of the omega-shaped rotary cavity.
FIG. 4 is a graph of deck load schematics and cross-sectional shape comparisons for a conventional deck and an omega-type turning cavity.
FIG. 5 is a diagram comparing the arrangement of the conventional layer plate and the omega-type rotary cavity layer plate units.
FIG. 6 is a schematic diagram of a layer plate structure of an omega-type rotary cavity with different cavity shapes.
In the figure: 1. laminating the board; 2. an air intake plate; 3. an air inlet; 4. the central line of the air inlet hole; 5. incident angle a 1; 6. an air inlet cavity; 7. an air inlet cavity turbulence column; 8. an air outlet cavity; 9. the air outlet cavity is provided with a flow disturbing column; 10. a gas film hole; 11. the center line of the air film hole; 12. an emergence angle < A2; 13. and (7) an air outlet plate.
Detailed Description
In order that the present invention may be more readily and clearly understood, a more particular description of the invention briefly described above will be rendered by reference to specific embodiments that are illustrated in the appended drawings.
Example 1
According to the invention, the comparison research of the flowing state of internal cooling air is carried out on the conventional laminate structure and the laminate inner cavity of the omega-shaped rotary cavity in the invention through three-dimensional numerical simulation, as shown in fig. 2(a) and fig. 2(b), the omega-shaped rotary cavity is smoothly connected with the air inlet hole and the air film hole, the turning angle is small, no obvious sectional area change exists, the phenomena of sudden expansion and throttling and mutual impact interference of air flow can not occur, and the laminate resistance is small due to the oval effect of the section of the comprehensive channel. Meanwhile, the cooling path of the omega-shaped rotary cavity is obviously increased, the exchange of the wall-attached airflow of the cavity and the internal airflow is realized, and the utilization rate of the cooling gas is improved. The structure of the invention is calculated and analyzed through numerical simulation, the flow resistance of the structure is about 10 percent smaller than that of the conventional laminated plate structure, the consumption of cooling gas is reduced by 15 percent, and the conclusion is verified.
Example 2
As shown in FIG. 1, the present invention is a laminate cooling structure suitable for a gas turbine engine, in which a double turbulence column, S-shaped air intake holes 3 and film holes 10, and an omega-shaped rotation cavity structure are main features different from the existing laminate structure. Each rotary cavity is approximate omega-shaped and can be regarded as a relatively independent minimum unit body, two turbulence columns are arranged in each unit body and are respectively an air inlet cavity turbulence column 7 and an air outlet cavity turbulence column 9, and the shapes of the turbulence columns are consistent with those of cavities, such as squares, circles and the like (as shown in figure 6). The cavity structure around the turbulence column in the unit body is tangent and smoothly connected with the air inlet hole 3 and the air film hole 10 and is in a rotary shape on the whole. The air inlet hole 3 on the air inlet plate 2 and the air film hole 10 on the air outlet plate 13 are centrosymmetric, the channel shape of the hole is S-shaped, namely the central line 4 of the air inlet hole and the central line 11 of the air film hole are both S-shaped, and the cross section is oval. The projection of the air inlet center line 4 of the air inlet 3 and the air film hole center line 11 of the air film hole 10 in each unit body in the same horizontal plane is axisymmetric.
The cross section of each part of the cooling channel along the path is elliptical, and the length ratio of the major axis to the minor axis of the ellipse is 2.
The central line 4 of the air inlet hole and the central line 11 of the air film hole are both composed of two sections of tangent arcs, the distance between the tangent points and the surface of the laminate is 0.3 times of the thickness of the laminate, and the ratio of the radius values of the two sections of arcs is 1: 3.15.
the incident angle and the emergent angle of the air inlet hole 3 and the air film hole 10 are both 30 degrees with respect to the horizontal plane, namely angle A1 and angle A2. The whole laminate is formed by a plurality of unit bodies which are arranged closely according to the periodicity.
As shown in fig. 1, the thermal load of the laminate is mainly from the outside of the gas outlet plate 11, which is generally high temperature gas. The cooling air flow enters the inner rotary cavity of the laminate plate from the turning angle of the air inlet hole 3 on the air inlet plate 2 to flow into the air inlet cavity 6 and flow in a rotary mode around the air inlet cavity flow disturbing column 7, then flows into the air outlet cavity 8 and flows in a rotary mode around the air outlet cavity flow disturbing column 9, after the inside and the wall surface perform sufficient heat exchange, flows out from the turning angle of the air film hole 9 on the air outlet plate 13 to be small and is influenced by the outside gas flow, air film covering is formed on the air outlet plate 13, direct heating of the laminate plate by the gas is reduced, and the covering effect is shown in fig. 3.
Example 3
As shown in FIG. 1, the present invention is a laminate cooling structure suitable for a gas turbine engine, in which a double turbulence column, S-shaped air intake holes 3 and film holes 10, and an omega-shaped rotation cavity structure are main features different from the existing laminate structure. Each rotary cavity is approximate omega-shaped and can be regarded as a relatively independent minimum unit body, two turbulence columns are arranged in each unit body and are respectively an air inlet cavity turbulence column 7 and an air outlet cavity turbulence column 9, and the shapes of the turbulence columns and the shapes of the cavities are in the same shape and are in the shape of a regular hexagon. The cavity structure around the turbulence column in the unit body is tangent and smoothly connected with the air inlet hole 3 and the air film hole 10 and is in a rotary shape on the whole. The air inlet hole 3 on the air inlet plate 2 and the air film hole 10 on the air outlet plate 13 are centrosymmetric, the channel shape of the hole is S-shaped, namely the central line 4 of the air inlet hole and the central line 11 of the air film hole are both S-shaped, and the section is oval. The projection of the air inlet center line 4 of the air inlet 3 and the air film hole center line 11 of the air film hole 10 in each unit body in the same horizontal plane is axisymmetric.
The cross section of each part of the cooling channel along the path is elliptical, and the length ratio of the long axis to the short axis of the ellipse is 1.2.
The central line 4 of the air inlet hole and the central line 11 of the air film hole are both formed by two sections of tangent circular arcs, the distance between the tangent point and the plate surface is 0.3 times of the thickness of the laminate, and the ratio of the radius values of the two sections of circular arcs is 1: 3.15.
the incident angle and the emergent angle of the air inlet hole 3 and the air film hole 10 are both 30 degrees with respect to the horizontal plane, namely angle A1 and angle A2. The whole laminate is formed by a plurality of unit bodies which are arranged closely according to the periodicity.
Example 4
As shown in FIG. 1, the present invention is a laminate cooling structure suitable for a gas turbine engine, in which a double turbulence column, S-shaped air intake holes 3 and film holes 10, and an omega-shaped rotation cavity structure are main features different from the existing laminate structure. Each rotary cavity is approximately S-shaped and can be regarded as a relatively independent minimum unit body, two turbulence columns are arranged in each unit body and respectively serve as an air inlet cavity turbulence column 7 and an air outlet cavity turbulence column 9, and the shapes of the turbulence columns and the shapes of the cavities are square. The cavity structure around the turbulence column in the unit body is tangent and smoothly connected with the air inlet hole 3 and the air film hole 10 and is in a rotary shape on the whole. The air inlet hole 3 on the air inlet plate 2 and the air film hole 10 on the air outlet plate 13 are centrosymmetric, the channel shape of the hole is S-shaped, namely the central line 4 of the air inlet hole and the central line 11 of the air film hole are both S-shaped, and the section is oval. The central line 4 of the air inlet hole 3 in each unit body is spatially and centrally symmetrical with the central line 11 of the air film hole 10.
The cross section of each part of the cooling channel along the path is elliptical, and the length ratio of the major axis to the minor axis of the ellipse is 2.
The central line 4 of the air inlet hole and the central line 11 of the air film hole are both composed of two sections of tangent arcs, the distance between the tangent points and the surface of the laminate is 0.25 times of the thickness of the laminate, and the ratio of the radiuses of the two sections of arcs is 1: 3.42.
the incident angle and the emergent angle of the air inlet hole 3 and the air film hole 10 are both 50 degrees with respect to the horizontal plane, namely angle A1 and angle A2. The whole laminate is formed by a plurality of unit bodies which are arranged closely according to the periodicity.
Claims (5)
1. The omega-shaped rotary cavity layer plate cooling structure is characterized by being composed of a plurality of unit bodies with the same shape, wherein each unit body structurally comprises an air inlet hole (3) positioned on an air inlet plate (2), an air film hole (10) positioned on an air outlet plate (13), a turbulence column and an omega-shaped rotary cavity; the omega-shaped rotary cavity can be divided into an air inlet cavity (6) and an air outlet cavity (8), flow disturbing columns are respectively arranged at the centers of the omega-shaped rotary cavity and the flow disturbing columns are consistent with the outline shape of the cavity; wherein the shape of the unit body is formed by two regular hexagons, squares or circles which are completely the same in size and are arranged in parallel;
in each unit body, an air inlet cavity (6) is connected with an air inlet hole (3), and an air outlet cavity (8) is connected with an air film hole (10); in the section vertical to the surface of the unit body, the central lines of the air inlet holes (3) and the air film holes (10) are S-shaped curves; the included angle between the tangential direction of the air inlet hole center line (4) at the outer surface of the air inlet plate (2) and the plate surface is an incident angle A1, the included angle between the tangential direction of the air film hole center line (11) at the outer surface of the air outlet plate and the plate surface is an emergent angle A2, and the values of angle A1 and angle A2 are 30-50 degrees;
the cross section of the air inlet hole (3) and the air film hole (10) is oval, and the air inlet hole (3) and the air film hole (10) are smoothly connected with a channel in the omega-shaped rotary cavity by adopting an arc-shaped slideway; the cross section of the cooling channel along the way is elliptical.
2. The ω -type rotational cavity plate cooling structure according to claim 1, wherein the ratio of the length of the major axis to the length of the minor axis of the elliptical cross-section of the cooling channel is 1.2 to 2.
3. The omega-type rotary cavity plate cooling structure as claimed in claim 1 or 2, wherein the central lines of the air inlet holes (3) and the air film holes (10) are formed by two tangent circular arcs, the radiuses of the two circular arcs are R1 and R2 respectively, and the bending directions are opposite; the starting end of the circular arc with the radius of R1 is tangent to the central axis of the laminate, and the included angle formed by the tangent line at the intersection point of the circular arc with the radius of R2 and the surface of the air inlet/outlet plate and the plate surface is the air inlet/outlet angle of the hole, namely the air inlet/outlet angle.
4. The ω -type rotary cavity plate cooling structure according to claim 1 or 2, wherein when the unit shape is two parallel regular hexagons, turbulence columns are respectively provided at the centers of the two regular hexagons, i.e. the centers of the inlet cavity and the outlet cavity of the ω -type rotary cavity, and the two cavities are smoothly communicated with each other through a v-shaped channel, so that the cooling channel is in an ω -type in plan view.
5. The ω -type rotary cavity plate cooling structure according to claim 3, wherein when the unit shape is two parallel regular hexagons, turbulence columns are respectively disposed at the centers of the two regular hexagons, i.e. the centers of the inlet cavity and the outlet cavity of the ω -type rotary cavity, and the two cavities are smoothly communicated with each other through a v-shaped channel, so that the cooling channel is in an ω -type in a top view.
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| CN202011014722.4A CN112145234B (en) | 2020-09-24 | 2020-09-24 | Omega type gyration chamber plywood cooling structure |
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| CN202011014722.4A CN112145234B (en) | 2020-09-24 | 2020-09-24 | Omega type gyration chamber plywood cooling structure |
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| CN112145234B true CN112145234B (en) | 2021-08-20 |
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| CN111075510B (en) * | 2020-01-06 | 2021-08-20 | 大连理工大学 | Turbine blade honeycomb spiral cavity cooling structure |
| CN113565573B (en) * | 2021-07-07 | 2023-08-11 | 上海空间推进研究所 | Turbine blade with internal cooling channels distributed in honeycomb-like manner and gas turbine |
| CN113669756B (en) * | 2021-08-31 | 2022-05-10 | 西北工业大学 | Double-layer double-effect heat insulation wall for afterburner cavity and double-effect cooling method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110925028B (en) * | 2019-12-05 | 2022-06-07 | 中国航发四川燃气涡轮研究院 | Gas turbine blade with S-shaped impingement cavity partition |
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| CN101008327A (en) * | 2006-01-27 | 2007-08-01 | 联合工艺公司 | Film cooling method and method of manufacturing a hole |
| CN101126351A (en) * | 2007-07-13 | 2008-02-20 | 北京航空航天大学 | Low flow resistance veneer structure |
| CN101545381A (en) * | 2008-03-25 | 2009-09-30 | 通用电气公司 | Film cooling of turbine components |
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