CN112523810B - Triangular column type flow guide structure applied to turbine blade trailing edge half-splitting seam - Google Patents
Triangular column type flow guide structure applied to turbine blade trailing edge half-splitting seam Download PDFInfo
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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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Abstract
The invention relates to a triangular column type flow guide structure and a flow guide method applied to a turbine blade trailing edge half-splitting seam. A part of wall surface of the pressure surface of the turbine blade close to the trailing edge is cut off and then forms a plurality of trailing edge half-split seam structures with the separating ribs, and cooling gas flows out of the outlet and then forms cooling gas films on the wall surface of the half-split seam and the downstream wall surface, so that high-temperature main stream gas is isolated, and the temperature of the wall surface is reduced. The triangular column type flow guide structure is arranged on the downstream wall surface of the half-splitting seam to generate a turbulent flow effect on the cooling air film, so that the nonuniformity of the downstream air film distribution of the half-splitting seam is obviously weakened, the spreading direction covering effect and the cooling efficiency of the cooling air film are improved, and the reduction of the highest temperature and the temperature gradient of the tail edge is realized. The triangular column type flow guide structure is arranged on the downstream wall surface of the half-split seam, has the characteristics of simple structure, convenience in processing and good cooling effect, and can be applied to various turbine blade tail edge half-split seam structures.
Description
Technical Field
The invention belongs to the technical field of cooling of turbine blades of gas turbines, and particularly relates to a triangular column type flow guide structure applied to a turbine blade trailing edge half-splitting seam.
Background
A gas turbine engine is a thermodynamic device based on the brayton cycle, which has been widely used in modern military and industry by virtue of its powerful output power and high thermal efficiency. Experience shows that under the premise that the size of an engine is not changed, the thrust of a gas turbine can be increased by 8-13% and the cycle efficiency can be increased by 2-4% when the temperature of the inlet of the turbine is increased by 56K. The turbine front temperature of the advanced aeroengine exceeds 2000K at present, and the temperature resistance limit of the turbine blade material is far less than the turbine inlet temperature, so that an efficient cooling technology must be adopted to ensure the normal operation of the turbine blade material. The two sides of the trailing edge of the turbine blade are influenced by the main flow, the convective heat transfer strength is high, and the turbine blade is an area with the highest heat load except the leading edge. In addition, in order to ensure aerodynamic performance of the turbine blade, the trailing edge structure is narrow and the space for arranging the cooling structure is limited. Therefore, the trailing edge region is a difficult and difficult region for cooling design on the turbine blade, and the efficient cooling technology is very important for reducing the temperature of the trailing edge and ensuring the normal operation of the turbine blade.
The turbine blade trailing edge region is typically cooled using internal channels with turbulator columns and ribs disposed within the channels to enhance heat transfer and increase structural strength. Internal channel cooling typically requires a wall thickness, while aerodynamic design of the trailing edge requires as thin a wall thickness as possible. The pure internal cooling mode is not enough to ensure the normal work of the blade tail edge, so three typical cooling modes of discrete hole film cooling, full split seam and half split seam are introduced into the tail edge part of the turbine blade on the basis of internal channel cooling. The half-split structure cuts off the wall surface of one side of the pressure surface of the trailing edge of the blade, and introduces cold air of the internal channel into the cut wall surface to form a cooling air film, so that the trailing edge is thinned, the pneumatic performance is improved, and meanwhile, the cooling performance is good. In addition, the half-split slit structure can extend the rib structure of the inner channel to the tail edge in practical application, and a separation rib structure is formed on the surface of the half-split slit, so that the structural strength of the half-split slit structure is ensured. At present, a half-split structure is a cooling structure widely adopted by a turbine blade and is also one of research hotspots of a turbine blade trailing edge cooling technology. Research has shown that the half-slit structure with the spacing ribs has the phenomenon of uneven air film distribution in the downstream area, and the air film cooling efficiency is reduced rapidly, which may cause the maximum temperature and the temperature gradient in the downstream area of the half-slit to rise, and the corresponding thermal stress is increased, thereby damaging the trailing edge structure. Therefore, the development and improvement of the trailing edge half-slit cooling structure can improve the air film cooling efficiency and distribution uniformity of the downstream area of the half-slit without increasing the amount of cold air, and is necessary and meaningful for further improving the performance of the aero-engine.
The Chinese patent application publication CN107013254A discloses a turbolator half-slit cooling structure for the trailing edge of a turbine blade with a spherical bump, wherein the spherical bump structure is applied to the wall surface of the half-slit, and on the premise of not increasing the air film outflow, the turbolator structure is used for improving the convective heat transfer coefficient and the heat transfer area of an air film and enhancing the convective heat transfer strength of air film cooling of the half-slit, so that the comprehensive cooling effect of the trailing edge of the blade is improved. However, the cooling structure of the scheme cannot improve the cooling air film spreading coverage effect and the cooling efficiency of the downstream area of the half-splitting seam, and the process for forming the plurality of spherical bump structures on the wall surface of the half-splitting seam is complex, the processing difficulty is high, and the cost is not reduced.
Prior art 1: the Chinese patent application publication CN107013254A discloses a turbolator half-slit cooling structure for the trailing edge of a turbine blade with a spherical bump, wherein the spherical bump structure is applied to the wall surface of the half-slit, and on the premise of not increasing the air film outflow, the turbolator structure is used for improving the convective heat transfer coefficient and the heat transfer area of an air film and enhancing the convective heat transfer strength of air film cooling of the half-slit, so that the comprehensive cooling effect of the trailing edge of the blade is improved. However, the cooling structure of the scheme cannot improve the cooling air film spreading coverage effect and the cooling efficiency of the downstream area of the half-splitting seam, and the process for forming the plurality of spherical bump structures on the wall surface of the half-splitting seam is complex, the processing difficulty is high, and the cost is not reduced.
Prior art 2: the Chinese patent application publication CN107060893A discloses a turbine blade trailing edge turbulent flow half-split seam cooling structure with V-shaped ribs, the V-shaped rib structure is arranged on the wall surface of the half-split seam to generate an enhanced heat transfer effect, and on the premise of not increasing the air film outflow, the turbulent flow structure is used for improving the air film convective heat transfer coefficient and the heat transfer area and enhancing the convective heat transfer strength of half-split seam air film cooling, so that the comprehensive cooling effect of the trailing edge of the blade is improved; the cooling air flow is ejected from the outflow seam to cover the wall surface of the half-split seam to form a cooling air film, so that the highest temperature and the average temperature of the suction surface are effectively reduced, and the high-temperature ablation of the suction surface of the turbine blade is avoided. However, the cooling structure of the scheme also cannot improve the cooling air film spreading coverage effect and the cooling efficiency of the downstream area of the half-split seam, and the structure that a plurality of V-shaped ribs are formed on the wall surface of each half-split seam is also not beneficial to simplifying the process and reducing the cost.
The prior art is used for the blade wall surface inside the half-splitting seam at the trailing edge of the turbine blade, and the partial blade wall surface is completely covered by the air film. The action mechanism of the prior art is that the heat convection coefficient and the heat exchange area at the wall surface are enhanced through the turbulent flow structure, so that the heat exchange quantity of the upstream flowing air film and the wall surface of the blade is increased to achieve the purpose of reducing the temperature of the part of the wall surface. However, for the downstream blade wall surface of the half-slit at the trailing edge of the turbine blade, the part of the blade wall surface has the condition that part of the blade wall surface is not covered by the air film due to the blocking effect of the upstream half-slit rib.
To sum up, how to design one kind and produce the vortex effect to the cooling air film, show and weaken half crack seam low reaches air film and distribute the inhomogeneity, promote the cooling air film exhibition to covering effect and cooling efficiency, realize the reduction of trailing edge highest temperature and temperature gradient to simple structure, processing is convenient, and the half crack water conservancy diversion structure that the cooling effect is good is the problem that the field is waited for to solve urgently.
Disclosure of Invention
The invention provides a triangular column type flow guide structure applied to a turbine blade trailing edge half-splitting seam, aiming at the problems, comprising a blade trailing edge pressure surface, a blade trailing edge suction surface, a trailing edge half-splitting seam wall surface, a trailing edge half-splitting seam downstream wall surface, a partition rib and a triangular column type flow guide structure, and being characterized in that:
part of the wall surface of the pressure surface of the trailing edge of the blade close to the trailing edge is cut off and is connected with the wall surface of one side of the suction surface of the trailing edge of the blade through the partition ribs, the whole of the partition rib is positioned above the wall surface on the suction surface side of the trailing edge of the blade, a part of the partition rib is positioned below the wall surface on the pressure surface side of the trailing edge of the blade, another part of the partition rib extends to the trailing edge, the partition rib does not extend beyond the wall surface trailing edge part on the suction surface side of the blade trailing edge, cold air inlets are formed on one end of the partition rib, the wall surface on one side of the pressure surface of the trailing edge of the blade and the wall surface on one side of the suction surface of the trailing edge of the blade, the partition rib extension part and the wall surface on one side of the suction surface of the tail edge of the blade form a plurality of tail edge half-splitting slits, and the wall surface cooling airflow enters from the cold air inlet and forms a cooling air film on the wall surface of the tail edge half-splitting slit on the downstream; the triangular column type flow guide structure comprises a plurality of continuously arranged isosceles triangle structures, and one isosceles triangle structure is arranged corresponding to each tail edge half-splitting seam; the triangular column type flow guide structure is arranged at the junction of the wall surface of the tail edge half-splitting seam and the downstream wall surface of the tail edge half-splitting seam.
As a further improvement of the above technical solution: the direction of the vertex angle of the isosceles triangle is opposite to the flowing direction of the cold air, and the adjacent triangular column type flow guide structures are connected with each other.
As a further improvement of the above technical solution: the included angle between the wall surface of the trailing edge half-splitting seam and the pressure surface of the trailing edge of the blade is 0-15 degrees.
As a further improvement of the above technical solution: the height of a wall cooling air outflow seam between the pressure surface of the trailing edge of the blade and the suction surface of the trailing edge of the blade is D, the width of the wall surface of the trailing edge half-splitting seam is W, and the ratio of the width x of the triangular column type flow guide structure at the outlet of the trailing edge half-splitting seam to the width W of the wall surface of the trailing edge half-splitting seam is 0.6-0.9.
As a further improvement of the above technical solution: the vertex angle of the isosceles triangle is 90-120 degrees.
As a further improvement of the above technical solution: the width x of the triangular column type flow guide structure at the tail edge half-splitting slit outlet refers to the width of the overlapped part of the triangular column type flow guide structure and the tail edge half-splitting slit wall surface.
As a further improvement of the above technical solution: the width W of the wall surface of the trailing edge half-splitting seam is 8mm, the height D of the wall surface cooling air outflow seam is 4mm, the vertex angle of the triangular column type flow guide structure 4 is 90 degrees, the height h is 0.8mm, and the width x of the triangular column type flow guide structure at the outlet of the splitting seam is 6.3 mm.
The invention also provides a triangular column type flow guiding method applied to the turbine blade trailing edge half-splitting seam, which adopts the triangular column type flow guiding structure applied to the turbine blade trailing edge half-splitting seam, cooling airflow from an internal channel of the turbine blade enters from the cold air inlet, flows out from the cold air outlet and flows along the surface of the wall surface of the trailing edge half-splitting seam and the downstream wall surface of the trailing edge half-splitting seam to form a cooling air film, high-temperature main flow from the pressure surface (1) of the trailing edge of the blade is isolated from the wall surface, and the trailing edge structure is protected from being eroded by the high-temperature main flow.
Compared with the prior art, the invention has the advantages that: the invention is used for the downstream blade wall surface of the half-slit at the trailing edge of the turbine blade, and the partial blade wall surface has the condition that partial blade wall surface is not covered by an air film due to the blocking effect of the upstream half-slit rib. The action mechanism of the invention is that the cover area of the gas film on the wall surface of the blade at the downstream of the half-splitting slit is increased through the flow guide structure, so that the average temperature of the gas on the surface of the blade is reduced to realize the purpose of reducing the temperature of the wall surface. The triangular column type flow guide structure has the characteristics of simple structure, convenience in processing and good cooling effect, and can be applied to various turbine blade trailing edge half-split seam structures.
Drawings
Fig. 1 is an isometric view of the present invention.
Fig. 2 is a top view of the present invention.
Fig. 3 is a right side view of the present invention.
Fig. 4 is a cross-sectional view a-a of fig. 2 of the present invention.
FIG. 5 is a distribution curve of the spanwise film cooling efficiency at different flow direction distances downstream of a half-split slit with a triangular column type flow guide structure and a conventional trailing edge half-split slit.
FIG. 6 is a distribution curve of the spanwise film cooling efficiency at different flow direction distances downstream of the half-split seam with the triangular column type flow guide structure and the half-split seams of the prior art 1 and 2.
FIG. 7 is a comparison curve of the average gas film cooling efficiency in the span direction of the downstream wall surface of the half-split slit with the triangular column type flow guide structure and the conventional tail edge half-split slit.
Fig. 8 is a comparison curve of the average gas film cooling efficiency in the span direction of the half-split seam with the triangular column type flow guide structure and the downstream wall surface of the half-split seam in the prior art 1 and 2.
Detailed Description
The following detailed description of the present invention is given for the purpose of better understanding technical solutions of the present invention by those skilled in the art, and the present description is only exemplary and explanatory and should not be construed as limiting the scope of the present invention in any way.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, specific embodiments thereof are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein, but rather should be construed as broadly as the present invention is capable of modification in various respects, all without departing from the spirit and scope of the present invention.
With reference to fig. 1-4, the present embodiment provides a triangular column type flow guiding structure applied to a turbine blade trailing edge half-splitting seam, which includes a blade trailing edge pressure surface 1, a blade trailing edge suction surface 6, a partition rib 2, a trailing edge half-splitting seam wall surface 3, a cold air inlet 8, a cold air outlet 7, a trailing edge half-splitting seam downstream wall surface 5, and a triangular column type flow guiding structure 4; the wall surface of the pressure surface 1 at the tail edge of the blade is cut off, one side wall surface of the suction surface 6 at the tail edge of the blade and the partition ribs 2 extending out of the cold air channel form a plurality of half-split seam structures, the wall surface cooling air flow covers the wall surface 3 of the half-split seam at the tail edge after flowing out from the cold air outlet 7 to form a cooling air film, and the cooling air film continuously covers the downstream wall surface 5 of the half-split seam at the tail edge after flowing through the wall surface 3 of the half-split seam at the tail edge.
The triangular column type flow guide structures 4 are arranged at the junction of the tail edge half-splitting seam wall surface 3 and the tail edge half-splitting seam downstream wall surface 5 and comprise a plurality of continuously arranged isosceles triangle structures, one isosceles triangle structure is arranged corresponding to each tail edge half-splitting seam, the vertex angle of each isosceles triangle is 90-120 degrees, the direction of the vertex angle is opposite to the flowing direction of cold air, and the adjacent triangular column type flow guide structures are mutually connected or keep smaller gaps.
The included angle between the trailing edge half-splitting seam wall surface 3 and the trailing edge pressure surface 1 of the blade is 0-15 degrees.
The height of a wall cooling air outflow seam between the blade trailing edge pressure surface 1 and the blade trailing edge suction surface 6 is D, the width of the trailing edge half-splitting seam wall surface 3 is W, and the ratio of the width x of the triangular column type flow guide structure 4 at the trailing edge half-splitting seam outlet to the width W of the trailing edge half-splitting seam wall surface 3 is 0.6-0.9.
The width x of the triangular column type flow guide structure 4 at the tail edge half-splitting slit outlet is the width of the overlapped part of the triangular column type flow guide structure 4 and the tail edge half-splitting slit wall surface 3.
In the embodiment, the cooling air flow from the internal channel of the turbine blade enters from the cold air inlet 8, flows out from the cold air outlet 7 and flows along the surface of the wall surface 3 of the trailing edge half-slit and the downstream wall surface 5 of the trailing edge half-slit to form a cooling air film, so that the high-temperature main flow from the pressure surface 1 of the trailing edge of the blade is isolated from the wall surface, and the trailing edge structure is protected from being eroded by the main flow. Due to the existence of the separation ribs, after the cooling air film flows through the tail edge half-slit wall surface 3 and enters the tail edge half-slit downstream wall surface 5, the phenomenon of uneven distribution can be generated, and the surface temperature and the temperature gradient of the tail edge half-slit downstream wall surface 5 can be overhigh. The triangular column type flow guide structure 4 is arranged at the junction of the tail edge half-splitting slit wall surface 3 and the tail edge half-splitting slit downstream wall surface 5, so that the flow structure of the cooling air film is changed, the cooling air film has stronger flow in the spreading direction, the phenomenon of uneven air film coverage caused by the separation ribs is weakened, and the cooling effect of the tail edge half-splitting slit downstream is improved.
In this embodiment, the width W of the trailing edge half-splitting slit wall surface 3 is 8mm, the height D of the wall surface cooling air outflow slit is 4mm, the vertex angle of the triangular column type flow guide structure 4 is 90 °, the height h is 0.8mm, and the width X of the triangular column type flow guide structure 4 at the trailing edge half-splitting slit outlet is 6.3 mm. In order to ensure result comparability, the flow conditions of the two half-split structures are completely consistent, and the geometric structure difference is that whether the triangular column type flow guide structure 4 is arranged at the junction of the tail edge half-split wall surface 3 and the tail edge half-split downstream wall surface 5 or not is only determined.
In order to verify the effectiveness of the invention, the cooling efficiency of the downstream wall surface of the semi-split seam at the trailing edge of 4 types of blades in the triangular column type flow guide structure and the turbulence-free structure in the embodiment is calculated by respectively adopting the spherical protrusion turbulence structure shown in the Chinese patent application publication CN107013254A, the V-shaped rib turbulence structure shown in the Chinese patent application publication CN107060893A and the triangular column type flow guide structure. UG modeling is used in the calculation process, an ICEM generates an unstructured grid, and a CFX solver is used for solving. The calculated spanwise film cooling efficiencies are shown in fig. 5-8, respectively.
Fig. 5 compares the distribution of the spanwise (N direction in fig. 2) film cooling efficiencies η at different flow direction (M direction in fig. 2) positions of the downstream wall surface 5 with the triangular pillar type flow guiding structure in the present embodiment and the conventional trailing edge half-split. Fig. 6 compares the half-split slit with the triangular-pillar-shaped flow guide structure of the present embodiment, the spanwise air film cooling efficiency distribution at different flow direction positions of the downstream wall surface 5 of the half-split slit with the spherical-protrusion flow disturbing structure shown in chinese patent application publication CN107013254A and the V-rib flow disturbing structure shown in chinese patent application publication CN 107060893A. The abscissa represents the distance in the spanwise direction and the ordinate represents the film cooling efficiency. It can be seen that the gas film coverage efficiency of the downstream wall surface of the half-slit with the triangular column type flow guiding structure of the present embodiment is the highest and the gas film coverage is the most uniform along the circumferential direction at the two flow direction positions of M/D =5 and M/D = 15. The effectiveness and advantages of the present invention are fully illustrated.
Fig. 7 compares the downstream wall surface 5 of the half-slit with the triangular-pillar type flow guide structure of the present embodiment with the conventional trailing-edge half-slit in the spanwise (N direction of fig. 2) average air film cooling efficiency η distribution in the flow direction (M direction in fig. 2). Fig. 8 compares the half-split slit with the triangular-pillar-shaped flow guide structure of the present embodiment, the half-split slit with the spherical-protrusion flow disturbing structure shown in chinese patent application publication CN107013254A, and the downstream wall surface 5 of the half-split slit with the V-rib flow disturbing structure shown in chinese patent application publication CN107060893A, with each other, and has the average air film cooling efficiency distribution along the span direction of the flow direction. The abscissa represents the distance in the direction of flow and the ordinate represents the spanwise average film cooling efficiency. It can be seen that most of the positions of the downstream wall surface of the half-split slit with the triangular-cylindrical flow guiding structure in different flow directions have the highest average air film cooling efficiency in the spreading direction, and the air film cooling efficiency is improved by over 200%. The effectiveness and advantages of the present invention are fully illustrated.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts of the present invention. The foregoing is only a preferred embodiment of the present invention, and it should be noted that there are objectively infinite specific structures due to the limited character expressions, and it will be apparent to those skilled in the art that a plurality of modifications, decorations or changes may be made without departing from the principle of the present invention, and the technical features described above may be combined in a suitable manner; such modifications, variations, combinations, or adaptations of the invention using its spirit and scope, as defined by the claims, may be directed to other uses and embodiments.
Claims (8)
1. The utility model provides a be applied to half triangular prism type water conservancy diversion structure of splitting seam of turbine blade trailing edge, includes blade trailing edge pressure face (1), blade trailing edge suction surface (6), trailing edge half splitting seam wall (3), trailing edge half splitting seam low reaches wall (5), spacer rib (2), triangular prism type water conservancy diversion structure (4), its characterized in that: cutting off a part of the wall surface of the pressure surface (1) close to the tail edge of the blade, connecting the wall surface of one side of the suction surface (6) of the tail edge of the blade with the partition rib (2), integrally locating the partition rib (2) above the wall surface of one side of the suction surface (6) of the tail edge of the blade, locating one part of the partition rib (2) below the wall surface of one side of the pressure surface (1) of the tail edge of the blade, extending the other part of the partition rib (2) to the tail edge, extending the partition rib (2) not to exceed the tail edge part of the wall surface of one side of the suction surface (6) of the tail edge of the blade, forming a cold air inlet (8) by one end of the partition rib (2), the wall surface of one side of the pressure surface (1) of the tail edge of the blade and the wall surface of one side of the suction surface (6) of the tail edge of the blade, forming a plurality of tail edge half-splitting seams by the extension parts of the partition rib (2) and the wall surface of one side of the suction surface (6) of the suction surface of the tail edge of the blade, the wall surface cooling airflow enters from the cold air inlet (8) and forms a cooling air film on the downstream tail edge half-splitting seam wall surface (3); the triangular column type flow guide structure (4) is arranged at the junction of the tail edge half-splitting seam wall surface (3) and the tail edge half-splitting seam downstream wall surface (5); the triangular column type flow guide structure (4) comprises a plurality of continuously arranged isosceles triangle structures, and one isosceles triangle structure is arranged corresponding to each tail edge half-splitting seam.
2. The triangular column type flow guiding structure applied to the turbine blade trailing edge half-splitting seam as claimed in claim 1, wherein: the direction of the vertex angle of the isosceles triangle is opposite to the flowing direction of the cold air, and the adjacent triangular column type flow guide structures are connected with each other.
3. The triangular column type flow guiding structure applied to the turbine blade trailing edge half-splitting seam as claimed in claim 1, wherein: the included angle between the trailing edge half-splitting seam wall surface (3) and the trailing edge pressure surface (1) of the blade is 0-15 degrees.
4. The triangular column type flow guiding structure applied to the turbine blade trailing edge half-splitting seam according to claim 2 or 3, wherein: the height of a wall cooling air outflow seam between the blade trailing edge pressure surface (1) and the blade trailing edge suction surface (6) is D, the width of the trailing edge half-splitting seam wall surface (3) is W, and the ratio of the width x of the triangular column type flow guide structure (4) at the trailing edge half-splitting seam outlet to the width W of the trailing edge half-splitting seam wall surface (3) is 0.6-0.9.
5. The triangular column type flow guiding structure applied to the turbine blade trailing edge half-splitting seam as claimed in claim 2, wherein: the vertex angle of the isosceles triangle is 90-120 degrees.
6. The triangular column type flow guiding structure applied to the turbine blade trailing edge half-splitting seam as claimed in claim 4, wherein: the width x of the triangular column type flow guide structure (4) at the tail edge half-splitting slit outlet is the width of the overlapped part of the triangular column type flow guide structure (4) and the tail edge half-splitting slit wall surface (3).
7. The triangular column type flow guiding structure applied to the turbine blade trailing edge half-splitting seam as claimed in claim 4, wherein: the width W of the tail edge half-splitting seam wall surface (3) is 8mm, the wall surface cooling air outflow seam height D is 4mm, the vertex angle of the triangular column type flow guide structure (4) is 90 degrees, the height h is 0.8mm, and the width x of the triangular column type flow guide structure (4) at the tail edge half-splitting seam outlet is 6.3 mm.
8. A triangular column type flow guiding method applied to a turbine blade trailing edge half-splitting seam, which adopts the triangular column type flow guiding structure applied to the turbine blade trailing edge half-splitting seam of any one of claims 1 to 7, and is characterized in that: the cooling air flow from the internal channel of the turbine blade enters from the cold air inlet (8), flows out from the cold air outlet (7) and flows along the surface of the wall surface (3) of the trailing edge half-slit and the downstream wall surface (5) of the trailing edge half-slit to form a cooling air film, so that the high-temperature main flow from the pressure surface (1) of the trailing edge of the blade is isolated from the wall surface, and the structure of the trailing edge is protected from being eroded by the high-temperature main flow.
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| CN114439552B (en) * | 2022-01-25 | 2023-05-05 | 北京航空航天大学 | Triangular pyramid-shaped flow guiding structure, turbine guider and gas turbine design method thereof |
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