CN112343666A - Be applied to half corrugated rib water conservancy diversion structure of splitting seam of turbine blade trailing edge - Google Patents
Be applied to half corrugated rib water conservancy diversion structure of splitting seam of turbine blade trailing edge Download PDFInfo
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- CN112343666A CN112343666A CN202011467795.9A CN202011467795A CN112343666A CN 112343666 A CN112343666 A CN 112343666A CN 202011467795 A CN202011467795 A CN 202011467795A CN 112343666 A CN112343666 A CN 112343666A
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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 corrugated rib flow guide structure and a flow guide method applied to a turbine blade trailing edge half-slit. 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 corrugated ribs are 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 invention arranges the continuous corrugated rib structure on the downstream wall surface of the half-split seam, has the characteristics of simple structure, convenient 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 corrugated rib flow guide structure applied to a half-split seam of a trailing edge of a turbine blade.
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.
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, has high processing difficulty, and is not beneficial to reducing the cost
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 two technical schemes in the prior art are both used for the inner blade wall surface of the half-splitting seam at the tail edge of the turbine blade, and the partial blade wall surface is completely covered by the air film. The two prior arts have the action mechanism that the heat convection coefficient and the heat exchange area at the wall surface are enhanced by the turbulent flow structure, so that the heat exchange quantity between 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 wall surface of the downstream blade of the half-slit at the trailing edge of the turbine blade, the part of the wall surface of the blade has the condition that the part of the wall surface of the blade 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 corrugated rib flow guide structure applied to a turbine blade trailing edge half-slit, which comprises a blade trailing edge pressure surface, a blade trailing edge suction surface, a trailing edge half-slit wall surface, a trailing edge half-slit downstream wall surface, a partition rib and a continuous corrugated rib, wherein part of the wall surface of the blade trailing edge pressure surface close to the trailing edge is cut off and is connected with the wall surface of one side of the blade trailing edge suction surface through the partition rib, the partition rib is integrally positioned above the wall surface of one side of the blade trailing edge suction surface, one part of the partition rib is positioned below the wall surface of one side of the blade trailing edge pressure surface, the other part of the partition rib extends towards the trailing edge, the partition rib does not extend beyond the wall surface trailing edge part of one side of the blade trailing edge suction surface, one end of the partition rib, the wall surface of one side of the blade trailing edge pressure surface and the wall surface of one side of the blade trailing edge suction surface form a cold air inlet, 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-split seams, 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-split seam on the downstream, the continuous corrugated rib is arranged on the downstream of the plurality of tail edge half-split seams, and the continuous corrugated rib is positioned above the wall surface on one side of the suction surface of the tail edge of the blade.
As a further improvement of the above technical solution: the continuous corrugated ribs comprise a plurality of crest ribs and trough ribs which are periodically and alternately arranged, one crest rib is arranged corresponding to each tail edge half-splitting seam, and one trough rib is arranged corresponding to each separating rib.
As a further improvement of the above technical solution: the continuous corrugated rib is arranged at the junction of the wall surface of the tail edge half-slit and the downstream wall surface of the tail edge half-slit.
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 width of each tail edge half-slit wall surface (3) is X, the width of each partition rib is Y, and the span-wise period distance p of the continuous corrugated rib is equal to the sum of the width X of the single half-slit and the width Y of the single partition rib.
As a further improvement of the above technical solution: the ratio of the flow direction spacing s between the wave crests and the wave troughs of the continuous corrugated ribs to the spanwise periodic distance p is 0.8-1.2.
As a further improvement of the above technical solution: the ratio of the height h of the continuous corrugated rib to the height D of the wall surface cooling air outflow seam between the pressure surface of the tail edge of the blade and the suction surface of the tail edge of the blade is 0.1-0.4, the rib width of the continuous corrugated rib is k, the ratio of k/h is 0.5-2, and the ratio of the width W of the continuous corrugated rib at the outlet of the tail edge half-splitting seam to the width W of the wall surface of the tail edge half-splitting seam is 0.6-0.9.
As a further improvement of the above technical solution: the width W of the continuous corrugated rib at the outlet of the tail edge half-splitting seam refers to the width of the overlapped part of the continuous corrugated rib and the wall surface of the tail edge half-splitting seam.
As a further improvement of the above technical solution: the width X of the wall surface of the tail edge half-slit is 8mm, the height D of the wall surface cooling air outflow slit is 4mm, the rib height h of the continuous corrugated rib is 0.8mm, the rib width k of the continuous corrugated rib is 0.8mm, and the width W of the continuous corrugated rib at the outlet of the tail edge half-slit is 6.3 mm.
The invention also provides a corrugated rib flow guiding method applied to the turbine blade trailing edge half-slit, which adopts any one of the corrugated rib flow guiding structures applied to the turbine blade trailing edge half-slit, wherein the cooling airflow from the 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-slit and the downstream wall surface of the trailing edge half-slit to form a cooling air film, so that the high-temperature main flow from the pressure surface 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 continuous corrugated rib 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 of the half-slit with the flow guiding corrugated ribs and the half-slit with the conventional tail edge at different downstream flow direction distances.
FIG. 6 is a distribution curve of the cooling efficiency of the spanwise air film between the half-slit with the diversion corrugated ribs and the positions with different flow direction distances at the downstream of the half-slit of the prior art 1 and the prior art 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-slit with the diversion corrugated ribs and the conventional tail edge half-slit.
FIG. 8 is a comparison curve of the average air film cooling efficiency of the half-slit with the flow guiding corrugated ribs and the downstream wall surface of the half-slit of 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 continuous corrugated rib flow guiding structure applied to a turbine blade trailing edge half-slit, including a blade trailing edge pressure surface 1, a blade trailing edge suction surface 6, a partition rib 2, a trailing edge half-slit wall surface 3, a cold air inlet 8, a cold air outlet 7, a trailing edge half-slit downstream wall surface 5, and a continuous corrugated rib 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 continuous corrugated ribs 4 are 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 and comprise a plurality of crest type ribs and trough type ribs which are periodically and alternately arranged, one crest type rib is arranged corresponding to each tail edge half-splitting slit, and one trough type rib is arranged corresponding to each separation rib 2. The included angle between the trailing edge half-slit wall surface 3 and the trailing edge pressure surface 1 of the blade is 0-15 degrees. The width of each tail edge half-slit wall surface 3 is X, the width of each partition rib 2 is Y, and the span-wise period distance p of the continuous corrugated rib 4 is equal to the sum of the width X of a single half-slit and the width Y of a single partition rib. The ratio of the flow direction spacing s between the wave crests and the wave troughs of the continuous corrugated ribs (4) to the spanwise periodic distance p is 0.8-1.2. The opening direction of the corrugated ribs in the area just downstream of the half-split seam is consistent with the flow direction, and the opening direction of the corrugated ribs in the area just downstream of the partition ribs is opposite to the flow direction.
The ratio of the height h of the continuous corrugated rib 4 to the height D of the wall surface cooling air outflow seam between the pressure surface 1 of the tail edge of the blade and the suction surface 6 of the tail edge of the blade is 0.1-0.4, the rib width of the continuous corrugated rib 4 is k, the ratio of k/h is 0.5-2, and the ratio of the width W of the continuous corrugated rib 4 at the outlet of the tail edge half-slit to the width W of the wall surface 3 of the tail edge half-slit is 0.6-0.9. The width W of the continuous corrugated rib 4 at the outlet of the tail edge half-slit is the width of the overlapped part of the continuous corrugated rib 4 and the tail edge half-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 4, 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 continuous corrugated rib 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 rib is weakened, and the cooling effect of the tail edge half-splitting slit downstream is improved.
In this embodiment, the width X of the trailing edge half-slit wall surface 3 is 8mm, the width Y of the partition rib 2 is 8mm, the wall surface cooling air outflow slit height D is 4mm, the rib height h of the continuous corrugated rib 4 is 0.8mm, the rib width k of the continuous corrugated rib (4) is 0.8mm, the flow direction interval s between the wave crest and the wave trough of the continuous corrugated rib 4 is 6mm, and the width W of the continuous corrugated rib 4 at the trailing edge half-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 geometrical structure difference is that whether the continuous corrugated rib 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 different.
In order to verify the effectiveness of the invention, the cooling efficiency of the downstream wall surface of the semi-split seam of the trailing edge of 4 types of blades in the corrugated rib 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 like. 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 efficiency η at different flow direction (M direction in fig. 2) positions of the downstream wall surface 5 of the half-slit with the guide corrugated ribs in the present embodiment and the conventional trailing edge half-slit. Fig. 6 compares the half-slit with the guide corrugated rib 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-slit with the spherical convex spoiler structure shown in chinese patent application publication CN107013254A and the V-shaped rib spoiler 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 corrugated rib flow guiding structure of the present embodiment is the highest and the gas film coverage is the most uniform in 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 corrugated rib flow guide structure of the present embodiment with the downstream wall surface of the conventional trailing edge half-slit in the spanwise direction (N direction in fig. 2) of the flow direction (M direction in fig. 2) with the average air film cooling efficiency η distribution. Fig. 8 compares the half-slit with the guide corrugated rib of the present embodiment, the half-slit with the spherical convex spoiler structure shown in chinese patent application publication CN107013254A, and the downstream wall 5 of the half-slit with the V-shaped rib spoiler 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 different flow direction positions of the downstream wall surface of the half-slit with the corrugated rib flow guide structure of the embodiment have the highest spanwise average air film cooling efficiency, 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 (10)
1. The utility model provides a be applied to corrugated rib water conservancy diversion structure of turbine blade trailing edge half-splitting seam, 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), spacing rib (2), continuous corrugated rib (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, the wall surface cooling air flow enters from the cold air inlet (8) and forms a cooling air film on the downstream tail edge half-slit wall surface (3), the continuous corrugated rib (4) is arranged downstream of the plurality of tail edge half-slits, and the continuous corrugated rib (4) is positioned above the wall surface on the side of the suction surface (6) of the tail edge of the blade.
2. The corrugated rib flow guide structure applied to the half-splitting seam of the trailing edge of the turbine blade as claimed in claim 1, wherein: the continuous corrugated ribs (4) comprise a plurality of crest type ribs and trough type ribs which are periodically and alternately arranged, one crest type rib is arranged corresponding to each tail edge half-splitting seam, and one trough type rib is arranged corresponding to each separation rib (2).
3. The corrugated rib flow guiding structure applied to the half-splitting seam of the trailing edge of the turbine blade as claimed in claim 2, wherein: the continuous corrugated rib (4) is arranged at the junction of the tail edge half-slit wall surface (3) and the tail edge half-slit downstream wall surface (5).
4. The corrugated rib flow guide structure applied to the half-splitting seam of the trailing edge of the turbine blade as claimed in claim 3, 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.
5. The corrugated rib flow guide structure applied to the half-splitting seam of the trailing edge of the turbine blade as claimed in claim 3, wherein: the width of each tail edge half-slit wall surface (3) is X, the width of each partition rib (2) is Y, and the span-wise period distance p of the continuous corrugated rib (4) is equal to the sum of the width X of a single half-slit and the width Y of a single partition rib.
6. The corrugated rib flow guide structure applied to the half-splitting seam of the trailing edge of the turbine blade as claimed in claim 3, wherein: the ratio of the flow direction spacing s between the wave crests and the wave troughs of the continuous corrugated ribs (4) to the spanwise periodic distance p is 0.8-1.2.
7. The corrugated rib flow guide structure applied to the half-splitting seam of the trailing edge of the turbine blade as claimed in claim 6, wherein: the ratio of the height h of the continuous corrugated rib (4) to the height D of a wall cooling air outflow seam between the pressure surface (1) of the tail edge of the blade and the suction surface (6) of the tail edge of the blade is 0.1-0.4, the rib width of the continuous corrugated rib (4) is k, the ratio of k/h is 0.5-2, and the ratio of the width W of the continuous corrugated rib (4) at the outlet of the tail edge half-slit to the width W of the wall surface (3) of the tail edge half-slit is 0.6-0.9.
8. The corrugated rib flow guide structure applied to the half-splitting seam of the trailing edge of the turbine blade as claimed in claim 6, wherein: the width W of the continuous corrugated rib (4) at the outlet of the tail edge half-slit is the width of the overlapped part of the continuous corrugated rib (4) and the tail edge half-slit wall surface (3).
9. The corrugated rib flow guide structure applied to the half-splitting seam of the trailing edge of the turbine blade as claimed in claim 6, wherein: the width X of the tail edge half-slit wall surface (3) is 8mm, the height D of the wall surface cooling air outflow slit is 4mm, the rib height h of the continuous corrugated rib (4) is 0.8mm, the rib width k of the continuous corrugated rib (4) is 0.8mm, and the width W of the continuous corrugated rib (4) at the tail edge half-slit outlet is 6.3 mm.
10. A corrugated rib flow guiding method applied to a turbine blade trailing edge half-slit, which adopts the corrugated rib flow guiding structure applied to the turbine blade trailing edge half-slit according to any one of claims 1 to 9, 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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| CN114198154A (en) * | 2021-12-15 | 2022-03-18 | 中国科学院工程热物理研究所 | Cooling structure |
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| JPH03141801A (en) * | 1990-09-19 | 1991-06-17 | Hitachi Ltd | Cooling blade of gas turbine |
| US5503529A (en) * | 1994-12-08 | 1996-04-02 | General Electric Company | Turbine blade having angled ejection slot |
| US20050249593A1 (en) * | 2004-01-14 | 2005-11-10 | Snecma Moteurs | Cooling air evacuation slots of turbine blades |
| US8096771B2 (en) * | 2008-09-25 | 2012-01-17 | Siemens Energy, Inc. | Trailing edge cooling slot configuration for a turbine airfoil |
| US20130017064A1 (en) * | 2010-03-19 | 2013-01-17 | Alstom Technology Ltd | Gas turbine airfoil with shaped trailing edge coolant ejection holes |
| CN107013254A (en) * | 2017-06-01 | 2017-08-04 | 西北工业大学 | A kind of turbine blade tail flow-disturbing with sphere projection partly splits seam cooling structure |
| CN107060893A (en) * | 2017-06-01 | 2017-08-18 | 西北工业大学 | A kind of turbine blade tail flow-disturbing with V-type rib partly splits seam cooling structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114198154A (en) * | 2021-12-15 | 2022-03-18 | 中国科学院工程热物理研究所 | Cooling structure |
| CN114198154B (en) * | 2021-12-15 | 2023-08-15 | 中国科学院工程热物理研究所 | Cooling structure |
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| CN112343666B (en) | 2021-08-24 |
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