CN113107607B - Turbine guide vane structure with through-slit on rib at tail edge - Google Patents
Turbine guide vane structure with through-slit on rib at tail edge Download PDFInfo
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- CN113107607B CN113107607B CN202110391292.6A CN202110391292A CN113107607B CN 113107607 B CN113107607 B CN 113107607B CN 202110391292 A CN202110391292 A CN 202110391292A CN 113107607 B CN113107607 B CN 113107607B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
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- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
According to the turbine guide vane structure with the through-slits on the ribs at the tail edges, through the through-slits on the separation ribs, after cooling air flows through the outflow slits, part of cooling air can cool the inside of the separation ribs through the through-slits on the separation ribs, and the convection heat exchange strength of the inner wall surfaces and the side wall surfaces of the separation ribs is enhanced under the condition that the cooling air flow is not increased, so that the comprehensive cooling effect of the tail edges is improved; preferably, the through seam is an inclined seam, and when the cooling airflow passes through the separation rib, the strength of the cold air vortex generated under the influence of the separation rib is weakened, so that the interaction of the lip falling vortex and the cold air vortex is weakened, and the air film cooling efficiency of the surface of the separation rib is improved. The invention has reasonable design and simple structure, and the inclined slits are arranged on the side wall surface of the partition rib, so that the invention not only has good heat transfer and cooling characteristics, but also has better processing integration and better practicability.
Description
Technical Field
The invention belongs to the technical field of cooling of turbine blades of gas turbines, and particularly relates to a turbine guide vane structure with a through seam on a rib at the tail edge.
Background
In order to make the aeroengine continuously and reliably work with long service life under the severe working condition of high temperature and high pressure for a long time, besides accelerating the research and development of new materials, the hot end components such as turbine blades of the aeroengine need to be effectively cooled. The trailing edge is a typical high temperature location of the blade, and because of the requirement of pneumatic design, the trailing edge is usually designed to be thin, and how to efficiently cool in a very small space is a major difficulty in the cooling design, so the trailing edge is also the location most prone to damage caused by thermal corrosion. The research of the gas film cooling characteristics of the tail edge of the turbine blade is one of hot spots in the research of the cooling technology of high-temperature parts of a gas turbine in recent years, and the research of the design of a tail edge split joint structure and the like is gradually focused by researchers.
The separation rib, which is an important structure of the tail edge half split joint, can keep the continuity of the main flow on the lip plate and reduce the aerodynamic loss. The heat transfer and cooling of the high-temperature turbine blade (pages 172-180 of the university of western traffic press) are compared with the split joint surface cooling efficiency and heat exchange coefficient when the separation ribs are respectively straight ribs, chamfer ribs and shrinkage ribs, and the research shows that compared with other rib structures, the shrinkage ribs can weaken the influence of lip falling vortex on the split joint surface air film to a certain extent, so that better cooling efficiency and heat exchange coefficient distribution are obtained. On the one hand, the rearward extension of the separation ribs strengthens the rectification effect of the cold air at the butt seam outlet, so that the cold air is difficult to diffuse upwards; on the other hand, the existence of the separation rib can generate flow angle vortex near the side wall surface of the rib, interaction can be generated between the flow angle vortex and the lip plate shedding vortex, and the two aspects of the interaction influence can cause the air film cooling efficiency on the surface of the separation rib to be lower, so that the surface temperature of the separation rib is higher, and the erosion of the tail edge part of the blade is further caused. Therefore, the development and innovation of the turbine blade trailing edge efficient cooling structure further improves the cooling effect, and is very necessary and significant for the development of advanced high-performance aeroengines.
Chinese patent application publication CN111502771a discloses a trailing edge half split cooling structure with slit straight ribs, which improves the convective heat transfer coefficient and heat transfer area by arranging slit straight ribs on the split surface, and simultaneously the slit has a certain diversion effect on cooling airflow, reducing the influence of the vortex generated before and after the ribs on the air film cooling efficiency on the split surface. However, such a straight rib structure with slits corresponds to an improvement of the conventional turbulent straight rib, and only the flow characteristics of the cooling air flow near the turbulent straight rib are optimized, and the cold flow vortex near the partition rib and the cooling thereof are not considered.
Therefore, how to design a vane structure which can improve cooling and heat exchange of the partition ribs without increasing the flow of cold air and has the characteristics of simple processing and low production cost is a problem to be solved.
Disclosure of Invention
Aiming at the problem that the cooling efficiency of the surface of a separation rib is low due to the fact that cooling of the separation rib is omitted in the design stage of the cooling structure of the tail edge in the prior art and the cooling of the side of the tail edge near the suction surface is not perfect, the invention provides a turbine guide vane structure with a through inclined seam on the tail edge.
The technical scheme of the invention is as follows:
the turbine guide vane structure is characterized in that a turbine blade tail edge area is provided with a tail edge half split joint structure, wherein part of the wall surface of the pressure surface of the tail edge of the turbine blade is cut off, and only the wall surface on one side of a suction surface and a plurality of separation ribs are reserved;
the method is characterized in that: the bottom of the partition rib, which is contacted with the wall surface of the half split seam, is provided with a plurality of through seams which laterally penetrate through the partition rib, and the through seams are used for communicating the space between the tail edge half split seam surfaces at two sides of the partition rib.
Further, the cold air outflow slot height h of the half split slot tail edge cooling structure 1 The value range of the air conditioner is 0.3-0.8 mm, and the width l of the cold air outflow slot of the tail edge 1 Height h of cold air outflow slot at tail edge 1 The ratio range is 3-10; span-wise distance p between two adjacent trailing edge cold air outflow slots 1 The range of the value of (2) is 1.8-4.8 mm; the thickness t of the lip plate of the half split joint structure and the height h of the cold air outflow joint 1 The ratio of (2) is between 0.2 and 1.5, and the half slit inclination angle is between 0 and 15 degrees.
Further, after the tail edge cooling air flows out of the tail edge cooling air cavity, the cooling air is ejected from the outflow slot, covers the half split slot wall surface to form a cooling air film, and also flows through the through slot penetrating through the partition rib to cool the inside of the partition rib.
Furthermore, an included angle exists between the slotting direction of the penetrating slot on the partition rib and the normal line of the side surface of the partition rib on a plane parallel to the surface of the tail edge half split slot, so that an inclined penetrating slot is formed, and the cooling air flow on one side of the partition rib flows to the other side of the partition rib more smoothly through the inclined penetrating slot.
Further, the cooling air flow flowing through the inclined through-slits penetrating through the partition ribs can weaken cold air corner vortex generated under the influence of the partition ribs, weaken interaction between the falling vortex and the corner vortex, and enhance the air film cooling efficiency near the partition ribs.
Further, on a plane parallel to the surface of the tail edge half split joint, the included angle between the slotting direction of the through joint and the normal line of the side surface of the separation rib is 10-15 degrees.
Further, the cross section of the through slit in the direction perpendicular to the slit is rectangular, parallelogram or right triangle.
Further, the through-slit is perpendicular to the slit directionWhen the cross section is rectangular, a plurality of rectangular through slits are formed on the same partition rib, the edge of the air flow inlet in the first rectangular through slit along the cooling air flow direction coincides with the starting line of the partition rib, and the width l of the single rectangular through slit 2 Height h of rectangular through slit of 0.25mm 2 And width l 2 The ratio of (2) is the pitch p of the rectangular through slits 2 Is 0.815mm.
Further, when the cross-sectional shape of the through-slit in the direction perpendicular to the slit direction is a parallelogram, a single parallelogram through-slit is formed in the same partition rib, and the lower end point of the airflow inlet in the parallelogram through-slit is located on the start line of the partition rib, the width l of the parallelogram through-slit 2 1.575mm, height h 2 Is 0.5mm.
Further, when the cross section of the through slit perpendicular to the slit direction is a right triangle, one of the right-angle sides is the bottom side of the partition rib, length l 2 Is 1.875mm, and the other right-angle edge of the air flow inlet coincides with the starting line of the partition rib, the height h 2 Is 0.5mm.
Advantageous effects
According to the turbine guide vane structure with the through-slits on the ribs at the tail edges, through the through-slits on the separation ribs, after cooling air flows through the outflow slits, part of cooling air can cool the inside of the separation ribs through the through-slits on the separation ribs, and the convection heat exchange strength of the inner wall surfaces and the side wall surfaces of the separation ribs is enhanced under the condition that the cooling air flow is not increased, so that the comprehensive cooling effect of the tail edges is improved; preferably, the through seam is an inclined seam, and when the cooling airflow passes through the separation rib, the strength of the cold air vortex generated under the influence of the separation rib is weakened, so that the interaction of the lip falling vortex and the cold air vortex is weakened, and the air film cooling efficiency of the surface of the separation rib is improved. The invention has reasonable design and simple structure, and the inclined slits are arranged on the side wall surface of the partition rib, so that the invention not only has good heat transfer and cooling characteristics, but also has better processing integration and better practicability.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
The foregoing and/or additional aspects and advantages of the invention will become apparent and may be better understood from the following description of embodiments taken in conjunction with the accompanying drawings in which:
fig. 1: the tail edge of the invention is provided with a turbine guide vane structure isometric view penetrating through the inclined seam on the rib; (a) example 1, (b) example 2, (c) example 3;
fig. 2: the tail edge of the turbine guide vane structure is provided with a top view of the turbine guide vane structure penetrating through the inclined seam on the rib;
fig. 3: the tail edge of the invention is provided with a cross section of the turbine guide vane structure with a rib penetrating through the inclined seam; (a) example 1, (b) example 2, (c) example 3;
fig. 4: a turbine guide vane schematic diagram of a turbine guide vane structure with a rib on the tail edge penetrating through the inclined seam; (a) example 1, (b) example 2, (c) example 3;
in the figure: 1. the blade comprises a blade tail edge pressure surface 2, a separation rib 3, a tail edge half split joint surface 4, an inclined joint 5 on the rib, a blade tail edge suction surface 6, a cold flow inlet 7, a cold air outflow joint 8, a tail edge area 9, a blade pressure surface 10, a blade suction surface 11 and a blade matrix.
Detailed Description
The following detailed description of embodiments of the invention is exemplary and intended to be illustrative of the invention and not to be construed as limiting the invention.
Referring to FIGS. 1, 2, 3, and 4, a turbine blade trailing edge cooling structure with a through slot in the rib and its placement in a turbine blade will be described in detail.
The turbine guide vane structure with the through seam on the rib at the tail edge is characterized in that a tail edge half split seam structure is arranged in the tail edge area of the turbine blade, part of the wall surface of the pressure surface of the tail edge of the turbine blade is cut off, and only the wall surface on one side of the suction surface and a plurality of separation ribs are reserved. Cold air outflow slot height h of half split slot tail edge cooling structure 1 The value range of the air conditioner is 0.3-0.8 mm, and the width l of the cold air outflow slot of the tail edge 1 Height h of cold air outflow slot at tail edge 1 The ratio range is 3-10; adjacent twoSpan-wise pitch p of trailing edge cold air outflow slot 1 The range of the value of (2) is 1.8-4.8 mm; the thickness t of the lip plate of the half split joint structure and the height h of the cold air outflow joint 1 The ratio of (2) is between 0.2 and 1.5, and the half slit inclination angle is between 0 and 15 degrees.
The bottom of the partition rib, which is contacted with the wall surface of the half split seam, is provided with a plurality of through seams which laterally penetrate through the partition rib, and the through seams are used for communicating the space between the tail edge half split seam surfaces at two sides of the partition rib. After the tail edge cooling air flow flows out of the tail edge cooling air cavity, the cooling air flow is ejected from the outflow slot, covers the half split slot wall surface to form a cooling air film, and also flows through the through slot penetrating through the separation rib to cool the inside of the separation rib.
As a further preferable scheme, an included angle of 10-15 degrees is formed between the slotting direction of the penetrating slot on the partition rib and the normal line of the side surface of the partition rib on the plane parallel to the half split slot surface of the tail edge, so that an inclined penetrating slot is formed, and the cooling air flow on one side of the partition rib flows to the other side of the partition rib more smoothly through the inclined penetrating slot. The cooling air flow flowing through the inclined through seam penetrating through the partition rib can weaken cold air corner vortex generated under the influence of the partition rib, weaken the interaction of the shedding vortex and the corner vortex, and strengthen the air film cooling efficiency near the partition rib.
The cross section of the through seam in the direction perpendicular to the slotting direction is rectangular, parallelogram or right triangle. The following is illustrated by three examples:
implementation example 1:
in the embodiment, a certain type of turbine guide vane with a rib penetrating through an inclined seam is arranged at the tail edge, cooling air flows into a turbine vane tail edge cooling structure with a rib penetrating through the inclined seam through a cold flow inlet 6, and the cooling air flows through a cold air outflow seam 7 and then covers a tail edge half split seam surface 3 to form a cooling air film, so that a pressure surface 1 of the tail edge of the vane is cooled, and the cooling air flows on the surfaces of different half split seam units are communicated through the inclined seam due to the action of three rectangular inclined seams 4 on a separation rib in the process of flowing downstream of the cold air, so that cold air vortex generated under the influence of the separation rib is weakened, the interaction of a lip falling vortex and the cold air vortex is weakened, and the air film cooling efficiency of the surface of the separation rib is improved. The cooling air flow enhances the convection heat exchange effect through the internal flow when entering the oblique slits on the ribs, and leads out the heat of the side wall and the inner wall of the separation rib 2, so that the cooling of the separation rib is enhanced while the cooling of the slit surface is not affected.
In this embodiment, the trailing edge half split seam structure has a seam height h 1 0.5mm, width of flow gap l 1 Height h of outflow slot 1 The ratio is 4; span-wise spacing p of two adjacent outflow slits 1 3mm; each partition rib is provided with three independent rectangular oblique slits, the included angle between the slit direction of the oblique slits, namely the central line direction and the normal direction of the side surface of the partition rib is 10 degrees, the left edge of the air inflow opening of the first oblique slit section along the cold air flow direction on the partition rib coincides with the starting line of the partition rib, and the width l of the oblique slits 2 Height h of the oblique seam is 0.25mm 2 And width l 2 The ratio of (2) and the pitch p of the oblique slits 2 Is 0.815mm. Implementation example 2:
in the embodiment, a certain type of turbine guide vane with a rib penetrating through an inclined seam is arranged at the tail edge, cooling air flows into a turbine vane tail edge cooling structure with a rib penetrating through the inclined seam through a cold flow inlet 6, and the cooling air flows through a cold air outflow seam 7 and then covers a tail edge half split seam surface 3 to form a cooling air film, so that a pressure surface 1 of the tail edge of the vane is cooled, and the cooling air flows on the surfaces of different half split seam units are communicated through the inclined seam due to the effect of a parallelogram inclined seam 4 on a separation rib, so that cold air vortex generated due to the influence of the separation rib is weakened, the interaction of a lip falling vortex and the cold air vortex is weakened, and the air film cooling efficiency of the surface of the separation rib is improved. The cooling air flow enhances the convection heat exchange effect through the internal flow when entering the oblique slits on the ribs, and leads out the heat of the side wall and the inner wall of the separation rib 2, so that the cooling of the separation rib is enhanced while the cooling of the slit surface is not affected.
In this embodiment, the trailing edge half split seam structure has a seam height h 1 0.5mm, width of flow gap l 1 Height h of outflow slot 1 The ratio is 4; span-wise spacing p of two adjacent outflow slits 1 3mm; each partition rib is provided with a parallelogram type inclined seam, and the central line of the inclined seamThe included angle between the direction and the normal direction of the side surface of the separation rib is 10 degrees, the left lower end point of the air flow inlet of the parallelogram inclined seam on each separation rib is positioned on the starting line of the separation rib, and the width l of the section of the inclined seam 2 The height h of the oblique seam is 1.575mm 2 Is 0.5mm.
Implementation example 3:
in the embodiment, a certain type of turbine guide vane with a rib and an inclined seam penetrating through the rib is arranged at the tail edge, cooling air flows into a turbine vane tail edge cooling structure with the rib and the inclined seam penetrating through the cold flow inlet 6, and the cooling air flows through the cold air outflow seam 7 and then covers the tail edge half split seam surface 3 to form a cooling air film, so that the pressure surface 1 of the tail edge of the vane is cooled, and the cooling air flows on the surfaces of different half split seam units are communicated through the inclined seam due to the action of the triangular inclined seam 4 on the separation rib, so that cold air vortex generated due to the influence of the separation rib is weakened, the interaction of lip falling vortex and cold air vortex is weakened, and the air film cooling efficiency on the surface of the separation rib is improved. The cooling air flow enhances the convection heat exchange effect through the internal flow when entering the oblique slits on the ribs, and leads out the heat of the side wall and the inner wall of the separation rib 2, so that the cooling of the separation rib is enhanced while the cooling of the slit surface is not affected.
In this embodiment, the trailing edge half split seam structure has a seam height h 1 0.5mm, width of flow gap l 1 Height h of outflow slot 1 The ratio is 4; span-wise spacing p of two adjacent outflow slits 1 3mm; each partition rib is provided with a triangular inclined seam, the included angle between the central line direction of the inclined seam and the normal line direction of the side surface of the partition rib is 10 degrees, the left edge of the airflow inlet of the triangular inclined seam on each partition rib is coincident with the starting line of the partition rib, and the width l of the inclined seam 2 Height h of the oblique seam is 1.875mm 2 Is 0.5mm.
Although embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations may be made in the above embodiments by those skilled in the art without departing from the spirit and principles of the invention.
Claims (6)
1. The turbine guide vane structure is characterized in that a turbine blade tail edge area is provided with a tail edge half split joint structure, wherein part of the wall surface of the pressure surface of the tail edge of the turbine blade is cut off, and only the wall surface on one side of a suction surface and a plurality of separation ribs are reserved;
the method is characterized in that: the bottom of the partition rib, which is contacted with the half split seam wall surface, is provided with a plurality of through seams which laterally penetrate through the partition rib, and the through seams are used for communicating the tail edge half split seam surface spaces at two sides of the partition rib;
under the condition that the flow of the cold air is not increased, after the tail edge cooling air flows out of the tail edge cold air cavity, the cooling air is ejected from the outflow slot, covers the wall surface of the half split slot to form a cooling air film, and flows through the through slot penetrating through the separation rib to cool the inside of the separation rib;
the parting direction of the through seam on the parting rib and the normal line of the side surface of the parting rib form an included angle on a plane parallel to the surface of the tail edge half split seam, so that the cooling air flow on one side of the parting rib flows to the other side of the parting rib more smoothly through the inclined through seam;
the cooling air flow flowing through the inclined through seam penetrating through the separation rib can weaken cold air angular vortex generated under the influence of the separation rib, weaken the interaction of the shedding vortex and the angular vortex, and strengthen the air film cooling efficiency near the separation rib;
on the plane parallel to the surface of the tail edge half split joint, the included angle between the slotting direction of the through joint and the normal line of the side surface of the separation rib is 10-15 degrees.
2. The turbine vane structure with a through slot on the trailing edge with ribs of claim 1, wherein: the value range of the cold air outflow slot height h 1 of the half split slot tail edge cooling structure is 0.3-0.8 mm, and the ratio of the tail edge cold air outflow slot width l 1 to the tail edge cold air outflow slot height h 1 is 3-10; the value range of the spanwise distance p 1 of the cold air outflow slots of the two adjacent tail edges is 1.8-4.8 mm; the ratio of the thickness t of the lip plate of the half split joint structure to the height h 1 of the cold air outflow joint is between 0.2 and 1.5, and the inclined angle of the half split joint is between 0 and 15 degrees.
3. The turbine vane structure with a through slot on the trailing edge with ribs of claim 1, wherein: the cross section of the through seam in the direction perpendicular to the slotting direction is rectangular, parallelogram or right triangle.
4. A turbine vane structure having a trailing edge with a through slot on the rib as claimed in claim 3, wherein: when the cross section of the penetrating slit in the direction perpendicular to the slotting direction is rectangular, a plurality of rectangular penetrating slits are formed in the same partition rib, the edge of an airflow inlet in the first rectangular penetrating slit along the cooling airflow direction coincides with the starting line of the partition rib, the width l 2 of the single rectangular penetrating slit is 0.25mm, the ratio of the height h 2 of the rectangular penetrating slit to the width l 2 is 2, and the distance p 2 of the rectangular penetrating slit is 0.815mm.
5. A turbine vane structure having a trailing edge with a through slot on the rib as claimed in claim 3, wherein: when the cross section of the penetrating slit in the direction perpendicular to the slitting direction is a parallelogram, a single parallelogram penetrating slit is arranged on the same partition rib, the lower end point of the airflow inlet in the parallelogram penetrating slit is positioned on the starting line of the partition rib, the width l 2 of the parallelogram penetrating slit is 1.575mm, and the height h 2 is 0.5mm.
6. A turbine vane structure having a trailing edge with a through slot on the rib as claimed in claim 3, wherein: when the cross-sectional shape of the through slit in the direction perpendicular to the slit is a right triangle, one of the right-angle sides is the bottom side of the partition rib, the length l 2 is 1.875mm, and the other right-angle side of the air flow inlet coincides with the start line of the partition rib, and the height h 2 is 0.5mm.
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| CN202110391292.6A CN113107607B (en) | 2021-04-13 | 2021-04-13 | Turbine guide vane structure with through-slit on rib at tail edge |
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| CN202110391292.6A CN113107607B (en) | 2021-04-13 | 2021-04-13 | Turbine guide vane structure with through-slit on rib at tail edge |
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| CN113107607B true CN113107607B (en) | 2023-05-26 |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1188401A (en) * | 1966-02-26 | 1970-04-15 | Gen Electric | Cooled Vane Structure for High Temperature Turbines |
| CN104791020B (en) * | 2015-04-23 | 2016-06-15 | 华能国际电力股份有限公司 | A kind of have the gas turbine blade longitudinally intersecting rib cooling structure |
| KR101797370B1 (en) * | 2016-07-04 | 2017-12-12 | 두산중공업 주식회사 | Gas Turbine Blade |
| CN107013255A (en) * | 2017-06-01 | 2017-08-04 | 西北工业大学 | A kind of turbine blade tail flow-disturbing with continuous straight rib partly splits seam cooling structure |
| CN111502771A (en) * | 2020-04-24 | 2020-08-07 | 哈尔滨工程大学 | Tail edge half-splitting seam cooling structure with slit straight ribs |
| CN112459852B (en) * | 2020-12-14 | 2021-09-24 | 北京航空航天大学 | Be applied to two water conservancy diversion rib water conservancy diversion structures of turbine blade trailing edge half-splitting seam |
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