CN212130558U - Turbine blade structure with truncated ribs and semi-split seam at tail edge - Google Patents
Turbine blade structure with truncated ribs and semi-split seam at tail edge Download PDFInfo
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- CN212130558U CN212130558U CN202020710288.2U CN202020710288U CN212130558U CN 212130558 U CN212130558 U CN 212130558U CN 202020710288 U CN202020710288 U CN 202020710288U CN 212130558 U CN212130558 U CN 212130558U
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Abstract
The utility model provides a turbine blade structure with a truncated rib and a semi-split seam at the tail edge, which comprises a blade front edge, a blade suction surface, a blade pressure surface, a surface of the semi-split seam at the tail edge, a separation rib and a lip plate; cutting off partial pressure side wall surfaces at the tail edge area of the blade, reserving suction side wall surfaces at the tail edge area of the blade, and forming a plurality of tail edge half-slit structures with the partition ribs; a plurality of cutting ribs are arranged on the wall surface of the trailing edge half-splitting seam, and the length direction of each cutting rib is perpendicular to the incoming flow direction of the low-temperature gas; a row of truncated ribs are formed by a plurality of truncated ribs along the length direction of the truncated ribs; the length of each cutting rib is 1/4-1/3 of the width of the cold air rectangular outlet, and the height of each cutting rib is 1/5-1/2 of the height of the cold air rectangular outlet; along the incoming flow direction of low-temperature gas, the ratio of the distance between two adjacent rows of truncated ribs to the degree of the truncated ribs is 4-10. The utility model discloses effectively reduced the surface temperature of blade pressure side and suction side in the trailing edge department, realized improving the purpose of the semi-slot cooling structure comprehensive cooling effect of trailing edge.
Description
Technical Field
The utility model belongs to the technical field of gas turbine blade cooling, concretely relates to turbine blade structure of trailing edge half-splitting seam with cut rib.
Background
The thrust characteristics and the cycle efficiency of the turbine, which is an important component of the gas turbine engine, can be effectively improved by increasing the temperature before the gas turbine. Research reports show that under the condition of keeping the size of an engine unchanged, the thrust of the engine can be increased by 8-13% when the temperature of the inlet of the turbine is increased by 56 ℃, and the cycle efficiency of the engine can be increased by 2-4%, so that the continuous increase of the temperature before the turbine is one of the development directions of the gas turbine, and in order to ensure that the turbine blade has enough safety reliability and service life in an ultralimit high-temperature service environment, efficient cooling measures must be taken.
The gas velocities of the pressure surface and the suction surface reach a relatively high value at the trailing edge of the turbine blade and are in a turbulent state, so that the convective heat transfer intensity of the gas at the trailing edge is very high. However, with the continuous increase of the gas temperature of the aero-engine, the cooling capacity of the traditional half-slit structure gradually approaches to the limit, and the ablation phenomenon of the trailing edge of the high-pressure turbine blade frequently occurs. Therefore, the efficient cooling structure for the trailing edge of the turbine blade is developed and innovated, the cooling effect is further improved on the basis of not increasing the amount of cold air, and the development of an advanced high-performance aircraft engine is very necessary and meaningful.
In the document "influence of turbulence columns on the convective heat transfer characteristics of the trailing edge of the blade" (report of the aeronautical dynamics, 2007, 10 th, 18-22 pages), an author uses an infrared temperature measurement technology to measure the influence of an internal cooling channel distributed with four different turbulence columns (cylindrical, elliptical, water drop type I, water drop type II) on the heat transfer coefficient of the trailing edge of the turbine blade, and research results show that the air film cooling convective heat transfer coefficient of the trailing edge of the blade of a cylindrical turbulence column is the largest under large air blowing. Although the heat exchange coefficient of the trailing edge of the turbine blade can be enhanced by arranging the cylindrical turbulence columns in the internal cooling channels, the increasing temperature of the turbine head requires a more efficient cooling structure for the trailing edge of the blade, so that the development of the more efficient cooling structure for the trailing edge is very necessary on the basis of not increasing the amount of cold air.
Disclosure of Invention
In order to further promote the cooling effect of blade trailing edge, the utility model provides a turbine blade structure of trailing edge half-splitting seam with cut the rib.
The technical scheme of the utility model is that:
the turbine blade structure with the truncated rib and the semi-split seam at the tail edge comprises a blade front edge, a blade suction surface, a blade pressure surface, a cold flow inlet, a cooling cavity inside the blade, the surface of the semi-split seam at the tail edge, a partition rib and a lip plate;
cutting off partial pressure side wall surfaces at the tail edge area of the blade, reserving suction side wall surfaces at the tail edge area of the blade, and forming a plurality of tail edge half-slit structures with the partition ribs;
the low-temperature gas for cooling the surface of the trailing edge half-split seam is supplied from a cooling cavity inside the blade through a cold flow inlet, the low-temperature gas can be sprayed out from a rectangular outlet formed between the partition ribs, the sprayed gas covers the surface of the half-split seam with the partition ribs, high-temperature gas flowing through the surface of the half-split seam from the upper side of the pressure surface of the blade can be isolated from the surface of the half-split seam, and meanwhile, the suction side wall surface of the blade is cooled through heat conduction;
the height ratio of a rectangular outlet formed between the height of the lip plate and the separating rib in the half-splitting seam structure is 0.2-1.5, and an included angle between the main flow direction of the pressure side in the half-splitting seam structure and the flow direction of cold air is 5-15 degrees;
the method is characterized in that: a plurality of cutting ribs are arranged on the wall surface of the trailing edge half-splitting seam, and the length direction of each cutting rib is perpendicular to the incoming flow direction of the low-temperature gas; a row of truncated ribs are formed by a plurality of truncated ribs along the length direction of the truncated ribs; the length of each cutting rib is 1/4-1/3 of the width of the cold air rectangular outlet, and the height of each cutting rib is 1/5-1/2 of the height of the cold air rectangular outlet; along the incoming flow direction of low-temperature gas, the ratio of the distance between two adjacent rows of truncated ribs to the degree of the truncated ribs is 4-10.
Furthermore, along the incoming flow direction of the low-temperature gas, the total row number of the truncated ribs arranged on the surface of the half-splitting seam is four, and the arrangement mode is in a sequential row or a staggered row.
Advantageous effects
The utility model has the advantages that: the structure of the cut rib is arranged on the surface of the semi-splitting seam, so that the surface of the semi-splitting seam at the tail edge can be made, the heat exchange area is increased through the turbulent flow structure on the premise of not increasing the amount of cold air, meanwhile, the disturbance effect on fluid is increased, the heat convection effect on the surface of the semi-splitting seam is improved, and meanwhile, the air film cooling efficiency reduction amount on the surface of the semi-splitting seam is smaller, so that the surface temperature of the pressure side and the suction side of the blade at the tail edge is effectively reduced, and the purpose of improving the comprehensive cooling effect of the cooling structure of the semi-splitting seam at the tail edge is finally realized. And simultaneously, the utility model provides a cut novel turbine blade trailing edge cooling structure of rib vortex structure only arranges simple rib that cuts on the surface at half split seam, and this makes it have good processing implementability, can make things convenient for it to be applied to in various turbine blade's the trailing edge cooling design.
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 above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is an axonometric view of the turbine blade structure of the trailing edge half-slit with truncated ribs of the present invention.
Fig. 2 is a partial enlarged view of the trailing edge region of a turbine blade structure having a trailing edge half-split with a truncated rib according to the present invention.
FIG. 3 is a Knoop number ratio distribution cloud diagram of the turbulent flow semi-splitting slit surface with the truncated rib turbulent flow structure and the smooth semi-splitting slit surface.
FIG. 4 is a cloud diagram and a streamline diagram of the surface velocity distribution of the turbulent semi-slot with the turbulent structure of the truncated rib.
In the figure: 1 blade leading edge, 2 blade suction surfaces, 3 blade pressure surfaces, 4 blade internal cooling cavities, 5 tail edge areas, 6 cold air inlets, 7 cutoff ribs and 8 half-split seam surfaces.
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
Example 1:
the embodiment is a turbine blade structure with a truncated rib and a half-split trailing edge. Referring to fig. 1 to 4, the turbine blade structure of the trailing edge half-slit with the cut-off rib in the present embodiment is applied to the trailing edge region of the turbine blade, and includes a blade leading edge, a blade suction surface, a blade pressure surface, a blade internal cooling cavity, a trailing edge region, a cold air inlet, a cut-off rib, a half-slit surface, a partition rib, and a lip.
In order to reduce the thickness of the trailing edge, a part of pressure side wall surface is cut off in the trailing edge area of the blade, a suction side wall surface in the trailing edge area of the blade is reserved, and a plurality of trailing edge half-slit structures are formed by the suction side wall surface and the partition ribs; the low-temperature gas for cooling the surface of the semi-split seam of the trailing edge is supplied by the cooling cavity in the blade, the low-temperature gas can be sprayed out from the rectangular outlet formed between the partition ribs, the sprayed gas covers the surface of the semi-split seam with the partition ribs, high-temperature gas flowing through the surface of the semi-split seam from the upper side of the pressure surface of the blade can be separated from the surface of the semi-split seam, the trailing edge is prevented from being ablated by the high-temperature gas, meanwhile, the temperature of the wall surface of the suction side wall of the blade is influenced by the high-temperature gas, and the temperature of the wall surface is higher than that of the surface of the semi-.
The height ratio of the rectangular outlet formed between the lip plate and the separating rib in the half-split slit structure is 0.5, and the included angle between the main flow direction of the pressure side in the half-split slit structure and the cold air flowing direction is 15 degrees.
4 rows of cut-off ribs are arranged on the wall surface of the tail edge half-splitting seam corresponding to the single rectangular outlet, and the length direction of each cut-off rib is perpendicular to the incoming flow direction of the low-temperature gas; the arrangement mode is staggered, and each row of the truncated ribs consists of 1 to 2 truncated ribs; the length of the single cutting rib is 1/4 of the width of the cold air rectangular outlet, and the height of the cutting rib is 1/5 of the height of the cold air rectangular outlet; along the incoming flow direction of the low-temperature gas, the ratio of the distance between two adjacent rows of the truncated ribs to the degree of the truncated ribs is 5.
In the embodiment, low-temperature gas from the cooling cavity in the blade enters through the cold air inlet and is sprayed out from the rectangular outlet formed by the partition ribs, and the mixing phenomenon is generated between the surface of the semi-split seam distributed with the partition ribs and high-temperature gas passing through the pressure surface of the blade. The cutting ribs are arranged on the surface of the tail edge half-splitting seam, so that the cooling fluid on the surface of the half-splitting seam is separated in a flowing mode, and the fluid is attached again, the flow structure of the wall surface close to the surface of the half-splitting seam is changed due to the existence of the cutting ribs, meanwhile, the heat exchange area of the surface of the half-splitting seam is increased, the convection heat exchange coefficient of the surface of the half-splitting seam and the cooling fluid is enhanced, and the comprehensive cooling effect of the tail edge is improved.
Fig. 3 and 4 show a knoop-zel number ratio distribution cloud chart, a surface velocity distribution cloud chart and a flow chart of a turbulent semi-split slit surface and a smooth semi-split slit surface of a turbulent flow semi-split slit structure distributed with truncated ribs, and the figures show that jet flows through an intercostal broken section, most of the air flow is contracted and converged to flow out from a gap of the intercostal broken section or the truncated section due to the reduction of the flow area, so that the jet speed is accelerated, the downstream of the accelerated jet flows winds a backward moving section to truncate the ribs, and larger spanwise backflow vortex is generated behind the ribs, and the turbulent flow effect of the turbulent flow on the outflow jet flow with the gap at the discontinuous ribs is weaker along with the reduction of the length of the truncated ribs at the backward moving section, so that the heat exchange. For the wall surface of the end of the truncated rib, due to the direct impact and turbulence of the wall surface airflow, the heat exchange strength is higher, and the area at the rear part of the rib end is a high heat exchange area. The heat exchange coefficient of the central line accessory of the surface of the half-split seam is relatively low, the heat exchange coefficient of the high heat exchange area at the rear part of the rib end is gradually enhanced along with the increase of the length of the backward-moving section cutting rib, and the range is enlarged. From the Knoop number ratio distribution cloud chart, the heat exchange coefficient of the surface of the half-splitting slit with the truncated ribs is higher than that of the smooth half-splitting slit structure, so that the comprehensive cooling effect of the tail edge can be improved by the novel turbine blade tail edge cooling structure with the truncated rib turbulent flow structure.
Example 2:
the embodiment is a turbine blade structure with a truncated rib and a half-split trailing edge. The turbine blade structure with the trailing edge half-split seam of cutting off the rib in this embodiment is applied to the trailing edge region of turbine blade, including blade leading edge, blade suction surface, blade pressure surface, the inside cooling chamber of blade, the trailing edge region, the air conditioning import cuts off the rib, half-split seam surface, the spacer rib, the lip.
In order to reduce the thickness of the trailing edge, a part of pressure side wall surface is cut off in the trailing edge area of the blade, a suction side wall surface in the trailing edge area of the blade is reserved, and a plurality of trailing edge half-slit structures are formed by the suction side wall surface and the partition ribs; the low-temperature gas for cooling the surface of the semi-split seam of the trailing edge is supplied by the cooling cavity in the blade, the low-temperature gas can be sprayed out from the rectangular outlet formed between the partition ribs, the sprayed gas covers the surface of the semi-split seam with the partition ribs, high-temperature gas flowing through the surface of the semi-split seam from the upper side of the pressure surface of the blade can be separated from the surface of the semi-split seam, the trailing edge is prevented from being ablated by the high-temperature gas, meanwhile, the temperature of the wall surface of the suction side wall of the blade is influenced by the high-temperature gas, and the temperature of the wall surface is higher than that of the surface of the semi-.
The height ratio of the rectangular outlet formed between the lip plate and the separating rib in the half-split slit structure is 0.2, and the included angle between the main flow direction of the pressure side in the half-split slit structure and the cold air flowing direction is 10 degrees.
4 rows of cut-off ribs are arranged on the wall surface of the tail edge half-splitting seam corresponding to the single rectangular outlet, and the length direction of each cut-off rib is perpendicular to the incoming flow direction of the low-temperature gas; the arrangement mode is in order, each row of the truncated ribs consists of 2 truncated ribs; the length of the single cutting rib is 1/3 of the width of the cold air rectangular outlet, and the height of the cutting rib is 1/2 of the height of the cold air rectangular outlet; along the incoming flow direction of the low-temperature gas, the ratio of the distance between two adjacent rows of the truncated ribs to the degree of the truncated ribs is 4.
Example 3:
the embodiment is a turbine blade structure with a truncated rib and a half-split trailing edge. The turbine blade structure with the trailing edge half-split seam of cutting off the rib in this embodiment is applied to the trailing edge region of turbine blade, including blade leading edge, blade suction surface, blade pressure surface, the inside cooling chamber of blade, the trailing edge region, the air conditioning import cuts off the rib, half-split seam surface, the spacer rib, the lip.
In order to reduce the thickness of the trailing edge, a part of pressure side wall surface is cut off in the trailing edge area of the blade, a suction side wall surface in the trailing edge area of the blade is reserved, and a plurality of trailing edge half-slit structures are formed by the suction side wall surface and the partition ribs; the low-temperature gas for cooling the surface of the semi-split seam of the trailing edge is supplied by the cooling cavity in the blade, the low-temperature gas can be sprayed out from the rectangular outlet formed between the partition ribs, the sprayed gas covers the surface of the semi-split seam with the partition ribs, high-temperature gas flowing through the surface of the semi-split seam from the upper side of the pressure surface of the blade can be separated from the surface of the semi-split seam, the trailing edge is prevented from being ablated by the high-temperature gas, meanwhile, the temperature of the wall surface of the suction side wall of the blade is influenced by the high-temperature gas, and the temperature of the wall surface is higher than that of the surface of the semi-.
The height ratio of the rectangular outlet formed between the lip plate and the separating rib in the half-split slit structure is 1.5, and the included angle between the main flow direction of the pressure side in the half-split slit structure and the cold air flowing direction is 5 degrees.
4 rows of cut-off ribs are arranged on the wall surface of the tail edge half-splitting seam corresponding to the single rectangular outlet, and the length direction of each cut-off rib is perpendicular to the incoming flow direction of the low-temperature gas; the arrangement mode is staggered, and each row of the truncated ribs consists of 1 to 2 truncated ribs; the length of the single cutting rib is 1/3 of the width of the cold air rectangular outlet, and the height of the cutting rib is 1/3 of the height of the cold air rectangular outlet; along the incoming flow direction of the low-temperature gas, the ratio of the distance between two adjacent rows of the truncated ribs to the degree of the truncated ribs is 10.
Although embodiments of the present invention have been shown and described, it is to be understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that changes, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art without departing from the principles and spirit of the present invention.
Claims (2)
1. A turbine blade structure with a truncated rib and a semi-split seam at the tail edge comprises a blade front edge, a blade suction surface, a blade pressure surface, a cold flow inlet, a cooling cavity inside the blade, a surface of the semi-split seam at the tail edge, a partition rib and a lip plate;
cutting off partial pressure side wall surfaces at the tail edge area of the blade, reserving suction side wall surfaces at the tail edge area of the blade, and forming a plurality of tail edge half-slit structures with the partition ribs;
the low-temperature gas for cooling the surface of the trailing edge half-split seam is supplied from a cooling cavity inside the blade through a cold flow inlet, the low-temperature gas can be sprayed out from a rectangular outlet formed between the partition ribs, the sprayed gas covers the surface of the half-split seam with the partition ribs, high-temperature gas flowing through the surface of the half-split seam from the upper side of the pressure surface of the blade can be isolated from the surface of the half-split seam, and meanwhile, the suction side wall surface of the blade is cooled through heat conduction;
the height ratio of a rectangular outlet formed between the height of the lip plate and the separating rib in the half-splitting seam structure is 0.2-1.5, and an included angle between the main flow direction of the pressure side in the half-splitting seam structure and the flow direction of cold air is 5-15 degrees;
the method is characterized in that: a plurality of cutting ribs are arranged on the wall surface of the trailing edge half-splitting seam, and the length direction of each cutting rib is perpendicular to the incoming flow direction of the low-temperature gas; a row of truncated ribs are formed by a plurality of truncated ribs along the length direction of the truncated ribs; the length of each cutting rib is 1/4-1/3 of the width of the cold air rectangular outlet, and the height of each cutting rib is 1/5-1/2 of the height of the cold air rectangular outlet; along the incoming flow direction of low-temperature gas, the ratio of the distance between two adjacent rows of truncated ribs to the degree of the truncated ribs is 4-10.
2. The turbine blade structure of claim 1, wherein the trailing edge half-slit comprises: the total row number of the truncated ribs arranged on the surface of the half-splitting seam is four along the incoming flow direction of the low-temperature gas, and the arrangement mode is in a forward row or a staggered row.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020710288.2U CN212130558U (en) | 2020-05-02 | 2020-05-02 | Turbine blade structure with truncated ribs and semi-split seam at tail edge |
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| CN202020710288.2U CN212130558U (en) | 2020-05-02 | 2020-05-02 | Turbine blade structure with truncated ribs and semi-split seam at tail edge |
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| CN202020710288.2U Expired - Fee Related CN212130558U (en) | 2020-05-02 | 2020-05-02 | Turbine blade structure with truncated ribs and semi-split seam at tail edge |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112943379A (en) * | 2021-02-04 | 2021-06-11 | 大连理工大学 | Turbine blade separation transverse rotation re-intersection type cooling structure |
| CN113847102A (en) * | 2021-10-10 | 2021-12-28 | 西北工业大学 | Structure of structural truncated rib for enhancing integral thermal performance |
-
2020
- 2020-05-02 CN CN202020710288.2U patent/CN212130558U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112943379A (en) * | 2021-02-04 | 2021-06-11 | 大连理工大学 | Turbine blade separation transverse rotation re-intersection type cooling structure |
| CN112943379B (en) * | 2021-02-04 | 2022-07-01 | 大连理工大学 | Turbine blade separation transverse rotation re-intersection type cooling structure |
| CN113847102A (en) * | 2021-10-10 | 2021-12-28 | 西北工业大学 | Structure of structural truncated rib for enhancing integral thermal performance |
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Granted publication date: 20201211 |