CN202417610U - Turbine blade tailing edge press seam cooling structure and turbine blade with same - Google Patents
Turbine blade tailing edge press seam cooling structure and turbine blade with same Download PDFInfo
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- CN202417610U CN202417610U CN2011205455166U CN201120545516U CN202417610U CN 202417610 U CN202417610 U CN 202417610U CN 2011205455166 U CN2011205455166 U CN 2011205455166U CN 201120545516 U CN201120545516 U CN 201120545516U CN 202417610 U CN202417610 U CN 202417610U
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- blade
- turbine blade
- trailing edge
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- cooling structure
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Abstract
The utility model provides a turbine blade tailing edge press seam cooling structure comprising a blade tailing edge suction force edge (1) and a blade tailing edge pressure edge (2), a plurality of openings (3) are formed in the joint (5) of the blade tailing edge suction force edge (1) and the blade tailing edge pressure edge (2), the blade tailing edge pressure edge (2) is flush with the joint (5), and a plurality of grooves (4) are formed in the positions of the joint (5) corresponding to the openings (3) and on the blade tailing edge suction force edge (1) in the direction of air outlet. The utility model further provides a turbine blade provided with the cooling structure. Due to the formation of grooves at the outlet of the half press seam on the tailing edge of the turbine blade, the area for heat exchange between the blade tailing edge part and cold air is increased, thereby further reducing the temperature of the blade tailing edge; and at the same time, the grooves are of a structure that is in the direction of air flow and excellent in manufacturability, thereby having no influence on flow resistance.
Description
Technical field
The utility model relates to a kind of turbine blade cooling structure, more specifically, relates to the turbine blade that a kind of turbine blade tail is split the seam cooling structure and had this cooling structure.
Background technique
Aero-turbine produces the gas of extreme temperatures in the firing chamber, can change into mechanical energy through turbine blade interior, so turbine blade is bearing very big temperature.Along with developing by leaps and bounds of aero engine technology, no matter inlet temperature all significantly improves before aero-engine compressor pressure ratio and the turbine, and this must cause the suffered heat load of turbine blade sharply to increase, and makes it bear very serious thermal stress.The too high meeting of temperature all has adverse influence to the performance and the life-span of turbine blade, although present high temperature material has been obtained very big achievement, the temperature with respect to the gas that comes out from the firing chamber also is nowhere near.At present, the trial of attempting to seek resistant to elevated temperatures blade material is all not too successful on cost and actual effect.Therefore, must take other measure to make the turbine blade of cooled engine.
The research of using the widest turbine engine blade type of cooling at present mainly concentrates on blade inlet edge and blade middle part, and turbine blade is adopted advanced efficient reinforcement cooling technology.A kind of typical mode is to adopt to impact to cool off the cooled blade leading edge, and cold air to the blade internal face, effectively cools off internal face with very high velocity shock through tiny impact opening.Impact cooling and generally be used on the leading edge of combustion gas guide vane and turbine blade, spray cooled gas with cooling by force to the leading edge of blade by the inside of hollow blade.Impacting cooled gas can flow out from the hole of combustion gas guide vane and turbine blade leading edge, is driven on the surface of blade by combustion gas and forms the cooling air film.But the cooling blast hole of holding at blade inlet edge can make blade be difficult to more make, and these holes also can cause stress to be concentrated, and life-span of blade is had a negative impact.
At present, also lacking really effective means comes blade trailing edge is cooled off.Therefore the blade trailing edge area thickness is thinner, and the outer coefficient of heat transfer is big, is one of the most difficult cooled zones of turbine blade, and maximum temperature usually appears at here.The normal form that splits seam that adopts of the cooling of blade trailing edge, in general, the cold effect of form of splitting seam entirely is higher.But because development of Aeroengines; Requirement to turbine efficiency improves constantly, and this just causes the continuous attenuation of thickness of turbine blade tail, process the structure of splitting seam entirely at very thin blade trailing edge; Difficulty is very big, and the methods for cooling of therefore partly splitting seam has just obtained using more widely.But because the exit flow of partly splitting crack structure that adopts at present and the blending of main combustion gas, temperature is higher, has therefore caused the cooling effect of blade trailing edge not good.
The model utility content
The purpose of the utility model is intended to increase the heat exchange area that trailing edge is partly split crack structure, strengthens the heat exchange of blade trailing edge, reduces the maximum temperature and the mean temperature of blade, thereby improves the working life of blade.
Above-mentioned purpose is to split the seam cooling structure through a kind of engine turbine blade trailing edge of the utility model to realize; What it comprised trailing edge partly splits crack structure; Promptly comprise blade trailing edge suction limit and blade trailing edge pressure limit; Joint on blade trailing edge suction limit and blade trailing edge pressure limit is provided with a plurality of openings, and blade trailing edge pressure limit is concordant with the joint, is on the outgassing direction of upper edge, blade trailing edge suction limit corresponding to the position of each opening in the joint to be furnished with a plurality of grooves; Be used for making cooled gas to flow out, and cooled blade trailing edge suction limit.
Advantageously, a plurality of grooves extend to the least significant end on blade trailing edge suction limit from the joint.
Advantageously, the width of each groove is approximately equal to the spacing between the adjacent grooves.
The utility model also provides a kind of turbine blade, includes like the described turbine blade tail of the utility model in its end and splits the seam cooling structure, and it is integrally formed that this turbine blade tail is split seam cooling structure and turbine blade body.
According to the utility model, partly to split the cooling blast direction of seam along blade trailing edge and arrange a plurality of grooves, the axis of groove is parallel with airflow direction.Like this; When cooling air when blade trailing edge is split the seam groove structure and is flowed out, this part cooling air increases with the heat exchange area of blade trailing edge part, and cold air is difficult in groove and very fast blending is carried out in the combustion gas of outside; Thereby the temperature of blade trailing edge cooling air can keep lower level; Simultaneously, because the increase of the flowing space, the cold air pressure loss of the feasible blade trailing edge of flowing through reduces.
The utility model adds some grooves through partly split the seam outlet at turbine blade tail, has increased the heat exchange area of blade trailing edge part with cold air, thereby further reduces the temperature of blade trailing edge; Simultaneously and since adopt following current to groove structure, to not influence of flow resistance, and the manufacturability of this structure is also relatively good, is a kind of effective blade trailing edge forced heat exchanging cooling structure therefore.
Description of drawings
Fig. 1 is the schematic representation according to a mode of execution of the turbine blade of the utility model, and said turbine blade has the turbine blade tail of the utility model and splits the seam cooling structure;
Fig. 2 is for splitting the partial schematic diagram of seam cooling structure according to the turbine blade tail of the utility model;
Fig. 3 is the sectional view of turbine blade shown in Figure 1, and said turbine blade has the turbine blade tail of the utility model and splits the seam cooling structure.
Embodiment
Following this paper will at length provide the description of the preferred embodiment of the utility model with reference to accompanying drawing.
The typical blade trailing edge of the utility model is split the seam cooling structure shown in Fig. 1-3.Blade trailing edge is split the seam cooling structure and is comprised blade trailing edge suction limit 1 and blade trailing edge pressure limit 2; 1 is provided with a plurality of openings 3 with the joint 5 on blade trailing edge pressure limit 2 on said blade trailing edge suction limit; Wherein blade trailing edge pressure limit 2 is concordant with joint 5, and 5 positions corresponding to each opening 3 are in blade trailing edge suction limit 1 upper edge outgassing direction and are processed with a plurality of grooves 4 in the joint.
The axis of groove 4 is parallel with the cooling blast direction, and the height of groove 4 and width setting will guarantee that the wall thickness of blade can satisfy the requirement of intensity.Typically, can approximately equal with the spacing of the width of each opening 3 corresponding groove 4 and adjacent grooves 4.As shown in Figure 3, groove 4 from the joint 5 extend to blade trailing edge suction limit 1 least significant end.
The described blade trailing edge of the utility model is split the seam cooling structure and can be applied in the various turbine blades; Wherein a kind of aero engine turbine blades of typical application has been shown among Fig. 1,3; Include like the described turbine blade tail of the utility model in the end of blade trailing edge and to split the seam cooling structure, this turbine blade tail split the seam cooling structure and turbine blade body 6 integrally formed.
When cooling blast when blade trailing edge is split the seam cooling structure and is flowed out; The heat exchange area of this part cooling blast and blade trailing edge obtains increasing; And cold air mobile in groove 4 makes its be difficult for carrying out very fast blending with combustion gas of outside, can reduce the temperature of blade trailing edge cooling air, simultaneously; Because the increase of the flowing space, the pressure loss of the feasible blade trailing edge of flowing through reduces.
The utility model is not limited to above-mentioned embodiment, and can change in every way based on the purport of the utility model or improve, and these changes and improve and not break away from the scope of liking the utility model that requires in the claim enclosed.
Claims (4)
1. a turbine blade tail is split the seam cooling structure; Comprise blade trailing edge suction limit (1) and blade trailing edge pressure limit (2); Joint (5) on said blade trailing edge suction limit (1) and said blade trailing edge pressure limit (2) is provided with a plurality of openings (3); Wherein said blade trailing edge pressure limit (2) is concordant with said joint (5), is in upper edge, said blade trailing edge suction limit (1) outgassing direction in said joint (5) corresponding to the position of each said opening (3) and is processed with a plurality of grooves (4).
2. turbine blade tail according to claim 1 is split the seam cooling structure, it is characterized in that, said a plurality of grooves (4) extend to the least significant end on said blade trailing edge suction limit (1) from said joint (5).
3. turbine blade tail according to claim 1 and 2 is split the seam cooling structure, it is characterized in that, said a plurality of grooves (4) width separately equals the spacing between adjacent said a plurality of grooves (4).
4. turbine blade includes like the described turbine blade tail of one of claim 1 to 3 in its end and to split the seam cooling structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205455166U CN202417610U (en) | 2011-12-22 | 2011-12-22 | Turbine blade tailing edge press seam cooling structure and turbine blade with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205455166U CN202417610U (en) | 2011-12-22 | 2011-12-22 | Turbine blade tailing edge press seam cooling structure and turbine blade with same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202417610U true CN202417610U (en) | 2012-09-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205455166U Expired - Lifetime CN202417610U (en) | 2011-12-22 | 2011-12-22 | Turbine blade tailing edge press seam cooling structure and turbine blade with same |
Country Status (1)
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| CN (1) | CN202417610U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103046967A (en) * | 2012-12-27 | 2013-04-17 | 中国燃气涡轮研究院 | Turbine air cooling blade |
| CN105569740A (en) * | 2016-03-03 | 2016-05-11 | 哈尔滨工程大学 | Turbine with blade wavy concave tailing edge slot cooling structures |
| 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 |
| CN111502770A (en) * | 2020-04-24 | 2020-08-07 | 哈尔滨工程大学 | Cactus-imitating half-splitting-slit cooling structure suitable for high-temperature turbine blades |
| CN112554962A (en) * | 2020-12-02 | 2021-03-26 | 中国航发沈阳发动机研究所 | Cooling structure of turbine guide cooling blade flange tail end |
| CN115093231A (en) * | 2022-06-23 | 2022-09-23 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite guide vane with tail edge cleft and preparation method thereof |
-
2011
- 2011-12-22 CN CN2011205455166U patent/CN202417610U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103046967A (en) * | 2012-12-27 | 2013-04-17 | 中国燃气涡轮研究院 | Turbine air cooling blade |
| CN105569740A (en) * | 2016-03-03 | 2016-05-11 | 哈尔滨工程大学 | Turbine with blade wavy concave tailing edge slot cooling structures |
| 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 |
| CN111502770A (en) * | 2020-04-24 | 2020-08-07 | 哈尔滨工程大学 | Cactus-imitating half-splitting-slit cooling structure suitable for high-temperature turbine blades |
| CN112554962A (en) * | 2020-12-02 | 2021-03-26 | 中国航发沈阳发动机研究所 | Cooling structure of turbine guide cooling blade flange tail end |
| CN112554962B (en) * | 2020-12-02 | 2022-11-22 | 中国航发沈阳发动机研究所 | Cooling structure of turbine guide cooling blade flange tail end |
| CN115093231A (en) * | 2022-06-23 | 2022-09-23 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite guide vane with tail edge cleft and preparation method thereof |
| CN115093231B (en) * | 2022-06-23 | 2023-09-01 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite guide vane with trailing edge split joint and preparation method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120905 |