CN203547803U - Turbine cooling blade with impacting bush - Google Patents
Turbine cooling blade with impacting bush Download PDFInfo
- Publication number
- CN203547803U CN203547803U CN201320789559.8U CN201320789559U CN203547803U CN 203547803 U CN203547803 U CN 203547803U CN 201320789559 U CN201320789559 U CN 201320789559U CN 203547803 U CN203547803 U CN 203547803U
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- blade
- cavity
- impact
- turbine cooling
- dividing plate
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- 238000001816 cooling Methods 0.000 title claims abstract description 55
- 230000003116 impacting effect Effects 0.000 title abstract description 15
- 230000004888 barrier function Effects 0.000 claims description 35
- 238000005336 cracking Methods 0.000 claims description 5
- 238000009826 distribution Methods 0.000 abstract description 11
- 230000000694 effects Effects 0.000 abstract description 4
- 230000000903 blocking effect Effects 0.000 abstract 3
- 238000005192 partition Methods 0.000 abstract 3
- 239000002737 fuel gas Substances 0.000 description 10
- 239000000567 combustion gas Substances 0.000 description 7
- 238000004378 air conditioning Methods 0.000 description 4
- 230000003247 decreasing effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 238000005266 casting Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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Abstract
The utility model relates to a turbine cooling blade with an impacting bush. The turbine cooling blade with the impacting bush comprises a blade body with a cavity, wherein the impacting bush is arranged in the cavity of the blade body, an annular cavity is formed between the impacting bush and the cavity of the blade, at least one radial blocking structure and a plurality of partition plates in the chord direction are arranged in the annular cavity, the annular cavity is divided into a convex blade side cavity and a concave blade side cavity through the radial blocking structure, the annular cavity is divided into a plurality of cavities through the partition plates in the chord direction so that a plurality of flow channels in the chord direction can be formed, and a plurality of front edge impacting holes are formed in the front edge of the impacting bush. According to the turbine cooling blade with the impacting bush, according to the radial distribution of the temperature of incoming gas from the turbine cooling blade and heat exchanger conditions of gas sides of the outer surfaces of a concave blade and a convex blade, the amount of cold air in all the flow channels in the chord direction is adjusted through the partition plates in the chord direction, the flow distribution of the cold air in the concave blade side and the convex blade side is adjusted through the radial blocking structure, and the heat exchange effect on the inner side of the blade is enhanced by adjusting the through-flow area of the front edge impacting holes.
Description
Technical field
The utility model relates to turbogenerator field, relates in particular to a kind of turbine cooling blade that impacts lining that has.
Background technique
In current advanced aero engine, turbine cooling blade fuel gas temperature far exceedes the allowable temperature of blade metallic material, for guaranteeing turbine cooling blade long-term safety, work reliably, need to implement efficient cooling technology to reduce the mean temperature of blade to turbine cooling blade, reduce as far as possible the blade temperature difference, thereby reduce blade thermal stress simultaneously.
As shown in Figure 1, for current common a kind of cooling structure that reduces turborotor mean temperature, blade 1 ' the inside of turbine cooling blade is provided with impacts lining 2 ', and the air-flow entering from the leading edge impact opening 3 ' of impact lining 2 ' flows to trailing edge through the toroidal cavity between blade 1 ' and impact lining 2 ' and splits seam 4 '.The cold air flow of above-mentioned cooling structure distributes wayward, and this is the radially uniformity of interior heat transfer intensity because of blade interior cold air flow influence area, and leaf basin is consistent with the interior heat transfer intensity of blade back; But, it is inhomogeneous that the fuel gas temperature of turbine inlet radially distributes, the combustion gas coefficient of heat transfer of turbine cooling blade outer surface has larger difference at leaf basin, blade back, thereby cause combustion gas inhomogeneous to the heat transfer of blade, through impacting the cooled leaf temperature skewness of lining, near leaf temperature central diameter is higher, blade back temperature drift, and blade local temperature difference is larger, and the intensity of blade cannot meet long-term usage requirement.
Model utility content
For the problems referred to above, the purpose of this utility model is to propose a kind of turbine cooling blade that impacts lining that has, and for adjusting air conditioning quantity, distributes, and leaf temperature is distributed and be tending towards even.
For achieving the above object, the utility model provides a kind of turbine cooling blade that impacts lining that has, it comprises the blade with cavity, in the cavity of described blade, be provided with impact lining, between described impact lining and the cavity of described blade, form toroidal cavity, in described toroidal cavity, be provided with at least one radially barrier structure and some tangential dividing plates, by described radially barrier structure, described toroidal cavity is divided into leaf backside cavity and leaf basin side cavity, by some described tangential dividing plates, described toroidal cavity is divided into some chambeies, and then form some tangential runners, the leading edge of described impact lining is provided with some leading edge impact openings.
Further, described radially barrier structure has two, be list structure, described in two, radially barrier structure is all arranged in the described toroidal cavity of described impact lining leading edge, and be positioned at the both sides of described leading edge impact opening, described in two radially the height of barrier structure and the radial height of described blade consistent.
Further, the appearance profile of described tangential dividing plate and described toroidal cavity adapt along the appearance profile in tangential cross section, each described tangential dividing plate is arranged in described toroidal cavity along the spaced radial of described blade, and described toroidal cavity is divided into some chambeies, and then forms some tangential runners.
Further, described radially barrier structure is the wherein one of cracking in dividing plate, perforate dividing plate, turbulence columns structure.
Further, described in crack and be provided with and crack on dividing plate, described in the crack thickness range of dividing plate be set to 0.3mm～1.0mm, described in the seam wide range that cracks be set to 0.2mm～1.0mm.
Further, on described perforate dividing plate, be provided with some perforates, the thickness range of described perforate dividing plate is set to 0.3mm～1.0mm, and the diameter range of described perforate is set to 0.2mm～1.0mm.
Further, described turbulence columns structure comprises some spaced turbulence columns, and the diameter range of described turbulence columns is set to 0.5mm～2.0mm, and the scope of the radial spacing of described turbulence columns and the diameter ratio of described turbulence columns is set to 1.5～5.
Further, some described tangential dividing plates by described toroidal cavity along described blade be radially divided into 3～10 chambeies, the thickness range of described tangential dividing plate is set to 0.3mm～1.0mm.
Further, the diameter range of described leading edge impact opening is set to 0.4mm～1.5mm, the scope of row's spacing of described leading edge impact opening and the diameter ratio of described leading edge impact opening is set to 2～20, and the scope of the diameter ratio of impact distance and described leading edge impact opening is set to 2～5.
Further, by described radially barrier structure, with described tangential dividing plate, described impact lining is fixedly connected with the cavity inner wall of described blade.
Based on technique scheme, in the cavity of the turbine cooling blade that the utility model provides, be provided with some tangential dividing plates, can be according to the distribution radially of turbine cooling blade incoming flow fuel gas temperature, regulate the flow area of leading edge impact opening, and then adjust the air conditioning quantity in each tangential runner, leaf temperature is distributed and be tending towards even; By radially barrier structure is set in the cavity of turbine cooling blade, can be according to the heat exchange situation of the leaf basin of turbine cooling blade, blade back outer surface combustion gas side, adjustment is positioned at the flow area of the radially barrier structure of blade back side cavity and leaf basin side cavity, and it is more reasonable that the cold air flow that is used in leaf basin, the blade back side of turbine cooling blade distributes; By adjustment, impact the flow area of the leading edge impact opening of lining, make more cold air flow strengthen the heat transfer effect of blade inner side, blade high-temperature area temperature is decreased, thereby reduce the radial symmetry gradient of turbine cooling blade.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, forms the application's a part, and schematic description and description of the present utility model is used for explaining the utility model, does not form improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is turbine cooling blade structural representation of the prior art;
The turbine cooling blade structural representation that Fig. 2 provides for the utility model;
Fig. 3 is the A-A schematic cross-section in Fig. 2;
Fig. 4 is the local enlarged diagram in Fig. 3;
Fig. 5 is the B-B schematic cross-section in Fig. 2;
Fig. 6 is the C-C schematic cross-section in Fig. 4;
The radial barrier structure that Fig. 7 A, Fig. 7 B and Fig. 7 C provide for the utility model is respectively perforate dividing plate, the schematic diagram of dividing plate and turbulence columns structure cracks.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technological scheme in embodiment is clearly and completely described.Obviously, described embodiment is only a part of embodiment of the present utility model, rather than whole embodiments.Based on embodiment of the present utility model, those of ordinary skills are not making the every other embodiment who obtains under creative work prerequisite, all belong to the scope of the utility model protection.
First term used in the utility model is made an explanation.
Tangential: to refer to the outside fuel gas flow direction of turbine cooling blade;
Radially: refer to turbine cooling blade short transverse.
As shown in Figure 2, the utility model provides has that the turbine cooling blade that impacts lining comprises blade 1, impacts lining 2, radially barrier structure 3 and tangential dividing plate 4.
The inside of blade 1 is provided with cavity, and blade 1 comprises leading edge and trailing edge, and the trailing edge of blade 1 is provided with trailing edge and splits seam 11.
As shown in Figure 2 and Figure 3, the appearance profile of the cavity in appearance profile and the blade 1 of impact lining 2 adapts, and impacts lining 2 and is arranged in the cavity of blade 1, impacts between the cavity wall in lining 2 and blade 1 and forms toroidal cavity 5.The leading edge of impacting lining 2 is provided with some row's leading edge impact openings 21.
As shown in Figure 2, Figure 3, Figure 4, radially barrier structure 3 is list structure, its can arrange one, two or more, preferably arrange two, the utility model take arrange two radially barrier structure 3 be elaborated as example.Two radially barrier structure 3 be all arranged in the toroidal cavity 5 that impacts lining 2 leading edges, and be positioned at the both sides of leading edge impact opening 21, toroidal cavity 5 is divided into leaf backside cavity and leaf basin side cavity, by regulating the radially flow area of barrier structure 3, reach the object that regulates the cold air flow that enters leaf basin side and blade back side.Radially the height of barrier structure 3 is consistent with the radial height of blade 1, and radially barrier structure 3 is connected with the cavity inner wall in blade 1 impacting lining 2.
Shown in Fig. 2, Fig. 5, the appearance profile of tangential dividing plate 4 and toroidal cavity 5 adapt along the appearance profile in tangential cross section, tangential dividing plate 4 has several, each tangential dividing plate 4 is radially disposed in toroidal cavity 5 up and down along blade 1, toroidal cavity 5 has been divided into some chambeies, and then has formed some tangential runners.Each tangential dividing plate 4 is connected with the cavity inner wall in blade 1 impacting lining 2.
As shown in Figure 2, each tangential dividing plate 4 and two radially barrier structure 3 are all arranged in toroidal cavity 5, and casting together with blade 1, the height of projection of tangential dividing plate 4 need be able to the fixing lining 2 that impacts, and radially the height of projection of barrier structure 3 need be able to the fixing lining 2 that impacts.Height of projection refers to along the cavity inner wall face in blade 1 to the protruding perpendicular distance of impacting lining 2 outer surface directions.
As shown in Figure 6, Figure 7, radially barrier structure 3 in above-described embodiment can be perforate dividing plate, on perforate dividing plate, be provided with some perforate 31(as shown in Fig. 6, Fig. 7 A), also can be the dividing plate that cracks, crack and be provided with and crack 32(as shown in Figure 7 B on dividing plate), also can be turbulence columns structure, turbulence columns structure comprises that some upper and lower spaced turbulence columns 33(are as shown in Fig. 7 C).
The utility model can radially distribute and actual required cold air flow distribution condition according to incoming flow fuel gas temperature before turbine cooling blade, adjust number and the position of tangential dividing plate 4, adjust the area of efflux size of the leading edge impact opening 21 that impacts lining 2, adjust the radially area of efflux size of barrier structure 3.
As shown in Figure 2, in above-described embodiment, at blade 1 cavity inside of turbine cooling blade, some tangential dividing plates 4 are set, the cavity of blade 1 has radially been divided into 3～10 chambeies up and down at blade 1.The position of tangential dividing plate 4 can evenly determine or inhomogeneous determine, the thickness range of tangential dividing plate 4 can be 0.3mm～1.0mm.
In above-described embodiment, can be according to the distribution radially of turbine cooling blade incoming flow fuel gas temperature, adjustment is arranged in the flow area of the leading edge impact opening 21 of each tangential runner, the diameter range of leading edge impact opening 21 can be 0.4mm～1.5mm, row's spacing of leading edge impact opening 21 and the diameter ratio scope of leading edge impact opening 21 can be 2～20, (impact distance refers to along the axial direction of leading edge impact opening 21 impact distance, from leading edge impact opening 21 to impacting the distance of target surface) with the diameter ratio scope of leading edge impact opening 21 can be 2～5, to can more reasonably distribute the air conditioning quantity of each tangential runner.The position that corresponding fuel gas temperature is higher or the outer coefficient of heat transfer is higher, by tuning up the circulation area of leading edge impact opening 21, make more cold air flow strengthen the heat transfer effect of blade inner side, the part that corresponding fuel gas temperature is low, by turning the circulation area of leading edge impact opening 21 down, reduce cold air flow.
In above-described embodiment, can adjust the radially seam of barrier structure 3 or the circulation area of hole or turbulence columns according to the heat exchange situation of the leaf basin of turbine cooling blade, blade back outer surface combustion gas side, reasonable distribution flows into the cold air flow of leaf basin, blade back, the ill-conditioned position of the outer heat exchange of combustion gas side, can supply with relatively many cold air.Radially barrier structure 3 is when cracking dividing plate, and the thickness range of the dividing plate that cracks can be 0.3mm～1.0mm, and 32 the seam wide range of cracking can be 0.2mm～1.0mm; When radially barrier structure 3 is for perforate dividing plate, the thickness range of perforate dividing plate can be 0.3mm～1.0mm, and the diameter range of perforate 31 can be 0.2mm～1.0mm; When radially barrier structure 3 is turbulence columns structure, the diameter range of turbulence columns 33 can be 0.5mm～2.0mm, and the diameter ratio scope of the radial spacing of turbulence columns 33 and turbulence columns 33 can be 1.5～5.
Impact the adjustment of the circulation area of the leading edge impact opening 21 of lining 2, and cracking or the adjustment of the circulation area of perforate or turbulence columns of barrier structure 3 radially, can realize by kinds of schemes optimization, optimization aim is to make the temperature distribution of turbine cooling blade more even.
By above-mentioned each embodiment, can sum up and obtain the utlity model has following advantage:
1) radial temperature profile of adjustment turbine cooling blade.According to the distribution radially of turbine cooling blade incoming flow fuel gas temperature, utilize the some tangential dividing plate arranging, control the air conditioning quantity in each tangential runner.The position that corresponding fuel gas temperature is higher or the outer coefficient of heat transfer is higher, by tuning up the flow area of leading edge impact opening of the impact lining in the corresponding tangential runner in this position, make more cold air flow strengthen the heat transfer effect of blade inner side, blade high-temperature area temperature is decreased, thereby reduce the radial symmetry gradient of turbine cooling blade.
2) leaf basin, the blade back temperature distribution of adjustment turbine cooling blade.Owing to having increased, crack or radially dividing plate or the turbulence columns structure of perforate, can be according to the heat exchange situation of the leaf basin of turbine cooling blade, blade back outer surface combustion gas side, by adjustment, be positioned at the flow area of the radially barrier structure of blade back side cavity and leaf basin side cavity, the cold air flow of leaf basin side, the blade back side of turbine cooling blade is distributed more reasonable, be that the outer ill-conditioned blade back of heat exchange of combustion gas side has more cold air relatively, thereby make the temperature distribution of leaf basin side, blade back side more even, reduce section temperature difference.
3) further reduce the temperature of turbine cooling blade.Tangential dividing plate, with seam or the radially dividing plate in hole or the setting of turbulence columns structure, increase cold air side heat exchange area, contributes to strengthen cold air heat transfer intensity, further reduces leaf temperature.
4) the fixing lining that impacts.The fixing lining that impacts of the tangential dividing plate that utilization arranges and radially barrier structure, saves the fixing device that needs the impact lining of independent setting in prior art.
In sum, adopt the cooling structure with impact lining that the utility model provides can make the temperature distribution of turbine cooling blade more even, maximum temperature can decrease, turbine cooling blade temperature gradient is more rational, thereby can reduce the thermal stress of turbine cooling blade, to improve the working life of turbine cooling blade.
Finally should be noted that: above embodiment is only in order to illustrate that the technical solution of the utility model is not intended to limit; Although the utility model is had been described in detail with reference to preferred embodiment, those of ordinary skill in the field are to be understood that: still can modify or part technical characteristics is equal to replacement embodiment of the present utility model; And not departing from the spirit of technical solutions of the utility model, it all should be encompassed in the middle of the technological scheme scope of the utility model request protection.
Claims (10)
1. one kind has the turbine cooling blade that impacts lining, it is characterized in that: it comprises the blade with cavity, in the cavity of described blade, be provided with impact lining, between described impact lining and the cavity of described blade, form toroidal cavity, in described toroidal cavity, be provided with at least one radially barrier structure and some tangential dividing plates, by described radially barrier structure, described toroidal cavity is divided into leaf backside cavity and leaf basin side cavity, by some described tangential dividing plates, described toroidal cavity is divided into some chambeies, and then form some tangential runners, the leading edge of described impact lining is provided with some leading edge impact openings.
2. the turbine cooling blade with impact lining as claimed in claim 1, it is characterized in that: described radially barrier structure has two, and be list structure, described in two, radially barrier structure is all arranged in the described toroidal cavity of described impact lining leading edge, and be positioned at the both sides of described leading edge impact opening, described in two radially the height of barrier structure and the radial height of described blade consistent.
3. the turbine cooling blade with impact lining as claimed in claim 1, it is characterized in that: the appearance profile of described tangential dividing plate and described toroidal cavity adapt along the appearance profile in tangential cross section, each described tangential dividing plate is arranged in described toroidal cavity along the spaced radial of described blade, described toroidal cavity is divided into some chambeies, and then forms some tangential runners.
4. the turbine cooling blade with impact lining as claimed in claim 2, is characterized in that: described radially barrier structure is the wherein one of cracking in dividing plate, perforate dividing plate, turbulence columns structure.
5. the turbine cooling blade with impact lining as claimed in claim 4, it is characterized in that: described in crack and be provided with and crack on dividing plate, the thickness range of the described dividing plate that cracks is set to 0.3mm～1.0mm, described in the seam wide range that cracks be set to 0.2mm～1.0mm.
6. the turbine cooling blade with impact lining as claimed in claim 4, it is characterized in that: on described perforate dividing plate, be provided with some perforates, the thickness range of described perforate dividing plate is set to 0.3mm～1.0mm, and the diameter range of described perforate is set to 0.2mm～1.0mm.
7. the turbine cooling blade with impact lining as claimed in claim 4, it is characterized in that: described turbulence columns structure comprises some spaced turbulence columns, the diameter range of described turbulence columns is set to 0.5mm～2.0mm, and the scope of the radial spacing of described turbulence columns and the diameter ratio of described turbulence columns is set to 1.5～5.
8. the turbine cooling blade with impact lining as claimed in claim 3, it is characterized in that: some described tangential dividing plates by described toroidal cavity along described blade be radially divided into 3～10 chambeies, the thickness range of described tangential dividing plate is set to 0.3mm～1.0mm.
9. the turbine cooling blade with impact lining as claimed in claim 1, it is characterized in that: the diameter range of described leading edge impact opening is set to 0.4mm～1.5mm, the scope of row's spacing of described leading edge impact opening and the diameter ratio of described leading edge impact opening is set to 2～20, and the scope of the diameter ratio of impact distance and described leading edge impact opening is set to 2～5.
10. the turbine cooling blade with impact lining as described in claim 1-9 any one, is characterized in that: by described radially barrier structure, with described tangential dividing plate, described impact lining is fixedly connected with the cavity inner wall of described blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320789559.8U CN203547803U (en) | 2013-12-04 | 2013-12-04 | Turbine cooling blade with impacting bush |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320789559.8U CN203547803U (en) | 2013-12-04 | 2013-12-04 | Turbine cooling blade with impacting bush |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203547803U true CN203547803U (en) | 2014-04-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320789559.8U Expired - Lifetime CN203547803U (en) | 2013-12-04 | 2013-12-04 | Turbine cooling blade with impacting bush |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203547803U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109763864A (en) * | 2018-12-26 | 2019-05-17 | 苏州大学 | Turbine stator blade, turbine stator blade cooling structure and cooling method |
| CN111783306A (en) * | 2020-07-06 | 2020-10-16 | 中国航发湖南动力机械研究所 | Turbine blade cold air quantity and cold effect characteristic analysis method |
| CN112523812A (en) * | 2020-12-02 | 2021-03-19 | 北京南方斯奈克玛涡轮技术有限公司 | Turbine guider blade with supporting structure |
| CN115199340A (en) * | 2022-07-27 | 2022-10-18 | 中国联合重型燃气轮机技术有限公司 | Double-walled turbine blade and gas turbine |
| CN115559789A (en) * | 2022-09-19 | 2023-01-03 | 中国航发湖南动力机械研究所 | Turbine guide vane with cooling structure |
-
2013
- 2013-12-04 CN CN201320789559.8U patent/CN203547803U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109763864A (en) * | 2018-12-26 | 2019-05-17 | 苏州大学 | Turbine stator blade, turbine stator blade cooling structure and cooling method |
| CN111783306A (en) * | 2020-07-06 | 2020-10-16 | 中国航发湖南动力机械研究所 | Turbine blade cold air quantity and cold effect characteristic analysis method |
| CN111783306B (en) * | 2020-07-06 | 2022-11-18 | 中国航发湖南动力机械研究所 | Turbine blade cold air quantity and cold effect characteristic analysis method |
| CN112523812A (en) * | 2020-12-02 | 2021-03-19 | 北京南方斯奈克玛涡轮技术有限公司 | Turbine guider blade with supporting structure |
| CN115199340A (en) * | 2022-07-27 | 2022-10-18 | 中国联合重型燃气轮机技术有限公司 | Double-walled turbine blade and gas turbine |
| CN115199340B (en) * | 2022-07-27 | 2025-12-19 | 中国联合重型燃气轮机技术有限公司 | Double-wall turbine blade and gas turbine |
| CN115559789A (en) * | 2022-09-19 | 2023-01-03 | 中国航发湖南动力机械研究所 | Turbine guide vane with cooling structure |
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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 |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: 201108 Shanghai city Minhang District Lotus Road No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140416 |
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| CX01 | Expiry of patent term |