CN202055870U - Gas turbine rotor blade - Google Patents
Gas turbine rotor blade Download PDFInfo
- Publication number
- CN202055870U CN202055870U CN2011200648919U CN201120064891U CN202055870U CN 202055870 U CN202055870 U CN 202055870U CN 2011200648919 U CN2011200648919 U CN 2011200648919U CN 201120064891 U CN201120064891 U CN 201120064891U CN 202055870 U CN202055870 U CN 202055870U
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- Prior art keywords
- blade
- cooling
- top closure
- cooling circuit
- channel
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Abstract
A gas turbine rotor blade comprises a blade root, a blade platform and a blade profile. An impingement cooling circuit used for cooling a front edge area of the blade, a tail edge rib and spray cooling circuit used for cooling a tail edge area of the cooling blade, a coiled passage strengthened convection cooling circuit used for cooling a middle area and a top area of the blade of the blade, at least one projection structure is arranged on the inner side of a top cap of the blade and used for strengthening cooling effect of the top cap of the blade, and accordingly the temperature of the top cap of the blade is reduced.
Description
Technical field
The utility model relates to a kind of turbine rotor blade of gas turbine, especially with the turbine rotor blade of a plurality of cooling circuits, reinforcement vane tip cooling effect.
Background technique
Along with improving constantly of gas turbine turbine inlet fuel gas temperature, the heat load environment that the turbine high-temperature component is faced is more abominable.In order to guarantee the reasonable life-span of high-temperature turbine blade, need cool off effectively it, wherein, especially complicated with the methods for cooling of high-temperature turbine rotor blade.State-of-the-art in the world turbine rotor blade all adopts many cooling circuits, serpentine channel to strengthen the form of convection current cooling at present, so that the temperature field of blade body and stress distribution remain on reasonable levels.Because on making, blade can be finished top closure the sealing of internal cooling circuit with the form of welding at vane tip after the precision casting of finishing the internal cooling channel chamber.
Simultaneously, in turbine high-temperature fuel gas runner, because the horizontal secondary flow and the leaf top leakage flow of combustion gas, failure phenomenons such as crackle even ablation appear to the leaf climax of turbine rotor blade in high temperature oxidation because temperature is too high or thermal stress is excessive easily.Therefore, need under the situation that does not increase total cooling air volume, carry out more effective and reasonable cooling, with temperature and the thermal stress level that reduces described top area to the vane tip zone.
The model utility content
The purpose of this utility model provides a kind of turbine rotor blade that is used for gas turbine, makes it under the situation that does not increase total cooling air volume, and more effective and reasonable cooling is carried out in the vane tip zone, to reduce the temperature in vane tip zone.
The purpose of this utility model is achieved by the following technical solution:
A kind of turbine rotor blade of gas turbine, described blade comprises: vane foil, blade root and the bucket platform that connects vane foil and blade root; The vane foil outer surface is made of suction surface and pressure side, and suction surface and pressure side juncture area are respectively blade inlet edge and blade trailing edge; In blade interior, comprise three cooling circuits: be used for impact cooling circuit, the serpentine channel reinforcement convection current cooling circuit that is used for blade middle part and vane tip cooling, the trailing edge rib of column that is used for the blade trailing edge cooling and injection cooling circuit that blade inlet edge cools off; Each cooling circuit has at least one cooling channel respectively.Vane tip is provided with a top closure, and this top closure is welded on vane tip with closed leave; The dividing plate of described top closure and blade interior forms the horizontal cooling channel in the serpentine channel reinforcement convection current cooling circuit, and described horizontal cooling channel has at least one opening that leads to the outer combustion gas main flow of blade; Side is provided with at least one protruding structure in the horizontal cooling channel of top closure; Described top closure has at least one top air film hole; Cooled gas is to flow to blade trailing edge from blade inlet edge in the described horizontal cooling channel, and finally the described opening from described top air film hole and horizontal cooling channel flows into the combustion gas main flow.
Described protruding structure is round column structure, hemispherical dome structure or rib structure; Protruding structure and described top closure are one processing; Described top closure is to make separately, and is installed in vane tip with the form of welding; The combustion gas side surface of described top closure also is sprayed with oxidation resistant coating and heat insulating coat.
At least one cooling channel internal face that described impact cooling circuit or described serpentine channel are strengthened the convection current cooling circuit has at least one rib structure.
Arranged at least one film cooling holes on the wall of described blade inlet edge; Described impact cooling circuit is provided with at least one and impacts cooling hole; Impact the interior cooled gas of cooling circuit through after the described impact cooling hole, flow out by described film cooling holes.Described blade trailing edge internal placement at least one rib of column structure; Described blade trailing edge has at least one and sprays through hole, so that the cooled gas in the described trailing edge rib of column and the injection cooling circuit flows out.
The utlity model has following advantage and high-lighting effect:
Be provided with at least one protruding structure on the horizontal cooling channel side surface of top closure, make cooled gas when flowing through the vane tip zone, because protruding structure has the effect of strengthening convection heat exchange, therefore can strengthen the heat transfer cooling effect of the horizontal cooling channel of top closure side surface.Generally, top closure combustion gas side surface can be coated with heat insulating coat; Simultaneously, because also there is the air film cooling in the vane tip zone, and the structure that is used to strengthen the convection heat exchange cooling of horizontal inside, cooling channel, therefore, several methods for cooling can cooperate the reasonable distribution that obtains temperature conductivity on the top closure.
Description of drawings
Fig. 1 is the 3-D view of the turbine rotor blade of gas turbine.
Fig. 2 is a gas turbine turbine rotor blade inner cooling system schematic cross-section of the present utility model.
Fig. 3 is that the A of Fig. 2 is to view.
Fig. 4 is the zoomed-in view of top closure.
Fig. 5 is the top closure side view.
Fig. 6 is the worm's eye view of top closure.
Fig. 7 is the B-B sectional view of Fig. 2.
Fig. 8 is the C-C sectional view of Fig. 2.
Among the figure: the inlet of 1-root cooling channel; The 2-film cooling holes; 3-impacts cooling hole; 4-sprays through hole; 5-top air film hole; The 11-blade root; The 12-bucket platform; The 13-vane foil; The 14-top closure; The 15-protruding structure; The 16-rib structure; 17-rib of column structure; 18-cooling channel demarcation strip; 19-blade profile mean camber line; 21-second impacts the cooling channel; 22-first impacts the cooling channel; 23-the 3rd serpentine cooling channel; The horizontal cooling channel of 24-; 25-second serpentine cooling channel; 26-first serpentine cooling channel; 27-trailing edge cooling channel; 28-impacts the cooling demarcation strip; The 31-blade suction surface; The 32-blade pressure surface; The 33-blade inlet edge; The 34-blade trailing edge.
Embodiment
Below in conjunction with accompanying drawing to principle of the present utility model, specifically implement and working procedure is described further:
Accompanying drawing is represented a specific embodiment of the present utility model.Fig. 1 is the 3-D view of the turbine rotor blade of gas turbine, and described rotor blade comprises vane foil 13, blade root 11 and the bucket platform 12 that connects vane foil and blade root; Along blade profile mean camber line 19 blade is cut open, can be obtained the structure of blade interior, as shown in Figure 2.The vane foil outer surface is made of blade suction surface 31 and blade pressure surface 32, and suction surface and pressure side juncture area are respectively blade inlet edge 33 and blade trailing edge 34.Blade interior has and is used for a plurality of cooling channels that cooled gas flows, cooled gas is extracted out from the correct position of gas compressor, be transported to the root cooling channel inlet 1 of rotor blade along gas turbine rotor axle system, the size of root cooling channel inlet and number are taken all factors into consideration according to required cooled gas flow and blade strength and are selected.
In blade interior, comprise three cooling circuits: promptly be used for impact cooling circuit, the serpentine channel reinforcement convection current cooling circuit that is used for blade middle part and vane tip cooling, the trailing edge rib of column that is used for the blade trailing edge cooling and injection cooling circuit that blade inlet edge cools off, these three cooling circuits separate by dividing plate in blade, are not communicated with mutually.Wherein, one cooled gas is used to carry out the impact cooling and the air film cooling of blade inlet edge, forms and impacts cooling circuit; One cooled gas is used to carry out the rib of column cooling and the blade trailing edge injection of blade trailing edge, forms the trailing edge rib of column and sprays cooling circuit; The 3rd strand of cooled gas is used for the convection current cooling at blade middle part, the cooling in vane tip zone, forms serpentine channel and strengthens the convection current cooling circuit.Strengthen in the convection current cooling circuit at serpentine channel, cooled gas flows to the blade trailing edge direction from blade inlet edge in the horizontal cooling channel 24 that is positioned at vane tip, finally from least one the top air film hole 5 of vane tip and an opening outflow of leading to combustion gas main flow outside the blade of horizontal cooling channel 24.
In the present embodiment, described impact cooling circuit comprises that first impacts the cooling channel 22 and the second impact cooling channel 21; Described two are impacted the cooling channel by impacting cooling demarcation strip 28 separately; Arranged at least one impact cooling hole 3 on the described impact cooling demarcation strip 28.First internal face that impacts cooling channel 22 is furnished with at least one rib structure 16 of strengthening the convection current cooling effect, cooled gas when the vane tip direction flows, can be arranged in second partial blade leading edge 33 internal faces that impact cooling channel 21 by 3 pairs of described impact cooling hole along journey and impact cooling in the first impact cooling channel 22.Arranged at least one film cooling holes 2 on the wall of blade inlet edge 33, cooled gas, forms air film and covers on blade suction surface 31 and the blade pressure surface 32, thereby high-temperature fuel gas is separated from described film cooling holes ejection through after the described impact cooling hole.Physical dimensions such as the angle of described film cooling holes, aperture and combined influence effects such as quantity is pneumatic according to blade, heat transfer are determined.
Be used for the trailing edge rib of column of blade trailing edge 34 coolings and spray cooling circuit comprising trailing edge cooling channel 27.At least one rib of column structure 17 has been arranged in described trailing edge cooling channel 27, to strengthen the convection current cooling effect of described blade trailing edge.Simultaneously, described rib of column structure connects blade suction surface 31 and blade pressure surface 32, plays the effect of strengthening blade structure intensity.The physical dimension of described rib of column structure 17 and quantity need comprehensively be selected according to cooling effect and requirement of strength equally.Arrange at least one injection through hole 4 at described blade trailing edge, can make cooled gas in described injection through hole, quicken usually, thereby strengthened the convection current cooling effect.
The serpentine channel reinforcement convection current cooling circuit that is used for blade middle part and vane tip cooling comprises first serpentine cooling channel 26, second serpentine cooling channel 25, the 3rd serpentine cooling channel 23 and horizontal cooling channel 24, wherein first serpentine cooling channel 26, second serpentine cooling channel 25 and the 3rd serpentine cooling channel 23 are radial direction, and laterally cooling channel 24 interior cooled gases are to the blade trailing edge lateral flow from blade inlet edge.Separate by cooling channel demarcation strip 18 between each cooling channel of serpentine channel reinforcement convection current cooling circuit, make cooled gas wriggle therein and flow.Serpentine channel is strengthened each cooling channel internal face of convection current cooling circuit and has all been arranged at least one rib structure 16, to strengthen the convection current cooling effect of each cooling channel internal face.Serpentine channel is strengthened geometrical construction, setting type and the number needs of the described rib structure in the convection current cooling circuit according to the requirement of the heat transfer and the pressure loss is selected.Cooled gas should guarantee that enough pressure can be from the described opening and 5 ejections of described top air film hole of horizontal cooling channel 24.
Because structural characteristics, vane tip has the dimple structure usually.After the precision casting of finishing blade interior cooling channel chamber, a top closure 14 can be finished the sealing of cooling circuit with the form of welding at vane tip, and form the dimple structure of vane tip.For vane tip is cooled off, on this top closure, arrange described top air film hole 5 usually, cooled gas forms air film and comes the cooled blade top.Nonetheless, because temperature is too high, reason such as the air film coverage effect is inhomogeneous, vane tip is still as easy as rolling off a log by high temperature oxidation, crackle occurs even ablates.Just because of this, the utility model is wished under the situation of not introducing unnecessary cooled gas, reduces the temperature of top closure.
Blade at aforementioned specific cooling structure form.The utility model is provided with at least one protruding structure 15 at the inner surface of the top closure of this horizontal cooling channel, and described protruding structure can be semicircular structure, round column structure or rib structure, as shown in Figure 4.Cooled gas is when the lateral flow of vane tip zone, and described protruding structure will increase the turbulivity of fluid, strengthen the convection current cooling effect on vane tip zone, especially the top closure internal face.Simultaneously, according to flowing heat transfer mechanism as can be known, under described protruding structure effect, non-uniform phenomenon can appear in the heat-transfer coefficient on the top closure internal face.In order to reduce the temperature of top closure, Gu can flow described protruding structure 15-Re-coupling calculates, to optimize its structural feature.As a kind of preferred special case, the utility model has provided a kind of top closure structure, and the top closure interior sidewall surface is furnished with the circular protrusions structure of 3/4 circular arc.Described top air film hole 5 is arranged in place, about one times of aperture, described protruding structure rear along the mobile direction of cooled gas.The particular location of described top air film hole as shown in Figure 6.
In order to reduce top closure thermal stress level, top closure 14 and described protruding structure 15 are finished for integrally casting.In order further to reduce the top closure temperature, be sprayed with oxidation resistant coating and heat insulating coat (TBC) at the blade combustion gas side surface of top closure 14, this coating can further reduce the temperature of top closure.
Although what the utility model was described is that the claimant thinks case the most practical and the process optimized choice, the utility model is not limited to the structural feature of foregoing detailed description.But cover the content that claims limit, and the equivalent structure of amplification and modification thus.
Claims (7)
1. the turbine rotor blade of a gas turbine is characterized in that: the bucket platform (12) that described blade includes vane foil (13), blade root (11) and connects vane foil and blade root; The vane foil outer surface is made of suction surface (31) and pressure side (32), and the juncture area of suction surface and pressure side is respectively blade inlet edge (33) and blade trailing edge (34);
In blade interior, comprise three cooling circuits: be used for the impact cooling circuit of blade inlet edge cooling, the serpentine channel that is used for blade middle part and vane tip cooling is strengthened the convection current cooling circuit, and is used for the trailing edge rib of column of blade trailing edge cooling and sprays cooling circuit; Each cooling circuit has at least one cooling channel respectively;
Vane tip is provided with a top closure (14), and this top closure is welded on vane tip with closed leave; The dividing plate of described top closure and blade interior forms the horizontal cooling channel (24) in the serpentine channel reinforcement convection current cooling circuit, and described horizontal cooling channel has at least one opening that leads to the outer combustion gas main flow of blade; Side is provided with at least one protruding structure (15) in the horizontal cooling channel of top closure (14); Described top closure (14) has at least one top air film hole (5); The interior cooled gas in described horizontal cooling channel (24) is to flow to blade trailing edge from blade inlet edge, and finally the described opening from described top air film hole (5) and horizontal cooling channel (24) flows into the combustion gas main flow.
2. the turbine rotor blade of a kind of gas turbine as claimed in claim 1 is characterized in that: described top closure (14) is for making separately, and is installed in vane tip with the form of welding; The combustion gas side surface of described top closure (14) also is sprayed with oxidation resistant coating and heat insulating coat.
3. the turbine rotor blade of a kind of gas turbine as claimed in claim 1, it is characterized in that: described protruding structure (15) is round column structure, hemispherical dome structure or rib structure.
4. the turbine rotor blade of a kind of gas turbine as claimed in claim 1 is characterized in that: described protruding structure (15) is one processing with described top closure (14).
5. the turbine rotor blade of a kind of gas turbine as claimed in claim 1 is characterized in that: at least one cooling channel internal face that described impact cooling circuit or described serpentine channel are strengthened the convection current cooling circuit has at least one rib structure (16).
6. the turbine rotor blade of a kind of gas turbine as described in claim 1 is characterized in that: arranged at least one film cooling holes (2) on the wall of described blade inlet edge (33); Described impact cooling circuit is provided with at least one and impacts cooling hole (3); After the cooled gas described impact cooling hole of process (3), flow out in the described impact cooling circuit by described film cooling holes (2).
7. the turbine rotor blade of a kind of gas turbine as claimed in claim 1 is characterized in that: described blade trailing edge (34) internal placement at least one rib of column structure (17); Described blade trailing edge has at least one and sprays through hole (4), so that the cooled gas in the described trailing edge rib of column and the injection cooling circuit flows out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200648919U CN202055870U (en) | 2011-03-11 | 2011-03-11 | Gas turbine rotor blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200648919U CN202055870U (en) | 2011-03-11 | 2011-03-11 | Gas turbine rotor blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202055870U true CN202055870U (en) | 2011-11-30 |
Family
ID=45015844
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011200648919U Expired - Lifetime CN202055870U (en) | 2011-03-11 | 2011-03-11 | Gas turbine rotor blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202055870U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102102543A (en) * | 2011-03-11 | 2011-06-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine rotor blade of gas turbine |
| CN102943693A (en) * | 2012-11-29 | 2013-02-27 | 哈尔滨汽轮机厂有限责任公司 | Efficient cooling turbine movable vane of gas turbine with low-heat and medium-heat values |
| CN102979583A (en) * | 2012-12-18 | 2013-03-20 | 上海交通大学 | Separate-type column rib cooling structure for turbine blade of gas turbine |
| CN110234840A (en) * | 2017-01-31 | 2019-09-13 | 西门子股份公司 | Turbine rotor blade or Turbomachinery for gas turbine |
-
2011
- 2011-03-11 CN CN2011200648919U patent/CN202055870U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102102543A (en) * | 2011-03-11 | 2011-06-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine rotor blade of gas turbine |
| CN102102543B (en) * | 2011-03-11 | 2013-05-15 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine rotor blade of gas turbine |
| CN102943693A (en) * | 2012-11-29 | 2013-02-27 | 哈尔滨汽轮机厂有限责任公司 | Efficient cooling turbine movable vane of gas turbine with low-heat and medium-heat values |
| CN102979583A (en) * | 2012-12-18 | 2013-03-20 | 上海交通大学 | Separate-type column rib cooling structure for turbine blade of gas turbine |
| CN102979583B (en) * | 2012-12-18 | 2015-05-20 | 上海交通大学 | Separate-type column rib cooling structure for turbine blade of gas turbine |
| CN110234840A (en) * | 2017-01-31 | 2019-09-13 | 西门子股份公司 | Turbine rotor blade or Turbomachinery for gas turbine |
| US11053802B2 (en) | 2017-01-31 | 2021-07-06 | Siemens Energy Global GmbH & Co. KG | Turbine blade or a turbine vane for a gas turbine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20111130 Effective date of abandoning: 20130515 |
|
| RGAV | Abandon patent right to avoid regrant |