CN108167026A - A kind of partition board and turbo blade internal cooling channel with recess - Google Patents
A kind of partition board and turbo blade internal cooling channel with recess Download PDFInfo
- Publication number
- CN108167026A CN108167026A CN201711433488.7A CN201711433488A CN108167026A CN 108167026 A CN108167026 A CN 108167026A CN 201711433488 A CN201711433488 A CN 201711433488A CN 108167026 A CN108167026 A CN 108167026A
- Authority
- CN
- China
- Prior art keywords
- recess
- partition board
- wall surface
- cooling duct
- clapboard body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
Abstract
The invention discloses a kind of for separating the partition board of turbo blade internal cooling channel, which includes clapboard body and the multiple recess being arranged in clapboard body.Also disclose a kind of cooling duct and the turbo blade including aforementioned barriers and cooling duct.The recess set on the partition board of the present invention will generate near wall Secondary Flow, enhance the turbulence intensity of near wall, improve partition board wall surface exchange capability of heat, therefore improve the overall heat exchange ability of cooling duct.
Description
Technical field
Cooling technology field more particularly to one kind the present invention relates to gas turbine or high-temperature unit of aircraft engine carry
The partition board of recess and turbo blade internal cooling channel.
Background technology
Turbine entrance temperature temperature is improved, is modern aeroengine and a main trend of gas turbine development.Therefore
There is an urgent need to more efficient, more advanced cooling technologies to ensure that turbine blade of gas turbine reliably works.Due to cooling
Air need to be extracted from compressor and be obtained, therefore the cooling technology enhanced means that the usage amount of cooling fluid can be reduced, favorably
In the whole efficiency for improving aero-engine and gas turbine.
Existing turbo blade usually has hollow structure, and with multiple internal coolant flow channels, these internal cooling streams
Road is limited (such as Fig. 1) by the on the pressure side wall surface 1 and suction side wall surface and partition board 3 of turbo blade.In cooling duct on the pressure side
Suction side wall surface inside is provided with flow-disturbing rib, cooling fluid flows in the coolant flow channel with flow-disturbing rib, to cool down turbine
Blade.
It finds by prior art documents, Daigo Fujimura etc. (U.S.Patent No.8556583B2),
Ching-pang Lee (U.S.Patent No.5797726) propose the cooling knot with ribbing inside turbo blade with multichannel
Structure.U-shaped cooling duct with fin flow spoiler on wall surface inside blade Zhong Xian areas.(the U.S.Patent such as Daigo Fujimura
No.8556583B2 it) proposes and recess is arranged on the wall surface with flow-disturbing rib, keep heat-transfer capability constant, but reduce to reach
The method of flow resistance.But if patent (U.S.Patent No.8556583B2) is described, recess whirlpool and flow-disturbing rib are arranged on the pressure side
On wall surface and suction side wall surface inner wall surface, although this can promote heat transfer property, aero engine turbine blades wall surface
Usually very thin, arrangement recess will be so that wall surface strength reduction on wall surface；And since concave interior is also there are flow separation zone,
There are localized heat transfer deteriorations, are susceptible to localized hyperthermia's hot spot.And the turbine blade of gas turbine wall surface of only power generation is thicker
In the case of, arrangement recess is only feasible on wall surface.In addition, due to the turbo blade on the pressure side inner wall of wall surface and suction side wall surface
Flow-disturbing fin has been disposed on face, therefore has arranged that the surface region of recess is very limited on these wall surfaces.This will also influence to be recessed
The performance of vortex strength heat-transfer capability.
Invention content
In view of the drawbacks described above of the prior art, the technical problems to be solved by the invention, which are to provide one kind, to be had and can carry
High convection current heat transfer property and keep the cooling duct of low flow resistance and the turbo blade with the cooling duct.
To achieve the above object, the first aspect of the present invention provides a kind of partition board, for separating inside turbo blade
Cooling duct, partition board include clapboard body and the multiple recess being arranged in clapboard body.
Further, multiple recess are in staggered arrangement in clapboard body, but not limited to this.Relative to other arrangement shapes
Formula, multiple recess can obtain more preferably heat conduction reinforced effect when in clapboard body being in staggered arrangement.
Further, the depth of recess is less than 0.5 with diameter ratio.
Further, multiple recess are arranged on the two side walls face or one of side wall surface of clapboard body.
Further, multiple recess include the first recess and the second recess, and the depth of the first recess is less than clapboard body
Thickness or thickness less than clapboard body half, the depth of the second recess is equal to the thickness of clapboard body or equal to partition board
The half of the thickness of ontology.
Further, the second recess is arranged on the end of clapboard body, and the end of the partition board refers to cooling duct
Partition part near turning area, the recess of partition board both sides can penetrate through.
The second aspect of the present invention provides a kind of cooling duct being set to inside turbo blade, and cooling duct is by turbine
The madial wall of blade and any of the above-described kind of partition board limit.
Further, partition board is provided with multiple so that cooling duct has multiple.
Further, one or more flow-disturbing ribs are provided on the madial wall of turbo blade so that cooling duct is by flow-disturbing
Rib, the madial wall of turbo blade, clapboard body and recess limit.
Further, one or more ribs-recess composite construction is provided on the madial wall of the turbo blade.
The third aspect of the present invention provides a kind of turbo blade, is cooled down including any of the above-described kind of partition board and any of the above-described kind
Channel, madial wall include on the pressure side wall surface and suction side wall surface, two ends of partition board respectively on the pressure side wall surface and suction side
Wall surface is connected, and cooling duct is divided into multiple cooling ducts by multiple partition boards.
In the better embodiment of the present invention, a kind of turbo blade, including madial wall, partition board and cooling duct, inside
Wall is including on the pressure side wall surface and suction side wall surface, two ends of partition board are connected respectively on the pressure side wall surface and suction side wall surface
It connects, cooling duct is limited by partition board, on the pressure side wall surface and suction side wall surface；Cooling duct is divided into multiple by multiple partition boards
Cooling duct.Wherein, one or more flow-disturbing ribs on the pressure side are provided on wall surface and/or suction side wall surface.Partition board includes partition board
Ontology and multiple recess, multiple recess are arranged on the two side walls face of clapboard body or one of side wall surface.
In another better embodiment of the present invention, a kind of turbo blade, including madial wall, partition board and cooling duct,
Madial wall includes on the pressure side wall surface and suction side wall surface, two ends of partition board respectively on the pressure side wall surface and suction side wall surface phase
Connection, cooling duct is limited by partition board, on the pressure side wall surface and suction side wall surface；Cooling duct is divided into more by multiple partition boards
A cooling duct.Wherein, one or more flow-disturbing ribs on the pressure side are provided on wall surface and/or suction side wall surface.Partition board include every
Plate ontology and multiple recess, multiple recess are arranged on the two side walls face of clapboard body or one of side wall surface.Multiple recess
Including the first recess and the second recess, the depth of the first recess is the thickness less than clapboard body or the thickness less than clapboard body
Half, the half of the depth of the second recess for the thickness equal to clapboard body or the thickness equal to clapboard body.Second recess
The end of clapboard body is arranged on, the end of partition board refers to the partition part near the turning area of cooling duct, at this moment partition board both sides
Second recess be mutually communicated.In existing turbo blade, since partition board side wall surface is smooth side wall surface, exchange capability of heat is relatively low,
And since partition board is connected with the on the pressure side wall surface and suction side wall surface of turbo blade, heat can be transmitted to by partition board side wall surface
Cooling fluid.
The present invention, relative to the prior art, is had the advantage that by setting multiple recess on partition board：
1st, the recess in partition board side wall surface will generate near wall Secondary Flow, enhance the turbulence intensity of near wall, improve
Partition board side wall surface exchange capability of heat, therefore the overall heat exchange ability of cooling duct is improved, and do not increase the pressure of cooling duct
Loss.Or flow-disturbing rib number can be reduced in the case where identical cooling duct heat-transfer capability is kept to adjust, so as to be substantially reduced cooling
The pressure loss of channel.The number for reducing flow-disturbing rib is also beneficial to mitigate the weight of turbo blade.
2nd, partition board side wall surface setting recess is conducive to mitigate the weight of turbo blade.
3rd, the recess set on partition board is conducive to inhibit the flow separation at internal cooling channel flowing turning, alleviates stream
Dynamic loss improves the heat exchange uniformity of inner cooling channel Turning regions.
4th, especially it is equal to partition board in the one or more depth of divider ends (close to flow separation regions) setting on partition board
The recess of the half of thickness or block board thickness, i.e., the recess punched partition board can inhibit another side runner (i.e. after flowing turning
Runner) flow separation, reduce the pressure loss of turbo blade internal cooling channel, and improve the wall surface with flow-disturbing rib
Heat transfer uniformity.
5th, by setting shallow depression (depth and the diameter ratio of recess are less than 0.5) in opposite partition board side wall surface, be conducive to
The pressure loss of cooling duct is reduced, and keeps heat transfer and the cooling capacity of cooling duct.
The 6th, recess on partition board is set, and also on the pressure side formed in turbo blade with setting recess on suction side internal face
Rib-recess composite construction can further promote cooling duct heat-transfer capability, and flow pressure drop increases unobvious.
The flow-disturbing rib cooling duct in the band recess whirlpool of the present invention is carried than traditional flow-disturbing rib cooling duct overall heat transfer performance
15%-20% is risen.
The technique effect of the design of the present invention, concrete structure and generation is described further below with reference to attached drawing, with
It is fully understood from the purpose of the present invention, feature and effect.
Description of the drawings
Fig. 1 is the schematic diagram of existing turbo blade；
Fig. 2 is the schematic diagram of the turbo blade in the preferred embodiment of the present invention；
Fig. 3 is the partial schematic diagram of the turbo blade of the preferred embodiment of the present invention；
Fig. 4 is the partial schematic diagram of the turbo blade of another preferred embodiment of the present invention；
Fig. 5 is that two kinds of cooling duct totality heat exchange property data compare figure.
Specific embodiment
As shown in figure 3, the present invention a preferred embodiment provide a kind of turbo blade 10, including on the pressure side wall surface 1,
Suction side wall surface 2, partition board 3 and cooling duct, wherein, multiple flow-disturbing ribs 4 on the pressure side are provided on wall surface 1 and suction side wall surface 2,
The flow-disturbing rib 4 is elongated, and multiple flow-disturbing ribs 4 are arranged in parallel.The both ends of partition board 3 respectively on the pressure side wall surface 1 and suction
Side wall surface 2 is to connection.Cooling duct is limited by partition board 3, on the pressure side wall surface 1 and suction side wall surface 2.If setting it is multiple every
Plate 3, then cooling duct will be divided into multiple cooling ducts.
Wherein, multiple recess 32 are provided on partition board 3.In staggered arrangement in clapboard body 31, this is multiple recess 32
A kind of preferred embodiment, in other embodiments, can also be according to other arrangement modes.It is multiple recess 32 be arranged on every
The two side walls face of plate ontology 31 or one of side wall surface.The depth of recess 32 is less than or equal to the thickness of clapboard body 31,
Or the depth of recess 32 is less than or equal to the half of the thickness of clapboard body 31.
In the present embodiment, 32 depth that is recessed and diameter ratio are less than 0.5, when the depth of recess 32 is 0.2 with diameter ratio
Preferably.
In one embodiment, multiple recess 32 include the first recess and the second recess, and the first recess and the second recess are set
One of side wall surface in clapboard body 31 is put, the depth of the first recess is less than the thickness of clapboard body 31, the second recess
Depth is equal to the thickness of clapboard body 31, i.e., the bottom of the second recess passes through clapboard body 31 in a thickness direction.
In one embodiment, multiple recess 32 include the first recess and the second recess, and the first recess and the second recess are set
The two side walls face of clapboard body 31 is placed in, the depth of the first recess is less than the half of the thickness of clapboard body 31, the second recess
Depth be equal to clapboard body 31 thickness half, i.e., positioned at both sides second recess bottom respectively wear in a thickness direction
A half thickness of clapboard body 31 is crossed, is punched clapboard body 31.
In one embodiment, the second recess is arranged on the upper and lower end of clapboard body 31, clapboard body 31
End refers to the partition part near the turning area of cooling duct, specifically, refers to the upper and lower end of clapboard body 31
Respectively with the junction of turbo blade or close to junction, at this moment the second recess of 31 both sides of clapboard body is mutually communicated.
The cooling duct of the present embodiment is by flow-disturbing rib 4, the on the pressure side wall surface 1 of turbo blade and suction side wall surface 2, partition board sheet
Body 31 and recess 32 limit.Recess 32 in 3 side wall surface of partition board will generate near wall Secondary Flow, enhance the rapids of near wall
Intensity of flow improves 3 side wall surface exchange capability of heat of partition board, therefore improves the overall heat exchange ability of cooling duct, and do not increase
The pressure loss of cooling duct.Or flow-disturbing 4 numbers of rib can be reduced in the case where identical cooling duct heat-transfer capability is kept to adjust,
So as to be substantially reduced the pressure loss of cooling duct.The number for reducing flow-disturbing rib 4 is also beneficial to mitigate the weight of turbo blade.Every
Setting recess 32 is also beneficial to mitigate the weight of turbo blade on plate 3.
A part is set to punch the recess 32 of partition board 3 on partition board 3, is conducive to inhibit the flow separation of opposite side, reduces
The pressure loss of turbo blade internal cooling channel, and improve the heat transfer uniformity of the wall surface with flow-disturbing rib 4.
As shown in figure 4, another embodiment of the present invention provides a kind of turbo blade, including on the pressure side wall surface 1, suction side
Wall surface 2, partition board 3 and cooling duct, wherein, on the pressure side multiple flow-disturbing ribs 4, the flow-disturbing are provided on wall surface 1 and suction side wall surface 2
Rib 4 is elongated, and multiple flow-disturbing ribs 4 are arranged in parallel.The both ends of partition board 3 respectively on the pressure side wall surface 1 and suction side wall surface 2
To connection.Cooling duct is limited by partition board 3, on the pressure side wall surface 1 and suction side wall surface 2.If setting multiple partition boards 3,
Cooling duct will be divided into multiple cooling ducts.Wherein, multiple recess 32 are provided on partition board 3.Multiple recess 32 are in partition board
It is in staggered arrangement on ontology 31.Multiple recess 32 are arranged on the two side walls face of clapboard body 31 or one of side wall surface.It is recessed
The depth for falling into 32 is less than or equal to the thickness of the thickness of clapboard body 31 or the depth of recess 32 less than or equal to clapboard body 31
The half of degree.
In this embodiment, the 32 density bigger in clapboard body 31 of more each recess.Due to being set in clapboard body 31
The recess 32 of higher density further improves the exchange capability of heat on 3 surface of partition board, logical so as to further improve entire cooling
The heat-transfer capability in road.
Fig. 5 shows two kinds of cooling ducts, i.e., flow-disturbing rib cooling duct and the flow-disturbing rib cooling duct with recess whirlpool is total
Body heat exchange property data compare figure.Flow-disturbing rib cooling duct is the prior art herein, refers to such situation：On the pressure side wall surface
With flow-disturbing rib is provided on suction side wall surface, but be not provided with being recessed on partition board, therefore flow-disturbing rib cooling duct is by pressure sidewall
Face, suction side wall surface, flow-disturbing rib and partition board limit.Flow-disturbing rib cooling duct with recess whirlpool refers to the feelings of the present invention
Condition：On the pressure side flow-disturbing rib is provided with, and recess is provided on partition board on wall surface and suction side wall surface, therefore with the flow-disturbing in recess whirlpool
Rib cooling duct is limited by the pressure side wall surface, suction side wall surface, flow-disturbing rib, recess and partition board.As shown in Figure 5, it is of the invention
The flow-disturbing rib cooling duct in the band recess whirlpool of embodiment is than traditional flow-disturbing rib cooling duct overall heat transfer performance boost 15%-
20%.
The preferred embodiment of the present invention described in detail above.It should be appreciated that those of ordinary skill in the art without
Creative work is needed according to the present invention can to conceive and makes many modifications and variations.Therefore, all technologies in the art
Personnel are available by logical analysis, reasoning, or a limited experiment on the basis of existing technology under this invention's idea
Technical solution, all should be in the protection domain being defined in the patent claims.
Claims (10)
1. a kind of partition board, for separating turbo blade internal cooling channel, which is characterized in that the partition board include clapboard body and
The multiple recess being arranged in the clapboard body.
2. partition board according to claim 1, which is characterized in that the multiple recess is arranged in the clapboard body in stagger arrangement
Row.
3. partition board according to claim 1, which is characterized in that the depth of the recess is less than 0.5 with diameter ratio.
4. partition board according to claim 1, which is characterized in that the multiple be recessed is arranged on two of the clapboard body
Side wall surface or one of side wall surface.
5. partition board according to claim 4, which is characterized in that the multiple recess includes the first recess and the second recess,
Half of the depth of first recess for the thickness less than the thickness of the clapboard body or less than the clapboard body, it is described
Half of the depth of second recess for the thickness equal to the thickness of the clapboard body or equal to the clapboard body.
6. partition board according to claim 5, which is characterized in that second recess is arranged on the end of the clapboard body
Portion, the end of the partition board refer to the partition part near the turning area of cooling duct.
7. a kind of cooling duct being set to inside turbo blade, which is characterized in that the cooling duct is by the turbo blade
Madial wall and any one of claim 1-6 described in partition board limit.
8. cooling duct according to claim 7, which is characterized in that the partition board is provided with multiple so that the cooling
Channel has multiple.
9. cooling duct according to claim 7, which is characterized in that on the madial wall of the turbo blade there are one settings
Or multiple flow-disturbing ribs.
10. a kind of turbo blade, which is characterized in that including the partition board described in any one of claim 1-6 and claim 7-9
Any one of described in cooling duct, the cooling duct is divided into multiple cooling ducts by multiple partition boards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711433488.7A CN108167026B (en) | 2017-12-26 | 2017-12-26 | Baffle plate with depressions and turbine blade internal cooling channel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711433488.7A CN108167026B (en) | 2017-12-26 | 2017-12-26 | Baffle plate with depressions and turbine blade internal cooling channel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108167026A true CN108167026A (en) | 2018-06-15 |
| CN108167026B CN108167026B (en) | 2020-02-07 |
Family
ID=62521248
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711433488.7A Active CN108167026B (en) | 2017-12-26 | 2017-12-26 | Baffle plate with depressions and turbine blade internal cooling channel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108167026B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114215609A (en) * | 2021-12-30 | 2022-03-22 | 华中科技大学 | Blade inner cooling channel capable of enhancing cooling and application thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5472316A (en) * | 1994-09-19 | 1995-12-05 | General Electric Company | Enhanced cooling apparatus for gas turbine engine airfoils |
| GB2382383B (en) * | 2001-11-27 | 2005-09-21 | Rolls Royce Plc | Gas turbine engine aerofoil |
| US20060269410A1 (en) * | 2005-05-31 | 2006-11-30 | United Technologies Corporation | Turbine blade cooling system |
-
2017
- 2017-12-26 CN CN201711433488.7A patent/CN108167026B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5472316A (en) * | 1994-09-19 | 1995-12-05 | General Electric Company | Enhanced cooling apparatus for gas turbine engine airfoils |
| GB2382383B (en) * | 2001-11-27 | 2005-09-21 | Rolls Royce Plc | Gas turbine engine aerofoil |
| US20060269410A1 (en) * | 2005-05-31 | 2006-11-30 | United Technologies Corporation | Turbine blade cooling system |
Non-Patent Citations (1)
| Title |
|---|
| 李麟: "新型凹陷涡发生器冷却结构内流动与传热的数值计算研究", 《CNKI》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114215609A (en) * | 2021-12-30 | 2022-03-22 | 华中科技大学 | Blade inner cooling channel capable of enhancing cooling and application thereof |
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| Publication number | Publication date |
|---|---|
| CN108167026B (en) | 2020-02-07 |
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