CN107503801A - A kind of efficiently array jetting cooling structure - Google Patents
A kind of efficiently array jetting cooling structure Download PDFInfo
- Publication number
- CN107503801A CN107503801A CN201710710525.8A CN201710710525A CN107503801A CN 107503801 A CN107503801 A CN 107503801A CN 201710710525 A CN201710710525 A CN 201710710525A CN 107503801 A CN107503801 A CN 107503801A
- Authority
- CN
- China
- Prior art keywords
- impact opening
- cooling structure
- jet
- impact
- cooling
- 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.)
- Pending
Links
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
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to gas turbine and high-temperature unit of aircraft engine cooling and some other field for being related to the cooling of array impact jet, specially a kind of efficiently array jetting cooling structure.Three kinds of array jetting impact opening structure designs and a kind of conical rib structure design are provided, include a kind of gradual shrinkage jet impulse hole orifice plate of porous array arrangement, a kind of impact opening orifice plate for having different pore size array arrangement, impact opening orifice plate of the one kind with (circle) angle array arrangement, and a kind of jet target plate of upper conical rib array arrangement.This purpose of design is to use minimum cooling air volume, farthest improves cooling effectiveness, while reduces the overall thermograde of cooling wall, makes heat transfer more uniform and stable.
Description
Technical field：
The invention belongs to gas turbine and high-temperature unit of aircraft engine cooling and some other array impact that is related to penetrate
The field of cooling is flowed, specially a kind of efficiently array jetting cooling structure.
Background technology：
The key technology of lifting thermal efficiency of gas turbine is to improve the inlet temperature of combustion engine turbine rotor, present gas turbine
The fuel gas temperature of turbine one-level movable vane has reached more than 1800K, at so high temperature, the hot-end component of gas turbine
(combustion chamber, burner inner liner, changeover portion, turbo blade etc.) can not work long hours at such high temperatures, it is necessary to using effective
Cooling technology.
At present, the development trend of gas turbine is the discharge for improving temperature rise and reducing pollutant, and the two is required for larger model
AIR Proportional of the raising enclosed for gas-turbine combustion chamber, thus cause the cooling air ratio drop for combustion engine hot-end component
It is low.In the case where ensureing thermal efficiency of gas turbine, how to pass through less cooling air volume, the more effective heat for cooling down combustion engine
The problem of end pieces are in the urgent need to address at present.
In all heat conduction reinforced technologies, array jetting impinging cooling be improve Local Condensing Heat Transfer Coefficients in it is most important and
Most efficient method, and one of technological means applied to turbine blade of gas turbine cooling earliest.Influence wall heat exchange most
Directly the reason for is due to that wall has gas boundary layer, have impact on the heat transfer effect of wall, and impinging cooling can be in jet
Stationary point region farthest reduces the thickness in boundary layer, reaches the purpose of enhancing heat exchange.
There is following limitation in existing array jetting cooling system：
(1) experiment cooling system is not accounted in the case of real work, and cooling air volume is limited.Have no idea
Significantly lift the Reynolds number of impact jet flow.
(2) existing array jetting cooling system, active cooling surface product is jet in other regions in the range of four times of impact openings
Target plate wall boundary layer is thicker, and heat transfer effect is bad.
(3) after impact jet flow impact target plate, it can go out to produce a certain amount of crossing current in target plate wall, crossing current can be to rear discharge
Stream has an impact so that heel row impact jet flow produces skew, causes the overall chilling temperature of target plate uneven, produces larger temperature
Gradient, influence the service life of material.
The content of the invention：
This purpose of design is to use minimum cooling air volume, farthest improves cooling effectiveness, reduce simultaneously
The overall thermograde of cooling wall, makes the heat transfer more uniform and stable.To achieve the above object, this secondary design provides three kinds
Impact opening structure design and a kind of structure design of the upper conical rib of jet target plate (cooling ribs), scheme are as follows：
A kind of efficiently array jetting cooling structure, including jet orifice plate and jet target plate, described jet orifice plate are provided with
The impact opening of multiple array arrangements；The jet orifice plate is located at the top of the jet target plate, is designed for cavity therebetween.
Further, flow above target plate and be provided with multiple raised conical ribs.
Further, impact opening from top to bottom designs for tapered hole, the gradual shrinkage impact opening upper/lower terminal mouth circular diameter
Difference be 1.5D, the normal of impact opening and impact wall surface of the hole institute into tilt angle theta be 45 °~90 °.
Further, the top of impact opening is that chamfering or rounding design, and bottom is designed for cylindrical hole；The chamfering impact
The chamfer angle α in hole is 30~45 °, and the size of chamfering is 0.1D~0.3D.
Further, impact opening is 3 kinds of different pore size array arrangements, and three kinds of apertures are respectively 1D, 1.5D and 2D.
Further, the conical surface of conical rib is to face directly or is curved surface.
Further, conical rib bottom circular diameter is 0.5D, and conical rib is highly 0.5D~1D.
Further, the quantity of conical rib and described impact opening is mutually matched, and the conical rib is located at the impact opening
Within the upper upright projection region of the jet target plate.
Further, described jet orifice plate is parallel with described jet target plate.
Main advantages of the present invention：
1st, cold air come flow it is certain in the case of, the design of tapered hole adds somewhat to impact Reynolds number, add
The strong coefficient of heat transfer.
2nd, the mode of different pore size arrangement causes the impact jet flow of different pore size to have different jet Reynolds numbers, to jet
The cooling of target plate is more uniform.
3rd, (circle) angle impact opening can increase the discharge coefficient of impact opening, reduce in impulse chamber, i.e., jet orifice plate with
The backflow vortex situation of cavity, improves its internal work condition between jet target plate.
4th, in general impact opening, the wall boundary layer in only impact opening upright projection region is very thin, therefore impacts
Stationary point region has very strong heat transfer effect, adds conical rib on jet target plate so that impact jet flow is in bigger model
The thickness in target plate wall boundary layer is reduced in enclosing, what described boundary layer referred to can produce in the place at wall, fluid
A kind of raw flow regime of laminar flow, a kind of similar film, boundary layer is thicker, and heat-transfer effect is poorer, has reached the effect of enhancing heat exchange
Fruit
5 at the same the pore structure that designs of the present invention and the manufacturing process of conical rib it is simple, easily realize.
Brief description of the drawings：
Fig. 1 is the structural representation of the present invention；
Fig. 2 is gradual shrinkage type AND DEWATERING FOR ORIFICE STRUCTURE schematic diagram；
Fig. 3 is the AND DEWATERING FOR ORIFICE STRUCTURE schematic diagram of different pore size arrangement；
Fig. 4 is chamfered bore plate structure schematic diagram；
Fig. 5 is rounding AND DEWATERING FOR ORIFICE STRUCTURE schematic diagram；
Fig. 6 is that conical rib is the target plate structural representation faced directly；
Fig. 7 is the target plate structural representation that conical rib is cambered surface；
Fig. 8 is the jet flow field schematic diagram with conical rib target plate；
Fig. 9 is that cylindrical hole impacts hole shape and tapered hole shape jet target plate Nu numbers profiles versus figure；
Figure 10 is to whether there is profiles versus's figure of conical rib structure jet target plate Nu numbers；
Embodiment：
Invention is described in further details with instantiation below in conjunction with the accompanying drawings, but the present invention is not limited to following implementation
Example.
With reference to figure 1, a kind of efficiently array jetting cooling structure, including jet orifice plate 1 and jet target plate 3, on jet orifice plate 1
Impact opening 2 provided with the arrangement of multiple arrays；The jet orifice plate 1 is located at the top of the jet target plate 3, is therebetween cavity
Design.
As the improvement of scheme, with reference to figure 2 and Fig. 9, impact opening 2 from top to bottom designs for tapered hole, the gradual shrinkage punching
The difference for hitting hole upper/lower terminal mouth circular diameter is 1.5D, and the spacing of impact opening 2 is 3D, and impact distance (impacts orifice plate to impact target plate
Distance) be 2D, the normal of impact opening 2 and the wall of impact opening 2 institute into angle of inclination be 45 °~90 °.As a result find：Initial
In the case of the condition identical such as cooling air delivery, pressure, compared to general cylindrical impact opening, rushed caused by tapered pore structure
Slap shot stream film-cooled heat is identical, and cooling effectiveness improves more than 10%,
As the improvement of scheme, with reference to figure 4-5, the top of impact opening 2 is designed for chamfering or rounding, and bottom is cylindrical hole
Design；The spacing of adjacent impingement hole 2 is 3D, and impact distance 2D, the chamfer angle α of chamfering impact opening 2 is 45 °, the length of chamfering
Size is 0.2D.As a result find：In the case of the condition identical such as initial cooling air delivery, pressure, compared to common cylinder
Impact opening, the interior backflow vortex situation of impulse chamber have obvious improvement, the discharge coefficient increase of impact opening 2, and the coefficient of heat transfer improves
More than 5.5%.
As the improvement of scheme, with reference to figure 3, impact opening 2 is 3 kinds of different pore size array arrangements, and the spacing of adjacent impingement hole 2 is
3D, impact distance 2D.Three kinds of apertures are respectively 1D, 1.5D and 2D, are specifically distributed as 3 rows 6 row and amount to 18 impact openings.This sets
Meter is in the case of the condition identical such as initial cooling air delivery, pressure, compared to common cylinder impact opening, although cooling effectiveness
It is not obviously improved, but the overall thermograde of target plate has an obvious reduction, the overall coefficient of heat transfer is more uniform.
As the improvement of scheme, with reference to figure 6-7 and Figure 10, jet target plate 3 is provided with multiple raised conical ribs 4 above, bores
The conical surface of shape rib 4 is to face directly or is curved surface.The spacing of adjacent impingement hole 2 is 3D, impact distance 2D, is rushed using plain cylindrical form
Hit 4 two kinds of combining structures of hole and conical rib 4 and gradual shrinkage type impact opening 2 and conical rib to compare, the bottom circular diameter of conical rib 4
For 0.5D, conical rib is highly D, and the conical surface is faces and two kinds of curved surface directly.As a result find：In initial cooling air delivery, pressure etc.
In the case of condition identical, the mode of common cylinder impact opening and conical rib combination, active cooling surface product is in 4 times of D region；
Tapered hole and the combination of conical rib 4, active cooling surface product is in 4.5 times of D region.Meanwhile curved cone rib 4 is compared to facing directly
The active cooling surface of conical rib 4 product improves 25%~35%.
As the improvement of scheme, with reference to figure 8, the quantity of conical rib 4 and described impact opening 3 is mutually matched, the taper
Rib 4 is located at the impact opening 2 within the upper upright projection region of the jet target plate 3.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
All any modification, equivalent and improvement made within refreshing and principle etc., should be included in the scope of the protection.
Claims (8)
- A kind of 1. efficiently array jetting cooling structure, it is characterised in that：Including jet orifice plate and jet target plate, described jet orifice Plate is provided with the impact opening of multiple arrays arrangement；The jet orifice plate is located at the top of the jet target plate, is therebetween sky Chamber designs.
- A kind of 2. efficiently array jetting cooling structure as claimed in claim 1, it is characterised in that：Above described jet target plate Provided with multiple raised conical ribs.
- A kind of 3. efficiently array jetting cooling structure as claimed in claim 1, it is characterised in that：Described impact opening is by up to Designed for tapered hole down, the difference of the gradual shrinkage impact opening upper/lower terminal mouth circular diameter is 1.5D, the normal of impact opening and punching Hit wall surface of the hole institute into tilt angle theta be 45 °~90 °.
- A kind of 4. efficiently array jetting cooling structure as claimed in claim 1, it is characterised in that：The top of the impact opening is Chamfering or rounding design, bottom is designed for cylindrical hole；The chamfer angle α of the chamfering impact opening is 30~45 °, the chi of chamfering Very little is 0.1D~0.3D.
- A kind of 5. efficiently array jetting cooling structure as described in claim 1-4 is any, it is characterised in that：Described impact opening For 3 kinds of different pore size array arrangements, three kinds of apertures are respectively 1D, 1.5D and 2D.
- A kind of 6. efficiently array jetting cooling structure as claimed in claim 2, it is characterised in that：The conical surface of the conical rib is Face directly or be curved surface.
- A kind of 7. efficiently array jetting cooling structure as claimed in claim 2, it is characterised in that：Described conical rib bottom circle is straight Footpath is 0.5D, and conical rib is highly 0.5D~1D.
- A kind of 8. efficiently array jetting cooling structure as claimed in claim 2, it is characterised in that：Described conical rib with it is described The quantity of impact opening be mutually matched, the conical rib is located at the impact opening in the upper upright projection region of the jet target plate Within.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710710525.8A CN107503801A (en) | 2017-08-18 | 2017-08-18 | A kind of efficiently array jetting cooling structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710710525.8A CN107503801A (en) | 2017-08-18 | 2017-08-18 | A kind of efficiently array jetting cooling structure |
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| Publication Number | Publication Date |
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| CN107503801A true CN107503801A (en) | 2017-12-22 |
Family
ID=60691955
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| CN201710710525.8A Pending CN107503801A (en) | 2017-08-18 | 2017-08-18 | A kind of efficiently array jetting cooling structure |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108223022A (en) * | 2018-01-04 | 2018-06-29 | 沈阳航空航天大学 | A kind of turbulence structure in array jetting cooling |
| CN109737788A (en) * | 2018-12-21 | 2019-05-10 | 西北工业大学 | A kind of raised target plate structure reducing flow losses, intensifying impact heat exchange |
| CN109931114A (en) * | 2019-03-15 | 2019-06-25 | 南京航空航天大学 | A kind of novel impinging cooling turbulence structure |
| CN110195615A (en) * | 2019-05-20 | 2019-09-03 | 沈阳航空航天大学 | A kind of impact overflow double-wall structure of target surface trough of belt |
| CN112234938A (en) * | 2020-10-14 | 2021-01-15 | 景德镇陶瓷大学 | Impact jet cooling system for concentrating solar cell and solar cell device |
| CN113225997A (en) * | 2021-05-13 | 2021-08-06 | 西北工业大学 | Take enhancement of multistage cylindrical boss to strike heat transfer structure |
| CN113374546A (en) * | 2021-06-27 | 2021-09-10 | 西北工业大学 | Array impact structure based on circular truncated cone and cylindrical bulge |
| US11499435B2 (en) * | 2018-10-18 | 2022-11-15 | Mitsubishi Heavy Industries, Ltd. | Gas turbine stator vane, gas turbine provided with same, and method of manufacturing gas turbine stator vane |
Citations (5)
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|---|---|---|---|---|
| CN1126795A (en) * | 1994-08-26 | 1996-07-17 | Abb管理有限公司 | Wall cooled by reflecting flow |
| EP0905353A1 (en) * | 1997-09-30 | 1999-03-31 | Abb Research Ltd. | Impingement cooled wall element |
| EP1574669A2 (en) * | 2004-03-10 | 2005-09-14 | Rolls-Royce Plc | Impingement cooling arrangement witin turbine blades |
| EP3054113A1 (en) * | 2015-02-09 | 2016-08-10 | United Technologies Corporation | Impingement cooled component, corresponding cooling method and gas turbine engine component |
| US20170191417A1 (en) * | 2016-01-06 | 2017-07-06 | General Electric Company | Engine component assembly |
-
2017
- 2017-08-18 CN CN201710710525.8A patent/CN107503801A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1126795A (en) * | 1994-08-26 | 1996-07-17 | Abb管理有限公司 | Wall cooled by reflecting flow |
| EP0905353A1 (en) * | 1997-09-30 | 1999-03-31 | Abb Research Ltd. | Impingement cooled wall element |
| EP1574669A2 (en) * | 2004-03-10 | 2005-09-14 | Rolls-Royce Plc | Impingement cooling arrangement witin turbine blades |
| EP3054113A1 (en) * | 2015-02-09 | 2016-08-10 | United Technologies Corporation | Impingement cooled component, corresponding cooling method and gas turbine engine component |
| US20170191417A1 (en) * | 2016-01-06 | 2017-07-06 | General Electric Company | Engine component assembly |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108223022A (en) * | 2018-01-04 | 2018-06-29 | 沈阳航空航天大学 | A kind of turbulence structure in array jetting cooling |
| US11499435B2 (en) * | 2018-10-18 | 2022-11-15 | Mitsubishi Heavy Industries, Ltd. | Gas turbine stator vane, gas turbine provided with same, and method of manufacturing gas turbine stator vane |
| CN109737788A (en) * | 2018-12-21 | 2019-05-10 | 西北工业大学 | A kind of raised target plate structure reducing flow losses, intensifying impact heat exchange |
| CN109931114A (en) * | 2019-03-15 | 2019-06-25 | 南京航空航天大学 | A kind of novel impinging cooling turbulence structure |
| CN110195615A (en) * | 2019-05-20 | 2019-09-03 | 沈阳航空航天大学 | A kind of impact overflow double-wall structure of target surface trough of belt |
| CN112234938A (en) * | 2020-10-14 | 2021-01-15 | 景德镇陶瓷大学 | Impact jet cooling system for concentrating solar cell and solar cell device |
| CN113225997A (en) * | 2021-05-13 | 2021-08-06 | 西北工业大学 | Take enhancement of multistage cylindrical boss to strike heat transfer structure |
| CN113374546A (en) * | 2021-06-27 | 2021-09-10 | 西北工业大学 | Array impact structure based on circular truncated cone and cylindrical bulge |
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Application publication date: 20171222 |
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