CN110259520A - A kind of design method of shaped air film cooling hole - Google Patents
A kind of design method of shaped air film cooling hole Download PDFInfo
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- CN110259520A CN110259520A CN201910617195.7A CN201910617195A CN110259520A CN 110259520 A CN110259520 A CN 110259520A CN 201910617195 A CN201910617195 A CN 201910617195A CN 110259520 A CN110259520 A CN 110259520A
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- hole
- air film
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Classifications
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- 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
- F01D5/186—Film cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of design methods of shaped air film cooling hole, are designed to shaped air film cooling hole, determine the master data of all kinds of passes, establish computation model；Its extended area ratio is calculated, has more sufficient research for influencing each other between parameters and its Influencing Mechanism.The design method is conducive to instruct engineering practice.By carrying out numerical simulation under different jet angle and the angle of flare for common shaped air film cooling hole; and comparison match difference modelling parameter; including air blowing ratio, ratio of momentum and speed effect colder than lower insulation, hole section temperature field and temperature in borehole and velocity field; it obtains needing matched modelling parameter; and sum up the rule of pass Yu the Parameters variation; find out optimal modelling parameter under certain pass; so as to solve pass parameters according to best modelling parameter is counter, simple and easy design method is provided to design shaped air film cooling hole.
Description
Technical field
The present invention relates to gas-turbine unit air film hole design fields, specifically, being related to power generation Heavy duty gas wheel
The method of the gaseous film control pass design of machine, aero-engine and Vessel personnel.
Background technique
Cylindrical air film hole is using being most generally also the gaseous film control pass for being easiest to manufacture in aero-engine, still
Largely studies have shown that shaped air film hole can effectively weaken air film jet stream penetrating in mainstream, so that air film jet stream holds
It is easily attached on wall surface under mainstream effect, to obtain better Film Cooling.By designing better pass, try
It is one in gaseous film control research now that better Film Cooling is obtained under identical or less cold air mass flow
A hot issue.
In recent years, Thole et al. is in document " Adiabatic Effectiveness Measurements for A
Baseline Shaped Film Cooling Hole " ASME Paper GT2014-25992, in the base for summarizing forefathers' research
A kind of expansion profiled holes of standard: the hole 7-7-7 are proposed on plinth, that is, opening up to the angle of flare and the angle of flare that leans forward is 7 ° of the fan that leans forward
Shape hole.In document " Shaped Hole Literature Review Database, " Penn State of Thole et al.
Experimental and Computational Convection Laboratory(ExCCL),Web,http://
It in www.mne.psu.edu/psuexccl, is measured under different densities using infrared technique, the insulation under different turbulivitys is cold
But efficiency.It was found that compared to cylindrical type air film hole optimal blowing ratio in M=0.5 or so, the hole 7-7-7 can most preferably blowing air film hole
Wind ratio is increased to M=1.5.For identical air blowing ratio, the high operating condition of density ratio, cooling efficiency is also higher.Turbulivity is high
Operating condition, cooling efficiency are then lower.They are, it was also found that be modelling parameter using air blowing ratio different from cylindrical hole simultaneously
Whether simulation cold air is detached from wall surface；Its cooling characteristics of the modelling of entirely accurate, but momentum are all unable to using air blowing ratio and ratio of momentum
Than matching effect than be substantially better than air blowing ratio.
Research shows that scallop hole and the scallop hole that leans forward are wherein relatively easy to manufacture, the preferable passes of cooling.
Although there is the research much about scallop hole and the scallop hole that leans forward at present, it is often absorbed in some structural parameters or boundary
Influence of the condition for profiled holes cooling characteristics, for influencing each other between parameters and its Influencing Mechanism, there has been no fill
The research divided.Also, the influence between parameters is intricate, in order to instruct engineering practice, it is necessary to sum up one easily
In the design criteria that engineering staff uses.Meanwhile by document it can be seen that, the modelling parameters selections of profiled holes and classical cylindrical type
Hole is also changed, in order to which the research carried out under the operating condition of laboratory has certain guidance to anticipate actual engine design
Justice, it is necessary to be studied for the height Conditions Matching and modelling parameter of expanding type hole.
Summary of the invention
In order to avoid the shortcomings of the prior art, the present invention proposes a kind of design method of shaped air film cooling hole.
The technical solution adopted by the present invention to solve the technical problems is:
The design method of shaped air film cooling hole, it is characterised in that the following steps are included:
Step 1. determines the master data of all kinds of passes, establishes computation model；
Choosing scallop hole, the scallop hole that leans forward respectively is 10 kinds of passes, 20 kinds in total；Wherein, α is air film hole efflux angle, and β is exhibition
To the angle of flare, γ is the angle of flare that leans forward；
1 pass type of table
Step 2. calculating simulation finds combustion gas and flows backward point；
Increase with exhibition to angle of flare β, the angle of flare that leans forward γ, the increase of profiled holes discharge area, cold air normal direction momentum
It reduces, wall cooling efficiency rises with it, need to search out wall cooling efficiency and have no the operating condition obviously risen, summarize all operating conditions
Hole in normal velocity cloud atlas in immeasurable cloud atlas and hole；
Step 3. finds the normal direction ratio of momentum that is most preferably averaged；
Data will be calculated and carry out analysis and nondimensionalization processing, propose that the normal direction based on expansion type hole inlet and outlet area ratio is dynamic
Amount ratioThe ratio for indicating air film hole momentum of impinging jet normal component and mainstream momentum, is defined as follows:
Wherein, I is the ratio of air film hole momentum of impinging jet and mainstream momentum that cylindrical section circulation area defines, ρcFor Secondary Flow
Density, ρgFor main current density, UcFor the speed in secondary curtain coating axially bored line direction, UgFor mainstream speed, α is air film hole efflux angle, Ucn
For the component velocity of Secondary Flow normal direction,For the average Secondary Flow normal velocity of area, AR is expanding hole exits area and enter
The definition of the ratio of open area, each value is as follows:
I=ρcUc 2/ρgUg 2
Uc,n=Uc*sinα
AR=Aout/Ain
Step 4. is counter to solve pass；
Its area average is asked to the cold effect of insulation that all operating conditions obtain, scallop hole and the scallop hole that leans forward are best there are one
'sValue, when passValue is bestWhen near value, the cold effect of wall surface air film is best；Determine experiment hole type design,
Determine oneValue, it is counter to solve optimal area ratio, so that it is determined that the angle of the angle of flare:
Beneficial effect
The design method of shaped air film cooling hole proposed by the present invention, is designed film cooling holes, determines each pores
The master data of type, establishes computation model；Its extended area ratio is calculated, for influencing each other between parameters and
Its Influencing Mechanism has more sufficient research.The design method is conducive to instruct engineering practice.By for common shaped air film
Cooling hole carries out numerical simulation, and comparison match difference modelling parameter under different jet angle and the angle of flare, including air blowing ratio, dynamic
Amount obtains needing matched modelling than being insulated cold effect, hole section temperature field and temperature in borehole and velocity field than lower with speed
Parameter, and the rule of pass Yu the Parameters variation is summed up, optimal modelling parameter under certain pass is found out, so as to basis
Best modelling parameter is counter to solve pass parameters, provides simple and easy design method to design shaped air film cooling hole.
Detailed description of the invention
A kind of design method of shaped air film cooling hole of the present invention is made with embodiment with reference to the accompanying drawing further detailed
It describes in detail bright.
Fig. 1 (a), (b), (c) are fan-shaped bore geometry schematic diagram.
Fig. 2 (a), (b), (c), (d) are the fan-shaped bore geometry schematic diagram that leans forward.
Scallop hole and scallop hole side view comparison of leaning forward when Fig. 3 (a), (b) are α=30 °.
Fig. 4 (a), (b) are scallop hole side view comparison of leaning forward when α=30 ° and α=45 °.
In figure:
It is exhibition be that flow to angle of flare θ be wall thickness d to angle of flare γ be air film bore dia L is air film that α, which is efflux angle β,
Hole axle line length L1For scallop hole expansion segment depth L2For the scallop hole expansion segment depth that leans forward
Specific embodiment
The present embodiment is a kind of design method of shaped air film cooling hole.
(a), (b), (c)~Fig. 4 (a), (b) refering to fig. 1, in the design method of the present embodiment shaped air film cooling hole, choosing
Two kinds of representative profiled holes are taken, one is scallop holes, only have exhibition to the angle of flare；Another kind is the scallop hole that leans forward, it
It is to be expanded again to flow direction on the basis of scallop hole, not only there is exhibition also to have to the angle of flare and flow to the angle of flare.Two kinds of passes
Expanding section depth is the 3/4 of hole length.
The profiled holes gaseous film control researched and analysed under 30 ° and 45 ° of two different air film hole efflux angles in the present embodiment is special
Property.
For common scallop hole and the scallop hole that leans forward, numerical simulation is carried out under different jet angle and the angle of flare, and compare
In modelling parameters different compared with matching, including air blowing ratio, ratio of momentum and speed effect colder than lower insulation, hole section temperature field and hole
Temperature and velocity field obtain needing matched modelling parameter, and sum up the rule of pass Yu the Parameters variation, find out certain hole
Optimal modelling parameter under type provides design shaped air film hole so as to solve pass parameters according to best modelling parameter is counter
A kind of criterion method；Specifically includes the following steps:
The first step, the master data for determining all kinds of passes, establish computation model；
Choosing scallop hole, the scallop hole that leans forward respectively is 10 kinds of passes, 20 kinds in total；Wherein, α is air film hole efflux angle, and β is exhibition
To the angle of flare, γ is the angle of flare that leans forward；
1 pass type of table
Second step, calculating simulation find combustion gas and flow backward point；
With the increase of angle of flare β, γ, the i.e. increase of profiled holes discharge area, the reduction of cold air normal direction momentum is most of
The wall cooling efficiency of operating condition can rise with it, and need to find wall cooling efficiency and have no what obvious rising was even also declined
Operating condition summarizes in the hole of all operating conditions normal velocity cloud atlas in immeasurable cloud atlas and hole.
Third step finds the normal direction ratio of momentum that is most preferably averaged；
Data will be calculated and carry out analysis and nondimensionalization processing, propose that the normal direction based on expansion type hole inlet and outlet area ratio is dynamic
Amount ratioThe ratio for indicating air film hole momentum of impinging jet normal component and mainstream momentum, is defined as follows:
Wherein, I is the ratio of air film hole momentum of impinging jet and mainstream momentum that cylindrical section circulation area defines, ρcFor Secondary Flow
Density, ρgFor main current density, UcFor the speed in secondary curtain coating axially bored line direction, UgFor mainstream speed, α is air film hole efflux angle,
Uc,nFor the component velocity of Secondary Flow normal direction,For the average Secondary Flow normal velocity of area, AR be expanding hole exits area with
The definition of the ratio of inlet area, each value is as follows:
I=ρcUc 2/ρgUg 2
Uc,n=Uc*sinα
AR=Aout/Ain
4th step counter solves pass；
Its area average is asked to the cold effect of insulation that all operating conditions obtain, scallop hole and the scallop hole that leans forward are best there are one
'sValue, when passValue is bestWhen near value, the cold effect of wall surface air film is best；Determine experiment hole type design,
Determine oneValue, it is counter to solve optimal area ratio, so that it is determined that the angle of the angle of flare:
In conjunction with the application of scallop hole design method under different operating conditions:
Computation model is established to scallop hole, for guarantee numerical simulation operating condition closer to reality Turbomachinery work operating condition,
The selection of design simulation operating condition guarantees that the Reynolds number of length is identical characterized by air film bore dia, Re=11000, then by blowing ratio M
It is 0.5,1.0,1.5,2.0 determining four Secondary Flow flows, in conjunction with the various combination of efflux angle and the angle of flare, specific operating condition is such as
It is listed in Table, wherein α is air film hole efflux angle, and β is exhibition to the angle of flare, and γ is the angle of flare that leans forward；
2 scallop hole of table calculates operating condition table (Red=11000)
The operating condition for comparing the different angles of flare, such as α=45 °, sector wall surface of the hole is insulated cold effect exhibition to mean value, integrally when β=15 °
Exhibition increase to mean value with the increase of air blowing ratio until M=2.0 just occur cold air be detached from wall surface the phenomenon that, illustrate for
For the scallop hole of this geometry, optimal blowing can reach 1.5 than, compare α=45 °, and the scallop hole of β=11 ° exists
Under identical air blowing ratio, opens up to mean value and improve 15% to 30%；Compared with α=45 °, the scallop hole of β=7 ° is promoted under low blowing
20% to 100%, air blowing ratio is bigger, increased amplitude is also bigger.
And pass through analysis hole middle section temperature of zero dimension distribution, it can be seen that the specifying information of some air film jet streams.Small
Under air blowing ratio, the cold air that each pass sprays just is attached on wall surface completely after ejection, and the air-film thickness formed is very thin,
The expansion angle of scallop hole is bigger simultaneously, and the air-film thickness of formation is thinner, this is because expansion angle is bigger, hole exits open up to
Width is longer, is easy to be attached on wall surface in the case where mainstream acts on after jet stream ejection, forms one layer than relatively thin air film.Big
Under air blowing ratio, for opening up the scallop hole small to expansion angle, since to penetrate momentum higher for normal direction, air film jet core area departing from
Wall surface, i.e., the minimum part of temperature does not contact wall surface in air film jet stream, and the phenomenon that jet core is detached from wall surface has occurred；With
The increase of the angle of flare, the normal direction of cold air penetrate momentum reduction, and there is a phenomenon where jet cores to be detached from wall surface.
For the analysis of the distribution of temperature in borehole and velocity field, it is found that for scallop hole, hole is substantially not present
Interior combustion gas is flowed backward；For the scallop hole that leans forward, combustion gas flow backward occur under the biggish operating condition of the angle of flare, i.e. 30-15-15 and
Two operating conditions of 45-15-15.This shows that when the angle of flare increases to a certain extent, the cold effect of wall surface air film does not rise anti-drop, due to combustion
Gas flows backward, and the span-wise length of hole exits can not be fully utilized；Blending then contacts cold air with wall surface in hole ahead of time
When had built up certain temperature, cause the decline of cooling effect.
Claims (1)
1. a kind of design method of shaped air film cooling hole, it is characterised in that the following steps are included:
Step 1. determines the master data of all kinds of passes, establishes computation model；
Choosing scallop hole, the scallop hole that leans forward respectively is 10 kinds of passes, 20 kinds in total；Wherein, α is air film hole efflux angle, β Zhan Xiangkuo
Subtended angle, γ are the angle of flare that leans forward；
1 pass type of table
Step 2. calculating simulation finds combustion gas and flows backward point；
Increase with exhibition to angle of flare β, the angle of flare that leans forward γ, the increase of profiled holes discharge area, cold air normal direction momentum are reduced,
Wall cooling efficiency rises with it, and need to search out wall cooling efficiency and have no the operating condition obviously risen, summarize the hole of all operating conditions
Normal velocity cloud atlas in interior immeasurable cloud atlas and hole；
Step 3. finds the normal direction ratio of momentum that is most preferably averaged；
Data will be calculated and carry out analysis and nondimensionalization processing, propose the normal direction ratio of momentum based on expansion type hole inlet and outlet area ratioThe ratio for indicating air film hole momentum of impinging jet normal component and mainstream momentum, is defined as follows:
Wherein, I is the ratio of air film hole momentum of impinging jet and mainstream momentum that cylindrical section circulation area defines, ρcFor secondary current density,
ρgFor main current density, UcFor the speed in secondary curtain coating axially bored line direction, UgFor mainstream speed, α is air film hole efflux angle, Uc,nIt is two
The component velocity of secondary stream normal direction,For the average Secondary Flow normal velocity of area, AR is expanding hole exits area and inlet face
The definition of long-pending ratio, each value is as follows:
I=ρcUc 2/ρgUg 2
Uc,n=Uc*sinα
AR=Aout/Ain
Step 4. is counter to solve pass；
Its area average is asked to the cold effect of insulation that all operating conditions obtain, scallop hole and the scallop hole that leans forward are optimal there are one
Value, when passValue is bestWhen near value, the cold effect of wall surface air film is best；It determines experiment hole type design, determines
OneValue, it is counter to solve optimal area ratio, so that it is determined that the angle of the angle of flare:
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110717276A (en) * | 2019-10-14 | 2020-01-21 | 西北工业大学 | Method for detecting and evaluating geometric structure of special-shaped air film hole based on industrial CT scanning |
| CN112084597A (en) * | 2020-09-08 | 2020-12-15 | 北京航空航天大学 | Single-exhaust-film cooling efficiency two-dimensional distribution AI prediction method based on bell-shaped curve |
| CN112146127A (en) * | 2020-08-13 | 2020-12-29 | 南京航空航天大学 | Special-shaped mixing hole for adjusting temperature distribution of outlet of combustion chamber |
| CN112627904A (en) * | 2020-12-23 | 2021-04-09 | 西北工业大学 | Novel bucket type air film cooling hole and design method thereof |
| CN113027537A (en) * | 2021-03-11 | 2021-06-25 | 河北工业大学 | Air film hole structure and turbine blade |
| CN113609615A (en) * | 2021-08-03 | 2021-11-05 | 中国航发湖南动力机械研究所 | Turbine blade multi-exhaust-film cold effect correction calculation method |
| CN113623015A (en) * | 2021-08-17 | 2021-11-09 | 清华大学 | Sectional type air film cooling hole and design method thereof |
| CN113864822A (en) * | 2021-10-13 | 2021-12-31 | 西北工业大学 | Machining ring type prefilming swirler |
| CN114687809A (en) * | 2022-03-10 | 2022-07-01 | 西北工业大学 | Design method and application for fan-shaped air film hole of turbine blade |
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- 2019-07-10 CN CN201910617195.7A patent/CN110259520A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110717276A (en) * | 2019-10-14 | 2020-01-21 | 西北工业大学 | Method for detecting and evaluating geometric structure of special-shaped air film hole based on industrial CT scanning |
| CN112146127A (en) * | 2020-08-13 | 2020-12-29 | 南京航空航天大学 | Special-shaped mixing hole for adjusting temperature distribution of outlet of combustion chamber |
| CN112084597A (en) * | 2020-09-08 | 2020-12-15 | 北京航空航天大学 | Single-exhaust-film cooling efficiency two-dimensional distribution AI prediction method based on bell-shaped curve |
| CN112084597B (en) * | 2020-09-08 | 2021-06-15 | 北京航空航天大学 | Single-exhaust-film cooling efficiency two-dimensional distribution AI prediction method based on bell-shaped curve |
| CN112627904A (en) * | 2020-12-23 | 2021-04-09 | 西北工业大学 | Novel bucket type air film cooling hole and design method thereof |
| CN112627904B (en) * | 2020-12-23 | 2023-06-09 | 西北工业大学 | Novel bucket type air film cooling hole and design method thereof |
| CN113027537A (en) * | 2021-03-11 | 2021-06-25 | 河北工业大学 | Air film hole structure and turbine blade |
| CN113609615A (en) * | 2021-08-03 | 2021-11-05 | 中国航发湖南动力机械研究所 | Turbine blade multi-exhaust-film cold effect correction calculation method |
| CN113609615B (en) * | 2021-08-03 | 2023-09-01 | 中国航发湖南动力机械研究所 | Turbine blade multi-exhaust gas film cold efficiency correction calculation method |
| CN113623015A (en) * | 2021-08-17 | 2021-11-09 | 清华大学 | Sectional type air film cooling hole and design method thereof |
| CN113864822A (en) * | 2021-10-13 | 2021-12-31 | 西北工业大学 | Machining ring type prefilming swirler |
| CN114687809A (en) * | 2022-03-10 | 2022-07-01 | 西北工业大学 | Design method and application for fan-shaped air film hole of turbine blade |
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Application publication date: 20190920 |