CN108416181A - A kind of all-pass stream turbine multi-dimensional Coupling Fast design method - Google Patents
A kind of all-pass stream turbine multi-dimensional Coupling Fast design method Download PDFInfo
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- CN108416181A CN108416181A CN201810531115.1A CN201810531115A CN108416181A CN 108416181 A CN108416181 A CN 108416181A CN 201810531115 A CN201810531115 A CN 201810531115A CN 108416181 A CN108416181 A CN 108416181A
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Abstract
The present invention provides a kind of all-pass stream turbine multi-dimensional Coupling Fast design method, further includes after turbine pneumatic design cycle：Turbo blade field and flow, efficiency and power are calculated using known Three-dimensional Numerical Simulation Method；For shrouded blade, leaf top hat leakage stream 1D/2D mathematical models and blade root wheel rim sealing leak stream 1D/2D mathematical models are dissolved into turbo blade mainstream Three-dimensional numerical calculation and realize that multi-dimensional Coupling calculates with it；For not shrouded blade, blade root wheel rim sealing leak stream 1D/2D mathematical models are dissolved into turbo blade mainstream Three-dimensional numerical calculation and realize that multi-dimensional Coupling calculates with it；The above quickly design of cycle calculates step, until turbine overall performance reaches predetermined design target；Then carry out the full Three-dimensional numerical calculation of all-pass stream turbine, explication de texte turbine interior flow field and overall performance.The present invention, which carries, can effectively improve turbine pneumatic efficiency, and can take into account computational efficiency and computational accuracy, shorten the turbine engineering design period.
Description
Technical field
The present invention relates to a kind of Pneumatic design method of gas turbine/aero-turbine more particularly to a kind of all-pass
Flow turbine multi-dimensional Coupling Fast design method.
Background technology
Turbine pneumatic designs, and in early days based on one-dimensional flow and the design of S2 stream interfaces, mainly includes the following steps that：It is root first
Carry out one-dimensional aerodynamic analysis according to general design requirement, groundwork is Rational choice turbine dimensionless design parameter at different levels with true
The parameters such as the speed triangle of fixed leaf middle sections at different levels, and then turbine meridional channel form is generated, it in the process can be according to need
Reasonably select even fully optimization to basic pneumatic and geometric parameter on low latitude design space；Then from two-dimentional level
It sets out, chooses rational twisting rule to obtain the speed triangle in the high section of stage of turbine difference leaf, and pass through inverse problem calculation
Key aerodynamic parameter is respectively arranged to obtain turbine, and then discharges into the parameters such as outlet flow angle according to blade and carries out the different high sections of leaf
Leaf grating moulding, and utilize the reasonability of S1 numerical simulation means inspection blade design；Carry out the product of blade three-dimensional on this basis
It is folded, and the overall performance and parameter distribution for obtaining turbine part are calculated using S2 or quasi three numerical simulation means, then carry out
Preliminary flow analysis and diagnosis；In the case where design result is met the requirements using full Three-dimensional simulation to turbine interior stream
Field carries out more careful diagnosis, the overall performance of comprehensive assessment turbine；Then it changes repeatedly until obtaining satisfied design result.
Develop by decades, above-mentioned conventional turbine pneumatic design technology is more perfect, and turbine design ability and design level obtain
To significant increase.
It is the important composition component of gas turbine/aero-engine in view of turbine, series is relatively more, and efficiency significantly affects
Engine overall performance.Practical turbine part due to running etc. completely, between turning quiet, equipotential between rotor blade and casing
Inevitable gap, sealing, step structure etc. are set, gas leakage necessarily occurs, these factors have clearly deteriorated turbine performance.Tradition meaning
In justice turbine pneumatic design be mainly turbine main channel design, however turbine main channel design calculate there is boundary conditions not
Really, and it cannot reflect the weakness such as multiple dimensioned, strong blending flow performance of objective reality in turbine.Due to ignoring in design
Petiolarea seal flow feature, in true gas turbine/aero-engine environment, the performance of turbine main channel pneumatic design is received
Benefit will be necessarily significantly affected.
Fast development with test method and numerical computation method and the requirements at the higher level to turbine pneumatic efficiency, having must
Ignored flowing details and feature in conventional turbine pneumatic design are fully considered in the fine pneumatic design of turbine, and herein
On the basis of targetedly inquire into turbine interior fining flow organization mode, designed for turbine pneumatic and increase new degree of freedom,
And be further improved turbine design ways and means etc., the final further promotion for realizing turbine design ability.However, by mesh
Before, not yet see the relevant report for promoting turbine design ability.
Invention content
The purpose of the invention is to which turbine pneumatic efficiency can be effectively improved, and computational efficiency and computational accuracy can be taken into account,
Shorten the turbine engineering design period and a kind of all-pass stream turbine multi-dimensional Coupling Fast design method is provided.
The object of the present invention is achieved like this：Further include following steps after turbine pneumatic design cycle：
Step 1：Using known Three-dimensional Numerical Simulation Method to turbo blade field and flow, efficiency and power into
Row calculates；
Step 2：If Three-dimensional numerical calculation does not restrain in step 1, changes computation model and repeat step 1, until step
Three-dimensional computations restrain in rapid 1；
Step 3：Judge turbo blade whether be preced with by band：If with hat, leaf top is preced with leakage stream 1D/2D mathematical models and leaf
Root wheel rim sealing leak stream 1D/2D mathematical models are dissolved into turbo blade mainstream Three-dimensional numerical calculation and realize multidimensional coupling with it
It is total to calculate；If without hat, blade root wheel rim sealing leak stream 1D/2D mathematical models are only dissolved into three dimension of turbo blade mainstream
Realize that multi-dimensional Coupling calculates during value calculates and with it；
Step 4：If the Three-dimensional numerical calculation that step 3 obtains does not restrain, multi-dimensional Coupling computation model and repetition are changed
Step 3, until multi-dimensional Coupling calculates convergence in step 3；
Step 5：If the indicators of overall performance obtained in step 4 does not meet predetermined design index, design optimization integral shroud
With blade root wheel rim sealing structure and repeat step 3~4, until the obtained indicators of overall performance of step 4 and predetermined design target phase
Meet, wherein overall performance includes flow, efficiency, power；
Step 6：The full Three-dimensional numerical calculation of all-pass stream turbine, explication de texte are carried out using known Three-dimensional Numerical Simulation Method
Turbine interior flow field and overall performance.
The invention also includes some such structure features：
1. passing through integral shroud/wheel rim sealing leak stream 1D mathematical models and turbo blade mainstream three-dimensional numerical value meter in step 3
Calculation is coupled to predict influence of the petiolarea sealing leak stream to mainstream；Then pass through integral shroud/wheel rim sealing leak stream 2D mathematical modulos
Type couples to calculate with mainstream is distributed the influence brought further to consider that the circumferential asymmetry of petiolarea sealing leak stream parameter is even.
Compared with prior art, the beneficial effects of the invention are as follows：The present invention is fully realizing turbine actual working environment
On the basis of, by being fully considered in being designed in turbine pneumatic, ignored leaf top hat and the sealing of blade root wheel rim are let out in traditional design
Leakage current moves details, is designed for turbine pneumatic and increases new degree of freedom, to improve turbine pneumatic efficiency, and by turbine leaf top
Integral shroud and blade root wheel rim Leakage Flow carry out dimension-reduction treatment, and realize that multi-dimensional Coupling quickly calculates with turbo blade mainstream,
To take into account computational efficiency and computational accuracy, so as to shorten the turbine engineering design period.
Description of the drawings
Fig. 1 is the turbine meridian view designed by traditional design method；
Fig. 2 is the quick design flow diagram of all-pass stream turbine multi-dimensional Coupling；
Fig. 3 is a quick design example of all-pass stream turbine multi-dimensional Coupling.
In figure：1D, 2D and 3D be respectively one-dimensional, two and three dimensions.
Specific implementation mode
Present invention is further described in detail with specific implementation mode below in conjunction with the accompanying drawings.
The all-pass stream turbine multi-dimensional Coupling Fast design method of the present invention is based on existing known conventional turbo blade
Pneumatic design recycles.
Turbo blade Pneumatic design method mainly includes the following steps that：It is that one-dimensional gas is carried out according to general design requirement first
Dynamic analysis, groundwork are Rational choice turbine dimensionless design parameter at different levels with the speed triangle of determination leaf middle sections at different levels
The parameters such as shape, and then turbine meridional channel form is generated, it in the process can be as needed on low latitude design space to basic
Pneumatic and geometric parameter reasonably select even fully optimization；Then from two-dimentional level, rational twisting rule is chosen
To obtain the speed triangle in the high section of stage of turbine difference leaf, and key aerodynamic ginseng is respectively arranged to obtain turbine by inverse problem calculation
Number, and then the leaf grating moulding that the parameters such as outlet flow angle carry out the different high sections of leaf is discharged into according to blade, and utilize S1 Numerical-Modes
Quasi- means examine the reasonability of blade design；The product for carrying out blade three-dimensional on this basis is folded, and utilizes S2 or quasi- three-dimensional numerical values
Simulation means calculate the overall performance and parameter distribution for obtaining turbine part, then carry out preliminary flow analysis and diagnosis；
Design result uses full Three-dimensional simulation to carry out more careful diagnosis to turbine interior flow field in the case of meeting the requirements, comprehensive
Assess the overall performance of turbine；Then it changes repeatedly until obtaining satisfied design result.
After the turbine pneumatic design cycle of a routine, turbine main channel stator blade 1 and movable vane piece 2 are obtained, sees figure
1.It is also needed on this basis by following steps (see Fig. 2)：
1) overall to turbo blade field and flow, efficiency and power etc. using known Three-dimensional Numerical Simulation Method
Performance parameter is calculated；
If 2) Three-dimensional numerical calculation does not restrain in step (1), by changing the means such as computation model, step is repeated
(1), until three-dimensional computations restrain in step (1)；
3) judge turbo blade whether if be preced with leakage stream 1D/2D mathematical models and blade root is taken turns by band hat with hat by leaf top
Edge sealing leak stream 1D/2D mathematical models are dissolved into turbo blade mainstream Three-dimensional numerical calculation and realize multi-dimensional Coupling meter with it
It calculates, if without hat, blade root wheel rim sealing leak stream 1D/2D mathematical models is only dissolved into turbo blade mainstream three-dimensional numerical value meter
Realize that multi-dimensional Coupling calculates in calculation and with it；
If 4) Three-dimensional numerical calculation does not restrain in step (3), by changing the means such as multi-dimensional Coupling computation model, weight
Multiple step (3), until multi-dimensional Coupling calculates convergence in step (3)；
5) if the indicators of overall performance obtained in step (4) does not meet predetermined design index, pass through design optimization leaf
Hat and the means such as blade root wheel rim sealing structure, repeat step (3)~(4), until the obtained indicators of overall performance of step (4) with it is pre-
Determine design object to be consistent, wherein overall performance includes flow, efficiency, power etc.；
6) the full Three-dimensional numerical calculation of all-pass stream turbine, explication de texte turbine are carried out using known Three-dimensional Numerical Simulation Method
Interior flow field and overall performance.
The present invention can also include：
1) pass through integral shroud/wheel rim sealing leak stream 1D mathematical models and turbo blade mainstream three-dimensional numerical value in step (3)
Calculating is coupled to predict influence of the petiolarea sealing leak stream to mainstream；Then pass through integral shroud/wheel rim sealing leak stream 2D mathematics
Model couples to calculate with mainstream is distributed the influence brought further to consider that the circumferential asymmetry of petiolarea sealing leak stream parameter is even.
Single-stage shrouded turbines designed by the invention is shown in Fig. 3 (3 be crown structure, and 4 be wheel rim sealing structure), gas
Efficiency of movement can be improved 0.5 percentage point or more.
Present invention may also apply to the designs of the efficient aerodynamic of multistage turbine.
To sum up, the present invention provides a kind of all-pass stream turbine multi-dimensional Coupling Fast design method, includes the turbine of a routine
Pneumatic design recycles, and further includes following steps after which：First with known Three-dimensional Numerical Simulation Method to turbo blade
The Performance Parameters such as field and flow, efficiency and power are calculated；For shrouded blade, leaf top is preced with leakage stream
1D/2D mathematical models and blade root wheel rim sealing leak stream 1D/2D mathematical models are dissolved into turbo blade mainstream Three-dimensional numerical calculation
In and with its realize multi-dimensional Coupling calculate；For not shrouded blade, blade root wheel rim sealing leak stream 1D/2D mathematical models are incorporated
Realize that multi-dimensional Coupling calculates in turbo blade mainstream Three-dimensional numerical calculation and with it；By changing computation model, design optimization
The means such as integral shroud and blade root wheel rim sealing structure recycle the above quickly design and calculate step, until turbine overall performance reaches pre-
Determine design object；Then carry out the full Three-dimensional numerical calculation of all-pass stream turbine, explication de texte turbine interior flow field and overall performance.It adopts
Turbine pneumatic efficiency can be effectively improved with all-pass stream turbine multi-dimensional Coupling Fast design method provided by the invention, and meter can be taken into account
Efficiency and computational accuracy are calculated, the turbine engineering design period is shortened.
Claims (2)
1. a kind of all-pass stream turbine multi-dimensional Coupling Fast design method, it is characterised in that：After turbine pneumatic design cycle also
Include the following steps：
Step 1：Turbo blade field and flow, efficiency and power are counted using known Three-dimensional Numerical Simulation Method
It calculates；
Step 2：If Three-dimensional numerical calculation does not restrain in step 1, changes computation model and repeat step 1, until in step 1
Three-dimensional computations restrain；
Step 3：Judge turbo blade whether be preced with by band：If with hat, leaf top is preced with leakage stream 1D/2D mathematical models and blade root is taken turns
Edge sealing leak stream 1D/2D mathematical models are dissolved into turbo blade mainstream Three-dimensional numerical calculation and realize multi-dimensional Coupling meter with it
It calculates；If without hat, blade root wheel rim sealing leak stream 1D/2D mathematical models are only dissolved into turbo blade mainstream three-dimensional numerical value meter
Realize that multi-dimensional Coupling calculates in calculation and with it；
Step 4：If the Three-dimensional numerical calculation that step 3 obtains does not restrain, changes multi-dimensional Coupling computation model and repeat step
3, until multi-dimensional Coupling calculates convergence in step 3；
Step 5：If the indicators of overall performance obtained in step 4 does not meet predetermined design index, design optimization integral shroud and leaf
Root wheel rim sealing structure simultaneously repeats step 3~4, until the indicators of overall performance that step 4 obtains is consistent with predetermined design target,
Wherein overall performance includes flow, efficiency, power；
Step 6：The full Three-dimensional numerical calculation of all-pass stream turbine, explication de texte turbine are carried out using known Three-dimensional Numerical Simulation Method
Interior flow field and overall performance.
2. a kind of all-pass stream turbine multi-dimensional Coupling Fast design method according to claim 1, it is characterized in that：In step 3
In be coupled by integral shroud/wheel rim sealing leak stream 1D mathematical models and turbo blade mainstream Three-dimensional numerical calculation to predict petiolarea
Influence of the sealing leak stream to mainstream；Then coupled with mainstream by integral shroud/wheel rim sealing leak stream 2D mathematical models calculating come
Further consider that the circumferential asymmetry of petiolarea sealing leak stream parameter is even and is distributed the influence brought.
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| CN2018103694915 | 2018-04-24 | ||
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114087029A (en) * | 2020-08-25 | 2022-02-25 | 中国航发商用航空发动机有限责任公司 | Active control method and system for turbine blade tip clearance and aircraft engine |
| CN114776389A (en) * | 2022-03-16 | 2022-07-22 | 北京航空航天大学 | Shrouded turbine with flange plate step casing |
| CN115062560A (en) * | 2022-06-16 | 2022-09-16 | 毕节高新技术产业开发区国家能源大规模物理储能技术研发中心 | Turbine multi-scale flow reduced-order coupling method based on machine learning |
-
2018
- 2018-05-29 CN CN201810531115.1A patent/CN108416181A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114087029A (en) * | 2020-08-25 | 2022-02-25 | 中国航发商用航空发动机有限责任公司 | Active control method and system for turbine blade tip clearance and aircraft engine |
| CN114087029B (en) * | 2020-08-25 | 2024-05-17 | 中国航发商用航空发动机有限责任公司 | Turbine blade tip clearance active control method, system and aeroengine |
| CN114776389A (en) * | 2022-03-16 | 2022-07-22 | 北京航空航天大学 | Shrouded turbine with flange plate step casing |
| CN114776389B (en) * | 2022-03-16 | 2024-03-12 | 北京航空航天大学 | Shrouded turbine with rim plate step casing |
| CN115062560A (en) * | 2022-06-16 | 2022-09-16 | 毕节高新技术产业开发区国家能源大规模物理储能技术研发中心 | Turbine multi-scale flow reduced-order coupling method based on machine learning |
| CN115062560B (en) * | 2022-06-16 | 2024-06-21 | 毕节高新技术产业开发区国家能源大规模物理储能技术研发中心 | Turbine multi-scale flow reduced-order coupling method based on machine learning |
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