CN111783306A - Turbine blade cold air quantity and cold effect characteristic analysis method - Google Patents

Turbine blade cold air quantity and cold effect characteristic analysis method Download PDF

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CN111783306A
CN111783306A CN202010642812.1A CN202010642812A CN111783306A CN 111783306 A CN111783306 A CN 111783306A CN 202010642812 A CN202010642812 A CN 202010642812A CN 111783306 A CN111783306 A CN 111783306A
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heat exchange
gas side
cold air
cold
cooling
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CN111783306B (en
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李洋
刘涛
贺宜红
薛树林
赵兰芳
董丽坤
陈文彬
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Hunan Aviation Powerplant Research Institute AECC
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • 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
    • F01D5/12—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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/08—Thermal analysis or thermal optimisation

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Abstract

The utility model provides a turbine blade cold air volume and cold effect characteristic analysis method, belongs to cooling analysis technical field, and this analysis method includes: obtaining gas side inlet parameters, one-dimensional flow channel parameters, blade parameters and gas side heat exchange coefficients h of the turbine bladesg(ii) a Determining cooling design parameters for the turbine blade; starting iteration step to determine estimated cold air quantity
Figure DDA0002571878750000011
According to the gas side inlet parameter, the one-dimensional runner parameter, the blade parameter and the gas side heat exchange coefficienthgCooling design parameters and estimated cooling capacity
Figure DDA0002571878750000012
Obtaining the actual amount of cold air
Figure DDA0002571878750000013
Obtaining estimated cooling air quantity
Figure DDA0002571878750000014
And the actual amount of cold air
Figure DDA0002571878750000015
And the estimated amount of cold gas
Figure DDA0002571878750000016
And actual amount of cold air
Figure DDA0002571878750000017
Average value y of
Figure DDA0002571878750000018
Comparing the size of λ to 1%; if lambda is less than or equal to 1%, outputting the actual cold air quantity
Figure DDA0002571878750000019
Cooling design parameters are calculated, and the analysis results of the turbine blade cold air quantity and the cold effect characteristic are obtained; if lambda is more than 1%, the iteration step is started, and the actual cold air quantity is used
Figure DDA00025718787500000110
Updating the estimated cold gas volume
Figure DDA00025718787500000111
Until lambda is less than or equal to 1 percent. The analysis method is suitable for the turbine blades with different cooling structures, and is wide in application range.

Description

Turbine blade cold air quantity and cold effect characteristic analysis method
Technical Field
The disclosure relates to the technical field of cooling analysis of turbine blades, in particular to a method for analyzing cold air quantity and cold effect characteristics of turbine blades.
Background
The increase of the turbine front temperature is one of the key factors for developing advanced aircraft engines, the increasingly high turbine front inlet temperature requires more advanced cooling technology, and the high-precision cooling analysis technology is one of the key technologies for advanced cooling design technology. The method has the advantages that the turbine blade cold air quantity analysis precision is improved, and the method has important significance for accurate evaluation of the performance of the engine in the one-dimensional design stage of the engine.
In the one-dimensional design stage of the existing turbine blade, a cold air quantity evaluation method mainly adopts a similar blade equivalent cold air quantity comparison method. The analogy method is mainly characterized in that the cold air flow of an actual blade is inversely calculated through the same equivalent cold air quantity by referring to the existing mature cooling blade under the condition that the engine power and the temperature level of a turbine front inlet are equivalent. In the definition of the equivalent cold air quantity, two factors of a heat exchange coefficient and a heat exchange area at the gas side are mainly considered, and no factor for cooling an inner cavity exists. Therefore, the equivalent cold air quantity analogy method is only suitable for the calculation of the cold air quantity and the cold efficiency of the turbine blade adopting the same cooling structure. In addition, based on the equivalence cold gas quantity analogy method, the heat balance is based on a heat balance route in which the convection heat exchange of the gas side and the heat storage quantity of the cold gas side are balanced, the heat conduction balance in the wall surface of the blade and the flow heat exchange balance of the inner cavity are ignored, and the estimation precision is greatly influenced by the deviation of the cooling efficiency of the inner cavity.
The above information disclosed in the background section is only for enhancement of understanding of the background of the present disclosure and therefore it may contain information that does not constitute prior art that is known to a person of ordinary skill in the art.
Disclosure of Invention
The invention aims to provide a wheel blade cold air quantity and cold effect characteristic analysis method which is accurate in analysis result and wide in application range.
In order to achieve the purpose, the technical scheme adopted by the disclosure is as follows:
according to a first aspect of the present disclosure, there is provided a method for analyzing the amount and characteristics of cold air in a turbine blade, comprising:
obtaining the gas side inlet parameters, one-dimensional flow channel parameters, blade parameters and gas side heat exchange coefficients h of the turbine bladesg；
Determining cooling design parameters for the turbine blade;
starting iteration step to determine estimated cold air quantity
Figure BDA0002571878730000021
According to the gas side inlet parameter, the one-dimensional runner parameter, the blade parameter and the gas side heat exchange coefficient hgThe cooling design parameter and the estimated cooling air quantity
Figure BDA0002571878730000022
Obtaining the actual amount of cold air
Figure BDA0002571878730000023
Obtaining the estimated cold gas amount
Figure BDA0002571878730000024
And the actual amount of cold air
Figure BDA0002571878730000025
And the estimated cold gas amount
Figure BDA0002571878730000026
And the actual amount of cold air
Figure BDA0002571878730000027
Average value y of
Figure BDA0002571878730000028
Comparing the size of λ to 1%;
if lambda is less than or equal to 1%, outputting the actual cold air quantity
Figure BDA0002571878730000029
Cooling design parameters are calculated, and the analysis results of the turbine blade cold air quantity and the cold effect characteristic are obtained; if lambda is more than 1%, the iteration step is started, and the actual cold air quantity is used
Figure BDA00025718787300000210
Updating the estimated cold gas amount
Figure BDA00025718787300000211
Until lambda is less than or equal to 1 percent.
In the exemplary embodiment of the present disclosure, the gas side heat exchange coefficient h is determined according to the gas side inlet parameter, the one-dimensional runner parameter, the vane parameter and the gas side heat exchange coefficientgThe cooling design parameter and the estimated cooling air quantity
Figure BDA00025718787300000212
Obtaining the actual amount of cold air
Figure BDA00025718787300000213
The method comprises the following steps:
obtaining the gas side heat exchange area A of the turbine blade according to the one-dimensional flow channel parameters and the blade parametersgAnd according to the gas side inlet parameter and the gas side heat exchange coefficient hgAnd the cooling design parameter is used for obtaining the gas side heat exchange quantity Q of the turbine blade1；
According to the cooling design parameter and the gas side heat exchange area AgObtaining the internal heat exchange area A of the turbine bladecAnd according to the heat exchange coefficient h of the gas sidegGas side heat exchange area AgThe internal heat exchange area AcAnd the cooling design parameter obtains the cool air side wall temperature T of the turbine bladew,c；
According to the estimated cold gas quantity
Figure BDA00025718787300000214
And cooling design parameters to obtain the cold air side heat exchange coefficient h of the turbine bladecAnd cold air outlet temperature Tc,out；
According to the gas side inlet parameters, the cooling design parameters and the cold gas side wall temperature Tw,cAnd the cooling outlet temperature Tc,outObtaining the actual amount of cold air
Figure BDA0002571878730000031
In exemplary embodiments of the present disclosure, the gas side inlet parameter comprises a gas side equivalent inlet average temperature; the one-dimensional flow channel parameters comprise the average blade height of the blades and the axial chord length of the blades; the blade parameters include the number of blades and the blade bending coefficient.
In exemplary embodiments of the present disclosure, the cooling design parameters include gas side limiting wall temperature, cold air inlet temperature, temperature reserve value, number of inner chambers, inner chamber axial dimension coefficient, inner chamber heat transfer enhancement coefficient, average wall thickness, and ratio of inner and outer heat transfer areas.
In the exemplary embodiment of the disclosure, the gas side heat exchange area A of the turbine blade is obtained according to the one-dimensional flow channel parameter and the blade parametergAnd according to the gas side inlet parameter and the gas side heat exchange coefficient hgAnd the cooling design parameter is used for obtaining the gas side heat exchange quantity Q of the turbine blade1The method comprises the following steps:
obtaining the gas side heat exchange area A according to the average blade height of the blades, the axial chord length of the blades and the bending and twisting coefficient of the bladesg；
According to the heat exchange coefficient h of the gas sidegGas side heat exchange area AgObtaining the gas side heat exchange quantity Q through the equivalent inlet average temperature of the gas side, the temperature reserve value and the gas side limiting wall temperature1。
In exemplary embodiments of the present disclosure, the cooling is performed according to theBut design parameters and the gas side heat exchange area AgObtaining the internal heat exchange area A of the turbine bladecAnd according to the heat exchange coefficient h of the gas sidegGas side heat exchange area AgThe internal heat exchange area AcAnd the cooling design parameter obtains the cool air side wall temperature T of the turbine bladew,cThe method comprises the following steps:
according to the heat exchange area A of the gas sidegAnd the ratio of the internal heat exchange area to the external heat exchange area to obtain the internal heat exchange area Ac；
According to the heat exchange coefficient h of the gas sidegGas side heat exchange area AgThe internal heat exchange area AcThe gas side limiting wall temperature and the average wall thickness obtain the cold gas side wall temperature Tw,c。
In exemplary embodiments of the present disclosure, the amount of cold air is estimated based on the estimated amount of cold air
Figure BDA0002571878730000032
And cooling design parameters to obtain the cold air side heat exchange coefficient h of the turbine bladecAnd cold air outlet temperature Tc,outThe method comprises the following steps:
simplifying a flow heat exchange model of the inner cavity of the turbine blade into a single-cavity inner and outer flow heat exchange model with a single inlet and a single outlet;
obtaining the axial length l of the single cavity of the single-cavity internal and external flow heat exchange model according to the inner cavity axial dimension coefficient and the inner cavity numberchannel；
According to the axial length lchannelObtaining the single-cavity hydraulic diameter D of the single-cavity internal and external flow heat exchange model according to the single-cavity width-height ratio of the single-cavity internal and external flow heat exchange modelh；
According to the hydraulic diameter DhAnd the estimated cold gas amount
Figure BDA0002571878730000049
Obtaining the Reynolds number Re of the single cavity of the single-cavity internal and external flow heat exchange modelc；
According to the heat exchange enhancement coefficient of the inner cavity and the Reynolds numberRecObtaining the heat exchange coefficient h of the cold gas sidec；
According to the cold air inlet temperature and the cold air side wall temperature Tw,cAnd the cold air side heat exchange coefficient hcObtaining the cold air outlet temperature Tc,out。
In an exemplary embodiment of the present disclosure, according to formula Dh＝4lchannel·(lchannel/AR)/(2lchannel+(lchannelAR)) calculating to obtain the hydraulic diameter DhWherein l ischannelFor axial length, AR is the single cavity aspect ratio.
In the exemplary embodiment of the present disclosure, according to the formula hc＝EF·0.023Rec 0.8Prc 0.4·λc/DhCalculating to obtain the heat exchange coefficient h of the cold air sidecWherein EF is the inner cavity heat exchange enhancement coefficient, RecIs Reynolds number, PrcIs the Plantaget number on the cold side, λcIs the heat conductivity of the cold air, DhIs the hydraulic diameter.
In an exemplary embodiment of the present disclosure, the method is based on a formula
Figure BDA0002571878730000041
Calculating to obtain the cold air outlet temperature Tc,outWherein, in the step (A),
Figure BDA0002571878730000042
hcis the cold air side heat transfer coefficient, AcThe heat exchange area is the area of the internal heat exchange,
Figure BDA0002571878730000043
to estimate the amount of cold gas, Tc,inIs the inlet temperature of the cold air, Cp,cThe constant pressure specific heat of cold air.
In an exemplary embodiment of the present disclosure, the method is based on a formula
Figure BDA0002571878730000044
Calculating to obtain the actual cold air quantity
Figure BDA0002571878730000045
Wherein, Wcη/((1- η)) is the equivalent cold, η is the average cooling effect of the turbine blade,
Figure BDA0002571878730000046
for the average cooling efficiency of the internal cavity of the turbine blade,
Figure BDA0002571878730000047
Tgis the average inlet temperature, T, of the gas sidew,gLimiting the wall temperature, T, for the gas sidec,inIs the inlet temperature of the cold air, Tc,outIs the cold air outlet temperature, Tw,cIs the cold gas side wall temperature.
In an exemplary embodiment of the present disclosure, the method is based on a formula
Figure BDA0002571878730000048
Calculating to obtain the estimated cold gas amount
Figure BDA0002571878730000051
The actual amount of cold air
Figure BDA0002571878730000052
According to the formula
Figure BDA0002571878730000053
Calculating to obtain the estimated cold gas amount
Figure BDA0002571878730000054
And the actual amount of cold air
Figure BDA0002571878730000055
Average value y of (a).
In an exemplary embodiment of the present disclosure, the analysis method further includes:
and changing the cooling design parameters to obtain a cold effect characteristic curve chart of the turbine blade.
In exemplary embodiments of the present disclosure, when the turbine blade gas side is designed with a thermal barrier coating, the combustion needs to be addressedGas side heat transfer coefficient hgMaking a correction according to the formula hg,TBC＝(λTBC·hg)/(λTBC+hg·TBC) Calculating to obtain equivalent gas side heat exchange coefficient hg,TBCWherein λ isTBCIs the thermal conductivity coefficient of the thermal barrier coating,TBCis the thickness of the thermal barrier coating.
According to the turbine blade cold air volume and cold effect characteristic analysis method, the gas side inlet parameters, the one-dimensional flow channel parameters and the blade parameters of the turbine blades are introduced, the one-dimensional flow channel structure factors, namely the inner cavity factors of the turbine blades, are considered, the turbine blade cold air volume and cold effect characteristic analysis method is applicable to analysis of the turbine blade cold air volume and the cooling characteristic of different cooling structures, and the application range is wider. The method can be used for analyzing and researching the cooling capacity and the cooling characteristic of the blade by single factors or multiple factors aiming at the cooling design parameters, and the analysis method is more flexible and the analysis result is more comprehensive and accurate.
Drawings
The above and other features and advantages of the present disclosure will become more apparent by describing in detail exemplary embodiments thereof with reference to the attached drawings.
FIG. 1 illustrates a flow diagram of a turbine blade cold air volume and cold efficiency characteristic analysis method in an exemplary embodiment of the present disclosure;
FIG. 2 illustrates a schematic view of an exemplary single stage turbine aerodynamic one-dimensional flow path configuration in an exemplary embodiment of the present disclosure;
FIG. 3 illustrates a schematic view of a one-dimensional internal cooling structure of a guide vane within a one-dimensional aerodynamic flow channel in an exemplary embodiment of the present disclosure;
FIG. 4 is a schematic diagram of a multi-cavity single-pass flow heat exchange model with a simplified one-dimensional internal cooling structure according to an exemplary embodiment of the disclosure;
FIG. 5 is a schematic diagram illustrating a single-inlet single-outlet single-cavity internal-external flow heat exchange model with a simplified one-dimensional internal cooling structure according to an exemplary embodiment of the disclosure;
fig. 6 shows a graph of cold efficiency characteristics in an exemplary embodiment of the present disclosure.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided to give a thorough understanding of embodiments of the disclosure.
The same reference numerals denote the same or similar structures in the drawings, and thus detailed descriptions thereof will be omitted.
The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided to give a thorough understanding of embodiments of the disclosure. One skilled in the relevant art will recognize, however, that the embodiments of the disclosure can be practiced without one or more of the specific details, or with other methods, components, materials, and so forth. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring the primary technical ideas of the disclosure.
The terms "a," "an," "the," and the like are used to denote the presence of one or more elements/components/parts; the terms "comprising" and "having" are intended to be inclusive and mean that there may be additional elements/components/etc. other than the listed elements/components/etc.
In the related art, in the one-dimensional design stage of the turbine blade, the cold air quantity evaluation method mainly adopts a similar blade equivalent cold air quantity comparison method. The equivalent cold air quantity analogy method mainly has the following defects: 1) the application range is narrow, the turbine blade cooling device is only suitable for the conditions that the power of an engine is equivalent and the temperature level difference before a turbine is not large, and the cooling requirements of the inner cavity of the turbine blade adopt the same structural form; 2) the cold air quantity and the cold effect value of a single design point can be evaluated, and the blade cold effect characteristic in a certain cold air/gas flow ratio range cannot be obtained; 3) the estimation precision has larger error when the aspect ratio of the blade is changed greatly, and the influence of the bending and twisting factors of the blade on the cold air quantity and the cold effect cannot be considered by the class comparison method.
As shown in fig. 1, the present disclosure provides a method for analyzing the amount and characteristics of cold air in a turbine blade, comprising the following steps:
s100, acquiring gas side inlet parameters, one-dimensional flow channel parameters, blade parameters and gas side heat exchange coefficients h of the turbine bladesg；
Step S200, determining cooling design parameters of the turbine blade;
step S300, starting iteration step, determining estimated cold air quantity
Figure BDA0002571878730000071
Step S400, according to the gas side inlet parameters, the one-dimensional flow channel parameters, the blade parameters and the gas side heat exchange coefficient hgCooling design parameters and estimated cooling capacity
Figure BDA0002571878730000072
Obtaining the actual amount of cold air
Figure BDA0002571878730000073
Step S500, obtaining the estimated cooling air quantity
Figure BDA0002571878730000074
And the actual amount of cold air
Figure BDA0002571878730000075
And the estimated amount of cold gas
Figure BDA0002571878730000076
And actual amount of cold air
Figure BDA0002571878730000077
Average value y of
Figure BDA0002571878730000078
Step S600, comparing the size of lambda with 1%;
step S700, if lambda is less than or equal to 1%, outputting the actual amount of cold air
Figure BDA0002571878730000079
Cooling design parameters are calculated, and the analysis results of the turbine blade cold air quantity and the cold effect characteristic are obtained; if lambda is more than 1%, the iteration step is started, and the actual cold air quantity is used
Figure BDA00025718787300000710
Updating the estimated cold gas volume
Figure BDA00025718787300000711
Until lambda is less than or equal to 1 percent.
According to the turbine blade cold air volume and cold effect characteristic analysis method, the gas side inlet parameters, the one-dimensional flow channel parameters and the blade parameters of the turbine blades are introduced, the one-dimensional flow channel structure factors, namely the inner cavity factors of the turbine blades, are considered, the turbine blade cold air volume and cold effect characteristic analysis method is applicable to analysis of the turbine blade cold air volume and the cooling characteristic of different cooling structures, and the application range is wider. The method can be used for analyzing and researching the cooling capacity and the cooling characteristic of the blade by single factors or multiple factors aiming at the cooling design parameters, and the analysis method is more flexible and the analysis result is more comprehensive.
The detailed process of each step in fig. 1 will be explained below with reference to the accompanying drawings.
As shown in fig. 2 and 3, the turbine blade according to the exemplary embodiment of the present disclosure is mainly an internal enhanced convection cooling blade without blade airfoil film outflow. In the exemplary embodiment of the present disclosure, the turbine aerodynamic one-dimensional flow passage and the guide vane shown in fig. 2 and 3 are mainly taken as an example for detailed description.
At present, a typical turbine aerodynamic one-dimensional flow path is schematically shown in fig. 2. The one-dimensional flow channel mainly comprises an upper flow channel 1, a lower flow channel 2, a guide vane 3, a working vane 4 and a rotating shaft 5. In FIG. 2, the difference between the average radial height of the upper flow passage 1 and the average radial height of the lower flow passage 2 is the average blade height H of the bladebladeThe length of the guide vane at the axial position is the axial chord length l of the vaneblade。
The schematic view of the one-dimensional internal cooling structure of the guide blade in the one-dimensional pneumatic flow passage is shown in fig. 3, and the cold air flow path 6 is a blade internal cooling flow form of a single-inlet three-cavity serpentine channel.
In step S100, gas side inlet parameters, one-dimensional flow channel parameters, blade parameters, and gas side heat transfer coefficients h of the turbine blades are obtainedg。
In exemplary embodiments of the present disclosure, the gas side inlet parameter includes a gas side equivalent inlet average temperature TgThe one-dimensional flow channel parameter comprises the average blade height H of the bladebladeAnd axial chord length l of bladeblade(ii) a The blade parameters comprise the number NUM of blades and the bending coefficient f of the bladestwist. Wherein the average blade height H of the bladesbladeAnd axial chord length l of bladebladeSee fig. 2. Blade bending coefficient ftwistRepresenting actual arc length and axial chord length l of bent and twisted bladebladeThe ratio of.
It should be noted that when the gas side of the turbine blade is designed with a thermal barrier coating, the heat exchange coefficient h of the gas side is requiredgCorrecting, considering the influence of the coating on external heat exchange, adopting a one-dimensional thermal resistance correction mode to calculate the equivalent heat exchange coefficient of the gas side,
hg,TBC＝(λTBC·hg)/(λTBC+hg·TBC)
in the formula, hg,TBCFor modified gas side heat transfer coefficient after thermal barrier coating, lambdaTBCIs the thermal conductivity coefficient of the thermal barrier coating,TBCis the thickness of the thermal barrier coating.
In step S200, cooling design parameters for the turbine blade are determined.
In exemplary embodiments of the present disclosure, the cooling design parameter includes a gas side limiting wall temperature Tw,gThe temperature T of the cold air inletc,inTemperature reserve value, number of lumens NchannelAxial size coefficient f of inner cavityaxialInner cavity heat exchange enhancement coefficient EF and average wall thicknesswArea ratio of internal and external heat exchange Areafactor. Axial size coefficient f of inner cavityaxialIs a vortexThe inner cavity of the wheel blade occupies the axial chord length l of the blade in the axial directionbladeThe ratio (generally between 0.8 and 0.95) of the heat exchange coefficient of the inner cavity, and the heat exchange enhancement coefficient EF of the inner cavity refers to the ratio (generally between 1.0 and 5.0) of the actual heat exchange coefficient of the inner cavity to the heat exchange coefficient of the smooth circular tube under the same flow.
In step S300, an iteration step is started to determine an estimated amount of cold air
Figure BDA0002571878730000084
In exemplary embodiments of the present disclosure, the predicted cold gas ratio MR required for a given turbine blade cooling design is combined with the gas side inlet cross-sectional flow W2And the number NUM of the blades, and the estimated cold air quantity can be calculated
Figure BDA0002571878730000081
Figure BDA0002571878730000082
In step S400, according to the gas side inlet parameter, the one-dimensional flow channel parameter, the blade parameter and the gas side heat exchange coefficient hgCooling design parameters and estimated cooling capacity
Figure BDA0002571878730000085
Obtaining the actual amount of cold air
Figure BDA0002571878730000083
The method comprises the following steps:
step S410, obtaining the gas side heat exchange area A of the turbine blade according to the one-dimensional flow channel parameters and the blade parametersgAnd according to the gas side inlet parameter and the gas side heat exchange coefficient hgAnd cooling design parameters to obtain the gas side heat exchange quantity Q of the turbine blade1；
In the exemplary embodiment of the disclosure, the gas side heat exchange area A is obtained according to the average blade height of the blades, the axial chord length of the blades and the bending coefficient of the bladesg(ii) a According to the heat exchange coefficient h of the gas sidegGas side heat exchange area, gas side equivalent inletObtaining the heat exchange quantity Q of the gas side by the average temperature, the temperature reserve value and the limited wall temperature of the gas side1。
Specifically, in exemplary embodiments of the present disclosure, the gas side heat exchange area AgIs calculated by the following formula to obtain,
Ag＝2Hblade·lblade·ftwist
wherein HbladeMean leaf height of the leaf, /)bladeIs the axial chord length of the blade, ftwistIs the blade bending coefficient.
Gas side heat exchange quantity Q1Is calculated by the following formula to obtain,
Q1＝hgAg(Tg-Tw,g)
wherein h isgIs the gas side heat transfer coefficient, TgIs the equivalent average inlet temperature (i.e. the sum of the actual turbine blade inlet average temperature and the temperature reserve value of the cooling design parameter) of the gas side, Tw,gThe gas side of which limits the wall temperature.
It should be noted here that the heat transfer coefficient h is given to the gas sidegWhen the turbine blade gas side is designed with a thermal barrier coating, the equivalent gas side heat exchange coefficient h is usedg,TBCSubstitute gas side heat transfer coefficient hg。
Step S420, according to the cooling design parameter and the gas side heat exchange area AgObtaining the internal heat exchange area A of the turbine bladecAnd according to the heat exchange coefficient h of the gas sidegGas side heat exchange area AgInner heat exchange area AcAnd obtaining the cooling gas sidewall temperature T of the turbine blade according to the cooling design parameterw,c。
In the exemplary embodiment of the present disclosure, the heat exchange area A is determined according to the gas sidegThe ratio of the internal heat exchange area to the external heat exchange area obtains the internal heat exchange area Ac(ii) a According to the heat exchange coefficient h of the gas sidegGas side heat exchange area AgInner heat exchange area AcGas side limiting wall temperature and average wall thickness to obtain cold gas side wall temperature Tw,c。
In particular, in exemplary embodiments of the present disclosure,internal heat exchange area AcIs calculated by the following formula to obtain,
Ac＝Ag·Areafactor
wherein A isgIs the gas side heat exchange Area, AreafactorThe ratio of the heat exchange area inside and outside the blade.
The cold air side wall temperature T is obtained according to the heat balance process that the heat conduction quantity of the turbine blade along the wall thickness is equal to the heat exchange quantity of the gas sidew,cIs obtained by the following formula calculation
Figure BDA0002571878730000101
Wherein A isgIs the gas side heat exchange area hgIs the heat transfer coefficient of the gas side, AcIs the internal heat exchange area, lambdawIs the thermal conductivity of the metal material of the blade,wis the average wall thickness.
Step S430, estimating the amount of cold air
Figure BDA0002571878730000102
Obtaining the cold air side heat exchange coefficient h of the turbine blade according to the cooling design parameterscAnd cold air outlet temperature Tc,out。
In an exemplary embodiment of the present disclosure, step S430 includes:
step S431, simplifying a flow heat exchange model of the inner cavity of the turbine blade into a single-cavity internal and external flow heat exchange model with a single inlet and a single outlet;
in the exemplary embodiment of the present disclosure, as shown in fig. 4 and 5, the one-dimensional internal cooling structure of the guide vane in fig. 3 is simplified and initially simplified into a multi-cavity single-flow heat exchange model as shown in fig. 4, and cold air flows in from a cold air inlet 7, passes through a three-cavity serpentine channel, and then flows out from a plurality of outflow holes 8 at the trailing edge. Then, the model is further simplified into a single-cavity internal and external flowing heat exchange model with a single inlet and a single outlet, specifically, as shown in fig. 5, cold air flows in from a single-inlet cold air inlet 9 and flows out from a single-outlet cold air outlet 10, the outer wall of the channel is a gas side heat exchange boundary 11, the temperature of the outer wall 13 of the channel is a cooling design limiting wall temperature value, and the inner wall 12 of the channel is in contact with the cold air and performs convection heat exchange with the cold air.
Step S432, obtaining the axial length l of the single cavity of the single-cavity internal and external flow heat exchange model according to the axial size coefficient and the number of the inner cavitieschannel。
In the exemplary embodiment of the present disclosure, according to formula lchannel＝(lblade/Nchannel)·faxialCalculating to obtain the axial length l of the single cavitychannelWherein N ischannelIs the number of lumens, faxialIs the axial size coefficient of the inner cavity.
Step S433, according to the axial length lchannelObtaining the single-cavity hydraulic diameter D of the single-cavity internal and external flowing heat exchange model according to the single-cavity width-height ratio of the single-cavity internal and external flowing heat exchange modelh；。
In an exemplary embodiment of the present disclosure, according to formula Dh＝4lchannel·(lchannel/AR)/(2lchannel+(lchannelAR)) calculating to obtain the hydraulic diameter DhWherein l ischannelFor axial length, AR is the single cavity aspect ratio.
Step S434, according to the hydraulic diameter DhAnd estimate the amount of cold
Figure BDA00025718787300001110
Obtaining Reynolds number Re of single cavity of single-cavity internal and external flow heat exchange modelc；。
In an exemplary embodiment of the present disclosure, the method is based on a formula
Figure BDA0002571878730000119
Calculating to obtain Reynolds number RecWherein A isflowIs the flow area of a single cavity and can pass through the hydraulic diameter D of the single cavityhObtained by calculation,. mu.cIs the viscosity coefficient of the cold air.
Step S435, heat exchange enhancement coefficient according to inner cavity and Reynolds number RecObtaining the heat exchange coefficient h of the cold air sidec。
In the exemplary embodiment of the present disclosure, according to the formula hc＝EF·0.023Rec 0.8Prc 0.4·λc/DhCalculating to obtain the heat exchange coefficient h of the cold air sidecWherein EF is the inner cavity heat exchange enhancement coefficient, RecIs Reynolds number, PrcIs the Plantaget number on the cold side, λcIs the heat conductivity of the cold air, DhIs the hydraulic diameter.
Step S436, according to the cool air inlet temperature and the cool air side wall temperature Tw,cHeat transfer coefficient h with cold air sidecObtaining the temperature T of the cold air outletc,out。
In the exemplary embodiment of the disclosure, the inner cavity of the turbine blade selects a heat balance route of inner side convection heat transfer and cold air heat storage, and simultaneously adopts an average reference temperature of inlet and outlet cold air based on arithmetic average to obtain a cold air outlet temperature Tc,out. According to the formula
Figure BDA0002571878730000111
Calculating to obtain the cold air outlet temperature Tc,outWherein, in the step (A),
Figure BDA0002571878730000112
hcis the cold air side heat transfer coefficient, AcThe heat exchange area is the area of the internal heat exchange,
Figure BDA0002571878730000113
to estimate the amount of cold gas, Tc,inIs the inlet temperature of the cold air, Cp,cThe constant pressure specific heat of cold air.
Step S440, according to the gas side inlet parameter, the cooling design parameter and the cold air side wall temperature Tw,cAnd cooling outlet temperature Tc,outObtaining the actual amount of cold air
Figure BDA0002571878730000114
In an exemplary embodiment of the present disclosure, the method is based on a formula
Figure BDA0002571878730000115
Calculating to obtain the actual cold air quantity
Figure BDA0002571878730000116
Wherein, Wcη/((1- η)) is the equivalent cold, η is the average cooling effect of the turbine blade,
Figure BDA0002571878730000117
for the average cooling efficiency of the internal cavity of the turbine blade,
Figure BDA0002571878730000118
Tgis the average inlet temperature, T, of the gas sidew,gLimiting the wall temperature, T, for the gas sidec,inIs the inlet temperature of the cold air, Tc,outIs the cold air outlet temperature, Tw,cIs the cold gas side wall temperature.
In step S500, an estimated amount of cold air is obtained
Figure BDA0002571878730000121
And the actual amount of cold air
Figure BDA0002571878730000122
And the estimated amount of cold gas
Figure BDA0002571878730000123
And actual amount of cold air
Figure BDA0002571878730000124
Average value y of
Figure BDA0002571878730000125
In particular according to the formula
Figure BDA0002571878730000126
Calculating to obtain estimated cold gas quantity
Figure BDA0002571878730000127
And the actual amount of cold air
Figure BDA0002571878730000128
According to the formula
Figure BDA0002571878730000129
Calculating to obtain estimated cold gas quantity
Figure BDA00025718787300001210
And actual amount of cold air
Figure BDA00025718787300001211
Average value y of (a).
Step S600, comparing the size of lambda with 1%;
step S700, if lambda is less than or equal to 1%, outputting the actual amount of cold air
Figure BDA00025718787300001212
Cooling design parameters are calculated, and the analysis results of the turbine blade cold air quantity and the cold effect characteristic are obtained; if lambda is more than 1%, the iteration step is started, and the actual cold air quantity is used
Figure BDA00025718787300001213
Updating the estimated cold gas volume
Figure BDA00025718787300001214
Until lambda is less than or equal to 1 percent.
In an exemplary embodiment of the present disclosure, step S700 is followed by:
and step S800, changing cooling design parameters to obtain a cold effect characteristic curve chart of the turbine blade.
Specifically, by changing the cooling design parameters, the wall temperature of the gas side in the cooling design parameters can be limited, so that the amount of cold air required by the blade can be calculated under different cooling design requirements, and the cold effect characteristic of the blade can be obtained. Meanwhile, after the iterative cycle calculation is completed, design parameters such as the number of inner cavities, the gas side limiting wall temperature, the axial size of the inner cavities, the enhanced heat exchange coefficient of the inner cavities and the like can be formed.
In one embodiment of the present disclosure, the gas side inlet parameters, one-dimensional flow channel parameters, vane parameters, gas side heat transfer coefficients, and cooling design parameters are shown in table 1.
TABLE 1
Figure BDA00025718787300001215
Figure BDA0002571878730000131
Wherein, the single cavity aspect ratio is the aspect ratio when the cross sections of the inner cavities are all simplified into rectangles.
The heat exchange area A on the gas side is obtained by the calculation of the stepsg＝4800mm2Heat exchange quantity Q of gas side14200W, cold air side wall temperature Tw,c1157K. Given that the ratio of the initial estimated cold air amount is MR 5.0%, the convergent actual cold air ratio 6.60% can be obtained through four iterative calculations, see table 2.
TABLE 2
Step1 Step2 Step3 Step4
Estimation of cold air ratio 5.0％ 6.28％ 6.54％ 6.59％
Reynolds number 11.3×104 14.2×104 14.8×104 14.9×104
Cold air outlet temperature (K) 96 92 91 91
Equivalent cold air 4.71 4.91 4.94 4.95
Actual cold air ratio 6.28％ 6.54％ 6.59％ 6.60％
The gas side limiting wall temperature is changed from 1140K to 1280K, the turbine blade cold air quantity under different cooling design input can be obtained, further, the blade global cooling effect value can be obtained, and the cold effect characteristic curve is shown in figure 6.
According to the turbine blade cold air volume and cold effect characteristic analysis method, the gas side inlet parameters, the one-dimensional flow channel parameters and the blade parameters of the turbine blades are introduced, the one-dimensional flow channel structure factors, namely the inner cavity factors of the turbine blades, are considered, the turbine blade cold air volume and cold effect characteristic analysis method is applicable to analysis of the turbine blade cold air volume and the cooling characteristic of different cooling structures, and the application range is wider. The method can be used for carrying out analysis and research on the blade cold air quantity and the cooling characteristic by single factors or multiple factors according to cooling design parameters such as the number of inner cavities, the heat exchange enhancement coefficient of the inner cavities, the aspect ratio and the like, and the analysis method is more flexible and has more comprehensive analysis results. In addition, the method overcomes the characteristic that the heat exchange coefficient of the inner cavity needs to be determined in the equivalent cold air quantity comparison method in the related technology, introduces the heat exchange strengthening coefficient based on the axial size coefficient of the inner cavity and the inner cavity, obtains a calculation model of the heat exchange coefficient of the cold air side, and has the characteristics of high prediction precision, strong robustness, good convergence and the like. And the correction calculation of the thermal barrier coating outside the turbine blade can be realized according to the actual requirement. In addition, the method for analyzing the cold air quantity and the cold efficiency characteristics based on internal and external heat balance is established by simplifying the one-dimensional internal cooling structure form of the turbine blade, and the method is short in iterative calculation period, high in estimation precision and good in convergence. The method for analyzing the cold air quantity and the cold effect characteristics of the turbine blade provided by the embodiment of the disclosure is verified by comparison of cold effect tests of various cooling blades, and the estimation precision of the overall cold effect characteristics is within +/-15%.
It should be noted that although the various steps of the methods of the present disclosure are depicted in the drawings in a particular order, this does not require or imply that these steps must be performed in this particular order, or that all of the depicted steps must be performed, to achieve desirable results. Additionally or alternatively, certain steps may be omitted, multiple steps combined into one step execution, and/or one step broken down into multiple step executions, etc., are all considered part of this disclosure.
It is to be understood that the disclosure is not limited in its application to the details of construction and the arrangements of the components set forth in the specification. The present disclosure is capable of other embodiments and of being practiced and carried out in various ways. The foregoing variations and modifications are within the scope of the present disclosure. It should be understood that the disclosure disclosed and defined in this specification extends to all alternative combinations of two or more of the individual features mentioned or evident from the text and/or drawings. All of these different combinations constitute various alternative aspects of the present disclosure. The embodiments of this specification illustrate the best mode known for carrying out the disclosure and will enable those skilled in the art to utilize the disclosure.

Claims (10)

1. A turbine blade cold air volume and cold effect characteristic analysis method is characterized by comprising the following steps:
obtaining the gas side inlet parameters, one-dimensional flow channel parameters, blade parameters and gas side heat exchange coefficients h of the turbine bladesg；
Determining cooling design parameters for the turbine blade;
starting iteration step to determine estimated cold air quantity
Figure FDA0002571878720000011
According to the gas side inlet parameter, the one-dimensional runner parameter, the blade parameter and the gas side heat exchange coefficient hgThe cooling design parameter and the estimated cooling air quantity
Figure FDA0002571878720000012
Obtaining the actual amount of cold air
Figure FDA0002571878720000013
Obtaining the estimated cold gas amount
Figure FDA0002571878720000014
And the actual amount of cold air
Figure FDA0002571878720000015
And the estimated cold gas amount
Figure FDA0002571878720000016
And the actual amount of cold air
Figure FDA0002571878720000017
Average value y of
Figure FDA0002571878720000018
Comparing the size of λ to 1%;
if lambda is less than or equal to 1%, outputting the actual cold air quantity
Figure FDA0002571878720000019
Cooling design parameters are calculated, and the analysis results of the turbine blade cold air quantity and the cold effect characteristic are obtained; if lambda is more than 1%, the iteration step is started, and the actual cold air quantity is used
Figure FDA00025718787200000110
Updating the estimated cold gas amount
Figure FDA00025718787200000111
Until lambda is less than or equal to 1 percent.
2. The method for analyzing the cold air quantity and cold air efficiency characteristics of turbine blades according to claim 1, wherein the method is characterized in that the method comprises the steps of obtaining the gas side inlet parameter, the one-dimensional flow channel parameter, the blade parameter and the gas side heat exchange coefficient hgThe cooling design parameter and the estimated cooling air quantity
Figure FDA00025718787200000112
Obtaining the actual amount of cold air
Figure FDA00025718787200000113
The method comprises the following steps:
obtaining the gas side heat exchange area A of the turbine blade according to the one-dimensional flow channel parameters and the blade parametersgAnd according to the gas side inlet parameter and the gas side heat exchange coefficient hgAnd the cooling design parameter is used for obtaining the gas side heat exchange quantity Q of the turbine blade1；
According to the cooling design parameter and the gas side heat exchange area AgObtaining the internal heat exchange area A of the turbine bladecAnd according to the heat exchange coefficient h of the gas sidegGas side heat exchange area AgThe internal heat exchange area AcAnd saidObtaining the cool air sidewall temperature T of the turbine blade according to the cooling design parametersw,c；
According to the estimated cold gas quantity
Figure FDA00025718787200000114
And cooling design parameters to obtain the cold air side heat exchange coefficient h of the turbine bladecAnd cold air outlet temperature Tc,out；
According to the gas side inlet parameters, the cooling design parameters and the cold gas side wall temperature Tw,cAnd the cooling outlet temperature Tc,outObtaining the actual amount of cold air
Figure FDA0002571878720000021
3. The turbine blade cold gas volume and cold gas efficiency characteristic analysis method of claim 2, wherein the gas side inlet parameters comprise a gas side equivalent inlet average temperature; the one-dimensional flow channel parameters comprise the average blade height of the blades and the axial chord length of the blades; the blade parameters comprise the number of blades and the bending and twisting coefficients of the blades; the cooling design parameters comprise the gas side limiting wall temperature, the cold air inlet temperature, the temperature reserve value, the number of inner cavities, the axial size coefficient of the inner cavities, the heat exchange strengthening coefficient of the inner cavities, the average wall thickness and the ratio of the inner heat exchange area to the outer heat exchange area.
4. The method for analyzing the cold air quantity and cold air efficiency characteristics of the turbine blade as claimed in claim 3, wherein the gas side heat exchange area A of the turbine blade is obtained according to the one-dimensional flow channel parameter and the blade parametergAnd according to the gas side inlet parameter and the gas side heat exchange coefficient hgAnd the cooling design parameter is used for obtaining the gas side heat exchange quantity Q of the turbine blade1The method comprises the following steps:
obtaining the gas side heat exchange area A according to the average blade height of the blades, the axial chord length of the blades and the bending and twisting coefficient of the bladesg；
According to the heat exchange coefficient h of the gas sidegGas side heat exchange area AgObtaining the gas side heat exchange quantity Q through the equivalent inlet average temperature of the gas side, the temperature reserve value and the gas side limiting wall temperature1。
5. The method for analyzing the amount and characteristics of the cooling air for the turbine blades as claimed in claim 3, wherein the design parameters of the cooling air and the heat exchange area A on the gas side are determined according to the design parameters of the cooling air and the heat exchange area A on the gas sidegObtaining the internal heat exchange area A of the turbine bladecAnd according to the heat exchange coefficient h of the gas sidegGas side heat exchange area AgThe internal heat exchange area AcAnd the cooling design parameter obtains the cool air side wall temperature T of the turbine bladew,cThe method comprises the following steps:
according to the heat exchange area A of the gas sidegAnd the ratio of the internal heat exchange area to the external heat exchange area to obtain the internal heat exchange area Ac；
According to the heat exchange coefficient h of the gas sidegGas side heat exchange area AgThe internal heat exchange area AcThe gas side limiting wall temperature and the average wall thickness obtain the cold gas side wall temperature Tw,c。
6. The method for analyzing the amount and characteristics of cooling air for turbine blades as claimed in claim 5, wherein the estimated amount of cooling air is used as a basis
Figure FDA0002571878720000031
And cooling design parameters to obtain the cold air side heat exchange coefficient h of the turbine bladecAnd cold air outlet temperature Tc,outThe method comprises the following steps:
simplifying a flow heat exchange model of the inner cavity of the turbine blade into a single-cavity inner and outer flow heat exchange model with a single inlet and a single outlet;
obtaining the axial length l of the single cavity of the single-cavity internal and external flow heat exchange model according to the inner cavity axial dimension coefficient and the inner cavity numberchannel；
According to the axial length lchannelThe single chamber flows inside and outsideObtaining the single-cavity hydraulic diameter D of the single-cavity internal and external flowing heat exchange model according to the single-cavity width-to-height ratio of the heat exchange modelh；
According to the hydraulic diameter DhAnd the estimated cold gas amount
Figure FDA0002571878720000032
Obtaining the Reynolds number Re of the single cavity of the single-cavity internal and external flow heat exchange modelc；
According to the heat exchange enhancement coefficient of the inner cavity and the Reynolds number RecObtaining the heat exchange coefficient h of the cold gas sidec；
According to the cold air inlet temperature and the cold air side wall temperature Tw,cAnd the cold air side heat exchange coefficient hcObtaining the cold air outlet temperature Tc,out。
7. The method for analyzing the amount and characteristics of the cooling air for the turbine blades as claimed in claim 6, wherein the method is based on formula Dh＝4lchannel·(lchannel/AR)/(2lchannel+(lchannelAR)) calculating to obtain the hydraulic diameter DhWherein l ischannelFor axial length, AR is the single cavity aspect ratio.
8. The method for analyzing the amount and characteristics of the cooling air for the turbine blades as claimed in claim 6, wherein the method is based on the formula hc＝EF·0.023Rec 0.8Prc 0.4·λc/DhCalculating to obtain the heat exchange coefficient h of the cold air sidecWherein EF is the inner cavity heat exchange enhancement coefficient, RecIs Reynolds number, PrcIs the Plantaget number on the cold side, λcIs the heat conductivity of the cold air, DhIs the hydraulic diameter.
9. The method for analyzing the amount and characteristics of cold gas in turbine blades according to claim 1, further comprising:
and changing the cooling design parameters to obtain a cold effect characteristic curve chart of the turbine blade.
10. The method for analyzing the cold air quantity and cold air efficiency characteristics of the turbine blade as claimed in claim 1, wherein when a thermal barrier coating is designed on the gas side of the turbine blade, the heat exchange coefficient h of the gas side is requiredgMaking a correction according to the formula hg,TBC＝(λTBC·hg)/(λTBC+hg·TBC) Calculating to obtain equivalent gas side heat exchange coefficient hg,TBCWherein λ isTBCIs the thermal conductivity coefficient of the thermal barrier coating,TBCis the thickness of the thermal barrier coating.
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