CN106840685B - A kind of gas turbine dynamic operation condition database sample point choosing method - Google Patents
A kind of gas turbine dynamic operation condition database sample point choosing method Download PDFInfo
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- CN106840685B CN106840685B CN201710048012.5A CN201710048012A CN106840685B CN 106840685 B CN106840685 B CN 106840685B CN 201710048012 A CN201710048012 A CN 201710048012A CN 106840685 B CN106840685 B CN 106840685B
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Abstract
The present invention relates to a kind of gas turbine dynamic operation condition database sample point choosing methods, the gas turbine is the adjustable three shaft gas turbine of power turbine guide vane, the combustion engine design feature that this method is directed to is that power turbine entry guide vane is adjustable and be the three-axis structure with height last item and power turbine shaft, this method includes the influence for calculating analysis power turbine revolving speed to gas turbine, it calculates under analysis steady state condition, the corresponding height last item revolving speed corresponding relationship of different guide vane angles, during calculating acceleration and deceleration, the variation range of low-pressure shaft revolving speed, according to above-mentioned calculated result, choose sample point, each sample point is obtained using Gas Turbine Simulation model, formation gas turbine dynamic operation condition database and etc..Gas turbine dynamic operation condition database sample point choosing method of the invention considers the case where power turbine guide vane angle changes using the working characteristics of gas turbine, reasonably reduces sample point value range, be substantially reduced sample size, reduce workload.
Description
Technical field
The present invention relates to Gas Turbine calculating fields, adjustable more particularly, to a kind of power turbine guide vane
Three shaft gas turbine dynamic operation condition database sample point choosing method.
Background technique
Durings carrying out gas turbine semi-physical simulation experiment and gas turbine control law research etc., need to calculate
Each unstable state working condition of gas turbine out.It is calculated by model or gas turbine dynamic operation condition database is established in bench test,
Gas turbine operating condition can be calculated in real time using System Discrimination.However, triple axle combustion gas wheel adjustable for power turbine guide vane
Machine, since structure is complicated, variable is more, directly establishes dynamic operation condition database and is faced with that sample point is excessive, and database is huge, work
Measure larger problem.
Summary of the invention
The present invention is to solve the defect of the above prior art, is mentioned for the adjustable three shaft gas turbine of power turbine guide vane
A kind of dynamic operation condition database sample point choosing method is supplied, this method passes through the adjustable triple axle combustion of analysis power turbine guide vane
The working characteristics of gas-turbine determines that gas turbine works normally lower locating working range, to reasonably choose gas turbine
Dynamic operation condition sample point, reduces sample size and workload.
To realize the above goal of the invention, the technical solution adopted by the present invention is that:
A kind of gas turbine dynamic operation condition database sample point choosing method, the gas turbine are that power turbine guide vane can
The three shaft gas turbine of tune, the gas turbine include that the gas generator with high and low pressure rotor and entry guide vane are adjustable
Power turbine, it is characterised in that: power turbine entry guide vane is adjustable and is the three axis knots with high and low last item and power turbine shaft
Structure, the database sample point choosing method the following steps are included:
SS1. influence of the analysis power turbine revolving speed to gas turbine is calculated.Component characteristic is that a kind of common gas turbine is built
Mould method, this method are based on each characteristics of components, according to flow equilibrium and rotor dynamics equation, by solving nonlinear equation
Group completes simulation modeling.External environment and high-pressure shaft revolving speed are calculated not using existing component characteristic Gas Turbine Simulation model
Each running parameter of engine assesses power turbine revolving speed pair to analyze with the variation tendency of power secondary speed in the case where change
The influence size of the adjustable three shaft gas turbine operating condition of power turbine guide vane.
SS2. it calculates under analysis steady state condition, the corresponding high and low last item revolving speed corresponding relationship of different guide vane angles.In combustion gas
Several guide vane angles are uniformly chosen in the variation range of guide vane angle when turbine works normally, utilize existing component characteristic combustion gas wheel
Machine simulation model, when calculating separately out gas turbine steady operation under these guide vane angles, different high-pressure shaft relative rotation speed NH
Corresponding low-pressure shaft relative rotation speed NL, is fitted data point using cubic polynomial, to obtain opposite turn of low-pressure shaft
The steady state relation formula of fast NL and high-pressure shaft relative rotation speed NH and power turbine guide vane angle VGV: NL=f (NH, VGV).
SS3. during calculating acceleration and deceleration, the variation range of low-pressure shaft revolving speed.To existing component characteristic Gas Turbine Simulation
Fuel supply rate curve when the mode input gas turbine limit acceleration and deceleration, the simulation combustion respectively in the case where power turbine guide vane is constant
Gas-turbine limit acceleration and deceleration obtain under limit acceleration and deceleration situation, and low-pressure shaft corresponding to different high-pressure shaft relative rotation speed NH is opposite
Revolving speed NL.Known gas turbine accelerates faster, and the corresponding NL of identical NH is lower relative to steady state relation, it is assumed that identical NH is corresponding
NL is relative to the at most low a value of steady state relation；Gas turbine slows down faster, and the corresponding NL of identical NH is got over relative to steady state relation
It is high, it is assumed that identical NH corresponding NL is relative to the at most high b value of steady state relation.It, can be in conjunction with the steady state relation of NH, NL in SS2
Obtain the variation range of low-pressure shaft revolving speed: f (NH, VGV)-a < NL < f (NH, VGV)+b.
SS4. according to above-mentioned calculated result, sample point is chosen.Fuel flow Wf, high-pressure shaft relative rotation speed NH, guide vane angle
Tri- parameters of VGV can uniformly choose c, d, e values in its normal range of operation respectively.Know that combustion gas occurs for NPT by analysis
Device influences very little, therefore NPT only selects two different values.NL can be in the section [f (NH, VGV)-a, f (NH, VGV)+b] equably
Choose f value.To sum up, sample point c × d × e × 2 × f group is chosen altogether.
SS5. Gas Turbine Simulation model is utilized, gas turbine dynamic operation condition database is completed.Each group of gas turbine is dynamic
State operating condition sample point consists of two parts, and a part is by fuel flow Wf, guide vane angle VGV, high-pressure shaft relative rotation speed NH, low
Input parameter composed by last item relative rotation speed NL and power turbine relative rotation speed NPT, another part be by gas turbine its
Remaining running parameter (such as: high-low pressure shaft angle acceleration, the inlet and outlet pressure and temperature etc. of high-low pressure compressor and turbine) is formed
Output parameter.C × the d chosen × e × 2 × f group sample point input parameter is sequentially inputted in Gas Turbine Simulation model,
The output parameter of every group of sample point can be calculated.It is a certain dynamic that 5 input parameters of every group of sample point have uniquely determined gas turbine
State operating condition, that is to say, that input parameter and output parameter correspond, and c × d × e × 2 × f group sample point constitutes gas turbine
Dynamic operation condition database.
The present invention is directed the adjustable three shaft gas turbine of power turbine guide vane, such combustion engine is by two part groups
At: the adjustable power turbine of gas generator and entry guide vane with high and low pressure rotor.Such gas turbine has more than variable
Feature needs revolving speed and the fuel flow and power turbine guide vane angle 5 of three axis of high and low last item and power turbine shaft
Amount can just uniquely determine the dynamic operation condition of gas turbine.The present invention analyze power turbine revolving speed on gas generator influence compared with
It is small, therefore have chosen seldom NPT value.It is calculated by model, specifies that NL can only fall in [f (NH, VGV)-a, f (NH, VGV)+b]
Interval range in, avoid and choose useless NL value, substantially reduce sample size.
Compared with prior art, the beneficial effects of the present invention are:
The present invention provides the adjustable three shaft gas turbine dynamic operation condition database sample points of power turbine guide vane to choose
Method, this method consider the case where power turbine guide vane angle changes using the working characteristics of gas turbine, reasonably reduce
Sample point value range, is substantially reduced sample size, reduces workload.
Detailed description of the invention
Fig. 1 is the structure diagram of the adjustable three shaft gas turbine of power turbine guide vane；
Fig. 2 is the implementation flow chart of gas turbine dynamic operation condition database sample point choosing method of the present invention.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention more comprehensible, below in conjunction with drawings and examples to this
Invention is further elaborated, and so that the advantages and features of the present invention can be more easily understood by those skilled in the art.It needs
Bright, as described below is only presently preferred embodiments of the present invention, is not intended to limit the scope of the present invention.In fact,
Without departing from the scope or spirit of the invention, it can carry out various modifications and change in the present invention, this is to ability
It will be apparent for field technique personnel.For example, the feature that shows or describe of a part as one embodiment can be with
It is used together with another embodiment to generate another embodiment.Therefore, it is intended that the present invention is by such modifications and variations
Including in the range of equivalent of the appended claims with them.
As shown in Figure 1, the adjustable three shaft gas turbine of power turbine guide vane is by the gas generator with HP&LP Rotor
With the adjustable power turbine two parts composition of entry guide vane, there is more variable and excellent acceleration and deceleration characteristic.The present invention
The adjustable three shaft gas turbine dynamic operation condition database sample point choosing method of power turbine guide vane the following steps are included:
SS1. influence of the analysis power turbine revolving speed to gas turbine is calculated.Utilize existing component characteristic Gas Turbine Simulation
In the case that model calculating external environment and high-pressure shaft revolving speed are constant, power turbine relative rotation speed NPT is respectively 0.5,0.6,
When 0.7,0.8,0.9,1.0,1.1, low-pressure compressor, high-pressure compressor, high-pressure turbine, low-pressure turbine, power turbine it is common
Active line analyzes influence of the NPT to each component equilibrium running line.As a result, it has been found that NPT is to low-pressure compressor, high-pressure compressor, height
It presses the influence of turbine and low-pressure turbine working condition minimum, can ignore, only have certain influence to power generating turbine efficiency.
SS2. it calculates under analysis steady state condition, the corresponding height last item revolving speed corresponding relationship of different guide vane angles.VGV takes
20 °, 25 °, 30 °, 40 °, 50 ° of five values, NH take 0.7,0.75,0.8,0.85,0.9,0.95,1.0,1.05 8 value, pass through
Gas Turbine Simulation model calculates the corresponding NL value of above-mentioned difference VGV, NH under steady state condition, using multinomial for different guide vanes
Height last item revolving speed corresponding relationship is fitted under angle, obtains following relational expression: NL=fVGV=20 °(NH), NL=fVGV=25 °
(NH), NL=fVGV=30 °(NH), NL=fVGV=35 °(NH), NL=fVGV=40 °(NH), NL=fVGV=45 °(NH), NL=fVGV=50 °
(NH).Using linear interpolation, the steady state relation formula of NL Yu NH, VGV: NL=g (NH, VGV) can be obtained.
SS3. it calculates in dynamic process, the variation range of low-pressure shaft revolving speed.It calculates under gas turbine limit acceleration deceleration state,
The corresponding relationship of height last item revolving speed, and be fitted with multinomial, respectively obtain the high-low pressure rotation speed relation formula of acceleration and deceleration: NL
=fa(NH) and NL=fd(NH).It can be found that fd(NH) > fa(NH).When limit acceleration and deceleration, due to the effect of inertia of rotor,
It is farthest that the corresponding relationship of height last item revolving speed deviates steady state relation, therefore can determine therefrom that under dynamic operation condition, and low-pressure shaft revolving speed can
The variation range of energy.Low-pressure shaft revolving speed must fall in following section:
[g(NH,VGV)+1.2(fa(NH)-fVGV=30 °(NH)),g(NH,VGV)+1.2(fd(NH)-fVGV=30 °(NH))]
30 ° be power turbine design point guide vane angle, when using VGV being 30 °, low-pressure shaft pole under identical high-pressure shaft revolving speed
The size that limit acceleration and deceleration deviate steady state relation can determine low-pressure shaft revolving speed under dynamic operation condition multiplied by 1.2 safety coefficient
Value range.In this example, NL value range are as follows: (g (NH, VGV) -0.15)≤NL≤(g (NH, VGV)+0.08)
SS4. according to above-mentioned calculated result, sample point is chosen.Wf can be selected in maximum fuel range of flow by arithmetic progression
Take 8 values.VGV takes 20 °, 25 °, 30 °, 40 °, 50 ° of totally 5 values within the scope of 20 ° to 50 °.NH is in 0.70 to 1.05 revolving speed models
8 values are taken by arithmetic progression in enclosing.It is smaller to engine performance impacts due to analyzing power turbine revolving speed, therefore NPT only takes 1.1
It is worth with 0.5 two.NL takes 5 values by arithmetic progression between g (NH, VGV) -0.15 to g (NH, VGV)+0.08.To sum up, sample
Point scale is 8 × 5 × 8 × 2 × 5=3200 group point.
S5. each sample point is obtained using Gas Turbine Simulation model, forms gas turbine dynamic operation condition database.For combustion
Gas-turbine dynamic operation condition database, each group of data are made of input parameter and corresponding output parameter.Input parameter
Are as follows: Wf, NH, NL, NPT, VGV, output parameter are each running parameter of gas turbine and cross section parameter, comprising: low-pressure compressor effect
Rate, low-pressure compressor inlet flow rate, low-pressure compressor pressure ratio, high-pressure compressor efficiency, high-pressure compressor pressure ratio, high-pressure turbine effect
Rate, low-pressure turbine efficiency, low-pressure turbine expansion ratio, power generating turbine efficiency, power turbine expansion ratio, is moved high-pressure turbine expansion ratio
Power turbine output rate, low-pressure compressor outlet stagnation pressure, low-pressure compressor outlet total temperature, high-pressure compressor export total temperature, high pressure
Blower outlet stagnation pressure, combustor exit total temperature, high-pressure turbine outlet stagnation pressure, high-pressure turbine export total temperature, low-pressure turbine exit
Stagnation pressure, low-pressure turbine exit total temperature, power turbine exit stagnation pressure, power turbine exit total temperature amount to 23 parameters.Utilize tradition
Component characteristic, by solve Nonlinear System of Equations can establish gas turbine total simulation model.Step is gathered into 3200 groups chosen in 4
Input parameter is input in model, calculates corresponding output parameter, completes gas turbine dynamic operation condition database.
Obviously, examples detailed above of the invention be only to clearly illustrate example of the present invention, and not be to this
The restriction of the embodiment of invention.It for those of ordinary skill in the art, on the basis of the above description can be with
It makes other variations or changes in different ways.There is no necessity and possibility to exhaust all the enbodiments.It is all in this hair
Made any modifications, equivalent replacements, and improvements etc., should be included in the claims in the present invention within bright spirit and principle
Within protection scope.
Claims (3)
1. a kind of gas turbine dynamic operation condition database sample point choosing method, the gas turbine is that power turbine guide vane is adjustable
Three shaft gas turbine, the gas turbine includes that the gas generator with high and low pressure rotor and entry guide vane are adjustable dynamic
Power turbine, it is characterised in that: power turbine entry guide vane is adjustable and is the three axis knots with high and low last item and power turbine shaft
Structure, the database sample point choosing method the following steps are included:
SS1. it calculates influence of the analysis power turbine revolving speed to gas turbine: utilizing existing component characteristic Gas Turbine Simulation mould
Type, calculate external environment and high-pressure shaft revolving speed it is constant in the case where each running parameter of engine with power secondary speed change
Change trend, so that it is big to analyze influence of the assessment power turbine revolving speed to the adjustable three shaft gas turbine operating condition of power turbine guide vane
It is small；
SS2. it calculates under analysis steady state condition, the corresponding high and low last item relative rotation speed relationship of different guide vane angles: in gas turbine
Several guide vane angles are uniformly chosen when normal work in the variation range of guide vane angle, it is imitative using existing component characteristic gas turbine
True mode, when calculating separately out gas turbine steady operation under these guide vane angles, different high-pressure shaft relative rotation speed NH institutes are right
The low-pressure shaft relative rotation speed NL answered, is fitted data point using cubic polynomial, to obtain low-pressure shaft relative rotation speed NL
With the steady state relation formula NL=f (NH, VGV) of high-pressure shaft relative rotation speed NH and guide vane angle VGV；
SS3. it calculates under dynamic operation condition, the variation range of low-pressure shaft relative rotation speed: to existing component characteristic Gas Turbine Simulation mould
Type inputs the fuel supply rate curve when acceleration and deceleration of the gas turbine limit, simulates combustion gas wheel respectively in the case where power turbine guide vane is constant
Machine limit acceleration and deceleration obtain under limit acceleration and deceleration situation, low-pressure shaft relative rotation speed corresponding to different high-pressure shaft relative rotation speed NH
NL；Assuming that identical NH corresponding NL is relative to the at most low a value of steady state relation, the corresponding NL of identical NH relative to steady state relation most
More high b values；In conjunction with the steady state relation of NH, NL in SS2, it can be deduced that the variation range f (NH, VGV)-of low-pressure shaft relative rotation speed
a<NL<f(NH,VGV)+b；
SS4. according to above-mentioned calculated result, sample point: fuel flow Wf, high-pressure shaft relative rotation speed NH, guide vane angle VGV tri- is chosen
A parameter can uniformly choose c, d, e values in its normal range of operation respectively；Know that NPT influences gas generator by analysis
Very little, therefore NPT only selects two different values；NL can equably choose f in the section (f (NH, VGV)-a, f (NH, VGV)+b)
Value；To sum up, sample point c × d × e × 2 × f group is chosen altogether；
SS5. each sample point is obtained using Gas Turbine Simulation model, forms gas turbine dynamic operation condition database: each group of combustion
Gas-turbine dynamic operation condition sample point consists of two parts, and a part is opposite by fuel flow Wf, guide vane angle VGV, high-pressure shaft
Parameter is inputted composed by revolving speed NH, low-pressure shaft relative rotation speed NL and power turbine relative rotation speed NPT, another part is by firing
Output parameter composed by remaining running parameter of gas-turbine；Successively by the c × d chosen × e × 2 × f group sample point input parameter
It is input in Gas Turbine Simulation model, the output parameter of every group of sample point can be calculated.
2. gas turbine dynamic operation condition database sample point choosing method according to claim 1, it is characterised in that: step
In SS5, remaining running parameter of the gas turbine includes high and low pressure shaft angle acceleration, the disengaging of high and low pressure compressor and turbine
Mouth pressure and temperature.
3. gas turbine dynamic operation condition database sample point choosing method according to claim 1, it is characterised in that: one group
The input parameter of sample point are as follows: fuel flow Wf, guide vane angle VGV, high-pressure shaft relative rotation speed NH, low-pressure shaft relative rotation speed NL with
And power turbine relative rotation speed NPT amounts to five parameters, output parameter is each cross section parameter of gas turbine and remaining each work
Parameter, i.e., the corresponding determining gas turbine working condition of one group of different Wf, VGV, NH, NL and NPT values.
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| CN113312718B (en) * | 2021-05-25 | 2022-11-11 | 上海中联重科桩工机械有限公司 | Electromechanical and hydraulic simulation method and device |
| CN113374582B (en) * | 2021-07-28 | 2022-09-27 | 哈电发电设备国家工程研究中心有限公司 | Device and method for evaluating running state of gas turbine |
| CN114635801B (en) * | 2022-03-23 | 2023-11-21 | 合肥工业大学 | Back pressure characteristic optimization method and device for gas generator |
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