CN108108528A - A kind of split shaft boat changes the one-dimensional adaptation design method of combustion engine power turbine - Google Patents
A kind of split shaft boat changes the one-dimensional adaptation design method of combustion engine power turbine Download PDFInfo
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Abstract
The present invention relates to a kind of split shaft boats to change the one-dimensional adaptation design method of combustion engine power turbine, and this method can be used for changing the one-dimensional scheme of gas generator Rapid matching design motivation turbine of combustion engine for split shaft boat, and avoids complete machine overtemperature and into surge area.This method comprises the following steps：Power turbine negotiability lower limit is obtained according to gas generator compressor surge nargin and the limitation of combustor exit total temperature, different dynamic turbine design parameter combination scheme is obtained using orthogonal design, the one-dimensional design of power turbine and analysis are carried out by design point demand, selects more than negotiability lower limit and the highest one-dimensional scheme of efficiency and carries out total simulation verification.The split shaft boat that the present invention is established changes the one-dimensional adaptation design method of combustion engine power turbine, it is designed with reference to the analysis of general components method with component Direct And Inverse Problems, the one-dimensional designing scheme of power turbine can be quickly obtained, while ensureing combustion engine design performance, improve slow-speed of revolution starting characteristic, so as to avoid compressor into asthma and turbine overtemperature.
Description
Technical field
The present invention relates to gas turbine fields, change one-dimensional of combustion engine power turbine more particularly, to a kind of split shaft boat
With design method.
Background technology
It is a kind of gas turbine based on ripe aero-engine remodeling that boat, which changes combustion engine, can share setting for aero-engine
Meter, manufacture and test system, reduce developing risk, shorten the lead time, reduce development cost.With certain aero-engine remodeling point
Exemplified by shaft type gas turbine, Core Engine can be used as gas generator, in downstream matched design power turbine
To output power.People focus mainly on performance of the power turbine in design point at present, yet with the flow of power turbine
Effect is blocked, gas turbine expansion ratio is caused to decline, in order to maintain gasifier speed constant, it is necessary to increase amount of fuel, by
This causes turbine inlet total temperature to improve, and compressor pressure ratio increases, and gas generator off-design performance was particularly started
Journey brings a series of influences, as compressor into asthma, turbine inlet temperature (TIT) is higher the problems such as, it is therefore desirable to consider design possess it is wider
Big flow characteristic power turbine.
The demand brings following two aspects problem：On the one hand, the non-design of complete machine can be met for guarantee power turbine characteristic
Working condition requirement is, it is necessary to verify influence of the different dynamic turbine wheel solution to combustion engine overall performance, i.e., repeatedly with reference to power turbine characteristic
Overall calculating is carried out with upstream gas generator characteristic, is taken longer.On the other hand, whether verification power turbine meets bulking property
It can require just to need to obtain power turbine characteristic curve, and precision of the one-dimensional conceptual design of power turbine itself is insufficient, particularly flows
Amount is affected to gas generator, it is therefore desirable to analyze to be closed with reference to the one-dimensional indirect problem design of turbine and one-dimensional direct problem
Believable one-dimensional scheme and characteristic are managed, and combines total demand Choice, to improve complete machine off-design point performance of operating condition.
The content of the invention
The defects of present invention is solves the more than prior art and deficiency provide a kind of based on total simulation decider stream
The split shaft of flow characteristic limit value and the one-dimensional Direct And Inverse Problems Iterative Design of turbine boat changes the one-dimensional adaptation design method of combustion engine power turbine,
While combustion engine design performance is ensured, slow-speed of revolution starting characteristic can be improved, so as to avoid compressor into asthma and turbine overtemperature.
The characteristics of this method combination split shaft aero-derived gas turbine, i.e. gas generator characteristics of components are it is known that power whirlpool
Wheel discharge characteristic influences gas generator apparent and efficiency characteristic only influences work(size, therefore can be derived by total simulation
Whether rationally power turbine discharge characteristic lower limit provides verification so as to be designed for power turbine, only needs the flow of power turbine
Characteristic meets the requirement more than its lower limit, you can meets overall needs, avoids power turbine characteristic substituting into totality repeatedly
Emulate the work verified.And the one-dimensional design of power turbine there is flow accuracy it is insufficient the shortcomings that, can be set by one-dimensional
Meter and One Dimension Analysis correct iteration and realize the accurate control of design point repeatedly, while the flow that can also obtain off-design behaviour is special
Property, it is compared with facilitating with above-mentioned power turbine discharge characteristic lower limit.
For realization more than goal of the invention, the technical solution adopted by the present invention is：
A kind of split shaft boat changes the one-dimensional adaptation design method of combustion engine power turbine, and the split shaft boat, which changes combustion engine, includes combustion gas
Generator and power turbine, the power turbine are located at the downstream of gas generator, it is characterised in that：The described method includes following
Step：
SS1. combine aggregate analysis and obtain power turbine negotiability lower limit
First, the power turbine negotiability lower limit limited by compressor surge nargin border is determined, then, it is determined that by
Combustor exit temperatureThe power turbine negotiability lower limit limited, finally, with reference to above-mentioned two negotiability lower limit model
It encloses, is power turbine negotiability lower limit.
SS2 gives different designs variable assembled scheme using orthogonal design
Orthogonal design is carried out to the one-dimensional design variable of 5 power turbines, including loading coefficient Ht, reaction degree Ω, flow system
NumberAxial speed ratio factor KaWith inlet and outlet central diameter ratioDeng, the restriction range of each parameter and different values are given on demand, and
Suitable orthogonal arrage is selected to obtain the various combination scheme of above-mentioned parameter.
SS3. the one-dimensional indirect problem design of power turbine
According to gas turbine master-plan demand, for parameter combination scheme different in SS2, a little lower power is designed
The one-dimensional indirect problem design of turbine, input parameter are included under design pointExpansion ratio πPTd, flow GPTd, rotating speed NPT, grade
Number etc. with reference to the parameter determined in input parameter and SS2, is designed by indirect problem, you can obtains one at power turbine central diameter
Tie up aerodynamic parameter and initial channel size.
SS4. the one-dimensional direct problem analysis of power turbine and design modification
Since the one-dimensional indirect problem design accuracy in SS3 is limited, with reference to the direct problem analysis corrections result.First,
It is pneumatic under different operating modes with the direct problem analysis method assessment power turbine that body force is combined using one-dimensional Eulerian equation
Performance, i.e. efficiency characteristicAnd discharge characteristicAnd extract the effect under design point
Rate ηPTdWith flow GPT′.Then, by GPT' and GPTdIt is compared, obtains difference DELTA GPT=GPTd-GPT', if residual error | Δ GPT/GPTd
| ＜ 0.02, then the program is feasible, otherwise amendment design flow, i.e. GPTd'=GPTd+ΔGPT, again by Gd' carry out indirect problem set
Meter and direct problem analysis, until residual error is met the requirements.So far the power turbine that all assembled schemes in SS2 can be completed one-dimensional is set
Meter.
SS5. option screening and verification
Option screening is carried out first, extracts the power turbine discharge characteristic line of all schemes in SS4With the power turbine flux lower limit line obtained in SS1It is compared.After screening
Scheme should meet under the above-mentioned different expansion ratios of each rotating speed, corresponding corrected flowIt is all higher than
The power turbine flux lower limit obtained in SS1Then, η in scheme is taken after screeningdMaximum scheme is final
Scheme.Finally, the power turbine characteristic combination gas generator characteristic line of the program can be obtained and matches the power turbine
Complete machine equilibrium running line is to carry out final verification.
Preferably, consider overtemperature limitation and surge margin limitation, with reference to gas generator characteristic, pass through ship performance calculation
Power turbine discharge characteristic lower limit is obtained, power turbine to be instructed to design.
Preferably, in step SS1, the power turbine negotiability lower limit limited by compressor surge nargin border is determined
Specific method be：With reference to existing gas generator compressor characteristics, surge margin k is given, determines that compressor turns in difference
The corresponding operating mode of the nargin under speed, and above-mentioned operating mode is defined as surge margin border, by solving Nonlinear System of Equations, obtain
Obtain the corresponding power turbine negotiability in the border.
Further, compressor surge nargin border and some gasifier speed N are givenG, it is known that gas turbine
Import total temperatureAnd stagnation pressureCompressor inlet converts into rotating speedT ' expression standard atmospheric temperatures, by
NcorCThe existing compressor surge nargin boundary line of interpolation, can obtain compressor pressure ratio πC, compressor inlet flow GCIt is imitated with compressor
Rate ηC；For gas generator, working condition also needs to two variables and determines, including combustor exit temperatureAnd
Gas turbine inlet flow GT, gas turbine expansion ratio πT, turbine efficiency ηTRotating speed can be converted by turbineAnd turbine
Import corrected flowIt is obtained by performance plot interpolation；
According to flow conservation, there is GC=GT-Gf；
According to power conservation, there is PC=PT；
Wherein, GfFor fuel mass flow, PC、PTRepresent power input to compressor respectively and gas turbine go out work(, using newton-
The gloomy method of pressgang solves above-mentioned Nonlinear System of Equations, and unknown parameter can be obtainedAnd GT, so far, the work of each component of gas generator
Situation and each cross section parameter are determined；By solving different NG, different power turbine expansion ratio π can be obtainedPTWith
Corrected flowTo sum up, power turbine negotiability lower limit of establishment due to surge margin boundary line is established.
Preferably, in step SS1, determine by combustor exit temperatureThe power turbine negotiability lower limit limited
Specific method is：Given combustor exit total temperatureLimits valueIt determinesRestricted boundary, by solving nonlinear equation
Group obtainsThe corresponding power turbine negotiability of restricted boundary.
Further, by the case of calculating different gasifier speedsReach the gas generator work during upper limit
Condition, so determine power turbine becauseThe negotiability lower limit of limitation.Specific calculating process is as follows：It is givenUpper limit value and certain
One NG, gas turbine inlet condition is known quantity, and unknown quantity is compressor inlet flow GCWith gas turbine inlet flow GT, pressure
Mechanism of qi and turbine efficiency, compressor pressure ratio and expansion ratio of turbine can be obtained by known characteristics of components figure interpolation；
According to flow conservation, there is GC=GT-Gf,
According to power conservation, there is PC=PT,
Above-mentioned Nonlinear System of Equations is solved using Newton-Raphson method, unknown parameter G can be obtainedCAnd GT, so far, combustion gas hair
The working condition of each component of raw device and each cross section parameter are determined.By solving different NG, different move can be obtained
Power expansion ratio of turbine πPTAnd corrected flowTo sum up, combustor exit temperatureUnder the power turbine negotiability limited
Limit is determined.
Preferably, in step SS1, the specific method for determining power turbine negotiability is：Take different dynamic turbine expansion
Compare πPTCorresponding corrected flowMaximum defines power turbine discharge characteristic lower limitWherein For power turbine import stagnation pressure,For power turbine import total temperature, GPTFor power turbine inlet flow
Amount.
Preferably, in step SS2, suitable orthogonal arrage is selected to obtain the various combination scheme of above-mentioned parameter, and need to use up can
Amount of projects can be reduced, while ensures that above-mentioned different assembled scheme is representative in gamut.
Preferably, the method that is combined is analyzed with one-dimensional direct problem using the design of one-dimensional indirect problem, by modified flow rate into
It goes and iterates to ensure design point traffic requirement, while one-dimensional Eulerian equation is used to be combined with body force to be quickly obtained completely
Performance of the power turbine of sufficient design point requirement under different operating modes.
Compared with prior art, the beneficial effects of the invention are as follows：
The present invention provides a kind of split shaft boats to change the one-dimensional adaptation design method of combustion engine power turbine, and this method passes through first
Total simulation obtains power turbine discharge characteristic lower limit, so as to avoid repeating power turbine discharge characteristic to substitute into total simulation
The work of calculating；Secondly, with reference to the one-dimensional Direct And Inverse Problems design and analysis of power turbine, can be screened with reference to above-mentioned discharge characteristic lower limit
Efficiency peak scheme is obtained, that is, complete machine is avoided while meeting design point demand into asthma and overtemperature；Again, taken in this method
Orthogonal design method reduces sample size, and reduces calculation amount using power turbine One Dimension Analysis, so as to quickly realize power
The one-dimensional scheme matched design of turbine.
Description of the drawings
Fig. 1 is that the split shaft boat of the present invention changes the flow chart of the one-dimensional adaptation design method of combustion engine power turbine.
Fig. 2 for the exemplary surge margin restraining line being expressed on compressor pressure ratio-discharge characteristic figure andRestrictive curve.
Fig. 3 for it is exemplary by surge margin restraining line andThe power turbine discharge characteristic lower limit that restrictive curve obtains.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention more comprehensible, develop simultaneously embodiment referring to the drawings, right
The present invention is further described, so that advantages and features of the invention can be easier to be readily appreciated by one skilled in the art.It needs
Illustrate, as described below is only presently preferred embodiments of the present invention, is not intended to limit the scope of the present invention.It is actual
On, in the case of 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 this
It will be apparent for field technology personnel.For example, the feature that the part as one embodiment shows or describes can
To be used together to generate another embodiment with another embodiment.It is therefore, it is intended that of the invention by such modification and change
Change is included in the range of appended claims and their equivalent.
The split shaft boat of the present invention changes the one-dimensional adaptation design method of combustion engine power turbine, and the split shaft boat, which changes combustion engine, to be included
Two components of gas generator and power turbine, wherein gas generator are ripe Core Engine, power turbine position
It is brand-new matched design in the downstream of gas generator.As shown in Figure 1, change geometry split gas turbine provided by the invention
Real-time simulation modeling method comprises the following steps：
SS1. combine aggregate analysis and obtain power turbine negotiability lower limit
First, the power turbine negotiability lower limit limited by compressor surge nargin border is determined：
Given compressor surge nargin border (see attached drawing 2) and some gasifier speed NG, it is known that gas turbine
Import total temperatureAnd stagnation pressureCompressor inlet converts into rotating speedT ' expression standard atmospheric temperatures, by
NcorCThe existing compressor surge nargin boundary line of interpolation, can obtain compressor pressure ratio πC, compressor inlet flow GCIt is imitated with compressor
Rate ηC.For gas generator, working condition also needs to two variables and determines, including combustor exit temperatureAnd
Gas turbine inlet flow GT(gas turbine expansion ratio πT, turbine efficiency ηTRotating speed can be converted by turbineAnd turbine
Import corrected flowIt is obtained by performance plot interpolation).
According to flow conservation, there is GC=GT-Gf。
According to power conservation, there is PC=PT。
Wherein, GfFor fuel mass flow, PC、PTRepresent power input to compressor respectively and gas turbine go out work(, using newton-
The gloomy method of pressgang solves above-mentioned Nonlinear System of Equations, and unknown parameter can be obtainedAnd GT, so far, the work of each component of gas generator
Situation and each cross section parameter are determined.By solving different NG, different power turbine expansion ratio π can be obtainedPTWith
Corrected flowTo sum up, power turbine negotiability lower limit of establishment due to surge margin boundary line is established (see attached drawing
3)。
Then, it is determined that combustor exit temperatureThe power turbine negotiability lower limit limited：By calculating different combustions
Under gas generator speed conditionsReach the gas generator operating mode during upper limit, so determine power turbine becauseThe stream of limitation
Logical ability lower limit.Specific calculating process is as follows：It is givenUpper limit value (see attached drawing 2) and a certain NG, gas turbine inlet condition is
Known quantity, unknown quantity are compressor inlet flow GCWith gas turbine inlet flow GT(remaining such as compressor and turbine efficiency,
Compressor pressure ratio and expansion ratio of turbine can be obtained by known characteristics of components figure interpolation).
According to flow conservation, there is GC=GT-Gf。
According to power conservation, there is PC=PT。
Above-mentioned Nonlinear System of Equations is solved using Newton-Raphson method, unknown parameter G can be obtainedCAnd GT, so far, combustion gas hair
The working condition of each component of raw device and each cross section parameter are determined.By solving different NG, different move can be obtained
Power expansion ratio of turbine πPTAnd corrected flowTo sum up, combustor exit temperatureUnder the power turbine negotiability limited
Limit is determined (see attached drawing 3).
It is power turbine negotiability lower limit with reference to above-mentioned two negotiability lower range.
SS2 gives different designs variable assembled scheme using orthogonal design
Orthogonal design is carried out to the one-dimensional design variable of 5 dimensionless power turbines, including loading coefficient Ht, reaction degree Ω,
Discharge coefficientAxial speed ratio factor KaWith inlet and outlet central diameter ratioDeng, give each parameter restriction range it is as follows：Ht∈[1.2,
1.8], Ω ∈ [0.3,0.7],Ka ∈ [1,1.4], The number of levels of each parameter is calmly
4, each parameter difference value is 0,33%, 66% and 100% in restriction range, selects orthogonal arrage L256 (54) above-mentioned to obtain
The various combination scheme of parameter so as to reduce amount of projects as far as possible, and ensures that said program combination has in gamut
It is representative.
SS3. the one-dimensional indirect problem design of power turbine
According to gas turbine master-plan demand, for parameter combination scheme different in SS2, a little lower power is designed
The one-dimensional indirect problem design of turbine, input parameter are included under design pointExpansion ratio πPTd, flow GPTd, rotating speed NPT, grade
Number etc. with reference to the parameter determined in input parameter and SS2, is designed by indirect problem, you can obtains one at power turbine central diameter
Tie up aerodynamic parameter and initial channel size.
SS4. the one-dimensional direct problem analysis of power turbine and design modification
Since the one-dimensional indirect problem design accuracy in SS3 is limited, with reference to the direct problem analysis corrections result.First,
Using aeroperformance of the one-dimensional direct problem analysis method assessment power turbine under different operating modes, AMDCKO loss moulds can be used
Type obtains efficiency characteristicAnd discharge characteristicAnd extract the effect under design point
Rate ηPTdWith flow GPT′.Then, by GPT' and GPTdIt is compared, obtains difference DELTA GPT=GPTd-GPT', if residual error | Δ GPT/
GPTd| ＜ 0.02, then the program is feasible, otherwise amendment design flow, i.e. GPTd'=GPTd+ΔGPT, again by Gd' carry out indirect problem
Design and direct problem analysis, until residual error is met the requirements.So far the power turbine that all assembled schemes in SS2 can be completed one-dimensional is set
Meter.
SS5. option screening and verification
Option screening is carried out first, extracts the power turbine discharge characteristic line of all schemes in SS4With the power turbine flux lower limit line obtained in SS1It is compared.After screening
Scheme should meet under the above-mentioned different expansion ratios of each rotating speed, corresponding corrected flowIt is all higher than
The power turbine flux lower limit obtained in SS1Then, η in scheme is taken after screeningdMaximum scheme is final
Scheme.Finally, the power turbine characteristic combination gas generator characteristic line of the program can be obtained and matches the power turbine
Complete machine equilibrium running line is to carry out final verification.
Obviously, examples detailed above of the invention is only intended to clearly illustrate example of the present invention, and is not 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
All any modification, equivalent and improvement made within bright spirit and principle etc., should be included in the claims in the present invention
Within protection domain.
Claims (9)
1. a kind of split shaft boat changes the one-dimensional adaptation design method of combustion engine power turbine, the split shaft boat changes combustion engine and is sent out including combustion gas
Raw device and power turbine, the power turbine are located at the downstream of gas generator, which is characterized in that the described method includes following steps
Suddenly：
SS1. combine aggregate analysis and obtain power turbine negotiability lower limit
The power turbine negotiability lower limit limited by compressor surge nargin border is determined first, it is then determined that by combustion chamber
Outlet temperatureThe power turbine negotiability lower limit limited finally with reference to above-mentioned two negotiability lower range, is
Power turbine negotiability lower limit；
SS2 gives different designs variable assembled scheme using orthogonal design
Orthogonal design is carried out to the one-dimensional design variable of multiple power turbines, the one-dimensional design variable includes loading coefficient Ht, counter-force
Spend Ω, discharge coefficientAxial speed ratio factor KaWith inlet and outlet central diameter ratioThe restriction range and not of each parameter is given on demand
Same value, and suitable orthogonal arrage is selected to obtain the various combination scheme of above-mentioned parameter；
SS3. the one-dimensional indirect problem design of power turbine
According to gas turbine master-plan demand, for parameter combination scheme different in step SS2, a little lower power is designed
The one-dimensional indirect problem design of turbine, input parameter are included under design pointExpansion ratio πPTd, flow GPTd, rotating speed NPT, grade
Number etc. with reference to the parameter determined in input parameter and step SS2, is designed by indirect problem, obtains one at power turbine central diameter
Tie up aerodynamic parameter and initial channel size；
SS4. the one-dimensional direct problem analysis of power turbine and design modification
The one-dimensional indirect problem design result in step SS3 is corrected with reference to direct problem method, first, is commented using direct problem analysis method
Estimate aeroperformance of the power turbine under different operating modes, i.e. efficiency characteristicAnd discharge characteristicAnd extract the efficiency eta under design pointPTdWith flow G 'PT；
Then, by G 'PTWith GPTdIt is compared, obtains difference DELTA GPT=GPTd-GPT', if residual error | Δ GPT/GPTd| ＜ 0.02, then
The program is feasible, otherwise amendment design flow, i.e. GPTd'=GPTd+ΔGPT；
Again, by Gd' indirect problem design and direct problem analysis are carried out, until residual error is met the requirements, so far complete institute in step SS2
There is the one-dimensional design of power turbine of assembled scheme；
SS5. option screening and verification
First, option screening is carried out, the power turbine discharge characteristic line of all schemes in extraction step SS4With the power turbine flux lower limit line obtained in step SS1It is compared, is sieved
Scheme after choosing should meet under the above-mentioned different expansion ratios of each rotating speed, corresponding corrected flow
More than the power turbine flux lower limit obtained in SS1
Then, η in scheme is taken after screeningdMaximum scheme is final scheme；
Finally, the power turbine characteristic combination gas generator characteristic line of the program can be obtained and matches the whole of the power turbine
Machine equilibrium running line is to carry out final verification.
2. split shaft boat according to claim 1 changes combustion engine power turbine adaptation design method, it is characterised in that：Consider super
With reference to gas generator characteristic, power turbine discharge characteristic is obtained by ship performance calculation for temperature limitation and surge margin limitation
Lower limit, power turbine to be instructed to design.
3. split shaft boat according to claim 1 changes combustion engine power turbine adaptation design method, it is characterised in that：Step
In SS1, the specific method for determining the power turbine negotiability lower limit limited by compressor surge nargin border is：With reference to
Some gas generator compressor characteristics give surge margin k, determine the nargin corresponding work of the compressor under different rotating speeds
Condition, and above-mentioned operating mode is defined as surge margin border, by solving Nonlinear System of Equations, obtain the corresponding power whirlpool in the border
Take turns negotiability.
4. split shaft boat according to claim 3 changes combustion engine power turbine adaptation design method, it is characterised in that：To level pressure
Mechanism of qi surge margin border and some gasifier speed NG, it is known that gas turbine inlet total temperatureAnd stagnation pressureIt calms the anger
Machine import converts into rotating speedT ' expression standard atmospheric temperatures, by NcorCThe existing compressor surge of interpolation is abundant
Boundary line is spent, compressor pressure ratio π can be obtainedC, compressor inlet flow GCWith compressor efficiency ηC；
For gas generator, working condition also needs to two variables and determines, including combustor exit temperature T3 *And
Gas turbine inlet flow GT, gas turbine expansion ratio πT, turbine efficiency ηTRotating speed can be converted by turbineAnd turbine
Import corrected flowIt is obtained by performance plot interpolation；
According to flow conservation, there is GC=GT-Gf；
According to power conservation, there is PC=PT；
Wherein, GfFor fuel mass flow, PC、PTPower input to compressor is represented respectively and gas turbine goes out work(, utilizes newton-pressgang
Gloomy method solves above-mentioned Nonlinear System of Equations, and unknown parameter can be obtainedAnd GT, so far, the working condition of each component of gas generator
And each cross section parameter is determined；
By solving different NG, different power turbine expansion ratio π can be obtainedPTAnd corrected flow
To sum up, power turbine negotiability lower limit of establishment due to surge margin boundary line is established.
5. the split shaft boat according to the claims changes combustion engine power turbine adaptation design method, it is characterised in that：Step
In rapid SS1, determine by combustor exit temperatureThe specific method of the power turbine negotiability lower limit limited is：Given combustion
Burn room outlet total temperatureLimits valueIt determinesRestricted boundary by solving Nonlinear System of Equations, obtainsRestricted boundary pair
The power turbine negotiability answered.
6. split shaft boat according to claim 5 changes combustion engine power turbine adaptation design method, it is characterised in that：Pass through meter
In the case of calculating different gasifier speedsReach the gas generator operating mode during upper limit, so determine power turbine becauseLimit
The negotiability lower limit of system, specific calculating process are as follows：
It is givenUpper limit value and a certain NG, gas turbine inlet condition is known quantity, and unknown quantity is compressor inlet flow GCAnd combustion
Air turbine inlet flow rate GT, compressor and turbine efficiency, compressor pressure ratio and expansion ratio of turbine can be special by known component
Property figure interpolation obtains；
According to flow conservation, there is GC=GT-Gf,
According to power conservation, there is PC=PT,
Above-mentioned Nonlinear System of Equations is solved using Newton-Raphson method, unknown parameter G can be obtainedCAnd GT, so far, gas generator
The working condition of each component and each cross section parameter are determined；
By solving different NG, different power turbine expansion ratio π can be obtainedPTAnd corrected flow
To sum up, combustor exit temperatureThe power turbine negotiability lower limit limited is determined.
7. the split shaft boat according to the claims changes combustion engine power turbine adaptation design method, it is characterised in that：Step
In rapid SS1, the specific method for determining power turbine negotiability is：Take different dynamic expansion ratio of turbine πPTCorresponding corrected flowMaximum defines power turbine discharge characteristic lower limitWherein For power whirlpool
Import stagnation pressure is taken turns,For power turbine import total temperature, GPTFor power turbine inlet flow rate.
8. the split shaft boat according to the claims changes combustion engine power turbine adaptation design method, it is characterised in that：Step
In rapid SS2, the restriction range for giving each parameter is as follows：Ht ∈ [1.2,1.8], Ω ∈ [0.3,0.7],Ka
∈ [1,1.4],The number of levels of fixed each parameter is 4, and each parameter difference value is 0 in restriction range,
33%, 66% and 100%, select orthogonal arrage L256 (54) to obtain the various combination scheme of above-mentioned parameter, so as to subtract as far as possible
Few amount of projects, and ensure that said program combination is representative in gamut.
9. the split shaft boat according to the claims changes combustion engine power turbine adaptation design method, it is characterised in that：It adopts
The method being combined with the design of one-dimensional indirect problem with the analysis of one-dimensional direct problem, iterates to ensure to set by modified flow rate
Enumeration traffic requirement, while be combined with body force using one-dimensional Eulerian equation and can be quickly obtained the power for meeting design point requirement
Performance of the turbine under different operating modes.
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| CN115186440A (en) * | 2022-06-15 | 2022-10-14 | 中国船舶重工集团公司第七0三研究所 | Pneumatic design method for two-stage high-speed power turbine of marine power generation type gas turbine |
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