CN103775139B - The clearance control system of turbogenerator and the clearance control method of turbogenerator - Google Patents
The clearance control system of turbogenerator and the clearance control method of turbogenerator Download PDFInfo
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- CN103775139B CN103775139B CN201210414622.XA CN201210414622A CN103775139B CN 103775139 B CN103775139 B CN 103775139B CN 201210414622 A CN201210414622 A CN 201210414622A CN 103775139 B CN103775139 B CN 103775139B
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Abstract
The invention discloses a kind of clearance control system of turbogenerator and the clearance control method of turbogenerator, relate to aero engine technology field.Solve the dissatisfactory problem of control effects that prior art exists turbine blade-tip gap.The clearance control system of this turbogenerator, comprise turbine casing detection device, turbine rotor detection device, control gear and cooling fluid feedway, turbine casing detection device, for detecting the radial-deformation of turbine casing in turbogenerator working procedure, and by testing result input control device; Control gear, calculates the actual gap size between turbine rotor blade blade tip and turbine casing for the value of radial-deformation according to the original gap size between turbine rotor blade blade tip during assembling and turbine casing, turbine casing, tachometer value and temperature value.Invention increases the precise control of the gap size between turbine rotor blade blade tip and turbine casing.
Description
Technical field
The present invention relates to aero engine technology field, be specifically related to the clearance control method of the turbogenerator of a kind of clearance control system of turbogenerator and the clearance control system application of this turbogenerator.
Background technique
Aero-turbine is due in transient process, the problem of deformation is there is between turbine rotor and turbine casing (or claiming casing, stator), when state of rest, reserved larger turbine cold conditions tip clearance is needed between the blade tip of rotor blade and turbine casing, mill can not be touched mutually to make rotor and turbine casing, but oil consumption rate increases when larger tip clearance can cause engine steady state to work, therefore, civil engine needs to take measures to make the tip clearance when engine stabilizer works keep best usually.
The main method controlling the gap (abbreviation turbine blade-tip gap) between turbine casing and turbine rotor blade blade tip is the thermal distortion by controlling turbine casing, with by the gap control between turbine blade and turbine casing in comparatively suitable scope.More rough research is thought: adopt effective turbine blade-tip gap control system, can make oil consumption rate decline about 1%-2%, improves Economy be significant for civil engine.Common turbine blade-tip gap controls to be the cooled gas adopting fan or blower outlet, carries out controlled cooling to control its thermal distortion to turbine casing.
The control strategy that above-mentioned turbine blade-tip gap control system is applied, common are two kinds of forms: one is open type gap control, in control strategy, preliminary election sets the cooling air scale of construction under different engine behavior, control system is according to motor current operating state, and control valve aperture is to carry out gap control; Another is semi-closure ring type gap control, namely on the basis of above-mentioned open type gap control, measures the temperature of turbine casing characteristic point, and this temperature feedback is to control system, and form half-closed loop control, this mode is more more effective than open type gap control.
At least there is following problem in prior art:
Open type gap control Problems existing is: do not form feedback in control strategy, do not form closed loop control, therefore Control platform is lower.
Semi-closure ring type gap control Problems existing is: the change of turbine casing temperature, the deformation of turbine casing can not be reflected completely, this due to the usual structure of turbine casing be extremely complicated, there is complicated linkage structure and turbine casing turbine casing in engine working process also can be subject to the impact of the series of factors such as ovality of inside and outside differential pressure, deadweight generation.Part test finds: the distortion obtained by turbine casing temperature computation, deviation is there is with the practical distortion of turbine casing, this deviate is only the deviation considered turbine casing linkage structure complexity and produce, if consider the factors such as turbine casing inside and outside differential pressure, deadweight, this deviate may be larger.Therefore, semiclosed loop gap control measures turbine casing temperature, can not react to entirely accurate the deformation of casing.
Because the temperature of turbine casing in prior art can not reflect its deformation completely, thus make that also certain error is existed to the prediction of turbine blade-tip gap, cause the control effects of turbine blade-tip gap not ideal enough.
Summary of the invention
The object of the invention is the clearance control method of the turbogenerator proposing a kind of clearance control system of turbogenerator and the clearance control system application of this turbogenerator, solve the dissatisfactory technical problem of control effects that prior art exists turbine blade-tip gap.
For achieving the above object, the invention provides following technological scheme:
The clearance control system of the turbogenerator that the embodiment of the present invention provides, comprises turbine casing detection device, turbine rotor detection device, control gear and cooling fluid feedway, wherein:
Described control gear is electrically connected by circuit or wireless signal transceiver with described turbine casing detection device, described turbine rotor detection device and described cooling fluid feedway;
Described turbine casing detection device, for detecting the radial-deformation of turbine casing in turbogenerator working procedure, and inputs described control gear by testing result;
Described turbine rotor detection device, for detecting the tachometer value of turbine rotor and the temperature value of turbine exhaust in described turbogenerator working procedure, and inputs described control gear by testing result;
Described control gear, the actual gap size between described turbine rotor blade blade tip and described turbine casing is calculated for the value of the radial-deformation according to the original gap size between described turbine rotor blade blade tip during assembling and described turbine casing, described turbine casing, described tachometer value and described temperature value, or, for calculating target casing amount of deformation according to original gap size, target gap size, described tachometer value and the described temperature value between described turbine rotor blade blade tip during assembling and described turbine casing;
Described control gear, also increasing instruction for sending flow to described cooling fluid feedway when described actual gap size is greater than the CLV ceiling limit value of target gap size or when the value of the radial-deformation of described turbine casing is greater than described target casing amount of deformation, when described actual gap size is less than the lower limit of target gap size or when the value of the radial-deformation of described turbine casing is less than described target casing amount of deformation, flow being sent to described cooling fluid feedway and reducing instruction;
Described cooling fluid feedway, for increasing the flow to the cooling fluid that described turbine casing exports after receiving described flow increase instruction, reduces the flow to the cooling fluid that described turbine casing exports after receiving described flow minimizing instruction.
In one embodiment, described control gear comprises centrifugal deformation computing module, radial heat distortion amount computing module and difference contrast module, wherein:
Described centrifugal deformation computing module, for calculating the amount of deformation that described turbine rotor produces because of centrifugal force according to the material characteristic parameter of described tachometer value and described turbine rotor;
Described radial heat distortion amount computing module, for calculating the radial heat distortion amount that described turbine rotor produces because of thermal expansion according to the material characteristic parameter of described temperature value and described turbine rotor;
Described difference contrast module is used for according to formula C
actual=C
original+ Δ L
casing-Δ L (N)-Δ L (T
exhaust), calculate the actual gap size between turbine rotor blade blade tip and described turbine casing described in described turbogenerator working procedure; Or described difference contrast module is used for according to formula Δ L
target casing=Δ L (N)+Δ L (T
exhaust)+C
target-C
originalcalculate described target casing amount of deformation; In formula:
C
actualfor the actual gap size described in described turbogenerator working procedure between turbine rotor blade blade tip and described turbine casing;
C
originalfor the original gap size between described turbine rotor blade blade tip during assembling and described turbine casing;
Δ L
casingfor the value of the radial-deformation of turbine casing in the described turbogenerator working procedure that detects in described turbogenerator working procedure;
The value of the amount of deformation that Δ L (N) produces because of centrifugal force for turbine rotor described in described turbogenerator working procedure;
Δ L (T
exhaust) value of radial heat distortion amount that produces because of thermal expansion for turbine rotor described in described turbogenerator working procedure;
Δ L
target casingfor described target casing amount of deformation;
C
targetfor described target gap size.
In one embodiment, described control gear, the value of the radial heat distortion amount that value and described turbine rotor for being calculated the amount of deformation that described turbine rotor produces because of centrifugal force by rotor deformation model are produced because of thermal expansion.
In one embodiment, described turbine casing detection device comprises at least one disformation sensor, and described turbine casing is high-pressure turbine casing or low-pressure turbine casing.
In one embodiment, described turbine casing is high-pressure turbine casing, described high-pressure turbine casing comprises outer casing, outer shroud supports and outer shroud, described actual gap size is the spacing dimension between described turbine rotor blade blade tip and described outer shroud, and described disformation sensor is arranged at described outer shroud and supports.
In one embodiment, described disformation sensor is uniformly distributed in the support of described outer shroud along the circumferential direction that described outer shroud supports.
In one embodiment, the number of described disformation sensor is 2 ~ 4.
In one embodiment, described disformation sensor is resistive transducer, described disformation sensor comprises palisade resistance wire, and described palisade resistance wire is pasted onto on the outer surface that described outer shroud supports, the distortion that the length of described palisade resistance wire and cross-section area all support with described outer shroud and changing.
In one embodiment, in the described turbogenerator working procedure that the described turbine casing detection device adopted in described formula detects, the value of the radial-deformation of turbine casing is maximum value, minimum value or the mean value in the testing result of at least two described disformation sensors.
In one embodiment, described turbine rotor detection device comprises speed probe and temperature transducer, and described control gear is control chip, wherein:
Described speed probe, for measuring described tachometer value;
Described temperature transducer is for measuring described temperature value;
The valve that described cooling fluid feedway comprises cooled gas feeding mechanism, gas transmission pipeline and is arranged on described gas transmission pipeline;
The gas delivery port of described gas transmission pipeline is towards described turbine casing, described valve is electrically connected with described control gear, and described valve increases instruction according to described flow or described flow reduces the size that instruction controls described gas transmission pipeline conducting area in real time.
The clearance control method of the turbogenerator that the embodiment of the present invention provides, at least comprises the following steps:
The radial-deformation of turbine casing is detected in turbogenerator working procedure;
The tachometer value of turbine rotor and the temperature value of turbine exhaust is detected in described turbogenerator working procedure;
The actual gap size between described turbine rotor blade blade tip and described turbine casing is calculated according to the value of the radial-deformation of the original gap size between described turbine rotor blade blade tip during assembling and described turbine casing, described turbine casing, described tachometer value and described temperature value, or, calculate target casing amount of deformation according to original gap size, target gap size, described tachometer value and the described temperature value between described turbine rotor blade blade tip during assembling and described turbine casing;
When described actual gap size is greater than the CLV ceiling limit value of target gap size or when the value of the radial-deformation of described turbine casing is greater than described target casing amount of deformation, increase the flow to the cooling fluid that described turbine casing exports;
When described actual gap size is less than the lower limit of target gap size or when the value of the radial-deformation of described turbine casing is less than described target casing amount of deformation, reduce the flow to the cooling fluid that described turbine casing exports.
In one embodiment, the method calculating the actual gap size between described turbine rotor blade blade tip and described turbine casing or calculate target casing amount of deformation comprises the following steps:
By rotor deformation model, calculate according to the material characteristic parameter of described tachometer value and described turbine rotor the amount of deformation that described turbine rotor produces because of centrifugal force;
By rotor deformation model, calculate according to the material characteristic parameter of described temperature value and described turbine rotor the radial heat distortion amount that described turbine rotor produces because of thermal expansion;
According to formula C
actual=C
original+ Δ L
casing-Δ L (N)-Δ L (T
exhaust), calculate the actual gap size between turbine rotor blade blade tip and described turbine casing described in described turbogenerator working procedure, or, according to formula Δ L
target casing=Δ L (N)+Δ L (T
exhaust)+C
target-C
originalcalculate described target casing amount of deformation; In formula:
C
actualfor the actual gap size described in described turbogenerator working procedure between turbine rotor blade blade tip and described turbine casing;
C
originalfor the original gap size between described turbine rotor blade blade tip during assembling and described turbine casing;
Δ L
casingfor the value of the amount of deformation of turbine casing detected in described turbogenerator working procedure;
The value of the amount of deformation that Δ L (N) produces because of centrifugal force for turbine rotor described in described turbogenerator working procedure;
Δ L (T
exhaust) value of radial heat distortion amount that produces because of thermal expansion for turbine rotor described in described turbogenerator working procedure;
Δ L
target casingfor described target casing amount of deformation;
C
targetfor described target gap size.
In one embodiment, in the described turbogenerator working procedure that detects of described turbine casing detection device, the value of the radial-deformation of turbine casing is maximum value, minimum value or the mean value at least two testing results.
Based on technique scheme, the embodiment of the present invention at least can produce following technique effect:
In the clearance control system of the turbogenerator provided due to the embodiment of the present invention and method, the radial-deformation (or claiming circumferential deformation amount) of turbine casing directly can be detected in turbogenerator working procedure, because the data that direct-detection goes out are more more accurate than the data estimated by other indirect modes, the radial deformation situation of the turbine casing reacted is more comprehensive (such as: by casing by inside and outside differential pressure, the series of factors etc. such as the ovality that deadweight produces also are taken into account), so when controlling gap size (actual gap size namely in working procedure) in turbogenerator working procedure between turbine rotor blade blade tip and turbine casing, this gap size can be controlled ideal, accurately in scope, so solve the dissatisfactory technical problem of control effects that prior art exists turbine blade-tip gap.
In addition, partly or entirely comparatively preferred technological scheme provided by the invention compared with prior art at least can also produce following technique effect:
1, turbine blade-tip gap controls to be by carrying out controlled cooling to realize to turbine casing, the distortion of casing is the direct object of gap control, therefore the distortion detecting turbine casing be the most directly, mode fast and accurately, the clearance control system of turbogenerator provided by the invention is made to define more reliable closed loop control system thus, make whole clearance control system feedback speed faster, the quality controlled is higher, and this clearance control method also has the advantage that step is simple, control procedure is saved time, efficiency is high simultaneously;
2, because turbine casing has complicated linkage structure, the distortion of the outer casing of turbine casing not necessarily directly can affect the distortion of turbo machine outer shroud, so by detecting the amount of deformation that (or claim: monitoring) outer shroud supports, more directly can detect the situation of change of turbine blade-tip gap, to the detection of turbine casing distortion, reflect the complexity of casing due to linkage structure, deadweight, inside and outside differential pressure, the distortion that maneuver load etc. cause, by turbine casing by inside and outside differential pressure, the series of factors etc. such as the ovality that deadweight produces also are taken into account, more directly reflect gap situation, and then ensure that the effect of gap control is even more ideal.
3, by multiple disformation sensors circumferentially, effectively can monitor radial direction (radial direction also the can be understood as circumference) inhomogeneous deformation because a variety of causes produces herein, more effectively monitor the gap situation of change of the circumference of motor, thus carry out more effectively gap control.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide a further understanding of the present invention, and form a application's part, schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
The schematic diagram of annexation between the clearance control system internal portions of the turbogenerator that Fig. 1 provides for the embodiment of the present invention and turbogenerator component home;
The schematic diagram of position relationship between the high-pressure turbine casing that Fig. 2 is the turbogenerator shown in Fig. 1 and turbine rotor blade blade tip;
Fig. 3 is the high-pressure turbine casing outer-loop support shown in Fig. 2 and the schematic diagram of annexation between disformation sensor;
A schematic flow sheet of the clearance control method of the turbogenerator that Fig. 4 provides for the embodiment of the present invention;
Another schematic flow sheet of the clearance control method of the turbogenerator that Fig. 5 provides for the embodiment of the present invention;
Mark in figure: 1, turbine casing detection device; 2, circuit; 3, control gear; 4, cooling fluid feedway; 41, valve; 42, gas transmission pipeline; 50, turbine casing; 501, outer casing; 502, outer shroud supports; 503, outer shroud; 51, high-pressure turbine; 52, low-pressure turbine 6, turbine rotor blade; 7, fan; 81, low pressure compressor; 82, high-pressure compressor; 9, firing chamber.
Embodiment
Below by accompanying drawing Fig. 1 ~ Fig. 5 and the mode enumerating embodiment more of the present invention, technological scheme of the present invention (comprising optimal technical scheme) is described in further detail.It should be noted that: any technical characteristics in the present embodiment, any technological scheme is all one or more in the technical characteristics of plurality of optional or optional technological scheme, cannot exhaustive all alternative technical characteristicss of the present invention and alternative technological scheme in order to describe succinct to need in presents, also the mode of execution being not easy to each technical characteristics all emphasizes that it is one of optional numerous embodiments, so those skilled in the art should know: any technical characteristics in the present embodiment and any technological scheme all do not limit the scope of the invention, protection scope of the present invention should comprise those skilled in the art and not pay the thinkable any alternate embodiments of creative work.
Embodiments provide the clearance control method of a kind of gap control effect more preferably turbogenerator of the clearance control system application of the clearance control system of turbogenerator and this turbogenerator.
Below in conjunction with the elaboration that Fig. 1 ~ Fig. 5 carries out specifically to technological scheme provided by the invention, the technological scheme of arbitrary technological means provided by the invention being carried out replacing or two or more technological means provided by the invention being carried out mutually combining and obtain all should within protection scope of the present invention.
System embodiment:
As shown in Fig. 1 ~ Fig. 5, the clearance control system of the turbogenerator that the embodiment of the present invention provides, comprise turbine casing detection device 1, turbine rotor detection device (not shown), as shown in Figure 1 control gear 3 and cooling fluid feedway 4 as shown in Figure 2, wherein:
Control gear 3 is electrically connected by circuit 2 or wireless signal transceiver with turbine casing detection device 1, turbine rotor detection device and cooling fluid feedway 4, is electrically connected in this example preferably by circuit 2.
Turbine casing detection device 1, for detecting the radial-deformation (also can be understood as circumferential deformation amount herein) of turbine casing 50, and by testing result input control device 3 in turbogenerator working procedure.
Turbine rotor detection device, for detecting the tachometer value of turbine rotor and the temperature value of turbine exhaust, and by testing result input control device 3 in turbogenerator working procedure.
Control gear 3, the actual gap size in turbogenerator working procedure between turbine rotor blade 6 blade tip and turbine casing 50 is calculated for the value of radial-deformation according to the original gap size between turbine rotor blade 6 blade tip during assembling and turbine casing 50, turbine casing 50, tachometer value and temperature value, or, for calculating target casing amount of deformation according to original gap size, target gap size, tachometer value and the temperature value between turbine rotor blade 6 blade tip during assembling and turbine casing 50.
Control gear 3, time also for being greater than the CLV ceiling limit value of target gap size in actual gap size or be greater than described target casing amount of deformation in the value of the radial-deformation of turbine casing 50 and flow is sent to cooling fluid feedway 4 increase instruction, when actual gap size is less than the lower limit of target gap size or when the value of the radial-deformation of turbine casing 50 is less than described target casing amount of deformation, flow is sent to cooling fluid feedway 4 and reduce instruction.
Cooling fluid feedway 4, for receiving the flow increasing the cooling fluid (being preferably cooled gas) to turbine casing 50 output after flow increases instruction, is receiving the flow reducing the cooling fluid to turbine casing 50 output after flow reduces instruction.
Fan 7, low pressure compressor 81, high-pressure compressor 82 and firing chamber 9 is also illustrated in Fig. 1.
Owing to directly can be detected the radial-deformation of turbine casing 50 in the embodiment of the present invention in turbogenerator working procedure by turbine casing detection device 1, because the data that direct-detection goes out are more more accurate than the data estimated by other indirect modes, the radial deformation situation of the turbine casing 50 reacted is more comprehensive (such as: by casing by inside and outside differential pressure, the series of factors etc. such as the ovality that deadweight produces also are taken into account), so this actual gap size can be controlled ideal when controlling the actual gap size between turbine rotor blade 6 blade tip and turbine casing 50, accurately in scope.
In the present embodiment, control gear 3 comprises centrifugal deformation computing module, radial heat distortion amount computing module and difference contrast module, wherein:
Centrifugal deformation computing module, for calculating the amount of deformation that turbine rotor produces because of centrifugal force according to the material characteristic parameter (such as: Young's modulus etc.) of tachometer value and turbine rotor.
Radial heat distortion amount computing module, for calculating the radial heat distortion amount that turbine rotor produces because of thermal expansion according to the material characteristic parameter (such as: expansion coefficient etc.) of temperature value and turbine rotor.
Difference contrast module is used for according to formula C
actual=C
original+ Δ L
casing-Δ L (N)-Δ L (T
exhaust), calculate the actual gap size between turbine rotor blade 6 blade tip and turbine casing 50 in turbogenerator working procedure, or difference contrast module is used for according to formula Δ L
target casing=Δ L (N)+Δ L (T
exhaust)+C
target-C
originalcalculate described target casing amount of deformation; In formula:
C
actualfor the actual gap size in turbogenerator working procedure between turbine rotor blade 6 blade tip and turbine casing 50.
C
originalfor the original actual gap size between turbine rotor blade 6 blade tip during assembling and turbine casing 50.
Δ L
casingfor the value of the radial-deformation of turbine casing 50 in the turbogenerator working procedure that detects in turbogenerator working procedure.
The value of the amount of deformation that Δ L (N) produces because of centrifugal force for turbine rotor in turbogenerator working procedure.
Δ L (T
exhaust) value of radial heat distortion amount that produces because of thermal expansion for turbine rotor in turbogenerator working procedure;
Δ L
target casingfor described target casing amount of deformation, namely the desired deflection amount of turbine casing 50;
C
targetfor described target gap size, the ideal gap size in target gap size i.e. turbogenerator working procedure between turbine rotor blade 6 blade tip and turbine casing 50.
Because in turbogenerator working procedure, turbine rotor and casing all radial deformation can occur, so need the amount of deformation considering both, the actual gap size between turbine rotor blade 6 blade tip and turbine casing 50 in reality, accurately turbogenerator working procedure just can be drawn.
Certainly, other formula are used to obtain the technological scheme (such as detecting the actual gap size between turbine rotor blade 6 blade tip and turbine casing 50 by optical sensor) of the actual gap size in turbogenerator working procedure between turbine rotor blade 6 blade tip and turbine casing 50 with alternative above-mentioned formula or other obtaining method all within protection scope of the present invention to substitute above-mentioned obtaining method.
In the present embodiment, control gear 3 calculates the value of the radial heat distortion amount that the value of the amount of deformation that turbine rotor produces because of centrifugal force and turbine rotor produce because of thermal expansion preferably by rotor deformation model.
Low, the fireballing advantage of cost should be had for the mode of test by the method for rotor deformation model calculating turbine rotor radial-deformation.
Target gap size in Fig. 4 is: the ideal value (this gap size and previously described target gap size) of the gap size between turbine rotor blade 6 blade tip and turbine casing 50, target gap refers to the tip clearance of wishing the best reached in engine operation process, under this gap, engine operating efficiency is higher, also safer, and fit up gap is: original actual gap size during assembling between turbine rotor blade 6 blade tip and turbine casing 50, fit up gap is the cold conditions gap of motor when assembling, target gap and fit up gap are diverse concepts,
Original actual gap size (C when target casing amount of deformation refers to the rotor deformation and target gap size sum that are calculated by rotor deformation model and assembling in Fig. 4 between turbine rotor blade 6 blade tip and turbine casing 50
original) between difference.The size of actual casing amount of deformation can be regulated by the mode of adjustment cold air flow (or claim: the flow of cooled gas), and the target that actual casing amount of deformation finally regulates is equal or close with target casing amount of deformation.
In the present embodiment, turbine casing detection device 1 comprises at least one disformation sensor as shown in Figure 3, and turbine casing 50 is high-pressure turbine casing or low-pressure turbine casing.
This technology not only can be applied to the actual gap size controlled between high-pressure turbine casing and turbine rotor, also can be applied to the actual gap size controlled between high-pressure turbine casing and turbine rotor.
Disformation sensor can be arranged on high-pressure turbine casing, also can be arranged on low-pressure turbine casing, also all can arrange on high-pressure turbine casing and low-pressure turbine casing.
Certainly, other sensors that can detect amount of deformation or detector is used with the technological scheme of alternative disformation sensor also within protection scope of the present invention.
In the present embodiment, turbine casing 50 is preferably high-pressure turbine casing as shown in Figure 2, high-pressure turbine casing comprises outer casing 501, outer shroud supports 502 and outer shroud 503, actual gap size is the spacing dimension between turbine rotor blade 6 blade tip and outer shroud 503, and disformation sensor is arranged at outer shroud and supports on 502.
Outer shroud support 502 can be more concentrated the radial-deformation embodying whole high-pressure turbine casing.Certainly, casing 501, outer shroud support on 502 and outer shroud 503 and all arrange the technological scheme of disformation sensor also within protection scope of the present invention outside.
The circumferential direction that in the present embodiment, disformation sensor supports 502 along outer shroud is uniformly distributed in outer shroud support 502.By disformation sensor circumferentially, effectively can monitor the even distortion of circumferential asymmetry because a variety of causes produces, detected radial-deformation data can embody outer shroud more abundantly, comprehensive, scientifical and support 502 and high-pressure turbine casing radial-deformation everywhere, the more effective radial clearance situation of change that detected motor, thus can more effectively gap control be carried out.
In the present embodiment, the number of disformation sensor can be 2 ~ 4, and can be uniform in circumference.Disformation sensor number can increase cost and installation difficulty too much, arranges and then cannot embody turbine casing 50 radial-deformation everywhere fully, all sidedly very little, 2 ~ 4 disformation sensors be relatively trade off, desirable number.
Certainly, use the technological scheme of the disformation sensor of other numbers also within protection scope of the present invention.
In the present embodiment, disformation sensor is resistive transducer, and disformation sensor comprises palisade resistance wire, and palisade resistance wire is pasted onto outer shroud and supports on the outer surface of 502, and the length of palisade resistance wire and cross-section area all support the distortion of 502 with outer shroud and change.
After resistive transducer detects distortion, the resistance in resistive transducer can change.This sensor have high temperature resistant, be quick on the draw, the advantage of good reliability.
Certainly, the sensor of other types is used with the technological scheme of substitutional resistance formula sensor also within protection scope of the present invention.
In the turbogenerator working procedure that the turbine casing detection device 1 adopted in above-mentioned formula in the present embodiment detects, the value of the radial-deformation of turbine casing 50 is maximum value, minimum value or the mean value in the testing result of at least two disformation sensors, is preferably maximum value or minimum value.
Can select as required to adopt one of them testing result, make actual gap size guarantee under turbine casing 50 and rotor blade 6 blade tip do not touch the prerequisite of mill little as much as possible.Such as: when needing actual gap size little as far as possible, then can select the maximum value in testing result, otherwise, when needing higher Security, the minimum value in testing result can be selected.
Certainly, testing result get other values or by the technological scheme that re-uses after testing result process also within protection scope of the present invention.
In the present embodiment, turbine rotor detection device comprises speed probe and temperature transducer, and control gear 3 is control chip, wherein:
Speed probe, for measuring tachometer value.
Temperature transducer, for measuring tempeature value.
The valve 41 that cooling fluid feedway 4 comprises cooled gas feeding mechanism, gas transmission pipeline 42 and is arranged on gas transmission pipeline 42.
The gas delivery port of gas transmission pipeline 42 is towards turbine casing 50, and valve 41 is electrically connected with control gear 3, and valve 41 increases instruction according to flow or flow reduces the size (or claiming aperture) that instruction controls gas transmission pipeline 42 conducting area in real time.
Cooling fluid is preferably cooled gas.Valve 41 can use solenoid valve, also can use other valves.The amount of the cooling fluid exporting turbine casing 50 to can be controlled by the size of the conducting area of control valve 41, and then control the amount of deformation of turbine casing 50 and the actual gap size between turbine rotor blade 6 blade tip and turbine casing 50.
Certainly, use the technological scheme of the mixture replacing cooled gas of cooling liquid or the lower gas of temperature and liquid also within protection scope of the present invention.
Certainly, it should be noted that: use other formula to substitute open or implicit this formula disclosed or use other obtaining method to obtain the technological scheme of the actual gap size in turbogenerator working procedure between turbine rotor blade 6 blade tip and turbine casing 50 all within protection scope of the present invention to substitute open or implicit this obtaining method disclosed herein herein.
Embodiment of the method:
As shown in Fig. 1 ~ Fig. 5, the clearance control method of the turbogenerator that the embodiment of the present invention provides, at least comprises the following steps:
S1, in turbogenerator working procedure, detect the radial-deformation of turbine casing 50.
S2, in turbogenerator working procedure, detect the tachometer value of turbine rotor and the temperature value of turbine exhaust.
S3, the value of radial-deformation, tachometer value and temperature value according to the original gap size between turbine rotor blade 6 blade tip during assembling and turbine casing 50, turbine casing 50 calculate the actual gap size between turbine rotor blade 6 blade tip and turbine casing 50, or, calculate target casing amount of deformation according to original gap size, target gap size, tachometer value and the temperature value between turbine rotor blade 6 blade tip during assembling and turbine casing 50.
S4, when actual gap size is greater than the CLV ceiling limit value of target gap size or when the value of the radial-deformation of described turbine casing is greater than described target casing amount of deformation, increase the flow of cooling fluid that turbine casing 50 is exported.When actual gap size is less than the lower limit of target gap size or when the value of the radial-deformation of described turbine casing is less than described target casing amount of deformation, reduce the flow to the cooling fluid that turbine casing 50 exports.
The clearance control system of the turbogenerator provided with present system embodiment in like manner, the clearance control method of the turbogenerator that the embodiment of the present invention provides at least can solve the technical problem identical with the clearance control system of the turbogenerator that present system embodiment provides, and at least produces identical technique effect.
Original actual gap size (C when can calculate rotor deformation and target gap size sum and assembling by rotor deformation model in above-mentioned steps S4 between turbine rotor blade 6 blade tip and turbine casing 50
original) between difference and target casing amount of deformation, then whether real time contrast's target casing amount of deformation is equal with the radial-deformation (the casing amount of deformation measured shown in this amount of deformation and Fig. 4) detecting the turbine casing 50 obtained, when target casing amount of deformation is greater than the radial-deformation detecting the turbine casing 50 obtained, then reduce the aperture of valve to reduce the flow to the cooling fluid that turbine casing 50 exports, otherwise, then the aperture of valve is increased to increase the flow to the cooling fluid that turbine casing 50 exports.
The method calculating the actual gap size between turbine rotor blade 6 blade tip and turbine casing 50 in the present embodiment or calculate described target casing amount of deformation comprises the following steps:
By rotor deformation model, calculate according to the material characteristic parameter (such as: Young's modulus etc.) of tachometer value and turbine rotor the amount of deformation that turbine rotor produces because of centrifugal force.
By rotor deformation model, calculate according to the material characteristic parameter (such as: expansion coefficient etc.) of temperature value and turbine rotor the radial heat distortion amount that turbine rotor produces because of thermal expansion.
According to formula C
actual=C
original+ Δ L
casing-Δ L (N)-Δ L (T
exhaust), calculate the actual gap size between turbine rotor blade 6 blade tip and turbine casing 50 in turbogenerator working procedure, or, according to formula Δ L
target casing=Δ L (N)+Δ L (T
exhaust)+C
target-C
originalcalculate described target casing amount of deformation; In formula:
C
actualfor the actual gap size in turbogenerator working procedure between turbine rotor blade 6 blade tip and turbine casing 50.
C
originalfor the original gap size between turbine rotor blade 6 blade tip during assembling and turbine casing 50.
Δ L
casingfor the value of the amount of deformation of turbine casing 50 detected in turbogenerator working procedure.
The value of the amount of deformation that Δ L (N) produces because of centrifugal force for turbine rotor in turbogenerator working procedure.
Δ L (T
exhaust) value of radial heat distortion amount that produces because of thermal expansion for turbine rotor in turbogenerator working procedure;
Δ L
target casingfor described target casing amount of deformation;
C
targetfor described target gap size.
The technique effect that this method for optimizing produces elaborates in system embodiment part, herein no longer repeat specification.
In the turbogenerator working procedure that in the present embodiment, turbine casing detection device 1 detects, the value of the radial-deformation of turbine casing 50 is maximum value, minimum value or the mean value at least two testing results.
The technique effect that the method produces elaborates in system embodiment part, herein no longer repeat specification.
No matter any device provided by the invention, module are realized by hardware, or are realized all within protection scope of the present invention by the mode that software or software restraint combine.
In addition, arbitrary technological scheme disclosed in the invention described above unless otherwise stated, if the number range of it discloses, so disclosed number range is preferred number range, anyly it should be appreciated by those skilled in the art: preferred number range is only the numerical value that in many enforceable numerical value, technique effect is obvious or representative.Because numerical value is more, cannot be exhaustive, so the present invention just discloses component values to illustrate technological scheme of the present invention, and the above-mentioned numerical value enumerated should not form the restriction to the invention protection domain.
Meanwhile, apply in arbitrary technological scheme disclosed in the invention described above for the term for position relationship or shape unless otherwise stated its implication comprise approximate with it, similar or close state or shape.
Finally should be noted that: above embodiment is only in order to illustrate that technological scheme of the present invention is not intended to limit; Although with reference to preferred embodiment to invention has been detailed description, those of ordinary skill in the field are to be understood that: still can modify to the specific embodiment of the present invention or carry out equivalent replacement to portion of techniques feature; And not departing from the spirit of technical solution of the present invention, it all should be encompassed in the middle of the technological scheme scope of request of the present invention protection.
Claims (12)
1. a clearance control system for turbogenerator, is characterized in that, comprises turbine casing detection device (1), turbine rotor detection device, control gear (3) and cooling fluid feedway (4), wherein:
Described control gear (3) is electrically connected by circuit (2) or wireless signal transceiver with described turbine casing detection device (1), described turbine rotor detection device and described cooling fluid feedway (4);
Described turbine casing detection device (1), for detecting the radial-deformation of turbine casing (50) in turbogenerator working procedure, and inputs described control gear (3) by testing result;
Described turbine rotor detection device, for detecting the tachometer value of turbine rotor and the temperature value of turbine exhaust in described turbogenerator working procedure, and inputs described control gear (3) by testing result;
Described control gear (3), for according to assembling time turbine rotor blade (6) blade tip and described turbine casing (50) between original gap size, the value of the radial-deformation of described turbine casing (50), described tachometer value and described temperature value calculate the actual gap size between described turbine rotor blade (6) blade tip and described turbine casing (50), or, for according to assembling time turbine rotor blade (6) blade tip and described turbine casing (50) between original gap size, target gap size, described tachometer value and described temperature value calculate target casing amount of deformation,
Described control gear (3), also increasing instruction for sending flow to described cooling fluid feedway (4) when described actual gap size is greater than the CLV ceiling limit value of target gap size or when the value of the radial-deformation of described turbine casing (50) is greater than described target casing amount of deformation, when described actual gap size is less than the lower limit of target gap size or when the value of the radial-deformation of described turbine casing (50) is less than described target casing amount of deformation, flow being sent to described cooling fluid feedway (4) and reducing instruction;
Described cooling fluid feedway (4), for increasing the flow to the cooling fluid that described turbine casing (50) exports after receiving described flow increase instruction, after receiving described flow minimizing instruction, reduce the flow to the cooling fluid that described turbine casing (50) exports;
Described control gear (3) comprises centrifugal deformation computing module, radial heat distortion amount computing module and difference contrast module, wherein:
Described centrifugal deformation computing module, for calculating the amount of deformation that described turbine rotor produces because of centrifugal force according to the material characteristic parameter of described tachometer value and described turbine rotor;
Described radial heat distortion amount computing module, for calculating the radial heat distortion amount that described turbine rotor produces because of thermal expansion according to the material characteristic parameter of described temperature value and described turbine rotor;
Described difference contrast module is used for according to formula C
actual=C
original+ Δ L
casing-Δ L (N)-Δ L (T
exhaust), calculate the actual gap size between turbine rotor blade (6) blade tip and described turbine casing (50) described in described turbogenerator working procedure; Or described difference contrast module is used for according to formula Δ L
target casing=Δ L (N)+Δ L (T
exhaust)+C
target-C
originalcalculate described target casing amount of deformation; In formula:
C
actualfor the actual gap size described in described turbogenerator working procedure between turbine rotor blade (6) blade tip and described turbine casing (50);
C
originalfor the original gap size between described turbine rotor blade (6) blade tip during assembling and described turbine casing (50);
Δ L
casingfor the value of the radial-deformation of turbine casing (50) in the described turbogenerator working procedure that detects in described turbogenerator working procedure;
The value of the amount of deformation that Δ L (N) produces because of centrifugal force for turbine rotor described in described turbogenerator working procedure;
Δ L (T
exhaust) value of radial heat distortion amount that produces because of thermal expansion for turbine rotor described in described turbogenerator working procedure;
Δ L
target casingfor described target casing amount of deformation;
C
targetfor described target gap size.
2. the clearance control system of turbogenerator according to claim 1, it is characterized in that, described control gear, the value of the radial heat distortion amount that value and described turbine rotor for being calculated the amount of deformation that described turbine rotor produces because of centrifugal force by rotor deformation model are produced because of thermal expansion.
3. the clearance control system of turbogenerator according to claim 1, is characterized in that, described turbine casing detection device comprises at least one disformation sensor, and described turbine casing is high-pressure turbine casing or low-pressure turbine casing.
4. the clearance control system of turbogenerator according to claim 3, it is characterized in that, described turbine casing is high-pressure turbine casing, described high-pressure turbine casing comprises outer casing, outer shroud supports and outer shroud, described actual gap size is the spacing dimension between described turbine rotor blade blade tip and described outer shroud, and described disformation sensor is arranged at described outer shroud and supports.
5. the clearance control system of turbogenerator according to claim 4, is characterized in that, described disformation sensor is uniformly distributed in described outer shroud along the circumferential direction that described outer shroud supports and supports.
6. the clearance control system of turbogenerator according to claim 5, is characterized in that, the number of described disformation sensor is 2 ~ 4.
7. the clearance control system of turbogenerator according to claim 5, it is characterized in that, described disformation sensor is resistive transducer, described disformation sensor comprises palisade resistance wire, described palisade resistance wire is pasted onto on the outer surface that described outer shroud supports, the distortion that the length of described palisade resistance wire and cross-section area all support with described outer shroud and changing.
8. according to the clearance control system of the arbitrary described turbogenerator of claim 3-7, it is characterized in that, the value calculating in the formula of the actual gap size described in described turbogenerator working procedure between turbine rotor blade (6) blade tip and described turbine casing (50) radial-deformation of turbine casing in the described turbogenerator working procedure that the described turbine casing detection device that adopts detects is maximum value, minimum value or mean value in the testing result of at least two described disformation sensors.
9. the clearance control system of turbogenerator according to claim 1, is characterized in that, described turbine rotor detection device comprises speed probe and temperature transducer, and described control gear is control chip, wherein:
Described speed probe is for measuring described tachometer value;
Described temperature transducer is for measuring described temperature value;
The valve that described cooling fluid feedway comprises cooled gas feeding mechanism, gas transmission pipeline and is arranged on described gas transmission pipeline;
The gas delivery port of described gas transmission pipeline is towards described turbine casing, described valve is electrically connected with described control gear, and described valve increases instruction according to described flow or described flow reduces the size that instruction controls the conducting area of described gas transmission pipeline in real time.
10. a clearance control method for turbogenerator, is characterized in that, at least comprises the following steps:
The radial-deformation of turbine casing is detected in turbogenerator working procedure;
The tachometer value of turbine rotor and the temperature value of turbine exhaust is detected in described turbogenerator working procedure;
The actual gap size between described turbine rotor blade blade tip and described turbine casing is calculated according to the value of the radial-deformation of the original gap size between turbine rotor blade blade tip during assembling and described turbine casing, described turbine casing, described tachometer value and described temperature value, or, calculate target casing amount of deformation according to original gap size, target gap size, described tachometer value and the described temperature value between turbine rotor blade blade tip during assembling and described turbine casing;
When described actual gap size is greater than the CLV ceiling limit value of target gap size or when the value of the radial-deformation of described turbine casing is greater than described target casing amount of deformation, increase the flow to the cooling fluid that described turbine casing exports;
When described actual gap size is less than the lower limit of target gap size or when the value of the radial-deformation of described turbine casing is less than described target casing amount of deformation, reduce the flow to the cooling fluid that described turbine casing exports.
The clearance control method of 11. turbogenerators according to claim 10, it is characterized in that, the method calculating the actual gap size between described turbine rotor blade blade tip and described turbine casing or calculate target casing amount of deformation comprises the following steps:
By rotor deformation model, calculate according to the material characteristic parameter of described tachometer value and described turbine rotor the amount of deformation that described turbine rotor produces because of centrifugal force;
By rotor deformation model, calculate according to the material characteristic parameter of described temperature value and described turbine rotor the radial heat distortion amount that described turbine rotor produces because of thermal expansion;
According to formula C
actual=C
original+ Δ L
casing-Δ L (N)-Δ L (T
exhaust), calculate the actual gap size between turbine rotor blade blade tip and described turbine casing described in described turbogenerator working procedure, or, according to formula Δ L
target casing=Δ L (N)+Δ L (T
exhaust)+C
target-C
originalcalculate described target casing amount of deformation; In formula:
C
actualfor the actual gap size described in described turbogenerator working procedure between turbine rotor blade blade tip and described turbine casing;
C
originalfor the original gap size between described turbine rotor blade blade tip during assembling and described turbine casing;
Δ L
casingfor the value of the amount of deformation of turbine casing detected in described turbogenerator working procedure;
The value of the amount of deformation that Δ L (N) produces because of centrifugal force for turbine rotor described in described turbogenerator working procedure;
Δ L (T
exhaust) value of radial heat distortion amount that produces because of thermal expansion for turbine rotor described in described turbogenerator working procedure;
Δ L
target casingfor described target casing amount of deformation;
C
targetfor described target gap size.
The clearance control method of 12. turbogenerators according to claim 10 or 11, it is characterized in that, in the described turbogenerator working procedure that turbine casing detection device detects, the value of the radial-deformation of turbine casing is maximum value, minimum value or the mean value at least two testing results.
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| CN105201562B (en) * | 2014-05-28 | 2017-07-04 | 中航商用航空发动机有限责任公司 | active clearance control method and system |
| CN104713731B (en) * | 2015-03-02 | 2017-06-13 | 南京航空航天大学 | A kind of aero-turbine active clearance controls casing model confirmatory experiment platform |
| FR3050483B1 (en) | 2016-04-26 | 2020-02-07 | Save Innovations | TURBINE FOR DRIVING WITH SPEED LIMITATION |
| CN109406114A (en) * | 2017-05-09 | 2019-03-01 | 中国航空制造技术研究院 | A kind of aeroengine rotor blade working condition checkout gear and detection method |
| US11211184B2 (en) | 2019-01-23 | 2021-12-28 | Pratt & Whitney Canada Corp. | System of harness and engine case for aircraft engine |
| CN110318823B (en) * | 2019-07-10 | 2022-07-15 | 中国航发沈阳发动机研究所 | Active clearance control method and device |
| CN112595520A (en) * | 2019-09-16 | 2021-04-02 | 中国航发商用航空发动机有限责任公司 | Gas compressor test bench and test method |
| CN111022135B (en) * | 2019-10-31 | 2022-06-07 | 中国航发南方工业有限公司 | Assembling method for controlling gap between grates of blade tips of engine power turbine |
| CN111982523B (en) * | 2020-06-30 | 2022-08-09 | 中国航发南方工业有限公司 | Exhaust test structure |
| CN111911241B (en) * | 2020-07-31 | 2022-09-20 | 中国航发沈阳发动机研究所 | Axial positioning and cooling sealing structure of guide vane |
| CN114646833B (en) * | 2022-03-23 | 2023-05-02 | 山东艾瑞得电气有限公司 | New energy inverter and application method thereof |
| CN114526161B (en) * | 2022-04-22 | 2022-07-08 | 成都中科翼能科技有限公司 | Gas turbine's intermediary machine casket and reinforcement structure thereof |
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