CN114659746A - Annular dynamic seal dynamic characteristic coefficient experiment measurement system and method - Google Patents
Annular dynamic seal dynamic characteristic coefficient experiment measurement system and method Download PDFInfo
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Abstract
The invention discloses an experimental measurement system and method for a dynamic characteristic coefficient of an annular dynamic seal, wherein the experimental measurement system comprises a dynamic seal experimental section, an air supply system, a driving system, an excitation system and a measurement system, and the dynamic characteristic coefficient related to non-contact annular dynamic seal frequency is efficiently and accurately measured and recognized in a frequency domain by providing stable harmonic excitation for a stator to enable the stator to deviate from a central position to carry out small-displacement periodic vortex motion and synchronously measuring the vortex motion displacement, the vortex acceleration and the applied excitation force of the stator. The invention can conveniently adjust the operation working condition parameters such as the air flow pressure at the sealing inlet, the rotating speed of the rotor, the inlet pre-rotation speed and the like, can also replace sealing elements with different geometric dimensions or different structural types for experiments, and provides reliable reference for the design and application of the dynamic sealing device of the turbine machinery.
Description
Technical Field
The invention belongs to the technical field of dynamic sealing of turbomachinery, and particularly relates to a system and a method for experimental measurement of dynamic characteristic coefficients of an annular dynamic seal.
Background
The annular dynamic sealing device is one of the key parts of the modern turbomachinery, and has the primary function of limiting the differential pressure flow of a working medium between a dynamic interface and a static interface of the turbomachinery, so that the influence of leakage quantity and leakage flow on a main flow is reduced, and the operation efficiency of the turbomachinery is improved. In addition, as turbomachinery develops towards high temperature, high pressure and high rotating speed, fluid exciting force induced by dynamic pressure effect in the annular dynamic seal micro channel is more and more non-negligible, and even instability of a rotor system can be caused, and safe and stable operation of turbomachinery is seriously threatened. Therefore, the research on the leakage of the annular dynamic seal and the dynamic characteristics of the rotor is deeply developed, and the method has important engineering application value for developing the modern dynamic seal technology with low leakage and high damping performance and improving the working efficiency and the operation reliability of the turbine machinery.
The non-contact annular dynamic seal applied in the field of turbomachinery comprises labyrinth seal, honeycomb/hole type damping seal, bag type damping seal and the like, and the research method of leakage and rotor dynamic characteristics mainly comprises a Bulk-Flow theory research method, a CFD numerical value calculation method and an experimental measurement method. Although the CFD numerical calculation method can predict the performance parameters of the annular dynamic seal more accurately, more experimental measurements are still required to provide reliability support for the annular dynamic seal. In the early experimental research, an impact excitation mechanical impedance method is mainly adopted to measure the effective damping, the critical rotating speed and the vibration amplitude of a rotor-bearing-sealing system, so as to analyze the influence of the dynamic sealing on the stability of a rotor system, but the method cannot obtain all sealing dynamic characteristic coefficients; the conventional common experimental device based on the unbalanced common-frequency excitation mechanical impedance method can only measure the sealing dynamic characteristic coefficient with the same frequency as the rotating speed, is not suitable for damping dynamic sealing with strong frequency correlation of the dynamic characteristic coefficient, needs a fluid exciting force amplifying device and has poor measurement precision.
At present, most annular dynamic seal experimental devices cannot measure the dynamic characteristic coefficient related to the sealing frequency, and a new annular dynamic seal dynamic characteristic coefficient experimental measurement system and method are urgently needed.
Disclosure of Invention
In order to overcome the disadvantages of the prior art, an object of the present invention is to provide a system and a method for measuring a dynamic coefficient of performance experiment of an annular dynamic seal, so as to solve one or more of the above technical problems. The method can efficiently and accurately measure and identify the dynamic characteristic coefficient related to the non-contact annular dynamic seal frequency under different operating conditions, and can provide reliable reference for the design and application of the dynamic seal device of the turbine machinery.
In order to achieve the purpose, the invention adopts the technical scheme that:
an experimental measurement system for dynamic characteristic coefficients of annular dynamic seal comprises a dynamic seal experimental section, an air supply system, a driving system, an excitation system and a measurement system; wherein:
the dynamic seal experiment section comprises a stator and a rotor which are concentrically and centrally arranged; the stator comprises a stator sleeve, a prerotation ring is arranged on an inner side assembly surface of the stator sleeve, a circumferentially-through air inlet cavity is formed between the prerotation ring and the inner side surface of the stator sleeve, and a circumferentially-through prerotation cavity is formed between the prerotation ring and the outer side surface of the rotor; a plurality of air inlets communicated with the air inlet cavity are uniformly arranged on the axial symmetrical surface of the stator sleeve along the circumferential direction; a first sealing element and a second sealing element are symmetrically arranged at two ends of the pre-rotation ring, the first sealing element and the second sealing element are matched with the inner side surface of the stator sleeve, and a small gap is formed between the first sealing element and the outer side surface of the rotor;
the gas supply system is used for supplying gas to the dynamic seal experiment section;
the driving system is used for driving the rotor to rotate at a given rotating speed;
the excitation system is used for providing stable harmonic excitation for the stator;
the measuring system is used for synchronously acquiring and recording pressure signals and electric signals measured in the experimental process.
In one embodiment, the stator is designed symmetrically, and airflow flows into the air inlet cavity from the middle part, flows into the pre-rotation cavity through the pre-rotation ring, and then flows out from gaps between the first sealing element and the second sealing element and the outer side face of the rotor to two ends along the axial direction; and two ends of the rotor respectively extend out of the first stator end cover and the second stator end cover, the two ends of the rotor are arranged on rotor supporting bearings arranged in the first bearing seat and the second bearing seat, and continuous and reliable lubricating oil gas is provided for the rotor supporting bearings by a bearing oil gas lubricating device.
In one embodiment, the air supply system comprises a shunt pipe, one end of the shunt pipe is connected with the compressor through the air storage tank, a plurality of branch pipes are arranged at the other end of the shunt pipe, each branch pipe is connected with one air inlet, a regulating valve is further arranged at the upstream of the shunt pipe, and a bypass with a bypass valve is connected.
In one embodiment, the driving system comprises a variable frequency motor, an output end of the variable frequency motor is connected with the rotor through a coupler, the variable frequency motor is connected with a computer to obtain a given rotating speed and a steering rotation control signal, and a rotating speed sensor is arranged at a free end of the variable frequency motor, so that the computer can adjust the output torque of the variable frequency motor according to the fed-back rotating speed signal, and the rotor is ensured to stably rotate at the given rotating speed.
In one embodiment, in the excitation system, a computer sends out a harmonic excitation signal, the harmonic excitation signal is amplified by a power amplifier and then is transmitted to a first vibration exciter and a second vibration exciter, and the computer can independently regulate and control frequency components of excitation force sent by the first vibration exciter and the second vibration exciter and amplitude and phase corresponding to each frequency component; the stator sleeve is fixedly provided with a first excitation rod and a second excitation rod, the first vibration exciter is rigidly connected with the first excitation rod, and the second vibration exciter is rigidly connected with the second excitation rod and is used for exciting the stator according to a received harmonic excitation signal; the first force sensor is arranged at the middle joint of the first excitation rod, and the second force sensor is arranged at the middle joint of the second excitation rod, so that a computer can adjust an output harmonic excitation signal according to a feedback excitation force signal, and a stator is ensured to be subjected to stable harmonic excitation.
In one embodiment, the first excitation rod and the second excitation rod are orthogonally arranged on an axial symmetrical surface of the stator sleeve along the radial direction of the rotor, are symmetrically arranged relative to the vertical direction, and are rigidly connected with the stator sleeve through threaded blind holes.
In one embodiment, the measurement system includes a pressure monitoring module and an electrical signal acquisition module;
the pressure monitoring module comprises a pressure sensor, a pitot tube and a static pressure leading tube; the pitot tube is arranged in the pre-rotation cavity, and the total pressure hole of the pitot tube is opposite to the tangential incoming flow direction; the static pressure leading pipe is arranged on the inner wall surface of the pre-rotation cavity; the pressure sensor measures the pressure of airflow introduced by the pitot tube and the static pressure leading tube and transmits signals to the computer for monitoring;
the electric signal acquisition module comprises a signal acquisition instrument, a first bearing temperature sensor, a second bearing temperature sensor, an air inlet temperature sensor, a first displacement sensor, a second displacement sensor, a third displacement sensor, a fourth displacement sensor, a first acceleration sensor, a second acceleration sensor, a first force sensor and a second force sensor; the bearing temperature sensor I is arranged in the bearing seat I at one end of the rotor, and the bearing temperature sensor II is arranged in the bearing seat II at the other end of the rotor; the air inlet temperature sensor is arranged in the air inlet cavity; the first displacement sensor, the second displacement sensor, the third displacement sensor and the fourth displacement sensor are fixed on the stator along the radial direction of the rotor, the first displacement sensor and the third displacement sensor are arranged in the same direction with the vibration exciting rod, and the second displacement sensor and the fourth displacement sensor are arranged in the same direction with the vibration exciting rod; the first acceleration sensor and the second acceleration sensor are fixed on the stator along the radial direction of the rotor, the first acceleration sensor and the excitation rod are arranged in the same direction, and the second acceleration sensor and the excitation rod are arranged in the same direction; the signal acquisition instrument is connected with the temperature sensor, the displacement sensor, the acceleration sensor and the force sensor, converts measured temperature, displacement, acceleration and exciting force signals into electric signals and transmits the electric signals to the computer for monitoring.
In one embodiment, the first displacement sensor and the second displacement sensor are fixed on the first stator end cover, and the third displacement sensor and the fourth displacement sensor are fixed on the second stator end cover; signals of the first displacement sensor and the third displacement sensor which are arranged along the direction of the excitation rod, and signals of the second displacement sensor and the fourth displacement sensor which are arranged along the direction of the excitation rod are respectively connected to a computer for synchronous monitoring, and the signals are used for observing whether the rotor generates torsional vibration.
The invention also provides an experimental measurement method based on the experimental measurement system for the dynamic characteristic coefficient of the annular dynamic seal, which comprises the following steps:
In the formula, RgIs the gas constant;
step 2, starting an excitation system, sending a pair of harmonic excitation signals with the same frequency components and 90-degree phase difference, and exciting a stator through an exciter; after the vortex motion track of the stator is stable, synchronously recording electric signals acquired by a measuring system, converting the electric signals into physical quantities under a frequency domain through fast Fourier transform, and separating the kinematic parameters of the stator corresponding to different vortex motion frequencies, wherein the kinematic parameters comprise vortex motion displacement D in two orthogonal excitation directions, namely an X direction and a Y directionxxAnd DxyAnd whirling acceleration AxxAnd AxyAnd the applied excitation force FexxAnd Fexy(ii) a Then a pair of harmonic excitation signals which are irrelevant to the amplitude of the harmonic excitation signals are sent out, and an excitation experiment is repeated to obtain stator vortex displacement D corresponding to different vortex frequencies in a frequency domainyxAnd DyyAnd whirling acceleration AyxAnd AyyAnd the applied excitation force FeyxAnd Feyy；
And 3, based on a small displacement vortex theory and by applying fast Fourier transform, obtaining a stator kinetic equation under a frequency domain:
in the formula, MsIs a stator quality matrix; hxxIs the direct impedance coefficient of the X-direction system, HxyIs the cross-impedance coefficient of the system in the X direction, HyyIs the direct impedance coefficient of the system in the Y direction, HyxIs the cross impedance coefficient of the system in the Y direction, and the 4 system impedance coefficients are abbreviated as Hij；
Substituting the physical quantity in the frequency domain measured in the step 2 into a formula (2) to solve to obtain a system impedance coefficient HijIncluding the bench reference impedance coefficient Hbl，ijAnd sealing impedance coefficient H of both-side sealings，ijThe seal impedance coefficient H is obtained from the formula (3)sij：
Step 4, sealing impedance coefficient Hs，ijIs defined as:
Hs，ij＝Ks，ij+j(ΩCs，ij) (9)
in the formula, Ks，ijIs the seal stiffness coefficient, representing the seal direct stiffness K in the X directions，xxX-direction seal cross stiffness Ks，xyDirect stiffness K for Y-direction seals，yyAnd Y-direction seal cross stiffness Ks，yx；Cs，ijIs the seal damping coefficient, representing the X-direction seal direct damping Cs，xxX-direction sealed cross damping Cs，xyY-direction sealing direct damping Cs，yyAnd Y-direction sealed cross damping Cs，yx(ii) a j is an imaginary unit; Ω is the rotor whirl angular frequency;
obtaining 8 dynamic characteristic coefficients of the annular dynamic seal to be measured under different vortex frequencies according to a formula (5):
in the formula, Re () and Im () represent the real part and imaginary part of a complex number, respectively.
In one embodiment, the pressure of the seal inlet airflow can be changed through a bypass valve and a regulating valve on an air supply system, the steps 1 to 4 are repeated to carry out experiments, and the influence of the inlet airflow pressure on the leakage of the annular dynamic seal and the dynamic characteristics of the rotor is researched; changing the rotating speed and the steering of the rotor by adjusting the output torque of a variable frequency motor of a driving system, repeating the steps 1 to 4 to perform experiments, and exploring the influence of the rotating speed and the steering of the rotor on the leakage of the annular dynamic seal and the dynamic characteristics of the rotor; the swirl speed of the sealing inlet is changed by replacing the pre-swirl ring with the jet holes with different angles, the steps 1 to 4 are repeated to carry out experiments, and the influence of the swirl speed of the inlet on the leakage of the annular dynamic seal and the dynamic characteristics of the rotor is explored.
In one embodiment, the experiment can be carried out by repeating the steps 1 to 4 by replacing the first sealing element and the second sealing element with different geometric dimensions, and the influence of the geometric dimensions on the leakage of the annular dynamic seal and the dynamic characteristics of the rotor is researched; and (3) replacing the first sealing element and the second sealing element with different structural types, repeating the steps 1 to 4 to perform experiments, and performing experimental research on leakage and rotor dynamic characteristics of the annular dynamic seals with different types.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides an experimental measurement system and method for dynamic characteristic coefficients of an annular dynamic seal, which are used for providing stable harmonic excitation for a stator to enable the stator to deviate from a central position to carry out small-displacement periodic vortex motion, synchronously measuring the vortex motion displacement, vortex motion acceleration and applied excitation force of the stator, realizing accurate identification of non-contact annular dynamic seal frequency-related dynamic characteristic coefficients in a frequency domain based on a small-displacement vortex motion theory and applying fast Fourier transform, and providing reliable reference for the design and application of a dynamic seal device of a turbine machine.
In the invention, the stator of the dynamic seal experimental section adopts a split design and is assembled by a stator sleeve, a stator end cover, a prerotation ring and a sealing element, the sealing elements with different structural types or different geometric dimensions can be conveniently replaced, and the dynamic sealing device can be widely applied to the research on the leakage and rotor dynamic characteristics of various non-contact annular dynamic seals (including labyrinth seals, honeycomb/hole type damping seals, bag type damping seals and the like).
In the invention, the stator of the dynamic seal experimental section adopts a symmetrical design, so that airflow flows in from the middle part of the stator and flows out from two sides of the stator, the axial thrust of the airflow is favorably balanced, and the risk of torsional vibration is reduced.
According to the invention, the plurality of air inlets are uniformly arranged along the circumferential direction of the stator sleeve and are communicated with the circumferentially-communicated air inlet cavity, so that air flow is uniformly mixed in the air inlet cavity and then flows into the pre-rotation cavity through the pre-rotation ring, and the uniformity of the sealed air inlet inflow is ensured.
In the invention, the downstream branch of the air storage tank is provided with the bypass valve, and the pressure of the air flow at the sealed inlet can be changed by jointly adjusting the bypass valve and the regulating valve on the premise of not changing the working condition of the compressor, so that the risk of surging of the compressor is reduced.
In the invention, a pair of displacement sensors which are arranged orthogonally are respectively arranged on the stator end covers at two ends of the stator, and signals of the displacement sensors in the same direction are accessed into a computer for synchronous monitoring, so that whether the rotor generates torsional vibration or not is conveniently monitored.
In the invention, the harmonic excitation signal sent by the computer can contain a plurality of frequency components, and the stator vortex displacement, vortex acceleration and the applied excitation force which are measured by the experiment can be separated into physical quantities corresponding to the frequency components in the frequency domain, so that the sealing dynamic characteristic coefficients under a plurality of frequencies can be obtained by only carrying out two excitation experiments by the experimental measurement method, and the experimental cost is effectively reduced.
According to the invention, the influences of the inlet airflow pressure, the rotor rotating speed and the inlet rotational flow speed on the dynamic seal leakage and the dynamic characteristics of the rotor can be researched by adjusting the air supply system and the driving system and replacing the pre-rotating ring.
Drawings
In order to more clearly explain the technical solution and the embodiments of the present invention, the drawings used in the description of the invention or the embodiments are briefly introduced below. It should be understood that the following drawings are illustrative of one embodiment of the present invention and should not be construed as limiting the present invention, and those skilled in the art can modify, substitute or improve the embodiment without departing from the technical principle of the present invention, thereby obtaining other drawings.
FIG. 1 is a schematic diagram of an experimental measurement system for dynamic characteristic coefficient of annular dynamic seal according to an embodiment of the present invention.
FIG. 2 is a schematic partial sectional structure diagram of a dynamic seal experimental section according to an embodiment of the invention.
Fig. 3 is a schematic structural diagram of a dynamic seal experimental section in the direction a in fig. 2.
Fig. 4 is a schematic sectional view at B-B in fig. 2.
FIG. 5 is a schematic cross-sectional view of a pre-swirl ring with different angle jet holes according to an embodiment of the invention.
Description of reference numerals:
1-a stator; 11-a stator sleeve; 12 a-stator end cover one; 12 b-stator end cover two; 13-prerotation ring; 14 a-seal one; 14 b-seal two; 15-an air inlet cavity; 16-a pre-rotation cavity; 17 a-an excitation rod I; 17 b-a second excitation rod; 18 a-inlet one; 18 b-inlet two; 18 c-inlet three; 18 d-air inlet four;
21-a compressor; 22-a gas storage tank; 23-pressure gauge; 24-a bypass valve; 25-a regulating valve; 26-a flow meter; 27-a shunt tube;
31-a variable frequency motor; 32-a rotational speed sensor; 33-a coupling; 34-a rotor; 35 a-bearing seat one; 35 b-bearing seat II; 36-bearing oil-gas lubrication device;
41-a power amplifier; 42 a-vibration exciter I; 42 b-vibration exciter two;
51-a pressure sensor; 52-Pitot tube; 53-static pressure leading pipe;
61-a signal acquisition instrument; 62 a-a first bearing temperature sensor; 62 b-bearing temperature sensor two; 63-an intake air temperature sensor; 64 a-displacement sensor one; 64 b-displacement sensor two; 64 c-displacement sensor III; 64 d-displacement sensor four; 65 a-acceleration sensor one; 65 b-acceleration sensor two; 66 a-force sensor one; 66 b-force sensor two;
7-computer.
Detailed Description
In order to more clearly illustrate the objects, technical solutions and technical advantages of the present invention, the present invention will be described in further detail below by referring to the accompanying drawings and examples. It should be understood that the embodiments described are part of the examples of the present invention, which are intended to be illustrative of the invention and should not be taken to be limiting. Other embodiments, which can be derived by one of ordinary skill in the art from the disclosed embodiments without inventive faculty, are within the scope of the invention.
Referring to fig. 1, fig. 2, fig. 3 and fig. 4, an experimental measurement system for a dynamic characteristic coefficient of an annular dynamic seal according to an embodiment of the present invention includes: the dynamic seal test system comprises a dynamic seal test section, an air supply system, a driving system, an excitation system and a measuring system.
Referring to fig. 2, the dynamic seal test section includes a stator 1 and a rotor 34. Wherein, stator 1 and rotor 34 are horizontal and concentric and central the arrangement, and rotor 34 both ends are installed respectively on the rotor support bearing that sets up in bearing frame one 35a and bearing frame two 35 b. The stator 1 adopts a split type design, comprises a stator sleeve 11, a first stator end cover 12a, a second stator end cover 12b, a pre-rotation ring 13, a first sealing element 14a and a second sealing element 14b, and is convenient to replace the pre-rotation ring 13 (see fig. 5) with jet holes at different angles to change the rotational flow speed of a sealing inlet or replace the first sealing element 14a and the second sealing element 14b to carry out experiments on annular dynamic seals with different structural types or geometric dimensions.
In the embodiment of the invention, the stator 1 adopts a symmetrical design, so that airflow flows in from the middle part and flows out from two sides of the stator 1, the axial thrust of the airflow is favorably balanced, and the risk of torsional vibration is reduced. Illustratively, a prerotation ring 13 is arranged on the inner assembling surface of the stator sleeve 11, a circumferentially through air inlet cavity 15 is arranged between the prerotation ring 13 and the inner side surface of the stator sleeve 11, and a circumferentially through prerotation cavity 16 is arranged between the prerotation ring and the outer side surface of the rotor 34. The first stator end cover 12a and the second stator end cover 12b are symmetrically arranged at two ends of the stator sleeve 11, and two ends of the rotor 34 respectively extend out of the first stator end cover 12a and the second stator end cover 12b and are arranged on rotor supporting bearings arranged in the first bearing seat 35a and the second bearing seat 35 b. The identical first sealing piece 14a and the second sealing piece 14b are symmetrically arranged at two ends of the prerotation ring 13, matched with the inner wall surface of the stator sleeve 11 and have a small gap with the outer side surface of the rotor 34.
Referring to fig. 4, in the embodiment of the present invention, a plurality of air inlets are uniformly arranged on an axial symmetric surface of the stator sleeve 11 along a circumferential direction and are communicated with the air inlet cavity 15, so that the air flow flows into the air inlet cavity 15 from a middle portion, is uniformly mixed in the air inlet cavity 15, then flows into the pre-rotation cavity 16 through the pre-rotation ring 13, ensures uniformity of the incoming flow of the sealed air, and then flows out from a gap between the first sealing element 14a and the second sealing element 14b and the outer side surface of the rotor 34 along the axial direction to two ends. Illustratively, the number of the air inlets of the present embodiment is 4, namely, an air inlet one 18a, an air inlet two 18b, an air inlet three 18c and an air inlet four 18 d.
In addition, the first excitation rod 17a and the second excitation rod 17b are orthogonally arranged on an axial symmetrical surface of the stator sleeve 11 along the radial direction of the rotor 34, are symmetrically arranged relative to the vertical direction, and are rigidly connected with the stator sleeve 11 through threaded blind holes; the X-axis is defined along the first excitation rod 17a and the Y-axis is defined along the second excitation rod 17 b.
The air supply system is used for supplying air to the dynamic seal experiment section, and in the embodiment of the invention, the air supply system comprises a compressor 21, an air storage tank 22 and a shunt pipe 27 which are sequentially communicated, and a bypass at the downstream of the air storage tank 22, wherein a pressure gauge 23 is arranged on the air storage tank 22 and is used for monitoring the pressure in the air storage tank 22. A bypass valve 24 is bypassed downstream of the reservoir 22. The shunt pipe 27 is provided with a regulating valve 25 and a flow meter 26 upstream, and the flow meter 26 is used for measuring the mass flow of the gas flow flowing into the dynamic seal experiment section. The end of the shunt pipe 27 is provided with a plurality of branches, each branch is connected with one air inlet, namely, each branch of the shunt pipe 27 is respectively communicated with the air inlets 18a to 18d on the stator sleeve 11, and dry air flow with stable pressure is provided for the dynamic seal experiment section. By adjusting bypass valve 24 and regulating valve 25 together, the seal inlet flow pressure can be varied without changing the operating conditions of compressor 21, reducing the risk of compressor 21 surge.
The driving system is used for driving the rotor 34 to rotate at a given rotating speed, and in the embodiment of the invention, the driving system comprises a computer 7, a variable frequency motor 31, a rotating speed sensor 32, a coupling 33, a first bearing seat 35a, a second bearing seat 35b and a bearing oil-gas lubricating device 36. The output end of the variable frequency motor 31 is connected with a rotor 34 through a coupling 33, and the rotor 34 is driven to rotate at the rotating speed and the rotating direction which are given by the computer 7. The rotating speed sensor 32 is arranged at the free end of the variable frequency motor 31 and used for measuring the rotating speed of the rotor and feeding back a rotating speed signal to the computer 7, and the computer 7 can adjust the output torque of the variable frequency motor 31 according to the feedback signal to ensure that the rotor 34 rotates stably at a given rotating speed. The first bearing seat 35a and the second bearing seat 35b are used for mounting a rotor supporting bearing. The bearing oil-air lubrication device 36 is used for providing continuous and reliable lubrication oil-air for the bearing.
The excitation system is used to provide stable harmonic excitation for the stator 1 and in an embodiment of the invention comprises a computer 7, a power amplifier 41, a first exciter 42a, a second exciter 42b, a first force sensor 66a and a second force sensor 66 b. The computer 7 sends out a harmonic excitation signal, the harmonic excitation signal is amplified by the power amplifier 41 and then transmitted to the first vibration exciter 42a and the second vibration exciter 42b, and the computer 7 can independently regulate and control the frequency components of the exciting force sent by the first vibration exciter 42a and the second vibration exciter 42b and the amplitude and the phase corresponding to each frequency component. The first vibration exciter 42a and the second vibration exciter 42b are respectively and rigidly connected with a first excitation rod 17a and a second excitation rod 17b which are fixed on the stator sleeve 11, and the stator 1 is excited according to the received harmonic excitation signal, so that the stator 1 deviates from the central position to carry out small-displacement periodic vortex motion. The first force sensor 66a and the second force sensor 66b are respectively arranged at the middle connection part of the first excitation rod 17a and the second excitation rod 17b and are used for measuring the excitation force applied to the stator 1 and feeding back the excitation force signal to the computer 7. The computer 7 can adjust the output harmonic excitation signal according to the feedback excitation force signal, and ensure that the stator 1 is stably excited by harmonic.
The measuring system is used for synchronously acquiring and recording pressure signals and electric signals measured in the experimental process, and in the embodiment of the invention, the measuring system comprises a computer 7, a pressure monitoring module and an electric signal acquisition module.
Illustratively, the pressure monitoring module includes a pressure sensor 51, a pitot tube 52, and a static pressure impulse tube 53. The pitot tube 52 is arranged in the pre-rotation cavity 16, and the total pressure hole of the pitot tube is opposite to the tangential incoming flow direction and used for measuring the total static pressure of the airflow at the sealing inlet and calculating the rotational flow speed of the sealing inlet. The static pressure leading pipe 53 is arranged on the inner wall surface of the pre-screwing cavity 16 and is used for measuring the static pressure in the sealed inlet cavity. The pressure sensor 51 is used for measuring the pressure of the airflow introduced by the pitot tube 52 and the static pressure leading tube 53 and transmitting a pressure signal to the computer 7 for monitoring.
Illustratively, the electric signal acquisition module comprises a signal acquisition instrument 61, a first bearing temperature sensor 62a, a second bearing temperature sensor 62b, an intake air temperature sensor 63, a first displacement sensor 64a, a second displacement sensor 64b, a third displacement sensor 64c, a fourth displacement sensor 64d, a first acceleration sensor 65a, a second acceleration sensor 65b, a first force sensor 66a and a second force sensor 66 b. The first bearing temperature sensor 62a and the second bearing temperature sensor 62b are respectively arranged inside the first bearing seat 35a and the second bearing seat 35b and used for monitoring the temperature of the bearing; an inlet air temperature sensor 63 is disposed within the inlet chamber 15 for measuring the sealed inlet airflow temperature. The first displacement sensor 64a, the second displacement sensor 64b, the third displacement sensor 64c and the fourth displacement sensor 64d are fixed on the stator 1 along the radial direction of the rotor 34, the first displacement sensor 64a and the third displacement sensor 64c are arranged in the same direction as the first excitation rod 17a, and the second displacement sensor 64b and the fourth displacement sensor 64d are arranged in the same direction as the second excitation rod 17 b. Specifically, the first displacement sensor 64a and the second displacement sensor 64b are arranged on the first stator end cover 12a along the radial direction of the rotor 34 and are arranged in parallel with the X axis and the Y axis respectively, and are used for measuring the vortex displacement of the first sealing element 14a relative to the rotor 34 along the excitation direction; the third displacement sensor 64c and the fourth displacement sensor 64d are arranged on the second stator end cover 12b in the radial direction of the rotor 34 and are arranged in parallel with the X axis and the Y axis respectively, and are used for measuring the whirling displacement of the second sealing element 14b relative to the rotor 34 in the excitation direction. The first acceleration sensor 65a and the second acceleration sensor 65b are fixed on the stator 1 along the radial direction of the rotor 34, and specifically, arranged on the stator sleeve 11 in a collinear manner with the X axis and the Y axis respectively, that is, the first acceleration sensor 65a is arranged in the same direction as the first excitation rod 17a, and the second acceleration sensor 65b is arranged in the same direction as the second excitation rod 17b, and is used for measuring the whirling acceleration of the stator 1 along the excitation direction. The first force sensor 66a and the second force sensor 66b are respectively arranged at the connecting position between the first excitation rod 17a and the second excitation rod 17b and used for measuring the excitation force applied to the stator 1.
The signal acquisition instrument 61 is used for acquiring temperature, displacement, acceleration and excitation force signals measured by the first bearing temperature sensor 62a, the second bearing temperature sensor 62b, the intake air temperature sensor 63, the first displacement sensor 64a, the second displacement sensor 64b, the third displacement sensor 64c, the fourth displacement sensor 64d, the first acceleration sensor 65a, the second acceleration sensor 65b, the first force sensor 66a and the second force sensor 66b, converting the temperature, the displacement, the acceleration and the excitation force signals into electric signals, and connecting the electric signals to the computer 7 for synchronous monitoring and recording.
In the embodiment of the invention, signals of the first displacement sensor 64a and the third displacement sensor 64c arranged along the X-axis direction and signals of the second displacement sensor 64b and the fourth displacement sensor 64d arranged along the Y-axis direction are respectively connected to the computer 7 for synchronous monitoring, so that whether the rotor 34 generates torsional vibration can be conveniently monitored.
Based on the annular dynamic seal dynamic characteristic coefficient experimental measurement system, the experimental measurement method comprises the following steps:
In the formula, RgIs the gas constant;
step 2, starting an excitation system, and sending a pair of harmonic excitation signals with the same frequency components and 90-degree phase difference through a computer 7 to enable a first vibration exciter 42a and a second vibration exciter 42b to excite the stator 1, so that the stator 1 deviates from the central position to perform small-displacement periodic vortex motion; after the vortex motion track of the stator 1 is stabilized, the computer 7 is used for synchronously recording the electric signals acquired by each sensor, and the electric signals are converted into physical quantities in a frequency domain by using fast Fourier transform to separate different vortex motion frequenciesKinematic parameters of stator 1 corresponding to rate, including vortex displacement D of stator 1xxAnd DxyWhirling acceleration AxxAnd AxyAnd the applied excitation force FexxAnd Fexy(ii) a A pair of harmonic excitation signals which are irrelevant to the amplitude of the harmonic excitation signals are sent out by a computer 7, and an excitation experiment is repeated to obtain the vortex displacement D of the stator 1 corresponding to different vortex frequencies in a frequency domainyxAnd DyyWhirling acceleration AyxAnd AyyAnd the applied excitation force FeyxAnd Feyy；
And 3, based on a small displacement vortex theory and by applying fast Fourier transform, obtaining a stator kinetic equation under a frequency domain:
in the formula, MsIs a stator quality matrix; hxxIs the direct impedance coefficient of the system in the X direction, HxyIs the cross-impedance coefficient of the system in the X direction, HyyIs the direct impedance coefficient of the system in the Y direction, HyxIs the cross impedance coefficient of the system in the Y direction, and the 4 system impedance coefficients are abbreviated as Hij；
Substituting the physical quantity in the frequency domain measured in the step 2 into the formula (2) to obtain the system impedance coefficient HijIncluding the reference impedance coefficient H of the experiment tablebl，ijAnd sealing impedance coefficient H of both-side sealings，ijThe sealing resistance coefficient H can be obtained from the formula (3)s，ij：
Step 4, sealing impedance coefficient Hs，ijIs defined as:
Hs，ij＝Ks，ij+j(ΩCs，ij) (14)
in the formula, Ks，ijIs the seal stiffness coefficient, representing the direct seal stiffness K in the X directions，xxX-direction seal cross stiffness Ks，xyDirect stiffness K for Y-direction seals，yyAnd Y-direction seal cross stiffness Ks，yx；Cs，ijIs the seal damping coefficient, representing the X-direction seal direct damping Cs，xxX-direction sealed cross damping Cs，xyY-direction sealing direct damping Cs，yyAnd Y-direction seal cross damping Cs，yx(ii) a j is an imaginary unit; Ω is the rotor whirl angular frequency;
then, 8 dynamic characteristic coefficients of the annular dynamic seal to be measured at different vortex frequencies can be obtained from the formula (5):
in the formula, Re () and Im () denote a real part and an imaginary part of a complex number, respectively.
Step 5, researching the influence of the operation condition: the pressure of the seal inlet airflow is changed by jointly adjusting the bypass valve 24 and the adjusting valve 25, the steps 1 to 4 are repeated to carry out experiments, and the influence of the inlet airflow pressure on the annular dynamic seal leakage and the rotor dynamic characteristic is researched; the rotating speed and the steering of the rotor are changed by adjusting the output torque of the variable frequency motor 31, the steps 1 to 4 are repeated to carry out experiments, and the influence of the rotating speed and the steering of the rotor on the leakage of the annular dynamic seal and the dynamic characteristic of the rotor is researched; the rotational flow speed of the sealed inlet is changed by replacing the pre-rotating ring 13 with the jet holes with different angles, the steps 1 to 4 are repeated to carry out experiments, and the influence of the rotational flow speed of the inlet on the annular dynamic seal leakage and the dynamic characteristics of the rotor is explored.
Step 6, structural parameter research: replacing a first sealing element 14a and a second sealing element 14b with different geometric dimensions, repeating the steps 1 to 4 to perform experiments, and researching the influence of the geometric dimensions on the leakage of the annular dynamic seal and the dynamic characteristics of the rotor; and (3) replacing the first sealing element 14a and the second sealing element 14b with different structural types (such as labyrinth seal, honeycomb/hole type damping seal, bag type damping seal and the like), repeating the steps 1 to 4 to perform experiments, and performing experimental study on leakage and rotor dynamic characteristics of different types of annular dynamic seals.
In conclusion, the invention provides an experimental measurement system and method for dynamic characteristic coefficients of annular dynamic seals, which can efficiently and accurately measure and identify the dynamic characteristic coefficients related to non-contact annular dynamic seal frequencies under different operating conditions. The experimental measurement system comprises a dynamic seal experimental section, an air supply system, a driving system, an excitation system and a measurement system, wherein the air supply system is used for providing dry air flow with stable pressure for the dynamic seal experimental section, the driving system is used for providing power required by rotation at a given rotating speed for a rotor, the excitation system is used for providing stable harmonic excitation for a stator so that the stator deviates from a central position to carry out small-displacement periodic vortex motion, and the measurement system is used for synchronously acquiring and recording vortex motion displacement, vortex acceleration and applied exciting force of the stator. Based on the experimental measurement method, the sealing dynamic characteristic coefficients under multiple frequencies can be obtained only by performing two excitation experiments, and the experimental cost is effectively reduced. In addition, the invention not only can conveniently adjust the operation working condition parameters such as the air flow pressure at the sealing inlet, the rotating speed of the rotor, the inlet prerotation speed and the like, but also can replace sealing elements with different geometric dimensions or different structural types for experiments, thereby providing reliable reference for the design and application of the dynamic sealing device of the turbine machinery.
The above examples are only for illustrating the technical solutions of the present invention and are not to be construed as limiting the present invention. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can make various changes, substitutions and alterations herein without departing from the spirit and scope of the invention.
Claims (10)
1. An experimental measurement system for dynamic characteristic coefficients of annular dynamic seals is characterized by comprising a dynamic seal experimental section, an air supply system, a driving system, an excitation system and a measurement system; wherein:
the dynamic seal experiment section comprises a stator (1) and a rotor (34), wherein the stator (1) and the rotor (34) are concentrically arranged in the center; the stator (1) comprises a stator sleeve (11), a prerotation ring (13) is arranged on an inner side assembly surface of the stator sleeve (11), a circumferentially-through air inlet cavity (15) is formed between the prerotation ring (13) and the inner side surface of the stator sleeve (11), and a circumferentially-through prerotation cavity (16) is formed between the prerotation ring and the outer side surface of the rotor (34); a plurality of air inlets communicated with the air inlet cavity (15) are uniformly arranged on the axial symmetrical surface of the stator sleeve (11) along the circumferential direction; a first sealing element (14a) and a second sealing element (14b) are symmetrically arranged at two ends of the prerotation ring (13), the first sealing element (14a) and the second sealing element (14b) are matched with the inner side surface of the stator sleeve (11), and a small gap is formed between the first sealing element (14a) and the outer side surface of the rotor (34);
the gas supply system is used for supplying gas to the dynamic seal experiment section;
the drive system is used for driving the rotor (34) to rotate at a given rotating speed;
the excitation system is used for providing stable harmonic excitation for the stator (1);
the measuring system is used for synchronously acquiring and recording pressure signals and electric signals measured in the experimental process.
2. The experimental measurement system for the dynamic characteristic coefficient of the annular dynamic seal according to claim 1, characterized in that the stator (1) is designed symmetrically, and the air flow flows into the air inlet cavity (15) from the middle part, flows into the pre-rotation cavity (16) through the pre-rotation ring (13), and then flows out from the gaps between the first sealing element (14a) and the second sealing element (14b) and the outer side surface of the rotor (34) to the two ends along the axial direction; stator sleeve (11) both ends set up stator end cover one (12a) and stator end cover two (12b) respectively, rotor (34) both ends are stretched out from stator end cover one (12a) and stator end cover two (12b) respectively, install on the rotor support bearing that sets up in bearing frame one (35a) and bearing frame two (35b) to use bearing oil gas lubricating arrangement (36) to provide continuous reliable lubricated oil gas for rotor support bearing.
3. The annular dynamic seal dynamic characteristic coefficient experiment measurement system according to claim 1, wherein the air supply system comprises a shunt pipe (27), one end of the shunt pipe (27) is connected with the compressor (21) through the air storage tank (22), the other end of the shunt pipe is provided with a plurality of branches, each branch is connected with one air inlet, and the upstream of the shunt pipe (27) is further provided with a regulating valve (25) and is connected with a bypass valve (24).
4. The experimental measurement system for the dynamic characteristic coefficient of the annular dynamic seal according to claim 1, wherein the driving system comprises a variable frequency motor (31), the output end of the variable frequency motor (31) is connected with the rotor (34) through a coupler (33), the variable frequency motor (31) is connected with a computer (7) to obtain a given rotating speed and steering rotation control signal, and a rotating speed sensor (32) is arranged at the free end of the variable frequency motor (31) so that the computer (7) can adjust the output torque of the variable frequency motor (31) according to the fed-back rotating speed signal to ensure that the rotor (34) rotates stably at the given rotating speed.
5. The experimental measurement system for the dynamic characteristic coefficient of the annular dynamic seal according to claim 1, wherein in the excitation system, a computer (7) sends out a harmonic excitation signal, the harmonic excitation signal is amplified by a power amplifier (41) and then transmitted to a first vibration exciter (42a) and a second vibration exciter (42b), and the computer (7) independently regulates and controls frequency components of an excitation force sent by the first vibration exciter (42a) and the second vibration exciter (42b) and amplitudes and phases corresponding to the frequency components; a first excitation rod (17a) and a second excitation rod (17b) are fixed on the stator sleeve (11), the first vibration exciter (42a) is rigidly connected with the first excitation rod (17a), the second vibration exciter (42b) is rigidly connected with the second excitation rod (17b), and the stator (1) is excited according to a received harmonic excitation signal; the middle connection part of the first excitation rod (17a) is provided with a first force sensor (66a), and the middle connection part of the second excitation rod (17b) is provided with a second force sensor (66b), so that the computer (7) can adjust the output harmonic excitation signal according to the feedback excitation force signal, and the stator (1) is ensured to be subjected to stable harmonic excitation.
6. The experimental measurement system for the dynamic characteristic coefficient of the annular dynamic seal is characterized in that the excitation rod I (17a) and the excitation rod II (17b) are orthogonally arranged on an axial symmetrical plane of the stator sleeve (11) along the radial direction of the rotor (34), are symmetrically arranged relative to the vertical direction, and are rigidly connected with the stator sleeve (11) through threaded blind holes.
7. The experimental measuring system for the dynamic characteristic coefficient of the annular dynamic seal according to claim 1, which comprises a pressure monitoring module and an electric signal acquisition module;
the pressure monitoring module comprises a pressure sensor (51), a pitot tube (52) and a static pressure leading tube (53); the pitot tube (52) is arranged in the pre-rotation cavity (16), and the total pressure hole of the pitot tube is opposite to the tangential incoming flow direction; the static pressure leading pipe (53) is arranged on the inner wall surface of the pre-rotation cavity (16); the pressure sensor (51) measures the pressure of airflow introduced by a pitot tube (52) and a static pressure leading tube (53), and transmits signals to the computer (7) for monitoring;
the electric signal acquisition module comprises a signal acquisition instrument (61), a first bearing temperature sensor (62a), a second bearing temperature sensor (62b), an air inlet temperature sensor (63), a first displacement sensor (64a), a second displacement sensor (64b), a third displacement sensor (64c), a fourth displacement sensor (64d), a first acceleration sensor (65a), a second acceleration sensor (65b), a first force sensor (66a) and a second force sensor (66 b); the first bearing temperature sensor (62a) is arranged in a first bearing seat (35a) at one end of the rotor (34), and the second bearing temperature sensor (62b) is arranged in a second bearing seat (35b) at the other end of the rotor (34); the air inlet temperature sensor (63) is arranged in the air inlet cavity (15); the first displacement sensor (64a), the second displacement sensor (64b), the third displacement sensor (64c) and the fourth displacement sensor (64d) are fixed on the stator (1) along the radial direction of the rotor (34), the first displacement sensor (64a) and the third displacement sensor (64c) are arranged in the same direction as the first excitation rod (17a), and the second displacement sensor (64b) and the fourth displacement sensor (64d) are arranged in the same direction as the second excitation rod (17 b); the first acceleration sensor (65a) and the second acceleration sensor (65b) are fixed on the stator (1) along the radial direction of the rotor (34), the first acceleration sensor (65a) and the first excitation rod (17a) are arranged in the same direction, and the second acceleration sensor (65b) and the second excitation rod (17b) are arranged in the same direction; the signal acquisition instrument (61) is connected with the temperature sensor, the displacement sensor, the acceleration sensor and the force sensor, converts measured temperature, displacement, acceleration and exciting force signals into electric signals and transmits the electric signals to the computer (7) for monitoring.
8. The experimental annular dynamic seal coefficient of dynamic characteristics measurement system of claim 7, wherein the first displacement sensor (64a) and the second displacement sensor (64b) are fixed on the first stator end cover (12a), and the third displacement sensor (64c) and the fourth displacement sensor (64d) are fixed on the second stator end cover (12 b); signals of a first displacement sensor (64a) and a third displacement sensor (64c) which are arranged along the direction of the first excitation rod (17a) and signals of a second displacement sensor (64b) and a fourth displacement sensor (64d) which are arranged along the direction of the second excitation rod (17b) are respectively connected to a computer (7) for synchronous monitoring, and the signals are used for observing whether the rotor (34) generates torsional vibration.
9. An experimental measurement method for dynamic characteristic coefficients of annular dynamic seals is characterized in that the experimental measurement system for the dynamic characteristic coefficients of annular dynamic seals based on the experimental measurement system for the dynamic characteristic coefficients of annular dynamic seals of claim 1 comprises the following steps:
step 1, starting a measuring system, a driving system and an air supply system in sequence, adjusting the rotating speed of a rotor and the pressure of a sealed inlet airflow to a test working condition, ensuring stability, and recording the mass flow of the airflow flowing into a dynamic seal experimental section and the temperature T of the sealed inlet airflowinTotal pressure P of air flow at sealed inletinAnd static pressure PsAnd calculating by formula (1) to obtain the rotational flow velocity W of the sealed inletin：
In the formula, RgIs the gas constant;
step 2, starting an excitation system, sending a pair of harmonic excitation signals with the same frequency components and 90-degree phase difference, and exciting the stator (1) through a vibration exciter; after the vortex motion track of the stator (1) is stable, synchronously recording the electric signals acquired by the measuring system, converting the electric signals into physical quantities under a frequency domain through fast Fourier transform, and separating the kinematic parameters of the stator (1) corresponding to different vortex motion frequencies, wherein the kinematic parameters comprise two orthogonal excitation directions, namely the X directionAnd a whirling displacement D in the Y directionxxAnd DxyWhirling acceleration AxxAnd AxyAnd the applied excitation force FexxAnd Fexy(ii) a Then a pair of harmonic excitation signals which are irrelevant to the amplitude of the harmonic excitation signals are sent out, and an excitation experiment is repeated to obtain the vortex displacement D of the stator (1) corresponding to different vortex frequencies in the frequency domainyxAnd DyyWhirling acceleration AyxAnd AyyAnd the applied excitation force FeyxAnd Feyy；
And 3, based on a small displacement vortex motion theory and by applying fast Fourier transform, obtaining a stator kinetic equation in a frequency domain:
in the formula, MsIs a stator quality matrix; hxxIs the direct impedance coefficient of the system in the X direction, HxyIs the cross-impedance coefficient of the system in the X direction, HyyIs the direct impedance coefficient of the system in the Y direction, HyxIs the cross impedance coefficient of the system in the Y direction, and the 4 system impedance coefficients are abbreviated as Hij；
Substituting the physical quantity in the frequency domain measured in the step 2 into a formula (2) to solve to obtain a system impedance coefficient HijIncluding the bench reference impedance coefficient Hbl,ijAnd sealing impedance coefficient H of both-side sealings,ijThe seal impedance coefficient H is obtained from the formula (3)s,ij：
Step 4, sealing impedance coefficient Hs,ijIs defined as:
Hs,ij＝Ks,ij+j(ΩCs,ij) (4)
in the formula, Ks,ijIs the seal stiffness coefficient, representing the direct seal stiffness K in the X directions,xxX-direction seal cross stiffness Ks,xyDirect stiffness K for Y-direction seals,yyAnd Y-direction seal cross stiffness Ks,yx；Cs,ijIs the seal damping coefficient, representing the X-direction seal direct damping Cs,xxX-direction sealed cross damping Cs,xyY-direction sealing direct damping Cs,yyAnd Y-direction sealed cross damping Cs,yx(ii) a j is an imaginary unit; Ω is the rotor whirl angular frequency;
obtaining 8 dynamic characteristic coefficients of the annular dynamic seal to be measured under different vortex frequencies according to a formula (5):
in the formula, Re () and Im () denote a real part and an imaginary part of a complex number, respectively.
10. The experimental measurement method for the dynamic characteristic coefficient of the annular dynamic seal according to claim 9, wherein the pressure of the inlet airflow of the seal is changed through a bypass valve (24) and a regulating valve (25) on an air supply system, the experiment from step 1 to step 4 is repeated, and the influence of the pressure of the inlet airflow on the leakage of the annular dynamic seal and the dynamic characteristic of a rotor is researched; changing the rotating speed and the steering of the rotor by adjusting the output torque of a variable frequency motor (31) of a driving system, repeating the steps 1 to 4 to perform experiments, and exploring the influence of the rotating speed and the steering of the rotor on the leakage of the annular dynamic seal and the dynamic characteristic of the rotor; changing the rotational flow speed of a sealing inlet by replacing a pre-rotating ring (13) with jet holes with different angles, repeating the steps 1 to 4 to perform experiments, and exploring the influence of the rotational flow speed of the inlet on the annular dynamic sealing leakage and the dynamic characteristics of a rotor;
the method comprises the following steps of (1) repeating the steps (1) to (4) to carry out experiments by replacing a first sealing element (14a) and a second sealing element (14b) with different geometric dimensions, and researching the influence of the geometric dimensions on annular dynamic seal leakage and rotor dynamic characteristics; and (3) replacing the first sealing element (14a) and the second sealing element (14b) with different structural types, repeating the steps 1 to 4 to perform experiments, and performing experimental study on leakage and rotor dynamic characteristics of different types of annular dynamic seals.
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