CN114878853A - Rotating speed signal generation and measurement method with key phase function based on blade tip timing - Google Patents
Rotating speed signal generation and measurement method with key phase function based on blade tip timing Download PDFInfo
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Abstract
The application belongs to the field of aeroengines, and particularly relates to a rotating speed signal generation and measurement method with a key phase function based on blade tip timing. One blade of the engine blades is subjected to non-reflective treatment, and the rest N are r 1, carrying out light reflection treatment on the blades; receiving a reflection signal when a reflection processing blade passes by the sensor through the sensor, converting the reflection signal into a pulse signal, and outputting the pulse signal; acquiring a time difference delta t between adjacent pulse signals; time difference delta t between pulse signals of two light reflection processing blades on two sides of non-light reflection processing blade 0 The time difference between the pulse signals of two adjacent light reflecting processing blades is larger than the time difference between the pulse signals of two adjacent light reflecting processing blades, and the pulse signals delta t of the two light reflecting processing blades at the two sides of the non-light reflecting processing blade are judged 0 Based on Δ t 0 Outputs a rotational speed signal with a key phase function.
Description
Technical Field
The application belongs to the field of aeroengines, and particularly relates to a rotating speed signal generation and measurement method with a key phase function based on blade tip timing.
Background
The vibration test, the pulsating pressure test, the dynamic stress test and the non-contact rotor part vibration test of the aero-engine are important marks for evaluating the stable operation safety of the aero-engine. The aircraft engine monitoring system monitors vibration of an engine, structural component vibration, pressure pulsation and the rotating speed of a rotor through sensors mounted at multiple positions of the engine. The three elements of the dynamic signal are amplitude, frequency and phase, and the three components jointly form all the characteristics of the signal.
At present, the vibration amplitude and frequency characteristics of a rotor are generally monitored in the vibration monitoring process of an aeroengine, important information of a phase is ignored, and 33% of information is lost to some extent. Common engine vibration fault reasons comprise excessive rotor unbalance, misalignment of a rotor, rubbing, local resonance, rotor cavity oil, rotor thermal bending and the like, wherein most vibration fault frequency domain characteristics are extremely similar and cannot be effectively identified only through frequency spectrum characteristics, but obvious differences exist in phase characteristics, so that the physical significance of vibration phase characteristic reflection is great, and the method is particularly applied to the field of engine vibration fault diagnosis methods.
According to statistics, the unbalance faults of the rotor of the aircraft engine account for more than 80% of vibration, the dynamic unbalance of the rotor is controlled by a low-speed process balance method mostly adopted by domestic aircraft engines so as to achieve the purpose of inhibiting vibration response in the whole machine test process, most of the rotors can realize the purpose of vibration control through the method, but the problem that the vibration response of the whole machine is larger due to the fact that the dynamic unbalance of the rotor is overlarge in the whole machine test process still exists, and therefore the vibration response of the rotor must be inhibited by adopting a local balance mode to serve as a follow-up supplementary means of process balance. In the process of carrying out local balance by adopting an influence coefficient method, vibration phase testing is necessary work and is not necessary. The precondition of the vibration phase test is stable rotating speed signal acquisition with a key phase function. The rotating speed signal acquisition method with the key phase function has important engineering significance.
In the relevant work of aero-engine tests such as a pressure pulsation test, a non-contact blade vibration test and the like, rotor blades in a high-speed rotating state are defined, fault positions are quickly positioned, vibration phase continuity between the blades in the rotating state is analyzed, and rotating speed signal key phase reference which is not movable relative to a rotating shaft is needed. The rotating speed signal acquisition method with the key phase function has important engineering significance.
The vibration phase testing of the aircraft engine at the present stage mainly comprises two measures, one measure is that a magnetic steel sensor is installed through a rotor part, in the rotating process of a rotor, an electric pulse signal generated by an induction coil of a stator part is used as a key phase reference (as shown in figure 1), a sensor and an induction coil need to be additionally installed on the rotor, a magnetic induction sensor is additionally installed on an adjacent stator, a rotating speed pulse signal is generated every time the aircraft engine rotates for one circle, the pulse signal position represents the initial position of every circle of the rotating shaft, and the initial position is determined by the physical position of the rotating speed magnetic steel sensor installed on the rotating shaft; the other is that a 'high tooth' or a 'low tooth' is designed at a speed measuring gear of a rotor of the engine, when the testing gear rotates along with a rotating shaft of the engine, teeth on the speed measuring gear sequentially rotate to sweep the eddy current sensor, and because the 'high tooth' or the 'low tooth' has difference relative to the amplitude of a voltage signal generated by unmodified common teeth, a rotating speed signal with a key phase function is obtained by identifying the difference of the voltage amplitude and counting the number of signals generated by the rotating speed teeth (as shown in fig. 2). The initial pulse signals obtained by the two are further demodulated by a signal conditioner at the rear end.
1. Technical aspects
a) The magnetic steel key phase test technology is additionally arranged on the rotating shaft, because the magnetic steel is small in size, poor in magnetism and strong in material brittleness, the quality of an electric signal generated by coil induction is weak, the influence of vortex motion of an engine rotor is simultaneously caused, a blind spot can be brought when a stator coil is far away from the pole of the magnetic steel, the signal is further attenuated, the rear end is extremely difficult to condition, the effective working time of a magnetic steel sensor is short, the requirement on the working environment is high, and the magnetic steel key phase test technology cannot work for a long time due to fast heating and degaussing. Because the diameter of the induction coil cable wound around the stator is very small, the induction coil cable is frequently broken due to improper installation and vibration fatigue factors in the use process, and the test success rate is low. Limited by the compact structure of the aircraft engine, it is difficult to find a sufficient position to install the magnetic steel sensor transceiver component. Because the sensor is additionally arranged on the rotating shaft, the rotating shaft is provided with a hole and a groove, the rotor structure is damaged, and the service life of the structural part is shortened. The magnetic steel sensor is influenced by the dynamic performance of the electromagnetic element device by the rotating speed pulse generated by induction, and the response speed is low. The sensor is additionally arranged on the rotating shaft, so that risks are brought to the structural safety of the engine.
b) The high-low tooth key phase testing technology is influenced by axial force and axial vibration of a rotor, a speed measuring gear is axially supported along with a rotating shaft of an engine, voltage amplitudes generated by the speed measuring gear and an eddy current sensor are variable under different rotating speeds and pneumatic working states, a proper threshold trigger voltage needs to be changed continuously to position high-low tooth signals, and the testing success rate is also low. The axial scraping causes the high teeth to collide with the probe of the rotating speed sensor for many times, the working state of hardware and the test result are adversely affected, and the test success rate is also low. The test method is limited by the dynamic characteristic of the eddy current sensor, a rotating speed signal (sine) generated by the eddy current needs to be further conditioned, the response speed is low, the test error of the key phase position caused by the key phase threshold value algorithm processing characteristic, the conditioning time lag characteristic and the dynamic characteristic of the sensor is large, and the rotating speed fluctuates, so that the test success rate is low.
2. Aspect of cost
Adopt magnet steel key phase test technique to need carry out a large amount of structure repacking to aeroengine rotor, stator, include: the rotor needs to be perforated at the comb teeth to ensure the installation of magnetic steel, the stator needs to be cut into a certain structure to wind the magnetic induction coil, and meanwhile, the lead is ensured by perforating all the stator parts on the lead path. The structure of the rotating shaft near the sensor mounting structure is damaged, so that the rotating shaft with the value of millions cannot be reused or the service life is reduced. In a word, the time cost and the hardware loss cost of the structural modification are large.
The high-tooth-key phase testing scheme brings the test safety risk of collision and abrasion of the rotating and static parts, the testing success rate is low, and additional test run cost is brought by repeated testing.
3. Aspect of efficiency
The existing rotating speed testing scheme with the key phase function needs to carry out complex modification on a rotor structure, effective maintenance and modification can not be carried out on the modification in an assembly completion state, the processing time of the modified structure is long, and when the test fails, only the modification measures can be added again through the engine platform decomposition, so that the efficiency is low.
Disclosure of Invention
The test method aims at the defects of complex modification, long processing period, high structure modification cost and complex implementation of the test modification scheme in the existing test scheme. The method is characterized in that structural modification of the rotating shaft and the vicinity of the rotating shaft is avoided by combining with structural characteristics of an engine, and an aeroengine rotating speed signal with a key phase function is tested and obtained by designing measures of designing a light diffuse reflection structure (painting, gluing and frosting) on the top of the blade tip of the rotor blade and additionally arranging an optical fiber sensor on an engine casing. This scheme only implements at 1 blade top of a certain 1 level rotor blade, and the repacking cycle is short, and the repacking volume is little, and high-low pressure blade treatment methods is the same, and is little to the rotor structure repacking, does not reequip the inside stator structure of engine, can not bring the safety risk. The processing period is short, and the test scheme is simple to implement. Because the sensor is installed on the machine casket, can dismantle, both mountable are maintained on the test bench, practice thrift test cost.
A rotating speed signal testing system with the key phase function is developed based on a Labview environment, the blade arrival time collected by an optical fiber sensor is calculated by using a 6602 series test board card, a key phase signal which is not changed relative to a rotating shaft is identified, and the rotating speed signal with the key phase function is generated. The optical fiber sensor has better dynamic performance compared with a magnetic steel sensor and an eddy current sensor, and generates an original signal directly through a photoelectric converter, thereby reducing signal regulation links and eliminating rotating speed errors caused by the signal regulation links compared with the prior scheme. Because the distance variation between the rotor blade and the sensor is small, the signal amplitude is almost unchanged, and the method is superior to a high-low tooth testing scheme.
The specific scheme of the application comprises the following steps: the method for generating and measuring the rotating speed signal with the key phase function based on the blade tip timing comprises the following steps:
step S1: one blade of the engine blades is subjected to non-reflective treatment, and the rest N are r 1, carrying out light reflection treatment on the blades;
step S2: receiving a reflection signal when a reflection processing blade passes by the sensor through the sensor, converting the reflection signal into a pulse signal, and outputting the pulse signal;
step S3: acquiring a time difference delta t between adjacent pulse signals;
step S4: time difference delta t between pulse signals of two light reflection processing blades on two sides of non-light reflection processing blade 0 The time difference between the pulse signals of two adjacent light reflecting processing blades is larger than the time difference between the pulse signals of two adjacent light reflecting processing blades, and the pulse signals delta t of the two light reflecting processing blades at the two sides of the non-light reflecting processing blade are judged 0 Based on Δ t 0 Outputs a rotational speed signal with a key phase function.
Preferably, the step S4 is to determine the pulse signals Δ t of two reflective processing blades at two sides of the non-reflective processing blade 0 The specific judging method is as follows: obtaining the period T of one rotation of the engine blade based on delta T 0 Is greater than
Judging pulse signals delta t of two light reflection processing blades at two sides of the non-light reflection processing blade 0 The position of (a).
Preferably, said base is based on Δ t 0 Is greater than
Judging pulse signals delta t of two light reflection processing blades at two sides of the non-light reflection processing blade 0 Including in particular based on Δ t 0 Is greater than
Judging pulse signals delta t of two light reflection processing blades at two sides of the non-light reflection processing blade 0 Position ofAnd c, setting a to be 1.5-1.8.
Preferably, the engine blades are numbered in order of the (N) th r -1) making non-reflective treatment on the blades.
Preferably, the sensor comprises a multimode optical fiber and an optoelectronic transducer, the multimode optical fiber comprises 1 path of emission light and 6 paths of receiving reflected light, the emission light is provided by the optoelectronic transducer, and the reflected light received by the multimode optical fiber is converted into a pulse signal through the optoelectronic transducer.
Preferably, the pulse signal is digitally acquired using an 80M clock using an NI-PXI, 6602 digital acquisition card.
It is preferable that: the blade is not subjected to light reflection treatment, and comprises blade painting and sanding treatment.
Preferably, the Nth record r Circumferential position of the blade, defining Nth r The rotation angle of the blade is 0 DEG, and the position of the generated rotation speed signal with the key phase function is N r The 0 position of the blade.
Preferably, Δ t 0 Is specifically Δ t 0 The rising edge of the latter pulse signal.
Preferably, the non-reflective treatment of the blade is positioned at the blade tip position.
The advantages of the present application include:
a) compared with the existing test scheme in which the sensor is arranged on the casing and is equivalent to the outside of an engine, the optical sensor test device has the advantages of simple structure installation, low structure modification cost, simplicity in disassembly and assembly and long working time.
b) Compared with the conventional magnetoelectric test scheme, the method for triggering the rotating speed signal with the key phase function has the advantages that the dynamic performance of the optical sensor is superior to that of the conventional scheme, the change amount of the rotor part of the engine is small, the modification period is short, a lead in the engine is not needed, and the structure modification cost is low.
c) The digital acquisition system based on NI-PXI and the acquisition software of Labview environment, which are realized by the invention, have the advantages that the rotation speed signal generation algorithm can accurately position the mark position, and a solid foundation is provided for the calculation precision and accuracy of the vibration phase.
Drawings
FIG. 1 is a schematic view of a test scheme of a rotating shaft with magnetic steel added;
FIG. 2 is a diagram of a key phase test scheme for high and low teeth test of a speed-measuring gear;
FIG. 3 is a timing diagram of the key phase rotation speed of the magnetic steel of the rotating shaft and the arrival time of the blade;
FIG. 4 is a timing diagram of raw signal samples without processing;
FIG. 5 is a timing diagram of a divided signal sample;
FIG. 6 is a graph of the processed timing acquisition results of the leaf tips;
FIG. 7 is a diagram of a system for acquiring a rotating speed signal with a key phase function;
FIG. 8 is a flow chart of a rotational speed signal generation with a key phase function;
FIG. 9 is a software operating interface.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
1 rotating speed signal acquisition principle with key phase function based on blade tip timing
1.1 the characteristics of rotating speed signals with key phase function and the characteristics of rotating blade sampling signals of a blade tip timing sampling principle:
the invention relates to a rotating speed signal acquisition technology with a key phase function based on a blade tip timing principle, which is characterized in that firstly, a rotating speed signal with the key phase function and a blade tip timing signal without special treatment are researched, and a test scheme is shown in figure 3. Through the magnetic steel sensor arranged on the rotor rotating shaft, a rotating speed pulse is generated when the rotor rotates for one circle, and the rotating speed pulse is the starting moment of the rotating speed ring. Through the optical fiber sensor arranged on the rotor case of the aircraft engine, when the rotating blade passes by the optical fiber sensor, reflected light is transmitted into the sensor, and a pulse signal of blade arrival time is generated through a photoelectric converter. The test results are shown in fig. 3.
The acquired rotating speed signals and the pulse signals of blade arrival can be analyzed and obtained, and N is uniformly distributed in the circumferential direction according to the characteristics of the rotor blade of the aircraft engine r Setting the pulse triggering time of the rotation speed sensor as the initial time of the current cycle of the rotor, and defining the 1 st collected blade reflection signal as the arrival time TOA of the 1# blade 1 The 2 nd collected blade reflection signal is defined as the arrival time TOA of the 2# blade 2 … … the pulse of the last leaf of the current turn is defined as N r Arrival time of # leaf
According to the principle of blade tip timing test, N is inevitably present between every two rotating speed pulses with key phase function r The rotating speed pulse signals brought by the blades. The sequence of the set rotating speed reaching time { t) can be obtained through a rotating speed acquisition system Rotational speed (n) }, in which t Rotational speed And (n) is the arrival time of the rotating speed pulse when the rotor rotates for the n-th cycle. There is a period of rotation T
The angle between the circumferential position of the i # blade and the absolute position of the magnetic steel sensor on the shaft is theta i ：
The rotating speed signal with the key phase function has the characteristics that:
a) one rotating speed pulse can be generated every time the rotor rotates for one circle, the time difference of two adjacent rotating speed pulses is the rotating speed period T of the current circle, and N is obtained every time the rotor rotates for one circle r Each leaf reflects the pulse and records the time of arrival TOA i (n)；
b) The number of the blades of the rotor blade is defined through the absolute position of the rotating speed sensor on the rotating shaft, the position of the blades is unchanged relative to the rotating shaft, and the circumferential relative angle theta between the circumferential positions of all the blades on the rotating shaft and the position of the magnetic steel rotating speed sensor i And is not changed.
1.2 rotating speed signal generation and collection principle with key phase function based on blade tip timing
As can be seen from the formula (1), the TOA can be obtained i (N) by adding adjacent N r The time difference of the pulse of the adjacent blades can be calculated to obtain the rotating speed period T. The difference between the arrival time of the previous circle of the i # blade and the time of the current circle is the rotating speed period T. The rotating speed signal is generated by only using blade tip timing blade reflection pulse, and assuming that 8 blades exist each week, a signal timing chart obtained by the rotating speed signal with the rotating speed key phase function is shown in figure 4, the rotating speed signal is generated by counting pulse frequency division and triggering every 8 blade pulses, the operation is called to use the frequency division signal of the blade pulse, and the sampling result is shown in figure 5.
Comparing the acquisition results of fig. 4 and 5, the position of the rotation speed signal obtained by frequency division of the 2# blade relative to the magnetic steel signal remains unchanged, which can be obtained according to the formula (1), and the rotation speed period T obtained by the magnetic steel and the frequency division is the same. However, because the first blade recorded by the frequency division operation is unknown, the blades which trigger frequency division rotating speed signals in different driving times are inconsistent, and the effect obtained by installing the sensor on the rotating shaft cannot be consistent. Even if the number of the 2# blade is changed to 8# under the positioning of the rotating speed signal by using the rotating speed signal obtained by frequency division of the 2# blade, although the same test run has a key phase function, the same test run cannot be used as a contrast key phase signal of different test runs.
On the basis of the frequency dividing operation, the 7# blade is subjected to hardware processing, and the top of the 7# blade is subjected to painting and frosting processing, so that the 7# blade is subjected to 7# treatmentThe top of the blade is subjected to diffuse reflection, effective light intensity cannot be reflected when the blade rotates through the optical fiber sensor, the acquisition result of the blade is shown in fig. 6, and the pulse time difference between the processed 6# blade and the processed 8# blade is the arrival time difference of other adjacent blades. Time difference between pulses of all adjacent blades except 6# and 8# blades
Time difference between 6# and 8# only
Through logic judgment and pulse trigger setting, the accumulated rotating speed period T is calculated by collecting 7 pulses every time, and the time difference delta T between every two blade pulses is judged when
The rising edge pulse of the blade triggers the generation of a rotating speed frequency division pulse. The result is shown in fig. 6, and the judgment scheme can enable the 8# blade to trigger the rotating speed signal every time, and the 8# blade does not change in the circumferential position. Therefore, the generated rotating speed signal has the key phase function, and the rotating speed signal with the key phase function is triggered by the 8# blade at different driving times. Can replace magnetic steel positioning signals to be used for acquiring rotating speed signals with key phase functions.
Extend to rotor N per week r Blade, to physical position (N) r The blade of the No. 1 (T) is processed in a non-reflection mode, so that the blade does not reflect light when passing through an optical fiber sensor on the casing, and a corresponding voltage pulse signal cannot be generated on the photoelectric converter. The PXI and 6602 acquisition board card is used for recording the time difference delta t between the current trigger pulse and the last pulse according to the rising edge trigger counter, and every time (N) is collected r -1) calculating a period of rotation T at a time Δ T, determining
When the current pulse rising edge is true, the rotating speed is triggered to generate a pulse; when false, the next pulse is determined. Obtaining the function with key phase by using the logic program and software and hardware processingA rotational speed signal.
Hardware composition of scheme for generating and acquiring aircraft engine rotating speed signal with key phase function
a. The flow chart of the aeroengine rotating speed signal acquisition scheme testing system with the key phase function is shown in fig. 7, and the aeroengine rotating speed signal acquisition scheme testing system is different from the existing testing method, namely a scheme of testing a speed measuring gear at low pressure and testing an accessory case at high pressure. The hardware mainly comprises:
and (3) structural modification of the tested piece: designing a sensor mounting structure on a tested rotor blade casing, enabling light rays emitted by an optical fiber sensor mounted on the casing to vertically emit to the top of a rotor blade, selecting the tail edge position of the blade for mounting in order to reduce the rotating speed test error, and determining the position in the circumferential direction N in an assembly state r Selecting 1# blade from the blades, determining the rotation direction of the rotor, and sequentially defining 2# and 3# … … N along the rotation direction r # leaves at (N) r Coating paint or glue which is not reflective, has enough temperature resistance, does not fall off and has allowable thickness in a gap at the irradiated position of the optical fiber at the top of the blade of the No. 1 blade, performing frosting and non-reflective treatment, and recording N r The circumferential position of the # blade is defined as 0 DEG, and the position corresponding to the generated rotation speed pulse is N r 0 ° position of # leaf.
b. Selecting an optical fiber sensor and a photoelectric converter: the optical fiber sensor selects multimode optical fibers, wherein 1 path of the optical fiber sensor transmits light, 6 paths of the optical fiber sensor receives reflected light, the transmitted light is provided by a photoelectric converter, the received reflected light is converted into pulse point signals through a photoelectric converter circuit, and compared with the rotating speed measuring mode of the existing electromagnetic sensors such as an eddy current sensor and magnetic steel, the optical fiber sensor has the obvious advantages of better dynamic characteristics, low ripple noise, fast response of flying speed and the like, the optical fiber sensor arranged on the case can be processed and replaced in a rack state (without disassembling an engine), and the maintainability is better.
c. Digital acquisition system and software: the NI-PXI and 6602 digital acquisition card is adopted, the 80M clock is used for digitally acquiring the pulse electric signal, the time resolution is higher than that of the existing rotating speed acquisition system, the more accurate rotating speed signal can be obtained, and the digital acquisition card is successfully connected with the pulse electric signal through the keyThe rotation speed signal with key phase function is generated by processing the rotation speed signal acquisition software, and a corresponding N is generated every time the rotor rotates for one circle r The rotational speed pulse at the circumferential 0 deg. position of the # blade is used by other acquisition equipment.
3 aeroengine rotating speed signal acquisition software process with key phase function
And writing rotating speed signal acquisition software according to a rotating speed signal acquisition principle of the aero-engine with the key phase function based on blade tip timing, wherein a software implementation flow chart is shown in fig. 8, and an operation interface is shown in fig. 9. And inputting the blade number and the pulse time difference counting channel, and connecting a signal cable according to the channel.
Step 1: collecting hardware information and the number of rotor blades;
step 2: establishing a rotating speed period T of a first circle of the rotor blade;
step 3: by rising edge departure and decision logic
Generating a key phase rotating speed pulse signal and executing in a circulating way;
step 4: infinite loop, manual stop.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The method for generating and measuring the rotating speed signal with the key phase function based on the blade tip timing is characterized in that:
step S1: one blade of the engine blades is subjected to non-reflective treatment, and the rest N are r 1, carrying out light reflection treatment on the blades;
step S2: receiving a reflection signal when a reflection processing blade passes by the sensor through the sensor, converting the reflection signal into a pulse signal, and outputting the pulse signal;
step S3: acquiring a time difference delta t between adjacent pulse signals;
step S4: time difference delta t between pulse signals of two light reflection processing blades on two sides of non-light reflection processing blade 0 The time difference between the pulse signals of two adjacent light reflecting processing blades is larger than the time difference between the pulse signals of two adjacent light reflecting processing blades, and the pulse signals delta t of the two light reflecting processing blades at the two sides of the non-light reflecting processing blade are judged 0 Based on Δ t 0 Outputs a rotational speed signal with a key phase function.
2. The method for generating and measuring a rpm signal with a key phase function based on blade tip timing as claimed in claim 1, wherein the step S4 is to determine the pulse signals Δ t of two retroreflective blades on both sides of the non-retroreflective blade 0 The specific judging method is as follows: obtaining the period T of one rotation of the engine blade based on delta T 0 Is greater than
Judging pulse signals delta t of two light reflection processing blades at two sides of the non-light reflection processing blade 0 The position of (a).
3. The method of claim 2, wherein the delta t-based key-phase function is based on a delta t signal 0 Is greater than
Judging pulse signals delta t of two light reflection processing blades at two sides of the non-light reflection processing blade 0 Including in particular based on Δ t 0 Is greater than
Judging pulse signals delta t of two light reflection processing blades at two sides of the non-light reflection processing blade 0 Wherein a takes a value of 1.5 to 1.8.
4. As claimed in claim 1The method for generating and measuring the rotating speed signal with the key phase function based on the blade tip timing is characterized in that the engine blades are numbered in sequence, and the (N) th rotating speed signal is processed r -1) making non-reflective treatment on the blades.
5. The method of claim 1, wherein the sensor comprises a multimode fiber and an optical-to-electrical converter, the multimode fiber comprises 1 path of emitting light and 6 paths of receiving reflected light, the emitting light is provided by the optical-to-electrical converter, and the reflected light received by the multimode fiber is converted into pulse signals by the optical-to-electrical converter.
6. The method as claimed in claim 1, wherein the NI-PXI 6602 digital acquisition card is used to digitally acquire the pulse signal by using 80M clock.
7. A method of generating and measuring a key phase function speed signal based on tip timing as claimed in claim 1, wherein: the blade is not subjected to light reflection treatment, and comprises blade painting and sanding treatment.
8. The method of claim 4 wherein the Nth is recorded r Circumferential position of the blade, defining Nth r The rotation angle of the blade is 0 DEG, and the position of the generated rotation speed signal with the key phase function is N r The 0 position of the blade.
9. The method of claim 1, wherein at is determined by delta t 0 Is specifically Δ t 0 The rising edge of the latter pulse signal.
10. The method of claim 7, wherein the blade tip timing-based keyed phase function tachometer signal is located at a blade tip location.
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