CN112733600A - Blade fault diagnosis method without rotating speed reference signal - Google Patents
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- G—PHYSICS
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
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- G06F2218/12—Classification; Matching
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/16—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring distance of clearance between spaced objects
Abstract
The invention discloses a blade fault diagnosis method without a rotating speed reference signal, which comprises the steps of establishing a blade vibration signal model, wherein the variable quantity of a gap between the ith blade and the (i + 1) th blade is the variable quantity of the ith blade tip distance, and the relationship between a blade tip distance change signal and a blade vibration signal is as follows: y isi＝xi+1‑xiThe blade tip interval change signal is calculated without a rotating speed reference signal, a linear relation exists between the blade tip interval change signal and the blade vibration signal, the frequency components of the blade tip interval change signal and the blade vibration signal are analyzed based on a multiple signal classification algorithm, intra-class comparison of the frequencies of the blade tip interval change signal is carried out, two frequency components exist in two adjacent blade tip interval change signals of a fault blade, and the fault blade is positioned based on the two frequency components.
Description
Technical Field
The invention belongs to the field of non-contact testing of blades, and particularly relates to a blade fault diagnosis method without a rotating speed reference signal.
Background
The blade end timing technology is a hotspot field of research in the field of blade fault diagnosis in recent years, and has the advantages of non-contact type, long service life cycle, online monitoring and the like. However, due to the performance and cost requirements of aircraft engines, tip-timed sensors are expensive to install. The traditional blade end timing test needs two sensors with different purposes, namely a rotating speed sensor and a blade end timing sensor. The tip timing sensor is typically mounted on the casing to monitor the blade arrival signal, and the speed sensor needs to be mounted near the shaft to monitor the key phase signal of the shaft. However, in an actual engine, it is not practical to mount a rotation speed sensor near the rotating shaft in consideration of lead problems, engine performance, and sensor operating temperature. The research on the blade end timing technology without the rotating speed sensor has important significance for reducing the cost of the blade end timing sensor and improving the feasibility of online monitoring.
The above information disclosed in this background section is only for enhancement of understanding of the background of the invention and therefore it may contain information that does not form the prior art that is already known in this country to a person of ordinary skill in the art.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a blade fault diagnosis method without a rotating speed reference signal.
The invention aims to realize the purpose through the following technical scheme, and the blade fault diagnosis method without the rotating speed reference signal comprises the following steps:
in the first step, a blade vibration signal model is established, wherein the blade vibration signal comprises k frequency components:
wherein x isi(t) is the vibration displacement of the ith blade, t is a time independent variable, aik，fik，
The amplitude, the frequency and the phase of the kth frequency component of the ith blade signal are respectively, e is a natural constant, and K is the number of the frequency components;
in the second step, the variation of the interval between the ith blade and the (i + 1) th blade is the variation of the ith blade tip interval, and the relationship between the blade tip interval variation signal and the blade vibration signal is as follows: y isi＝xi+1-xiWherein x isiFor the vibration displacement of the ith blade, the blade tip interval change signal passes through yi＝(αi-α′i) R is calculated, R is the blade radius, alphaiIs theoretical tip spacing, α'iFor actual measured tip spacing, αi＝2πfr(TOAi+1-TOAi) Wherein f isrFor rotor frequency conversion, TOAiThe calculation of the tip interval change signal does not need a rotating speed reference signal for the arrival time of the ith blade,
in the third step, a linear relation exists between the blade tip interval change signal and the blade vibration signal, the frequency components of the blade tip interval change signal and the blade vibration signal are analyzed based on a multiple signal classification algorithm to obtain the frequency components of the blade tip interval change signal and the frequency components of the blade vibration signal,
and in the fourth step, analyzing the frequency of the blade tip distance change signal, wherein two frequency components exist in two adjacent blade tip distance change signals of the fault blade, and positioning the fault blade based on the two frequency components.
In the fourth step, the intra-class comparison of the blade tip interval change signal and the blade vibration signal frequency is carried out, and the validity of the blade tip interval change signal is verified based on whether the fault blade identification results are the same or not.
In the method, in the first step, the blade vibration signal model is a complex exponential signal of multiple frequency components.
In the method, in the second step, the rotor frequency required for calculating the tip pitch change is represented by the reciprocal of the time difference between two consecutive rotations of a blade passing the same sensor.
In the third step, the tip interval change signal and the blade vibration signal are independently calculated.
In the fourth step, whether two frequency components exist in the tip interval change signal is judged based on the frequency difference.
The blade arrival time corresponds to a time point, so that a rotating speed reference signal is needed as a reference, and the theoretical arrival time and the actual arrival time are calibrated, so that the blade displacement is obtained. According to the method, the blade tip interval passing time corresponds to a time period, the theoretical passing time and the actual passing time do not need reference signals for calculation, and the blade tip interval change signals are used for replacing blade vibration signals in the blade end timing technology, so that the dependence on a rotating speed sensor can be overcome, the sensor cost is reduced, the feasibility of the blade end timing technology is improved, and the fault blade can be positioned.
The above description is only an overview of the technical solutions of the present invention, and in order to make the technical means of the present invention more clearly apparent, and to make the implementation of the content of the description possible for those skilled in the art, and to make the above and other objects, features and advantages of the present invention more obvious, the following description is given by way of example of the specific embodiments of the present invention.
Drawings
Various other advantages and benefits of the present invention will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. It is obvious that the drawings described below are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort. Also, like parts are designated by like reference numerals throughout the drawings.
In the drawings:
FIG. 1 is a schematic representation of steps of a method of diagnosing a blade fault without a rotational speed reference signal according to an embodiment of the present disclosure;
FIG. 2 is a schematic tip timing installation diagram of a method of diagnosing blade faults without a speed reference signal according to one embodiment of the present invention;
FIG. 3 is a schematic diagram of tip timing rectangular pulses of a method of diagnosing a blade fault without a speed reference signal according to an embodiment of the present invention;
FIG. 4 is a disk coordinate diagram of a method of diagnosing blade faults without a rotational speed reference signal according to an embodiment of the present invention;
FIG. 5 is a bench diagram of a method of blade fault diagnosis without a rotational speed reference signal according to an embodiment of the present invention;
FIG. 6 is a test blisk diagram of a method of diagnosing blade faults without a rotational speed reference signal according to one embodiment of the present invention;
FIG. 7 is a damaged blade map number three of a blade fault diagnosis method without a rotational speed reference signal according to an embodiment of the invention;
FIG. 8 is a damaged blade number eight diagram of a blade fault diagnosis method without a rotational speed reference signal according to an embodiment of the invention;
FIG. 9 is a time domain signal diagram of a method of blade fault diagnosis without a speed reference signal according to one embodiment of the present invention.
The invention is further explained below with reference to the figures and examples.
Detailed Description
Specific embodiments of the present invention will be described in more detail below with reference to fig. 1 to 9. While specific embodiments of the invention are shown in the drawings, it should be understood that the invention may be embodied in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
It should be noted that certain terms are used throughout the description and claims to refer to particular components. As one skilled in the art will appreciate, various names may be used to refer to a component. This specification and claims do not intend to distinguish between components that differ in name but not function. In the following description and in the claims, the terms "include" and "comprise" are used in an open-ended fashion, and thus should be interpreted to mean "include, but not limited to. The description which follows is a preferred embodiment of the invention, but is made for the purpose of illustrating the general principles of the invention and not for the purpose of limiting the scope of the invention. The scope of the present invention is defined by the appended claims.
For the purpose of facilitating understanding of the embodiments of the present invention, the following description will be made by taking specific embodiments as examples with reference to the accompanying drawings, and the drawings are not to be construed as limiting the embodiments of the present invention.
The blade fault diagnosis method without the rotating speed reference signal comprises the following steps,
in a first step S1, a blade vibration signal model is established, wherein the blade vibration signal includes k frequency components:
wherein x isi(t) is the vibration displacement of the ith blade, t is a time independent variable, aik，fik，
The amplitude, the frequency and the phase of the kth frequency component of the ith blade signal are respectively, e is a natural constant, and K is the number of the frequency components;
in the second step S2, the variation of the interval between the i-th and i + 1-th blades is the variation of the i-th blade tip pitch, and the relationship between the blade tip pitch variation signal and the blade vibration signal is as follows: y isi＝xi+1-xiWherein x isiIs the vibrational displacement of the ith vane,tip pitch change signal pass yi＝(αi-α′i) R is calculated, R is the blade radius, alphaiIs theoretical tip spacing, α'iFor actual measured tip spacing, αi＝2πfr(TOAi+1-TOAi) Wherein f isrFor rotor frequency conversion, TOAiThe calculation of the tip interval change signal does not need a rotating speed reference signal for the arrival time of the ith blade,
in a third step S3, a linear relationship exists between the tip clearance change signal and the blade vibration signal, the frequency components of the tip clearance change signal and the blade vibration signal are analyzed based on a multiple signal classification algorithm to obtain the frequency components of the tip clearance change signal and the frequency components of the blade vibration signal,
in the fourth step S4, the tip pitch change signal frequency is analyzed, two frequency components exist in two adjacent tip pitch change signals of the faulty blade, and the faulty blade is located based on the two frequency components.
Alternatively, the intra-class comparison means that the frequencies of the blade pitch change signals are compared with each other, and the comparison is limited to the class of the tip pitch change signals.
In the preferred embodiment of the method, in the first step S1, since the blade vibration is usually a superposition of a plurality of sinusoidal vibrations, it is modeled as a complex exponential signal of multiple frequency components, without considering noise factors.
In a preferred embodiment of the method, in the second step S2, the rotor frequency required for calculating the tip pitch change in the absence of the speed reference signal is represented by the inverse of the time difference between two consecutive revolutions of a blade passing the same sensor.
In a preferred embodiment of the method, in the third step S3, the tip pitch variation and the blade vibration signal are independently calculated.
In a preferred embodiment of the method, in the fourth step S4, it is determined whether two frequency components exist in the tip pitch change signal based on the frequency difference.
For further understanding, fig. 1 is a flowchart of a method for diagnosing a blade fault without a rotational speed reference signal, as shown in fig. 1, the method for diagnosing a blade fault without a rotational speed reference signal includes the following steps:
in a first step S1, a blade vibration signal model is established without considering the influence of noise, assuming that the blade vibration signal contains K frequency components:
wherein x isi(t) is the vibration displacement of the ith vane, aik，fik，
The amplitude, frequency and phase, respectively, of the kth frequency component of the ith vane signal, e is a natural constant,
in the second step S2, assuming that the variation of the interval between the ith and i +1 th blades is the ith tip pitch variation, the relationship between the tip pitch variation signal and the blade vibration signal can be obtained: y isi＝xi+1-xi，
The blade tip spacing change signal can pass through yi＝(αi-α′i) R is calculated as R is the blade radius, alphaiIs theoretical tip spacing, α'iFor actual measured tip spacing, αi＝2πfr(TOAi+1-TOAi) Wherein f isrFor rotor frequency conversion, TOAiFor the arrival time of the ith blade, it can be seen that the calculation of the blade tip spacing change signal does not need the participation of the rotating speed reference signal,
in the third step S3, since there is a linear relationship between the tip pitch change signal and the blade vibration signal, the multiple signal classification algorithm can be used to analyze the frequency components of the tip clearance change signal and the blade vibration signal,
in the fourth step S4, intra-class comparison of the blade tip interval change signal frequencies is performed, and since a faulty blade may cause a frequency drop, two frequency components may exist in two adjacent blade tip interval change signals of the faulty blade, and based on the two frequency components, the faulty blade is located, intra-class comparison of the blade tip interval change signal and the blade vibration signal frequencies is performed, whether the identification results of the two faulty blades are the same is observed, and the validity of the blade tip interval change signal is verified.
To further illustrate the method of the present invention, fig. 2 is a schematic diagram of the tip timing installation of a method for diagnosing blade faults without a rotational speed reference signal according to the present invention, as shown in fig. 2, a rotational speed sensor needs to be installed near a rotating shaft to obtain a key phase signal as a reference signal, and the tip timing sensor is used to obtain a blade arrival pulse. FIG. 3 is a schematic diagram of a blade end timing rectangular pulse of a blade fault diagnosis method without a rotating speed reference signal according to the invention, the sensors in FIG. 3 and FIG. 2 are arranged in a corresponding relationship, the arrival time of the blade due to blade vibration is calculated by using the arrival time of the key phase signal, and the vibration displacement of the blade is calculated by further combining the diameter of the rotor and the period of the key phase signal. FIG. 4 is a disk coordinate diagram illustrating a method for diagnosing blade faults without a rotational speed reference signal according to the present invention, for explaining the y between a tip pitch variation signal and a blade vibration signali＝xi+1-xiThe relationship (2) of (c). FIG. 5 is a bench chart of a method of diagnosing blade faults without a rotational speed reference signal according to the present invention, using three tip timing sensors and simulating blade excitation using gas. FIG. 6 is a test vane disk diagram of a vane fault diagnosis method without a rotating speed reference signal according to the invention, wherein the vane has the thickness of 1mm, the width of 20mm, the height of 48mm and the diameter of 136 mm. FIG. 7 is a graph of damaged blades number three of a method for diagnosing blade faults without a rotational speed reference signal according to the present invention. FIG. 8 is a graph of damaged blade number eight of a method of diagnosing blade faults without a rotational speed reference signal according to the present invention. FIG. 9 is a time domain signal diagram of a method of blade fault diagnosis without a speed reference signal according to the present invention.
In a preferred embodiment of the present invention, the blade fault diagnosis method without the rotational speed reference signal, in the first step S1: for the purpose of derivation, the blade vibration signal is modeled without considering the influence of noise, assuming that the blade vibration signal contains K frequency components:
wherein x isi(t) is the vibration displacement of the ith vane, aik，fik，
The amplitude, frequency and phase, respectively, of the kth frequency component of the ith vane signal, e is a natural constant,
in a preferred embodiment of the present invention, the blade fault diagnosis method without the rotational speed reference signal, in the second step S2: the calculation of the tip pitch change signal requires the participation of a rotational speed, which can be represented by the reciprocal of the time difference between two consecutive rotations of one blade passing the same sensor.
In a preferred embodiment of the present invention, the blade fault diagnosis method without the rotational speed reference signal, in the third step S3: the included angle between the first leaf end timing sensor and the second leaf end timing sensor is 18 degrees, the included angle between the second leaf end timing sensor and the third leaf end timing sensor is 36 degrees, and the frequency results of the multiple signal classification identification are as follows:
in a preferred embodiment of the blade fault diagnosis method without the rotation speed reference signal of the present invention, in the fourth step S4: combining the identification results of multiple signal classification, through the intra-class comparison of the blade tip distance change frequency results, it can be seen that the blade tip distance change two and three contain the frequency of the blade three, and the blade tip distance change seven and eight contain the frequency of the blade three.
In an embodiment, as shown in fig. 7, which is a diagram of a damaged blade with no rotational speed reference signal according to the blade fault diagnosis method of the present invention, and fig. 8, which is a diagram of an damaged blade with no rotational speed reference signal according to the blade fault diagnosis method of the present invention, it can be seen by combining the analysis of the foregoing multiple signal classification results that cracks of the blade three and the blade eight can be reflected by the frequency component of the tip interval change signal. Fig. 9 is a time domain signal diagram of a blade fault diagnosis method without a rotational speed reference signal according to the present invention, and it can be seen that the time domain signal of the first tip pitch variation is equivalent to the accumulation of the vibration signals of the first blade and the second blade, and corresponds to the relationship between the inferred tip pitch variation and the blade vibration signals, and is preset. The rationality of the method provided by the invention is verified.
Although the embodiments of the present invention have been described above with reference to the accompanying drawings, the present invention is not limited to the above-described embodiments and application fields, and the above-described embodiments are illustrative, instructive, and not restrictive. Those skilled in the art, having the benefit of this disclosure, may effect numerous modifications thereto without departing from the scope of the invention as defined by the appended claims.
Claims (6)
1. A method of diagnosing a blade fault without a speed reference signal, the method comprising the steps of:
in a first step (S1), a blade vibration signal model is established, wherein the blade vibration signal includes K frequency components:
wherein x isi(t) is the vibration displacement of the ith blade, t is a time independent variable, aik，fik，
The vibration amplitude, the vibration frequency and the vibration phase of the kth frequency component of the ith blade signal are respectively, e is a natural constant, and K is the number of the frequency components;
in the second step (S2),the variable quantity of the interval between the ith blade and the (i + 1) th blade is the variable quantity of the ith blade tip interval, and the relationship between the blade tip interval change signal and the blade vibration signal is as follows: y isi＝xi+1-xiWherein x isiFor the vibration displacement of the ith blade, the blade tip interval change signal passes through yi＝(αi-α′i) R is calculated, R is the blade radius, alphaiIs theoretical tip spacing, α'iFor actual measured tip spacing, αi＝2πfr(TOAi+1-TOAi) Wherein f isrFor rotor frequency conversion, TOAiThe calculation of the tip interval change signal does not need a rotating speed reference signal for the arrival time of the ith blade,
in the third step (S3), a linear relationship exists between the tip clearance change signal and the blade vibration signal, the frequency components of the tip clearance change signal and the blade vibration signal are analyzed based on a multiple signal classification algorithm to obtain the frequency components of the tip clearance change signal and the frequency components of the blade vibration signal,
in the fourth step (S4), the tip pitch change signal frequency is analyzed, two frequency components exist in two adjacent tip pitch change signals of the faulty blade, and the faulty blade is located based on the two frequency components.
2. The method according to claim 1, wherein preferably in the fourth step (S4), an intra-class comparison of the blade tip pitch change signal and the blade vibration signal frequency is performed to verify the validity of the blade tip pitch change signal based on whether the faulty blade identification results are the same.
3. The method of claim 1, wherein in the first step (S1), the blade vibration signal model is a complex exponential signal of multiple frequency components.
4. The method of claim 1, wherein in the second step (S2), the rotor revolution at which the tip pitch change is calculated is represented by the inverse of the time difference between two consecutive revolutions of a blade passing the same sensor.
5. The method according to claim 1, wherein in the third step (S3), the tip pitch change signal and the blade vibration signal are calculated separately and independently.
6. The method according to claim 1, wherein in the fourth step (S4), it is determined whether there are two frequency components of the tip pitch change signal based on the frequency difference value.
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