Aero-engine multi-parameter measuring device and method based on optical fiber sensing

Abstract

The invention discloses an aero-engine multi-parameter measuring device and method based on optical fiber sensing, and the device comprises a composite light source module, an optical signal transmission link module, a plurality of optical signal interfaces, a plurality of universal sensing demodulation modules, and a multi-physical-quantity collection integrated module. The plurality of optical fiber sensors with different principles are respectively connected to the plurality of optical signal interfaces through transmission optical fibers; the wavelength range of output light of the composite light source module covers the working wavelength ranges of the optical fiber sensors, and each optical fiber sensor receives light matched with the principle of the optical fiber sensor and generates and returns an optical signal containing measured information; the universal sensing demodulation module performs photoelectric conversion according to the wavelength range of the received optical signal, and demodulates measured information contained in the optical signal; and the multi-physical quantity acquisition integrated module acquires measured information and time information to form a demodulation result. According to the invention, synchronous demodulation of a plurality of different types of optical fiber sensors required by measurement of a plurality of parameters in an aero-engine can be realized.

Description

Technical Field

[0001] The invention belongs to the technical field of optical fiber sensing, and in particular relates to an aero-engine multi-parameter measurement device and method based on optical fiber sensing. Background Art

[0002] For the measurement needs of strain, temperature and vibration parameters in narrow areas such as aircraft engine shafts, gears, bearings, etc., it is necessary to use fiber optic sensors based on different principles in a targeted manner to meet the testing needs of different parameters. For example, the requirements for sensors for strain or vibration parameter measurement usually include a large range, high speed, and high precision, and interference fiber optic sensors are suitable for such requirements; temperature parameters usually require sensors to have high precision characteristics, and the measurement rate is usually not high, and wavelength fiber optic sensors are suitable for such requirements. Therefore, when the front-end fiber optic sensors include fiber optic sensors based on different types of principles, it is necessary to select instruments that do not use demodulation principles to demodulate the signals of different types of fiber optic sensors in order to achieve the measurement of multiple parameters. The problems caused by using multiple demodulation instruments include: the demodulation instruments are not universal, resulting in a complex and bulky measurement system; the data between the demodulation instruments are not synchronized, and the synchronous demodulation of the signals of multiple sensors cannot be achieved; the subsequent data processing is cumbersome, and the comprehensive analysis of multiple physical quantity parameters cannot be achieved in a timely and accurate manner.

[0003] Therefore, a multi-parameter measurement method and device are needed to achieve synchronous demodulation of multiple optical fiber sensors of different types. Summary of the invention

[0004] The purpose of the present invention is to provide an aero-engine multi-parameter measurement device and method based on optical fiber sensing, which can realize the synchronous demodulation of multiple different types of optical fiber sensors required for measuring multiple parameters in application objects such as aero-engines.

[0005] In order to achieve the above-mentioned object, one aspect of the present invention provides an aircraft engine multi-parameter measurement device based on optical fiber sensing, comprising a composite light source module, an optical signal transmission link module, multiple optical signal interfaces, multiple universal sensor demodulation modules and a multi-physical quantity acquisition integrated module.

[0006] A plurality of optical fiber sensors based on different principles are respectively connected to the plurality of optical signal interfaces through transmission optical fibers;

[0007] The wavelength range of the output light of the composite light source module covers the working wavelength range of multiple optical fiber sensors, and each optical fiber sensor receives the light output by the composite light source module that matches its own principle, generates and returns an optical signal containing measured information;

[0008] The optical signal transmission link module is used to transmit the light output by the composite light source module to each optical signal interface, and to receive the optical signal returned by each optical fiber sensor from each optical signal interface and transmit it to the corresponding universal sensor demodulation module;

[0009] The universal sensor demodulation module includes a photoelectric conversion component and a data acquisition and processing component. The photoelectric conversion component includes a plurality of photoelectric detectors that can respond to different wavelength bands and can perform photoelectric conversion according to the wavelength range of the received optical signal; the data acquisition and processing component is used to receive the synchronous acquisition instruction of the multi-physical quantity acquisition integrated module and control the photoelectric detector to perform photoelectric conversion, and by processing the converted electrical signal, demodulate the measured information contained in the optical signal, and transmit the measured information and time information to the multi-physical quantity acquisition integrated module;

[0010] The multi-physical quantity acquisition integration module is used to control the universal sensor demodulation module to perform synchronous acquisition, acquire the measured information and time information demodulated and transmitted by the universal sensor demodulation module, and form a demodulation result.

[0011] Preferably, the device further comprises a processor, and the multi-physical quantity acquisition integrated module is further used to process the measured information and time information and upload the data to the processor.

[0012] Preferably, the device further comprises a communication port and a power supply port, the communication port is connected to the processor, and the power supply port is connected to a power source.

[0013] Another aspect of the present invention provides an aircraft engine multi-parameter measurement method based on optical fiber sensing, using the above-mentioned device to perform aircraft engine multi-parameter measurement, the method comprising:

[0014] According to the measurement requirements, optical fiber sensors based on different principles are installed at different test locations of the aircraft engine, and multiple optical fiber sensors are connected to various optical signal interfaces through transmission optical fibers.

[0015] The light emitted by the composite light source module is transmitted to the optical signal interface through the optical signal transmission link module, and then transmitted to each optical fiber sensor installed at the test location through the transmission optical fiber;

[0016] Each optical fiber sensor receives the light that matches itself in the composite light source module according to its own different principles. After being modulated by the external measured quantity, the optical signal containing the measured information is returned to the optical signal interface through the transmission optical fiber again.

[0017] The optical signal interface transmits the optical signal containing the measured information to the optical signal transmission link module, and transmits it to the universal sensor demodulation module of the corresponding channel of the optical signal interface through the optical signal transmission link module;

[0018] The multi-physical quantity acquisition integrated module issues a synchronous acquisition instruction. After receiving the synchronous acquisition instruction, the data acquisition and processing components in each universal sensor demodulation module control each photoelectric detector to perform photoelectric conversion according to the wavelength range of the received optical signal, and automatically match the demodulation algorithm to demodulate the measured information contained in the optical signal.

[0019] The universal sensor demodulation module transmits the demodulated measured information and the synchronous time information to the multi-physical quantity acquisition integration module, collects the measured information and the time information demodulated and transmitted by the universal sensor demodulation module, and forms a demodulation result.

[0020] The optical fiber sensing-based aircraft engine multi-parameter measurement device and method according to the above aspects of the present invention can realize the synchronous demodulation of multiple optical fiber sensors of different types required for measuring multiple parameters in application objects such as aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solution of the present invention, the following briefly introduces the drawings used in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative work:

[0022] Figure 1 It is a schematic structural diagram of an aircraft engine multi-parameter measurement device based on optical fiber sensing according to an embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of the structure of an aircraft engine multi-parameter measurement device based on optical fiber sensing according to an embodiment of the present invention;

[0024] Figure 3 A schematic diagram of the spectrum output of a composite light source module according to an embodiment of the present invention;

[0025] Figure 4 A schematic diagram of an interference spectrum returned by a vibration sensor according to an embodiment of the present invention;

[0026] Figure 5 Schematic diagram of interference spectrum and Gaussian spectrum returned by a strain sensor and a temperature sensor according to an embodiment of the present invention. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] The embodiment of the present invention provides an aircraft engine multi-parameter measurement device based on optical fiber sensing, such as Figure 1 As shown, the multi-parameter measurement device of an aircraft engine based on optical fiber sensing according to an embodiment of the present invention comprises a composite light source module 5, an optical signal transmission link module 6, multiple optical signal interfaces 8, multiple universal sensor demodulation modules 7 and a multi-physical quantity acquisition integrated module 9. The composite light source module 5, the optical signal transmission link module 6, the multiple optical signal interfaces 8, the multiple universal sensor demodulation modules 7 and the multi-physical quantity acquisition integrated module 9 constitute a demodulation instrument 3, and the demodulation instrument 3 is also provided with a communication port 10 and a power supply port 11, the communication port 10 is connected to the processor 4, and the power supply port 11 is connected to the power supply. Multiple optical fiber sensors 1 of different principles are respectively connected to the multiple optical signal interfaces 8 through transmission optical fibers 2.

[0029] The wavelength range of the output light of the composite light source module 5 should cover the working wavelength range of the multiple optical fiber sensors being measured. Each optical fiber sensor 1 receives the light output by the composite light source module 5 that matches its own principle, and generates and returns an optical signal containing the measured information. The optical signal transmission link module 6 is used to transmit the light output by the composite light source module 5 to each optical signal interface 8 of the demodulation instrument 3, and to receive the optical signal of each optical fiber sensor 1 returned from each optical signal interface, and transmit it to the universal sensor demodulation module 7 corresponding to the optical signal interface 8.

[0030] The universal sensor demodulation module 7 mainly includes a photoelectric conversion component and a data acquisition and processing component. The photoelectric conversion component includes a plurality of photoelectric detectors that can respond to different wavelength bands, and can perform photoelectric conversion according to the wavelength range of the received optical signal; the data acquisition and processing component has control, acquisition and processing functions, can receive the synchronous acquisition instructions of the multi-physical quantity acquisition integrated module 9 and control the photoelectric detector to perform photoelectric conversion, can process the converted electrical signal, automatically match the demodulation algorithm, demodulate the measured information contained in the optical signal, and transmit the measured information and time information to the multi-physical quantity acquisition integrated module 9.

[0031] The multi-physical quantity acquisition integration module 9 is mainly used to control the universal sensor demodulation module 7 to perform synchronous acquisition, collect the measured information and time information demodulated and transmitted by the universal sensor demodulation module 7, and perform data processing and analysis and data fusion on the measured information and time information and upload them to the processor 4.

[0032] The embodiment of the present invention further provides an aircraft engine multi-parameter measurement method based on optical fiber sensing, which uses the device of the above embodiment to perform aircraft engine multi-parameter measurement, comprising the following steps:

[0033] First, according to the measurement requirements, optical fiber sensors 1 with different principles are installed at different test locations of the application object such as an aircraft engine, and multiple optical fiber sensors 1 are connected to the optical signal interface of the demodulation instrument 3 through the transmission optical fiber 2;

[0034] Connect the communication port 10 of the demodulation instrument 3 to the processor 4, and connect the power supply port 11 to the power supply;

[0035] After the demodulation instrument 3 is powered on and starts working, the light emitted by the internal composite light source module 5 is transmitted to the optical signal interface 8 of the demodulation instrument 3 through the optical signal transmission link module 6, and then transmitted to each optical fiber sensor 1 installed at the test location through the transmission optical fiber 2;

[0036] Each optical fiber sensor 1 receives the optical signal matching itself in the composite light source module 5 according to its own different principles, and after being modulated by the external measured quantity, the optical signal containing the measured information is returned to the optical signal interface 8 of the demodulation instrument 3 through the transmission optical fiber 2 again;

[0037] The optical signal interface 8 transmits the optical signal containing the measured information to the optical signal transmission link module 6 inside the demodulation instrument 3, and transmits it to the universal sensor demodulation module 7 of the corresponding channel of the optical signal interface 8 through the optical signal transmission link module 6;

[0038] The multi-physical quantity acquisition integrated module 9 issues a synchronous acquisition instruction. After receiving the synchronous acquisition instruction, the data acquisition and processing components in each universal sensor demodulation module 7 control each photoelectric detector to perform photoelectric conversion according to the wavelength range of the received optical signal, and automatically match the demodulation algorithm to demodulate the measured information contained in the optical signal.

[0039] The universal sensor demodulation module 7 transmits the demodulated measured information and synchronized time information to the multi-physical quantity acquisition integration module 9. The multi-physical quantity acquisition integration module 9 performs data processing, analysis and data fusion on the collected measured information and time information, and forms a demodulation result which is uploaded to the processor 4, completing the entire demodulation process and realizing the comprehensive measurement and analysis of multi-physical quantity parameters.

[0040] In a specific embodiment, Figure 2 As shown, according to the measurement requirements, a certain aircraft engine needs to perform multi-point measurement of three parameters such as strain, vibration and temperature. The measured signals include static signals and dynamic high-frequency signals. Therefore, optical fiber Fabry-Perot sensors are selected as strain sensors 13 and vibration sensors 14, and optical fiber Bragg grating sensors are selected as temperature sensors 12.

[0041] The composite light source module 5 mainly includes three DFB diode lasers 15 and one broadband scanning laser light source 16. The central wavelength of the DFB diode laser 15 does not overlap with the wavelength range of the broadband scanning laser light source 16. Figure 3 As shown. Among them, Figure 3 The left side shows the wavelength range of the broadband scanning laser light source 16 , and the right side shows the central wavelengths of the three DFB diode lasers 15 .

[0042] The vibration sensor 14 matches the light emitted by the three DFB diode lasers 15 and returns three interference spectra, such as Figure 4 The strain sensor 13, the temperature sensor 14 matches the light emitted by the broadband scanning laser light source 16, and returns the interference spectrum and the Gaussian spectrum, such as Figure 5 shown.

[0043] The universal sensor demodulation module 7 includes 4 photodetectors, 3 of which can respond to the three interference spectra of the vibration sensor 14, and 1 photodetector can respond to the optical signals of the strain sensor 13 and the temperature sensor 14; after the 4 photodetectors perform photoelectric conversion, the converted electrical signals are sent to the corresponding data acquisition and processing components for processing, and the demodulation algorithm is automatically matched to demodulate the measured information contained in the optical signal.

[0044] In summary, the aircraft engine multi-parameter measurement device and method based on optical fiber sensing according to the embodiment of the present invention has the following beneficial effects:

[0045] 1) Use a composite light source module to adapt to optical fiber sensors of different principles, ensuring that different optical fiber sensors can receive optical signals that are adapted to their response ranges;

[0046] 2) Design a universal sensor demodulation module that can realize adaptive demodulation according to the received optical signal and can be adapted to optical fiber sensors based on various principles;

[0047] 3) The universal sensor demodulation module is modularly designed to achieve channel expansion and simultaneous measurement of multiple parameters, thereby realizing the comprehensive measurement and analysis of multiple physical field parameters.

[0048] The above description is only by way of illustration of certain exemplary embodiments of the present invention. It is undoubted that those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. An aero-engine multi-parameter measurement device based on optical fiber sensing, characterized in that: It includes a composite light source module, an optical signal transmission link module, multiple optical signal interfaces, multiple universal sensor demodulation modules and a multi-physical quantity acquisition integration module. A plurality of optical fiber sensors based on different principles are respectively connected to the plurality of optical signal interfaces through transmission optical fibers; The wavelength range of the output light of the composite light source module covers the working wavelength range of multiple optical fiber sensors, and each optical fiber sensor receives the light output by the composite light source module that matches its own principle, generates and returns an optical signal containing measured information; The optical signal transmission link module is used to transmit the light output by the composite light source module to each optical signal interface, and to receive the optical signal returned by each optical fiber sensor from each optical signal interface and transmit it to the corresponding universal sensor demodulation module; The universal sensor demodulation module includes a photoelectric conversion component and a data acquisition and processing component. The photoelectric conversion component includes a plurality of photoelectric detectors that can respond to different wavelength bands and can perform photoelectric conversion according to the wavelength range of the received optical signal; the data acquisition and processing component is used to receive the synchronous acquisition instruction of the multi-physical quantity acquisition integrated module and control the photoelectric detector to perform photoelectric conversion, and by processing the converted electrical signal, demodulate the measured information contained in the optical signal, and transmit the measured information and time information to the multi-physical quantity acquisition integrated module; The multi-physical quantity acquisition integration module is used to control the universal sensor demodulation module to perform synchronous acquisition, acquire the measured information and time information demodulated and transmitted by the universal sensor demodulation module, and form a demodulation result.

2. The device according to claim 1, characterized in that It also includes a processor, and the multi-physical quantity acquisition integrated module is also used to process the measured information and time information and upload them to the processor.

3. The device according to claim 2, characterized in that It also includes a communication port and a power supply port, wherein the communication port is connected to the processor, and the power supply port is connected to a power source.

4. A method for measuring multi-parameters of an aircraft engine based on optical fiber sensing, characterized in that: The device according to any one of claims 1 to 3 is used to measure multiple parameters of an aircraft engine, and the method comprises: According to the measurement requirements, optical fiber sensors based on different principles are installed at different test locations of the aircraft engine, and multiple optical fiber sensors are connected to various optical signal interfaces through transmission optical fibers. The light emitted by the composite light source module is transmitted to the optical signal interface through the optical signal transmission link module, and then transmitted to each optical fiber sensor installed at the test location through the transmission optical fiber; Each optical fiber sensor receives the light that matches itself in the composite light source module according to its own different principles. After being modulated by the external measured quantity, the optical signal containing the measured information is returned to the optical signal interface through the transmission optical fiber again. The optical signal interface transmits the optical signal containing the measured information to the optical signal transmission link module, and transmits it to the universal sensor demodulation module of the corresponding channel of the optical signal interface through the optical signal transmission link module; The multi-physical quantity acquisition integrated module issues a synchronous acquisition instruction. After receiving the synchronous acquisition instruction, the data acquisition and processing components in each universal sensor demodulation module control each photoelectric detector to perform photoelectric conversion according to the wavelength range of the received optical signal, and automatically match the demodulation algorithm to demodulate the measured information contained in the optical signal. The universal sensor demodulation module transmits the demodulated measured information and the synchronous time information to the multi-physical quantity acquisition integration module, collects the measured information and the time information demodulated and transmitted by the universal sensor demodulation module, and forms a demodulation result.

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