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CN-122016747-A - Method for monitoring deep coupling of experimental bench components and pressure field of scramjet engine

CN122016747ACN 122016747 ACN122016747 ACN 122016747ACN-122016747-A

Abstract

The invention belongs to the technical field of optical diagnosis of a ground test of a scramjet engine, and discloses a method for monitoring the deep coupling of components and a pressure field of a scramjet engine experiment table, which comprises the steps of constructing and obtaining a single-wavelength laser-component response matrix when the experiment table is adjusted to a test working condition; when the experiment table is adjusted from the test working condition to the experiment working condition, the single-wavelength excitation light source is utilized to excite the flow field and the wall pressure sensitive coating, component fluorescence intensity signals of different wavebands are collected to form fluorescence intensity observation vectors and coating luminescence signals, inversion calculation is carried out on the fluorescence intensity observation vectors according to the response matrix to obtain content information of each target component including oxygen, the oxygen component content information is utilized to calculate pressure information of a monitoring position, and component content information and pressure distribution of the monitoring position are output. The accuracy and the reliability of the components and the pressure measurement of the experiment table are improved.

Inventors

  • WU KEXIN
  • CHEN XIN

Assignees

  • 浙江理工大学

Dates

Publication Date
20260512
Application Date
20260227

Claims (9)

  1. 1. The method for monitoring the deep coupling of the components and the pressure field of the experimental bench of the scramjet engine is characterized by comprising the following steps of: when the experiment table is adjusted to a test working condition, carrying out normalization processing on laser energy and detection efficiency, collecting fluorescence intensity information of multiple flow field target components in multiple detection wavebands, obtaining response coefficients of multiple target components in different detection wavebands under the single-wavelength laser, and constructing and obtaining a single-wavelength laser-component response matrix; When the experiment table is adjusted from the test working condition to the experiment working condition, the single-wavelength excitation light source is utilized to excite the flow field and the wall pressure sensitive coating, and component fluorescence intensity signals of different detection wavebands are synchronously collected to form a fluorescence intensity observation vector and a coating luminescence signal; According to the single-wavelength laser-component response matrix, carrying out inversion calculation on the fluorescence intensity observation vector to obtain content information of each target component including oxygen; And calculating pressure information of the monitoring position by utilizing the oxygen component content information, and outputting component content information and pressure distribution of the monitoring position.
  2. 2. The method of claim 1, wherein the construction of the single wavelength laser-component response matrix comprises: The method comprises the steps of adopting single-wavelength pulse laser after spectrum frequency selection as an excitation light source, adjusting the angle of a light path through a reflecting mirror, shaping the original three-dimensional laser into sheet laser through a beam shaping cylindrical lens, respectively introducing single target components into a controllable calibration environment according to experiment requirements under the condition that the excitation light source and optical detection conditions are consistent, and then exciting a flow field in a preset two-dimensional section; And normalizing the fluorescence intensity signals of the different components by introducing laser energy and detection efficiency to obtain response coefficients of each target component in different detection channels, thereby constructing a single-wavelength laser-component response matrix.
  3. 3. The method of claim 1, further comprising an initialization of the laboratory bench, the initialization comprising: (1) Carrying out space initialization on the experiment table, wherein the space initialization comprises the steps of determining the space position of excitation laser relative to an engine runner and the focal length of an imaging system, so that an imaging range covers the section of a flow field to be detected and a pressure sensitive coating area; (2) Keeping the experimental laser wavelength and the spectrum separation component of the camera consistent with the construction of a single-wavelength laser-component response matrix; (3) And adjusting the operation parameters of an engine experiment table to enable the flow field to reach a preset experiment working condition.
  4. 4. The method of claim 1, wherein collecting component fluorescence intensity signals of different detection bands constitutes a fluorescence intensity observation vector and a coating luminescence signal, comprising: after the initialization of the experimental equipment is completed, the single-wavelength pulse laser is adopted as an excitation light source to synchronously excite the target components in the flow field and the wall pressure sensitive coating; the flow field component fluorescent signals and wall pressure sensitive coating luminous signals generated after excitation enter an imaging system through an optical window of a scramjet engine experiment table, are separated according to a preset wave band through a spectroscopic imaging device and are projected to sensors of a plurality of detection channels; At each sampling moment, carrying out normalized correction of laser energy fluctuation and spatial distribution non-uniformity on the fluorescence intensity signal; And synchronously collecting component fluorescence intensity signals of different wave bands, combining the fluorescence intensity signals of a plurality of detection channels at the same spatial position to form a fluorescence intensity observation vector, and simultaneously recording the luminescence signals of the pressure sensitive coating.
  5. 5. The method of claim 1, wherein inverting the fluorescence intensity observation vector based on the single wavelength laser-component response matrix yields information on the content of each target component including oxygen, comprising: Performing inversion calculation on the fluorescence intensity observation vector based on a pre-constructed single-wavelength laser-component response matrix to obtain content information of each target component at a corresponding position; physical constraint conditions are applied to inversion results to eliminate non-physical results, so that stability and reliability of component inversion are improved.
  6. 6. The method of claim 1, wherein calculating pressure information for the monitoring location using the oxygen component content information, outputting component content information and pressure distribution for the monitoring location, comprises: and taking the two-dimensional oxygen concentration field in the content information of each target component and the real-time fluorescence intensity field acquired by the sensor as input variables, and calculating the pressure information of the monitoring position, so as to output the component content information and the pressure distribution of the monitoring position.
  7. 7. The utility model provides a scramjet engine laboratory bench component-pressure field degree of depth coupling monitoring devices which characterized in that includes: The response matrix construction module is used for carrying out normalization processing on laser energy and detection efficiency when the experiment table is adjusted to a test working condition, collecting fluorescence intensity information of multiple flow field target components in multiple detection wave bands, obtaining response coefficients of multiple target components in different detection wave bands under the single-wavelength laser, and further constructing and obtaining a single-wavelength laser-component response matrix; the experiment module is used for exciting the flow field and the wall pressure sensitive coating by utilizing the single-wavelength excitation light source when the experiment table is adjusted from the test working condition to the experiment working condition, and synchronously collecting component fluorescence intensity signals of different detection wavebands to form a fluorescence intensity observation vector and a coating luminescence signal; The component inversion calculation module is used for carrying out inversion calculation on the fluorescence intensity observation vector according to the single-wavelength laser-component response matrix to obtain content information of each target component including oxygen; And the pressure calculation module is used for calculating the pressure information of the monitoring position by utilizing the oxygen component content information and outputting the component content information and the pressure distribution of the monitoring position.
  8. 8. An electronic device, comprising: one or more processors; A memory for storing one or more programs; The one or more programs, when executed by the one or more processors, cause the one or more processors to implement the method of any of claims 1-6.
  9. 9. A computer readable storage medium having stored thereon computer instructions which, when executed by a processor, implement the steps of the method according to any of claims 1-6.

Description

Method for monitoring deep coupling of experimental bench components and pressure field of scramjet engine Technical Field The application relates to the technical field of optical diagnosis of a ground test of a scramjet engine, in particular to a method for monitoring the deep coupling of a component of a scramjet engine experiment table and a pressure field. Background The scramjet engine has important application prospect in hypersonic aircrafts, and an internal flow field of the scramjet engine generally shows high Mach number, a strong shock wave structure and complex chemical reaction. In order to accurately evaluate the combustion characteristics, thrust performance and structural safety of an engine in a ground test stage, it is necessary to accurately measure the component distribution and wall pressure characteristics of the internal flow field of the engine. The flow field component distribution can reflect the fuel mixing efficiency, the combustion reaction intensity and the oxygen consumption process, and the wall pressure distribution is directly related to the shock wave structure, the load distribution and the overall aerodynamic performance in the engine, so that the synchronous acquisition of the component information and the wall pressure information is realized under the ground test condition, and the method has important significance for revealing the physical mechanism of the flow field in the scramjet engine. At present, an optical diagnosis method based on laser-induced fluorescence is generally adopted for flow field component monitoring, and as different target components often correspond to different excitation wavelengths, in order to realize multi-component simultaneous measurement in the prior art, a plurality of laser light sources with different wavelengths are generally required to be configured, and a plurality of optical systems are matched. In addition, in wall pressure measurements, conventional pressure sensitive coatings are susceptible to local oxygen content variations in the combustion environment, resulting in deviations in the measurement results. In the process of implementing the present invention, the inventor finds that at least the following problems exist in the prior art: 1. The experimental system is complex and high in cost, the complexity and cost of the system structure are obviously increased by the traditional multi-wavelength monitoring scheme, the requirements on the stability and time synchronization of the light path are extremely high, and the system is difficult to be applied to the environment of the scramjet engine experiment table with limited space and complex working conditions; 2. The accuracy of pressure measurement is limited, and because the local oxygen content change in the combustion process cannot be accurately obtained in real time, obvious systematic errors exist in the wall pressure measurement based on the pressure sensitive coating, and the wall pressure distribution under the complex combustion working condition is difficult to truly reflect. Disclosure of Invention The embodiment of the application aims to provide a method for monitoring the deep coupling of a component of a scramjet engine experiment table and a pressure field, which aims to solve the technical problems that a multi-wavelength laser system is usually required for monitoring the component of the scramjet engine experiment table in the related technology, and a pressure sensitive coating measuring result is easily influenced by local oxygen content change. According to a first aspect of an embodiment of the present application, there is provided a scramjet engine laboratory bench component-pressure field deep coupling monitoring method, including: when the experiment table is adjusted to a test working condition, carrying out normalization processing on laser energy and detection efficiency, collecting fluorescence intensity information of multiple flow field target components in multiple detection wavebands, obtaining response coefficients of multiple target components in different detection wavebands under the single-wavelength laser, and constructing and obtaining a single-wavelength laser-component response matrix; When the experiment table is adjusted from the test working condition to the experiment working condition, the single-wavelength excitation light source is utilized to excite the flow field and the wall pressure sensitive coating, and component fluorescence intensity signals of different detection wavebands are synchronously collected to form a fluorescence intensity observation vector and a coating luminescence signal; According to the single-wavelength laser-component response matrix, carrying out inversion calculation on the fluorescence intensity observation vector to obtain content information of each target component including oxygen; And calculating pressure information of the monitoring position by utilizing the oxygen component content