CN119437726A - A three-dimensional high-speed measurement system for aircraft engine combustion chamber based on flexible optical fiber bundle - Google Patents

A three-dimensional high-speed measurement system for aircraft engine combustion chamber based on flexible optical fiber bundle Download PDF

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Publication number
CN119437726A
CN119437726A CN202411634609.4A CN202411634609A CN119437726A CN 119437726 A CN119437726 A CN 119437726A CN 202411634609 A CN202411634609 A CN 202411634609A CN 119437726 A CN119437726 A CN 119437726A
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CN
China
Prior art keywords
optical fiber
combustion chamber
fiber bundle
flexible
flexible optical
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202411634609.4A
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Chinese (zh)
Inventor
陈爽
周全
雷庆春
李响
谭思洋
范玮
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Northwestern Polytechnical University
Equipment Design and Testing Technology Research Institute of China Aerodynamics Research and Development Center
Original Assignee
Northwestern Polytechnical University
Equipment Design and Testing Technology Research Institute of China Aerodynamics Research and Development Center
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Application filed by Northwestern Polytechnical University, Equipment Design and Testing Technology Research Institute of China Aerodynamics Research and Development Center filed Critical Northwestern Polytechnical University
Priority to CN202411634609.4A priority Critical patent/CN119437726A/en
Publication of CN119437726A publication Critical patent/CN119437726A/en
Pending legal-status Critical Current

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/04—Testing internal-combustion engines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/02—Details or accessories of testing apparatus
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/04—Testing internal-combustion engines
    • G01M15/10—Testing internal-combustion engines by monitoring exhaust gases or combustion flame

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Testing Of Engines (AREA)

Abstract

The invention discloses a three-dimensional high-speed measurement system of an aeroengine combustion chamber based on a flexible optical fiber bundle, which comprises a high-speed camera, a group of flexible optical fiber bundles and a plurality of high-temperature resistant endoscopes, wherein one end of each group of flexible optical fiber bundles is a parent optical fiber, the other end of each group of flexible optical fiber bundles is formed by a plurality of child optical fibers, the child optical fibers are connected with the plurality of high-temperature resistant endoscopes in a one-to-one correspondence manner, the plurality of high-temperature resistant endoscopes are uniformly arranged at the periphery of the combustion chamber to be measured and are inserted into the combustion chamber, and the high-speed camera is used for collecting signals of the parent optical fibers. The system adopts the flexible optical fiber bundle as the sensor, and can meet the requirements of the severe environment in the combustion chamber of the aero-engine. Meanwhile, the system adopts a single-camera high-speed three-dimensional imaging technology, and a plurality of high-speed cameras are not required to be synchronously controlled, so that the experiment cost and the synchronous control difficulty are reduced. The three-dimensional high-speed acquisition is realized, and meanwhile, the endoscope adopts a heat insulation and vibration resistance structure, can stably work for a long time in the combustion chamber of the aeroengine, and remarkably prolongs the service life of the aeroengine.

Description

Three-dimensional high-speed measurement system of aeroengine combustion chamber based on flexible optical fiber bundle
Technical Field
The invention relates to the field of experimental testing devices, in particular to a three-dimensional high-speed measuring system for an aeroengine combustion chamber based on a flexible optical fiber bundle.
Background
The combustion chamber is one of the core components of the engine, and the reliability, aggressiveness and life of the engine are largely dependent on the reliability and effectiveness of the combustion chamber. Therefore, the design level of the combustion chamber is improved, and the development of the combustion chamber with high combustion efficiency, high heat capacity intensity, small heat loss, less flow loss, stable combustion, reliable ignition, long service life, low pollutant discharge, high temperature rise and reasonable outlet temperature distribution is an important task in the development of modern high-performance aircrafts. The power propulsion system developed in China has a certain gap with foreign countries in thrust-weight ratio, combustion efficiency, power performance, pollution emission and the like. One of the key reasons is that the flow field in the propulsion system is a complex process involving chemical reaction flow and heat transfer interaction, and the lack of reliable and effective non-contact measurement technology leads to far insufficient understanding of basic phenomena and intrinsic laws of the flow field in the engine, which restricts the technical level of the engine. Therefore, the realization of multi-field and multi-parameter measurement of the flow field in the engine has important significance for deeply understanding the real state of the combustion chamber and optimizing and improving the performance of the engine.
At present, the traditional two-dimensional optical method, namely a path integration method and a plane measurement method, can lack relevant three-dimensional information to cause inaccurate measurement results. The three-dimensional tomography technology can overcome the limitation of low space-time resolution caused by scanning, and the three-dimensional parameter measuring capability of fuel concentration, combustion product component concentration and flame structure under different working conditions is formed. However, the conventional three-dimensional high-speed measurement requires a plurality of high-speed cameras, and has extremely high experimental cost and great difficulty in synchronous control. In addition, the interior of the combustion chamber of the aeroengine has the characteristics of high temperature, high pressure, strong vibration and the like, so that the three-dimensional high-speed measurement system is required to meet the requirements of high temperature resistance, high pressure resistance, strong stability, difficult damage and the like.
Therefore, there is a need to develop a three-dimensional high-speed measurement system for an aircraft engine combustion chamber based on flexible fiber bundles.
Disclosure of Invention
In view of the above, the present invention provides a three-dimensional high-speed measurement system for an aeroengine combustion chamber based on a flexible optical fiber bundle, which aims to solve the above technical problems.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
a three-dimensional high-speed measurement system of an aeroengine combustion chamber based on a flexible optical fiber bundle comprises a high-speed camera, a group of flexible optical fiber bundles and a plurality of high-temperature resistant endoscopes;
The group of flexible optical fiber bundles consists of a plurality of sub-optical fibers, wherein one end of each sub-optical fiber is a parent optical fiber, and the other end of each sub-optical fiber is connected with a plurality of high temperature resistant endoscopes in a one-to-one correspondence manner, and the plurality of high temperature resistant endoscopes are uniformly arranged at the periphery of a combustion chamber to be tested and are inserted into the combustion chamber;
the high-speed camera is used for collecting the mother optical fiber signals.
Further, the high temperature resistant endoscope comprises a sapphire window, a front lens barrel, a rear objective lens, a rear lens barrel and a cooling sleeve;
the front lens is arranged in the front lens barrel, and the installation position is adjusted in the front lens barrel according to the requirement of the angle of view;
The front end lens cone consists of a metal shell and an internal heat insulation material, and wraps an internal optical element;
The rear end lens barrel is connected with the front end lens barrel through threads, and the rear end lens barrel is composed of a metal shell and an internal heat insulation material;
The rear end lens is arranged in the rear end lens barrel, and the position of the rear end lens in the rear end lens barrel is adjusted according to the position of the front end lens;
The sub-optical fibers of the flexible optical fiber bundle are connected with the rear-end mirror cylinder through threads, and the optical signals of the combustion chamber are transmitted to the parent optical fibers of the flexible optical fiber bundle.
Further, the front lens is a wide angle lens.
Further, a cooling air channel and a cooling water channel are arranged in the cooling sleeve.
Further, the rear lens is a tele lens.
Further, the front end lens is consistent with the optical axis of the rear end lens.
Further, the high-speed camera is used for collecting the parent optical fiber signals and combining a three-dimensional chromatography algorithm to obtain the three-dimensional flow field characteristics inside the combustion chamber.
Compared with the prior art, the invention discloses a three-dimensional high-speed measuring system for the aero-engine combustion chamber based on the flexible optical fiber bundles, which adopts the flexible optical fiber bundles as sensors, has the characteristics of high temperature resistance, high pressure resistance, strong stability, difficult damage and the like, and can meet the requirements of the severe environment inside the aero-engine combustion chamber. Meanwhile, the system adopts a single-camera high-speed three-dimensional imaging technology, and a plurality of high-speed cameras are not required to be synchronously controlled, so that the experiment cost and the synchronous control difficulty are reduced. By the system, high-speed measurement of three-dimensional parameters such as fuel concentration, combustion product component concentration, flame structure and the like can be realized, and important basis is provided for understanding the real state of the combustion chamber in depth and optimizing and improving the performance of the engine.
The invention can perform three-dimensional high-speed acquisition on the radiation signals of the flame in the combustion chamber of the aero-engine under the conditions of low cost and low complexity. Meanwhile, the endoscope adopts a heat insulation and vibration resistance structure, can stably work for a long time in the combustion chamber of the aeroengine, and remarkably prolongs the service life of the aeroengine.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present invention, and that other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural diagram of a three-dimensional high-speed measurement system of an aero-engine combustion chamber based on a flexible optical fiber bundle.
Fig. 2 is a schematic structural view of the high temperature resistant endoscope provided by the invention.
The drawing illustrates that 1 is a high-speed camera, 2 is a flexible optical fiber bundle, 3 is a high-temperature-resistant endoscope, 4 is a combustion chamber, 5 is a sapphire window, 6 is a cooling sleeve, 7 is a front lens, 8 is a front lens barrel, 9 is a rear lens, and 10 is a rear lens barrel.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The embodiment of the invention discloses a three-dimensional high-speed measurement system of an aeroengine combustion chamber based on a flexible optical fiber bundle, which is shown by referring to fig. 1, wherein all parts of components are assembled according to the structure shown in fig. 1, the system comprises a high-speed camera 1, a group of flexible optical fiber bundles 2 and a plurality of high-temperature resistant endoscopes 3, the group of flexible optical fiber bundles 1 are composed of a plurality of sub-optical fibers with one ends being parent optical fibers and the other ends being in one-to-one correspondence with the plurality of high-temperature resistant endoscopes 3, the plurality of high-temperature resistant endoscopes 3 are uniformly arranged at the periphery of the combustion chamber to be measured and inserted into the combustion chamber 4, and the high-speed camera 1 is used for collecting parent optical fiber signals.
The high temperature resistant endoscope 3, referring to fig. 2, comprises a sapphire window 5, a cooling jacket 6, a front lens 7, a front lens barrel 8, a rear lens 9 and a rear lens barrel 10. The sapphire window 5 and the front lens 7 are sequentially arranged on one side of the front lens barrel 8, the front lens 7 is a wide-angle lens and is arranged in the front lens barrel, and the specific position of the front lens 7 can be adjusted in the front lens barrel according to the requirements of the angle of view.
The front end lens barrel 8 is composed of a metal shell and an internal heat insulation material and wraps an optical element in the front end lens barrel 8, the cooling sleeve 6 completely wraps the front end lens barrel 8 and is internally provided with a cooling air and cooling water channel, the rear end lens barrel 10 is connected with the front end lens barrel 8 through threads, the rear end lens barrel 10 is composed of the metal shell and the internal heat insulation material, the rear end lens 9 is a long focal lens and is arranged in the rear end lens barrel, the position of the rear end lens 9 in the rear end lens barrel 10 is adjusted according to the position of the front end lens 7, sub-optical fibers of the flexible optical fiber bundle are connected with the rear end lens barrel 10 through threads and transmit optical signals of the combustion chamber 4 to a mother optical fiber of the flexible optical fiber bundle, and the high-speed camera 1 is used for collecting the mother optical fiber signals of the flexible optical fiber bundle and combining a three-dimensional chromatography technology to obtain the three-dimensional flow field characteristics in the combustion chamber.
The front end lens barrel formed by the metal shell, the internal heat insulation material and the cooling sleeve can continuously work in a high-temperature high-pressure environment, and internal optical elements are protected. The sapphire glass is used as an optical window of the front-end lens barrel, so that the inner lens can be effectively protected under the high-temperature and high-pressure condition. The positions of the front end lens and the rear end lens in the lens barrel can be adjusted according to the actual measured field angle requirement.
As shown in fig. 1, the endoscope and the flexible optical fiber bundle are combined, and optical signals in the combustion chambers with different angles are synchronously converged to the mother optical fiber of the flexible optical fiber bundle through the child optical fibers of the flexible optical fiber bundle. And combining the high-speed camera with the flexible optical fiber bundle, and directly acquiring the mother optical fiber signals of the flexible optical fiber bundle by using a single high-speed camera, so that the child optical fiber signals of all the flexible optical fiber bundles can be synchronously acquired.
Working principle:
The high temperature resistant endoscopes 3 are inserted into the combustion chamber 4 of the aeroengine along different angles, the sapphire window 5 is arranged at the front end of the front end lens barrel 8, flame radiation enters the front end lens barrel 8 from the sapphire window 5, the first imaging is completed through the front end lens 7, then the flame radiation reaches the sub-optical fibers of the flexible optical fiber bundle 2 after the second imaging through the rear end lens 9, the sub-optical fibers of the flexible optical fiber bundles transmit the flame radiation signals to the mother optical fibers of the flexible optical fiber bundles, and finally the high speed camera 1 is used for collecting signals of the mother optical fibers of the flexible optical fiber bundles.
The three-dimensional high-speed measurement system for the aero-engine combustion chamber based on the flexible optical fiber bundle has the advantages of three-dimensional high-speed imaging capability, high measurement stability and long service life, can be applied to the field of experimental tests, and can be used for three-dimensional high-speed acquisition of radiation signals of flame in the aero-engine combustion chamber at low cost and low complexity. Meanwhile, the endoscope adopts a heat insulation and vibration resistance structure, can stably work for a long time in the combustion chamber of the aeroengine, and remarkably prolongs the service life of the aeroengine.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other. For the device disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant points refer to the description of the method section.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (7)

1. A three-dimensional high-speed measurement system of an aeroengine combustion chamber based on a flexible optical fiber bundle is characterized by comprising a high-speed camera, a group of flexible optical fiber bundles and a plurality of high-temperature resistant endoscopes;
The group of flexible optical fiber bundles consists of a plurality of sub-optical fibers, wherein one end of each sub-optical fiber is a parent optical fiber, and the other end of each sub-optical fiber is connected with a plurality of high temperature resistant endoscopes in a one-to-one correspondence manner, and the plurality of high temperature resistant endoscopes are uniformly arranged at the periphery of a combustion chamber to be tested and are inserted into the combustion chamber;
the high-speed camera is used for collecting the mother optical fiber signals.
2. The three-dimensional high-speed measurement system of the aeroengine combustion chamber based on the flexible optical fiber bundle, which is disclosed in claim 1, is characterized in that the high-temperature resistant endoscope comprises a sapphire window, a front lens barrel, a rear objective lens, a rear lens barrel and a cooling sleeve;
the front lens is arranged in the front lens barrel, and the installation position is adjusted in the front lens barrel according to the requirement of the angle of view;
The front end lens cone consists of a metal shell and an internal heat insulation material, and wraps an internal optical element;
The rear end lens barrel is connected with the front end lens barrel through threads, and the rear end lens barrel is composed of a metal shell and an internal heat insulation material;
The rear end lens is arranged in the rear end lens barrel, and the position of the rear end lens in the rear end lens barrel is adjusted according to the position of the front end lens;
The sub-optical fibers of the flexible optical fiber bundle are connected with the rear-end mirror cylinder through threads, and the optical signals of the combustion chamber are transmitted to the parent optical fibers of the flexible optical fiber bundle.
3. A three-dimensional high-speed measurement system for an aircraft engine combustion chamber based on a flexible fiber bundle according to claim 2, wherein the front lens is a wide-angle lens.
4. A three-dimensional high-speed measurement system for an aircraft engine combustion chamber based on flexible fiber optic bundles according to claim 2, wherein said cooling jacket has cooling air and cooling water passages therein.
5. A three-dimensional high-speed measurement system for an aircraft engine combustion chamber based on a flexible fiber bundle according to claim 2, wherein the rear lens is a tele lens.
6. A three-dimensional high-speed measurement system for an aircraft engine combustion chamber based on a flexible fiber bundle according to claim 2, wherein the front lens coincides with the optical axis of the rear lens.
7. The three-dimensional high-speed measurement system for the combustion chamber of the aeroengine based on the flexible optical fiber bundle, as claimed in claim 1, wherein the high-speed camera is used for collecting the parent optical fiber signals and combining a three-dimensional chromatography algorithm to obtain the three-dimensional flow field characteristics inside the combustion chamber.
CN202411634609.4A 2024-11-15 2024-11-15 A three-dimensional high-speed measurement system for aircraft engine combustion chamber based on flexible optical fiber bundle Pending CN119437726A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202411634609.4A CN119437726A (en) 2024-11-15 2024-11-15 A three-dimensional high-speed measurement system for aircraft engine combustion chamber based on flexible optical fiber bundle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202411634609.4A CN119437726A (en) 2024-11-15 2024-11-15 A three-dimensional high-speed measurement system for aircraft engine combustion chamber based on flexible optical fiber bundle

Publications (1)

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CN119437726A true CN119437726A (en) 2025-02-14

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