Method for testing wall temperature distribution of aero-engine combustion chamber

Abstract

The invention discloses a method for testing wall temperature distribution of an aero-engine combustion chamber. The aero-engine combustion chamber wall temperature distribution test method comprises the following steps: coating the inner wall of a combustion chamber with a temperature indicating paint, and carrying out a first combustion test to obtain a global temperature measurement result; whether hot spots exist or not is judged according to the global temperature measurement result, and if yes, the structure of the combustion chamber is adjusted; and after the structure of the combustion chamber is adjusted, a temperature measurement structure is arranged at the distribution position of the hot spots, and a second combustion test is carried out to obtain a local temperature measurement result. According to the wall temperature distribution test method, the research and development efficiency of the combustion chamber is improved.

Description

Technical Field

[0001] The present application relates to the technical field of aero-engines, and in particular to a test method for the wall temperature distribution of a combustion chamber of an aero-engine. Background Art

[0002] The combustion chamber of an aircraft engine is the core hot end component of the engine. During its development, the design and testing must be closely coordinated to quickly and accurately meet the design requirements and ensure the successful development of the entire engine product. The design and testing coordination process of the combustion chamber is generally carried out after the combustion chamber design plan is initially determined, and a large number of performance verification tests are carried out and the design plan is iteratively modified based on the test results.

[0003] The combustion chamber wall temperature distribution performance, as a core test item in the early stage of combustion chamber design, can reflect the collaborative process of design and testing. How to improve the test and design process of combustion chamber wall temperature distribution performance is a technical problem that needs to be solved urgently.

[0004] It should be noted that the statements in this background technology section only provide background technology related to the present application and do not necessarily constitute prior art. Summary of the invention

[0005] The present application provides a test method for the wall temperature distribution of an aircraft engine combustion chamber to improve the research and development efficiency of the combustion chamber.

[0006] The present application provides a test method for the wall temperature distribution of an aircraft engine combustion chamber, comprising the following steps:

[0007] Apply temperature-indicating paint on the inner wall of the combustion chamber and conduct the first combustion test to obtain global temperature measurement results;

[0008] Determine whether there is a hot spot based on the global temperature measurement results, and if there is a hot spot, adjust the structure of the combustion chamber;

[0009] After adjusting the structure of the combustion chamber, a temperature measurement structure is set at the distribution position of the hot spots and a second combustion test is carried out to obtain local temperature measurement results.

[0010] In some embodiments, the test method further includes: if it is determined based on the global temperature measurement result that no hot spot exists, then there is no need to adjust the structure of the combustion chamber.

[0011] In some embodiments, adjusting the structure of the combustion chamber includes adjusting the aerodynamic structure of the combustion chamber.

[0012] In some embodiments, adjusting the aerodynamic structure of the combustion chamber includes adjusting the fuel injection method and / or the arrangement of the spray holes of the combustion chamber.

[0013] In some embodiments, adjusting the structure of the combustion chamber includes: adjusting the cooling structure of the combustion chamber.

[0014] In some embodiments, arranging a temperature measuring structure at the distribution position of hot spots includes: arranging a thermocouple or a temperature measuring crystal at the distribution position of hot spots for local temperature measurement.

[0015] In some embodiments, the test method further includes obtaining the temperature gradient of each part in the burner according to the global temperature measurement result, and adjusting the structure of the combustion chamber according to the temperature gradient and the actual hot spot distribution.

[0016] In some embodiments, the test method further includes, after obtaining the local temperature measurement result, comparing and analyzing the global temperature measurement result and the local temperature measurement result, and further adjusting the structure of the combustion chamber according to the comparison and analysis result.

[0017] Based on the technical solution provided by the present application, a test method for the wall temperature distribution of an aero-engine combustion chamber includes the following steps: coating a temperature indicating paint on the inner wall of the combustion chamber and conducting a first combustion test to obtain a global temperature measurement result; judging whether there are hot spots according to the global temperature measurement result, and if there are hot spots, adjusting the structure of the combustion chamber; after adjusting the structure of the combustion chamber, arranging a temperature measuring structure at the distribution position of hot spots and conducting a second combustion test to obtain a local temperature measurement result. The test method for the wall temperature distribution of the aero-engine combustion chamber in the embodiments of the present application, after obtaining the preliminary design scheme of the combustion chamber, does not conduct a simulation test, directly coats a temperature indicating paint on the inner wall of the combustion chamber of the preliminary design scheme and conducts a first combustion test to obtain a global temperature measurement result. If there are hot spots in the global temperature measurement result, directly adjust the structure of the combustion chamber. After adjustment, conduct a second test on the adjusted combustion chamber. During the second test, only arrange a local temperature measuring structure at the hot spot area position of the global temperature measurement result, so as to verify whether the temperature of the hot spot area of the adjusted combustion chamber structure has been improved. It can be seen that the test method for the wall temperature distribution in the embodiments of the present application only needs to go through three stages of "preliminary test - design modification - test verification", thereby improving the R & D efficiency of the combustion chamber.

[0018] Through the following detailed description of the exemplary embodiments of the present application with reference to the accompanying drawings, other features and advantages of the present application will become clear. Description of the Drawings

[0019] The accompanying drawings described herein are used to provide a further understanding of the present application, and constitute a part of the present application. The schematic embodiments of the present application and their descriptions are used to explain the present application, and do not constitute an improper limitation to the present application. In the drawings:

[0020] Figure 1 It is a schematic diagram of the principle of the test method for the wall temperature distribution of the aero-engine combustion chamber in the embodiments of the present application. Detailed implementation manners

[0021] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The description of at least one exemplary embodiment is actually only illustrative and in no way restrictive of the present application and its application or use. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts belong to the scope of protection of the present application.

[0022] Unless otherwise specifically stated, the relative arrangements of components and steps, numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present application. At the same time, it should be understood that, for the sake of description, the dimensions of the various parts shown in the drawings are not drawn in actual proportional relationships. Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and devices should be regarded as part of the description. In all the examples shown and discussed here, any specific value should be construed as merely exemplary and not as a limitation. Therefore, other examples of the exemplary embodiments may have different values. It should be noted that like reference numerals and letters denote like items in the following drawings, and thus, once an item is defined in one drawing, it does not need to be further discussed in subsequent drawings.

[0023] For the sake of description, spatial relative terms, such as "above...", "on top of...", "on the upper surface of...", "above", etc., may be used here to describe the spatial positional relationship of one device or feature to another device or feature as shown in the drawings. It should be understood that the spatial relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the drawings. For example, if the device in the drawing is inverted, the device described as "above other devices or structures" or "on top of other devices or structures" will then be positioned "below other devices or structures" or "beneath other devices or structures". Thus, the exemplary term "above..." can include both the orientation of "above..." and "below...". The device may also be positioned in other different ways, and corresponding interpretations should be made for the spatial relative descriptions used here.

[0024] In some embodiments, in the initial stage of the combustion chamber design, for the test and design iteration scheme of the combustion chamber wall temperature distribution, the designer first conducts CFD (Computational Fluid Dynamics) simulation calculations on the temperature distribution to obtain the predicted temperature distribution and predicted hot spot areas on the combustion chamber wall. Then, the tester applies temperature indicating paint on the combustion chamber wall for global temperature monitoring and arranges thermocouples in the predicted hot spot areas for temperature monitoring. The combustion chamber wall temperature distribution test carried out in this way can not only obtain the overall temperature distribution of the combustion chamber wall better, but also conduct local temperature monitoring for the relatively critical hot spot areas. After obtaining the test results, the designer modifies the design scheme according to the test results and then verifies the performance of the modified scheme, and finally determines the final combustion chamber design scheme.

[0025] However, due to the complexity of the flow and combustion processes in the combustion chamber, the reliability of the CFD simulation calculation results of the temperature distribution is not high, and there are often hot spots outside the hot spot areas predicted by the simulation results in the test results. To overcome this problem, generally, multiple tests are used to determine the hot spot positions or temperature indicating paint temperature measurement and thermocouple temperature measurement are arranged simultaneously in each test. However, this makes the iteration of the test and design go through at least four stages: "initial test - re-test - design modification - test verification", and the test needs to repeat the test wiring of the thermocouple and the spraying of the temperature indicating paint, which greatly prolongs the development cycle of the combustion chamber and increases the expenditure of the test funds.

[0026] In order to shorten the R & D cycle and improve the R & D efficiency, the embodiment of the present application proposes a test method for the combustion chamber wall temperature distribution of an aeroengine. After obtaining the preliminary design scheme of the combustion chamber, in the first test, only temperature indicating paint testing is used to obtain the inner wall temperature distribution of the combustion chamber, and the design scheme is directly iterated according to the results of the first test. In the re-test, only local thermocouple temperature measurement or crystal temperature measurement is arranged in the hot spot temperature areas of the first test. This makes the iteration of the test and design only go through three stages: "preliminary test - design modification - test verification", saving at least one test cycle, one test wiring cycle and the corresponding costs, and greatly improving the overall efficiency of the combustion chamber R & D.

[0027] Reference Figure 1 , the embodiment of the present application provides a test method for the combustion chamber wall temperature distribution of an aeroengine, including the following steps:

[0028] Step 210, coat the inner wall of the combustion chamber with temperature indicating paint and conduct the first combustion test to obtain the global temperature measurement result;

[0029] Step 220, judge whether there are hot spots according to the global temperature measurement result. If there are hot spots, adjust the structure of the combustion chamber;

[0030] Step 230, after adjusting the structure of the combustion chamber, a temperature measurement structure is set at the distribution position of the hot spots and a second combustion test is carried out to obtain local temperature measurement results.

[0031] In the test method for the wall temperature distribution of the aero-engine combustion chamber according to the embodiment of the present application, after obtaining the preliminary design scheme of the combustion chamber, instead of carrying out a simulation test, a temperature indicating paint is directly coated on the inner wall of the combustion chamber of the preliminary design scheme and a first combustion test is carried out to obtain the global temperature measurement results. If there are hot spots in the global temperature measurement results, the structure of the combustion chamber is directly adjusted. After the adjustment, a second test is carried out on the adjusted combustion chamber. During the second test, only a local temperature measurement structure is set at the hot spot area position of the global temperature measurement results, so as to verify whether the temperature of the hot spot area of the adjusted combustion chamber structure has been improved. It can be seen that the test method for the wall temperature distribution according to the embodiment of the present application only needs to go through three stages of "preliminary test - design modification - test verification", thereby improving the R & D efficiency of the combustion chamber.

[0032] The inventor of the present application found that the simulation results were inaccurate. Therefore, after obtaining the preliminary design scheme of the engine, instead of carrying out a simulation, a combustion test is directly carried out. Moreover, during the first combustion test, only global temperature measurement is carried out to obtain the hot spot distribution, and then the design scheme of the engine is directly modified and adjusted according to the hot spot distribution. After the adjustment, a second combustion test is carried out on the engine, and a local temperature measurement structure is used to measure the temperature of the hot spot area to verify whether the adjustment of the design scheme is effective.

[0033] In some embodiments, the test method further includes: if it is determined according to the global temperature measurement results that there are no hot spots, there is no need to adjust the structure of the combustion chamber. That is to say, if it is found during the first combustion test that there are no hot spots on the inner wall temperature of the combustion chamber, there is no need to adjust the structure of the combustion chamber. Then, at this time, the design scheme of the structure of the combustion chamber is the final scheme.

[0034] In the description of the embodiment of the present application, the purpose of adjusting the structure of the combustion chamber is mainly to adjust the wall temperature distribution of the combustion chamber so that there are no hot spots on the inner wall of the combustion chamber. Therefore, when adjusting the structure of the combustion chamber, mainly those structures that affect the temperature adjustment of the combustion chamber are adjusted. That is to say, the reasons for the appearance of hot spots need to be analyzed to adaptively adjust the structure of the combustion chamber.

[0035] The temperature indicating paint is a kind of paint sensitive to temperature and can display the highest temperature experienced.

[0036] In some embodiments, adjusting the structure of the combustion chamber includes: adjusting the aerodynamic structure of the combustion chamber. Specifically, adjusting the aerodynamic structure of the combustion chamber includes adjusting the fuel injection mode and / or the nozzle arrangement of the combustion chamber.

[0037] In some other embodiments, adjusting the structure of the combustion chamber includes: adjusting the cooling structure of the combustion chamber. For example, making corresponding adjustments to the distribution path of the cooling channels in the combustion chamber.

[0038] During the second combustion test, it is mainly to verify the adjusted structure of the combustion chamber, that is, to verify whether the previous hot spot areas have been improved or reduced. In some embodiments, setting a temperature measurement structure at the distribution position of the hot spots includes: setting a thermocouple or a temperature measurement crystal at the distribution position of the hot spots for local temperature measurement. Setting a thermocouple or a temperature measurement crystal at the distribution position of the hot spots for local temperature measurement to confirm the improvement of the temperature distribution of the modification plan.

[0039] In some embodiments, the test method further includes obtaining the temperature gradient of each part in the burner according to the global temperature measurement result. And adjusting the structure of the combustion chamber according to the temperature gradient and the actual hot spot distribution. That is, during the first combustion test, the temperature gradient and local hot spot information are obtained through the color distribution of the temperature indicating paint. In this way, by comprehensively analyzing the temperature gradient and local hot spot information, it provides guidance for adjusting the design plan, which can reduce the number of tests and further improve the test and R & D efficiency.

[0040] In some embodiments, the test method further includes, after obtaining the local temperature measurement result, comparing and analyzing the global temperature measurement result and the local temperature measurement result, and further adjusting the structure of the combustion chamber according to the comparison and analysis result. That is, after obtaining the local temperature measurement result, if there are still hot spots, then the design plan of the engine structure needs to be further adjusted.

[0041] The test method for the combustion chamber wall temperature distribution in the efficient collaborative design and test process proposed by the embodiments of the present application is as follows:

[0042] After the designers complete the preliminary design scheme, there is no need to carry out CFD numerical simulation analysis anymore. Instead, directly conduct the first test to carry out the combustion chamber wall temperature distribution test in the preliminary design scheme stage. For the first test, only thermochromic paint testing is required, and there is no need to measure the temperature of the combustion chamber wall with thermocouples. In this way, the test wiring cycle and cost can be directly saved. After the first test is completed, the global temperature distribution of the inner wall of the combustion chamber, including the temperature gradients and local hot spot information of each part, can be obtained based on the thermochromic paint test results. The designers directly modify the design scheme according to the results of the first test. After the modified scheme is completed, conduct the second test. In the second test, only local thermocouples or crystal temperature measurement are arranged in the hot spot areas of the first test, and there is no need to spray thermochromic paint again. Based on the results of the second test, the designers can analyze the improvement of the modified scheme on the hot spots of the combustion chamber wall temperature and confirm the next step of work. In this way, the entire test and design scheme iteration process only needs to go through three stages: "first test - design modification - second test", saving at least one test cycle, one test wiring cycle and the corresponding costs, and greatly improving the overall efficiency of combustion chamber research and development.

[0043] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application and not to limit them; although the present application has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that: still can modify the specific implementation manners of the present application or make equivalent replacements for some technical features; without departing from the spirit of the technical solutions of the present application, they should all be covered within the scope of the technical solutions claimed in the present application.

Claims

1. A test method for the wall temperature distribution of an aero-engine combustion chamber, characterized in that, it comprises the following steps: Coat the inner wall of the combustion chamber with temperature indicating paint and conduct the first combustion test to obtain the global temperature measurement result; Judge whether there is a hot spot according to the global temperature measurement result. If there is a hot spot, adjust the structure of the combustion chamber; After adjusting the structure of the combustion chamber, set up a temperature measurement structure at the distribution position of the hot spot and conduct the second combustion test to obtain the local temperature measurement result.

2. The test method for the wall temperature distribution of an aero-engine combustion chamber according to claim 1, characterized in that, the test method further comprises: if it is judged that there is no hot spot according to the global temperature measurement result, there is no need to adjust the structure of the combustion chamber.

3. The test method for the wall temperature distribution of an aero-engine combustion chamber according to claim 1, characterized in that, the adjustment of the structure of the combustion chamber includes: adjusting the aerodynamic structure of the combustion chamber.

4. The test method for the wall temperature distribution of an aero-engine combustion chamber according to claim 3, characterized in that, the adjustment of the aerodynamic structure of the combustion chamber includes adjusting the fuel injection mode and / or the nozzle arrangement of the combustion chamber.

5. The test method for the wall temperature distribution of an aero-engine combustion chamber according to claim 1, characterized in that, the adjustment of the structure of the combustion chamber includes: adjusting the cooling structure of the combustion chamber.

6. The test method for the wall temperature distribution of an aero-engine combustion chamber according to claim 1, characterized in that, setting up a temperature measurement structure at the distribution position of the hot spot includes: setting up a thermocouple or a temperature measurement crystal at the distribution position of the hot spot for local temperature measurement.

7. The test method for the wall temperature distribution of an aero-engine combustion chamber according to claim 1, characterized in that, the test method further comprises obtaining the temperature gradient of each part in the burner according to the global temperature measurement result, and adjusting the structure of the combustion chamber according to the temperature gradient and the actual hot spot distribution.

8. The test method for the wall temperature distribution of an aero-engine combustion chamber according to claim 1, characterized in that, the test method further comprises, after obtaining the local temperature measurement result, comparing and analyzing the global temperature measurement result and the local temperature measurement result, and further adjusting the structure of the combustion chamber according to the comparison and analysis result.

Images