Fuel compatibility verification method and system

Abstract

The invention provides a fuel compatibility verification method. The method comprises the following steps: selecting any fuel type and test piece material; determining a test temperature, wherein the test temperature is the highest temperature of the test piece applied to the aviation product; determining test items for the test piece, wherein the test items comprise necessary test items and optional test items; testing is conducted, a test result is obtained, and when the material is metal, the test result shows that the test piece is not corroded or discolored, and it is judged that the fuel oil is compatible with the test piece; and when the material is a non-metallic material, the test result shows that the performance of the non-metallic material can still meet the value required by the preset function after the compatibility test, and judging that the fuel oil is compatible with the test piece. The invention further provides a fuel compatibility verification system. According to the method and the system, automatic design of compatibility tests of different application scenes, compatibility data processing and conclusion judgment can be realized.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, and more specifically to the field of aviation fuel compatibility testing. Background Technology

[0002] Fuel compatibility refers to the characteristics of the interaction and influence between aviation fuel and the materials it comes into contact with. Generally speaking, if aviation fuel exhibits neither a chemical reaction nor a significant physical effect upon contact with materials, its compatibility is good. Conversely, if aviation fuel causes significant corrosion or changes in fuel quality after contact with materials, its compatibility is poor. Poor fuel compatibility can lead to significant safety issues for engines. Currently, there are hundreds of commonly used materials and dozens of types of aviation fuel in aero engines, as well as numerous engine models. Compatibility verification procedures vary; therefore, a systematic verification method is needed to systematically verify the compatibility of aviation fuels. Summary of the Invention

[0003] One object of the present invention is to provide a method for verifying the compatibility of aviation fuels.

[0004] The fuel compatibility verification method for achieving the above objectives includes the following steps: selecting any type of fuel and material of the test piece; determining the test temperature, which is the highest temperature at which the test piece is used in aviation products; determining the test items for the test piece, including mandatory test items and optional test items; conducting the test and obtaining the test results. When the material is metallic, if the test results show that the test piece does not show corrosion or discoloration, it is determined that the fuel is compatible with the test piece. When the material is non-metallic, if the test results show that the performance of the non-metallic material still meets the predetermined functional requirements after the compatibility test, it is determined that the fuel is compatible with the test piece.

[0005] In one or more embodiments, the method further includes the following steps: constructing a matrix of fuel types and test specimen materials, and selecting a fuel type and test specimen material in the matrix for testing.

[0006] In one or more embodiments, tests are conducted to complete all matching schemes of fuel type and test piece material in the matrix.

[0007] In one or more embodiments, the mandatory test items include one or more of the following: surface inspection, microscopic inspection, hardness test, volume expansion rate test, elongation at break test, tensile strength test, and peel strength test.

[0008] In one or more embodiments, the optional test items include one or more of the following: hardness test, tensile strength test, fatigue performance test, and peel strength test.

[0009] In one or more embodiments, the material is metal, rubber, composite material, or graphite.

[0010] In one or more embodiments, the fuel type is a novel fuel type not used in engines, and multiple test results are obtained for this novel fuel and different test specimen types and materials. Based on this, the multiple test results are compared with data from fuels already used in engines and the same test specimen type and material.

[0011] In one or more embodiments, the test specimen is made of a novel material not previously used in engines, and the compatibility test results of the novel material with the reference fuel of the aero-engine are obtained.

[0012] In one or more embodiments, the fuel compatibility verification method further includes a risk rating step: comparing the test results of rubber test specimens with the fuel compatibility evaluation criteria for rubber materials to determine the risk level; or comparing the test results of metal test specimens with the fuel compatibility evaluation criteria for metal materials to determine the risk level; or comparing the test results of test specimens of materials other than rubber and metal with the fuel compatibility evaluation criteria for other materials to determine the risk level.

[0013] In one or more embodiments, the fuel compatibility verification method further includes a fuel compatibility rating step: based on the test results, if a type of fuel and material can be used normally at temperatures of 150°C and above, the fuel and material are determined to be Class I compatible; if the type of fuel and material can be used normally within a temperature range of 100°C to 150°C, the fuel and material are determined to be Class II compatible; if the type of fuel and material can be used normally within a temperature range of room temperature to 100°C, the fuel and material are determined to be Class III compatible; if the type of fuel and material cannot be used in room temperature and high temperature environments, the fuel and material are determined to be incompatible.

[0014] Another object of the present invention is to provide a fuel compatibility verification system for performing the above-mentioned aviation fuel compatibility verification method. The system includes a database, functional modules, and an editor. The database contains a temperature list, fuel type information, and test specimen material information. The functional modules include a compatibility test control module, which includes a fuel verification submodule and a material verification submodule. The editor is used to edit the functional modules and the database.

[0015] The aforementioned fuel compatibility verification method establishes the compatibility test temperature and criteria determination principles, and proposes the concept and method for fuel and material compatibility rating. Currently, there are hundreds of commonly used materials in aero engines and dozens of types of aviation fuel. This method can make the compatibility verification process the same for all materials, ensure the universality of compatibility data, and provide a unified standard for the determination of test conclusions. Furthermore, it can continuously update the compatibility test process and judgment criteria according to industry development.

[0016] For the research and development of new aviation fuels and aviation materials, the above-mentioned fuel compatibility verification methods can be used to realize the automatic design of compatibility tests for different application scenarios, the processing of compatibility data and the determination of conclusions. It can also complete the design of compatibility tests for new materials and new fuels. The determination of test conclusions and compatibility data are universal. The results of comparison with the compatibility data of similar materials and reference fuels can serve as important reference data when using new materials. Attached Figure Description

[0017] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, wherein:

[0018] Figure 1 This is a flowchart of the fuel compatibility verification method;

[0019] Figure 2 This is a flowchart of a specific embodiment of the fuel compatibility verification method;

[0020] Figure 3 This is a schematic diagram of a fuel compatibility verification system;

[0021] Figure 4 This is a flowchart illustrating the steps involved in risk level assessment.

[0022] Figure 5 This is a flowchart illustrating the steps involved in the overall risk level assessment process. Detailed Implementation

[0023] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0024] It should be noted that these and other accompanying drawings are merely examples and are not drawn to scale, and should not be construed as limiting the scope of protection of the present invention.

[0025] Civil aircraft engines must meet relevant airworthiness regulations to obtain type certificates. Currently, the main international airworthiness authorities include the U.S. Federal Aviation Administration (FAA), the European Aviation Safety Agency (EASA), and the Civil Aviation Administration of China (CAAC), whose corresponding engine airworthiness regulations are FAR Part 33, CS-E, and CCAR-33, respectively.

[0026] FAR / CCAR 33.7 Engine Ratings and Usage Restrictions specifies requirements for determining and verifying aviation fuel grades or specifications. The CS-E regulations also contain substantive requirements related to aviation fuel verification. Advisory Circular AC 20-24D, "Approval of Powerplant Fuels, Additives and Lubricants," also sets forth requirements for fuel and material compatibility verification.

[0027] There are no unified standards or procedures for verifying the compatibility of aviation fuels. For example, ASTM D4054 in the United States is a standard practice for the approval of new fuels and additives. The scope of application and guidance of the compatibility concept and verification approach proposed in it are not very applicable to the current development status and needs of the domestic civil aviation products, fuels and materials industries.

[0028] However, this standard provides guidance for the approval of a completely new fuel or additive. The fuel under test is a new oil that has not yet obtained fuel specification approval after development. The performance of the new fuel is determined by the results of compatibility tests with typical materials. However, its benchmark fuel specifications are not applicable to the current state of my country's fuel industry. The scope of application of this standard means that the guidance in it is not applicable to the development and certification needs of domestic civil aviation products. Second, there are inconsistencies in the selection of typical materials that come into contact with aviation products and fuel, as well as inconsistencies in the actual application temperature of the materials. Third, it does not clarify the method for extending the existing fuel compatibility test criteria for non-metallic materials to the same type of materials, nor does it provide the criteria for passing the fuel compatibility test for metallic materials.

[0029] Fuel compatibility verification is a comprehensive technical issue involving fuel system design, engine material selection, and fuel selection; its verification is also a complex problem that crosses these three dimensions. For different fuel system design conditions, engine material selections, and fuel selections, implementing verification one by one is costly, time-consuming, and leads to data governance challenges and resource waste due to repeated verification. For example, the selection of new fuels, new engine materials, and changes in the design temperature of new engine fuel systems all present fuel-material compatibility issues, requiring verification for each case, resulting in high costs, long cycles, and the inability to share and utilize data.

[0030] Based on this, the present invention proposes an aviation fuel compatibility verification method, which can determine the design specifications for compatibility tests in different application scenarios and realize the processing of compatibility data and the determination of conclusions.

[0031] Reference Figure 1 and Figure 2 The method includes the following steps: selecting any type of fuel and material for the test specimen, and conducting the following tests; determining the test temperature, which, to verify the rationality of the fuel and material selection for aviation products, is based on the highest actual application temperature of the material in contact with the fuel in the aviation product, including transient temperatures. In some embodiments, to verify the development of new fuels and materials, the compatibility test temperature can be set to multiple temperature points such as room temperature, 100°C, and 150°C; determining the test items for the test specimen, including mandatory and optional test items; conducting the tests and obtaining the test results. When the material is metallic, if the test results show that the test specimen does not show corrosion or discoloration, the fuel is considered compatible with the test specimen. When the material is non-metallic, if the material properties still meet the predetermined functional requirements after the compatibility test, the fuel is considered compatible with the test specimen. The predetermined functional requirements can be derived from the design requirements of the product to which the material is applied, or can be derived from the corresponding material specifications. Material specifications include, but are not limited to, national standards, American standards, and enterprise standards.

[0032] Preferably, a matrix can be constructed first regarding fuel type and test specimen material; then, combinations of fuel type and test specimen material can be selected from the matrix. After completing the test for that type of fuel and test specimen, the above steps can be repeated to complete the test for all matching schemes of fuel type and test specimen material in the matrix at once, obtaining complete fuel compatibility verification results.

[0033] The compatibility of aviation products with fuels involves a wide variety of materials. Table 1 shows the materials and categories of some test specimens.

[0034] Table 1. List of Materials for Aeronautical Test Components

[0035] Serial Number Material Category Material grade 1 Structural steel UNS S30400 2 Structural steel 17-4PH 3 Structural steel 1Cr13 4 Structural steel 45 steel 5 aluminum alloy 2618-T61 6 Cast aluminum C335.0-T6 7 Titanium alloy TC4 8 copper alloy C93700 9 AlNiCo alloy LNGT72 10 rubber PTFE 11 rubber 5080 12 rubber SFB-2 13 graphite M233H 14 Composite materials FC-5A 15 Composite materials PF1-1

[0036] The mandatory test items in the experimental program include one or more of the following: surface inspection, microscopic inspection, hardness test, volume expansion rate test, elongation at break test, tensile strength test, and peel strength test. Optional test items include one or more of the following: hardness test, tensile strength test, fatigue performance test, and peel strength test.

[0037] The test items before and after the compatibility test are determined according to the type and failure mode of the material in contact with the fuel. Please refer to Table 2 below.

[0038] Table 2: Reference Table for Test Items

[0039]

[0040]

[0041] This method also provides a unified basis for determining the compatibility test temperature and gives principles for determining test criteria for the vast majority of materials. The compatibility test between fuel and materials involves a wide variety of materials. Specifically, the principles for determining test criteria can be divided into two categories: metallic materials show no obvious corrosion or discoloration after the compatibility test; non-metallic materials still meet the material properties specified in the material standards and still meet the design requirements of aerospace products after the compatibility test.

[0042] Based on the above embodiments, the fuel compatibility test process can also include a more detailed scheme: 1) determining the test specimen and test fuel; 2) determining the test items; 3) determining the test conditions; 4) pre-test inspection and testing; 5) test implementation; 6) post-test inspection and testing; 7) test data processing; 8) risk level assessment / compatibility rating.

[0043] The following is based on Figure 4 The flowchart shown introduces the complete fuel compatibility test procedure.

[0044] First, based on the characteristics such as structural form and surface process, the test specimen and test oil are determined. Then, based on the type, failure mode, and structural form of the material in contact with the fuel, the test items before and after the compatibility test are determined. Referring to the examples recorded in Table 2, the processing requirements and quantity requirements of the test specimen can be determined.

[0045] Subsequently, based on the operating temperature or set temperature, the test conditions are determined, such as the test temperature, duration, and equipment requirements. Pre-test checks, tests, and final implementation are then conducted. The test specimens are subjected to prolonged contact and immersion in the test oil, and mandatory and optional tests are performed to obtain pre-test performance data, surface data, and microscopic data.

[0046] After the test, post-test performance measurements, surface evaluation, and microscopic evaluation are performed. The data obtained from the test is then processed, and can be combined with pre-test performance data for a comprehensive assessment. Based on the principles for determining test criteria and rating standards, a risk level assessment / compatibility rating is given.

[0047] For example, the specific steps for fuel compatibility rating are as follows:

[0048] If aviation fuel can be used normally with a material at temperatures of 150°C and above, then the fuel and the material are classified as Class I compatible; if aviation fuel can be used normally with a material within a temperature range of 100°C to 150°C, then the fuel and the material are classified as Class II compatible; if aviation fuel can be used normally with a material within a temperature range of room temperature to 100°C, then the fuel and the material are classified as Class III compatible. If aviation fuel cannot be used with a material in room temperature or high-temperature environments, then the fuel and the material are classified as incompatible.

[0049] The specific steps for assessing the fuel compatibility risk level of different materials are as follows: the risk level is determined by comparing the test results of rubber test specimens with the fuel compatibility assessment criteria for rubber materials; or the risk level is determined by comparing the test results of metal test specimens with the fuel compatibility assessment criteria for metal materials; or the risk level is determined by comparing the test results of test specimens of materials other than rubber and metal with the fuel compatibility assessment criteria for other materials.

[0050] Specifically, for rubber materials, this method proposes a fuel compatibility evaluation criterion for rubber materials, as shown in Table 3 below.

[0051] Table 3. Risk Level Assessment Criteria for Fuel Compatibility of Rubber Materials

[0052]

[0053]

[0054] For metallic materials, this method proposes a fuel compatibility evaluation criterion for metallic materials, as shown in Table 4 below.

[0055] Table 4. Risk Level Assessment Criteria for Fuel Compatibility of Metallic Materials

[0056]

[0057] For materials other than rubber and metal, this method proposes a fuel compatibility evaluation criterion for other materials, as shown in Table 5.

[0058] Table 5. Risk Level Assessment Criteria for Fuel Compatibility of Metallic Materials

[0059]

[0060] Table 6 and Appendices Figure 5 The table shows the total risk level assessment, where material type is: X-rubber, Y-metal, Z-other; test type is: tensile strength and elongation at break - a, compression deformation - b, hardness - c, volumetric expansion rate - d, intergranular corrosion - e, surface corrosion - f, weight - g, and visual inspection - h. Based on the judgment criteria, calculate the corresponding R value and output the risk level result.

[0061] Table 6 Risk Level Total Score Assessment Table

[0062]

[0063] This method is also applicable to fuel compatibility verification processes in different verification scenarios. When the fuel type is a new type of fuel not used in engines, or the material of the test piece is a new type of material not used in engines, it can meet the verification requirements of new fuels or materials and guide engineers in different fields such as aviation fuel engineering, aviation product design, and materials science to carry out design and verification work.

[0064] For example, in the first verification scenario, a list of typical materials for fuel compatibility testing is constructed for the development of a new type of aviation fuel not yet used in engines. The test matrix includes combinations of the new fuel with typical materials and compatibility test items.

[0065] Based on the list determined by the test matrix, the above-mentioned aviation fuel compatibility verification methods were used to obtain multiple test results for the new fuel with different types and materials of test specimens. Typical materials can be referred to in Table 1. The compatibility test temperature can be selected as room temperature, 100℃, or 150℃. After the compatibility test is completed, the new fuel can be determined to be Class I, Class II, or Class III compatible based on the compatibility rating.

[0066] For example, in the second verification scenario, regarding the design process of aviation product models, the basic procedure for fuel compatibility testing is divided into: determining the test matrix, pre-test inspection and performance testing of test pieces, fuel and material compatibility testing, and post-test inspection and performance testing of test pieces. The test matrix is ​​determined based on the selected fuel, the materials and surface treatment of components in contact with the fuel, and the temperature of the fuel system. To verify the rationality of the fuel and material selection for aviation products, the compatibility test temperature is based on the highest actual application temperature of the materials in contact with the fuel in the aviation product, including transient temperatures. For a single test, the test criteria are determined based on the aforementioned judgment standards for non-metallic or metallic materials. Regarding the risk of material selection for aviation products, the assessment method is determined based on the specific steps of the aforementioned assessment of the fuel compatibility risk levels of different materials.

[0067] For example, in the third verification scenario, for the research and development of new aviation materials, compatibility tests are conducted between the new material and the reference fuel for aero-engines, and the compatibility data are compared with those of similar materials and the reference fuel. The reference fuel specifications are shown in Table 7 and can be updated dynamically according to industry developments and the application of this invention. The compatibility test temperature can be selected from room temperature, 100℃, or 150℃. After the compatibility test is completed, the new material can be determined to be Class I, Class II, or Class III compatible based on the compatibility rating.

[0068] Table 7. Baseline Fuel Specifications

[0069]

[0070]

[0071] The test results and fuel compatibility data of benchmark fuel and typical materials are used as comparative reference data. The test results can be included in the database to update the list.

[0072] The aforementioned method establishes a complete testing methodology and process for aviation fuel and materials compatibility, integrating fuel verification and material verification functions. It enables the automatic formulation of compatibility verification procedures, automatic processing of compatibility data, and automatic determination of compatibility conclusions. While guiding and completing compatibility verification work in related fields, this system can also utilize experience and data to optimize the system, continuously adapting it to the use of new aviation fuels and materials.

[0073] Based on the above introduction to fuel compatibility verification methods, a fuel compatibility verification system can also be understood, referring to... Figure 2 and Figure 3 As shown, it includes a database, functional modules, and an editor.

[0074] Specifically, Database A contains a temperature list, fuel type information, and test specimen material information. This includes a typical application temperature list, a typical metallic / non-metallic material database, an international mainstream fuel database, and a fuel compatibility database. The typical application temperature list stores the main usage restrictions for mainstream international aviation products (aircraft, engines) and products under development, including fuel system operating temperature limits. The typical metallic / non-metallic material database stores the grades, standards, surface conditions, and main material properties of various materials used in aviation products, including fuel compatibility ratings. The international mainstream fuel database stores the grades, standards, main component content, and main characteristic parameters of domestic and international aviation fuels. The fuel compatibility database stores all verified aviation fuel and material compatibility test data. The editor allows for editing of functional modules and databases, enabling personnel in the aviation product, materials, and fuel industries to edit and modify settings according to industry developments and compatibility testing progress.

[0075] Functional module B includes a compatibility test control module, which includes a fuel verification submodule and a material verification submodule. The functional module embeds the compatibility test process. Depending on the different verification objectives, the fuel verification module or the material verification module can be selected to call different test processes and provide verification guidance.

[0076] The editor is used to edit functional module B and database A.

[0077] This fuel compatibility verification system is linked to various stages of aviation product research and development, design and testing, materials engineering, and fuel engineering. For example... Figure 3 As shown, the materials engineering provides material performance data 101 to the aviation fuel and materials compatibility verification system, the fuel engineering provides basic fuel performance data 102 to the aviation fuel and materials compatibility verification system, and the designers provide engine design information 103 to the aviation fuel and materials compatibility verification system. The engine design information 103 includes fuel circuit design temperature and fuel circuit material selection list.

[0078] The aviation fuel and material compatibility verification system executes test information 104, including determining the typical material list, test conditions, test items and requirements, and provides it to the test personnel. After completing the compatibility test, the test personnel send the compatibility test data 105 back to the aviation fuel and material compatibility verification system.

[0079] The aviation fuel and material compatibility verification system performs compatibility rating and feeds back the rating results to relevant roles and the database. The system can also make judgments based on input; if the result already exists in the fuel compatibility database, it directly returns the existing data and rating result without triggering a test.

[0080] The above method establishes the compatibility test criteria for metallic and non-metallic material specimens, proposes the concept and method for fuel and material compatibility rating, and puts forward a complete fuel compatibility verification process for different verification scenarios, ensuring the execution and consistency of compatibility design and verification under different application scenarios.

[0081] This application uses specific terms to describe embodiments of the application. Terms such as "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic associated with at least one embodiment of the application. Therefore, it should be emphasized and noted that references to "an embodiment," "one embodiment," or "an alternative embodiment" in different locations throughout this specification do not necessarily refer to the same embodiment. Furthermore, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0082] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A fuel compatibility verification method, characterized in that, Includes the following steps: Choose any type of fuel and material for the test specimen; Determine the test temperature, which is the highest temperature at which the test piece is used in aerospace products; The test items for the test specimen are determined, including mandatory test items and optional test items; Tests were conducted to obtain test results. When the material was metal, the test results showed that the test piece did not show corrosion or discoloration, indicating that the fuel was compatible with the test piece. When the material was non-metallic, the test results showed that the performance of the non-metallic material still met the predetermined functional requirements after the compatibility test, indicating that the fuel was compatible with the test piece.

2. The fuel compatibility verification method as described in claim 1, characterized in that, The method also includes the following steps: Construct a matrix of fuel types and test specimen materials, and select one fuel type and one test specimen material from the matrix for testing.

3. The fuel compatibility verification method as described in claim 2, characterized in that, Complete the tests for all matching schemes of fuel type and test piece material in the matrix.

4. The fuel compatibility verification method as described in claim 1, characterized in that, The mandatory test items include one or more of the following: surface inspection, microscopic inspection, hardness test, volume expansion rate test, elongation at break test, tensile strength test, and peel strength test.

5. The fuel compatibility verification method as described in claim 1, characterized in that, The optional test items include one or more of the following: hardness test, tensile strength test, fatigue performance test, and peel strength test.

6. The fuel compatibility verification method as described in claim 1, characterized in that, The material is metal, rubber, composite material, or graphite.

7. The fuel compatibility verification method as described in claim 1, characterized in that, The fuel type is a new type of fuel that has not been used in engines. Multiple test results were obtained for this new fuel and for different types and materials of test specimens.

8. The fuel compatibility verification method as described in claim 7, characterized in that, The test results and the data of fuel already applied to the engine were compared with the data of the same type and material of test specimens.

9. The fuel compatibility verification method as described in claim 1, characterized in that, The test specimen was made of a novel material not previously used in engines, and the compatibility test results of this novel material with the reference fuel for aero-engines were obtained.

10. The fuel compatibility verification method as described in claim 1, characterized in that, The fuel compatibility verification method also includes a risk rating step: The risk level is determined by comparing the test results of the rubber test specimens with the fuel compatibility assessment criteria for rubber materials; or The risk level is determined by comparing the test results of the metal test specimens with the fuel compatibility assessment criteria for metal materials. or The risk level is determined by comparing the test results of test specimens of materials other than rubber and metal with the fuel compatibility assessment criteria of other materials.

11. The fuel compatibility verification method as described in claim 1, characterized in that, The fuel compatibility verification method also includes a fuel compatibility rating step: Based on the test results, the fuel and the material can be used normally at temperatures of 150°C and above, indicating that the fuel and the material are Class I compatible. This type of fuel and material can be used normally in a temperature range of 100℃-150℃, and it is determined that the fuel and the material are Class II compatible. This type of fuel and material can be used normally in a temperature range from room temperature to 100°C, and it is determined that the fuel and the material are Class III compatible. This type of fuel cannot be used with the material in both room temperature and high temperature environments, indicating that the fuel and the material are incompatible.

12. A fuel compatibility verification system, characterized in that, For performing the aviation fuel compatibility verification method according to any one of claims 1-11, the system comprises: The database contains a temperature list, fuel type information, and test specimen material information; The functional modules include a compatibility test control module, which comprises a fuel verification submodule and a material verification submodule; and An editor is used to edit the functional modules and the database.

Images