Aero-engine test scheme design method

Abstract

The invention belongs to the field of aero-engine test technology design, and particularly relates to an aero-engine test scheme design method, which comprises the following steps of: 1, determining a test platform required for verifying a system requirement according to an aero-engine system requirement content; 2, determining a verification purpose according to the requirement content of the aviation engine system, and further determining a test item and a debugging method thereof, a result admission standard and an evaluation standard; step 3, according to the test platform and the test items thereof, extracting a test name required by the aviation engine system; 4, performing affinity classification on the test items based on test names required by each aviation starting system, and integrating a debugging method, result admission and evaluation standards to obtain the test items actually required and the debugging method, result admission and evaluation standards thereof; and step 5, according to the actually required test items, the debugging method thereof, the result admission and the evaluation standard, carrying out test, debugging, result admission and conformity evaluation.

Description

Technical Field

[0001] This application belongs to the field of aero-engine test technology design, specifically involving a design method for aero-engine test schemes. Background Technology

[0002] Due to their complex structure and working principle, aircraft engines present significant challenges in both design and testing.

[0003] Currently, most aero-engine test program designs do not consider the requirements of the aero-engine system. Instead, they directly refer to relevant standards, specifications, and guidelines for test design and planning, or make corresponding modifications to these to arrive at the aero-engine test program. This can easily lead to situations where too few local test items are planned, failing to fully verify the aero-engine design level and performance, or too many local test items are planned, resulting in a waste of test resources.

[0004] Furthermore, directly referencing relevant standards, specifications, and guidelines for test design and planning in the design of aero-engine test programs, without considering the aero-engine system requirements, can easily lead to the omission of test items, resulting in incomplete test programs. This is especially true for test items involving the functional / performance verification of multi-configuration aero-engines with variable cycle parameters, which fail to achieve the goal of comprehensively verifying the aero-engine design requirements. Moreover, neglecting the mission positioning of the aero-engine can easily lead to a mismatch between the test plan and the actual testing needs of the aero-engine. For example, a technology demonstrator that only conducts ground bench tests does not involve high-altitude or flight test benches. However, if the test plans of other aero-engines already in production or finalized are referenced, high-altitude and flight test benches may be included in the test plan of this technology demonstrator, leading to unnecessary iterative changes to the test program later.

[0005] In view of the aforementioned technical deficiencies, this application is hereby filed. Summary of the Invention

[0006] The purpose of this application is to provide a design method for an aero-engine test scheme to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] A method for designing an aero-engine test scheme, comprising:

[0009] Step 1: Based on the requirements of the aviation engine system, determine the test platform needed to verify the system requirements;

[0010] Step 2: Based on the requirements of the aircraft engine system, determine the verification objectives, and then determine the test items, debugging methods, result recording, and evaluation standards;

[0011] Step 3: Based on the test platform and its test items, extract the test names required for the aircraft engine system;

[0012] Step 4: Based on the test names required by each aviation engine system, classify the test items according to their affinity, and combine the debugging methods, result admission, and evaluation criteria to obtain the actual required test items and their debugging methods, result admission, and evaluation criteria.

[0013] Step 5: Conduct experiments, perform debugging, record results, and conduct conformity evaluations according to the actual required test items, debugging methods, result admission, and evaluation standards.

[0014] According to at least one embodiment of this application, in the above-described aero-engine test scheme design method, the test platform includes a ground test bench, a high-altitude test bench, and a flight test bench.

[0015] According to at least one embodiment of this application, in the above-described aero-engine test scheme design method, the test item debugging method includes adjusting the control law of the geometrically adjustable components of the aero-engine and adjusting the afterburner fuel supply law.

[0016] According to at least one embodiment of this application, the control law for adjusting the geometrically adjustable components of the aero-engine in the above-described aero-engine test scheme design method includes the control law for adjusting components such as the nozzle throat area and guide vane angle.

[0017] According to at least one embodiment of this application, in the above-described aero-engine test scheme design method, the test items are classified by affinity, specifically by optimizing, merging, decomposing, extending, or merging different test items.

[0018] This application has at least the following beneficial technical effects:

[0019] This paper presents a design method for aero-engine test schemes. Based on the forward design concept, it takes the aero-engine system requirements as the foundation, starts from the system requirements of the aero-engine, considers the mission positioning of the aero-engine, conducts a forward analysis of the test requirement elements, comprehensively and systematically captures the test requirement elements of the aero-engine, and gradually analyzes the test verification projects to be carried out to fully verify the system requirements, thereby formulating a reasonable test method. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the design method for an aero-engine test scheme provided in the embodiments of this application;

[0021] Figure 2 This is a schematic diagram illustrating the affinity classification of test items provided in the embodiments of this application.

[0022] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0023] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0024] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0025] To address the problems of overlooked test items and mismatch between designed test schemes and actual test requirements in current aero-engine test scheme designs, this application provides an aero-engine test scheme design method, such as... Figure 1 As shown, starting from the system requirements of aero-engines, we conduct forward design of test elements, comprehensively and accurately grasp the test items of aero-engines, and formulate reasonable test plans in order to shorten the test cycle, reduce test costs, and fully verify the results.

[0026] Different systems of an aero-engine may have the same test items for SR (Self-Testing) requirements, while the same system may have different test items for SR requirements.

[0027] Step 1: Based on the requirements of the aviation engine system, determine the test platform needed to verify the system requirements.

[0028] The test platform includes a ground test bench, a high-altitude test bench, and a flight test bench.

[0029] Taking the system requirement of a certain aero-engine, "the maximum ground thrust under standard atmospheric static conditions at sea level shall not be less than X kN", as an example, in order to test the maximum ground thrust, the required test platform is determined to be a ground test bench, without involving high-altitude test benches or flight test benches.

[0030] Step 2: Based on the requirements of the aircraft engine system, determine the verification purpose, and then determine the test items, debugging methods, result recording, and evaluation standards.

[0031] The requirement for verifying the aero-engine system requirement of "maximum ground thrust not less than X kN under standard atmospheric static conditions at sea level" necessitates conducting a maximum thrust performance test to assess the ground thrust. The main tasks of this performance test include developing test procedures, monitoring test runs, and recording performance parameters. The debugging methods primarily involve adjusting the control laws of geometrically adjustable components of the aero-engine, such as the control laws of nozzle throat area and guide vane angle, as well as adjusting the afterburner fuel supply.

[0032] For the requirement of "the maximum ground thrust not less than X kN under standard atmospheric stationary conditions at sea level" for aero-engine systems, it is necessary to complete the maximum thrust performance assessment at the specified time according to the determined test items and debugging methods, and convert it to standard atmospheric stationary conditions according to a certain conversion method.

[0033] For the requirement of "the maximum ground thrust is not less than X kN under standard atmospheric stationary conditions at sea level", the evaluation standard is "thrust not less than X kN". When conducting the requirement compliance evaluation, if the maximum thrust converted to standard atmospheric stationary conditions is greater than X kN, the requirement is met; if it is less than X kN, the requirement is not met.

[0034] Step 3: Based on the test platform and its test items, extract the test names required for the aircraft engine system.

[0035] For the requirement of aero-engine systems, "the maximum ground thrust under standard atmospheric static conditions at sea level shall not be less than X kN", thrust falls under the category of performance parameters. Therefore, the test name can be refined to "Ground bench maximum state performance admission test".

[0036] Step 4: Based on the test names required by each aviation engine system, classify the test items according to their affinity, and combine the debugging methods, result admission, and evaluation criteria to obtain the actual required test items and their debugging methods, result admission, and evaluation criteria.

[0037] The requirements for each aero-engine system (SR-1, SR-2, ..., SR-N) and the test items (A1, A2, ..., AX) are not in a one-to-one relationship; rather, there is a one-to-many relationship. Figure 2 As shown, the test items are categorized by affinity, that is, different test items are optimized, merged, decomposed, extended, or combined. Test items A1, A2, ..., AX are simplified into scientific, reasonable, and feasible test planning items B1, B2, ..., BY, where Y≤X. This reduces the number of times aero-engines are tested, shortens the test cycle, and reduces test costs. For example:

[0038] The test named "Ground Test Platform Maximum State Performance Record Test" and "Ground Test Platform Intermediate State Performance Record Test" are combined to obtain the "Ground Test Platform Steady-State Performance Record Test".

[0039] The "Functional Verification Test of Ground Test System" will be conducted concurrently with the "Steady-State Performance Recording Test of Ground Test System" and the "Acceleration and Deceleration Performance Recording Test of Ground Test System," and no separate tests will be arranged.

[0040] Step 5: Conduct experiments, perform debugging, record results, and conduct conformity evaluations according to the actual required test items, debugging methods, result admission, and evaluation standards.

[0041] The aero-engine test scheme design method disclosed in the above embodiments, based on a forward analysis of test requirements and considering the aero-engine system requirements and mission tasks, designs test schemes and has the following advantages:

[0042] By considering the requirements of aero-engine systems, we can avoid omitting test verification items required for different categories of requirements such as functions, performance, interfaces, and constraints. When formulating test plans, we can be more targeted, making the test plan more closely match the actual test requirements of aero-engines, making the test plan more complete, ensuring that the test items are neither redundant nor missing, guaranteeing comprehensive verification of aero-engine system requirements, and avoiding unnecessary iterative changes to the test plan.

[0043] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for designing an aero-engine test scheme, characterized in that, include: Step 1: Based on the requirements of the aviation engine system, determine the test platform needed to verify the system requirements; Step 2: Based on the requirements of the aircraft engine system, determine the verification objectives, and then determine the test items, debugging methods, result recording, and evaluation standards; Step 3: Based on the test platform and its test items, extract the test names required for the aircraft engine system; Step 4: Based on the test names required by each aviation engine system, classify the test items according to their affinity, and combine the debugging methods, result admission, and evaluation criteria to obtain the actual required test items and their debugging methods, result admission, and evaluation criteria. Step 5: Conduct experiments, perform debugging, record results, and conduct conformity evaluations according to the actual required test items, debugging methods, result admission, and evaluation standards.

2. The method for designing an aero-engine test scheme according to claim 1, characterized in that, The test platform includes a ground test bench, a high-altitude test bench, and a flight test bench.

3. The method for designing an aero-engine test scheme according to claim 2, characterized in that, The debugging methods for the test project include adjusting the control laws of the geometrically adjustable components of the aero-engine and adjusting the afterburner fuel supply law.

4. The method for designing an aero-engine test scheme according to claim 3, characterized in that, The control laws for adjusting the geometrically adjustable components of an aero-engine include the control laws for adjusting components such as the nozzle throat area and guide vane angle.

5. The method for designing an aero-engine test scheme according to claim 4, characterized in that, The experimental projects are categorized by affinity, specifically by optimizing, merging, decomposing, extending, or integrating different experimental projects.

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