Civil high-bypass-ratio turbofan engine acceleration and deceleration flight test method
By conducting acceleration and deceleration flight tests on an aircraft platform and controlling the position and time of the engine throttle lever, the safety and performance verification issues in the acceleration and deceleration flight tests of civil high-bypass turbofan engines were resolved, and the engine's acceleration and deceleration control law and transient performance were optimized.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AECC COMML AIRCRAFT ENGINE CO LTD
- Filing Date
- 2024-11-27
- Publication Date
- 2026-05-29
AI Technical Summary
In the existing technology, there are specific technical problems in the acceleration and deceleration flight tests of civil high-bypass turbofan engines, which affect the safe flight of the aircraft and the verification of the engine's transient performance.
This paper provides a method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine. By acquiring acceleration and deceleration flight test points, controlling the flight platform and engine status, adjusting the throttle position and time period, and conducting slow acceleration and deceleration tests, the method ensures that the flight altitude and speed tolerances are within the set range.
The optimization of the acceleration and deceleration control law for a civil high-bypass turbofan engine on an aircraft platform was achieved, the applicability of the engine in its installed state was verified, the transient performance model was improved, and flight safety was ensured.
Smart Images
Figure CN122108618A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aircraft engine technology, and more specifically, to a method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine. Background Technology
[0002] The acceleration and deceleration of an aircraft engine directly affect the safe flight of the aircraft. Acceleration and deceleration flight tests of civil high-bypass turbofan engines are a crucial component of the flight thrust performance testing of civil aviation turbofan engines, and are a mandatory flight test subject for all engines seeking airworthiness certification. The acceleration and deceleration control law designed for a civil high-bypass turbofan engine determines the engine's acceleration and deceleration.
[0003] Before a high-bypass turbofan engine can be officially installed on an aircraft for certification flight tests, it needs to undergo transient performance flight tests on an aircraft platform. These tests verify the engine's compliance with airworthiness regulations, its acceleration time in go-around scenarios, its transient operating characteristics within the flight envelope, and ensure that within the engine's operating limits, it will not exhibit adverse phenomena such as engine surge, overheating, or engine shutdown that could affect flight safety. Based on the results of the engine's acceleration and deceleration flight tests on the aircraft platform, the engine's transient performance model can be revised, and the engine's acceleration and deceleration control law can be further optimized. Summary of the Invention
[0004] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.
[0005] The present invention aims to provide, for example, a method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine, which can improve the problem that there is no specific technology for acceleration and deceleration flight testing of civil high-bypass turbofan engines.
[0006] The embodiments of the present invention can be implemented as follows:
[0007] An embodiment of the present invention provides a method for conducting acceleration and deceleration flight tests on a civil high-bypass turbofan engine, comprising: acquiring an acceleration and deceleration flight test point; controlling the flight platform to fly to the required flight altitude and speed of the acceleration and deceleration flight test point; controlling the test engine to adjust its operating state to idle state; controlling the test engine throttle lever to uniformly push it from the idle position to the maximum position in a first time period, stabilizing it in a second time period; then controlling the test engine throttle lever to uniformly return it from the maximum position to the idle position in a third time period, stabilizing it in a fourth time period; and controlling the test engine according to the allowable tolerances of the test engine's flight altitude and flight speed relative to the acceleration and deceleration flight point, as well as the first, second, third, and fourth time periods.
[0008] In addition, the civil high-bypass turbofan engine acceleration and deceleration flight test method provided in the embodiments of the present invention may also have the following additional technical features:
[0009] Optionally, the step of obtaining acceleration and deceleration flight test points includes: obtaining typical go-around points for typical go-around scenarios of aircraft acceleration requirements.
[0010] Optionally, the step of obtaining acceleration and deceleration flight test points further includes: obtaining typical test points for evaluating the engine's acceleration and deceleration safety characteristics under the most unfavorable combination of bleed air and power extraction within the envelope of airworthiness requirements.
[0011] Optionally, the step of obtaining acceleration and deceleration flight test points further includes: obtaining typical test points for the time required for the engine to safely accelerate from minimum flight idle to 95% of rated takeoff thrust, in accordance with airworthiness requirements.
[0012] Optionally, the step of obtaining acceleration and deceleration flight test points further includes: obtaining typical test points for transition state performance model correction.
[0013] Optionally, the following steps are performed: controlling the flight platform to fly to the required flight altitude and speed at the acceleration / deceleration flight test point; adjusting the test engine's operating state to idle; controlling the test engine throttle lever to move uniformly from the idle position to the maximum position in the first time period, stabilizing in the second time period; then controlling the test engine throttle lever to move uniformly from the maximum position to the idle position in the third time period, stabilizing in the fourth time period; and controlling the test engine according to the allowable tolerances of the test engine's flight altitude and flight speed relative to the acceleration / deceleration flight point, as well as the first, second, third, and fourth time periods, to conduct a slow acceleration / deceleration test.
[0014] Then, the flight platform is controlled to fly to the required flight altitude and speed at the acceleration / deceleration flight test point; the test engine's operating state is adjusted to idle; the test engine throttle lever is controlled to move from the idle position to the maximum position at a constant speed in the first time period, and stabilized in the second time period; the test engine throttle lever is then controlled to move from the maximum position to the idle position at a constant speed in the third time period, and stabilized in the fourth time period; and the test engine is controlled according to the allowable flight altitude and speed tolerances of the test engine relative to the acceleration / deceleration flight point, as well as the first, second, third, and fourth time periods, to conduct a fast acceleration / deceleration test.
[0015] Optionally, the steps of controlling the test engine throttle lever to be pushed from the slow position to the maximum position at a constant speed in the first time period, stabilizing in the second time period; and then controlling the test engine throttle lever to be released from the maximum position to the slow position at a constant speed in the third time period, stabilizing in the fourth time period, include:
[0016] In the slow acceleration and deceleration test, the test engine throttle lever is controlled to be pushed from the slow position to the maximum position at a constant speed for 30 seconds and stabilized for 30 seconds; then the test engine throttle lever is controlled to be pulled back from the maximum position to the slow position at a constant speed for 30 seconds and stabilized for 30 seconds; wherein, the first time period is 30 seconds, the second time period is 30 seconds, the third time period is 30 seconds, and the fourth time period is 30 seconds.
[0017] In the rapid acceleration and deceleration test, the test engine throttle lever is controlled to be pushed from the slow position to the maximum position at a constant speed in 1 second and stabilized for 5 minutes; then the test engine throttle lever is controlled to be pulled back from the maximum position to the slow position at a constant speed in 1 second and stabilized for 5 minutes. The first time period is 1 second, the second time period is 5 minutes, the third time period is 1 second, and the fourth time period is 5 minutes.
[0018] Optionally, the step of controlling the test engine based on the allowable tolerances of flight altitude and flight speed of the test engine relative to the acceleration / deceleration flight points, and the first time period, second time period, third time period, and fourth time period includes:
[0019] If the flight altitude tolerance is ±100m, the flight speed tolerance is ±0.01 Mach number, the test engine throttle lever push-retract position is within the set position range, and the first time period, the second time period, the third time period, and the fourth time period meet the time setting requirements, then the acquisition of acceleration and deceleration flight test points is executed; otherwise, the control test engine operating state is adjusted to idle state again.
[0020] Optionally, the method for testing the acceleration and deceleration flight of a civil high-bypass turbofan engine further includes the following steps: between the step of adjusting the operating state of the test engine to idle state and the step of controlling the test engine throttle lever to move from the idle position to the maximum position at a constant speed in the first time period, stabilizing in the second time period; and controlling the test engine throttle lever to move from the maximum position to the idle position at a constant speed in the third time period, stabilizing in the fourth time period; and controlling the non-test engine to control the aircraft platform to maintain stable straight-line level flight at the acceleration and deceleration flight test point in the fifth time period.
[0021] Optionally, in the slow acceleration and deceleration test, the non-test engine is controlled to make the aircraft platform fly stably in a straight line for 30 seconds at the acceleration and deceleration flight test point, and the fifth time period is 30 seconds;
[0022] In the rapid acceleration and deceleration test, the non-test engine is controlled to make the aircraft platform fly stably in a straight line for 5 minutes at the acceleration and deceleration flight test point. The fifth time period is 5 minutes.
[0023] The beneficial effects of the civil high-bypass turbofan engine acceleration and deceleration flight test method of the present invention include, for example:
[0024] A method for conducting acceleration and deceleration flight tests on a civil high-bypass turbofan engine includes: acquiring an acceleration and deceleration flight test point; controlling the flight platform to fly to the required flight altitude and speed at the acceleration and deceleration flight test point; adjusting the test engine's operating state to idle; controlling the test engine's throttle lever to uniformly push it from the idle position to the maximum position in the first time period, stabilizing it in the second time period; then controlling the test engine's throttle lever to uniformly return it from the maximum position to the idle position in the third time period, stabilizing it in the fourth time period; and controlling the test engine according to the allowable flight altitude and speed tolerances relative to the acceleration and deceleration flight point, as well as the first, second, third, and fourth time periods.
[0025] This method allows for the testing of acceleration, deceleration, and control laws of civil high-bypass turbofan engines on aircraft platforms, assessing the engine's transient flight performance; verifying the applicability of the engine's acceleration, deceleration, and control laws during flight, in accordance with aircraft requirements, enabling situational optimization; and addressing the lack of specific acceleration and deceleration flight testing technologies for civil high-bypass turbofan engines. Attached Figure Description
[0026] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.
[0027] Figure 1A flowchart illustrating the acceleration and deceleration flight test method for a civil high-bypass turbofan engine provided in an embodiment of the present invention;
[0028] Figure 2 A schematic diagram illustrating the engine operating envelope and acceleration / deceleration test point selection embodiment of the acceleration / deceleration flight test method for a civil high-bypass turbofan engine provided in this invention.
[0029] Figure 3 A flowchart of a method for accelerating and decelerating flight tests of a civil high-bypass turbofan engine provided in an embodiment of the present invention. Detailed Implementation
[0030] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.
[0031] In the description of this invention, it should be noted that if terms such as "upper," "lower," "inner," "outer," or "vertical" appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of this invention is usually placed when in use, and does not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.
[0032] At the same time, it should be noted that the terms "first" and "second" are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.
[0033] In the description of this invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, an integral connection, or a detachable connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or a connection within two components, etc. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.
[0034] The following is combined with Figures 1 to 3 The acceleration and deceleration flight test method for a civil high-bypass turbofan engine provided in this embodiment is described in detail.
[0035] Please refer to Figure 1 The present invention provides a method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine, comprising:
[0036] Step S1: Obtain acceleration / deceleration flight test points;
[0037] Step S2: Control the flight platform to fly to the required flight altitude and speed at the acceleration / deceleration flight test point;
[0038] Step S3: Adjust the operating state of the test engine to slow speed.
[0039] Step S4: Control the test engine throttle lever to push it from the slow position to the maximum position at a constant speed in the first time period, and stabilize it in the second time period; then control the test engine throttle lever to return it from the maximum position to the slow position at a constant speed in the third time period, and stabilize it in the fourth time period.
[0040] Step S5: Control the test engine based on the flight altitude tolerance and flight speed tolerance of the test engine relative to the acceleration and deceleration flight points, as well as the first time period, the second time period, the third time period, and the fourth time period.
[0041] It should be noted that: Civil High Bypass Ratio Turbofan Engine: A civil high bypass ratio turbofan engine is a turbofan engine with a bypass ratio of 4 or higher installed in civil aircraft. Engine Acceleration and Deceleration: Within the entire engine envelope, the acceleration process from idle (or in-flight idle) to maximum operating state and the deceleration process from maximum operating state to idle (or in-flight idle), as well as the acceleration / deceleration transition state between two steady-state limits. Engine Acceleration and Deceleration Control Law: The engine acceleration / deceleration control law is a plan written into the engine's electronic controller for engine acceleration and deceleration control. Flight Test: A test conducted on the engine mounted on an aircraft platform through flight testing. Acceleration / deceleration flight test points include flight altitude and flight Mach number.
[0042] This embodiment provides a technology for acceleration and deceleration flight testing of a civil high-bypass turbofan engine. This method allows for acceleration, deceleration, and control law tests of a civil high-bypass turbofan engine on an aircraft platform, assessing the engine's transitional flight performance. By benchmarking against aircraft requirements, it verifies the applicability of the engine's acceleration, deceleration, and control laws during flight, enabling situational optimization. It also verifies and corrects the engine's transitional model, validates the transitional model correction method, and optimizes the transitional model. This improves upon the challenges of acceleration and deceleration flight testing, acceleration and deceleration control law optimization testing, and assessment of the engine's transitional flight performance on an aircraft platform for civil high-bypass turbofan engines.
[0043] Reference Figure 2In this embodiment, step S1, the step of obtaining acceleration and deceleration flight test points, includes: step S11, obtaining typical go-around points for typical aircraft go-around scenarios with acceleration requirements. These test points are proposed for aircraft go-around scenarios.
[0044] Reference Figure 2 In this embodiment, step S1, obtaining the acceleration / deceleration flight test point, further includes step S12, obtaining the typical test point for evaluating the engine's acceleration / deceleration safety characteristics under the most unfavorable combination of bleed air and power extraction within the envelope of airworthiness requirements. Analysis of this test point reveals that power extraction and bleed air draw energy from the high-pressure shaft and core engine; therefore, these conditions are prone to overheating during acceleration.
[0045] Reference Figure 2 In this embodiment, step S1, obtaining the acceleration / deceleration flight test point, further includes step S13, obtaining the typical test point for the engine's safe acceleration from minimum idle to 95% of rated takeoff thrust, which is required for airworthiness. This test point for airworthiness requirements must be verified through flight testing.
[0046] Reference Figure 2 In this embodiment, step S1, obtaining the acceleration / deceleration flight test points, further includes step S14, obtaining typical test points for transitional performance model correction. These test points are obtained through a digital engine model capable of simulating the acceleration / deceleration process. The model simulation must be able to handle experimental data, requiring tests to be conducted within the engine envelope and at boundary points to accumulate data and correct the model.
[0047] Determine the flight test priority for all acceleration and deceleration flight test points, and prioritize the implementation of typical go-around conditions and typical assessment points. The priority is ranked according to the importance of the assessment, with the most important being the test points for go-around requirements and those proposed by the aircraft manufacturer, followed by supplementary points for model correction.
[0048] Based on the altitude, Mach number, and flight test priority of all test points, and considering the aircraft platform conditions, the number of acceleration / deceleration flight test sorties and test points are comprehensively arranged. The flight envelope of the flight platform may not be completely consistent with the operating envelope of the engine; therefore, some boundary points need to be adjusted to the flight envelope of the flight platform. According to the test cycle, test points are appropriately reduced, starting with those of lower importance.
[0049] Before conducting flight tests at each test point, simulation analysis of the acceleration and deceleration control laws is performed to eliminate flight test risks and formulate risk mitigation measures. Before the test, digital engine models are used for simulation calculations to obtain the calculation results for each test point, identifying test points with high temperatures and low surge margins, and appropriately adjusting the fuel supply pattern. Alternatively, acceleration and deceleration tests can be conducted step-by-step for each test point, initially using a reduced fuel supply pattern and then gradually increasing to the target fuel supply pattern.
[0050] Reference Figure 3 , Figure 3 The illustrations on the two pages of the accompanying drawings show a continuous sequence. In this embodiment, step S2 involves controlling the flight platform to reach the required flight altitude and speed for the acceleration / deceleration flight test point; step S3 involves adjusting the test engine's operating state to idle; and step S4 involves controlling the test engine throttle lever to move uniformly from the idle position to the maximum position in the first time period, stabilizing it in the second time period; then controlling the test engine throttle lever to move uniformly from the maximum position to the idle position in the third time period, stabilizing it in the fourth time period. This process, along with controlling the test engine based on the allowable flight altitude and speed tolerances relative to the acceleration / deceleration flight point, and the first, second, third, and fourth time periods, constitutes a slow acceleration / deceleration test.
[0051] Then, step S2 is executed to control the flight platform to fly to the required flight altitude and speed at the acceleration / deceleration flight test point; step S3 is executed to adjust the working state of the test engine to idle state; and step S4 is executed to control the test engine throttle lever to push it from the idle position to the maximum position at a constant speed in the first time period, and stabilize it in the second time period; then the test engine throttle lever is controlled to return to the idle position at a constant speed in the third time period, and stabilize it in the fourth time period. The test engine is then controlled according to the flight altitude tolerance and flight speed tolerance of the test engine relative to the acceleration / deceleration flight point, as well as the first time period, the second time period, the third time period, and the fourth time period, to conduct a fast acceleration / deceleration test.
[0052] The aircraft platform flies to the required flight altitude and speed at the test point, first conducting a slow acceleration and deceleration test, and then a fast acceleration and deceleration test.
[0053] Reference Figure 3 In this embodiment, step S4, controlling the test engine throttle lever to move uniformly from the slow position to the maximum position in the first time period, stabilizing in the second time period; and then controlling the test engine throttle lever to move uniformly from the maximum position to the slow position in the third time period, stabilizing in the fourth time period, includes the following steps:
[0054] In the slow acceleration and deceleration test, the test engine throttle lever is controlled to be pushed from the slow position to the maximum position at a constant speed for 30 seconds and stabilized for 30 seconds; then the test engine throttle lever is controlled to be pulled back from the maximum position to the slow position at a constant speed for 30 seconds and stabilized for 30 seconds; the first time period is 30 seconds, the second time period is 30 seconds, the third time period is 30 seconds, and the fourth time period is 30 seconds.
[0055] In the rapid acceleration and deceleration test, the test engine throttle lever is controlled to be pushed from the slow position to the maximum position at a constant speed in 1 second and stabilized for 5 minutes; then the test engine throttle lever is controlled to be pulled back from the maximum position to the slow position at a constant speed in 1 second and stabilized for 5 minutes. The first time period is 1 second, the second time period is 5 minutes, the third time period is 1 second, and the fourth time period is 5 minutes.
[0056] Reference Figure 3 In this embodiment, step S5, which involves controlling the test engine based on the allowable tolerances of flight altitude and flight speed relative to the acceleration / deceleration flight points, as well as the first time period, the second time period, the third time period, and the fourth time period, includes:
[0057] If the flight altitude tolerance is ±100m, the flight speed tolerance is ±0.01 Mach number, the test engine throttle lever push-retract position is within the set position range, and the first time period, second time period, third time period, and fourth time period meet the time setting requirements, then the execution continues from step S1, obtaining the acceleration / deceleration flight test point; otherwise, step S3 is executed again to control the test engine to adjust its working state to idle state, followed by steps S4 and S5.
[0058] To determine whether the aircraft platform remains stable during the test, if the flight altitude remains stable within ±100m of the selected altitude and the flight Mach number remains stable within ±0.01 of the selected Mach number, then the aircraft platform is considered to have remained stable during the test; otherwise, the test is repeated.
[0059] Determine whether the throttle lever push-and-retract position and the throttle lever push-and-retract time meet the requirements during the test. If both are met, the slow acceleration / deceleration test at this test point is complete. Otherwise, restart step S3.
[0060] The “time setting requirements” are those mentioned above, which specify the time requirements for the first, second, third, and fourth time periods in both slow and fast acceleration / deceleration tests.
[0061] Reference Figure 3 In this embodiment, the method for accelerating and decelerating flight tests of a civil high-bypass turbofan engine further includes the following steps: Step S3, controlling the test engine to adjust its operating state to idle; and Step S4, controlling the test engine throttle lever to uniformly push it from idle to maximum position in the first time period, stabilizing it in the second time period; then controlling the test engine throttle lever to uniformly return it from maximum to idle position in the third time period, stabilizing it in the fourth time period; and finally controlling the non-test engine to control the non-test engine to maintain stable straight-line level flight at the acceleration / deceleration flight test point in the fifth time period. These are the starting conditions for slow acceleration / deceleration tests and fast acceleration / deceleration tests.
[0062] Reference Figure 3In this embodiment, during the slow acceleration / deceleration test, the non-test engine is controlled to make the aircraft platform fly stably in a straight line for 30 seconds at the acceleration / deceleration flight test point, and the fifth time period is 30 seconds; during the fast acceleration / deceleration test, the non-test engine is controlled to make the aircraft platform fly stably in a straight line for 5 minutes at the acceleration / deceleration flight test point, and the fifth time period is 5 minutes.
[0063] Reference Figure 3 According to the embodiment of this invention, a method for testing the acceleration and deceleration flight of a civil high-bypass turbofan engine is provided. The working principle of this method includes:
[0064] (1) The aircraft platform flies to the required flight altitude and speed at the test point and first conducts a slow acceleration and deceleration test.
[0065] (2) Adjust the operating state of the control test engine to idle state. The acceleration test starts at idle state.
[0066] (3) Adjust the non-test engine to ensure that the aircraft platform flies stably in a straight line for 30 seconds at the test point. Slow acceleration and deceleration starting conditions.
[0067] (4) Push the throttle lever of the test engine at a constant speed, taking 30 seconds to push it from the slow position to the maximum position, and stabilize it for 30 seconds. Then, release the throttle lever of the test engine at a constant speed, taking 30 seconds to release it from the maximum position to the slow position, and stabilize it for 30 seconds.
[0068] (5) Determine whether the aircraft platform remains stable during the test in step (4). If the flight altitude is stable within ±100m of the selected altitude relative to the acceleration / deceleration test point and the flight Mach number is stable within ±0.01 of the selected Mach number relative to the acceleration / deceleration test point, then the aircraft platform is considered stable during the test; otherwise, repeat the test. Start from step (2).
[0069] (6) Determine whether the throttle lever push-and-retract position and the throttle lever push-and-retract time meet the requirements during the test in step (4). If both are met, the slow acceleration / deceleration test at this test point is completed. Otherwise, restart step (2).
[0070] (7) The aircraft platform maintains the required flight altitude and speed at the test point and conducts a rapid acceleration and deceleration test.
[0071] (8) Adjust the engine under test to idle state, and adjust the non-test engines to ensure that the aircraft platform flies stably in a straight line at each test point for 5 minutes. Initial conditions for rapid acceleration and deceleration.
[0072] (9) Push the test engine throttle lever from the idle position to the maximum position within 1 second and stabilize for 5 minutes. Retract the test engine throttle lever from the maximum position to the idle position within 1 second and stabilize for 5 minutes. Ensure that the aircraft platform flies stably in a straight line at the test point during the test process.
[0073] (10) Determine whether the aircraft platform remains stable during the test in step (9). If the flight altitude is stable within ±100m of the selected altitude and the flight Mach number is stable within ±0.01 of the selected Mach number during the test, then the aircraft platform is considered to be stable during the test. Otherwise, repeat the test and execute step (8).
[0074] (11) Determine whether the throttle lever push-and-retract position and the throttle lever push-and-retract time meet the requirements during the test in step (9). If both are met, the acceleration / deceleration test at this test point is complete. Otherwise, restart step (8).
[0075] The method for acceleration and deceleration flight testing of a civilian high-bypass turbofan engine provided in this embodiment has at least the following advantages:
[0076] This method, applied to acceleration and deceleration flight testing technology for civil high-bypass turbofan engines, enables the testing of acceleration, deceleration, and control laws of civil high-bypass turbofan engines on aircraft platforms. It allows for the assessment of the engine's transitional flight performance; verification of the applicability of the engine's acceleration, deceleration, and control laws during flight, aligning with aircraft requirements and enabling situational optimization; and calibration and correction of the engine's transitional model, validating the correction method and optimizing the transitional model. This approach improves upon the challenges of acceleration and deceleration flight testing, control law optimization testing, and assessment of engine transitional flight performance for civil high-bypass turbofan engines on aircraft platforms.
[0077] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.
Claims
1. A method for acceleration and deceleration flight testing of a civilian high-bypass turbofan engine, characterized in that, include: Obtain acceleration and deceleration test points; Control the flight platform to fly to the required flight altitude and speed at the acceleration and deceleration flight test point; The operating status of the test engine was adjusted to idle mode; The test engine throttle lever is controlled to be pushed from the slow position to the maximum position at a constant speed in the first time period, and stabilized in the second time period; then the test engine throttle lever is controlled to be pulled back from the maximum position to the slow position at a constant speed in the third time period, and stabilized in the fourth time period. The test engine is controlled based on the allowable flight altitude and speed tolerances of the test engine relative to the acceleration and deceleration flight points, as well as the first, second, third, and fourth time periods.
2. The method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine according to claim 1, characterized in that, The steps for obtaining acceleration and deceleration flight test points include: obtaining typical go-around points for typical go-around scenarios with acceleration requirements.
3. The method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine according to claim 1, characterized in that, The steps for obtaining acceleration and deceleration flight test points also include: obtaining typical test points for evaluating the engine's acceleration and deceleration safety characteristics under the most unfavorable combination of bleed air and power extraction within the envelope of airworthiness requirements.
4. The method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine according to claim 1, characterized in that, The steps for obtaining acceleration and deceleration flight test points also include: obtaining typical test points for the time required for the engine to safely accelerate from minimum flight idle to 95% of rated takeoff thrust, which are required for airworthiness.
5. The method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine according to claim 1, characterized in that, The steps for obtaining acceleration and deceleration flight test points also include: obtaining typical test points for transition state performance model correction.
6. The method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine according to any one of claims 1-5, characterized in that, The process involves executing the steps of controlling the flight platform to fly to the required flight altitude and speed at the acceleration / deceleration flight test point; adjusting the test engine's operating state to idle; controlling the test engine's throttle lever to move uniformly from the idle position to the maximum position in the first time period, stabilizing in the second time period; then controlling the test engine's throttle lever to move uniformly from the maximum position to the idle position in the third time period, stabilizing in the fourth time period; and controlling the test engine according to the allowable tolerances of the test engine's flight altitude and flight speed relative to the acceleration / deceleration flight point, as well as the first, second, third, and fourth time periods, to conduct a slow acceleration / deceleration test. Then, the flight platform is controlled to fly to the required flight altitude and speed at the acceleration / deceleration flight test point; the test engine's operating state is adjusted to idle; the test engine throttle lever is controlled to move from the idle position to the maximum position at a constant speed in the first time period, and stabilized in the second time period; the test engine throttle lever is then controlled to move from the maximum position to the idle position at a constant speed in the third time period, and stabilized in the fourth time period; and the test engine is controlled according to the allowable flight altitude and speed tolerances of the test engine relative to the acceleration / deceleration flight point, as well as the first, second, third, and fourth time periods, to conduct a fast acceleration / deceleration test.
7. The method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine according to claim 6, characterized in that, The steps of controlling the test engine throttle lever to be pushed from the slow position to the maximum position at a constant speed in the first time period, and then stabilized in the second time period; and then controlling the test engine throttle lever to be released from the maximum position to the slow position at a constant speed in the third time period, and then stabilizing in the fourth time period include: In the slow acceleration and deceleration test, the test engine throttle lever is controlled to be pushed from the slow position to the maximum position at a constant speed for 30 seconds and stabilized for 30 seconds; then the test engine throttle lever is controlled to be pulled back from the maximum position to the slow position at a constant speed for 30 seconds and stabilized for 30 seconds; wherein, the first time period is 30 seconds, the second time period is 30 seconds, the third time period is 30 seconds, and the fourth time period is 30 seconds. In the rapid acceleration and deceleration test, the test engine throttle lever is controlled to be pushed from the slow position to the maximum position at a constant speed in 1 second and stabilized for 5 minutes; then the test engine throttle lever is controlled to be pulled back from the maximum position to the slow position at a constant speed in 1 second and stabilized for 5 minutes. The first time period is 1 second, the second time period is 5 minutes, the third time period is 1 second, and the fourth time period is 5 minutes.
8. The method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine according to claim 7, characterized in that, The steps of controlling the test engine based on the allowable tolerances of flight altitude and flight speed relative to the acceleration / deceleration flight points, and the first, second, third, and fourth time periods, include: If the flight altitude tolerance is ±100m, the flight speed tolerance is ±0.01 Mach number, the test engine throttle lever push-retract position is within the set position range, and the first time period, the second time period, the third time period, and the fourth time period meet the time setting requirements, then the acquisition of acceleration and deceleration flight test points is executed; otherwise, the control test engine operating state is adjusted to idle state again.
9. The method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine according to claim 6, characterized in that, The civil high-bypass turbofan engine acceleration and deceleration flight test method further includes the steps between the step of adjusting the operating state of the test engine to idle state and the steps of pushing the throttle lever of the test engine uniformly from the idle position to the maximum position in the first time period, stabilizing in the second time period; and then controlling the throttle lever of the test engine uniformly returning from the maximum position to the idle position in the third time period, stabilizing in the fourth time period. Controlling the non-test engines to ensure the aircraft platform maintains stable straight-line level flight at acceleration and deceleration test points during the fifth time period.
10. The method for acceleration and deceleration flight testing of a civil high-bypass turbofan engine according to claim 9, characterized in that: In the slow acceleration and deceleration test, the non-test engine is controlled to make the aircraft platform fly stably in a straight line for 30 seconds at the acceleration and deceleration flight test point. The fifth time period is 30 seconds. In the rapid acceleration and deceleration test, the non-test engine is controlled to make the aircraft platform fly stably in a straight line for 5 minutes at the acceleration and deceleration flight test point. The fifth time period is 5 minutes.