Aero-engine rotor working state monitoring method

Abstract

The invention provides a method for monitoring the working state of an aero-engine rotor. The method comprises the following steps: step 1, preliminarily determining monitored characteristic parameters; starting from the influence possibly brought to the working state of the engine rotor after the damage occurs, engine monitoring parameters associated with the working state of the rotor are analyzed and researched, and typical rotor damage comprises blade damage, transmission mechanism damage and bearing failure; and 2, analyzing and formulating a reasonable monitoring range: selecting a typical state or process, comparing in a consistent state to ensure the accuracy and effectiveness of evaluation, and analyzing to serve as a typical monitoring state. Monitoring parameters are selected, wherein the parameters for formulating monitoring standards are selected according to the slow vehicle working state before parking and parking process data analysis. The method has the advantages that the working state of the engine rotor can be effectively monitored, damage to the engine in the use process is timely monitored, possible loss is reduced, and guarantee is provided for safe use of the engine.

Description

Technical Field

[0001] The invention relates to the field of aeroengines, and in particular to a method for monitoring the working state of an aeroengine rotor. Background Art

[0002] The rotor of an aircraft engine is the core power unit of an aircraft. It is a high-speed rotating mechanical component with easily damaged rotating blades and a complex transmission and lubrication system. During operation, blade damage, abnormal wear, and bearing failure damage will pose a hidden danger to flight safety. There are clear monitoring indicators for various parameters in the engine operation process. With the accumulation of experience in problem handling, it is found that in the early stage of some damage, some monitoring parameters will change slightly but not exceed the allowable standards. Therefore, it is necessary to develop specific monitoring methods to detect clues of some damage from engine parameters in advance.

[0003] Analyze and study the engine characteristic parameters that are associated with the rotor working state, find out the changing trend of the characteristic parameters at the initial stage of damage, formulate the monitoring range accordingly, confirm the damaged part through additional inspection, eliminate the damage in time when it is found, avoid further deterioration of the rotor working state, and ensure the safe use of the engine. Summary of the invention

[0004] The purpose of the present invention is to monitor and track the use data of aircraft engines, sense the deviation of the working state of the aircraft engine rotor, discover mechanical damage problems in advance through changes in characteristic parameters, and realize the monitoring of the working state of the aircraft engine rotor. By using the present invention, the working state of the engine rotor can be effectively monitored to ensure flight safety, and a method for monitoring the working state of the aircraft engine rotor is provided.

[0005] A method for monitoring the working state of an aircraft engine rotor, characterized in that: Step 1: Preliminarily determine the characteristic parameters to be monitored

[0006] Starting from the possible impact on the working state of the engine rotor after the damage occurs, the engine monitoring parameters related to the working state of the rotor are analyzed and studied. Typical rotor damage includes blade damage, transmission mechanism damage, and bearing failure. After different damages occur, the impacts on the engine as a whole mainly include the following aspects:

[0007] Damage causes the engine to work abnormally, and the main engine vibration increases suddenly, exceeding the use standard;

[0008] Damage causes engine efficiency to decrease, and exhaust temperature to increase under the same operating conditions;

[0009] After the damage, the operating temperature of the transmission system increases, the lubricating oil pressure changes under the same working condition, and the lubricating oil temperature increases;

[0010] Damage increases rotor resistance, leading to higher exhaust temperatures and changes in travel ease during parking.

[0011] According to the impact caused by the damage, the characteristic parameters to be monitored are preliminarily identified, such as vibration value, exhaust temperature, lubricating oil pressure difference, lubricating oil temperature, and ease of rotor stroke. The monitoring parameters and specific monitoring requirements are then further analyzed and confirmed in combination with the model characteristics.

[0012] Step 2: Analyze and establish a reasonable monitoring scope

[0013] (1) Select a typical state or process

[0014] Comparisons are made under consistent conditions to ensure the accuracy and effectiveness of the evaluation, including similar throttle operation processes of the engines, the main engines being in the same hot or cold state, similar flight altitudes, and similar intake temperatures. Through analysis, the slow-running operating state before engine shutdown and the shutdown process can meet the above conditions and serve as typical monitoring states.

[0015] (2) Select monitoring parameters

[0016] Through the analysis of the slow vehicle working status before parking and the parking process data, the parameters for formulating the monitoring standards are selected:

[0017] In the data performance, the vibration performance of the engine has a certain randomness, and it is not suitable to determine whether there is damage through small changes;

[0018] Based on the stable performance of the exhaust temperature in the slow state before parking, as the monitoring standard, the exhaust temperature range of a single unit under similar atmospheric temperature is formulated, see Figure 1 For the same engine, when the difference in inlet air temperature is less than 5°C, the dispersion of its exhaust temperature is basically within 15°C. However, according to experience, after damage occurs, the exhaust temperature rise in the slow-running state before parking is much greater than 15°C.

[0019] After damage, the rotor resistance may increase, the travel ease will change during the parking process, and the rotor stop time will be shortened. Therefore, a monitoring standard for the travel ease of a single engine can be established through statistics. The operating time from the moment the engine throttle lever is pulled to the moment the low-pressure speed drops to less than 15%, and the operating time from the moment the engine throttle lever is pulled to the moment the high-pressure speed drops to less than 15%, are counted, and the travel ease distribution range of a single engine is established as a monitoring standard, see Figure 2 .

[0020] When damage causes heat increase in the transmission system, the lubricating oil temperature will increase, and the corresponding lubricating oil pressure difference may also change. The lubricating oil temperature and lubricating oil pressure difference are basically stable in the slow-moving state before parking, and their working range is established as a monitoring standard.

[0021] Step 3: Verify and perfect

[0022] Based on the results of step one and step two, establish a monitoring range for the process parameters of a single engine. When a parameter exceeds the upper or lower limit, perform necessary supplementary inspections in addition to the normal inspection items, including inspections of the flow path of the rotor blades, metal content in the lubricating oil, and the working condition of the oil filter. Adjust the monitoring range based on the actual inspection results.

[0023] Compared with the prior art, the present invention has the following advantages:

[0024] The method for monitoring the working state of an aircraft engine rotor described in the present invention can effectively monitor the working state of the engine rotor, detect damage during engine use in a timely manner, reduce possible losses, and provide protection for the safe use of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments:

[0026] Figure 1 It is a schematic diagram of the exhaust temperature monitoring range;

[0027] Figure 2 Schematic diagram of the travel ease monitoring range. DETAILED DESCRIPTION

[0028] The present invention will be further explained below in conjunction with specific implementation plans, but the present invention is not limited thereto. The structures, proportions, and sizes illustrated in the drawings of the specification are only used to match the contents disclosed in the specification so that people familiar with this technology can understand and read them. They are not used to limit the conditions under which the present invention can be implemented, so they have no substantive technical significance. Any structural modification, change in proportional relationship, or adjustment of size should still fall within the scope of the technical content disclosed by the present invention without affecting the effects and purposes that can be achieved by the present invention.

[0029] Step 1: Determine the associated parameters of the damage

[0030] According to the characteristics of the model itself and the actual use of the collected monitoring parameters, a comprehensive analysis is performed to determine the characteristic parameters that characterize the changes in the rotor state, which are generally engine exhaust temperature, lubricating oil pressure difference, lubricating oil temperature, and travel time.

[0031] Step 2: Analyze and determine the typical status of monitoring

[0032] According to actual usage habits, parameters of typical states are selected for evaluation. In addition to the slow-moving state before parking and the parking process, typical states can also be added as needed.

[0033] Step 3: Through continuous parameter analysis of a single engine, establish the monitoring range of exhaust temperature, lubricating oil pressure difference, lubricating oil temperature, and travel time under its typical state.

[0034] Step 4: Draw the parameter range curve in step 3 as the monitoring and evaluation standard of the parameters under typical conditions. Figure 1 and Figure 2 .

[0035] Step 5: During use, evaluate the working condition of the engine rotor according to the parameter monitoring range. When it exceeds the range, perform additional inspections to determine whether damage has occurred and eliminate it in a timely manner if damage is found.

[0036] Matters not covered by the present invention are known technologies.

[0037] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and alterations may be made to the embodiments without departing from the principles and spirit of the invention, the scope of the invention being defined by the appended claims and their equivalents.

Claims

1. A method for monitoring the working state of an aircraft engine rotor, characterized in that: The following steps are involved: Step 1: Preliminary determination of monitoring characteristic parameters Starting from the possible impact on the working state of the engine rotor after the damage occurs, the engine monitoring parameters related to the working state of the rotor are analyzed and studied. Typical rotor damage includes blade damage, transmission mechanism damage, and bearing failure. After different damages occur, the impacts on the engine as a whole mainly include the following aspects: Damage causes the engine to work abnormally, and the main engine vibration increases suddenly, exceeding the use standard; Damage causes engine efficiency to decrease, and exhaust temperature to increase under the same operating conditions; After the damage, the operating temperature of the transmission system increases, the lubricating oil pressure changes under the same working condition, and the lubricating oil temperature increases; Damage increases rotor resistance, leading to higher exhaust temperatures and changes in travel ease during parking. According to the impact of the damage, the characteristic parameters to be monitored are initially identified, such as vibration value, exhaust temperature, lubricating oil pressure difference, lubricating oil temperature, and rotor stroke ease. The monitoring parameters and specific monitoring requirements are then further analyzed and confirmed in combination with the model characteristics. Step 2: Analyze and establish a reasonable monitoring scope Select a typical state or process Comparisons are made under consistent conditions to ensure the accuracy and effectiveness of the evaluation, including similar throttle operation processes of the engines, the same hot or cold state of the main engine, similar flight altitudes, and similar intake temperatures. Through analysis, the slow-running state before the engine stops and the stopping process can meet the above conditions and serve as typical monitoring states; Select the parameters to monitor Through the analysis of the slow vehicle working status before parking and the parking process data, the parameters for formulating the monitoring standards are selected: In the data performance, the vibration performance of the engine has a certain randomness, and it is not suitable to determine whether there is damage through small changes; Based on the stable performance of the exhaust temperature at slow speed before parking, the exhaust temperature range of a single unit at a similar atmospheric temperature is established as the monitoring standard; After damage, the rotor blocking force may increase, the travel ease will change during the parking process, and the rotor stop time will be shortened. Therefore, the monitoring standard of the travel ease of a single engine can be established through statistics; the operating time from the moment the engine throttle lever is pulled to the moment the low-pressure speed drops to less than 15%, and the operating time from the moment the engine throttle lever is pulled to the moment the high-pressure speed drops to less than 15% can be counted, and the distribution range of the travel ease of a single engine can be established as a monitoring standard; When damage causes heat increase in the transmission system, the lubricating oil temperature will increase, and the corresponding lubricating oil pressure difference may also change. The lubricating oil temperature and lubricating oil pressure difference are basically stable in the slow-moving state before parking, and their working range is established as a monitoring standard.

2. The method for monitoring the working state of an aircraft engine rotor according to claim 1, characterized in that: Verify and improve, Based on the results of step one and step two, establish a monitoring range for the process parameters of a single engine. When a parameter exceeds the upper or lower limit, perform necessary supplementary inspections in addition to the normal inspection items, including inspections of the flow path of the rotor blades, metal content in the lubricating oil, and the working condition of the oil filter. Adjust the monitoring range based on the actual inspection results.

Images