CN114970022A - Monitoring method for airborne state of aircraft engine - Google Patents
Monitoring method for airborne state of aircraft engine Download PDFInfo
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- CN114970022A CN114970022A CN202210585257.2A CN202210585257A CN114970022A CN 114970022 A CN114970022 A CN 114970022A CN 202210585257 A CN202210585257 A CN 202210585257A CN 114970022 A CN114970022 A CN 114970022A
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Abstract
The invention provides a method for monitoring an airborne state of an aircraft engine, which comprises the following steps: acquiring thermal performance parameters such as engine speed, temperature and pressure and operation data in real time through a controller of the aircraft engine; then correcting the equivalent working duration and the equivalent start-stop times of the hot end component of the aero-engine according to an airborne online model; and then determining a maintenance plan according to the set maintenance rule and feeding back the maintenance plan to the crew. The invention fully considers the difference of each thermodynamic cycle of the aircraft engine under different flight conditions, can obtain accurate equivalent working time of the aircraft engine, ensures the safe and reliable operation of the aircraft engine and reduces unnecessary maintenance times.
Description
Technical Field
The invention relates to a method for monitoring the airborne state of an aircraft engine, which is used for judging the real start-stop times and the use duration of the aircraft engine so as to carry out the prepared maintenance judgment according to the situation and belongs to the technical field of health management of the aircraft engine.
Background
The maintenance of the aero-engine plays an important role in the whole-life cost management of the aero-engine, and besides the sale cost paid by purchasing the aero-engine, the cost for replacing parts, maintaining and maintaining in the later period is huge. In the whole life cycle of the aircraft engine, the cost required in the maintenance stage accounts for about 45-50%, and is close to the purchase cost, and in addition, the profit of the engine maintenance stage is higher. On the other hand, the operating state of the aircraft engine is directly related to the life safety of aircraft crewmembers and passengers, so that the aircraft engine must be maintained accurately and timely.
At present, the maintenance modes of the aircraft engine are mainly 2, firstly, a regular maintenance plan is very clear and easy, but the airline company worrys about the safety of the aircraft and carries out regular repair according to the takeoff frequency and the operation time of the aircraft, but the maintenance plan has the defect of waste, and sometimes the aircraft does not need to be repaired. The other method is maintenance according to the situation, namely, a maintenance plan is determined by monitoring the health state of the aircraft engine, the method needs to be well known about the design and manufacturing process of the aircraft engine, otherwise, the defect of 'overhaul' caused by one-time monitoring misappropriation can be caused, and an accident happens to the aircraft.
Based on the above, the invention provides a method for monitoring the airborne state of the aircraft engine, which can accurately obtain the equivalent operation times and the operation duration of the aircraft engine according to the actual state and the performance failure condition of the aircraft engine, and determine a maintenance plan by combining the traditional regular maintenance interval to prevent the aircraft engine from being overhauled and overhauled.
Disclosure of Invention
In order to achieve the aim, the invention provides a method for monitoring the airborne state of an aircraft engine, which is characterized by comprising the following steps:
acquiring thermal performance parameters such as engine speed, temperature and pressure and operation data in real time through a controller of the aircraft engine; then, with the help of the thermal performance parameters and the operation data, correcting the equivalent working duration and the equivalent start-stop times of the hot end component of the aircraft engine according to an airborne-based online model; and then determining a maintenance plan according to a set maintenance rule by combining the corrected parameters, and feeding back the maintenance plan to the crew. The invention fully considers the difference of each thermodynamic cycle of the aircraft engine under different flight conditions, can obtain accurate equivalent working time of the aircraft engine, ensures the safe and reliable operation of the aircraft engine and reduces unnecessary maintenance times.
Furthermore, the aircraft engine maintenance device can directly obtain the thermal performance parameters and the operation data of the aircraft engine through communication with the controller.
Further, the thermodynamic performance parameters and the operation data of the aircraft engine, the thermodynamic performance at least comprises a fan outlet temperature Tf, a high-pressure compressor outlet temperature Tc, a high-pressure compressor outlet pressure Pc, a high-pressure rotor rotating speed Nh, a low-pressure rotor rotating speed Nl and a turbine outlet temperature Tt, and the operation data at least comprises the normal start-stop times Ln, the rapid start-stop times Lm and the engine working duration Tw of the aircraft engine.
Further, the corrected start-stop times formula is as follows: and Lr is (Ln + Lm multiplied by a) multiplied by b, wherein Lr is the corrected start-stop times of the aircraft engine, a is a correction factor of the rapid start-stop times of the aircraft, and b is a correction factor according to the engine performance failure.
Further, the value of the correction factor a of the number of times of the rapid start and stop of the airplane is 10.
Further, the engine performance failure correction factor b is corrected by adopting the deviation between a mathematical model in an aircraft engine onboard maintenance device and an actual measured value, and the calculation formula of the engine performance failure correction factor b is as follows:
wherein Bm represents an engine parameter calculated by an airborne model of the airborne maintenance device of the aircraft engine, and Br is an actual measurement value of the aircraft engine on the wing.<Bm，Br>Representing two vectors Bm andinner product of vector Br | · | | non-woven phosphor 2 Representing the 2 norm of the vector.
Further, Bm calculated by the onboard model is [ Tf Tc Pc Nh Nl Tt ], where Tf, Tc, Pc, Nh, Nl, Tt are respectively a fan outlet temperature Tf, a high-pressure compressor outlet temperature Tc, a high-pressure compressor outlet pressure Pc, a high-pressure rotor rotation speed Nh, a low-pressure rotor rotation speed Nl, and a turbine outlet temperature Tt. The vector Br is also vector-assembled using the same parameters, except that its data is derived from the measured values of the aircraft engine on the wing.
Further, the engine performance failure correction factor b can also be calculated by adopting artificial intelligence algorithms such as a neural network and the like, and the deviation between the calculated value and the actual measured value of the airborne model is also obtained.
Further, the corrected engine operating time period is: tr is Tw multiplied by b, wherein Tr is the working time length of the corrected aircraft engine, and the value of b is the same as the value of the working time length of the corrected aircraft engine.
Further, the maintenance rule of the aero-engine is set as follows: if Lr is greater than 300 or Tr is greater than 1000, performing maintenance on the hot end part of the aircraft engine; and if Lr is greater than 1000 or Tr is greater than 2000, performing the maintenance of the whole aircraft engine.
Compared with the prior art, the invention has the following advantages and prominent technical effects:
1. the airborne maintenance device of the aircraft engine acquires data from the controller instead of directly acquiring data from the sensor, so that the wiring challenge on the engine is reduced, and the requirement on data processing capacity is lowered;
2. the start-stop times and the running time of the aero-engine are corrected by adopting the airborne model, so that the method is closer to the actual working and running of the aero-engine, and the prediction accuracy is higher because the service life of a hot end part of the aero-engine is closely related to the working temperature of the aero-engine;
3. the whole algorithm is simple and easy to implement, the whole maintenance framework is suitable for various aero-engines, engineering is easy to realize, and the maintenance cost of the engines is reduced.
Drawings
FIG. 1 is a logic diagram of a method for monitoring an airborne state of an aircraft engine according to an embodiment of the invention.
Detailed Description
In order that the above objects, features and advantages of the present invention can be more clearly understood, a more particular description of the invention will be rendered by reference to the appended drawings. It should be noted that the embodiments and features of the embodiments of the present application may be combined with each other without conflict.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than those specifically described herein, and therefore the scope of the present invention is not limited by the specific embodiments disclosed below.
Example one
The logic of the device and the method for monitoring the onboard state of the aero-engine is shown in figure 1, wherein the logic of the device and the method for monitoring the onboard state of the aero-engine is that a certain type of small aero-engine is taken as an application object, the combustion fuel of the small aero-engine is aviation kerosene, and the method comprises the following steps:
s1, the maintenance device of the aero-engine is directly connected with a controller and arranged on a fan case of the aero-engine.
S2, the maintenance device obtains thermal performance parameters and operation data of the aircraft engine in real time, wherein the thermal performance parameters comprise fan outlet temperature Tf, high-pressure compressor outlet temperature Tc, high-pressure compressor outlet pressure Pc, high-pressure rotor rotating speed Nh, low-pressure rotor rotating speed Nl and turbine outlet temperature Tt. The operation data at least comprises the normal start-stop times Ln, the rapid start-stop times Lm and the engine working time Tw of the aircraft engine.
And S3, extracting the thermal performance parameters of the aircraft engine calculated by the onboard model on the maintenance device, wherein the thermal performance parameters also comprise the fan outlet temperature Tf, the high-pressure compressor outlet temperature Tc, the high-pressure compressor outlet pressure Pc, the high-pressure rotor rotating speed Nh, the low-pressure rotor rotating speed Nl and the turbine outlet temperature Tt.
And S4, calculating the corrected start-stop times Lr and the corrected engine working time Tr according to the method.
And S5, judging whether Lr is greater than 1000 or Tr is greater than 2000, if so, entering S6, and recommending the maintenance of the whole aircraft engine. In this embodiment, this condition is not satisfied, and the process proceeds to S7.
S7, continuously judging whether Lr is greater than 300 or Tr is greater than 1000, and if the conditions are met, entering S8 to recommend maintenance of the combustion chamber and the turbine of the hot-end component of the aircraft engine. In this embodiment, this condition is not satisfied, and the process proceeds to S9.
And S9, the aero-engine can continue to operate when the service life of the aero-engine is not reached.
Claims (10)
1. A method for monitoring the airborne state of an aircraft engine is characterized by comprising the following steps:
(1) acquiring thermal performance parameters and operation data of an engine in real time through a controller of the aircraft engine;
(2) then, the data is used for correcting the equivalent working duration and the equivalent start-stop times of the hot end component of the aero-engine according to an airborne online model;
(3) and then determining a maintenance plan according to the set maintenance rule by combining the corrected equivalent working time and the equivalent start-stop times, and feeding back the maintenance plan to the crew.
The invention fully considers the difference of each thermodynamic cycle of the aircraft engine under different flight conditions, can obtain accurate equivalent working time of the aircraft engine, ensures the safe and reliable operation of the aircraft engine and reduces unnecessary maintenance times.
2. A method of monitoring the condition of an aircraft engine on board a vehicle as claimed in claim 1, wherein: the thermal performance parameters of the aircraft engine at least comprise a fan outlet temperature Tf, a high-pressure compressor outlet temperature Tc, a high-pressure compressor outlet pressure Pc, a high-pressure rotor rotating speed Nh, a low-pressure rotor rotating speed Nl and a turbine outlet temperature Tt, and the operation data at least comprise the normal start-stop times Ln, the rapid start-stop times Lm and the engine working time Tw of the aircraft engine.
3. A method of monitoring the condition onboard an aircraft engine as claimed in claim 2, wherein: the corrected engine operating time period is: tr is Tw multiplied by b, wherein Tr is the working time length of the corrected aircraft engine and is a correction factor according to the engine performance failure.
4. A method of monitoring the condition onboard an aircraft engine as claimed in claim 2, wherein: the formula of the corrected start-stop times is as follows: and Lr is (Ln + Lm multiplied by a) multiplied by b, wherein Lr is the corrected start-stop times of the aircraft engine, a is a correction factor of the rapid start-stop times of the aircraft, and b is a correction factor according to the engine performance failure.
5. A method for monitoring the condition onboard an aircraft engine, as claimed in claim 4, wherein: and the value of the correction factor a of the number of times of the rapid start and stop of the airplane is 10.
6. A method for monitoring the condition onboard an aircraft engine according to any one of claims 3 to 5, characterized in that: the engine performance failure correction factor b is corrected by adopting the deviation between a mathematical model in an airborne maintenance device of the aircraft engine and an actual measured value, and the calculation formula of the engine performance failure correction factor b is as follows:
wherein Bm represents an engine parameter calculated by an airborne model of the airborne maintenance device of the aircraft engine, and Br is an actual measurement value of the aircraft engine on the wing.<Bm，Br>Represents the inner product of two vectors Bm and Br, | | · | | the girth 2 Representing the 2-norm of the vector.
7. A method of monitoring the condition of an aircraft engine on-board a vehicle as claimed in claim 6, wherein: and (3) calculating Bm [ TfTcPnHNl Tt ] by the airborne model, wherein Tf, Tc, Pc, Nh, Nl and Tt are respectively fan outlet temperature Tf, high-pressure compressor outlet temperature Tc, high-pressure compressor outlet pressure Pc, high-pressure rotor rotating speed Nh, low-pressure rotor rotating speed Nl and turbine outlet temperature Tt, and vector Br is subjected to vector combination by adopting the same parameters, except that the data of the vector Br is from the actual measurement value of the aeroengine on the wing.
8. A method for monitoring the condition onboard an aircraft engine according to any one of claims 3 to 5, characterized in that: the engine performance failure correction factor b is calculated by adopting an artificial intelligence algorithm, the deviation between the calculated value of the airborne model and the actual measured value is also obtained, and preferably, the artificial intelligence algorithm is a neural network artificial intelligence algorithm.
9. A method for monitoring the condition onboard an aircraft engine as claimed in claim 3 or 4, characterized in that: the maintenance rule of the aero-engine is set as follows: if Lr is greater than 300 or Tr is greater than 1000, performing maintenance on the hot end part of the aeroengine; if Lr is greater than 1000 or Tr is greater than 2000, the aircraft engine is maintained as a whole, and if both are not satisfied, the aircraft engine can continue to operate without reaching the service life.
10. A method of monitoring the condition onboard an aircraft engine as claimed in any one of claims 1 to 9, characterised in that: the aircraft engine maintenance device directly obtains thermal performance parameters and operation data of the aircraft engine through communication with the controller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210585257.2A CN114970022A (en) | 2022-05-27 | 2022-05-27 | Monitoring method for airborne state of aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210585257.2A CN114970022A (en) | 2022-05-27 | 2022-05-27 | Monitoring method for airborne state of aircraft engine |
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| CN114970022A true CN114970022A (en) | 2022-08-30 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116147929A (en) * | 2023-04-20 | 2023-05-23 | 清华大学 | Method, device and equipment for determining current value of stress-applied flame detector of aero-engine |
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2022
- 2022-05-27 CN CN202210585257.2A patent/CN114970022A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116147929A (en) * | 2023-04-20 | 2023-05-23 | 清华大学 | Method, device and equipment for determining current value of stress-applied flame detector of aero-engine |
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