CN114970022A - Monitoring method for airborne state of aircraft engine - Google Patents

Abstract

The invention provides a method for monitoring the airborne state of an aeroengine, the method comprising: obtaining thermal performance parameters and operating data such as engine speed, temperature and pressure in real time through a controller of the aeroengine; Correct the equivalent working hours and equivalent start-stop times of the hot-end components of the aero-engine; then determine the maintenance plan according to the set maintenance law, and feed it back to the crew. The present invention fully considers the difference of each thermodynamic cycle of the aero-engine under different flight conditions, can obtain accurate equivalent working time of the aero-engine for a long time, ensure the safe and reliable operation of the aero-engine, and reduce unnecessary maintenance times.

Description

A method for monitoring the airborne condition of aero-engine

technical field

The invention relates to a monitoring method for the airborne state of an aeroengine, which is used for judging the actual start and stop times and use time of the aeroengine, so as to make a condition-based maintenance judgment of preparations, and belongs to the technical field of aeroengine health management.

Background technique

The maintenance of aero-engines plays an important role in the life-cycle cost management of aero-engines. In addition to the sales expenses paid for purchasing the engine, the cost of replacing parts, repairs and maintenance in the later period is huge. In the entire life cycle of an aero-engine, the cost of the maintenance stage accounts for about 45-50%, which is close to the procurement cost. In addition, the profit of the engine maintenance stage is also relatively high. On the other hand, the running state of aero-engines is directly related to the life safety of aircraft crew and passengers, so it is necessary to carry out accurate and timely maintenance on aero-engines.

At present, there are mainly two maintenance methods for aero-engines. One is the regular maintenance plan. This plan is very clear and easy. However, because the airlines are worried about the safety of the aircraft, they carry out regular repairs according to the number of aircraft takeoffs and operating hours, but this maintenance plan exists. The downside of waste, sometimes the plane doesn't need repairs. The other is condition-based maintenance, that is, by monitoring the health status of the aero-engine to determine the maintenance plan. This method requires a very good understanding of the design and manufacturing process of the aero-engine itself, otherwise an improper monitoring may cause the drawback of "disrepair", leading to Airplane accident.

Based on this, the present invention provides a method for monitoring the on-board state of an aero-engine, which can accurately obtain the equivalent running times and running time of the aero-engine according to the actual state and performance failure of the aero-engine. Combined with the traditional regular maintenance interval, Determine the maintenance plan to prevent "over-repair" and "disrepair" of aero-engines.

SUMMARY OF THE INVENTION

In order to achieve the above purpose, the present invention proposes a method for monitoring the airborne state of an aero-engine, which is characterized by comprising the following steps:

The thermal performance parameters and operating data such as engine speed, temperature and pressure are obtained in real time through the controller of the aero-engine; then, with the help of the above thermal performance parameters and operating data, the equivalent of the hot-end components of the aero-engine is corrected according to an airborne online model. Working hours and equivalent start-stop times; then according to the set maintenance rules, combined with the above revised parameters, the maintenance plan is determined and fed back to the maintenance personnel. The present invention fully considers the difference of each thermodynamic cycle of the aero-engine under different flight conditions, can obtain accurate equivalent working time of the aero-engine for a long time, ensure the safe and reliable operation of the aero-engine, and reduce unnecessary maintenance times.

Further, the aero-engine maintenance device can directly obtain the thermal performance parameters and operating data of the aero-engine by communicating with the controller.

Further, the thermal performance parameters and operating data of the aero-engine include at least the fan outlet temperature Tf, the high pressure compressor outlet temperature Tc, the high pressure compressor outlet pressure Pc, the high pressure rotor speed Nh, the low pressure rotor speed N1 and the turbine outlet temperature Tt. , the operation data at least include the normal start-stop times Ln, the quick start-stop times Lm and the engine working time Tw.

Further, the corrected start-stop times formula is: Lr=(Ln+Lm×a)×b, where Lr is the number of starts and stops after the aero-engine correction, a is the correction factor for the number of quick starts and stops of the aircraft, and b is the number of starts and stops based on the engine. Performance exhaustion correction factor.

Further, the correction factor a of the number of times of rapid start and stop of the aircraft takes a value of 10.

Further, the engine performance failure correction factor b is corrected by the deviation between the mathematical model in the aero-engine on-board maintenance device and the actual measured value, and the calculation formula of the engine performance failure correction factor b is as follows:

Among them, Bm represents the engine parameter calculated by the on-board model of the aero-engine on-board maintenance device, and Br is the measured value of the aero-engine on the wing. <Bm, Br> represents the inner product of two vectors Bm and Br, and ||·|| ₂ represents the 2-norm of the vector.

Further, Bm=[Tf Tc Pc Nh Nl Tt] calculated by the airborne model, where Tf, Tc, Pc, Nh, Nl, and Tt are the fan outlet temperature Tf, the high-pressure compressor outlet temperature Tc, and the high-pressure compressor outlet pressure, respectively. Pc, high pressure rotor speed Nh, low pressure rotor speed Nl and turbine outlet temperature Tt. The vector Br also uses the same parameters for vector combination, but its data comes from the measured value of the aero-engine on the wing.

Further, the engine performance failure correction factor b can also be calculated by artificial intelligence algorithms such as neural network, which also obtains the deviation between the calculated value of the airborne model and the actual measured value.

Further, the corrected operating time of the engine is: Tr=Tw×b, where Tr is the corrected operating time of the aero-engine, and the value of b is the same as the above.

Further, the set aero-engine maintenance rule is: if Lr>300 or Tr>1000, carry out the maintenance of the hot-end parts of the aero-engine; if Lr>1000 or Tr>2000, carry out the maintenance of the whole aero-engine.

Compared with the prior art, the present invention has the following advantages and outstanding technical effects:

1. This aero-engine airborne maintenance device uses data obtained from the controller instead of directly from the sensor, which reduces the challenge of wiring on the engine and reduces the requirements for data processing capabilities;

2. The on-board model is used to correct the start-stop times and running time of the aero-engine, which is closer to the actual operation of the aero-engine, because the life of the hot-end components of the aero-engine is closely related to the working temperature, and the prediction accuracy is higher;

3. The entire algorithm is simple and easy to implement, and the entire maintenance framework is applicable to all types of aero-engines, which is easy to implement in engineering and reduces engine maintenance costs.

Description of drawings

FIG. 1 is a logic diagram of a method for monitoring the on-board state of an aero-engine provided by an embodiment of the present invention.

Detailed ways

In order to understand the above objects, features and advantages of the present invention more clearly, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that the embodiments of the present application and the features in the embodiments may be combined with each other in the case of no conflict.

Many specific details are set forth in the following description to facilitate a full understanding of the present invention. However, the present invention can also be implemented in other ways different from those described herein. Therefore, the protection scope of the present invention is not limited by the specific details disclosed below. Example limitations.

Example 1

Taking a certain type of small aero-engine as the application object, and its combustion fuel is aviation kerosene, the on-board state monitoring device and method logic of the aero-engine are shown in Figure 1. The method includes:

S1. The aero-engine maintenance device is directly connected to the controller and installed on the fan casing of the aero-engine.

S2. The maintenance device obtains the thermal performance parameters and operating data of the aero-engine in real time. The thermal performance parameters include the fan outlet temperature Tf, the high-pressure compressor outlet temperature Tc, the high-pressure compressor outlet pressure Pc, the high-pressure rotor speed Nh, the low-pressure rotor speed Nl and the turbine. Outlet temperature Tt. The operating data include at least the normal start-stop times Ln, the rapid start-stop times Lm and the engine working time Tw.

S3. Extract the aero-engine thermal performance parameters calculated by the airborne model on the maintenance device, including the fan outlet temperature Tf, the high-pressure compressor outlet temperature Tc, the high-pressure compressor outlet pressure Pc, the high-pressure rotor speed Nh, the low-pressure rotor speed Nl, and the turbine outlet. temperature Tt.

S4. Calculate the corrected start-stop times Lr and the corrected engine operating time Tr according to the present invention.

S5. Determine whether Lr>1000 or Tr>2000, if the conditions are met, go to S6, and it is recommended to carry out maintenance of the aero-engine. In this embodiment, this condition is not satisfied, so it goes to S7.

S7. Continue to judge whether Lr>300 or Tr>1000. If the conditions are met, go to S8, and it is recommended to carry out maintenance of the combustion chamber and turbine of the aero-engine hot-end components. In this embodiment, this condition is not satisfied, so it goes to S9.

S9. The aero-engine can continue to run if it has not reached its lifespan.

Claims (10)

1. a monitoring method of aero-engine airborne state, is characterized in that comprising the following steps: (1) Obtain the thermal performance parameters and operating data of the engine in real time through the controller of the aero-engine; (2) Then use the above data to correct the equivalent working time and equivalent start-stop times of the aero-engine hot-end components according to an airborne online model; (3) Then, according to the set maintenance rules, combined with the corrected equivalent working hours and equivalent start-stop times, the maintenance plan is determined and fed back to the maintenance personnel. The present invention fully considers the difference of each thermodynamic cycle of the aero-engine under different flight conditions, can obtain accurate equivalent working time of the aero-engine for a long time, ensure the safe and reliable operation of the aero-engine, and reduce unnecessary maintenance times. 2. the monitoring method of a kind of aero-engine airborne state according to claim 1, it is characterized in that: the thermal performance parameter of described aero-engine at least comprises fan outlet temperature Tf, high-pressure compressor outlet temperature Tc, high-pressure compressor outlet Pressure Pc, high pressure rotor speed Nh, low pressure rotor speed Nl and turbine outlet temperature Tt, the operating data at least include the normal start-stop times Ln, rapid start-stop times Lm and engine operating time Tw of the aero-engine. 3. the monitoring method of a kind of aero-engine airborne state according to claim 2, it is characterized in that: the engine working time length after the correction is: Tr=Tw × b, wherein Tr is the working time length after the aero-engine correction, is Failure correction factor based on engine performance. 4. the monitoring method of a kind of aero-engine airborne state according to claim 2 is characterized in that: the formula of the number of times of starting and stopping after the correction is: Lr=(Ln+Lm×a)×b, wherein Lr is the aero-engine The number of starts and stops after correction, a is the correction factor for the number of rapid start and stop of the aircraft, and b is the correction factor according to engine performance failure. 5 . The method for monitoring the on-board state of an aero-engine according to claim 4 , wherein the correction factor a for the number of times of rapid start and stop of the aircraft takes a value of 10. 6 . 6. The method for monitoring the on-board state of an aero-engine according to any one of claims 3-5, wherein the engine performance failure correction factor b adopts the mathematical model in the on-board maintenance device of the aero-engine and the actual The deviation of the measured value is corrected, and the calculation formula of the engine performance failure correction factor b is as follows:

Among them, Bm represents the engine parameter calculated by the on-board model of the aero-engine on-board maintenance device, and Br is the measured value of the aero-engine on the wing. <Bm, Br> represents the inner product of two vectors Bm and Br, and ||·|| ₂ represents the 2-norm of the vector. 7. The method for monitoring the on-board state of an aero-engine according to claim 6, wherein: Bm=[TfTc Pc Nh Nl Tt] calculated by the on-board model, wherein Tf, Tc, Pc, Nh, Nl and Tt are the fan outlet temperature Tf, the high pressure compressor outlet temperature Tc, the high pressure compressor outlet pressure Pc, the high pressure rotor speed Nh, the low pressure rotor speed Nl and the turbine outlet temperature Tt, respectively. The vector Br also uses the same parameters for vector combination, It's just that its data comes from the measured value of the aircraft engine on the wing. 8. The method for monitoring the airborne state of an aero-engine according to any one of claims 3-5, wherein the engine performance failure correction factor b is calculated by an artificial intelligence algorithm, and is also calculated by obtaining an airborne model. The deviation between the value and the actual measured value, preferably, the artificial intelligence algorithm is a neural network artificial intelligence algorithm. 9. the monitoring method of a kind of aero-engine airborne state according to claim 3 or 4, it is characterized in that: the maintenance rule of aero-engine set is: if Lr>300 or Tr>1000, carry out aero-engine hot-end components Maintenance; if Lr>1000 or Tr>2000, complete aero-engine maintenance, if both are not satisfied, the aero-engine can continue to run before reaching its lifespan. 10. The method for monitoring the on-board state of an aero-engine according to any one of claims 1-9, wherein the aero-engine maintenance device directly obtains the thermal performance parameters and operating data of the aero-engine by communicating with the controller .

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