CN111693180B - Exhaust temperature over-temperature fault detection method for auxiliary power system - Google Patents
Exhaust temperature over-temperature fault detection method for auxiliary power system Download PDFInfo
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- CN111693180B CN111693180B CN202010461026.1A CN202010461026A CN111693180B CN 111693180 B CN111693180 B CN 111693180B CN 202010461026 A CN202010461026 A CN 202010461026A CN 111693180 B CN111693180 B CN 111693180B
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- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
- G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Abstract
The invention belongs to the field of aviation power control, and provides a fault detection method for exhaust temperature overtemperature of an auxiliary power system, aiming at the defect of inaccurate control caused by a temperature threshold and delay time setting method in the traditional detection method. On the basis of the traditional fixed temperature threshold, the traditional fixed temperature threshold condition is corrected, the temperature threshold value and the delay time length of the over-temperature of the APU exhaust temperature are dynamically adjusted according to the environmental conditions such as the flight height, the cold end compensation temperature, the APU rotating speed, the APU exhaust temperature and the inlet temperature, the operation time of the auxiliary power device is prolonged, unnecessary stop control is reduced, key parts of an engine can be protected, and faults can be delayed as much as possible.
Description
Technical Field
The invention belongs to the field of aviation power control, and relates to a method for detecting an exhaust temperature overtemperature fault of an Auxiliary Power Unit (APU).
Background
The auxiliary power system is a power system independent from the engine, is used for providing auxiliary or emergency energy for the airplane, and simultaneously provides bleed air power, hydraulic power and electric power, and is a key system for ensuring safe flight of the airplane.
The APU exhaust temperature, which is one of key performance indexes of a reaction auxiliary power system, plays a very important role in the whole system, is not only the most common aerodynamic performance index, provides decision basis for health management of the auxiliary power system, but also one of important parameters influencing fuel control, anti-surge control and start-stop control, and important engine parts such as a combustion chamber, a turbine blade, a tail nozzle and the like can be damaged when the temperature of the APU exhaust temperature exceeds the temperature.
The traditional APU exhaust temperature over-temperature fault condition is that different temperature thresholds and delay times are set according to different phases in which the APU is located, but different operating environments can also influence the temperature thresholds and the delay times in addition to different phases in which the APU is located, for example, when the APU operates on the ground, the temperature threshold is a, and when the APU operates in the sky, the temperature threshold is b in the same operating phase, and it is assumed that b is larger than a. Then according to the conventional control process, when the APU operates in the sky and the APU exhaust temperature reaches a, the operation is stopped, which results in a shortened APU operating state and inaccurate control.
Disclosure of Invention
Aiming at the defect that the traditional detection method causes inaccurate control due to a temperature threshold and delay time setting method, the invention introduces a dynamic regulation mechanism, improves the detection method of the APU exhaust temperature over-temperature fault, and dynamically regulates the temperature threshold and the delay time of the APU exhaust temperature over-temperature through factors such as flight height, cold end compensation temperature, APU rotating speed, APU exhaust temperature and inlet temperature, so that the effects of protecting important parts of an engine, having certain regulation capacity and delaying the fault as much as possible are achieved.
The technical scheme of the invention is as follows:
the method for detecting the exhaust temperature overtemperature fault of the auxiliary power system is characterized by comprising the following steps of:
step one, setting an exhaust temperature overtemperature threshold and delay time according to different stages of the rotation speed of the APU and by referring to different influence factors:
step 1, when the rotation speed of the APU is in a starting stage, the influence factors are flight height, cold end compensation temperature, the rotation speed of the APU and the exhaust temperature of the APU, and an exhaust temperature overtemperature threshold and delay time are set according to the flight height, the cold end compensation temperature, the rotation speed of the APU and the exhaust temperature of the APU;
step 2, when the rotation speed of the APU is in a steady state stage, the influence factors are inlet temperature and APU exhaust temperature, and an exhaust temperature overtemperature threshold and delay time are set according to the inlet temperature and the APU exhaust temperature;
and step two, collecting the APU exhaust temperature and the time delay, judging the current APU rotating speed stage and the corresponding influence factors, comparing the collected APU exhaust temperature and the time delay with the exhaust temperature overtemperature threshold and the time delay set under the corresponding APU rotating speed stage and the influence factors in the step 1 respectively, and judging whether the APU exhaust temperature is in overtemperature fault or not.
Further, the first step is specifically as follows:
when the APU rotating speed is in the starting stage, the exhaust temperature overtemperature threshold and the delay time are comprehensively set according to the flight height, the cold end compensation temperature, the APU rotating speed and the APU exhaust temperature.
Step 1.1, when the cold end compensation temperature is abnormal or the flying height is higher than 8km, because the cold end compensation temperature is failed at the moment, the APU is in a starting stage, and the rotation speed of the APU is in a full power rising stage, an exhaust temperature overtemperature threshold and delay time are set according to the rotation speed of the APU at the moment.
Step 1.1.1, when the rotation speed of the APU is in the interval of [0, the starter is disengaged from the rotation speed ], the APU is in the acceleration starting stage at the moment, the exhaust temperature of the APU also changes rapidly, the exhaust temperature overtemperature threshold is set to be the maximum starting allowable temperature at the moment, and the delay time is set to be the maximum starting allowable time.
Step 1.1.2, when the rotation speed of the APU is in the interval of the (starter disengagement rotation speed point and the steady state rotation speed point), because the APU is already in the self-acceleration stage at the moment, the exhaust temperature of the APU is gradually reduced to the steady state, the exhaust temperature overtemperature threshold is gradually reduced to the maximum allowable temperature for steady state switching at the moment, and the delay time is set as the longest allowable starting time.
And step 1.2, when the cold end compensation temperature is normal and the airplane is in low altitude or on the ground, setting an exhaust temperature overtemperature threshold and delay time according to the flying height.
And 1.2.1, when the flying height is in a high-altitude interval, setting the temperature overtemperature threshold of the exhaust valve as the minimum starting allowable temperature, and setting the delay time as the starting allowable time.
And step 1.2.2, when the flying height is in a low-altitude interval, setting an exhaust temperature overtemperature threshold and delay time according to the exhaust temperature of the APU.
Step 1.2.2.1, when the APU exhaust temperature does not exceed the set temperature, wherein the set temperature is set according to different objects and is lower than the starting maximum allowable temperature by 100-.
And 1.2.2.2, when the APU exhaust temperature exceeds the set temperature, because the abnormal APU exhaust temperature is high at the moment and can cause key faults such as engine ignition and the like, immediately shortening the exhaust temperature delay time to be the minimum starting allowed time, and setting the exhaust temperature overtemperature threshold to be the minimum starting allowed temperature.
When the rotation speed of the APU is in a steady state stage, an exhaust temperature overtemperature threshold and a delay time are set according to the inlet temperature and the APU exhaust temperature.
And 2.1, when the inlet temperature is normal, setting an exhaust temperature overtemperature threshold and delay time according to the exhaust temperature of the APU.
Step 2.1.1, when the APU exhaust temperature does not exceed the set temperature, calculating the exhaust temperature overtemperature threshold according to the inlet temperature, wherein the specific formula is as follows:
adjusting the baseline temperature by the exhaust temperature overtemperature threshold value k + the inlet temperature; wherein k is an inlet temperature adjustment coefficient;
the delay time is the maximum allowable time of the steady state;
and 2.1.2, when the exhaust temperature of the APU exceeds the set temperature, because the APU is already in a steady state at the moment, the exhaust temperature of the APU and the rotation speed of the APU tend to be stable and the inlet temperature is normal, setting the exhaust temperature overtemperature threshold as the maximum allowable temperature of the steady state, and setting the delay time as the minimum allowable time of the steady state.
And 2.2, when the inlet temperature is abnormal, setting an exhaust temperature overtemperature threshold and delay time according to the exhaust temperature of the APU.
And 2.2.1, when the APU exhaust temperature does not exceed the set temperature, setting the exhaust temperature overtemperature threshold as the minimum allowable steady-state temperature due to abnormal inlet temperature, and setting the delay time as the maximum allowable steady-state time.
And 2.2.2, when the exhaust temperature of the APU exceeds the set temperature, immediately setting the exhaust valve temperature over-temperature as the maximum allowable steady-state temperature, and setting the delay time as the minimum allowable steady-state time.
The invention has the beneficial effects that:
aiming at the problem of the over-temperature of the exhaust temperature of the APU, the invention corrects the traditional fixed temperature threshold condition on the basis of the traditional fixed temperature threshold, and dynamically sets the temperature threshold value and the time delay duration of the over-temperature of the exhaust temperature of the APU according to the environmental conditions such as the flight height, the cold end compensation temperature, the rotation speed of the APU, the exhaust temperature of the APU, the inlet temperature and the like, thereby not only protecting key parts of an engine, but also delaying the occurrence of faults as much as possible, prolonging the working time of an auxiliary power system and forbidding unnecessary parking operation.
Drawings
FIG. 1 is a logic diagram of an APU exhaust temperature over-temperature fault;
FIG. 2a is a plot of ground/air APU exhaust temperature fault failure reporting data at startup;
FIG. 2b is a plot of ground/air APU exhaust temperature fault failure reporting data at steady state;
Detailed Description
The method for detecting the exhaust temperature overtemperature fault of the auxiliary power system mainly comprises the following two steps: firstly, setting an exhaust temperature overtemperature threshold and delay time according to different stages of the rotation speed of the APU and by referring to different parameters or influencing factors. Specifically, when the APU rotating speed is in the starting stage, the exhaust temperature overtemperature threshold and the delay time can be set according to the flight height, the cold end compensation temperature, the APU rotating speed and the APU exhaust temperature; when the rotation speed of the APU is in a steady state stage, an exhaust temperature overtemperature threshold and delay time can be set according to the inlet temperature and the APU exhaust temperature; and then, collecting the current APU exhaust temperature and delay time, judging the current APU rotating speed stage and corresponding condition parameters or influencing factors, comparing the collected APU exhaust temperature and delay time with the exhaust temperature overtemperature threshold and the delay time under the corresponding APU rotating speed stage and the condition parameters or the influencing factors in the step 1 respectively, and judging whether the APU exhaust temperature is in overtemperature fault or not.
The invention is further described with reference to the following figures and specific embodiments.
In this embodiment, for an electronic controller of a certain type of auxiliary power system, the method shown in fig. 1 is adopted to set the over-temperature threshold and the delay time of the APU exhaust temperature, which specifically includes the following steps:
step 1.1, when the cold end compensation temperature fault or the flying height is higher than 8km, because the cold end compensation temperature fault and the APU are in the starting stage at the moment, and the rotation speed of the APU is in the full power rising stage, the exhaust temperature overtemperature threshold and the delay time are set according to the rotation speed of the APU at the moment.
Step 1.1.1, when the rotation speed of the APU is in the interval of [0, the starter is disengaged from the rotation speed ], the APU is in the acceleration starting stage at the moment, the exhaust temperature of the APU also changes rapidly, the exhaust temperature overtemperature threshold is set as the maximum starting allowable temperature at the moment, and the delay time is set as the maximum starting allowable time. In the embodiment, the starting machine disengagement rotating speed point is set to be 60%, the maximum starting allowable temperature is 1084 ℃, and the maximum starting allowable time is 10 s.
Step 1.1.2, when the rotation speed of the APU is in an interval of (a starter disengagement rotation speed point and a steady state rotation speed point), because the APU is already in a self-acceleration stage at the moment, the exhaust temperature of the APU is gradually reduced to a steady state, the exhaust temperature overtemperature threshold is gradually reduced to the maximum allowable temperature for steady state switching at the moment, and the delay time is set as the maximum allowable starting time of 10 s. The present embodiment sets the steady state rotation speed point to 98%, and the steady state switching maximum allowable temperature point 881 ℃. The start-to-steady interpolation is set as a linear interpolation, the temperature profile is set as a linear interpolation, and the steady state inlet temperature adjustment factor is set at 0.3634.
And step 1.2, when the cold end compensation temperature is normal and the airplane is in low altitude or on the ground, setting an exhaust temperature overtemperature threshold and delay time according to the flying height.
Step 1.2.1, when the flight height is in a high-altitude interval, wherein the high-altitude interval is [4500m,8000m ]; the exhaust valve temperature overtemperature threshold is set as a starting minimum allowable temperature, and the delay time is set as a starting allowable time. The present embodiment sets the startup minimum allowable temperature to 742 ℃ and the startup allowable time to 4 s.
Step 1.2.2, when the flight height is in a low altitude area, wherein the low altitude area is a bottom surface or is lower than 4500 m; and setting an exhaust temperature overtemperature threshold and delay time according to the exhaust temperature of the APU.
Step 1.2.2.1, when the APU exhaust temperature does not exceed the set temperature, which is 844 ℃ in the embodiment, because the APU is about to finish starting at the moment, the exhaust temperature overtemperature threshold is set to be 742 ℃ which is the minimum allowable starting temperature, and the delay time is set to be 10s which is the maximum allowable starting time.
And step 1.2.2.2, when the APU exhaust temperature exceeds the set temperature, because the abnormal APU exhaust temperature is high at the moment, the key faults such as engine ignition and the like can be caused, the exhaust temperature delay time is immediately shortened to be the minimum starting allowable time, and the exhaust temperature overtemperature threshold is set to be the minimum starting allowable temperature 742 ℃. The present embodiment sets the starting shortest allowable time to 1 s.
When the rotation speed of the APU is in a steady state stage, an exhaust temperature overtemperature threshold and a delay time are set according to the inlet temperature and the APU exhaust temperature.
And 2.1, when the inlet temperature is normal, setting an exhaust temperature overtemperature threshold and delay time according to the exhaust temperature of the APU.
Step 2.1.1, when the APU exhaust temperature does not exceed the set temperature, calculating the exhaust temperature overtemperature threshold according to the inlet temperature, wherein the specific formula is as follows:
the exhaust temperature overtemperature threshold value k + inlet temperature adjustment baseline temperature 724 ℃; where k is equal to 0.3634, the inlet temperature adjustment coefficient;
the delay time is the longest allowable steady-state time of 10 s;
and 2.1.2, when the exhaust temperature of the APU exceeds the set temperature, because the APU is already in a steady state at the moment, the exhaust temperature of the APU and the rotation speed of the APU tend to be stable and the inlet temperature is normal, setting the exhaust temperature overtemperature threshold as the maximum allowable temperature of the steady state, and setting the delay time as the minimum allowable time of the steady state. In the embodiment, the maximum allowable steady-state temperature is 844 ℃, and the minimum allowable steady-state time is 1 s;
and 2.2, when the inlet temperature is abnormal, setting an exhaust temperature overtemperature threshold and delay time according to the exhaust temperature of the APU.
And 2.2.1, when the APU exhaust temperature does not exceed the set temperature, setting the exhaust temperature overtemperature threshold as the minimum allowable steady-state temperature due to abnormal inlet temperature, and setting the delay time as the maximum allowable steady-state time. In this example, the minimum allowable steady-state temperature is 718 ℃ and the maximum allowable steady-state time is 10 s.
And 2.2.2, when the exhaust temperature of the APU exceeds the set temperature, immediately setting the overtemperature of the exhaust valve temperature to be 844 ℃ of the maximum allowable steady-state temperature, and setting the delay time to be 1s of the minimum allowable steady-state time.
And performing functional performance reliability verification on the fault detection method on the environment test equipment.
Firstly, simulating a fault site, and injecting faults through an environment test device.
And secondly, setting the control period to be 20ms, normally starting the APU through the environment test equipment, wherein fault data in the starting process are shown in figure 2a, and fault data in the steady state process are shown in figure 2 b.
In FIG. 2a, APU exhaust temperature over-temperature data is injected in the starting process of the APU, and when the APU exhaust temperature exceeds a set threshold value (1084 ℃) and the delay time exceeds 10 seconds, the controller reports a fault. FIG. 2b shows that when the APU exhaust temperature exceeds the set threshold (844 ℃) and the delay time exceeds 1s, the controller reports a fault, wherein the APU exhaust temperature overtemperature data is injected in the steady-state operation process of the APU.
Claims (2)
1. The method for detecting the exhaust temperature overtemperature fault of the auxiliary power system is characterized by comprising the following steps of:
step one, setting an exhaust temperature overtemperature threshold and delay time according to different stages of the rotation speed of the APU and by referring to different influence factors:
step 1, when the rotation speed of the APU is in a starting stage, the influence factors are flight height, cold end compensation temperature, the rotation speed of the APU and the exhaust temperature of the APU, and an exhaust temperature overtemperature threshold and delay time are set according to the flight height, the cold end compensation temperature, the rotation speed of the APU and the exhaust temperature of the APU;
step 2, when the rotation speed of the APU is in a steady state stage, the influence factors are inlet temperature and APU exhaust temperature, and an exhaust temperature overtemperature threshold and delay time are set according to the inlet temperature and the APU exhaust temperature;
and step two, collecting the APU exhaust temperature and the time delay, judging the current APU rotating speed stage and the corresponding influence factors, comparing the collected APU exhaust temperature and the time delay with the exhaust temperature overtemperature threshold and the time delay set under the corresponding APU rotating speed stage and the influence factors in the step 1 respectively, and judging whether the APU exhaust temperature is in overtemperature fault or not.
2. The auxiliary power system exhaust temperature over-temperature fault detection method according to claim 1, characterized in that the first step is specifically:
when the APU speed is in the starting phase:
step 1.1, when the cold end compensation temperature is abnormal or the flying height is higher than 8km, setting an exhaust temperature overtemperature threshold and delay time according to the rotation speed of an APU (auxiliary Power Unit);
step 1.1.1, when the rotation speed of the APU is in an interval of [0, starter disengaged rotation speed ], setting an exhaust temperature overtemperature threshold as a maximum starting allowable temperature, and setting delay time as the maximum starting allowable time;
step 1.1.2, when the rotation speed of the APU is in an interval of [ a starter is disengaged from a rotation speed point and a steady state rotation speed point ], setting the linear reduction of an exhaust temperature overtemperature threshold from a starting maximum allowable temperature to a steady state switching maximum allowable temperature, and setting the delay time as the starting maximum allowable time;
step 1.2, when the cold end compensation temperature is normal and the flying height of the airplane is less than or equal to 8km or the ground, setting an exhaust temperature overtemperature threshold and delay time according to the flying height;
step 1.2.1, when the flying height is in a high-altitude interval, setting an exhaust temperature overtemperature threshold as a starting minimum allowable temperature, and setting delay time as starting allowable time;
step 1.2.2, when the flying height is not high altitude, the APU exhaust temperature self sets the exhaust temperature overtemperature threshold and the delay time:
step 1.2.2.1, when the exhaust temperature of the APU does not exceed the set temperature, setting an exhaust temperature overtemperature threshold as a starting minimum allowable temperature, and setting delay time as a starting maximum allowable time;
step 1.2.2.2, when the exhaust temperature of the APU exceeds the set temperature, setting the exhaust temperature overtemperature threshold as the minimum starting allowable temperature; the delay time is set as the shortest starting allowed time;
when the APU speed is in the steady state stage:
step 2.1, when the inlet temperature is normal, setting an exhaust temperature overtemperature threshold and delay time according to the exhaust temperature of the APU;
step 2.1.1, when the APU exhaust temperature does not exceed the set temperature, calculating the exhaust temperature overtemperature threshold according to the inlet temperature, wherein the specific formula is as follows:
adjusting the baseline temperature by the exhaust temperature overtemperature threshold value k + the inlet temperature; wherein k is an inlet temperature adjustment coefficient;
the delay time is the maximum allowable time of the steady state;
step 2.1.2, when the exhaust temperature of the APU exceeds the set temperature, setting the exhaust temperature overtemperature threshold as the maximum allowable temperature of the steady state, and setting the delay time as the minimum allowable time of the steady state;
2.2, when the inlet temperature is abnormal, setting an exhaust temperature overtemperature threshold and delay time according to the exhaust temperature of the APU;
step 2.2.1, when the APU exhaust temperature does not exceed the maximum allowable exhaust temperature, setting the exhaust temperature overtemperature threshold as the minimum allowable steady-state temperature, and setting the delay time as the maximum allowable steady-state time;
and 2.2.2, when the exhaust temperature of the APU exceeds the set temperature, setting the exhaust temperature overtemperature threshold as the maximum allowable steady-state temperature, and setting the delay time as the minimum allowable steady-state time.
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| CN102343983A (en) * | 2011-07-07 | 2012-02-08 | 中国国际航空股份有限公司 | Airplane APU (Auxiliary Power Unit) performance detecting method |
| US20140130510A1 (en) * | 2012-11-09 | 2014-05-15 | Honeywell International Inc. | Systems and methods for directing cooling flow into the surge plenum of an exhaust eductor cooling system |
| CN104343476B (en) * | 2013-07-24 | 2016-06-08 | 中国国际航空股份有限公司 | Airplane auxiliary power unit turbine efficiency monitoring method and apparatus |
| CN104345273B (en) * | 2013-07-24 | 2017-11-24 | 中国国际航空股份有限公司 | Airplane auxiliary power unit starter method for testing performance and device |
| GB2518893B (en) * | 2013-10-07 | 2018-11-21 | Ge Aviat Systems Ltd | Method for predicting an auxiliary power unit fault |
| WO2015052458A1 (en) * | 2013-10-07 | 2015-04-16 | Ge Aviation Systems Limited | Method for diagnosing an auxiliary power unit fault |
| CN105569847B (en) * | 2015-12-11 | 2017-10-24 | 中国航空工业集团公司西安航空计算技术研究所 | Auxiliary power unit, which is started, accelerates fuel flow control method |
| CN109681328B (en) * | 2018-12-11 | 2021-02-09 | 中国航空工业集团公司西安航空计算技术研究所 | Control method and device for starting main engine by adjusting air entraining flow of APU (auxiliary Power Unit), and storage medium |
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