CN116295592A - Method and system for judging anti-icing working state of aero-engine - Google Patents
Method and system for judging anti-icing working state of aero-engine Download PDFInfo
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- CN116295592A CN116295592A CN202310536106.2A CN202310536106A CN116295592A CN 116295592 A CN116295592 A CN 116295592A CN 202310536106 A CN202310536106 A CN 202310536106A CN 116295592 A CN116295592 A CN 116295592A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
- G06F17/10—Complex mathematical operations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
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- G—PHYSICS
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- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
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- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K3/00—Thermometers giving results other than momentary value of temperature
- G01K3/08—Thermometers giving results other than momentary value of temperature giving differences of values; giving differentiated values
- G01K3/10—Thermometers giving results other than momentary value of temperature giving differences of values; giving differentiated values in respect of time, e.g. reacting only to a quick change of temperature
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K3/00—Thermometers giving results other than momentary value of temperature
- G01K3/08—Thermometers giving results other than momentary value of temperature giving differences of values; giving differentiated values
- G01K3/14—Thermometers giving results other than momentary value of temperature giving differences of values; giving differentiated values in respect of space
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Abstract
The application provides a method and a system for judging an anti-icing working state of an aero-engine, which belong to the technical field of aero-engines, and the method comprises the following steps: constructing a relation between the inlet temperature of the anti-icing bleed air and the outlet temperature of the air compressor, and obtaining the inlet temperature of the anti-icing bleed air according to the measured value of the outlet temperature of the air compressor and the relation; setting a temperature sensor at an outlet of the anti-icing control device, constructing a first-order inertial link transfer function of the temperature of the anti-icing bleed air inlet and the temperature of the outlet of the anti-icing control device, and calculating to obtain a temperature calculated value at the outlet of the anti-icing bleed air device according to the temperature of the anti-icing bleed air inlet and the first-order inertial transfer function; and judging the anti-icing working state of the aeroengine according to the difference value between the acquired value of the temperature sensor at the outlet of the anti-icing control device and the calculated temperature value. The method can solve the problems of low reliability of the anti-icing working state judgment and high false alarm rate, and reduce the risk caused by misjudgment of anti-icing signals.
Description
Technical Field
The application belongs to the technical field of aeroengines, and particularly relates to a method and a system for judging an anti-icing working state of an aeroengine.
Background
The aeroengine is provided with an intermittent active hot gas anti-icing system, and high-temperature air-entraining of an engine compressor is supplied to an easily-icing part (such as an adjustable blade, a fairing and the like) at an engine inlet through an anti-icing control device and related pipelines so as to ensure safe and reliable operation of the engine in an icing envelope. If the anti-icing control device works abnormally under icing conditions, the anti-icing system cannot be connected, and a pilot cannot be informed of the anti-icing working state in time, ice accumulation can be caused at an engine inlet, the flow of the engine inlet can be reduced due to excessive accumulation of the ice accumulation, the aerodynamic performance is poor, and when serious, the ice accumulation falls into an air inlet channel or a runner to scratch an engine rotor part, so that a flight accident is caused.
At present, the state judgment of an aircraft engine anti-icing system is realized by adopting a small-sized airborne pressure signal combination switch. As shown in fig. 1, the pressure annunciator includes a bellows assembly 10 (including a bellows) and a microswitch 20, the interior chamber of the bellows assembly 10 being in communication with the anti-icing control assembly outlet and the exterior chamber thereof being in an engine compartment pressure environment. When the anti-icing system is closed, the bellows inside the bellows assembly 10 is equivalent to the engine inlet pressure P01, the pressure difference of the bellows is smaller than the engine cabin pressure Ph, the elongation of the bellows is smaller, the right side of the bellows assembly 10 is not contacted with the micro switch 20, and therefore two points A, B in the micro switch 20 are in an open state, and an anti-icing indication signal is not connected. When the anti-icing bleed air is opened, the pressure inside the bellows assembly 10 increases, the pressure difference with the engine compartment pressure Ph is large, the bellows stretches, and the micro switch 20 is closed, and the anti-icing indication signal is on.
However, the above technical solution has the following problems:
1) Because the micro switch 20 is triggered by mechanical contact, the diaphragm capsule assembly 10 frequently knocks the micro switch 20 in the long-term use process, so that the elastic diaphragm 21 in the micro switch is broken and cannot be reset, and the anti-icing on state cannot be normally fed back, so that the fault rate is high;
2) When the anti-icing control device is not connected with the anti-icing bleed air, the inner cavity of the corrugated pipe of the bellows assembly 10 is communicated with the engine inlet, and when the anti-icing control device is in large Mach flight outside the anti-icing wrapping wire, the anti-icing control device is not connected with the anti-icing control device, but at the moment, the inlet pressure P01 of the engine is higher, the pressure difference between the inlet pressure P and the engine cabin pressure Ph is larger, the corrugated pipe is also stretched, so that the micro switch 20 is closed to missignal the connection of an anti-icing indication signal.
Disclosure of Invention
The invention aims to provide a method and a system for judging an anti-icing working state of an aeroengine, which are used for solving or relieving at least one problem in the background art.
The technical scheme of the application is as follows: a method for determining an anti-icing operating condition of an aircraft engine, the method comprising:
constructing a relation between the inlet temperature of the anti-icing bleed air and the outlet temperature of the air compressor, and obtaining the inlet temperature of the anti-icing bleed air according to the measured value of the outlet temperature of the air compressor and the relation;
setting a temperature sensor at an outlet of the anti-icing control device, constructing a first-order inertial link transfer function of the temperature of the anti-icing bleed air inlet and the temperature of the outlet of the anti-icing control device, and calculating to obtain a temperature calculated value at the outlet of the anti-icing bleed air device according to the temperature of the anti-icing bleed air inlet and the first-order inertial transfer function;
and judging the anti-icing working state of the aeroengine according to the difference value between the acquired value of the temperature sensor at the outlet of the anti-icing control device and the calculated temperature value.
Further, the anti-icing bleed air inlet is arranged at the blade tip of a certain stage of the air compressor, wherein the number of blade stages corresponding to the anti-icing bleed air inlet is smaller than the total number of blade stages of the air compressor.
Further, the relation between the inlet temperature of the anti-icing bleed air and the outlet temperature of the air compressor is as follows:
，
in the method, in the process of the invention,
inlet temperature for anti-icing bleed air;
the total temperature of the outlet of the high-pressure compressor is; k1 is a conversion coefficient;
the temperature of the anti-icing air entraining inlet under different engine states is measured by additionally installing test temperature measuring points at the anti-icing inlet in the ground environment
And corresponding compressor outlet temperature
Thereby obtaining a conversion coefficient K1.
Further, the gain and the time constant in the first-order inertial link transfer function are identified according to the on-state or off-state point test data curve of the anti-icing control device, so that the first-order inertial link transfer function is obtained.
Further, when the engine is in the anti-icing envelope, if the difference between the measured value of the temperature sensor at the outlet of the anti-icing control device and the calculated temperature value exceeds a predetermined range and lasts for a plurality of times, the anti-icing control device is judged to be not operated, and if the difference between the measured value of the temperature sensor at the outlet of the anti-icing control device and the calculated temperature value does not exceed the predetermined range and lasts for a plurality of times, the anti-icing control device is judged to be in an operating state;
when the engine is positioned outside the anti-icing package, if the difference value between the measured value of the temperature sensor at the outlet of the anti-icing control device and the calculated temperature value does not exceed a preset range and lasts for a plurality of times, the anti-icing control device is judged to be opened abnormally, and if the difference value between the measured value of the temperature sensor at the outlet of the anti-icing control device and the calculated temperature value exceeds the preset range and lasts for a plurality of times, the anti-icing control device is judged to be in a closed state.
In addition, the application also provides a system for judging the anti-icing working state of the aero-engine, which comprises:
a first temperature sensor at the compressor outlet;
a second temperature sensor at the outlet of the anti-icing control device; and
an engine digital electronic controller which is processed according to the method for determining the anti-icing operating condition of an aeroengine as described in any of the above.
The method for judging the anti-icing working state of the aeroengine by using the airborne temperature sensor provided by the application adopts the non-contact airborne temperature sensor with a simple and reliable structure, and is matched with an airborne judging process, so that the problems of lower working reliability and higher false alarm rate of the anti-icing working state judgment of the pressure signal device are solved, the risk caused by misjudgment of the anti-icing signal is reduced, the pneumatic stability and reliability of the engine are improved, the flight safety is ensured, and the implementation process is simple, easy to improve and wide in adaptability.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
FIG. 1 is a schematic diagram of a prior art pressure type annunciator.
Fig. 2 is a flow chart of the method of the present application.
Fig. 3 is a schematic view of bleed air from the anti-icing control assembly of the present application.
FIG. 4 is a schematic diagram of a first manual anti-icing model identification process according to an embodiment of the present application.
FIG. 5 is a schematic diagram of a second manual anti-icing model identification process according to an embodiment of the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
The temperature sensor has the advantages of simple structure, non-contact, strong environmental adaptability and the like, but because the response characteristic of the temperature sensor is far lower than that of the pressure sensor, the state of an engine in the process of opening the anti-icing and air-entraining can be changed in real time, so that the on state of the anti-icing and air-entraining cannot be accurately judged only by the original acquired data of the temperature sensor in the prior art, and the problems of long judging time, high false alarm rate and the like exist.
In order to realize timely and accurate judgment of the anti-icing state by adopting a relatively reliable temperature sensor, and timely inform a pilot of disengaging from an icing area as soon as possible when an anti-icing control device is abnormally closed, the application provides a judgment method for realizing the anti-icing system state of an aeroengine by using the temperature sensor.
As shown in fig. 2, the method for judging the state of the anti-icing system of the aero-engine by using the temperature sensor provided by the application comprises the following steps:
s1, constructing a relation between the inlet temperature of the anti-icing bleed air and the outlet temperature of the air compressor, and obtaining the inlet temperature of the anti-icing bleed air according to the measured value of the outlet temperature of the air compressor and the relation.
As shown in fig. 3, the aircraft engine anti-icing bleed air mostly adopts bleed air at the tip of a certain stage of stator blade 31 of the compressor 30, and the number of stator blade stages corresponding to the position of the anti-icing bleed air inlet is generally smaller than the total number of the compressor blade in consideration of the temperature and pressure bearing capacity of components (such as fan inlet variable camber blades, fairing and the like) of the engine inlet, which need anti-icing. For example, the compressor blade stage number is 6 stages and bleed air may be located at the 2 nd or 3 rd stage stator blade tips. Because the anti-icing bleed air inlet position is positioned at the middle position of the air compressor, a temperature sensor cannot be arranged, and the temperature sensor is usually arranged at the outlet of the air compressor, the temperature of the anti-icing bleed air inlet position is obtained by establishing the temperature conversion relation between the anti-icing bleed air inlet position and the outlet position of the air compressor, namely:
in the method, in the process of the invention,
inlet temperature for anti-icing bleed air;
k1 is a conversion coefficient.
The relation can be used for measuring the temperature of the anti-icing air entraining inlet under different engine states through the test temperature measuring point at the anti-icing inlet additionally arranged in the ground environment
And corresponding compressor outlet temperature
Thereby obtaining a conversion coefficient K1.
Step S2, setting a temperature sensor at an outlet of the anti-icing control device, constructing a first-order inertial link transfer function of the inlet temperature of the anti-icing bleed air and the outlet temperature of the anti-icing control device, and calculating to obtain a temperature calculated value at the outlet of the anti-icing bleed air device according to the inlet temperature of the anti-icing bleed air and the first-order inertial transfer function.
With continued reference to fig. 3, an onboard temperature sensor is disposed on the anti-icing gas-introducing pipeline at the outlet of the anti-icing control device, and the temperature acquisition value of the onboard temperature sensor at the outlet of the anti-icing control device is recorded in real time
。
According to the heat transfer characteristic of an air medium between an anti-icing air-entraining inlet of a compressor and an outlet of an anti-icing control device and the temperature sensing characteristic of an onboard temperature sensor, a first-order inertial link transfer function G(s) =K/(Ts+1) between the temperature of the anti-icing air-entraining inlet and the temperature of the outlet of the anti-icing control device is constructed, wherein Ts is an anti-icing opening time constant, and K is an anti-icing opening gain.
The gain K and the time constant Ts in the first-order inertial link transfer function can be identified according to the test data curve of the on-state or off-state point of the anti-icing control device, and partial identification results are shown in 4 and fig. 5. The temperature calculated value at the outlet of the anti-icing bleed air device can be further obtained by calculation according to the temperature of the anti-icing bleed air inlet and the first-order inertia transfer function in the first step
。
And S3, judging the anti-icing working state of the aero-engine according to the difference value between the temperature sensor acquisition value and the temperature calculation value of the outlet of the anti-icing control device.
In order to accurately indicate the anti-icing state, an anti-icing indication signal is arranged in the anti-icing control device and used for informing the current anti-icing state of the aircraft cabin, if the anti-icing indication signal is valid, the anti-icing control device is operated, otherwise, the anti-icing control device is not operated; meanwhile, an anti-icing unable-to-close signal and an anti-icing unable-to-turn-on signal are also provided for alarming.
When the aircraft or the engine is in the anti-icing covered wire and the anti-icing control device is opened, firstly, the anti-icing cannot be closed, the signal is not alarmed, and meanwhile, the anti-icing indication signal is effective; if the temperature sensor at the outlet of the anti-icing control device collects values
Calculated value of temperature
If the difference value of the anti-icing control signal exceeds the preset range and lasts for a period of time or a calculation period, judging that the anti-icing control device works abnormally, and judging that the anti-icing indication signal is invalid while the anti-icing cannot be connected with the signal for alarming; if the temperature sensor at the outlet of the anti-icing control device collects values
Calculated value of temperature
If the difference value of the signal is within the preset range and lasts for a period of time or a calculation period, the anti-icing control device is judged to work normally, the alarm that the anti-icing cannot be conducted is stopped, and meanwhile the anti-icing indication signal is judged to be valid.
When the aircraft or the engine is positioned outside the anti-icing package wire and the anti-icing control device is closed, firstly, an anti-icing unable-on signal does not give an alarm, and meanwhile, an anti-icing indication signal is invalid; if the temperature sensor at the outlet of the anti-icing control device collects values
Calculated value of temperature
If the difference value of the two is within the preset range and lasts for a period of time or a calculation period, judging that the anti-icing control device is abnormally opened, and carrying out anti-icing and incapable of closing alarm; if the temperature sensor at the outlet of the anti-icing control device collects values
And temperature acquisition value
If the difference value of the two signals is out of the preset range and lasts for a period of time or a calculation period, the anti-icing control device is judged to be normally closed, and the anti-icing is stopped and the signal alarm is not closed.
The method for judging the anti-icing working state of the aeroengine by using the airborne temperature sensor provided by the application adopts the non-contact airborne temperature sensor with a simple and reliable structure, and is matched with an airborne judging process, so that the problems of lower working reliability and higher false alarm rate of the anti-icing working state judgment of the pressure signal device are solved, the risk caused by misjudgment of the anti-icing signal is reduced, the pneumatic stability and reliability of the engine are improved, the flight safety is ensured, and the implementation process is simple, easy to improve and wide in adaptability.
In addition, the application also provides a system for judging the anti-icing working state of the aeroengine by adopting the temperature sensor, the system comprises a first temperature sensor arranged at the outlet of the air compressor, a second temperature sensor arranged at the outlet side of the anti-icing control device and an engine digital electronic controller, wherein the engine digital electronic controller is connected with the two temperature sensors, when the anti-icing air entraining of the engine is switched on or off, the outlet temperature of the anti-icing control device can change, the temperature value number of the temperature sensor is acquired in real time based on the engine digital electronic controller, and the temperature value is compared with the calculated value of the temperature airborne model of the anti-icing control device in the engine digital electronic controller in real time so as to realize accurate judgment of the anti-icing state.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A method for determining an anti-icing operating condition of an aircraft engine, the method comprising:
constructing a relation between the inlet temperature of the anti-icing bleed air and the outlet temperature of the air compressor, and obtaining the inlet temperature of the anti-icing bleed air according to the measured value of the outlet temperature of the air compressor and the relation;
setting a temperature sensor at an outlet of the anti-icing control device, constructing a first-order inertial link transfer function of the temperature of the anti-icing bleed air inlet and the temperature of the outlet of the anti-icing control device, and calculating to obtain a temperature calculated value at the outlet of the anti-icing bleed air device according to the temperature of the anti-icing bleed air inlet and the first-order inertial transfer function;
and judging the anti-icing working state of the aeroengine according to the difference value between the acquired value of the temperature sensor at the outlet of the anti-icing control device and the calculated temperature value.
2. The method for determining an ice protection operating condition of an aircraft engine of claim 1, wherein the ice protection bleed air inlet is disposed at a blade tip of a stage of the compressor, and wherein the number of blade stages corresponding to the ice protection bleed air inlet is less than the total number of blade stages of the compressor.
3. The method for determining an anti-icing operating condition of an aircraft engine according to claim 1 or 2, wherein the relation between the anti-icing bleed air inlet temperature and the compressor outlet temperature is:
in the method, in the process of the invention,
inlet temperature for anti-icing bleed air;
the total temperature of the outlet of the high-pressure compressor is; k1 is a conversion coefficient;
the temperature of the anti-icing air entraining inlet under different engine states is measured by additionally installing test temperature measuring points at the anti-icing inlet in the ground environment
And corresponding compressor outlet temperature
Thereby obtaining a conversion coefficient K1.
4. A method for determining an anti-icing operating condition of an aircraft engine as claimed in claim 3 wherein the first order inertial member transfer function is obtained by identifying the gain and time constant in the first order inertial member transfer function from an on or off state point test data curve of the anti-icing control means.
5. The method for determining an anti-icing operating condition of an aircraft engine according to claim 4, wherein when the engine is within an anti-icing envelope, if the difference between the temperature sensor measurement at the outlet of the anti-icing control and the calculated temperature value exceeds a predetermined range for a number of times, it is determined that the anti-icing control is not operating, and if the difference between the temperature sensor measurement at the outlet of the anti-icing control and the calculated temperature value does not exceed the predetermined range for a number of times, it is determined that the anti-icing control is in operation;
when the engine is positioned outside the anti-icing package, if the difference value between the measured value of the temperature sensor at the outlet of the anti-icing control device and the calculated temperature value does not exceed a preset range and lasts for a plurality of times, the anti-icing control device is judged to be opened abnormally, and if the difference value between the measured value of the temperature sensor at the outlet of the anti-icing control device and the calculated temperature value exceeds the preset range and lasts for a plurality of times, the anti-icing control device is judged to be in a closed state.
6. A system for determining an anti-icing operating condition of an aircraft engine, the system comprising:
a first temperature sensor at the compressor outlet;
a second temperature sensor at the outlet of the anti-icing control device; and
engine digital electronic controller, which is processed according to the method for determining an anti-icing operating condition of an aeroengine according to any of claims 1 to 5.
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| CN116295592B (en) | 2023-08-22 |
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