Turbofan engine signal reconstruction method and system

Abstract

The invention relates to the technical field of aero-engines, in particular to a turbofan engine signal reconstruction method and system. The invention provides a method for reconstructing signals of a turbofan engine. The method comprises the following steps that a plurality of key signals of the engine are collected and monitored in real time through a plurality of collection channels of different signal sources; when a difference value between the key signals of different signal sources or different acquisition channels is greater than a tolerance threshold value, voting and / or reconstructing the key signals; wherein the key signals comprise key signals, related to thrust control, of the engine and key signals, related to fuel oil control, of the engine. According to the turbofan engine signal reconstruction method and system and the turbofan engine, the key signals are classified according to the reliability of the channel signals, the failure signals are voted and reconstructed, the reliability and safety of an aero-engine can be effectively improved, and a more reliable guarantee is provided for safe flight of an aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and more particularly to a method and system for reconstructing turbofan engine signals. Background Art

[0002] For aviation turbofan engines, engine signal failure may occur during engine operation. If protection measures are not taken in time after the engine signal failure is detected, the fault signal cannot be correctly located and it may become or dominate the output signal of the signal selection logic, and eventually enter the control loop and affect the performance and safety of the engine. This may cause the engine to stall, performance degradation or loss of control, thus having a serious impact on flight safety.

[0003] During flight, signal failures often occur due to the small number of onboard sensor measurement points. At this time, signal reconstruction processing measures are particularly important. If the signal failure cannot be processed and thrust recovery and fuel selection are correct, it will have a certain impact on flight safety.

[0004] Signal reconstruction methods and systems can represent the development direction of engine airborne control technology and can significantly improve flight safety. Signal reconstruction means that when all signals fail, the control logic can rely on the reconstructed signal method to replace the failed signal to achieve control functions and ensure the safe operation of the engine.

[0005] On the engine test bench, various sensors or monitoring devices can be used to detect signal failures and handle them in a timely manner. However, during the actual flight of the aircraft, due to the limited number of onboard sensors, signal failure reconstruction can only rely on the limited speed, temperature or pressure signals carried by the engine itself.

[0006] Therefore, in order to ensure the safety of engine operation, the processing method needs to ensure both thrust and engine performance. However, in the prior art, there is no suitable method for engine signal reconstruction to achieve thrust recovery and fuel selection correctness under signal failure. Therefore, it is necessary to further research and develop new signal reconstruction methods and technologies to improve flight safety and represent the direction of engine onboard control technology development. Summary of the invention

[0007] The purpose of the present invention is to provide a method for reconstructing turbofan engine signals to solve the safety problem caused by the difficulty in timely processing of engine signal failures during actual flight of an aircraft in the prior art.

[0008] In order to achieve the above object, the present invention provides a method for reconstructing a turbofan engine signal, comprising the following steps:

[0009] Collect and monitor several key engine signals in real time through multiple acquisition channels of different signal sources;

[0010] When the difference between key signals from different signal sources or different acquisition channels is greater than a tolerance threshold, the key signal is considered to be invalid, and voting and / or reconstruction is performed on the key signal;

[0011] Among them, the key signals include key signals related to engine and thrust control and key signals related to engine and fuel control.

[0012] In one embodiment, the key signals of the engine related to thrust control include:

[0013] Atmospheric static pressure P0, ambient total temperature T0, Mach number Ma, high-pressure shaft speed N2, low-pressure shaft speed N1, fan inlet total temperature T12, high-pressure compressor inlet total temperature T25 and fan inlet static pressure PS12.

[0014] In one embodiment, the atmospheric static pressure P0 is determined by voting the aircraft atmospheric static pressure signal P0_AC and the engine atmospheric static pressure signal P0_Eng;

[0015] The total ambient temperature T0 is determined by voting the aircraft ambient total temperature signal T0_AC and the fan inlet total temperature T12;

[0016] The Mach number Ma is determined by voting between the aircraft Mach number Ma_AC and the engine Mach number Ma_Eng.

[0017] In one embodiment, the high-pressure shaft speed N2 and the low-pressure shaft speed N1 serve as backup for each other and are reconstructed by converting the speed relationship.

[0018] In one embodiment, the high-pressure shaft speed N2 is calculated by the high-pressure conversion speed N2R. The relationship between the high-pressure shaft speed N2 and the high-pressure conversion speed N2R is N2=N2R*

[0019] (T25 / 288.15)^0.5;

[0020] The engine high-pressure shaft speed N2 and the low-pressure shaft speed N1 can be reconstructed through the conversion speed relationship, and the high-pressure conversion speed N2R calculation function N2R=f(N1R).

[0021] In one embodiment, the low-pressure shaft speed N1 is calculated by the low-pressure conversion speed N1R. The relationship between the low-pressure shaft speed N1 and the low-pressure conversion speed N1R is N1=N1R*

[0022] (T12 / 288.15)^0.5;

[0023] The engine low-pressure shaft speed N1 and the high-pressure shaft speed N2 can be reconstructed through the conversion speed relationship, and the low-pressure conversion speed N1R calculation function N1R=f(N2R).

[0024] In one embodiment, the fan inlet total temperature T12 is reconstructed by the ambient total temperature T0;

[0025] The high-pressure compressor inlet total temperature T25 is reconstructed by the low-pressure converted speed N1R and the fan inlet total temperature T12;

[0026] The fan inlet static pressure PS12 is reconstructed by the atmospheric static pressure P0.

[0027] In one embodiment, the key signals related to the engine and fuel control include:

[0028] High pressure compressor outlet static pressure PS3, high pressure compressor inlet total pressure P25, high pressure compressor inlet total temperature T25 and high pressure compressor outlet total temperature T3.

[0029] In one embodiment, the engine and fuel control related parameters include:

[0030] The fuel distribution ratio M, the corresponding calculation function is: M = f (WF, PS3, T3);

[0031] Convert the fuel flow rate WFR, and the corresponding calculation function is:

[0032] WFR=WF / (PS3 / 101.325)^beta / (T25 / 288.15)^alpha;

[0033] The corresponding calculation function for the converted acceleration rate N2dotR is:

[0034] N2dotR=N2dot / (P25 / 101.325);

[0035] Wherein, WF is the fuel flow rate, beta and alpha are conversion indices, and N2dot is the change rate of the high-pressure shaft speed N2.

[0036] In one embodiment, the high-pressure compressor outlet static pressure PS3 is reconstructed by the high-pressure compressor inlet total pressure P25 and the high-pressure converted speed N2R, or by the high-pressure compressor inlet total pressure P25 and the high-pressure compressor outlet total temperature T3 / the high-pressure compressor inlet total temperature T25;

[0037] The high-pressure compressor inlet total pressure P25 is reconstructed by the atmospheric static pressure P0 and the low-pressure conversion speed N1R, or by the atmospheric static pressure P0 and the high-pressure compressor inlet total temperature T25 / the fan inlet total temperature T12;

[0038] The high-pressure compressor inlet total temperature T25 is reconstructed through the fan inlet total temperature T12 and the low-pressure conversion speed N1R;

[0039] The high-pressure compressor outlet total temperature T3 is reconstructed through the high-pressure compressor inlet static pressure T25 and the high-pressure converted speed N2R.

[0040] In one embodiment, the voting on the key signal corresponds to a signal voting method, further comprising:

[0041] Determine whether the signal parameters of the signal source participating in the voting are valid;

[0042] For valid signal parameters, the corresponding weight coefficients are assigned, and for invalid signal parameters, the weight coefficient is assigned to be 0, and the sum of all weight coefficients is 1;

[0043] All signal parameters are multiplied by the corresponding weight coefficients and then summed to obtain the voted signal parameters.

[0044] In one embodiment, when all signal parameters are invalid, the signal parameters voted for adopt a default value, which is a preset constant value.

[0045] In order to achieve the above object, the present invention provides a turbofan engine signal reconstruction system, comprising:

[0046] a memory for storing instructions executable by a processor;

[0047] A processor is used to execute the instructions to implement a method for reconstructing a turbofan engine signal as described in any one of the above items.

[0048] In order to achieve the above-mentioned objectives, the present invention provides a turbofan engine, which adopts the method for reconstructing turbofan engine signals as described in any one of the above-mentioned items.

[0049] The present invention provides a turbofan engine signal reconstruction method, reconstruction system and turbofan engine, which classify key signals according to the reliability of channel signals, vote on and reconstruct failed signals, and can effectively improve the reliability and safety of aircraft engines and provide more reliable protection for the safe flight of aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always represent the same features.

[0051] in:

[0052] Figure 1Reveals the flowchart of the reconstruction method for turbofan engine signals according to an embodiment of the present invention;

[0053] Figure 2 Reveals the flowchart of the voting and reconstruction of engine signals according to an embodiment of the present invention. Detailed implementation manners

[0054] In order to make the objectives, technical solutions and advantages of the present invention more clear and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the invention and are not used to limit the invention.

[0055] A method for reconstructing turbofan engine signals proposed by the present invention, when the aero-engine signals fail, classifies key signals according to the reliability of channel signals, and uses the signal with the lowest signal failure probability as the starting point of the signal chain, while ensuring that the failure probabilities of all channels of this signal meet the requirements, so as to ensure that the signal chain can still be reconstructed in the case of multiple signal failures, and the signal reconstruction method has high reliability.

[0056] Figure 1 Reveals the flowchart of the reconstruction method for turbofan engine signals according to an embodiment of the present invention,

[0057] Figure 2 Reveals the flowchart of the voting and reconstruction of engine signals according to an embodiment of the present invention, as Figure 1 and Figure 2 shown, a method for reconstructing turbofan engine signals proposed by the present invention includes the following steps:

[0058] Step S1: Real-time collect and monitor several key signals of the engine through multiple acquisition channels of different signal sources;

[0059] Step S2: When the difference between the key signals of different signal sources or different acquisition channels is greater than the tolerance threshold, it is considered that the key signal fails, and vote and / or reconstruct the key signal;

[0060] Among them, the key signals include key signals related to engine and thrust control, and key signals related to engine and fuel control.

[0061] A method for reconstructing turbofan engine signals proposed by the present invention, when there are differences greater than the tolerance threshold in signals from different signal sources and different channels, it is necessary to vote and reconstruct the signal, and the reconstruction criterion is to determine the signal source that meets the safety requirements, so as to ensure that after the signal with the safety failure probability not meeting the requirements fails, it can be reconstructed with reliable signals.

[0062] As Figure 2The signal voting and reconstruction flow chart shown, wherein the starting point of the arrow is the signal source, the end point of the arrow voting is the signal voting result, the end point of the arrow function is the signal reconstruction result, and the calculation relationship is directly connected to the signal source through the arrow.

[0063] In this embodiment, the key signals related to engine thrust control include:

[0064] Atmospheric static pressure P0, ambient total temperature T0, Mach number Ma, high-pressure shaft speed N2, low-pressure shaft speed N1, fan inlet total temperature T12, high-pressure compressor inlet total temperature T25, fan inlet static pressure PS12.

[0065] Among them, the key signals for voting are as follows:

[0066] Atmospheric static pressure P0 is determined by voting between the aircraft atmospheric static pressure signal P0_AC and the engine atmospheric static pressure signal P0_Eng;

[0067] The total ambient temperature T0 is determined by voting between the aircraft ambient total temperature signal T0_AC and the fan inlet total temperature T12;

[0068] The Mach number Ma is determined by voting between the aircraft Mach number Ma_AC and the engine Mach number Ma_Eng.

[0069] Among them, the calculation function of the engine Mach number is Ma_Eng=f(Ps12,P0,N1R).

[0070] Among them, the key signals and reconstruction methods for reconstruction are as follows:

[0071] The total temperature of the fan inlet, T12, is reconstructed by the total temperature of the environment, T0, T12 = T0;

[0072] The total temperature at the high-pressure compressor inlet, T25, is reconstructed by the low-pressure conversion speed N1R and the total temperature at the fan inlet, T25 = f(N1R)*T12;

[0073] The fan inlet static pressure PS12 is reconstructed by the atmospheric static pressure P0, PS12 = P0.

[0074] The low-pressure shaft is the transmission shaft that connects the low-pressure turbine and the low-pressure compressor inside a twin-shaft turbofan engine. One end of the low-pressure shaft is connected to the low-pressure turbine, and the other end is connected to the low-pressure compressor, that is, the fan and the supercharger stage. The power and torque generated by the low-pressure turbine are transmitted to the fan and supercharger stage components through the low-pressure shaft.

[0075] The high-pressure shaft is the transmission shaft that connects the high-pressure turbine and the high-pressure compressor in a twin-shaft turbofan engine. One end of the high-pressure shaft is connected to the high-pressure turbine, and the other end is connected to the high-pressure compressor. The work and torque generated by the high-pressure turbine are transmitted to the high-pressure compressor components through the high-pressure shaft.

[0076] According to the thrust level and related signals, the thrust management low-pressure conversion speed above idle is calculated as N1R=f(P0,T0,Ma).

[0077] According to the thrust level and related signals, the high-pressure conversion speed of the slow-speed thrust management is calculated as N2R=f(P0,T0,Ma).

[0078] The engine low-pressure shaft speed N1 is calculated by the low-pressure conversion speed N1R. The relationship between the low-pressure shaft speed N1 and the low-pressure conversion speed N1R is N1=N1R*(T12 / 288.15)^0.5. The relationship between the low-pressure conversion speed N1R and the engine low-pressure shaft speed N1 is:

[0079] N1R=N1 / (T12 / 288.15)^0.5.

[0080] The engine high-pressure shaft speed N2 is calculated through the high-pressure converted speed N2R. The relationship between the high-pressure shaft speed N2 and the high-pressure converted speed N2R is N2=N2R*(T25 / 288.15)^0.5. The relationship between the high-pressure converted speed N2R and the high-pressure shaft speed N2 is: N2R=N2 / (T25 / 288.15)^0.5.

[0081] The high-pressure shaft speed N2 and the low-pressure shaft speed can back up each other. Each signal source has multiple channel signals, and its failure probability should meet the safety requirements as the source of the signal chain.

[0082] The engine low-pressure shaft speed N1 and the high-pressure shaft speed N2 can be reconstructed through the conversion speed relationship, and the low-pressure conversion speed N1R calculation function N1R=f(N2R).

[0083] The engine high-pressure shaft speed N2 and the low-pressure shaft speed N1 can be reconstructed through the conversion speed relationship, and the high-pressure conversion speed N2R calculation function N2R=f(N1R).

[0084] In addition to thrust control, fuel control plays an important role in steady-state and unsteady-state control. In steady-state and unsteady-state control, in order to prevent turbine overheating, fuel distribution needs to be adjusted, involving parameters such as the fuel distribution ratio M. In unsteady-state control, it is necessary to ensure the accuracy of fuel selection, which involves the conversion of fuel flow WFR and the conversion of acceleration rate N2dotR and other rules corresponding to fuel parameters.

[0085] The fuel distribution ratio M, the corresponding calculation function is: M = f (WF, PS3, T3);

[0086] Wherein, WF is the fuel flow rate, which is obtained by interpolating the target fuel and the calibration table and is a non-measured value; PS3 is the high-pressure compressor outlet static pressure, and T3 is the high-pressure compressor outlet total temperature.

[0087] Convert the fuel flow rate WFR, and the corresponding calculation function is:

[0088] WFR=WF / (PS3 / 101.325)^beta / (T25 / 288.15)^alpha;

[0089] Among them, beta and alpha are conversion indices, WF is the fuel flow rate, PS3 is the high pressure compressor outlet static pressure, and T25 is the high pressure compressor inlet total temperature;

[0090] The conversion acceleration rate N2dotR, the corresponding calculation function is: N2dotR = N2dot / (P25 / 101.325);

[0091] Among them, P25 is the total pressure at the high-pressure compressor inlet, and N2dot is the change rate of the high-pressure shaft speed N2.

[0092] In this embodiment, the key signals related to engine and fuel control include:

[0093] High-pressure compressor outlet static pressure PS3, high-pressure compressor inlet total pressure P25, high-pressure compressor inlet total temperature T25, high-pressure compressor outlet total temperature T3.

[0094] Among them, the high-pressure compressor inlet total pressure P25 can be replaced by the high-pressure compressor inlet static pressure PS25 or PS25 sensor.

[0095] Among them, the key signals and reconstruction methods for reconstruction are as follows:

[0096] The high-pressure compressor outlet static pressure PS3 is reconstructed by the high-pressure compressor inlet total pressure P25 and the high-pressure converted speed N2R, or by the high-pressure compressor inlet total pressure P25 and the high-pressure compressor outlet total temperature T3 / the high-pressure compressor inlet total temperature T25, PS3 = f(N2R)*P25 (or PS3 = f(T3 / T25)*P25). The reconstruction method is not limited to the thermodynamic method, and the parameter model correction method can also be used as an alternative.

[0097] It should be noted that the high-pressure compressor outlet total temperature T3 / high-pressure compressor inlet total temperature T25 refers to the ratio of the high-pressure compressor outlet total temperature T3 to the high-pressure compressor inlet total temperature T25, and has the same meaning in the formulas appearing in the text.

[0098] The total pressure P25 at the high pressure compressor inlet is reconstructed by the atmospheric static pressure P0 and the low pressure conversion speed N1R, or by the atmospheric static pressure P0 and the high pressure compressor inlet total temperature T25 / the fan inlet total temperature T12, P25=f(N1R)*P0 (or P25=f(T25 / T12)*P0). The reconstruction method is not limited to the thermodynamic method, and the parameter model correction method can also be used as an alternative.

[0099] The total temperature T3 at the high pressure compressor outlet is reconstructed by the static pressure T25 at the high pressure compressor inlet and the high pressure conversion speed N2R, T3 = f(N2R)*T25. The reconstruction method is not limited to the thermodynamic method, and the parameter model correction method can also be used as an alternative.

[0100] The total temperature T25 at the high-pressure compressor inlet is reconstructed by the total temperature T12 at the fan inlet and the low-pressure converted speed N1R, T25=f(N1R)*T12. The reconstruction method is not limited to the thermodynamic method, and the parameter model correction method can also be used as an alternative.

[0101] The method for reconstructing turbofan engine signals proposed by the present invention votes on the key signals, and the corresponding signal voting method further includes:

[0102] Determine whether the signal parameters of the signal source participating in the voting are valid;

[0103] The signal parameters are assigned corresponding weight systems, wherein valid signal parameters are assigned corresponding weight coefficients, and invalid signal parameters are assigned weight coefficients of 0, and the sum of all weight coefficients is 1;

[0104] All signal parameters are multiplied by the corresponding weight coefficients and then summed to obtain the voted signal parameters.

[0105] Furthermore, when all signal parameters are invalid, the signal parameters voted for adopt a default value, which is a preset constant value.

[0106] As shown in the signal voting logic in Table 1, the signal parameter of the X signal source participating in the voting is recorded as Xsel, the signal parameter of the Y signal source participating in the voting is recorded as Ysel, and the signal parameter voted out is recorded as ZSEL.

[0107] The X signal source signal and the Y signal source signal can be aircraft or engine signals, T is valid and F is invalid.

[0108] Table 1

[0109] Serial number XSEL YSEL ZSEL 1 T T XSEL+A*(YSEL-XSEL) 2 T F XSEL 3 F T YSEL 4 F F F

[0110] In case 1, the XSEL signal is valid, the YSEL signal is valid, the weight coefficient of the X source signal XSEL is (1-A), the weight coefficient of the Y source signal YSEL is A, and the signal parameter ZSEL=XSEL+A*(YSEL-XSEL).

[0111] In case 2, the XSEL signal is valid, the YSEL signal is invalid, the weight coefficient of the X source signal XSEL is 1, the weight coefficient of the Y source signal YSEL is 0, and the signal parameter ZSEL=XSEL is voted.

[0112] In case of sequence number 3, the XSEL signal is invalid, the YSEL signal is valid, the weight coefficient of the X source signal XSEL is 0, the weight coefficient of the Y source signal YSEL is 1, and the signal parameter ZSEL=YSEL is voted.

[0113] In case of sequence number 4, the XSEL signal fails, the YSEL signal fails, and the signal parameter ZSEL voted adopts the default value, which is a preset constant value.

[0114] The signal voting method is not limited to the relationship in Table 1 above. When there are multiple signals in the signal source X and the signal source Y, a weighted relationship can still be used for processing.

[0115] The present invention also provides a turbofan engine signal reconstruction system, which comprises at least a memory and a processor, wherein the memory stores computer instructions that can be run on the processor, and when the processor runs the computer instructions, the steps of any of the above-mentioned turbofan engine signal reconstruction methods are executed.

[0116] When the implementation process file of the reconstruction method of the turbofan engine signal is a computer program, it can also be stored in a computer-readable storage medium as a product. For example, a computer-readable storage medium may include, but is not limited to, a magnetic storage device (e.g., a hard disk, a floppy disk, a magnetic strip), an optical disk (e.g., a compact disk (CD), a digital versatile disk (DVD)), a smart card, and a flash memory device (e.g., an electrically erasable programmable read-only memory (EPROM), a card, a stick, a key drive). In addition, the various storage media described herein can represent one or more devices and / or other machine-readable media for storing information. The term "machine-readable medium" may include, but is not limited to, wireless channels and various other media (and / or storage media) that can store, contain and / or carry code and / or instructions and / or data.

[0117] The present invention also provides a computer-readable storage medium, which is a non-volatile storage medium or a non-transient storage medium, on which computer instructions are stored. When the computer instructions are executed, the steps corresponding to any of the above methods are executed, which will not be repeated here.

[0118] The present invention also provides a turbofan engine using the above signal reconstruction method. The turbofan engine uses the above signal reconstruction method to optimize its performance, improve its reliability and extend its service life.

[0119] The present invention provides a turbofan engine signal reconstruction method, a reconstruction system and a turbofan engine, which have the following beneficial effects:

[0120] 1) By introducing the signal reconstruction processing method, the thrust recovery and fuel selection in the event of signal failure are correct, thus significantly improving the engine's operating safety and flight safety;

[0121] 2) It can be applied in the whole-machine bench test of aircraft engines, which can reduce the harm caused by engine signal failure to the engine and provide a new solution for the research and development and testing of aircraft engines;

[0122] 3) It is not only applicable to other types of aviation turbine engines, but can also be applied to the signal reconstruction of ground gas turbines and marine gas turbines, which is beneficial to improving the operating safety of gas turbines.

[0123] As shown in this application and claims, unless the context clearly indicates an exception, the words "a", "an", "an" and / or "the" do not refer to the singular and may also include the plural. Generally speaking, the terms "include" and "comprise" only indicate the inclusion of the steps and elements that have been clearly identified, and these steps and elements do not constitute an exclusive list. The method or device may also include other steps or elements.

[0124] Those skilled in the art will appreciate that information, signals, and data may be represented using any of a variety of different technologies and techniques. For example, data, instructions, commands, information, signals, bits, symbols, and chips cited throughout the above description may be represented by voltage, current, electromagnetic waves, magnetic fields or magnetic particles, optical fields or optical particles, or any combination thereof.

[0125] Those skilled in the art will further appreciate that the various illustrative logic blocks, modules, circuits, and algorithm steps described in conjunction with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or a combination of the two. To clearly illustrate this interchangeability of hardware and software, various illustrative components, blocks, modules, circuits, and steps are generally described above in terms of their functionality. Whether such functionality is implemented as hardware or software depends on the specific application and the design constraints imposed on the overall system. The technician may implement the described functionality in different ways for each specific application, but such implementation decisions should not be interpreted as resulting in a departure from the scope of the present invention.

[0126] The various illustrative logic modules and circuits described in conjunction with the embodiments disclosed herein may be implemented or executed with a general purpose processor, a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components, or any combination thereof designed to perform the functions described herein. A general purpose processor may be a microprocessor, but in the alternative, the processor may be any conventional processor, controller, microcontroller, or state machine. The processor may also be implemented as a combination of computing devices, such as a combination of a DSP and a microprocessor, a plurality of microprocessors, one or more microprocessors in cooperation with a DSP core, or any other such configuration.

[0127] The steps of the method or algorithm described in conjunction with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. The software module may reside in a RAM memory, a flash memory, a ROM memory, an EPROM memory, an EEPROM memory, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor so that the processor can read and write information from / to the storage medium. In an alternative, a storage medium may be integrated into a processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and the storage medium may reside in a user terminal as discrete components.

[0128] In one or more exemplary embodiments, the functions described may be implemented in hardware, software, firmware, or any combination thereof. If implemented as a computer program product in software, each function may be stored on or transmitted by a computer-readable medium as one or more instructions or codes. Computer-readable media include both computer storage media and communication media, including any medium that facilitates the transfer of a computer program from one place to another. Storage media may be any available medium that can be accessed by a computer. As an example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disk storage, disk storage or other magnetic storage device, or any other medium that can be used to carry or store the desired program code in the form of an instruction or data structure and can be accessed by a computer. Any connection is also properly referred to as a computer-readable medium. For example, if the software is transmitted from a website, a server, or other remote source using a coaxial cable, a fiber optic cable, a twisted pair, a digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwaves, the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwaves are included in the definition of the medium. As used herein, disk and disc include compressed discs.

[0129] Computer-readable media may include CDs, laser discs, optical discs, digital versatile discs (DVDs), floppy disks, and Blu-ray discs, where disks typically reproduce data magnetically, while discs reproduce data optically with lasers. Combinations of the above should also be included within the scope of computer-readable media.

[0130] The above embodiments are provided for persons familiar with the art to implement or use the present invention. Persons familiar with the art can make various modifications or changes to the above embodiments without departing from the inventive concept of the present invention. Therefore, the protection scope of the present invention is not limited to the above embodiments, but should be the maximum scope of the innovative features mentioned in the claims.

Claims

1. A method for reconstructing turbofan engine signals, It is characterized in that The following steps are involved: Collect and monitor several key engine signals in real time through multiple acquisition channels of different signal sources; When the difference between key signals from different signal sources or different acquisition channels is greater than a tolerance threshold, the key signal is considered to be invalid, and voting and / or reconstruction is performed on the key signal; Among them, the key signals include key signals related to engine and thrust control and key signals related to engine and fuel control.

2. The method for reconstructing a turbofan engine signal according to claim 1, It is characterized in that The key signals related to engine thrust control include: Atmospheric static pressure P0, ambient total temperature T0, Mach number Ma, high-pressure shaft speed N2, low-pressure shaft speed N1, fan inlet total temperature T12, high-pressure compressor inlet total temperature T25 and fan inlet static pressure PS12.

3. The method for reconstructing a turbofan engine signal according to claim 2, It is characterized in that The atmospheric static pressure P0 is determined by voting the aircraft atmospheric static pressure signal P0_AC and the engine atmospheric static pressure signal P0_Eng; The total ambient temperature T0 is determined by voting the aircraft ambient total temperature signal T0_AC and the fan inlet total temperature T12; The Mach number Ma is determined by voting between the aircraft Mach number Ma_AC and the engine Mach number Ma_Eng.

4. The method for reconstructing a turbofan engine signal according to claim 2, It is characterized in that The high-pressure shaft speed N2 and the low-pressure shaft speed N1 serve as backup for each other and are reconstructed by converting the speed relationship.

5. The method for reconstructing a turbofan engine signal according to claim 2, It is characterized in that The fan inlet total temperature T12 is reconstructed by the ambient total temperature T0; The high-pressure compressor inlet total temperature T25 is reconstructed by the low-pressure converted speed N1R and the fan inlet total temperature T12; The fan inlet static pressure PS12 is reconstructed by the atmospheric static pressure P0.

6. The method for reconstructing a turbofan engine signal according to claim 1, It is characterized in that The key signals related to the engine and fuel control include: High pressure compressor outlet static pressure PS3, high pressure compressor inlet total pressure P25, high pressure compressor inlet total temperature T25 and high pressure compressor outlet total temperature T3.

7. The method for reconstructing a turbofan engine signal according to claim 6, It is characterized in that The engine and fuel control related parameters include: The fuel distribution ratio M, the corresponding calculation function is: M = f (WF, PS3, T3); Convert the fuel flow rate WFR, and the corresponding calculation function is: WFR=WF / (PS3 / 101.325)^beta / (T25 / 288.15)^alpha; The corresponding calculation function for the converted acceleration rate N2dotR is: N2dotR=N2dot / (P25 / 101.325); Wherein, WF is the fuel flow rate, beta and alpha are conversion indices, and N2dot is the change rate of the high-pressure shaft speed N2.

8. The method for reconstructing a turbofan engine signal according to claim 6, It is characterized in that The high-pressure compressor outlet static pressure PS3 is reconstructed by the high-pressure compressor inlet total pressure P25 and the high-pressure converted speed N2R, or by the high-pressure compressor inlet total pressure P25 and the high-pressure compressor outlet total temperature T3 / the high-pressure compressor inlet total temperature T25; The high-pressure compressor inlet total pressure P25 is reconstructed by the atmospheric static pressure P0 and the low-pressure conversion speed N1R, or by the atmospheric static pressure P0 and the high-pressure compressor inlet total temperature T25 / the fan inlet total temperature T12; The high-pressure compressor inlet total temperature T25 is reconstructed by the fan inlet total temperature T12 and the low-pressure converted speed N1R; The high-pressure compressor outlet total temperature T3 is reconstructed by the high-pressure compressor inlet static pressure T25 and the high-pressure converted speed N2R.

9. The method for reconstructing a turbofan engine signal according to claim 1, It is characterized in that The voting on the key signal corresponds to a signal voting method, further comprising: Determine whether the signal parameters of the signal source participating in the voting are valid; For valid signal parameters, the corresponding weight coefficients are assigned, and for invalid signal parameters, the weight coefficient is assigned to be 0, and the sum of all weight coefficients is 1; All signal parameters are multiplied by the corresponding weight coefficients and then summed to obtain the voted signal parameters.

10. The method for reconstructing a turbofan engine signal according to claim 9, It is characterized in that In the case that all signal parameters are invalid, the signal parameters voted for adopt default values, which are preset constant values.

11. A turbofan engine signal reconstruction system, It is characterized in that include: a memory for storing instructions executable by a processor; A processor, configured to execute the instructions to implement the method for reconstructing a turbofan engine signal as described in any one of claims 1-10.

12. A turbofan engine, It is characterized in that A method for reconstructing a turbofan engine signal as described in any one of claims 1 to 10 is adopted.

Images