(19)
(11)EP 2 388 672 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
18.03.2020 Bulletin 2020/12

(21)Application number: 11166633.5

(22)Date of filing:  18.05.2011
(51)Int. Cl.: 
G05B 23/02  (2006.01)
G05B 9/02  (2006.01)

(54)

Identifying of turbomachine faults

Identifikation von Turbomaschinen-Fehlern

Identification des défauts de turbomachine


(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

(30)Priority: 18.05.2010 US 782685

(43)Date of publication of application:
23.11.2011 Bulletin 2011/47

(73)Proprietor: United Technologies Corporation
Farmington, CT 06032 (US)

(72)Inventors:
  • Yeramalla, Sampath K.
    Manchester, CT 06040 (US)
  • Donat, William
    Manchester, CT 06040 (US)
  • Rajamani, Ravi
    West Hartford, CT 06117 (US)

(74)Representative: Dehns 
St. Bride's House 10 Salisbury Square
London EC4Y 8JD
London EC4Y 8JD (GB)


(56)References cited: : 
EP-A1- 2 175 336
EP-A2- 2 149 832
EP-A2- 2 149 824
WO-A1-02/46848
  
      
    Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention).


    Description

    BACKGROUND



    [0001] This disclosure relates generally to partitioning faults. More particularly, this disclosure relates to diagnosing operational faults detected within a turbomachine as a module performance change, an actuator fault, or a sensor fault.

    [0002] Turbomachines (e.g., gas turbine engines) are known. A typical turbomachine includes multiple modules or sections, such as a fan module, a compression module, a combustor module, a turbine module, etc. Measuring parameters of the turbomachine facilitates identif ying operational faults. For example, measuring the temperature and pressures of the modules can indicate changes in the performance of the module and help in identifying faults related to module performance. Another operational fault relates to actuators of the turbomachines. As known, the actuators manipulate the positions of various components that are essential for proper operation of the turbomachinery. An example actuator fault includes an actuator that is stuck in a closed position, which can negatively affect performance of the turbomachine.

    [0003] Turbomachines include sensors that measure parameters along the gas paths of the turbomachine. Example gas path measurements include the rotational speeds of turbomachine spools, the temperature of gas exhausted from the turbomachine, etc. Other sensors of the turbomachine measure parameters within subsystems of the turbomachine. Example subsystem measurements include turbine case cooling temperatures, air bleed flow, variable stator vanes measurements, etc. Still other sensors measure power conditions of the turbomachine. If the turbomachine is a gas turbine engine, some sensors may measure flight conditions. Examples of these measurements include Mach numbers, altitudes, ambient temperatures, power requirements, etc. Failure of the sensors may result in inaccurate measurements. Sensor failure is another type of operational fault.

    [0004] EP 2175336 A1 discloses a method of determining a difference between measured data and modeled data, establishing a correction value by applying a filter to the difference, and generating a component alert based entirely on an analysis of the correction value.

    [0005] EP 2149832 A2 discloses a system that generates maintenance requests based on a comparison of determined operating parameter values to actual operating condition values.

    SUMMARY



    [0006] The present invention relates to a method of partitioning turbomachine faults as defined by claim 1 and a turbomachine fault partitioning arrangement as defined by claim 8.

    [0007] An example method of partitioning turbomachine faults includes using a modeling computer to model a system, to establish a modeled gas path parameter, and to establish a modeled subsystem parameter. The method then determines a gas path condition representing a difference between an actual gas path parameter and the modeled gas path parameter. The method also determines a subsystem condition representing a difference between an actual subsystem parameter and the modeled subsystem parameter. The method diagnoses a sensor failure based on the gas path condition and the subsystem condition.

    [0008] Another example method of partitioning gas turbine engine faults includes establishing a model of a gas turbine engine, using the model to determine a modeled gas path parameter, and using the model to determine a modeled subsystem parameter. The method identifies a fault in the gas turbine engine based on a comparison of the modeled gas path parameter to a measurement of an actual gas path parameter of the gas turbine engine, and based on a comparison of the modeled subsystem parameter to an actual subsystem parameter from the gas turbine engine.

    [0009] An example arrangement for partitioning gas turbine engine faults includes a modeling computer configured to establish a model of a gas turbine engine. The modeling computer determines a modeled gas path parameter and a modeled subsystem parameter. A controller module is configured to identify a fault in the gas turbine engine based on comparison of the modeled gas path parameter to a measurement of an actual gas path parameter received from the gas turbine engine, and a comparison of the modeled subsystem parameter to an actual subsystem parameter received from a gas turbine engine.

    [0010] These and other features of the disclosed examples can be best understood from the following specification and drawings, the following of which is a brief description:

    BRIEF DESCRIPTION OF THE DRAWINGS



    [0011] 

    Figure 1 shows a sectional view of an example gas turbine engine.

    Figure 2 shows a highly schematic view of an arrangement configured to partition faults within the gas turbine engine of Figure 1.

    Figures 3A and 3B show a flow of an example method for partitioning faults utilizing the Figure 1 arrangement.

    Figure 4 shows a schematic method of providing model driven gas path parameters for the Figures 3A and 3B method.


    DETAILED DESCRIPTION



    [0012] Figure 1 schematically illustrates an example gas turbine engine 10, which is a type of turbomachine. The example gas turbine engine 10 includes (in serial flow communication) a fan section 14, a low pressure compressor 18, a high pressure compressor 22, a combustor 26, a high pressure turbine 30, and a low pressure turbine 34. The gas turbine engine 10 is circumferentially disposed about an engine centerline X.

    [0013] During operation, air is pulled into the gas turbine engine 10 by the fan section 14. Some of the air is pressurized by the compressors 18 and 22, mixed with fuel, and burned within the combustor 26. The turbines 30 and 34 extract energy from the hot combustion gases flowing from the combustor 26.

    [0014] In a two spool design, the high pressure turbine 30 utilizes the extracted energy from the hot combustion gases to power the high pressure compressor 22 through a high speed shaft 38, and the low pressure turbine 34 utilizes the extracted energy from the hot combustion gases to power the low pressure compressor and the fan section 14 through a low speed shaft 42.

    [0015] The examples described in this disclosure are not limited to the two spool engine architecture described, however, and may be used in other architectures, such as single spool axial design, a three spool axial design, and still other architectures. Further, although the examples described herein are described with regard to the gas turbine engine 10, those having skill in this art and the benefit of this disclosure will understand that other examples include other types of turbomachines.

    [0016] Referring now to Figure 2 with continuing reference to Figure 1, in an example fault partitioning arrangement, the sections of the engine 10 correspond generally to engine modules 46. Some of the engine modules 46 include subsystem actuators 54. The example engine 10 also includes subsystem actuators 54 that are not located within the engine modules 46. Some of the engine modules 46 include subsystem sensors 76. The example engine 10 also includes subsystem sensors 76 that are not located within the engine modules 46.

    [0017] In this example, the fault partitioning arrangement includes a modeling computer 62 configured to generate a physics-based model 64 of the gas turbine engine 10. The example modeling computer 62 includes a memory module 66, a controller module 70, and a display 74. In one example, an engine simulation program, such as MATLAB, stored in the memory module 66 and executed with the controller module 70 is used to generate the model 64. Other examples utilize other types of software to generate the model 64.

    [0018] Many types of modeling computers 62 can be used to implement various functions described herein. In terms of hardware architecture, modeling computer 62 can additionally include one or more input and/or output (I/O) device interface(s) that are communicatively coupled via a local interface. The local interface can include, for example, but is not limited to, one or more buses and/or other wired or wireless connections. The local interface may have additional elements, which are omitted for simplicity, such as additional controllers, buffers (caches), drivers, repeaters, and receivers to enable communications. Further, the local interface may include address, control, and/or data connections to enable appropriate communications among the aforementioned components.

    [0019] The example controller module 70 comprises a processor for executing software, particularly software stored in the memory module 66. The processor can be a custom made or commercially available processor, a central processing unit (CPU), an auxiliary processor among several processors associated with the computing device, a semiconductor based microprocessor (in the form of a microchip or chip set) or generally any device for executing software instructions.

    [0020] The memory module 66 can include any one or combination of volatile memory elements (e.g., random access memory (RAM, such as DRAM, SRAM, SDRAM, VRAM, etc.)) and/or nonvolatile memory elements (e.g., ROM, hard drive, tape, CD-ROM, Flash, etc.). Moreover, the memory module 66 may incorporate electronic, magnetic, optical, and/or other types of storage media.

    [0021] As mentioned previously, the model generating software in the memory module 66 may include one or more additional or separate programs, each of which includes an ordered listing of executable instructions for implementing logical functions. A system component embodied as software may also be construed as a source program, executable program (object code), script, or any other entity comprising a set of instructions to be performed. When constructed as a source program, the program is translated via a compiler, assembler, interpreter, or the like, which may or may not be included within the memory module 66.

    [0022] The Input/Output devices that may be coupled to system I/O Interface(s) may include input devices, for example but not limited to, a keyboard, mouse, scanner, microphone, camera, proximity device, etc. Further, the Input/Output devices may also include output devices, for example but not limited to, a printer, display, etc. Finally, the Input/Output devices may further include devices that communicate both as inputs and outputs, for instance but not limited to, a modulator/demodulator (modem; for accessing another device, system, or network), a radio frequency (RF) or other transceiver, a telephonic interface, a bridge, a router, etc.

    [0023] The example modeling computer 62 is configured to receive measurements from a plurality of sensors 76 and other devices within the engine 10. Example measurements received from the sensors 76 include measurements from the engine modules 46, the positions of the subsystem actuators 54, measurements from the subsystem sensors 58, etc.

    [0024] The measurements received by the modeling computer 62 generally fall into three categories: engine inputs (U), gas path parameters (Y), and engine subsystem parameters (Z). Example engine inputs include mach numbers, altitudes, total ambient temperatures, engine power requirements, etc. Example gas path parameters include measurements collected along the engine's gas path, such as low spool speeds, high spool speeds, exhaust gas temperatures, etc. Example subsystem parameter measurements include turbine case cooling measurements, bleed measurements, variable stator vane measurements, etc.

    [0025] In this example, the modeling computer 62 is configured to generate modeled gas path parameters () based on the engine inputs received from the engine 10. The example modeling computer 62 is further configured to generate modeled subsystem parameters () based on the engine inputs received from the engine 10.

    [0026] Once generated, the modeling computer 62 compares the modeled gas path parameter () to an actual gas path parameter (y) measured from the engine 10 and determines a difference between the two. Similarly, the modeling computer 62 compares modeled subsystem parameter () generated by the modeling computer 62 to an actual subsystem parameter (z) measured from the engine 10.

    [0027] Referring to Figures 3A and 3B with continuing reference to Figure 2, an example diagnosis method 100 uses the differences to partition faults into three categories of faults: faults of the subsystem sensors 58, faults of the subsystem actuators 54, and faults in the performance of engine modules 46.

    [0028] Example failures of the subsystem sensors 58 include a sensor failing to properly measure feedback of the subsystem parameter values of the engine 10. A sensor measuring turbine case cooling positions may fail during operation of the engine, for example.

    [0029] Example failures of the subsystem actuators 54 include a subsystem actuator of the engine 10 that is stuck at a particular position or not operating as controlled. For example, a bleed 2.5 actuator may not completely close or completely open when such actions are initiated.

    [0030] Example fault associated with module performance includes one of the engine modules 46 operating at a reduced efficiency. For example, the high pressure compressor 18 has a particular flow capacity and efficiency that experiences a change in performance due to contamination or fouling in the high pressure compressor.

    [0031] At a step 104, the diagnosis method 100 models the engine 10, a type of system, using the modeling computer 62. The diagnosis method 100 determines the difference (Δy) between the modeled gas path condition () and the actual gas path condition (y) at a step 108. The diagnosis method 100 determines a difference between the modeled subsystem parameter () and the actual subsystem parameter (z) at a step 112.

    [0032] At a step 116, the diagnosis method 100 determines whether the gas path difference (Δy) determined in the step 108 is less than or equal to an established gas path threshold value (α). The method at the step 116 also determines if the subsystem difference (Δz) is less than or equal to an established subsystem threshold value (β). In one example, a threshold value for nl is Δy > α2%RPM, a threshold value for EGT is y > α50°C, a threshold value for TCC is Δz > 5% ← β, and a threshold value for B25 bleed is Δz > 3%.

    [0033] If the gas path difference (Δy) is less than or equal to the established gas path threshold value, and if the subsystem difference (Δz) is less than or equal to the established subsystem threshold value, the diagnosis method 100 moves to a step 118 and determines that there is no fault capable of partitioning. Otherwise, the diagnosis method 100 moves to a step 120.

    [0034] At the step 120, the diagnosis method 100 determines if the gas path difference (Δy) is less than or equal to the established gas path threshold value (α). If yes, the diagnosis method 100 can deduce at a step 124 that the subsystem difference is greater than an established subsystem parameter (based on the step 116). The diagnosis method 100 then diagnoses a sensor failure at a step 130.

    [0035] In this example, recall that the failure diagnosed at step 130 refers to a condition where a sensor measuring the subsystem parameter values (z) has failed during operation of the engine 10. During this type of failure, there is no significant disagreement between the measured gas path parameters (y) and model-assumed gas path parameters (). This is because the gas path parameter measurements are based on the position of the actuator and not on the sensor measurements of feedback engine sub-system parameters (z). As shown in Equation (1), the gas path parameters delta is below the threshold value (α) when a sensor failure is diagnosed at the step 130.



    [0036] There is also considerable disagreement between the measured sub-system parameters (z) and modeled sub-system parameters () when a sensor failure is diagnosed at the step 130. This is because the measured sub-system parameters (z) come directly from the sensor 26, which in this case has failed. As a result, engine sub-system parameters deltas (Δz) are above a certain threshold (provided β > 0) as shown in Equation (2).



    [0037] If the gas path difference (Δy) is not less than or equal to the established gas path threshold value (α) at the step 120, the diagnosis method 100 then determines if the subsystem difference (Δz) established in the step 112 is greater than the subsystem threshold value (β) at a step 132. If yes, the diagnosis method determines the difference (Δyz) between the actual gas path parameter (y) and the model driven parameter (z) at a step 136.

    [0038] The diagnosis method 100 then determines if the difference (Δyz) in the step 136 is less than or equal to an established model driven gas path threshold value at a step 138. If yes, the diagnosis method 100 diagnoses an actuator failure at a step 140. A user is then able to focus a repair or replacement procedure to the particular actuator within the engine 10, for example.

    [0039] If the difference (Δyz) in the step 138 is not less than or equal to the established model driven gas path threshold value, the diagnosis method 100 determines, at a step 142, that there is no fault capable of partitioning.

    [0040] In this example, the actuator failure at the step 140 represents a condition where engine sub-system actuator is stuck at a certain position or not operating as controlled (e.g., a bleed 2.5 actuator not completely closed or not completely open). During this type of a failure there will be considerable disagreement between the measured gas-path parameters (y) and modeled gas-path parameters (). This is because the measured gas-path parameters are directly related to the position of the actuator, which in this case is the cause for failure. The gas path parameters deltas are above a certain threshold when the actuator failure is diagnosed in the step 140 as shown in Equation (3).



    [0041] Also during this type of failure, there will be considerable disagreement between the actual subsystem parameters (z) and modeled subsystem parameters () as shown in Equation (4). This is because, unlike a sensor failure, an actuator failure will affect the measured sub-system parameters.



    [0042] Referring again to the step 132, if the subsystem parameter difference (Δz) is not greater than the established subsystem parameter threshold value, the diagnosis method 100 determines the difference (Δyz) between the actual gas path parameter (y) and the modeled gas path parameter (z) at a step 144. The diagnosis method 100 then determines if the difference (Δyz) is greater than an established model driven gas path threshold value at a step 146. If yes, the diagnosis method 100 diagnoses a module performance change failure at a step 150. The user is then able to focus a repair or replacement procedure on that module within the engine 10, for example.

    [0043] If the difference in the step 146 is not greater than the established model driven gas path threshold value, the diagnosis method 100 determines, at a step 156, that there is no fault capable of partitioning.

    [0044] In this example, the module performance change failure diagnosed in the step 150 refers to a condition where the engine module 46 is operating at reduced efficiency (e.g., high pressure flow capacities and efficiencies changing due to contamination or fouling in HPC). During this type of a failure there will be considerable disagreement between the measured gas-path parameters (y) and modeled gas-path parameters () because the measured gas-path parameters are directly related to the performance of engine modules 46. As shown in Equation (5), the gas path parameters deltas are above a certain threshold (α > 0) when the module performance change failure is diagnosed.



    [0045] The model driven gas path parameter (z) at the step 144 is determined by driving the engine model 64 to have the same sub-system parameter setting as the actual engine 10. For example, the engine model 64 is driven to generate model subsystem parameters that are the same as the system parameter.

    [0046] Referring to Figure 4 with continuing reference to Figures 2-3, a collection method 160 is used to gather the variables utilized in the example method 100. A portion of the method 164 shows the measured gas path parameters (y) and the measured sub-system parameters (z) obtained from the actual engine measurements compared to the modeled values. Another portion of the method 168 shows the model when driven with the measured subsystem parameters (z) compared to the modeled values.

    [0047] In the method 160, the model-driven gas path parameter delta is represented as (z). In the method 160, the model-driven sub-system parameters () are the same as the measured sub-system parameters (z). As a result, the model-assumed deltas of the sub-system parameters are zero (Δz = 0). The model-driven gas path parameters deltas (Δyz) are utilized in portions of the method 100.

    [0048] The model driven gas path parameters (z) are estimates of gas-path parameters (y) using a schedule that is based on engine inputs (u) and engine subsystem parameters (z). As shown in Equation (6), the model driven gas path parameter deltas (Δyz) represent the deviation of measured gas path parameters (y) from the model-driven estimates of gas-path parameters (z).



    [0049] In this example, a failed actuator is the cause for the difference in the model-assumed gas path parameters () and model-driven gas path parameters (z). Thus, if the method 100 diagnoses an actuator failure at the step 150, the model-driven gas-path parameters (z) and the model-assumed gas-path parameters () are both below the threshold (provided γ > 0) as shown in Equation (7).



    [0050] In this example, a module performance change failure is indicated when the deltas of model-driven gas-path parameters (Δyz) are above some threshold (provided γ > 0) as shown in Equation (8) after driving the model with the measured subsystem parameters (z).

    Table 1 shows the diagnosis logic for the example method 100.
    Condition 1Condition 2Condition 3Diagnosis
    Δyα Δz > β -- Sensor Failure
    Δy > α Δz > β Δyzγ Actuator Failure
    Δy > α Δzβ Δyz > γ Module Performance Change


    [0051] Features of the disclosed example include identifying faults within a particular area of an engine based on data analysis rather than physical examination of the engine.

    [0052] The preceding description is exemplary rather than limiting in nature. Variations and modifications to the disclosed examples may become apparent to those skilled in the art that do not necessarily depart from the essence of this disclosure. Thus, the scope of legal protection given to this disclosure can only be determined by studying the following claims.


    Claims

    1. A method of partitioning turbomachine faults, comprising the following steps in the given order:

    establishing a model (64) of a turbomachine (10);

    using the model to determine a modeled gas path parameter (ŷ) and a modeled subsystem parameter (); and

    identifying a fault in the turbomachine;

    wherein the fault comprises a sensor failure, and

    wherein
    the fault is identified based on a comparison of the modeled gas path parameter to a measurement of an actual gas path parameter (y) of the turbomachine and a comparison of the modeled subsystem parameter to an actual subsystem (z) parameter from the turbomachine;

    characterised in that the method further comprises

    determining (108) a gas path condition (Δy) representing a difference between an actual gas path parameter (y) and the modeled gas path parameter (ŷ);

    determining (112) a subsystem condition (Δz) representing a difference between an actual subsystem parameter (z) and the modeled subsystem parameter (), and

    diagnosing a sensor failure based on the gas path condition and the subsystem condition;

    adjusting the modeled subsystem parameter to match the actual subsystem parameter, determining a model-driven gas path parameter (yz) based on the modeled subsystem parameter, and

    diagnosing an actuator failure or a module performance change failure based on a comparison of the actual gas path parameter and the model-driven gas path parameter,

    wherein an actuator failure is diagnosed (140) when the gas path condition is greater than a first gas path threshold value (120), the subsystem condition is greater than a subsystem threshold value (132), and the difference between the actual gas path parameter and the model-driven gas path parameter is less than or equal to a second gas path threshold value; and

    wherein a module performance change failure is diagnosed (150) when the gas path condition is greater than a first gas path threshold value, the subsystem condition is less than or equal to a subsystem threshold value, and the difference between the actual gas path parameter and the model-driven gas path parameter is greater than a second gas path threshold value.


     
    2. The method of claim 1 wherein the turbomachine is a gas turbine engine (10).
     
    3. The method of claim 1 or 2 comprising:
    using a modeling computer (62) to model the turbomachine system (64) and to establish the modeled gas path parameter (ŷ) and a modeled subsystem parameter.
     
    4. The method of any preceding claim, wherein a sensor failure is diagnosed (130) when the gas path condition is less than or equal to an established first gas path threshold value (α, 120) and the subsystem condition is greater than a subsystem threshold value (β, 124).
     
    5. The method of any preceding claim, including utilizing a physics-based system model (64) to establish the modeled gas path parameter and the modeled subsystem parameter.
     
    6. The method of any preceding claim, wherein the actual gas path parameter comprises a measurement collected along a gas path of a turbomachine.
     
    7. The method of any preceding claim, wherein the modeled gas path parameter and the modeled subsystem parameter are calculated using a model that is exclusively adjusted using gas turbine engine input variables.
     
    8. A turbomachine fault partitioning arrangement, comprising:

    a modeling computer (62) configured to establish a model (64) of a turbomachine (10), the modeling computer further configured to determine a modeled gas path parameter (ŷ) and a modeled subsystem parameter (); and

    a controller module (70) configured to identify a fault of the turbomachine, wherein the controller module is configured to identify a fault of the turbomachine based on a first comparison of the modeled gas path parameter to a measurement of an actual gas path parameter (y), and a second comparison of the modeled subsystem parameter to an actual subsystem parameter (z); characterised in that the controller module is configured to perform a method according to any of the preceding claims.


     
    9. The turbomachine fault partitioning arrangement of claim 8, wherein fault comprises a sensor failure; and/or wherein the actual gas path parameter and the actual subsystem parameters are received from at least one sensor (76) of the gas turbine engine.
     


    Ansprüche

    1. Verfahren zum Aufteilen von Turbomaschinenfehlern, umfassend die folgenden Schritte in der vorgegebenen Reihenfolge:

    Erstellen eines Modells (64) einer Turbomaschine (10);

    Nutzen des Modells zum Bestimmen eines modellierten Gaswegparameters (ŷ) und eines modellierten Teilsystemparameters (ẑ); und

    Identifizieren eines Fehlers in der Turbomaschine; wobei der Fehler eine Sensorstörung umfasst, und wobei der Fehler auf der Grundlage eines Vergleichs des modellierten Gaswegparameters mit einer Messung eines tatsächlichen Gaswegparameters (ŷ) der Turbomaschine und eines Vergleichs des modellierten Teilsystemparameters und eines tatsächlichen Teilsystemparameters (ẑ) der Turbomaschine identifiziert wird;

    gekennzeichnet dadurch, dass das Verfahren ferner das Bestimmen (108) eines Gaswegzustandes (Δy), der einen Unterschied zwischen einem tatsächlichen Gaswegparameter (y) und dem modellierten Gaswegparameter (ŷ) darstellt, umfasst;

    Bestimmen (112) eines Teilsystemzustandes (Δz), der einen Unterschied zwischen einem tatsächlichen Teilsystemparameter (z) und dem modellierten Teilsystemparameter (ẑ) darstellt, und

    Diagnostizieren einer Sensorstörung auf Grundlage des Gaswegzustandes und des Teilsystemzustandes;

    Anpassen des modellierten Teilsystemparameters, um mit dem tatsächlichen Teilsystemparameter übereinzustimmen, wobei ein modellgetriebener Gaswegparameter (yz) auf der Grundlage des modellierten Teilsystemparameters bestimmt wird, und

    Diagnostizieren einer Betätigungselementstörung oder einer Modulleistungsänderungsstörung auf der Grundlage eines Vergleichs des tatsächlichen Gaswegparameters und des modellgetriebenen Gaswegparameters,

    wobei eine Betätigungselementstörung diagnostiziert (140) wird, wenn der Gaswegzustand größer ist als ein erster Gaswegschwellenwert (120), der Teilsystemzustand größer ist als ein Teilsystemschwellenwert (132) und der Unterschied zwischen dem tatsächlichen Gaswegparameter und dem modellgetriebenen Gaswegparameter weniger oder gleich einem zweiten Gaswegschwellenwert ist; und

    wobei eine Modelleistungsänderungsstörung diagnostiziert (150) wird, wenn der Gaswegzustand größer als ein erster Gaswegschwellwert ist, der Teilsystemzustand kleiner oder gleich einem Teilsystemschwellenwert ist und der Unterschied zwischen dem tatsächlichen Gaswegparameter und dem modellgetriebenen Gaswegparameter größer als ein zweiter Gaswegschwellenwert ist.


     
    2. Verfahren nach Anspruch 1, wobei die Turbomaschine ein Gasturbinentriebwerk (10) ist.
     
    3. Verfahren nach Anspruch 1 oder 2, ferner umfassend:
    Verwenden eines Modelliercomputers (62) zum Modellieren des Turbomaschinensystems (64) und zum Erstellen des modellierten Gaswegparameters (ŷ) und eines modellierten Teilsystemparameters.
     
    4. Verfahren nach jedem vorhergehenden Anspruch, wobei eine Sensorstörung diagnostiziert (130) wird, wenn der Gaswegzustand weniger oder gleich einem erstellten ersten Gaswegschwellenwert (α, 120) und der Teilsystemzustand größer als ein Teilsystemschwellenwert (β, 124) ist.
     
    5. Verfahren nach jedem vorhergehenden Anspruch, umfassend das Verwenden eines Systemmodells (64) auf der Grundlage der Physik, um den modellierten Gaswegparameter und den modellierten Teilsystemparameter zu erstellen.
     
    6. Verfahren nach jedem vorhergehenden Anspruch, wobei der tatsächliche Gaswegparameter eine Messung umfasst, die entlang eines Gaswegs einer Turbomaschine gesammelt wurde.
     
    7. Verfahren nach jedem vorhergehenden Anspruch, wobei der modellierte Gaswegparameter und der modellierte Teilsystemparameter unter Anwendung eines Modells berechnet werden, das ausschließlich unter Nutzung von Gasturbinentriebwerkseingabevariablen eingestellt wurde.
     
    8. Turbomaschinenfehlerteilungsanordnung, die Folgendes umfasst:

    ein Modelliercomputer (62), der dazu konfiguriert ist, ein Modell (64) einer Turbomaschine (10) zu erstellen, der Modelliercomputer ist ferner dazu konfiguriert, einen modellierten Gaswegparameter (ŷ) und einen modellierten Teilsystemparameter (ẑ) zu bestimmen; und

    ein Steuermodul (70), das dazu konfiguriert ist, einen Fehler der Turbomaschine zu identifizieren, wobei das Steuermodul dazu konfiguriert ist, einen Fehler der Turbomaschine auf der Grundlage eines ersten Vergleichs des modellierten Gaswegparameters mit einer Messung eines tatsächlichen Gaswegparameters (y) und eines zweiten Vergleichs des modellierten Teilsystemparameters mit einem tatsächlichen Teilsystemparameter (z) zu identifizieren; dadurch gekennzeichnet, dass das Steuermodul dazu konfiguriert ist, ein Verfahren entsprechend jedem der vorhergehenden Ansprüche durchzuführen.


     
    9. Turbomaschinenfehlerteilungsanordnung nach Anspruch 8, wobei ein Fehler eine Sensorstörung umfasst; und/oder wobei der tatsächliche Gaswegparameter und der tatsächliche Teilsystemparameter von mindestens einem Sensor (76) des Gasturbinentriebwerks empfangen werden.
     


    Revendications

    1. Procédé de segmentation de défauts de turbomachine, comprenant les étapes suivantes dans l'ordre donné :

    l'établissement d'un modèle (64) d'une turbomachine (10) ;

    l'utilisation du modèle pour déterminer un paramètre de trajet de gaz modélisé (ŷ) et un paramètre de sous-système modélisé () ; et

    l'identification d'un défaut dans la turbomachine ;

    dans lequel le défaut comprend une défaillance de capteur, et dans lequel le défaut est identifié d'après une comparaison du paramètre de trajet de gaz modélisé à une mesure d'un paramètre de trajet de gaz réel (y) de la turbomachine et une comparaison du paramètre de sous-système modélisé à un paramètre de sous-système réel (z) issu de la turbomachine ;

    caractérisé en ce que le procédé comprend en outre la détermination (108) d'un état de trajet de gaz (Δy) représentant une différence entre un paramètre de trajet de gaz réel (y) et le paramètre de trajet de gaz modélisé (ŷ) ;

    la détermination (112) d'un état de sous-système (Δz) représentant une différence entre un paramètre de sous-système réel (z) et le paramètre de sous-système modélisé (), et

    le diagnostic d'une défaillance de capteur d'après l'état de trajet de gaz et l'état de sous-système ;

    l'ajustement du paramètre de sous-système modélisé pour qu'il concorde avec le paramètre de sous-système réel, la détermination d'un paramètre de trajet de gaz guidé par modèle (yz) d'après le paramètre de sous-système modélisé, et

    le diagnostic d'une défaillance d'actionneur ou d'une défaillance de changement de performance de module d'après une comparaison du paramètre de trajet de gaz réel et du paramètre de trajet de gaz guidé par modèle,

    dans lequel une défaillance d'actionneur est diagnostiquée (140) lorsque l'état de trajet de gaz est supérieur à une première valeur seuil de trajet de gaz (120), l'état de sous-système est supérieur à une valeur seuil de sous-système (132), et la différence entre le paramètre de trajet de gaz réel et le paramètre de trajet de gaz guidé par modèle est inférieure ou égale à une seconde valeur seuil de trajet de gaz ; et

    dans lequel une défaillance de changement de performance de module est diagnostiquée (150) lorsque l'état de trajet de gaz est supérieur à une première valeur seuil de trajet de gaz, l'état de sous-système est inférieur ou égal à une valeur seuil de sous-système, et la différence entre le paramètre de trajet de gaz réel et le paramètre de trajet de gaz guidé par modèle est supérieure à une seconde valeur seuil de trajet de gaz.


     
    2. Procédé selon la revendication 1, dans lequel la turbomachine est un moteur à turbine à gaz (10).
     
    3. Procédé selon la revendication 1 ou 2, comprenant :
    l'utilisation d'un ordinateur de modélisation (62) pour modéliser le système de turbomachine (64) et pour établir le paramètre de trajet de gaz modélisé (ŷ) et un paramètre de sous-système modélisé.
     
    4. Procédé selon une quelconque revendication précédente, dans lequel une défaillance de capteur est diagnostiquée (130) lorsque l'état de trajet de gaz est inférieur ou égal à une première valeur seuil de trajet de gaz (α, 120) établie et l'état de sous-système est supérieur à une valeur seuil de sous-système (β, 124).
     
    5. Procédé selon une quelconque revendication précédente, comportant l'emploi d'un modèle de système basé sur la physique (64) pour établir le paramètre de trajet de gaz modélisé et le paramètre de sous-système modélisé.
     
    6. Procédé selon une quelconque revendication précédente, dans lequel le paramètre de trajet de gaz réel comprend une mesure recueillie le long d'un trajet de gaz d'une turbomachine.
     
    7. Procédé selon une quelconque revendication précédente, dans lequel le paramètre de trajet de gaz modélisé et le paramètre de sous-système modélisé sont calculés à l'aide d'un modèle qui est ajusté exclusivement à l'aide de variables d'entrée de moteur à turbine à gaz.
     
    8. Agencement de segmentation de défaut de turbomachine, comprenant :

    un ordinateur de modélisation (62) configuré pour établir un modèle (64) d'une turbomachine (10), l'ordinateur de modélisation étant en outre configuré pour déterminer un paramètre de trajet de gaz modélisé (ŷ) et un paramètre de sous-système modélisé () ; et

    un module de dispositif de commande (70) configuré pour identifier un défaut de la turbomachine, dans lequel le module de dispositif de commande est configuré pour identifier un défaut de la turbomachine d'après une première comparaison du paramètre de trajet de gaz modélisé à une mesure d'un paramètre de trajet de gaz réel (y), et une seconde comparaison du paramètre de sous-système modélisé à un paramètre de sous-système réel (z) ; caractérisé en ce que le module de dispositif de commande est configuré pour réaliser un procédé selon l'une quelconque des revendications précédentes.


     
    9. Agencement de segmentation de défaut de turbomachine selon la revendication 8, dans lequel un défaut comprend une défaillance de capteur ; et/ou dans lequel le paramètre de trajet de gaz réel et les paramètres de sous-système réel sont reçus en provenance d'au moins un capteur (76) du moteur à turbine à gaz.
     




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    REFERENCES CITED IN THE DESCRIPTION



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    Patent documents cited in the description