CA1188775A - Method and apparatus for failure detection and correction in gas turbine engine control system - Google Patents
Method and apparatus for failure detection and correction in gas turbine engine control systemInfo
- Publication number
- CA1188775A CA1188775A CA000292813A CA292813A CA1188775A CA 1188775 A CA1188775 A CA 1188775A CA 000292813 A CA000292813 A CA 000292813A CA 292813 A CA292813 A CA 292813A CA 1188775 A CA1188775 A CA 1188775A
- Authority
- CA
- Canada
- Prior art keywords
- control
- engine
- parameters
- values
- controlled
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
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Classifications
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/46—Emergency fuel control
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B9/00—Safety arrangements
- G05B9/02—Safety arrangements electric
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/50—Control logic embodiments
- F05D2270/54—Control logic embodiments by electronic means, e.g. electronic tubes, transistors or IC's within an electronic circuit
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/70—Type of control algorithm
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/70—Type of control algorithm
- F05D2270/71—Type of control algorithm synthesized, i.e. parameter computed by a mathematical model
Abstract
METHOD AND APPARATUS FOR FAILURE DETECTION AND CORRECTION
IN GAS TURBINE ENGINE CONTROL SYSTEM
Abstract of the Disclosure In a system for controlling the performance of a gas turbine engine, a small digital computer is placed between the output from the sensors which measure the value of the various engine parameters used for control and the computational unit which computes the values of output signals to actuators which maintain values for controlled engine parameters such as engine fuel flow and geometry. The digital computer includes a stored program which models the engine being controlled and which is continually updated by the output from the control parameter sensors and by signals indicating the value of controlled parameters. The control parameters input to the computational unit are continuously generated by the computer and represent the model's estimate of the actual value of the control parameter sensor signals input to the computer. The computer continuously compares received control parameter sensor inputs with the corresponding input generated by the engine model and in the event a difference exceeding stored and calculated tolerances is detected, that sensor is inhibited from updating the engine model. The computer continues to estimate values for control parameters for the inhibited sensor inputs using the stored model updated by the remaining uninhibited control parameter sensor signals and by the signal indicating the value of the controlled parameters. An indication of an interrupted control parameter sensor signal may be provided to the engine operator. The system permits continued operation of the engine control even though one or more control parameter sensor inputs are lost. When used with a digital engine control, the system may be integrated into the control without the need of separate computer components.
IN GAS TURBINE ENGINE CONTROL SYSTEM
Abstract of the Disclosure In a system for controlling the performance of a gas turbine engine, a small digital computer is placed between the output from the sensors which measure the value of the various engine parameters used for control and the computational unit which computes the values of output signals to actuators which maintain values for controlled engine parameters such as engine fuel flow and geometry. The digital computer includes a stored program which models the engine being controlled and which is continually updated by the output from the control parameter sensors and by signals indicating the value of controlled parameters. The control parameters input to the computational unit are continuously generated by the computer and represent the model's estimate of the actual value of the control parameter sensor signals input to the computer. The computer continuously compares received control parameter sensor inputs with the corresponding input generated by the engine model and in the event a difference exceeding stored and calculated tolerances is detected, that sensor is inhibited from updating the engine model. The computer continues to estimate values for control parameters for the inhibited sensor inputs using the stored model updated by the remaining uninhibited control parameter sensor signals and by the signal indicating the value of the controlled parameters. An indication of an interrupted control parameter sensor signal may be provided to the engine operator. The system permits continued operation of the engine control even though one or more control parameter sensor inputs are lost. When used with a digital engine control, the system may be integrated into the control without the need of separate computer components.
Description
Background of the Invention The invention relates to a control system for a gas turbine engine and more particularly to a method and apparatus for failure correction in such control systerns.
Gas turbine engine control systems particularly for use in aircraft generally include electrical sensOrs which measure various engine parameters for control oE the engine. Such sensors have typically measured gas generator and fan rotational velocities and engine operalting pressures and temperatures. These, in turn, are used to control the position of the actuators which vary engine controlled parameters, typically fuel flow and geometry. In conventional engine control systems ~he control pararneter sensors and sensors indicating the value of controlled parameters are connected by electrical cables to the electronic cornputation sections of the engine control system. The electronic computation section may be the analog in which dedicated circuits perEorm continuous computations or it may he digital in which computations are performed sequentially on a time-sharing basis, In either case, the computational unit of the control using the sensed values for control and controlled parameters and known engine behavior characteristics computes values of output signals to modify the controlled parameters in order to maintain a desired level of engine performance. The electrical outputs from the computation section are amplified, conditioned and then input to the various electrohydraulic and electromechanical actuators which position the electric~lly controlled fuel and hydraulic valves which alter the controlled parameters. These in turn modify engine 13 DV -6 5'3 8 operation which change the measured control parameters, i. e.
engine rotational velocity, pressures, and temperatur2s, thereby completing closed loop control of the engine.
A major problem associated with such prior art control systerns is that loss of tne proper input from one or more sensors may cause loss of control of the corresponding engine pararneter resulting in major degradation of engine performance. Such signal loss may be dub to any nurnber of factors including failure of thLe sensor, failure of the interconnection between the sensor and control or failure of any of the processing circuitry for such s ignals .
Object of the Invention .~
Accordingly, it is the primary object of this invention to provide a control system for gas turbine engines which prevents major degradat~on of engine performance in the event of loss of the proper signal from the engine control parameter sensors.
It is a further object of this invention to provide a control system which transmits an indication to the engine operator when the failure of an engine sensor has occurred.
SummLary of the Invention -These and other objects of the invention have been achieved in the preferred embodiment of the invention wherein a system for controlling the gas turbine engine is irnproved by providing a small digital computer between the input sensors which measure engine control parameters and the computational unit which cornputes values of output signals to the actuators which control engine controlled parameters such as fuel flow, and geometry. The digital computer includes a stored program which models the engine being controlled 5; 13I~ ~i5 and which is continually updated by the signals received from the control parameter sensors and signals received from sensors for the controlled pararneters. The computer in turn uses these inputs, the model and stored data items representing est ima te s of the internal status o~ the engine to generate output signals for transmittal to the control computational unit. These signals represent the models estimate of the actual value oE the control parameter sensor signals input to the computer and are continuously updated by received control and controlled parameter sensor signals. The computer continuously compares each control parameter sensor input with the corresponding output to the control computationaL uni-t and in the event a difference exceeding s-tored or calculated tolerances is detected that con~rol parameter sensor is inhibited from updating the engine n-lodel.
However, the loss OI a control parameter sensor input does not significantly degrade engine performance~ since the computer continues to provide output signals corresponding to the inhibited input sensor signal. This outpu1; represents the computers best estimate of the value of the inhibited input signal which is calculated using the stored engine model updated by the remaining uninhibited control parameter input signals and by the controlled parameter input signals. An indication that a particular control parameter sensor input signal has been interrupted may be provided to the engine operator through an engine operator interface circuit, The control system of this invention thus permits continued operation OI the engine control without major performance degradation, even though one or more control parameter sensor signal.s is not properly received.
131~V-659 Further, because the model uses the interaction ~etween the various control parameters to compute the value oî a s gnal parameterJ spurious error or small inaccuracies in measured parameters is nninimi~ed such that when no sensors are inhibited the value of th~ control parameters input from the computer are more accurate than those input directly from the individual control parameter sensors.
When used with a control system incorporating a digital computer, the system may be integrated into the control withoul; the need of separate computer components. The system may also be added to an existing analog or other electrical control dS an interconnection between control parameter engine sensors and the control computational unit.
Brief Description OI the Drawings _ . . _ . . . .
The invention may be better understood by reading the following description of the preferred embodiment in conjunction with the accompanying drawings wherein:
Figure 1 is a schematic diagram in block format of the control system of this invention, Figure 2 is a computer ~low diagram of a control program for the control system of this invention.
Description of the Preferred Embodiment :E~eferring to Figure 1 there is shown a control system for a gas turbine engine 10.
Gas turbine engine 10 may be of any type known in the art including a turbojet, turboprop, turboshaft) or high or low bypass ~ 13DV-659~
turbofan. All such engines generally include a plurality of sensors 12 used to measure the values of the parameters used to control the various engine controlled parameters such as engine fuel flow and geometry in order to malntain a desired level of engine performance. A plurality of sensors 13 is also provided to measure the value of the controlled parameters.
The analog signals from the sensors 12 and 13 are input to signal processing amplifiers and analog to digital converters 16 which amplify the signals to a standard DC analog voltage range and thereafter convert these analog signals to a digital format. The digital control signals are then input to a digital computer 18 through the input/output unit 20 thereof.
Digital computer 20 is of the type well-known in the art and comprises a machine having a cycle time fast enough to provide real time operation. It further includes an input/output unit 20 for external interface, an arithmetic unit 22 for performing arithmetic calculations and a program memory 24 for storing programs, information and data. In accordance with this inven-tion, the program memory 24 includes an engine model which simulates the performance of the gas turbine engine 10. Such models are well known in the gas tur~ine engine art and generally comprise a set of mathematical equations defining the inter-relationship between the engine control parameters, typically the pressures and temperatures of the various engine components, as a function of the value of controlled parameters, typically engine fuel flow and geometry (e~g. inlet and e~haust area) and the internal status of the engine. Thus, ~or any given set of controlled parameter conditions, the model will provide calculated values for engine control parameters and vice versa.
~ - 5 -~ 13DV-6598 The program memory 24 also includes an operational program to control data processiny. Referring -to Figure 2, therein is shown a flow chart for the operational program.
After an initialization in which initial values for both control and controlled parameters are preset into the computer, the operational program continually receives signals from the controlled parameter sensors 13 which are input to the engine model. The engine model uses the sensed controlled parameter values plus stored data representing estimates of the internal status of the engine to compute corresponding values for the control parameters. These calculated control parameter values are then inpu-t to the control computational unit which uses them and the controlled parameter values from the sensors 13 to calculate signals for positioning the actuators 14. The calculated control parameter values are also compared with the control parameter values received from the engine sensors 12 and their respective difference calculated. If these differences exceed a tolerance, which may either be stored or calculated as a function of other sensed engine control or operational parametexs, the control program takes action (as will he described below~ to prevent the out of tolerance signal inputs from further updating the model. The operational program may also output a signal to the engine operator indicating that an out of tolerance sensor signal has been received and that the sensor has been inhibited from updating the engine model.
The engine model is updated by changing the stored data representing estimates of the internal status of the engine as a function of the difference between the calculated control parameter values and the corresponding control parameter values received from the engine sensors 12 ~' .( ~ 13DV-6598 Thus, for each control parameter difference computed, a corresponding change is made to each stored data item re-presenting an estimate of the internal status of the engine which is affected by that control parameter. If the control parameter has been inhibited then no corresponding changes are made to the data items affected by that control parameter.
Further, for greater accuracy of response, the magnitude of the change to each stored data item representing an estimate of the internal status of the englne may be weighted so as to proportional to the degree of control the responsible sensed control parameter has over that data item as compared with the degree of control the remaining control parameters have over that data item.
The calculated values for the control parameters are transmitted by the computer to the control computational unit 26. The control computational unit 26 is of the type well-known in the art ~hich may be digital or analog. If analog, a digital to analog converter (not shown) must be provided between the computer 18 and computational unit 26.
The computational unit in the manner well-known in the gas turbine control art uses signals received from the engine control parameter sensors r controlled parameter sensors and known engine behavior characteris-tics, which are generally stored as analog algorithms or digital data r to compute values of output signals to position the engine electromechanical and electrohyclraulic actuators 14 in order to maintain a desired engine performance level. Suitable amplifiers and digital to analoy converters 28 are provided intermediate the control compu-tational unit and actuators 14, in order to condition and/or con-vert the output signals from the control computational unit to the standard voltage range required to operate actuators 14.
. .:,"~, The signal processing amplifiers and analog to digital converters ~, 16, -~t~ , control computational uni-t 26, signal processing amplifiers and digital to analog converters 28 are a11 commercially available devices well-known in the art, the details of which do not form a part of this invention.
In this manner, the controi system of thts invention permits continued operation of the engine controi without major performance degradation even though one or more control parameters sensors inputs are lost.
Various changes could be made to the digital control system as shown in :Figures 1 and 2 without departing from the sc.~pe of this invention. Thus, if this system i9 used with a digital control the logic described herein may be programmed and integrated therein without the need of separate computer components. Alternatively, 15 this system may be applied following a sensor failure in a control system in which direct sensor input to the control computational unit is used.
In this case, the failed sensor signal will be supplied by the engine model,
Gas turbine engine control systems particularly for use in aircraft generally include electrical sensOrs which measure various engine parameters for control oE the engine. Such sensors have typically measured gas generator and fan rotational velocities and engine operalting pressures and temperatures. These, in turn, are used to control the position of the actuators which vary engine controlled parameters, typically fuel flow and geometry. In conventional engine control systems ~he control pararneter sensors and sensors indicating the value of controlled parameters are connected by electrical cables to the electronic cornputation sections of the engine control system. The electronic computation section may be the analog in which dedicated circuits perEorm continuous computations or it may he digital in which computations are performed sequentially on a time-sharing basis, In either case, the computational unit of the control using the sensed values for control and controlled parameters and known engine behavior characteristics computes values of output signals to modify the controlled parameters in order to maintain a desired level of engine performance. The electrical outputs from the computation section are amplified, conditioned and then input to the various electrohydraulic and electromechanical actuators which position the electric~lly controlled fuel and hydraulic valves which alter the controlled parameters. These in turn modify engine 13 DV -6 5'3 8 operation which change the measured control parameters, i. e.
engine rotational velocity, pressures, and temperatur2s, thereby completing closed loop control of the engine.
A major problem associated with such prior art control systerns is that loss of tne proper input from one or more sensors may cause loss of control of the corresponding engine pararneter resulting in major degradation of engine performance. Such signal loss may be dub to any nurnber of factors including failure of thLe sensor, failure of the interconnection between the sensor and control or failure of any of the processing circuitry for such s ignals .
Object of the Invention .~
Accordingly, it is the primary object of this invention to provide a control system for gas turbine engines which prevents major degradat~on of engine performance in the event of loss of the proper signal from the engine control parameter sensors.
It is a further object of this invention to provide a control system which transmits an indication to the engine operator when the failure of an engine sensor has occurred.
SummLary of the Invention -These and other objects of the invention have been achieved in the preferred embodiment of the invention wherein a system for controlling the gas turbine engine is irnproved by providing a small digital computer between the input sensors which measure engine control parameters and the computational unit which cornputes values of output signals to the actuators which control engine controlled parameters such as fuel flow, and geometry. The digital computer includes a stored program which models the engine being controlled 5; 13I~ ~i5 and which is continually updated by the signals received from the control parameter sensors and signals received from sensors for the controlled pararneters. The computer in turn uses these inputs, the model and stored data items representing est ima te s of the internal status o~ the engine to generate output signals for transmittal to the control computational unit. These signals represent the models estimate of the actual value oE the control parameter sensor signals input to the computer and are continuously updated by received control and controlled parameter sensor signals. The computer continuously compares each control parameter sensor input with the corresponding output to the control computationaL uni-t and in the event a difference exceeding s-tored or calculated tolerances is detected that con~rol parameter sensor is inhibited from updating the engine n-lodel.
However, the loss OI a control parameter sensor input does not significantly degrade engine performance~ since the computer continues to provide output signals corresponding to the inhibited input sensor signal. This outpu1; represents the computers best estimate of the value of the inhibited input signal which is calculated using the stored engine model updated by the remaining uninhibited control parameter input signals and by the controlled parameter input signals. An indication that a particular control parameter sensor input signal has been interrupted may be provided to the engine operator through an engine operator interface circuit, The control system of this invention thus permits continued operation OI the engine control without major performance degradation, even though one or more control parameter sensor signal.s is not properly received.
131~V-659 Further, because the model uses the interaction ~etween the various control parameters to compute the value oî a s gnal parameterJ spurious error or small inaccuracies in measured parameters is nninimi~ed such that when no sensors are inhibited the value of th~ control parameters input from the computer are more accurate than those input directly from the individual control parameter sensors.
When used with a control system incorporating a digital computer, the system may be integrated into the control withoul; the need of separate computer components. The system may also be added to an existing analog or other electrical control dS an interconnection between control parameter engine sensors and the control computational unit.
Brief Description OI the Drawings _ . . _ . . . .
The invention may be better understood by reading the following description of the preferred embodiment in conjunction with the accompanying drawings wherein:
Figure 1 is a schematic diagram in block format of the control system of this invention, Figure 2 is a computer ~low diagram of a control program for the control system of this invention.
Description of the Preferred Embodiment :E~eferring to Figure 1 there is shown a control system for a gas turbine engine 10.
Gas turbine engine 10 may be of any type known in the art including a turbojet, turboprop, turboshaft) or high or low bypass ~ 13DV-659~
turbofan. All such engines generally include a plurality of sensors 12 used to measure the values of the parameters used to control the various engine controlled parameters such as engine fuel flow and geometry in order to malntain a desired level of engine performance. A plurality of sensors 13 is also provided to measure the value of the controlled parameters.
The analog signals from the sensors 12 and 13 are input to signal processing amplifiers and analog to digital converters 16 which amplify the signals to a standard DC analog voltage range and thereafter convert these analog signals to a digital format. The digital control signals are then input to a digital computer 18 through the input/output unit 20 thereof.
Digital computer 20 is of the type well-known in the art and comprises a machine having a cycle time fast enough to provide real time operation. It further includes an input/output unit 20 for external interface, an arithmetic unit 22 for performing arithmetic calculations and a program memory 24 for storing programs, information and data. In accordance with this inven-tion, the program memory 24 includes an engine model which simulates the performance of the gas turbine engine 10. Such models are well known in the gas tur~ine engine art and generally comprise a set of mathematical equations defining the inter-relationship between the engine control parameters, typically the pressures and temperatures of the various engine components, as a function of the value of controlled parameters, typically engine fuel flow and geometry (e~g. inlet and e~haust area) and the internal status of the engine. Thus, ~or any given set of controlled parameter conditions, the model will provide calculated values for engine control parameters and vice versa.
~ - 5 -~ 13DV-6598 The program memory 24 also includes an operational program to control data processiny. Referring -to Figure 2, therein is shown a flow chart for the operational program.
After an initialization in which initial values for both control and controlled parameters are preset into the computer, the operational program continually receives signals from the controlled parameter sensors 13 which are input to the engine model. The engine model uses the sensed controlled parameter values plus stored data representing estimates of the internal status of the engine to compute corresponding values for the control parameters. These calculated control parameter values are then inpu-t to the control computational unit which uses them and the controlled parameter values from the sensors 13 to calculate signals for positioning the actuators 14. The calculated control parameter values are also compared with the control parameter values received from the engine sensors 12 and their respective difference calculated. If these differences exceed a tolerance, which may either be stored or calculated as a function of other sensed engine control or operational parametexs, the control program takes action (as will he described below~ to prevent the out of tolerance signal inputs from further updating the model. The operational program may also output a signal to the engine operator indicating that an out of tolerance sensor signal has been received and that the sensor has been inhibited from updating the engine model.
The engine model is updated by changing the stored data representing estimates of the internal status of the engine as a function of the difference between the calculated control parameter values and the corresponding control parameter values received from the engine sensors 12 ~' .( ~ 13DV-6598 Thus, for each control parameter difference computed, a corresponding change is made to each stored data item re-presenting an estimate of the internal status of the engine which is affected by that control parameter. If the control parameter has been inhibited then no corresponding changes are made to the data items affected by that control parameter.
Further, for greater accuracy of response, the magnitude of the change to each stored data item representing an estimate of the internal status of the englne may be weighted so as to proportional to the degree of control the responsible sensed control parameter has over that data item as compared with the degree of control the remaining control parameters have over that data item.
The calculated values for the control parameters are transmitted by the computer to the control computational unit 26. The control computational unit 26 is of the type well-known in the art ~hich may be digital or analog. If analog, a digital to analog converter (not shown) must be provided between the computer 18 and computational unit 26.
The computational unit in the manner well-known in the gas turbine control art uses signals received from the engine control parameter sensors r controlled parameter sensors and known engine behavior characteris-tics, which are generally stored as analog algorithms or digital data r to compute values of output signals to position the engine electromechanical and electrohyclraulic actuators 14 in order to maintain a desired engine performance level. Suitable amplifiers and digital to analoy converters 28 are provided intermediate the control compu-tational unit and actuators 14, in order to condition and/or con-vert the output signals from the control computational unit to the standard voltage range required to operate actuators 14.
. .:,"~, The signal processing amplifiers and analog to digital converters ~, 16, -~t~ , control computational uni-t 26, signal processing amplifiers and digital to analog converters 28 are a11 commercially available devices well-known in the art, the details of which do not form a part of this invention.
In this manner, the controi system of thts invention permits continued operation of the engine controi without major performance degradation even though one or more control parameters sensors inputs are lost.
Various changes could be made to the digital control system as shown in :Figures 1 and 2 without departing from the sc.~pe of this invention. Thus, if this system i9 used with a digital control the logic described herein may be programmed and integrated therein without the need of separate computer components. Alternatively, 15 this system may be applied following a sensor failure in a control system in which direct sensor input to the control computational unit is used.
In this case, the failed sensor signal will be supplied by the engine model,
Claims (10)
1. An improved gas turbine engine control system of the type which comprises means for measuring and transmitting the values of engine control parameters, means for measuring and transmitting the values of engine controlled parameters, actuator means for setting values of engine controlled parameters and control computational means for receiving the control para-meter values and the controlled parameter values and generating signals in response thereto to position the actuator means and to modify the controlled parameter values in order to maintain a desired level of engine performance wherein the improvement comprises:
computer means disposed between the control parameter measuring and transmitting means and the control computational means which receives both the control parameter values and the controlled parameter values and calculates signals representing estimates of the engine control parameter values and transmits said signals to the control computational means.
computer means disposed between the control parameter measuring and transmitting means and the control computational means which receives both the control parameter values and the controlled parameter values and calculates signals representing estimates of the engine control parameter values and transmits said signals to the control computational means.
2. The control system of claim 1 wherein the computer means disregards received control parameters having the values which exceed predetermined and calculated tolerance limits and uses the values of the remaining control parameters and the controlled parameter values to estimate the values of the disregarded control parameters.
3. The control system of claim 2 wherein the computer means includes an engine model which uses stored formula and stored data items representing the interrelationships between the control parameters and the controlled parameters to develop estimates of the internal status of the engine to simulate engine performance.
4. The control system of claim 3 wherein the computer means uses the engine model to calculate control parameter values for transmittal to the control computational means.
5. The control system of claim 4 wherein the computer means compares the calculated control parameter values with the values of control parameters received from corresponding control parameter measuring and transmitting means and calculates a plurality of signals each corresponding to the difference between the respective calculated and measured control parameter values.
6. The control system of claim 5 wherein the computer means determines whether each calculated difference signal is within predetermined and calculated tolerance limits.
7. The control system of claim 6 wherein the computer means provides an indication to the engine operator when any difference signal exceeds the predetermined and calculated tolerance limits.
8. The control system of claim 6 wherein the computer means uses the calculated difference signals to modify the value of each stored data item representing an estimate of the internal status of the engine which is affected by the control parameter corresponding to the difference signal.
9. The control system of claim 8 wherein those difference signals which exceed the predetermined and calculated tolerance limits are inhibited from modifying stored data items representing an estimate of the internal status of the engine.
10. The control system of claim 8 wherein the magnitude of the change to each stored data item produced by a calculated difference signal is weighted so as to be in pro-portion to the degree of control that the control parameter
10. The control system of claim 8 wherein the magnitude of the change to each stored data item produced by a calculated difference signal is weighted so as to be in pro-portion to the degree of control that the control parameter
Claim 10 continued:
corresponding to the calculated difference signal has over that data item as compared with the degree of control that the remaining control parameters have over that data item.
corresponding to the calculated difference signal has over that data item as compared with the degree of control that the remaining control parameters have over that data item.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US75205076A | 1976-12-20 | 1976-12-20 | |
| US752,050 | 1976-12-20 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1188775A true CA1188775A (en) | 1985-06-11 |
Family
ID=25024630
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000292813A Expired CA1188775A (en) | 1976-12-20 | 1977-12-09 | Method and apparatus for failure detection and correction in gas turbine engine control system |
Country Status (7)
| Country | Link |
|---|---|
| JP (1) | JPS5395410A (en) |
| BE (1) | BE862071A (en) |
| CA (1) | CA1188775A (en) |
| DE (1) | DE2756681C2 (en) |
| FR (1) | FR2374513A1 (en) |
| GB (1) | GB1597129A (en) |
| IT (1) | IT1088432B (en) |
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| US4504905A (en) * | 1981-09-05 | 1985-03-12 | Lucas Industries Plc | Digital control system including means for maintaining signals supplied thereby within limiting values |
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| US4845617A (en) * | 1987-06-01 | 1989-07-04 | United Technologies Corporation | Autofeather state maintenance |
| US4992946A (en) * | 1988-06-20 | 1991-02-12 | General Electric Company | Data link for gas turbine engine control |
| DE19729101A1 (en) * | 1997-07-08 | 1999-01-14 | Bosch Gmbh Robert | System for operating an internal combustion engine, in particular a motor vehicle |
| US6568166B2 (en) | 2000-12-22 | 2003-05-27 | Pratt & Whitney Canada Corp. | Back-up control apparatus for turbo machine |
| US6687596B2 (en) * | 2001-08-31 | 2004-02-03 | General Electric Company | Diagnostic method and system for turbine engines |
| US7216071B2 (en) * | 2002-04-23 | 2007-05-08 | United Technologies Corporation | Hybrid gas turbine engine state variable model |
| DE102007025447A1 (en) * | 2006-10-09 | 2008-04-17 | Siemens Ag | Method for controlling and / or regulating an industrial process |
| US7630820B2 (en) * | 2007-04-24 | 2009-12-08 | Honeywell International Inc. | Feedback control system and method that selectively utilizes observer estimates |
| DE102008041571B4 (en) | 2008-08-26 | 2019-12-05 | Robert Bosch Gmbh | Method and device for error handling during operation of an internal combustion engine |
| CN111475889B (en) * | 2020-03-30 | 2022-12-06 | 西安交通大学 | Physical and data-driven aeroengine digital twin modeling method |
| CN114508421B (en) * | 2021-12-14 | 2023-05-05 | 泸州懋威科技有限公司 | Microminiature aeroengine control system and operation method thereof |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2851855A (en) * | 1953-03-27 | 1958-09-16 | Curtiss Wright Corp | Fuel control system for jet engines |
| US3851157A (en) * | 1973-07-09 | 1974-11-26 | United Aircraft Corp | Self-correcting feedback control system |
| GB1523275A (en) * | 1974-08-20 | 1978-08-31 | Cav Ltd | Digital control system for a gas turbine engine |
-
1977
- 1977-12-07 GB GB5093277A patent/GB1597129A/en not_active Expired
- 1977-12-09 CA CA000292813A patent/CA1188775A/en not_active Expired
- 1977-12-09 IT IT3056177A patent/IT1088432B/en active
- 1977-12-19 JP JP15165977A patent/JPS5395410A/en active Pending
- 1977-12-20 BE BE183636A patent/BE862071A/en unknown
- 1977-12-20 DE DE19772756681 patent/DE2756681C2/en not_active Expired
- 1977-12-20 FR FR7738477A patent/FR2374513A1/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| IT1088432B (en) | 1985-06-10 |
| BE862071A (en) | 1978-04-14 |
| DE2756681C2 (en) | 1986-06-05 |
| FR2374513A1 (en) | 1978-07-13 |
| GB1597129A (en) | 1981-09-03 |
| DE2756681A1 (en) | 1978-06-22 |
| FR2374513B1 (en) | 1984-10-19 |
| JPS5395410A (en) | 1978-08-21 |
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