Patent US2334474A successfully refreshed from Google Patents.
US4425614A
Expired / Lapsed
US
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Self-organizing control system
Assignee: Adaptronics Inc
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Filing: 1973-07-20
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Granted: 1984-01-10
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Expires: 1993-07-20
Abstract
Abstract The disclosure relates to a self-organizing control of advanced turbine engines wherein thrust is controlled and thrust specific fuel consumption (TSFC) is minimized by control of the fuel flow rate as well as optimization of system geometric parameters. The controller computes the net thrust error by comparing commanded thrust with an inferred or calculated thrust measurement.
Inventors
- 👤 Roger L. Barron
- 👤 Dixon Cleveland
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 10:46
CPC Classifications
G; G05; G05B; G05B13/00; G05B13/02; F; F02; F02C; F02C9/00; F02C9/26; F02C9/28; G06; G06G; G06G7/00; G06G7/48; G06G7/78
Claims Analysis
Total Claims: 43
Claim 1
Independent Claim
165 words
A system for on-line control of deviation between system commanded thrust and system calculated thrust of an engine having plural variable and measurable parameters, which comprises: (1) command means for providing a commanded thrust signal, (2) calculation means responsive to on-line measured engine parameters to calculate engine thrust, (3) error means responsive to signals from said command and calculation means to provide an error signal indicative of the difference between the commanded and calculated thrust signals, and (4) controller means responsive to said error signal which includes integration means for generating a signal representing an integral of said error signal, differentiation means for generating a signal representing a derivative of said error signal, scaling means for generating a signal proportional to said error signal, and summing means for summing said integral, derivative and proportional signals, where the output of said summing means provides control of a predetermined one of said engine parameters, further including integration limit means for limiting the output of said integration means.
Claim 2
Independent Claim
165 words
A system for on-line control of deviation between system commanded thrust and system calculated thrust of an engine having plural variable and measurable parameters, which comprises: (1) command means for providing a commanded thrust signal, (2) calculation means responsive to on-line measured engine parameters to calculate engine thrust, (3) error means responsive to signals from said command and calculation means to provide an error signal indicative of the difference between the commanded and calculated thrust signals, and (4) controller means responsive to said error signal which includes integration means for generating a signal representing an integral of said error signal, differentiation means for generating a signal representing a derivative of said error signal, scaling means for generating a signal proportional to said error signal, and summing means for summing said integral, derivative and proportional signals, where the output of said summing means provides control of a predetermined one of said engine parameters, further including integration limit means for limiting the output of said integration means.
Claim 3
Dependent Claim
22 words
A system as set forth in claim 1 further including means responsive to on-line measured engine parameters for controlling said integration limits.
Claim 4
Dependent Claim
28 words
A system as set forth in claim 2 further including means responsive to on-line measured engine parameters for controlling the limits of the output of said summing means.
Claim 5
Dependent Claim
36 words
A system as set forth in claim 1 further including integration means responsive to on-line measured engine parameters to control at least one of variable turbine inlet area and variable exhaust nozzle area of said engine.
Claim 6
Dependent Claim
26 words
A system as set forth in claim 4 wherein said integration means is responsive to on-line measured fuel flow, engine rotational speed and calculated engine thrust.
Claim 7
Dependent Claim
18 words
A system as set forth in claim 4 wherein said integration means controls said variable turbine inlet area.
Claim 8
Dependent Claim
18 words
A system as set forth in claim 4 wherein said integration means controls said variable exhaust nozzle area.
Claim 9
Dependent Claim
36 words
A system as set forth in claim 1 further including integration means responsive to on-line measured engine parameters to control at least one of variable turbine inlet area and variable exhaust nozzle area of said engine.
Claim 10
Dependent Claim
26 words
A system as set forth in claim 8 wherein said integration means is responsive to on-line measured fuel flow, engine rotational speed and calculated engine thrust.
Claim 11
Dependent Claim
18 words
A system as set forth in claim 8 wherein said integration means controls said variable turbine inlet area.
Claim 12
Dependent Claim
18 words
A system as set forth in claim 8 wherein said integration means controls said variable exhaust nozzle area.
Claim 13
Independent Claim
165 words
A system for on-line control of deviation between system commanded thrust and system calculated thrust of an engine having plural variable and measurable parameters, which comprises: (1) command means for providing a commanded thrust signal, (2) calculation means responsive to on-line measured engine parameters to calculate engine thrust, (3) error means responsive to signals from said command and calculation means to provide an error signal indicative of the difference between the commanded and calculated thrust signals, and (4) controller means responsive to said error signal which includes integration means for generating a signal representing an integral of said error signal, differentiation means for generating a signal scaling means for generating a signal proportional to said error signal, representing a derivative of said error signal, and summing means for summing said integral, derivative and proportional signals, where the output of said summing means provides control of a predetermined one of said engine parameters, further including summing limit means for limiting the output of said summing means.
Claim 14
Independent Claim
165 words
A system for on-line control of deviation between system commanded thrust and system calculated thrust of an engine having plural variable and measurable parameters, which comprises: (1) command means for providing a commanded thrust signal, (2) calculation means responsive to on-line measured engine parameters to calculate engine thrust, (3) error means responsive to signals from said command and calculation means to provide an error signal indicative of the difference between the commanded and calculated thrust signals, and (4) controller means responsive to said error signal which includes integration means for generating a signal representing an integral of said error signal, differentiation means for generating a signal scaling means for generating a signal proportional to said error signal, representing a derivative of said error signal, and summing means for summing said integral, derivative and proportional signals, where the output of said summing means provides control of a predetermined one of said engine parameters, further including summing limit means for limiting the output of said summing means.
Claim 15
Dependent Claim
22 words
A system as set forth in claim 12 further including means responsive to on-line measured engine parameters for controlling said summing limits.
Claim 16
Independent Claim
117 words
A system for on-line control of deviation between system commanded thrust and system calculated thrust of an engine having plural variable and measurable parameters including variable turbine inlet area, variable exhaust nozzle area and variable fuel flow rate which comprises: (1) command means for providing a commanded thrust signal, (2) calculation means responsive to on-line measured engine parameters to calculate engine thrust, (3) error means responsive to the signal from said command means and a function of the signal from said calculating means to provide an error signal indicative of the difference between said signal and said function of said signal, and (4) controller means responsive to said error signal to control said variable turbine inlet area.
Claim 17
Independent Claim
117 words
A system for on-line control of deviation between system commanded thrust and system calculated thrust of an engine having plural variable and measurable parameters including variable turbine inlet area, variable exhaust nozzle area and variable fuel flow rate which comprises: (1) command means for providing a commanded thrust signal, (2) calculation means responsive to on-line measured engine parameters to calculate engine thrust, (3) error means responsive to the signal from said command means and a function of the signal from said calculating means to provide an error signal indicative of the difference between said signal and said function of said signal, and (4) controller means responsive to said error signal to control said variable turbine inlet area.
Claim 18
Dependent Claim
26 words
A system as set forth in claim 14 further including nozzle area control means responsive to said error signal to control the variable exhaust nozzle area.
Claim 19
Dependent Claim
51 words
A system as set forth in claim 15 further including error means responsive to the signal from said command means and the signal from said calculation means to provide a second error signal and fuel flow rate control means responsive to said second error signal to control the variable flow rate.
Claim 20
Dependent Claim
57 words
A system as set forth in claim 16 further including optimization means responsive simultaneously to engine fuel flow rate, commanded engine thrust and calculated on-line engine thrust to determine substantially optimum values for exhaust nozzle area and turbine inlet nozzle area to minimize thrust specific fuel consumption for controlling said controller means and nozzle area control means.
Claim 21
Dependent Claim
19 words
A system as set forth in claim 17 wherein said optimization means is further responsive to engine rotary speed.
Claim 22
Dependent Claim
20 words
A system as set forth in claim 18 wherein said optimization means further affects said fuel flow rate control means.
Claim 23
Dependent Claim
19 words
A system as set forth in claim 17 wherein said optimization means further affects fuel flow rate control means.
Claim 24
Dependent Claim
51 words
A system as set forth in claim 14 further including error means responsive to the signal from said command means and the signal from said calculation means to provide a second error signal and fuel flow rate control means responsive to said second error signal to control the variable flow rate.
Claim 25
Dependent Claim
52 words
A system as set forth in claim 21 further including optimization means responsive simultaneously to engine fuel flow rate, commanded engine thrust and calculated on-line engine thrust to determine substantially optimum values for exhaust nozzle area and turbine inlet nozzle area to minimize thrust specific fuel consumption for controlling said controller means.
Claim 26
Dependent Claim
19 words
A system as set forth in claim 22 wherein said optimization means is further responsive to engine rotary speed.
Claim 27
Dependent Claim
19 words
A system as set forth in claim 23 wherein said optimization means affects said fuel flow rate control means.
Claim 28
Dependent Claim
20 words
A system as set forth in claim 22 wherein said optimization means further affects said fuel flow rate control means.
Claim 29
Independent Claim
117 words
A system for on-line control of deviation between system commanded thrust and system calculated thrust of an engine having plural variable and measurable parameters including variable turbine inlet areas, variable exhaust nozzle area and variable fuel flow rate which comprises: (1) command means for providing a command thrust signal, (2) calculation means responsive to on-line measured engine parameters to calculate engine thrust, (3) error means responsive to the signals from said command means and a function of the signal from said calculation means to provide an error signal indicative of the difference between said signal and said function of said signal, and (4) control means responsive to said error signal to control said variable exhaust nozzle area.
Claim 30
Independent Claim
117 words
A system for on-line control of deviation between system commanded thrust and system calculated thrust of an engine having plural variable and measurable parameters including variable turbine inlet areas, variable exhaust nozzle area and variable fuel flow rate which comprises: (1) command means for providing a command thrust signal, (2) calculation means responsive to on-line measured engine parameters to calculate engine thrust, (3) error means responsive to the signals from said command means and a function of the signal from said calculation means to provide an error signal indicative of the difference between said signal and said function of said signal, and (4) control means responsive to said error signal to control said variable exhaust nozzle area.
Claim 31
Dependent Claim
51 words
A system as set forth in claim 26 further including error means responsive to the signal from said command means and the signal from said calculation means to provide a second error signal and fuel flow rate control means responsive to said second error signal to control the variable flow rate.
Claim 32
Dependent Claim
52 words
A system as set forth in claim 27 further including computing means responsive simultaneously to engine fuel flow rate, commanded engine thrust and calculated on-line engine thrust to determine substantially optimum values for exhaust nozzle area and turbine inlet nozzle area to minimize thrust specific fuel consumption for controlling said control means.
Claim 33
Dependent Claim
19 words
A system as set forth in claim 28 wherein said computing means is further responsive to engine rotary speed.
Claim 34
Dependent Claim
89 words
In a self-organizing control system for a turbine type of power plant having a compressor and variable area mechanisms, said system having performance assessment means responsive to power plant operating parameters for assessing the performance of said power plant, correlation logic means responsive to the performance assessment means for adjusting the performance by varying said variable area mechanism in a phase relationship, said performance assessment means including the rate of change of said compressor so that the performance assessment is made during a transient condition of the power plant.
Claim 35
Dependent Claim
89 words
In a self-organizing control system for a turbine type of power plant having a compressor and variable area mechanisms, said system having performance assessment means responsive to power plant operating parameters for assessing the performance of said power plant, correlation logic means responsive to the performance assessment means for adjusting the performance by varying said variable area mechanism in a phase relationship, said performance assessment means including the rate of change of said compressor so that the performance assessment is made during a transient condition of the power plant.
Claim 36
Dependent Claim
102 words
A fuel control for a turbine type of power plant having a compressor and variable area geometry, in combination with a self-organizing control having means for assessing the performance of said power plant, fuel metering means having its independent control, means for ascertaining the net thrust of said power plant, said self-organizing control including power assessment means responsive to said fuel metering means, said net thrust ascertaining means and the rate of change of the speed of said compressor wherein said rate of change of the speed of said compressor serves to speed up the response time of said power assessment means.
Claim 37
Dependent Claim
102 words
A fuel control for a turbine type of power plant having a compressor and variable area geometry, in combination with a self-organizing control having means for assessing the performance of said power plant, fuel metering means having its independent control, means for ascertaining the net thrust of said power plant, said self-organizing control including power assessment means responsive to said fuel metering means, said net thrust ascertaining means and the rate of change of the speed of said compressor wherein said rate of change of the speed of said compressor serves to speed up the response time of said power assessment means.
Claim 38
Dependent Claim
61 words
A self-organizing control as claimed in claim 31 including a correlation logic unit responsive to said performance assessment means for determining the phase relationship of the signal generated by said performance assessment means and means establishing the time interval of said correlation logic unit for performing experiments on the performance of said power plant by perturbations of said variable area geometry.
Claim 39
Dependent Claim
120 words
A fuel control for a turbine type of power plant having a compressor, a burner, a turbine receiving the exhaust gases of said burner for driving the compressor, and having variable geometry where area varies, a source of fuel, means including a fuel metering means for metering fuel from said source to said burner, means responsive to a plurality of engine operating parameters for calculating an inferred thrust for any given engine operation, means for establishing a desired thrust, means responsive to the calculated inferred thrust and the desired thrust for controlling said fuel metering means, and a self-organizing control system responsive to a plurality of engine operating conditions for adjusting said variable geometry to obtain optimum specific fuel consumption.
Claim 40
Dependent Claim
120 words
A fuel control for a turbine type of power plant having a compressor, a burner, a turbine receiving the exhaust gases of said burner for driving the compressor, and having variable geometry where area varies, a source of fuel, means including a fuel metering means for metering fuel from said source to said burner, means responsive to a plurality of engine operating parameters for calculating an inferred thrust for any given engine operation, means for establishing a desired thrust, means responsive to the calculated inferred thrust and the desired thrust for controlling said fuel metering means, and a self-organizing control system responsive to a plurality of engine operating conditions for adjusting said variable geometry to obtain optimum specific fuel consumption.
Claim 41
Dependent Claim
26 words
A fuel control as claimed in claim 33 wherein said means for calculating an inferred thrust is responsive to turbine inlet pressure and turbine discharge pressure.
Claim 42
Dependent Claim
23 words
A fuel control as claimed in claim 34 wherein said means for calculating also is responsive to the area of the variable geometry.
Claim 43
Dependent Claim
26 words
A fuel control as claimed in claim 33 wherein said self-organizing control is responsive to the metered fuel flow, the net engine thrust and compressor speed.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-01-09 | 1987-07-11 | 1988-01-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-01-09 | 1991-07-11 | 1992-01-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-01-09 | 1995-07-11 | 1996-01-10 | $7700.00 | Window Closed / Lapsed |