Compact aero-thermo model based degraded mode control
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-009/16
G05B-017/02
F02C-007/26
F02C-009/20
G05D-007/06
F01D-021/00
F02C-003/04
F04D-029/32
G05B-013/04
G05B-023/02
출원번호
US-0767818
(2014-03-14)
등록번호
US-10196985
(2019-02-05)
국제출원번호
PCT/US2014/028002
(2014-03-14)
국제공개번호
WO2014/143852
(2014-09-18)
발명자
/ 주소
Karpman, Boris
Meisner, Richard P.
출원인 / 주소
UNITED TECHNOLOGIES CORPORATION
대리인 / 주소
Cantor Colburn LLP
인용정보
피인용 횟수 :
0인용 특허 :
40
초록▼
Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an
Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode. The system may include a control law for directing the actuator as a function of a model output and for determining if the control device is operating with deteriorated conditions. The model processor may further include an estimate state module for determining an estimated state of the model based on a prior state model output and the current state model of an open loop model.
대표청구항▼
1. A control system, comprising: an actuator for positioning a control device comprising a control surface, wherein the actuator positions the control surface;a processing circuit configured to execute a control law, the control law configured to direct the actuator as a function of a model output a
1. A control system, comprising: an actuator for positioning a control device comprising a control surface, wherein the actuator positions the control surface;a processing circuit configured to execute a control law, the control law configured to direct the actuator as a function of a model output and for determining if the control device is operating with deteriorated conditions; anda model processor configured to generate the model output, the model processor comprising: an input object for processing a model input vector and setting a model operating mode;a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode;wherein the open loop model generates current state derivatives, solver state errors, and the synthesized parameters as a function of the dynamic states and the model input vector, a constraint on the current state derivatives and solver state errors being based on a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the control device and comprising a series of utilities, the utilities based on mathematical abstractions of physical laws that govern behavior of the component;an estimate state module configured to determine an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters, wherein the set state module, the series of cycle syntheses modules, and the estimate state module comprise a plurality of non-transitory machine-readable instructions stored in a memory; andan output object for processing at least the synthesized parameters of the model to determine the model output. 2. The control system of claim 1, further comprising system sensors for determining actual cycle measurements for the control device. 3. The control system of claim 2, wherein determining if the control device is operating with deteriorated conditions comprises: comparing the model output to the actual cycle measurements for the control device; and determining if the control device is operating with deteriorated conditions based on discrepancies between the model output and the actual cycle measurements for the control device. 4. The control system of claim 3, wherein the deteriorated conditions include failure of one or more system sensors. 5. The control system of claim 1, wherein the deteriorated conditions include one or more of a passive actuator, a broken actuator, a failed sensor, a drifted sensor, a worn turbomachinery blade, a broken turbomachinery blade, an iced gas path, or volcanic ash ingestion. 6. The control system of claim 1, wherein the model output generated by the model processor includes corrector states, the corrector states used by the control law to determine if the control device is operating with deteriorated conditions. 7. The control system of claim 1, wherein the model input vector includes one or more of raw effector data, boundary conditions, engine sensing data, unit conversion information, range limiting information, rate limiting information, dynamic compensation determinations, and synthesized lacking inputs. 8. The control system of claim 1, wherein the control device is a gas turbine engine. 9. The control system of claim 8, wherein the one or more cycle synthesis modules are based on one or more mathematical abstractions of physical processes associated with components of a thermodynamic cycle of the gas turbine engine. 10. A method for controlling a control device, the method comprising: generating, by a computer processor, a model output using a model processor;processing a model input vector and setting a model operating mode;setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode;generating current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and the model input vector, wherein a constraint on the current state derivatives, solver state errors is based on a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the control device and comprising a series of utilities, the utilities based on mathematical abstractions of physical laws that govern behavior of the component, wherein the series of cycle synthesis modules comprise a plurality of non-transitory machine-readable instructions stored in a memory;determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters; andprocessing at least the synthesized parameters of the model to determine the model output;directing an actuator associated with the control device as a function of a model output using a control law;determining if the control device is operating with deteriorated conditions using the control law; andpositioning the control device comprising a control surface using the actuator, wherein the actuator positions the control surface. 11. The method of claim 10, further comprising determining actual cycle measurements for the control device using system sensors. 12. The method of claim 11, wherein determining if the control device is operating with deteriorated conditions comprises: comparing the model output to the actual cycle measurements for the control device; and determining if the control device is operating with deteriorated conditions based on discrepancies between the model output and the actual cycle measurements for the control device. 13. The method of claim 12, wherein the deteriorated conditions include failure of one or more system sensors. 14. The method of claim 10, wherein the deteriorated conditions include one or more of a passive actuator, a broken actuator, a failed sensor, a drifted sensor, a worn turbomachinery blade, a broken turbomachinery blade, an iced gas path, or volcanic ash ingestion. 15. The method of claim 10, wherein at least one of the utilities is a configurable utility comprising one or more sub-utilities. 16. A gas turbine engine comprising: an actuator for positioning the gas turbine engine comprising a control surface, wherein the actuator positions a control surface of an element of the gas turbine engine;a processing circuit configured to execute a control law, the control law configured to direct the actuator as a function of a model output and for determining if the gas turbine engine is operating with deteriorated conditions;a model processor configured to generate the model output, the model processor comprising:an input object for processing a model input vector and setting a model operating mode;a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode;wherein the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and the model input vector, wherein a constraint on the current state derivatives and solver state errors is based on a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the gas turbine engine and comprising a series of utilities, the utilities based on mathematical abstractions of physical laws that govern behavior of the component;an estimate state module configured to determine an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters, wherein the set state module, the series of cycle synthesis modules, and the estimate state module comprise a plurality of non-transitory machine-readable instructions stored in a memory; andan output object for processing at least the synthesized parameters of the model to determine the model output. 17. The gas turbine engine of claim 1, further comprising system sensors for determining actual cycle measurements for the gas turbine engine. 18. The gas turbine engine of claim 17, wherein determining if the gas turbine engine is operating with deteriorated conditions comprises: comparing the model output to the actual cycle measurements for the gas turbine engine; anddetermining if the gas turbine engine is operating with deteriorated conditions based on discrepancies between the model output and the actual cycle measurements for the gas turbine engine. 19. The gas turbine engine of claim 18, wherein the degraded mode is failure of one or more system sensors. 20. The gas turbine engine of claim 16, wherein the deteriorated conditions include one or more of a passive actuator, a broken actuator, a failed sensor, a drifted sensor, a worn turbomachinery blade, a broken turbomachinery blade, an iced gas path, or volcanic ash ingestion.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (40)
Brunell, Brent Jerome; Mathews, Jr., Harry Kirk; Kumar, Aditya, Adaptive model-based control systems and methods for controlling a gas turbine.
Livshiz, Michael; Kaiser, Jeffrey M.; Whitney, Christopher E.; Hysko, Jr., Gerald J.; White, David A.; Song, B. Jerry, Airflow control systems and methods.
Whitney, Christopher E.; Jin, Ning; Genslak, Robert J.; Chen, Jyh-Shin; Wong, Kevin C., Airflow control systems and methods using model predictive control.
Spang ; III Henry A. (Schenectady NY) Wanger Robert P. (Fairfield OH), Apparatus for sensor failure detection and correction in a gas turbine engine control system.
Karpman, Boris; Meisner, Richard P.; Lacour, Mark E., Design and control of engineering systems utilizing component-level dynamic mathematical model with multiple-input multiple-output estimator.
Karpman, Boris; Meisner, Richard P.; Shade, John L., High fidelity integrated heat transfer and clearance in component-level dynamic turbine system control.
Finnigan,Peter Michael; Srinivas,Mullahalli Venkataramaniah; Albers,Robert Joseph; DeLeonardo,Guy Wayne, Method and system for active tip clearance control in turbines.
Healy, Timothy Andrew; Intile, John Charles; Citeno, Joseph Vincent; Frederick, Garth Curtis, Method and system to determine composition of fuel entering combustor.
Javelot, Christophe; Bonneau, Damien; Gaully, Bruno Robert; Olivier, Amaury, Method for controlling the clearance at the tips of blades of a turbine rotor.
Treinies Stefan,DEX ; Engl Maximilian,DEX ; Rosel Gerd,DEX, Method for determining an air mass flow into cylinders of an internal combustion engine with the aid of a model.
Meisner, Richard P.; Winebrenner, Brian V.; Feulner, Matthew R.; Karpman, Boris; Marcos, Juan A.; Ma, David L., Real time model based compressor control.
Karpman, Boris; Meisner, Richard P.; Lacour, Mark E., System and method for design and control of engineering systems utilizing component-level dynamic mathematical model.
Boris Karpman ; John L. Shade ; Daniel E. Kane, System and method of controlling clearance between turbine engine blades and case based on engine components thermal growth model.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.