Patents by Inventor Sheldon Carpenter
Sheldon Carpenter has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Patent number: 11125169Abstract: A fuel metering system for a combustion section of a turbo machine is provided. The turbo machine includes a main fuel line configured to provide a flow of fuel and a zone fuel line split from the main fuel line through which at least a portion of the flow of fuel is provided. A fuel valve is disposed at the zone fuel line and is configured to obtain and receive a present fuel valve area value and a present valve position value. A first pressure sensor is disposed upstream of the fuel valve, in which the first pressure sensor is configured to obtain a first pressure value. A second pressure sensor is disposed downstream of the fuel valve, in which the second pressure sensor is configured to obtain a second pressure value. A flow meter is disposed downstream of the fuel valve.Type: GrantFiled: December 19, 2018Date of Patent: September 21, 2021Assignee: General Electric CompanyInventors: R. Sheldon Carpenter, Manxue Lu, William James Mailander, David Anthony Moster, Guoxin Li
-
Patent number: 11099238Abstract: A distributed control system having at least a distributed control module is disclosed. The distributed control module may be configured to determine a fault state associated with a control loop using a built-in test module. The built-in test module may be incorporated into the distributed control module. The fault state may include no faults, a communication fault, a sensor operation fault, or a controllable component fault. The distributed control module may be configured to transmit a closed-loop control command from the distributed control module to a controllable component when the fault state comprises no faults, or transmit an augmented control command from the distributed control module to the controllable component when the fault state comprises a communication fault or a sensor operation fault, or transmit a disconnect control command from the distributed control module to a controllable component when the fault state comprises a controllable component fault.Type: GrantFiled: March 27, 2019Date of Patent: August 24, 2021Assignee: General Electric CompanyInventors: Manxue Lu, R. Sheldon Carpenter, John Lawrence DeJager
-
Publication number: 20200309852Abstract: A distributed control system may include a main processing unit, a distributed control module, and a controllable component. The distributed control module may be configured to determine a fault state associated with a control loop using a built-in test module. The built-in test module may be incorporated into the distributed control module. The fault state may include no faults, a communication fault, a sensor operation fault, or a controllable component fault. The distributed control module may be configured to transmit a closed-loop control command from the distributed control module to a controllable component when the fault state comprises no faults, or transmit an augmented control command from the distributed control module to the controllable component when the fault state comprises a communication fault or a sensor operation fault, or transmit a disconnect control command from the distributed control module to the controllable component when the fault state comprises a controllable component fault.Type: ApplicationFiled: March 27, 2019Publication date: October 1, 2020Inventors: Manxue Lu, R. Sheldon Carpenter, John Lawrence DeJager
-
Publication number: 20200200098Abstract: A fuel metering system for a combustion section of a turbo machine is provided. The turbo machine includes a main fuel line configured to provide a flow of fuel and a zone fuel line split from the main fuel line through which at least a portion of the flow of fuel is provided. A fuel valve is disposed at the zone fuel line and is configured to obtain and receive a present fuel valve area value and a present valve position value. A first pressure sensor is disposed upstream of the fuel valve, in which the first pressure sensor is configured to obtain a first pressure value. A second pressure sensor is disposed downstream of the fuel valve, in which the second pressure sensor is configured to obtain a second pressure value. A flow meter is disposed downstream of the fuel valve.Type: ApplicationFiled: December 19, 2018Publication date: June 25, 2020Inventors: R. Sheldon Carpenter, Manxue Lu, William James Mailander, David Anthony Moster, Guoxin Li
-
Patent number: 10025301Abstract: A method and system for controlling a plant having a plurality of actuators, a plurality of inputs corresponding to the operational state of the actuators and plurality of outputs corresponding to an operating condition of the plant according to a model-based control and a plant model. The plant model is on-line reconfigured and the model-based control is built such that the model-based control adapts to the reconfigured plant model.Type: GrantFiled: July 31, 2015Date of Patent: July 17, 2018Assignee: General Electric CompanyInventors: Manxue Lu, R. Sheldon Carpenter
-
Patent number: 9880527Abstract: A method of tracking variable states of a gas turbine engine in transient conditions includes obtaining input data representative of rotor velocity and pressure ratio; calculating a reference transient scheduled trajectory based on the input data; calculating a speed reference transient scheduled trajectory based on the input data; calculating a feedforward variable based on the reference transient scheduled trajectory; obtaining a feedback control variable; and determining a control variable based on a combination of the feedforward variable and the feedback control variable.Type: GrantFiled: June 25, 2015Date of Patent: January 30, 2018Assignee: General Electric CompanyInventors: Guoxin Li, R. Sheldon Carpenter
-
Patent number: 9845145Abstract: A method and control system for an aircraft engine comprising a gas turbine driving a fan propeller with a mechanical gear-train and a dedicated pitch change mechanism for the fan propeller includes a fuel flow signal input; a pitch change mechanism signal input; a controlled plant for relating a pitch change mechanism pitch angle (BetaP) and a fuel flow (Wf) to at least two controlled outputs and a set of constraints. A decoupling control decoupling the controlled plant and/or the constraints into two separate single-input single-output (SISO) control loops for the first and second controlled outputs and a decoupling control decoupling the constraints from the decoupled controlled outputs and the constraints from one another provide gas turbine and fan propeller coordinate control while coordinately controlling constraints and outputs. A feedforward control can compensate the load change effect on engine speed and fan propeller rotor speed control.Type: GrantFiled: August 20, 2015Date of Patent: December 19, 2017Assignee: General Electric CompanyInventors: Manxue Lu, R. Sheldon Carpenter
-
Patent number: 9388744Abstract: In one embodiment, a gas turbine engine control system includes an engine controller configured to control multiple parameters associated with operation of a gas turbine engine system. The gas turbine engine control system also includes multiple remote interface units communicatively coupled to the engine controller. The remote interface unit is configured to receive an input signal from the engine controller indicative of respective target values of at least one parameter, and the remote interface unit is configured to provide closed-loop control of the at least one parameter based on the input signal and feedback signals indicative of respective measured values of the at least one parameter.Type: GrantFiled: March 30, 2012Date of Patent: July 12, 2016Assignee: General Electric CompanyInventors: Harry Kirk Mathews, Jr., Brent Jerome Brunell, Simon Shlomo Lis, R. Sheldon Carpenter, Samhita Dasgupta, Sridhar Adibhatla, Scott Douglas Waun, Emad Andarawis Andarawis
-
Publication number: 20160159461Abstract: A method and control system for an aircraft engine comprising a gas turbine driving a fan propeller with a mechanical gear-train and a dedicated pitch change mechanism for the fan propeller includes a fuel flow signal input; a pitch change mechanism signal input; a controlled plant for relating a pitch change mechanism pitch angle (BetaP) and a fuel flow (Wf) to at least two controlled outputs and a set of constraints. A decoupling control decoupling the controlled plant and/or the constraints into two separate single-input single-output (SISO) control loops for the first and second controlled outputs and a decoupling control decoupling the constraints from the decoupled controlled outputs and the constraints from one another provide gas turbine and fan propeller coordinate control while coordinately controlling constraints and outputs. A feedforward control can compensate the load change effect on engine speed and fan propeller rotor speed control.Type: ApplicationFiled: August 20, 2015Publication date: June 9, 2016Inventors: Manxue LU, R. Sheldon CARPENTER
-
Publication number: 20160062353Abstract: A method and system for controlling a plant having a plurality of actuators, a plurality of inputs corresponding to the operational state of the actuators and plurality of outputs corresponding to an operating condition of the plant according to a model-based control and a plant model. The plant model is on-line reconfigured and the model-based control is built such that the model-based control adapts to the reconfigured plant model.Type: ApplicationFiled: July 31, 2015Publication date: March 3, 2016Inventors: Manxue LU, R. Sheldon CARPENTER
-
Publication number: 20150378327Abstract: A method of tracking variable states of a gas turbine engine in transient conditions includes obtaining input data representative of rotor velocity and pressure ratio; calculating a reference transient scheduled trajectory based on the input data; calculating a speed reference transient scheduled trajectory based on the input data; calculating a feedforward variable based on the reference transient scheduled trajectory; obtaining a feedback control variable; and determining a control variable based on a combination of the feedforward variable and the feedback control variable.Type: ApplicationFiled: June 25, 2015Publication date: December 31, 2015Inventors: Guoxin Li, R. Sheldon Carpenter
-
Patent number: 9081378Abstract: A method and apparatus for multiple variable control of a physical plant with high dimension multiple constraints, includes: mathematically decoupling primary controlled outputs of a controlled physical plant from one another and shaping the pseudo inputs/controlled outputs desired plant dynamics; tracking primary control references and providing pseudo inputs generated by desired primary output tracking for selection; mathematically decoupling constraints from one another; mathematically decoupling constraints from non-traded off primary controlled outputs of the controlled physical plant; shaping the pseudo inputs/constraint outputs desired plant dynamics; tracking constraint control limits; providing pseudo inputs generated by desired constraint output tracking for selection; selecting the most limiting constraints and providing the smooth pseudo inputs for the decoupled primary control; and controlling the physical plant using the decoupled non-traded off primary controlled outputs and the decoupled selecType: GrantFiled: October 25, 2012Date of Patent: July 14, 2015Assignee: General Electric CompanyInventors: Manxue Lu, Sheldon Carpenter
-
Patent number: 8689539Abstract: Simple, robust and systematic solutions are provided for controlling counter-rotating open-rotor (CROR) gas turbine engines. The solutions mathematically decouple the two counter rotating rotors of a CROR engine by model-based dynamic inversion, which allows application of single-input-single-output (SISO) control concepts. The current solutions allow fuel flow to be treated as a known disturbance and rejected from the rotor speeds control. Furthermore, the current control solutions allow a simple and well-coordinated speed phase synchronizing among the four rotors on a two-engine vehicle.Type: GrantFiled: October 11, 2012Date of Patent: April 8, 2014Assignee: General Electric CompanyInventors: Manxue Lu, Sheldon Carpenter
-
Publication number: 20130269363Abstract: Simple, robust and systematic solutions are provided for controlling counter-rotating open-rotor (CROR) gas turbine engines. The solutions mathematically decouple the two counter rotating rotors of a CROR engine by model-based dynamic inversion, which allows application of single-input-single-output (SISO) control concepts. The current solutions allow fuel flow to be treated as a known disturbance and rejected from the rotor speeds control. Furthermore, the current control solutions allow a simple and well-coordinated speed phase synchronizing among the four rotors on a two-engine vehicle.Type: ApplicationFiled: October 11, 2012Publication date: October 17, 2013Inventors: Manxue Lu, Sheldon Carpenter
-
Publication number: 20130255220Abstract: In one embodiment, a gas turbine engine control system includes an engine controller configured to control multiple parameters associated with operation of a gas turbine engine system. The gas turbine engine control system also includes multiple remote interface units communicatively coupled to the engine controller. The remote interface unit is configured to receive an input signal from the engine controller indicative of respective target values of at least one parameter, and the remote interface unit is configured to provide closed-loop control of the at least one parameter based on the input signal and feedback signals indicative of respective measured values of the at least one parameter.Type: ApplicationFiled: March 30, 2012Publication date: October 3, 2013Applicant: General Electric CompanyInventors: Harry Kirk Mathews, JR., Brent Jerome Brunell, Simon Shlomo Lis, R. Sheldon Carpenter, Samhita Dasgupta, Sridhar Adibhatla, Scott Douglas Waun, Emad Andarawis Andarawis
-
Patent number: 5197280Abstract: A control system for a gas turbine engine receives a signal representative of a first target engine operating condition and also receives a signal representative of an actual engine condition. The system produces an error signal representative of the difference between the target signal and the actual engine condition signal. A gain means adjusts the gain of the error signal to be equal to the desired change in the controlled engine parameter. The output of the gain means is then coupled to an activator of the engine which controls the parameter.Type: GrantFiled: October 29, 1990Date of Patent: March 30, 1993Assignee: General Electric CompanyInventors: R. Sheldon Carpenter, William L. Gazzola