Patents by Inventor Marko Bacic

Marko Bacic 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).

  • Publication number: 20210103297
    Abstract: A method of determining a flight trajectory of a vertical take-off aircraft (10) having vectorable propulsion (30, 32). The method comprises: receiving one or more aircraft flight constraints; inputting the aircraft flight constraints to a trajectory planning algorithm to determine a minimum energy aircraft transition trajectory; and outputting a control schedule to fly the aircraft (10) to the flight trajectory.
    Type: Application
    Filed: June 22, 2020
    Publication date: April 8, 2021
    Inventors: David FILLINGHAM, Marko BACIC
  • Publication number: 20210062732
    Abstract: A method of controlling a gas turbine engine including receiving an instantaneous thrust demand for current operation of the engine, determining the inlet flow rate and/or the pressure ratio within the compressor of the engine and determining whether the inlet flow rate and/or the pressure ratio match the working line for the compressor. The angle of one or more vane of the compressor is adjusted according to a closed control loop if the inlet flow rate and/or pressure ratio lie outside said desired range in order to adjust the inlet inflow rate and/or pressure ratio to meet the working line. The fuel flow to the engine combustor is adjusted concurrently in order to meet the thrust demand.
    Type: Application
    Filed: July 31, 2020
    Publication date: March 4, 2021
    Applicant: ROLLS-ROYCE plc
    Inventors: Cerith DAVIES, Marko BACIC
  • Patent number: 10926882
    Abstract: A control system for use in controlling a cabin blower system. The cabin blower system includes a gas turbine engine spool, a cabin blower compressor powered by the spool and arranged in use to compress fluid used in a cabin of an aircraft, and one or more control mechanisms via which the control system controls the power extracted by the cabin blower compressor from the spool. The control system is arranged in use to control the power extracted from the spool by the cabin blower compressor in accordance with one or more primary control parameters. The control system is arranged in use to alter the spool power extracted by the cabin blower compressor by comparison with the power that would have been extracted in accordance with the primary control parameters alone, in response to modifications in a secondary control parameter indicative of the commencement or occurrence of an engine transient.
    Type: Grant
    Filed: September 14, 2017
    Date of Patent: February 23, 2021
    Assignee: ROLLS-ROYCE PLC
    Inventors: Marko Bacic, Benjamin J. Sellers, Rory D. Stieger
  • Patent number: 10890083
    Abstract: A method of controlling turbine tip clearance includes measuring turbine speed; measuring turbine temperature; measuring parameters indicative of current operating conditions; determining limits for the turbine speed and turbine temperature; calculating target tip clearance from the turbine speed, turbine temperature and parameters, to optimise turbine efficiency within the turbine speed and turbine temperature limits; and controlling turbine tip clearance apparatus to the calculated target tip clearance.
    Type: Grant
    Filed: April 20, 2016
    Date of Patent: January 12, 2021
    Assignee: ROLLS-ROYCE plc
    Inventors: Arthur Laurence Rowe, Marko Bacic
  • Publication number: 20200149480
    Abstract: A method of actively controlling torsional resonance of a rotating shaft of an engine is provided. The shaft has a rotational velocity characterised by a low frequency, rotational velocity term and a high frequency, oscillatory term superimposed on the low frequency term, the oscillatory term being caused by torsional resonance. The method including: measuring the rotational velocity of the shaft; extracting the oscillatory term from the measured rotational velocity; and on the basis of the extracted oscillatory term, applying a torque component to the shaft, the torque component being modulated at the same frequency as the torsional resonance to counteract the torsional resonance.
    Type: Application
    Filed: October 10, 2019
    Publication date: May 14, 2020
    Applicant: ROLLS-ROYCE plc
    Inventor: Marko BACIC
  • Patent number: 10611466
    Abstract: A fluidic device for providing analogue output control includes a main channel, a first control channel, a second control channel, a comparator which receives respective input fluid flows from the main, the first and the second control channels. The first control channel is configured such that the input fluid flow therefrom carries an oscillating pressure wave signal, the second control channel includes a flow regulator controllable to vary the mass flow rate of the input fluid flow from the second control channel, and the main channel is configured such that the input fluid flow therefrom is at a reference mass flow rate. The comparator is configured such that the input fluid flows from the first control and the second control channels act in combination on the input fluid flow from the main channel to produce an output fluid flow from the comparator having a PWM mass flow rate characteristic.
    Type: Grant
    Filed: July 18, 2018
    Date of Patent: April 7, 2020
    Assignee: Rolls-Royce plc
    Inventors: Pawel Chmielarczyk, Richard A. Young, Marko Bacic
  • Patent number: 10605107
    Abstract: A gas turbine engine is disclosed having a tip clearance control system. The tip clearance control system has a cabin blower system, a casing arranged in use about a rotor of a gas turbine engine and a fluid delivery passage. The cabin blower system having a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and to compress fluid conducted via the fluid delivery passage into heat exchange with the casing.
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: March 31, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Marko Bacic, Glenn A Knight
  • Publication number: 20200023963
    Abstract: An aircraft defining longitudinal, lateral and vertical directions the aircraft comprising: a main wing and a tail, each being pivotable about the lateral direction (B); a plurality of main propellers mounted to the main wing, and configured to pivot with the main wing; at least one cruise propeller mounted to the tail, and configured to pivot with the tail; each main propeller being stowable from a deployed position to a stowed position; wherein each main propeller has a fixed pitch, and each cruise propeller has a variable pitch.
    Type: Application
    Filed: June 25, 2019
    Publication date: January 23, 2020
    Applicant: ROLLS-ROYCE plc
    Inventors: Darren JAMES, Anmol A. MANOHAR, David FILLINGHAM, Marko BACIC
  • Publication number: 20190345837
    Abstract: The present disclosure concerns control a hybrid electric gas turbine system (300) for an aircraft. The system comprises an electric generator (308) and a gas turbine (309) to form a generator system, an electric motor (303) and a fan (302) to form a propulsor (301), a controller (306) and an electric storage unit (307). After receiving a command for a change in demand for thrust, the controller (306) determines an operational profile that minimises a function comprising a measure of fuel supplied to the gas turbine (309), a transfer of electric power from or to the electric storage unit (307) and a difference between measures of current and demanded thrust over a time period. The controller then operates the electric motor (303), gas turbine (309) and electric storage unit (307) according to the determined operational profile over the time period.
    Type: Application
    Filed: April 23, 2019
    Publication date: November 14, 2019
    Applicant: ROLLS-ROYCE plc
    Inventor: Marko BACIC
  • Publication number: 20190031321
    Abstract: A fluidic device for providing analogue output control includes a main channel, a first control channel, a second control channel, a comparator which receives respective input fluid flows from the main, the first and the second control channels. The first control channel is configured such that the input fluid flow therefrom carries an oscillating pressure wave signal, the second control channel includes a flow regulator controllable to vary the mass flow rate of the input fluid flow from the second control channel, and the main channel is configured such that the input fluid flow therefrom is at a reference mass flow rate. The comparator is configured such that the input fluid flows from the first control and the second control channels act in combination on the input fluid flow from the main channel to produce an output fluid flow from the comparator having a PWM mass flow rate characteristic.
    Type: Application
    Filed: July 18, 2018
    Publication date: January 31, 2019
    Applicant: ROLLS-ROYCE plc
    Inventors: Pawel CHMIELARCZYK, Richard A. YOUNG, Marko BACIC
  • Patent number: 10184348
    Abstract: A system and method are provided for controlling turbine blade tip-to-static structure clearance in a gas turbine engine installed on an aircraft. Mode control data are processed to determine that a fuel-saving mode is enabled, and aircraft data are processed to determine that the aircraft gas turbine engine is generating a substantially constant thrust. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is minimized upon determining that both the aircraft gas turbine engine is generating a substantially constant thrust and the fuel-saving mode is enabled. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is then selectively increased to a predetermined clearance, and a change in aircraft gas turbine engine thrust is prevented until the predetermined clearance is achieved.
    Type: Grant
    Filed: December 5, 2013
    Date of Patent: January 22, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Gregory C. Carlucci, Glenn Alexander Knight, Jim Rumbo, Dennis D Loots, Roger Peckham, Marko Bacic, James Kenneth Haberstock
  • Patent number: 9988924
    Abstract: A gas turbine engine comprising first and second axially spaced turbine rotor stages (46, 48) and a turbine casing (56) radially outside the rotor stages. A first seal segment arrangement (58) forms a cavity (64) radially between the first turbine rotor stage (46) and the turbine casing (56). A first air source (82) is coupled to the first seal segment arrangement (58). A second seal segment arrangement (70) forms a cavity (74) radially between the second turbine rotor stage (48) and the turbine casing (56). A heating chamber (84) is provided radially between the second seal segment arrangement (70) and the turbine casing (56). A duct (86) is coupled between the first air source (82) and the heating chamber (84).
    Type: Grant
    Filed: November 26, 2014
    Date of Patent: June 5, 2018
    Assignee: ROLLS-ROYCE PLC
    Inventors: Marko Bacic, Leo Vivian Lewis, Robert John Irving
  • Publication number: 20180079510
    Abstract: A control system for use in controlling a cabin blower system. The cabin blower system includes a gas turbine engine spool, a cabin blower compressor powered by the spool and arranged in use to compress fluid used in a cabin of an aircraft, and one or more control mechanisms via which the control system controls the power extracted by the cabin blower compressor from the spool. The control system is arranged in use to control the power extracted from the spool by the cabin blower compressor in accordance with one or more primary control parameters. The control system is arranged in use to alter the spool power extracted by the cabin blower compressor by comparison with the power that would have been extracted in accordance with the primary control parameters alone, in response to modifications in a secondary control parameter indicative of the commencement or occurrence of an engine transient.
    Type: Application
    Filed: September 14, 2017
    Publication date: March 22, 2018
    Applicant: ROLLS-ROYCE plc
    Inventors: Marko BACIC, Benjamin J. SELLERS, Rory D. STIEGER
  • Publication number: 20180066588
    Abstract: A fuel flow system comprising a fuel manifold and a fuel nozzle. A fluidic valve having an inlet, a first outlet and a control flow inlet. The inlet is coupled to the fuel manifold. The first outlet is coupled to the fuel nozzle. The control flow inlet is coupled to a source of control fuel. The fluidic valve is configured to selectively couple the inlet to the first outlet dependent on the control flow into the control flow inlet.
    Type: Application
    Filed: August 22, 2017
    Publication date: March 8, 2018
    Applicant: ROLLS-ROYCE plc
    Inventors: James H. DALY, Marko BACIC
  • Publication number: 20170370242
    Abstract: A gas turbine engine is disclosed having a tip clearance control system. The tip clearance control system has a cabin blower system, a casing arranged in use about a rotor of a gas turbine engine and a fluid delivery passage. The cabin blower system having a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and to compress fluid conducted via the fluid delivery passage into heat exchange with the casing.
    Type: Application
    Filed: June 12, 2017
    Publication date: December 28, 2017
    Applicant: ROLLS-ROYCE PLC
    Inventors: Marko BACIC, Glenn A KNIGHT
  • Patent number: 9828869
    Abstract: A thrust demand signal is provided to a processor of a gas turbine engine and is modified, according to growth time constants of a rotor and/or a casing of the engine, in order to control the rotational speed or the rate of change of rotational speed of the engine so as to prevent contact between the rotor and the casing.
    Type: Grant
    Filed: November 10, 2014
    Date of Patent: November 28, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Marko Bacic, Glenn Alexander Knight, Parag Vyas, Sean Patrick Ellis
  • Patent number: 9719365
    Abstract: A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energize the first and second plasma generators at an energizing frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.
    Type: Grant
    Filed: September 19, 2013
    Date of Patent: August 1, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Marko Bacic, Timothy John Scanlon, Ronald William Daniel
  • Patent number: 9689400
    Abstract: A fluidic actuator comprising: a fluid nozzle for delivering fluid and a tube having an open end and a closed end, the open end spaced from the fluid nozzle. Also a pair of electrodes mounted in the tube and spaced apart to create a spark gap therebetween. A voltage source is arranged to supply a voltage across the pair of electrodes wherein the voltage causes plasma formation in the spark gap thereby shortening the effective length of the tube.
    Type: Grant
    Filed: September 19, 2013
    Date of Patent: June 27, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Marko Bacic, Ronald William Daniel
  • Patent number: 9657587
    Abstract: A method of controlling a rotor tip clearance arrangement of a gas turbine engine and a control system configured to control rotor tip clearance. Steps include measuring at least one engine parameter; determining engine power demand from the at least one engine parameter; and calculating rotor tip clearance given the determined engine power demand. The rotor tip clearance arrangement is controlled to increase or decrease the rotor tip clearance based on the difference between the calculated clearance and a predefined target clearance.
    Type: Grant
    Filed: August 13, 2014
    Date of Patent: May 23, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Marko Bacic, James Tooke
  • Patent number: 9506401
    Abstract: A method of detecting shaft break in a gas turbine engine having a shaft system. The shaft system including a shaft that couples a compressor and a turbine. First construct a frequency model of the shaft system. Then determine a notch frequency and a first torsional frequency for the shaft system from the model. Then in real time measure a rotational speed of the shaft; detect the presence or absence of a feature at least one of the notch frequency and the first torsional frequency in the measured speed; and generate a shaft break signal in response to the absence of at least one of the features.
    Type: Grant
    Filed: February 24, 2012
    Date of Patent: November 29, 2016
    Assignee: ROLLS-ROYCE plc
    Inventors: Marko Bacic, Stephen Granville Garner