Patents Assigned to Weston Aerospace Limited
  • Patent number: 9786828
    Abstract: A method is disclosed for tailoring the thermoelectric response of a thermocouple to that desired by a user. The method comprises the steps of; (a) selecting a first thermoelectric material, (b) selecting a second thermoelectric material having dissimilar thermoelectric properties to the first thermoelectric material, a thermocouple formed from the first thermoelectric material and the second thermoelectric material having a known thermoelectric response, and (c) modifying the chemical composition of at least one of the first thermoelectric material and the second thermoelectric material to produce a thermocouple having a tailored thermoelectric response. In specific embodiments, the chemical composition may be modified by selectively depleting one or more chemical elements from the thermoelectric material or by selectively adding, or increasing the proportion of, one or more elements to the thermoelectric material.
    Type: Grant
    Filed: February 20, 2014
    Date of Patent: October 10, 2017
    Assignee: WESTON AEROSPACE LIMITED
    Inventor: Paul Hanscombe
  • Patent number: 9778145
    Abstract: An engine probe system for monitoring a moving engine element. The probe system includes a capacitive sensor (1) including a sensing electrode (5) defining one of the electrodes of a capacitor and an output lead for coupling the sensing electrode (5) to data processing means for monitoring changes in the capacitance of the capacitor including the sensing electrode. The output lead includes a first conductor for connecting the sensing electrode to the data processing means, an insulation jacket surrounding the first conductor, and a flexible conduit (11) surrounding the insulation jacket and defining a fluid passage between the insulation jacket and the flexible conduit.
    Type: Grant
    Filed: January 15, 2015
    Date of Patent: October 3, 2017
    Assignee: WESTON AEROSPACE LIMITED
    Inventor: Paul Walling
  • Patent number: 9733131
    Abstract: A cooled thermocouple arrangement (1) including a thermocouple (2) comprising two wires (3,4) joined at a first sensing end (5) to define a hot thermocouple function. At least a portion of the wires (3,4) are in thermal communication with a cooling arrangement, and the cooling arrangement has an inlet (14) for coolant and an outlet (15) for coolant. The thermocouple probe arrangement (1) includes a first inlet temperature sensor (21) for determining the temperature of the coolant as it enters the cooling arrangement, and a flow rate sensor (20) for determining the flow rate of coolant passing through the cooling arrangement. The thermocouple probe arrangement (1) includes connectors for connecting the outputs from the thermocouple (2), first inlet temperature sensor (21) and the flow rate sensor (20) to a correction data processor (23) whereby the data processor can correct the temperature sensed by the thermocouple to take account of the effect of the cooling arrangement.
    Type: Grant
    Filed: June 23, 2014
    Date of Patent: August 15, 2017
    Assignee: WESTON AEROSPACE LIMITED
    Inventors: James Ewing, Daniel Loveless
  • Patent number: 9506818
    Abstract: The invention provides a thermocouple assembly for use with a thermocouple harness in a gas turbine engine, comprising a thermocouple connected to a resistor, the resistor comprising a conductor, a mineral insulating material surrounding the conductor, and a metal sheath surrounding the conductor.
    Type: Grant
    Filed: July 31, 2012
    Date of Patent: November 29, 2016
    Assignee: Weston Aerospace Limited
    Inventor: Paul Walling
  • Patent number: 9164122
    Abstract: There is disclosed a dual output compressive mode accelerometer having first and second output channels, comprising: a supporting base; first and second transducers mounted on the supporting base adjacent to one another, each transducer comprising a piezoelectric element and a seismic mass, the piezoelectric element positioned between the supporting base and the seismic mass; and a rigid mechanical coupling between the first and second transducers, the rigid mechanical coupling coupled to both of the first and second transducers above the supporting base.
    Type: Grant
    Filed: July 11, 2012
    Date of Patent: October 20, 2015
    Assignee: Weston Aerospace Limited
    Inventors: Paul Walling, David Yeomans
  • Patent number: 9068503
    Abstract: A sensor element for use in a backing sensor to monitor a gas turbine shaft. The sensor includes an oscillator circuit 30 having an oscillator and a resonance circuit 42, and a frequency detector 31 for monitoring the frequency of the oscillation circuit. Abnormal movement of the shaft cuts the circuit in the sensor along a cutting line (15). The cutting of the sensor changes the capacitance and/or inductance of the resonance circuit and thereby changes the frequency of oscillation.
    Type: Grant
    Filed: September 14, 2012
    Date of Patent: June 30, 2015
    Assignee: Weston Aerospace Limited
    Inventor: Wojciech Konrad Kulczyk
  • Patent number: 8947071
    Abstract: A system and method for measuring frequency which reduces the impact of noise. The system and method includes the steps of sampling a signal train over a first signal portion of the signal train, determining a first average period for the first signal portion (t1) of the signal train, sampling the signal train over a second signal portion (t2) of the signal train, wherein, the second portion of the signal train overlaps with the first signal portion, determining a second average period for the second signal portion (t2) of the output signal train, and then determining the average of the determined average periods.
    Type: Grant
    Filed: March 2, 2012
    Date of Patent: February 3, 2015
    Assignee: Weston Aerospace Limited
    Inventors: Mark Rudkin, Anthony Palmer
  • Patent number: 8847723
    Abstract: The invention provides a system for monitoring an operational parameter of a gas turbine, including a magnetic coupling between a signal source and a data output terminal. The magnetic coupling comprises a primary coil electrically connected to the signal source and wound around a first magnetic core section, and a secondary coil electrically connected to the output terminal but electrically isolated from the primary coil and wound around a second magnetic core section, wherein the first and second magnetic core sections are physically separated from one another.
    Type: Grant
    Filed: July 15, 2009
    Date of Patent: September 30, 2014
    Assignee: Weston Aerospace Limited
    Inventor: Robert Michael George Bodin
  • Patent number: 8549931
    Abstract: There is provided a variable reluctance sensor for sensing the speed or torque of a shaft in a gear box or gas turbine engine, comprising a magnetic pole piece a conductive wire wrapped around the pole piece a housing surrounding the pole piece, the housing having a front face and at least one side wall, wherein, in use, the front face is positioned proximate to an object to be sensed wherein the pole piece is rigidly fixed to the side wall of the housing. This arrangement reduces microphony in the sensor.
    Type: Grant
    Filed: June 16, 2011
    Date of Patent: October 8, 2013
    Assignee: Weston Aerospace Limited
    Inventor: Robert Michael George Bodin
  • Publication number: 20130243035
    Abstract: The invention provides a thermocouple assembly for use with a thermocouple harness in a gas turbine engine, comprising a thermocouple connected to a resistor, the resistor comprising a conductor, a mineral insulating material surrounding the conductor, and a metal sheath surrounding the conductor.
    Type: Application
    Filed: July 31, 2012
    Publication date: September 19, 2013
    Applicant: WESTON AEROSPACE LIMITED
    Inventor: Paul Walling
  • Publication number: 20130071230
    Abstract: A sensor element for use in a backing sensor to monitor a gas turbine shaft. The sensor includes an oscillator circuit 30 having an oscillator and a resonance circuit 42, and a frequency detector 31 for monitoring the frequency of the ossilation circuit. Abnormal movement of the shaft cuts the circuit in the sensor along a cutting line (15). The cutting of the sensor changes the capacitance and/or inductance of the resonance circuit and thereby changes the frequency of oscillation.
    Type: Application
    Filed: September 14, 2012
    Publication date: March 21, 2013
    Applicant: WESTON AEROSPACE LIMITED
    Inventor: Wojciech Konrad Kulczyk
  • Publication number: 20130063127
    Abstract: A system and method for measuring frequency which reduces the impact of noise. The system and method includes the steps of sampling a signal train (2) over a first signal portion (t1) of the signal train, determining a first average period for the first signal portion (t1) of the signal train, sampling the signal train over a second signal portion (t2) of the signal train, wherein, the second portion of the signal train overlaps with the first signal portion, determining a second average period for the second signal portion (t2) of the output signal train, and then determining the average of the determined average periods.
    Type: Application
    Filed: March 2, 2012
    Publication date: March 14, 2013
    Applicant: WESTON AEROSPACE LIMITED
    Inventors: Mark Rudkin, Anthony Palmer
  • Publication number: 20130014586
    Abstract: There is disclosed a dual output compressive mode accelerometer having first and second output channels, comprising: a supporting base; first and second transducers mounted on the supporting base adjacent to one another, each transducer comprising a piezoelectric element and a seismic mass, the piezoelectric element positioned between the supporting base and the seismic mass; and a rigid mechanical coupling between the first and second transducers, the rigid mechanical coupling coupled to both of the first and second transducers above the supporting base.
    Type: Application
    Filed: July 11, 2012
    Publication date: January 17, 2013
    Applicant: WESTON AEROSPACE LIMITED
    Inventors: Paul Walling, David Yeomans
  • Patent number: 8253410
    Abstract: The invention provides a transformer probe for sensing movement of a body of magnetic material, having multiple output channels wherein the output in each output channel is substantially unaffected by faults in other output channels.
    Type: Grant
    Filed: February 24, 2010
    Date of Patent: August 28, 2012
    Assignee: Weston Aerospace Limited
    Inventor: Nigel Philip Turner
  • Patent number: 8229646
    Abstract: A method (and corresponding apparatus) for monitoring gas turbine blades. The output from an eddy current sensor monitoring the movement of turbine blades past the sensor is processed to determine when the signal train from the sensor omits a signal or pulse corresponding to one of the shaft's full complement of blades. The signal processor compares sensed blade periods with average blade periods.
    Type: Grant
    Filed: December 19, 2008
    Date of Patent: July 24, 2012
    Assignee: Weston Aerospace Limited
    Inventors: Wojciech Konrad Kulczyk, Anthony Palmer, Matthew Clifton-Welker
  • Patent number: 8197134
    Abstract: A mounting terminal head of a thermocouple head unit having a metal casing for an end of a thermocouple wire, and thermocouple signal terminals 4 for connection to a thermocouple wire. The thermocouple head unit includes an insulating support member 8 extending around the outside of the thermocouple head unit and supporting the thermocouple signal terminals.
    Type: Grant
    Filed: August 11, 2008
    Date of Patent: June 12, 2012
    Assignee: Weston Aerospace Limited
    Inventor: Barry Peter Robinson
  • Publication number: 20120112769
    Abstract: A method is provided for determining timing points indicative of the passage of a blade in a turbine engine. The method comprises the steps of: providing a s first sensing coil proximate to a path of the blade, providing a second sensing coil proximate to the path of the blade, the second sensing coil spaced from the first sensing coil in a direction parallel to the path of the blade, and comparing a signal generated in the first sensing coil with a signal generated in the second sensing coil to derive a timing point indicative of the passage of the blade.
    Type: Application
    Filed: May 18, 2011
    Publication date: May 10, 2012
    Applicant: Weston Aerospace Limited
    Inventors: Anthony Palmer, Matthew Clifton-Welker, Leslie William Allen
  • Patent number: 8157440
    Abstract: The invention provides a total gas temperature sensor for measuring the temperature of gas in a gas flow. A gas temperature sensor in accordance with the invention comprises a measurement chamber having a gas inlet and a gas outlet; an outlet valve located at the gas outlet, operable to seal the gas outlet when in a closed position, and a temperature sensing element located in the measurement chamber. The sensor is simple to manufacture, is robust, provides for a low recovery correction and does not suffer from significant boundary layer problems.
    Type: Grant
    Filed: June 6, 2008
    Date of Patent: April 17, 2012
    Assignee: Weston Aerospace Limited
    Inventor: Wojciech Konrad Kulczyk
  • Publication number: 20110308331
    Abstract: There is provided a variable reluctance sensor for sensing the speed or torque of a shaft in a gear box or gas turbine engine, comprising a magnetic pole piece a conductive wire wrapped around the pole piece a housing surrounding the pole piece, the housing having a front face and at least one side wall, wherein, in use, the front face is positioned proximate to an object to be sensed wherein the pole piece is rigidly fixed to the side wall of the housing. This arrangement reduces microphony in the sensor.
    Type: Application
    Filed: June 16, 2011
    Publication date: December 22, 2011
    Applicant: WESTON AEROSPACE LIMITED
    Inventor: Robert Michael George Bodin
  • Publication number: 20110252884
    Abstract: The invention provides a vibrating cylinder transducer for measuring the pressure or density of a fluid medium comprising: a cylindrical vibrator, in use having at least one surface coupled to a fluid medium to be measured; a drive means for vibrating the cylindrical vibrator; a sensor for detecting the resonant frequency of the cylindrical vibrator; and an output coupled to the sensor, the output configured to provide an output signal indicative of the pressure and/or the density of the fluid medium; wherein the surface coupled to the fluid medium is coated in a corrosion resistant polymer layer. Preferably the corrosion resistant polymer layer is formed from parylene.
    Type: Application
    Filed: April 14, 2011
    Publication date: October 20, 2011
    Applicant: WESTON AEROSPACE LIMITED
    Inventors: Paul Hanscombe, Mark Rudkin