Patents by Inventor Ninad Joshi

Ninad Joshi 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: 11092078
    Abstract: The gas turbine engine includes a fluid system fluidly connecting at least two components of the gas turbine engine, and a tunable resonator in fluid flow communication with the fluid system. The tunable resonator has a resonating volume that varies as a function of a volume of an inflatable member located inside the tunable resonator. The inflatable member having a means for varying the volume of the inflatable member, to thereby tune the resonating volume to a selected frequency of pressure fluctuations or acoustic waves within the fluid system.
    Type: Grant
    Filed: November 28, 2018
    Date of Patent: August 17, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ninad Joshi, Sid-Ali Meslioui
  • Patent number: 11092077
    Abstract: An aircraft component and an associated method of manufacturing such aircraft component are disclosed. The aircraft component comprises a backing member, a porous sheet spaced apart from the backing member, and a cellular structure disposed between the backing member and the porous sheet. The cellular structure is attached to at least one of the backing member and the porous sheet by one or more non-adhesive connections.
    Type: Grant
    Filed: March 28, 2018
    Date of Patent: August 17, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ninad Joshi, Sid-Ali Meslioui, François Richard
  • Publication number: 20210102496
    Abstract: A fluid system of an aircraft engine includes a first and second fluid conduits. The first conduit fluid conduit fluidly connects to the aircraft engine. A pump fluidly connects to the first fluid conduit and moves therethrough a fluid imparting an excitation frequency to the fluid. The second fluid conduit fluidly connects to the first fluid conduit and to a pressure sensor. A weight is disposed in the second fluid conduit and movable between a first and second positions. A mass of the weight and a liquid capacitance of the second fluid conduit between the second position and a second end of the second fluid conduit define a resonance frequency that is less than the excitation frequency. Fluid pressure monitoring and pressure noise filter construction methods are also disclosed.
    Type: Application
    Filed: March 31, 2020
    Publication date: April 8, 2021
    Inventors: Daniel ALECU, Ninad JOSHI
  • Publication number: 20200378317
    Abstract: A multi-engine aircraft includes first and second gas turbine engines for providing motive power to the aircraft, each of the first and second engines comprising an air system, an air pressure line extending between and fluidly connecting the air systems of the first and second engines, and a pressure wave damper communicating with the air pressure line extending between the first and second engines.
    Type: Application
    Filed: November 4, 2019
    Publication date: December 3, 2020
    Inventors: Ninad JOSHI, Sid-Ali MESLIOUI
  • Patent number: 10829236
    Abstract: Herein provided are systems and methods for operating an aircraft engine during inclement weather. At least one image of a location substantially in line with a heading of the aircraft is acquired. Based on the at least one image, an inclement weather condition in the location is detected. An alert mode of the engine is triggered upon detecting the inclement weather condition. Responsive to the alert mode being triggered, at least one predetermined performance parameter of the engine is monitored. Upon detecting a change in the at least one predetermined performance parameter beyond a predetermined threshold, at least one operating condition of the engine is altered.
    Type: Grant
    Filed: June 22, 2018
    Date of Patent: November 10, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ninad Joshi, Yen-Wen Wang, Tony Yee
  • Patent number: 10823055
    Abstract: A bleed air system is disclosed for a turbofan engine having a bypass duct. The bleed air system includes a bleed air conduit having an inlet end connected to the bypass duct and a bleed air flow control valve disposed downstream of the inlet end, and a louver assembly disposed within the opening at inlet end of the bleed air conduit. The louver assembly includes an airfoil-shaped louver blade which extends across the opening in a direction transverse to the flow direction within the bypass duct. A reinforcing rib is attached to the louver blade and extends across the louver assembly in a direction generally parallel to the flow direction.
    Type: Grant
    Filed: September 26, 2016
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ninad Joshi, Sid-Ali Meslioui
  • Patent number: 10731570
    Abstract: Herein provided are methods and systems for reducing an acoustic signature of a gas turbine engine. An acceleration command for the engine is received. In response to receiving the acceleration command: a fuel flow to the engine is increased for a first predetermined time period; subsequent to the first predetermined time period, the fuel flow to the engine is reduced for a second predetermined time period; and subsequent to the second predetermined time period, the fuel flow to the engine is increased for a third time period.
    Type: Grant
    Filed: May 31, 2017
    Date of Patent: August 4, 2020
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ninad Joshi, Sid-Ali Meslioui, Tony Yee
  • Publication number: 20190389591
    Abstract: Herein provided are systems and methods for operating an aircraft engine during inclement weather. At least one image of a location substantially in line with a heading of the aircraft is acquired. Based on the at least one image, an inclement weather condition in the location is detected. An alert mode of the engine is triggered upon detecting the inclement weather condition. Responsive to the alert mode being triggered, at least one predetermined performance parameter of the engine is monitored. Upon detecting a change in the at least one predetermined performance parameter beyond a predetermined threshold, at least one operating condition of the engine is altered.
    Type: Application
    Filed: June 22, 2018
    Publication date: December 26, 2019
    Inventors: Ninad Joshi, Yen-Wen Wang, Tony Yee
  • Publication number: 20190301370
    Abstract: An aircraft component and an associated method of manufacturing such aircraft component are disclosed. The aircraft component comprises a backing member, a porous sheet spaced apart from the backing member, and a cellular structure disposed between the backing member and the porous sheet. The cellular structure is attached to at least one of the backing member and the porous sheet by one or more non-adhesive connections.
    Type: Application
    Filed: March 28, 2018
    Publication date: October 3, 2019
    Inventors: Ninad JOSHI, Sid-Ali MESLIOUI, François RICHARD
  • Patent number: 10280871
    Abstract: A nacelle exhaust nozzle having a deployable noise-reducing component is described. The noise-reducing component includes an annular perforated sleeve coinciding with the inner nacelle loft line and circumscribing a mixed exhaust gas flow exiting the nacelle. The annular perforated sleeve is radially spaced apart from of a displaceable wall of an inflatable envelope that is displaceable between a deployed position, wherein noise-reduction is active, and a retracted position, wherein noise-reduction is inactive. When the inflatable envelope is pressurized, portions of the displaceable wall project through openings in the perforated sleeve and into the exhaust gas flow to form a rough surface at the loft line which causes a reduction in noise level. The portions of the displaceable wall that project through the openings in the perforated sleeve when the inflatable enveloped is pressurized include a plurality of dimples formed on the inner wall and forming the rough surface.
    Type: Grant
    Filed: July 7, 2016
    Date of Patent: May 7, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ninad Joshi, Gaetan Girard
  • Publication number: 20190101063
    Abstract: A method for operating a gas turbine engine comprises providing fuel flow and compressed airflow to a combustor with a fuel-to-air ratio, the compressed airflow being from a compressed air source; detecting at least one parameter indicative of the fuel-to-air ratio being below a predetermined value; and bleeding compressed air from the compressed air source when the at least one parameter indicative of the fuel-to-air ratio is below the predetermined value to increase the fuel-to-air ratio to at least the predetermined value.
    Type: Application
    Filed: September 29, 2017
    Publication date: April 4, 2019
    Inventors: Ninad JOSHI, Sid-Ali MESLIOUI
  • Publication number: 20190093565
    Abstract: The gas turbine engine includes a fluid system fluidly connecting at least two components of the gas turbine engine, and a tunable resonator in fluid flow communication with the fluid system. The tunable resonator has a resonating volume that varies as a function of a volume of an inflatable member located inside the tunable resonator. The inflatable member having a means for varying the volume of the inflatable member, to thereby tune the resonating volume to a selected frequency of pressure fluctuations or acoustic waves within the fluid system.
    Type: Application
    Filed: November 28, 2018
    Publication date: March 28, 2019
    Inventors: Ninad JOSHI, Sid-Ali MESLIOUI
  • Patent number: 10167780
    Abstract: The gas turbine engine including, in serial flow communication, a compressor, a combustor, a turbine, and a fluid system fluidly connecting at least two components of the gas turbine engine, also includes a tunable resonator in fluid flow communication with the fluid system, the tunable resonator. The tunable resonator has a resonating volume that varies as a function of a volume of an inflatable member located inside the tunable resonator. The inflatable member having a means for varying the volume of the inflatable member, to thereby tune the resonating volume to a selected frequency of pressure fluctuations or acoustic waves within the fluid system.
    Type: Grant
    Filed: May 25, 2017
    Date of Patent: January 1, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ninad Joshi, Sid-Ali Meslioui
  • Publication number: 20180347475
    Abstract: Herein provided are methods and systems for reducing an acoustic signature of a gas turbine engine. An acceleration command for the engine is received. In response to receiving the acceleration command: a fuel flow to the engine is increased for a first predetermined time period; subsequent to the first predetermined time period, the fuel flow to the engine is reduced for a second predetermined time period; and subsequent to the second predetermined time period, the fuel flow to the engine is increased for a third time period.
    Type: Application
    Filed: May 31, 2017
    Publication date: December 6, 2018
    Inventors: Ninad JOSHI, Sid-Ali MESLIOUI, Tony YEE
  • Publication number: 20180340472
    Abstract: The gas turbine engine including, in serial flow communication, a compressor, a combustor, a turbine, and a fluid system fluidly connecting at least two components of the gas turbine engine, also includes a tunable resonator in fluid flow communication with the fluid system, the tunable resonator. The tunable resonator has a resonating volume that varies as a function of a volume of an inflatable member located inside the tunable resonator. The inflatable member having a means for varying the volume of the inflatable member, to thereby tune the resonating volume to a selected frequency of pressure fluctuations or acoustic waves within the fluid system.
    Type: Application
    Filed: May 25, 2017
    Publication date: November 29, 2018
    Inventors: Ninad JOSHI, Sid-Ali MESLIOUI
  • Patent number: 10071820
    Abstract: Methods and systems for detecting inclement weather in the vicinity of an aircraft engine are described. Vibration levels of the engine are monitored. Upon detection of an increase in the vibration levels beyond a threshold, an alert mode is triggered. At least one predetermined performance parameter is monitored while in the alert mode, and inclement weather is detected when the at least one predetermined performance parameter meets at least one inclement weather condition.
    Type: Grant
    Filed: September 19, 2016
    Date of Patent: September 11, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ninad Joshi, Andrea Lindsay Henning, Faran Hafeez
  • Publication number: 20180079520
    Abstract: Methods and systems for detecting inclement weather in the vicinity of an aircraft engine are described. Vibration levels of the engine are monitored. Upon detection of an increase in the vibration levels beyond a threshold, an alert mode is triggered. At least one predetermined performance parameter is monitored while in the alert mode, and inclement weather is detected when the at least one predetermined performance parameter meets at least one inclement weather condition.
    Type: Application
    Filed: September 19, 2016
    Publication date: March 22, 2018
    Inventors: Ninad JOSHI, Andrea Linsay Henning, Faran Hafeez
  • Publication number: 20180073435
    Abstract: A transfer duct and an associated active tip clearance control system of a gas turbine engine are disclosed. In one embodiment, the duct comprises: an upstream duct portion for fluid communication with an air source; a downstream duct portion for fluid communication with a manifold for directing the air toward a rotor case; and a noise-mitigating device disposed between the upstream duct portion and the downstream duct portion. The duct may define an abrupt change in internal cross sectional area between the upstream duct portion and the noise-mitigating device.
    Type: Application
    Filed: September 9, 2016
    Publication date: March 15, 2018
    Inventors: Li-Jen CHEN, Ninad JOSHI, Sid-Ali MESLIOUI
  • Publication number: 20180038279
    Abstract: A bleed air system is disclosed for a turbofan engine having a bypass duct. The bleed air system includes a bleed air conduit having an inlet end connected to the bypass duct and a bleed air flow control valve disposed downstream of the inlet end, and a louver assembly disposed within the opening at inlet end of the bleed air conduit. The louver assembly includes an airfoil-shaped louver blade which extends across the opening in a direction transverse to the flow direction within the bypass duct. A reinforcing rib is attached to the louver blade and extends across the louver assembly in a direction generally parallel to the flow direction.
    Type: Application
    Filed: September 26, 2016
    Publication date: February 8, 2018
    Inventors: Ninad JOSHI, Sid-Ali MESLIOUI
  • Publication number: 20170122255
    Abstract: A surface-increasing feature system for a gas turbine engine comprising deployable surface-increasing features such as chevrons each defined by panels connected to a deployment mechanism providing a translational actuation to deploy said deployable surface-increasing feature from a stowed configuration concealed fore of a trailing edge of a case of the gas turbine engine, to a deployed configuration extending beyond the trailing edge. Joints provide one or more degree of freedom for the first panel and the second panel relative to the deployment mechanism. A guide operatively contacts the deployable surface-increasing feature to rotatably displace the first panel and the second panel away from one another in the at least one degree of freedom in response to movement induced by the translational actuation from the stowed configuration to the deployed configuration.
    Type: Application
    Filed: October 28, 2015
    Publication date: May 4, 2017
    Inventors: Ninad Joshi, Sid-Ali Meslioui