Patents by Inventor Karan ANAND

Karan ANAND 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: 10487847
    Abstract: A gas turbine engine is described having a rotor with a plurality of rotor blades each extending radially between a blade root to a blade tip and axially between a leading edge and a trailing edge. An annular casing body housing the rotor blades includes an abradable segment of the inner surface facing the blade tips and having an abradable member. The abradable segment having one or more annular grooves, extending into the casing body from an inner surface thereof, and including an edge groove axially aligned with and facing the leading edge or the trailing edge of the rotor blades. The edge groove extends axially between a first position on the inner surface upstream of the leading edge or the trailing edge, and a second position on the inner surface downstream of the leading edge or the trailing edge.
    Type: Grant
    Filed: January 19, 2017
    Date of Patent: November 26, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Thomas Veitch, Karan Anand, Peter Townsend, Tibor Urac, Terry Brownridge
  • Patent number: 10393128
    Abstract: A bleed of valve comprises a ring axially translatable between a retracted position in which the ring is configured to close an annular bleed off opening defined in a converging portion of a radially outer annular wall of a gas turbine engine gaspath and a deployed position in which the ring protrudes into the gaspath to mechanically scoop out incoming air and water/hail particles.
    Type: Grant
    Filed: May 26, 2015
    Date of Patent: August 27, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Tibor Urac, Karan Anand
  • Publication number: 20190085868
    Abstract: A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.
    Type: Application
    Filed: September 15, 2017
    Publication date: March 21, 2019
    Inventors: Karan ANAND, Farid ABRARI, Ernest ADIQUE, Paul AITCHISON, Daniel FUDGE, Kari HEIKURINEN, Paul STONE, Tibor URAC, Thomas VEITCH
  • Patent number: 9879540
    Abstract: Compressor stators (22) for gas turbine engines (10) are disclosed. An exemplary compressor stator (22) comprises a circumferential array of stator vanes (28) and a shroud (24, 26) for supporting the stator vanes (28). The shroud (24, 26) has a circumferentially extending inner endwall (30, 32) exposed to an annular gas path (20) of the compressor (14). The endwall (30, 32) has a circumferentially uniform axial cross-sectional profile (42). The axial cross-sectional profile (42) comprises at least one deviation (48, 50) from a nominal axial cross-sectional profile (44) defining an overall shape of the annular gas path (20). The at least one deviation comprises a concave deviation (48) and a convex deviation (50).
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: January 30, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Yau-Wai Li, Karan Anand, Peter Townsend
  • Publication number: 20170204876
    Abstract: A gas turbine engine is described having a rotor with a plurality of rotor blades each extending radially between a blade root to a blade tip and axially between a leading edge and a trailing edge. An annular casing body housing the rotor blades includes an abradable segment of the inner surface facing the blade tips and having an abradable member. The abradable segment having one or more annular grooves, extending into the casing body from an inner surface thereof, and including an edge groove axially aligned with and facing the leading edge or the trailing edge of the rotor blades. The edge groove extends axially between a first position on the inner surface upstream of the leading edge or the trailing edge, and a second position on the inner surface downstream of the leading edge or the trailing edge.
    Type: Application
    Filed: January 19, 2017
    Publication date: July 20, 2017
    Inventors: Thomas VEITCH, Karan ANAND, Peter TOWNSEND, Tibor URAC, Terry BROWNRIDGE
  • Publication number: 20170089210
    Abstract: A seal arrangement for a gas turbine engine comprises a rotor hub. A a stator portion projects toward the rotor hub, an annular gap formed between the rotor hub and an end of the stator portion. A leakage path is defined from a first cavity on a first side of the stator portion, through the annular gap, and to a second cavity on a second side of the stator portion by positive pressure differential from the first cavity to the second cavity when in operation. A dynamic seal is secured to the rotor hub, the dynamic seal having geometrical features positioned relative to the annular gap to induce a flow of gas through the annular gap from the second cavity to the first cavity when in operation and rotating with the rotor hub.
    Type: Application
    Filed: September 29, 2015
    Publication date: March 30, 2017
    Inventor: Karan ANAND
  • Publication number: 20160348685
    Abstract: A bleed of valve comprises a ring axially translatable between a retracted position in which the ring is configured to close an annular bleed off opening defined in a converging portion of a radially outer annular wall of a gas turbine engine gaspath and a deployed position in which the ring protrudes into the gaspath to mechanically scoop out incoming air and water/hail particles.
    Type: Application
    Filed: May 26, 2015
    Publication date: December 1, 2016
    Inventors: TIBOR URAC, KARAN ANAND
  • Publication number: 20140271158
    Abstract: Compressor stators (22) for gas turbine engines (10) are disclosed. An exemplary compressor stator (22) comprises a circumferential array of stator vanes (28) and a shroud (24, 26) for supporting the stator vanes (28). The shroud (24, 26) has a circumferentially extending inner endwall (30, 32) exposed to an annular gas path (20) of the compressor (14). The endwall (30, 32) has a circumferentially uniform axial cross-sectional profile (42). The axial cross-sectional profile (42) comprises at least one deviation (48, 50) from a nominal axial cross-sectional profile (44) defining an overall shape of the annular gas path (20). The at least one deviation comprises a concave deviation (48) and a convex deviation (50).
    Type: Application
    Filed: March 12, 2013
    Publication date: September 18, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventors: Yau-Wai LI, Karan ANAND, Peter TOWNSEND