Patents by Inventor Tin Cheung John HU

Tin Cheung John HU 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: 10865761
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a fuel receiver adjacent the heater rod, the fuel receiver including a portion located closest to the heater rod, the rod end protruding axially relative to the axis from the fuel receiver portion located closest to the heater rod.
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: December 15, 2020
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
  • Publication number: 20200355369
    Abstract: Wall assemblies for a combustor of a gas turbine engine are disclosed. A wall assembly comprises an outer shell made of a metallic material, adjacent first and second inner panels mounted to the outer shell via an insert and a damper disposed between the outer shell and at least one of the first and second inner panels. The first and second inner panels may be spaced apart from the outer shell to define a double-wall configuration with the outer shell. The first and second inner panels may be made of a composite material. The insert may be made from substantially the same or other type of composite material.
    Type: Application
    Filed: December 16, 2019
    Publication date: November 12, 2020
    Inventor: Tin-Cheung John HU
  • Patent number: 10816200
    Abstract: The build-up of carbon deposition on the front face of a combustor heat shield is discouraged by jetting air out from the front face of the heat shield with sufficient momentum to push approaching fuel droplets or rich fuel-air mixture way from the heat shield.
    Type: Grant
    Filed: November 8, 2016
    Date of Patent: October 27, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Tin Cheung John Hu, Robert Sze, Honza Stastny
  • Patent number: 10788209
    Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.
    Type: Grant
    Filed: August 5, 2015
    Date of Patent: September 29, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lev Alexander Prociw, Parham Zabeti, Tin Cheung John Hu
  • Publication number: 20200200387
    Abstract: A combustor for a gas turbine engine comprises a combustor chamber defined at least partially by an outer combustor skin and an inner combustor skin. A plurality of stand-off devices have a body including a first end and a second end, the second end of the body retained in an opening in the outer combustor skin, the first end spaced apart from the second end and abutting the inner combustor skin to space the inner combustor skin apart from the outer combustor skin.
    Type: Application
    Filed: June 21, 2019
    Publication date: June 25, 2020
    Inventors: Tin-Cheung John HU, Oleg MORENKO
  • Publication number: 20200173661
    Abstract: An interface for double-skin combustor liner comprises an annular ceramic matrix composite (CMC) body. The annular body extends from a first side to a second side, the first and second sides each having an annular inner joint groove configured to receive a CMC combustor skin and an annular outer joint groove configured to receive a metal combustor skin. The outer joint groove is radially outward of the inner joint groove. A combustor and an gas turbine engine with the interface are also provided.
    Type: Application
    Filed: November 30, 2018
    Publication date: June 4, 2020
    Inventors: Tin-Cheung John HU, Robert SZE
  • Publication number: 20200158344
    Abstract: A ring assembly for holding a double-skin combustor liner has an inner skin of ceramic matrix composite and an outer skin. The assembly comprises an annular end body, a first projecting portion projecting relative to the annular end body at least partially in an axial direction, the first projecting portion configured for supporting the inner skin, a second projecting portion projecting relative to the annular end body at least partially in the axial direction, the second projecting portion configured for supporting the outer skin. The first and second projecting portions are radially spaced apart to provide a radial spacing between the inner skin and the outer skin. An expansion joint is between the ring assembly and the inner skin configured to permit motion resulting from a variation in thermal expansion between the inner skin and the ring assembly.
    Type: Application
    Filed: November 15, 2018
    Publication date: May 21, 2020
    Inventors: Tin-Cheung John HU, Nassim BEDRANI
  • Publication number: 20200080530
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a fuel receiver adjacent the heater rod, the fuel receiver including a portion located closest to the heater rod, the rod end protruding axially relative to the axis from the fuel receiver portion located closest to the heater rod.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
  • Publication number: 20200080486
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a sleeve extending at least partially axially along the heater rod, the sleeve having an inner surface facing and spaced apart from the rod, the inner surface defining a pocket adjacent to the heater rod and having a radial depth relative to the axis.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080490
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a flow impeding member extending along the axis and having a distal end spaced from the base and extending axially relative to the axis beyond the rod end, the flow impeding member sized and configured such that the distal end extends into a combustion chamber of the gas turbine engine upon the base connected to the casing.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080483
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, and a plurality of fins disposed circumferentially around the glow plug heater rod, the fins extending axially along at least a portion of the glow plug heater rod. A gas turbine engine including such an igniter is further disclosed.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080489
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the heater rod extending from the base along an axis and terminating in a rod end, a peripheral wall extending circumferentially around the rod end and having a distal end directed away from the base, a gap between the peripheral wall and the heater rod, the rod end being axially retracted relative the distal end of the peripheral wall.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080484
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis and terminating in a rod end, a combustor liner plug extending circumferentially around the heater rod, the combustor liner plug being sized and configured to extend inside an aperture in a combustor liner of the gas turbine engine when the base is connected to the casing between the heater rod and a periphery of the aperture.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080529
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a sleeve extending circumferentially around the glow plug heater rod along at least a portion of a length of the glow plug heater rod, the sleeve having an inner surface spaced from the glow plug heater rod to provide a gap between the inner surface and the glow plug heater rod, the gap extending radially relative to said axis.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080482
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a structure having open porosity disposed adjacent the glow plug heater rod. A method of operating the igniter and a gas turbine engine having such an igniter are also disclosed.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080492
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod extending from the base along an axis and terminating in a rod end, a sleeve extending circumferentially around the glow plug heater rod along at least a portion of a length of the glow plug heater rod, the igniter having a ventilation path extending from an inlet to an outlet, the inlet fluidly connectable to a spacing located between a casing and a combustor liner of the gas turbine engine, the outlet extending circumferentially around the glow plug heater rod and oriented axially relative to the axis, the outlet fluidly connectable to a combustion chamber of the gas turbine engine delimited by the combustor liner.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080488
    Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis to a rod end distal from the base, the glow plug heater rod sized such that that the rod end is exposed to a combustion chamber of the gas turbine engine when the base is connected to the casing.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Publication number: 20200080491
    Abstract: There is disclosed a method of servicing a gas turbine engine having a spark plug igniter connected to a spark plug igniter socket of the engine, the method including: removing the spark plug from the spark plug igniter socket of the gas turbine engine; inserting a glow plug igniter having a base configured for matingly engaging the spark plug igniter socket; and securing the glow plug igniter to the gas turbine engine.
    Type: Application
    Filed: March 29, 2019
    Publication date: March 12, 2020
    Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
  • Patent number: 10378774
    Abstract: In a gas turbine combustor having an inner and outer liner defining an annular combustion chamber, at least an annular scoop ring provided on each inner and outer combustor liner. The annular scoop ring includes a solid radial inner base provided with bores defined therein and communicating with the combustion chamber to form air dilution inlets. The scoop ring has a radial outer portion in the form of a C-shaped scoop open to receive high velocity annular air flow. The bores of the inlets communicating with the scoop portion to direct the air flow into the combustion chamber whereby the bores of the inlets form jet nozzles to generate air jet penetration and direction within the combustion chamber.
    Type: Grant
    Filed: October 25, 2013
    Date of Patent: August 13, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Tin Cheung John Hu, Oleg Morenko, Lev Alexander Prociw, Parham Zabeti
  • Patent number: 10260751
    Abstract: A combustor for a gas turbine engine comprises a single skin liner defining a combustion chamber. The single skin liner has an inner surface facing the combustion chamber and an outer surface exposed to a coolant flow discharged in a plenum extending from the outer surface of the single skin liner to the engine casing. Cooling holes extend through the single skin liner. Cooling protuberances, such as fins or pin fins, project integrally from the outer surface of the single skin liner into the plenum, the cooling fins being interspersed between the cooling holes.
    Type: Grant
    Filed: September 28, 2015
    Date of Patent: April 16, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Tin-Cheung John Hu, Si-Man Amy Lao, Sri Sreekanth, Michael Papple