Patents by Inventor Oleg Morenko

Oleg Morenko 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: 10955140
    Abstract: A gas turbine engine comprises a combustor. The combustor comprises an annular combustor chamber formed between an inner liner and an outer liner spaced apart from the inner liner. An annular fuel manifold has fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber.
    Type: Grant
    Filed: November 29, 2016
    Date of Patent: March 23, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • Patent number: 10927764
    Abstract: The gas turbine engine fuel manifold assembly includes a fuel manifold, and fuel nozzles secured to the fuel manifold and in fluid communication therewith. A fuel inlet connector has a body secured to the fuel manifold, and is in-line therewith. The fuel inlet connector has at least one connector outlet fluidly connected to the fuel manifold. The at least one connector outlet defines a fuel flow direction having a main component in a circumferential direction relative to the axis.
    Type: Grant
    Filed: September 26, 2018
    Date of Patent: February 23, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Oleg Morenko, Ryan Miskie
  • Publication number: 20210025337
    Abstract: A method of operating a fuel delivery system of an aircraft engine of an aircraft includes operating the aircraft engine in a standby mode by maintaining combustion in a combustor of the aircraft engine by supplying fuel to the combustor via a first set of fuel nozzles of a first fuel manifold while providing a trickle flow of fuel via a second set of fuel nozzles of a second fuel manifold into the combustor during engine operation, the trickle flow being defined as a fuel flow rate selected to prevent flame-out of the combustion while providing one of: substantially no motive power to the aircraft, and no motive power to the aircraft, via the combustion of the trickle flow of fuel. An aircraft gas turbine engine is also described.
    Type: Application
    Filed: November 1, 2019
    Publication date: January 28, 2021
    Inventors: Oleg MORENKO, Aleksandar KOJOVIC, Jeffrey Richard VERHIEL
  • Publication number: 20210025332
    Abstract: A fuel delivery system for an aircraft engine includes a first fuel manifold operable to deliver fuel to a combustor of the aircraft engine via a first set of fuel nozzles, a second fuel manifold operable to deliver fuel to a combustor of the aircraft engine via a second set of fuel nozzles, and a valve in a fuel nozzle of the second set of fuel nozzles, the valve operable to block fuel flow from the second fuel manifold to the fuel nozzle when the aircraft engine is operated in a standby mode. An aircraft gas turbine engine and a method of operating an aircraft engine are also disclosed.
    Type: Application
    Filed: November 1, 2019
    Publication date: January 28, 2021
    Inventors: Oleg MORENKO, Kian MCCALDON, Jeffrey Richard VERHIEL
  • Publication number: 20210025333
    Abstract: A fuel delivery system for an aircraft engine includes a first fuel manifold operable to deliver fuel to a combustor of the aircraft engine via a first set of fuel nozzles, a first fuel conduit fluidly connected to the first fuel manifold at a first point, the first fuel conduit being fluidly connectable to a fuel source, a second fuel manifold operable to deliver fuel to a combustor of the aircraft engine via a second set of fuel nozzles, a second fuel conduit fluidly connected to the second fuel manifold at a second point, the second fuel conduit being fluidly connectable to the fuel source, and a cross-flow fuel conduit fluidly connecting the first fuel manifold to the second fuel manifold. A method of operating an aircraft engine is also described.
    Type: Application
    Filed: November 1, 2019
    Publication date: January 28, 2021
    Inventors: Oleg MORENKO, Aleksandar KOJOVIC, Jeffrey Richard VERHIEL
  • Publication number: 20210003283
    Abstract: A floating collar assembly is configured to receive a fuel nozzle or an igniter projecting through an opening defined in a combustor shell lined with heat shields having studs projecting through the combustor shell for engagement with corresponding fasteners outside the combustor shell. A floating collar is mounted outside the combustor shell with an opening in alignment with the opening in the combustor shell for receiving the fuel nozzle or the igniter. An external retaining bracket is mounted to the heat shield studs or other studs projecting outwardly from the combustor shell so as to trap the floating collar between the combustor shell and the bracket.
    Type: Application
    Filed: July 3, 2019
    Publication date: January 7, 2021
    Inventors: Maximilian BARANOWICZ, Si-Man Amy LAO, Oleg MORENKO
  • Publication number: 20200362760
    Abstract: Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and discharging pressurized air from an accumulator into the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.
    Type: Application
    Filed: May 11, 2020
    Publication date: November 19, 2020
    Inventors: Oleg MORENKO, Stephen TARLING, Ian BROCCOLINI, Aleksandar KOJOVIC, Jeffrey Richard VERHIEL
  • Publication number: 20200355370
    Abstract: A fuel swirler, for a gas turbine engine, has a primary cone housing defining an interior chamber. The interior chamber has an inlet in communication with a source of pressurized fuel. The interior chamber has a transition portion and a socket portion with an axisymmetric interior surface. A swirler core is disposed within the interior chamber. The swirler core has a downstream end and an upstream shank portion having an exterior surface mating the axisymmetric interior surface of the socket portion. The shank portion has a plurality of axially extending grooves. The grooves are disposed axisymmetrically about the exterior surface of the shank portion.
    Type: Application
    Filed: May 8, 2019
    Publication date: November 12, 2020
    Inventors: Sylvain JETTE, Oleg MORENKO
  • Patent number: 10823073
    Abstract: A fuel supply assembly for a gas turbine engine includes at least one fuel transfer tube, at least one fuel nozzle, and at least one retaining bracket. The transfer tube and the nozzle are assembled in fluid communication with one another. The retaining bracket is fixedly attached to one of the nozzle and the transfer tube and displaceable relative thereto between a first position and a second position. A free end of the bracket is engageable with the other of the fuel nozzle and the transfer tube to retain the transfer tube to the fuel nozzle when the bracket is in the second position. The retaining bracket is disengaged from one of the fuel nozzle and the transfer tube in the first position so that the fuel nozzle and the transfer tube are disengageable from one another.
    Type: Grant
    Filed: February 19, 2016
    Date of Patent: November 3, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Oleg Morenko, Ryan Miskie
  • Publication number: 20200284199
    Abstract: An annular heat shield arrangement for a combustor liner comprises annular heat shield assemblies. The annular heat shield assemblies include heat shield segments circumferentially distributed around an axis of the annular heat shield assembly. The heat shield segments extend from a first lateral edge face to a second lateral edge face, a first overlap joint portion being defined at the first lateral edge face, a second overlap joint portion being defined at the second lateral edge face. The first overlap joint portion and the second overlap joint portion are complementary to form an overlap joint when pairs of the heat shield segments are side by side in any one of the heat shield assemblies. An adjacent pair of the annular heat shield assemblies are connected to one another at an overlap between the pair, and wherein the overlap joints from a first of the annular heat shield assemblies of the pair are circumferentially offset from a second of the annular heat shield assemblies of the pair.
    Type: Application
    Filed: March 7, 2019
    Publication date: September 10, 2020
    Inventor: Oleg Morenko
  • 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: 20200103116
    Abstract: A fuel supply assembly for a gas turbine engine comprises a plurality of fuel injectors configured for mounting circumferentially to an engine casing of the gas turbine engine and to be serially interconnected. At least one pair of the plurality of the fuel injectors has a first fuel injector including a first manifold adapter having a first outlet defined around a first outlet axis, and a first stem connected to the first manifold adapter at the first outlet and extending longitudinally along a first stem axis; and a second fuel injector including a second manifold adapter having a second outlet defined around a second outlet axis, and a second stem connected to the second manifold adapter at the second outlet, the first and second outlet axes being disposed circumferentially between the first and second stem axes.
    Type: Application
    Filed: October 2, 2018
    Publication date: April 2, 2020
    Inventors: Oleg MORENKO, Aleksandar KOJOVIC, Bryan Micheal BOND
  • Publication number: 20200095935
    Abstract: The gas turbine engine fuel manifold assembly includes a fuel manifold, and fuel nozzles secured to the fuel manifold and in fluid communication therewith. A fuel inlet connector has a body secured to the fuel manifold, and is in-line therewith. The fuel inlet connector has at least one connector outlet fluidly connected to the fuel manifold. The at least one connector outlet defines a fuel flow direction having a main component in a circumferential direction relative to the axis.
    Type: Application
    Filed: September 26, 2018
    Publication date: March 26, 2020
    Inventors: Oleg MORENKO, Ryan MISKIE
  • Patent number: 10563587
    Abstract: A gas turbine engine fuel nozzle comprises a spray tip defining a fuel exit passage therethrough that extends along a central axis. The fuel exit passage has an exit orifice aligned with the central axis. The exit orifice is circumscribed by an inner annular surface. The inner annular surface has a spherically-convex profile in cross-section, the profile being constant around the circumference of the inner annular surface.
    Type: Grant
    Filed: April 14, 2016
    Date of Patent: February 18, 2020
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Hayley Ozem, Oleg Morenko, Jean-Francois Grenier
  • Patent number: 10508600
    Abstract: A retaining bracket is attached to a fuel nozzle for cooperating with a flange on a fuel transfer tube to prevent the fuel transfer tube from becoming disconnected from the fuel nozzle during engine operation. The retaining bracket is shaped so as to form an enclosure over a head of the nozzle, the enclosure acting as a fire shield to allow the nozzle to perform its intended functions for a predetermined period of time when exposed to an engine fire event.
    Type: Grant
    Filed: May 27, 2016
    Date of Patent: December 17, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • Patent number: 10436114
    Abstract: A gas turbine engine has a combustor supported in a gas generator case. A baffle apparatus is attached to the gas generator case, surrounding an upstream section of the combustor to create at least one passage for directing an air flow discharged from a compressor diffuser to pass therethrough for cooling the combustor. The at least one passage extends from an upstream end of the combustor and has a passage exit immediately upstream of a dilution hole in the combustor. The baffle apparatus is configured to increase a velocity of the air flow entering the at least one passage and passing over the combustor.
    Type: Grant
    Filed: August 26, 2015
    Date of Patent: October 8, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Patent number: 10378775
    Abstract: A heat shield for a gas turbine engine having a combustor includes an annular configuration extending substantially 360 degrees about the combustor for protecting a dome portion thereof, which is formed by radially extending flanges of inner and outer liners of the combustor. The heat shield fixedly secures the radially extending flanges of the inner and outer liners together in a sealing relationship such as to structurally form the dome portion of the combustor. The heat shield is disposed internally within the combustor and substantially entirely overlying the dome portion. The heat shield includes at least two separate heat shield segments cooperating to provide the annular heat shield, each heat shield segment being sheet metal and including at least two circumferentially spaced apart openings therein for receiving fuel nozzles therethrough. Each of the heat shield segments has a circumferential span not exceeding 180 degrees.
    Type: Grant
    Filed: March 23, 2012
    Date of Patent: August 13, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • 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
  • Publication number: 20190234311
    Abstract: A thermally insulated fluid carrying component, such as fuel manifold, comprises a monolithic body having an internal insulation cavity extending along at least one fluid passage to be shielded from a heat source. Additive manufacturing or metal injection molding technologies can be used to optimise the relative positioning of the insulation cavity and the fuel passage as well as the shape of the monolithic body for thermal insulation purposes.
    Type: Application
    Filed: January 29, 2018
    Publication date: August 1, 2019
    Inventors: Oleg MORENKO, Aleksandar KOJOVIC
  • Publication number: 20190234310
    Abstract: A fuel manifold assembly for supplying fuel to a combustor of a gas turbine engine comprises an engine case defining a plenum around the combustor. An annular fuel manifold is mounted inside the engine case in the plenum. The fuel manifold has a plurality of manifold ring segments removable from the engine case via an access port defined in the engine case. A method of maintaining the fuel manifold comprises disconnecting a first manifold ring segment from a fuel source; opening an access port in a side of the engine case; and physically disconnecting the first manifold ring segment from the engine case. Then, the first manifold ring segment can be removed from the engine case via the access port for maintenance or replacement purposes.
    Type: Application
    Filed: January 29, 2018
    Publication date: August 1, 2019
    Inventors: Oleg MORENKO, Aleksandar KOJOVIC