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).

  • 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: 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
  • 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
  • Patent number: 10294865
    Abstract: A combustor assembly in a gas turbine engine includes a gas generator casing, an annular combustor supported within the casing, and a fuel injection system that includes an internal fuel manifold assembly having a fuel manifold ring with at least one fuel conveying passage in fluid flow communication with fuel injection nozzles. An inlet member is connected to the manifold ring and includes a drainage passage for collecting possible leaked fuel that is defined between the inlet member and a heat shield surrounding the inlet member. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: May 21, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko
  • Publication number: 20190107285
    Abstract: There is provided a segmented fuel distributor for injecting fuel into a combustion chamber. The segmented fuel distributor comprises segments serially interconnected in to provide an annular structure. The segments include a main conduit defining a first axis along which a main fuel flow path extends. The segments having two or more secondary conduits extending from the main conduit and being in fluid flow communication therewith, and fuel injectors fluidly connected to the secondary conduits at remote ends thereof.
    Type: Application
    Filed: October 6, 2017
    Publication date: April 11, 2019
    Inventors: Oleg MORENKO, Aleksandar KOJOVIC, Gavin Rohiteshwar KISUN
  • Patent number: 10184403
    Abstract: A fuel nozzle for a gas turbine engine. The nozzle has a body and a center axis. The body has an inner circumferential surface circumscribing a central passageway which is coaxial with the center axis. The nozzle also has air passages which extend predominantly radially inward through the body. The air passage outlets of each air passage are circumferentially spaced apart from one another along the inner circumferential surface. Each air passage conveys air through the body toward the nozzle center axis and into the central passageway. The nozzle also has fuel passages which extend through the body. Each fuel passage is disposed within the body between adjacent circumferentially spaced apart air passages and is transverse to the direction of extension of its neighboring air passages.
    Type: Grant
    Filed: August 13, 2014
    Date of Patent: January 22, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Kian McCaldon, Oleg Morenko
  • Publication number: 20180328586
    Abstract: A fuel injector for a fuel spray nozzle of a gas turbine engine combustor includes an angular lip axially projecting into an upstream section of an annular passage to guide a fuel layer vortex to flow along a radially outer passage wall of the annular passage and to guide an air layer vortex to fill into and pass through an annular space between the fuel layer vortex and a radially-inner passage wall of the annular passage. The air layer vortex is free of mixing with the fuel layer vortex before the fuel layer vortex is discharged from the annular passage for fuel atomization.
    Type: Application
    Filed: July 11, 2018
    Publication date: November 15, 2018
    Inventors: Bhawan B. PATEL, Oleg MORENKO
  • Publication number: 20180306117
    Abstract: A gas turbine engine fuel supply system has a plurality of fuel nozzles fluidly connected to a source of fuel by transfer tubes extending between the fuel nozzles. At least one plug extends between first and second adjacent nozzles of the set of fuel nozzles. The plug has a first end plugging a port on the first adjacent nozzle and a second end plugging another port on the second adjacent nozzle.
    Type: Application
    Filed: April 20, 2017
    Publication date: October 25, 2018
    Inventor: OLEG MORENKO
  • Patent number: 9879606
    Abstract: The described method of supplying fuel to an internal fuel manifold of a bypass gas turbine engine includes directing a fuel flow through a fuel fairing having an outer surface exposed to a cool bypass airflow, directing the fuel flow in the fuel fairing through a heat exchanging structure on the outer surface of the fuel fairing to cool the fuel flow being below a coking temperature of the fuel, and then feeding the cooled fuel flow from the fuel fairing to the internal fuel manifold.
    Type: Grant
    Filed: July 28, 2014
    Date of Patent: January 30, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Oleg Morenko, Bryan Olver
  • Publication number: 20180023477
    Abstract: A combustor assembly in a gas turbine engine includes a gas generator casing, an annular combustor supported within the casing, and a fuel injection system that includes an internal fuel manifold assembly having a fuel manifold ring with at least one fuel conveying passage in fluid flow communication with fuel injection nozzles. An inlet member is connected to the manifold ring and includes a drainage passage for collecting possible leaked fuel that is defined between the inlet member and a heat shield surrounding the inlet member. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.
    Type: Application
    Filed: September 15, 2017
    Publication date: January 25, 2018
    Inventor: Oleg MORENKO
  • Patent number: 9874148
    Abstract: There is provided a method for improving the combustion efficiency of a combustor of a gas turbine engine powering an aircraft. The method comprises selectively using two distinct fuel injection units or a combination thereof for spraying fuel in a combustion chamber of the combustor of the gas turbine engine. A first one of the two distinct fuel injection units is selected and optimized for high power demands, whereas a second one of the two distinct fuel injection units is selected and optimized for low power level demands. In operation, the fuel flow ratio between the two distinct injection units is controlled as a function of the power level demand.
    Type: Grant
    Filed: January 31, 2014
    Date of Patent: January 23, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Publication number: 20170363292
    Abstract: A method of accessing a nozzle tip assembly of a gas turbine engine fuel nozzle is disclosed. The fuel nozzle has a stem and a heat shield enclosing at least part of the stem. The nozzle tip assembly is disposed within an inner cavity of the stem. The method includes forming an opening in at least the heat shield of the fuel nozzle, the opening providing access to the inner cavity of the stem via a first end thereof. The first end of the cavity is positioned opposite to a fuel nozzle exit from which fuel is conveyed from the fuel nozzle. The method includes accessing the nozzle tip assembly in the inner cavity via the opening. The method includes closing the opening after accessing the nozzle tip assembly.
    Type: Application
    Filed: June 17, 2016
    Publication date: December 21, 2017
    Inventors: OLEG MORENKO, BHAWAN BHAI PATEL, JEAN-FRANCOIS GRENIER
  • Publication number: 20170342907
    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: Application
    Filed: May 27, 2016
    Publication date: November 30, 2017
    Inventor: OLEG MORENKO
  • Patent number: 9797313
    Abstract: An internal fuel manifold assembly includes a fuel manifold ring having at least one fuel conveying passage in fluid flow communication with at least one inlet passage defined through an inlet member. The inlet member is connected to the manifold ring proximate its first end and connected proximate its second end to at least one transfer tube. The inlet member includes a drainage passage for collecting possible leaked fuel from an annulus, defined between the inlet member and a heat shield surrounding the inlet member and spaced apart therefrom. Any leaked fuel is discharged out of the inlet member at an exit of the fuel passage on an end surface of the inlet member proximate the second end thereof.
    Type: Grant
    Filed: January 16, 2014
    Date of Patent: October 24, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Oleg Morenko