Patents Examined by Craig Kim
  • Patent number: 10669939
    Abstract: A combustor seal for use in a combustor of a gas turbine engine including a seal with a multiple of slots that correspond with a multiple of 1st HPT vanes. A method of cooling within a gas turbine engine including communicating cooling air through combustor seal toward each of a multiple of 1st HPT vanes.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: June 2, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Jonathan Jeffery Eastwood, Dennis M. Moura
  • Patent number: 10662880
    Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
    Type: Grant
    Filed: April 21, 2015
    Date of Patent: May 26, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 10655856
    Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: May 19, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Jonathan J. Eastwood, Dennis M. Moura, Lee E. Bouldin, Monica Pacheco-Tougas
  • Patent number: 10655492
    Abstract: An abrasive tip comprises an additive, the additive is configured to prevent adhesion of an organic component from an abradable seal onto an abrasive blade tip.
    Type: Grant
    Filed: April 29, 2016
    Date of Patent: May 19, 2020
    Assignee: United Technologies Corporation
    Inventors: James O Hansen, Christopher W Strock
  • Patent number: 10634061
    Abstract: A gas turbine engine comprises a compressor, a combustor and a turbine. A housing for the gas turbine engine includes a mount member to define a vertically upper location. Sides of the engine are defined on opposed sides of the mount, with a fuel filter, a fuel pump and a fuel flow meter being positioned on a first side and an oil pump, an oil filter and an oil tank positioned on a second of the sides.
    Type: Grant
    Filed: February 4, 2015
    Date of Patent: April 28, 2020
    Assignee: United Technologies Corporation
    Inventors: Ryan K. Snyder, Eric J. Heims, Mark W. Colebrook
  • Patent number: 10626753
    Abstract: A pulsed pressure, heat recovery system includes a pressure vessel for holding a vaporisable first fluid. The vessel contains a heat exchanger, and provides communication to the heat exchanger for flow of a heated second fluid. The heat exchanger enables heat transfer from the second fluid to vaporise the first fluid. The system also includes a flow loop for the first fluid extending from an outlet of the vessel to an inlet to the vessel, having in series: a first non-return valve, a turbine and a second non-return valve. The first non-return valve allows the vaporised first fluid to flow from the vessel to the turbine when the pressure of the vaporised first fluid in the vessel exceeds a predetermined limit. The turbine extracts energy from expansion of the vaporised first fluid. The second non-return valve prevents flow reversal around flow loop between the turbine and the inlet.
    Type: Grant
    Filed: April 12, 2016
    Date of Patent: April 21, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventor: Roger Alexander Sutherland
  • Patent number: 10625868
    Abstract: A bleed air heat ejector includes a housing defining an inner passage extending in an axial direction from an inlet of the housing to an outlet of the housing, wherein the inlet is configured to channel ambient air into the housing, and wherein the outlet is configured to channel mixed heated and ambient air out of the housing. A dispenser is mounted in the housing between the inlet and the outlet. The dispenser includes an inner chamber configured to receive heated air from a bleed line. The dispenser includes a plurality of apertures therein for issuing heated air from the inner chamber into the inner passage of the housing to form a flow of mixed ambient and bleed air. The apertures of the inner chamber can be angled primary jets, vortex generators can be included, and/or secondary jets can be included to promote mixing of bleed and ambient air.
    Type: Grant
    Filed: July 10, 2017
    Date of Patent: April 21, 2020
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Jose A. daSilva, Joseph Lawrence Simonetti, Donald William Lamb, Jr., Nhan R. Tran
  • Patent number: 10619934
    Abstract: A plate heat exchanger comprising a plurality of plates having a plane peripheral zone, an inner zone having sinusoidal undulations and two chimneys positioned at two opposite corners of the plates. Modules are formed by assembling two plates that make contact via the undulation troughs and the peripheral zones. The modules are stacked so as to make contact via the inlet and outlet chimneys. Each module may thus deform independently, in particular at the undulation troughs and ridges without transmitting stress to the other modules of the heat exchanger. In addition, the heat exchanger may comprise a tie rod in each inlet and outlet pipe so as to withstand the static pressure of the fluids flowing in the pipes.
    Type: Grant
    Filed: June 16, 2015
    Date of Patent: April 14, 2020
    Assignee: Airbus Helicopters
    Inventors: Olivier Honnorat, Christophe Dubourg
  • Patent number: 10612469
    Abstract: A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.
    Type: Grant
    Filed: August 1, 2014
    Date of Patent: April 7, 2020
    Assignee: United Technologies Corporation
    Inventors: Vito Guardi, Christopher B. Lyons, Nathan Snape
  • Patent number: 10612462
    Abstract: The present disclosure relates generally to turbomachinery in which a rotating component is disposed adjacent a counter-rotating component in order to achieve a relative rotational velocity that is higher than would be achieved with a rotating component disposed adjacent to a stationary component.
    Type: Grant
    Filed: December 12, 2014
    Date of Patent: April 7, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Gary D. Roberge
  • Patent number: 10605201
    Abstract: A gas turbine engine (10) comprises a main fluid flow exhaust nozzle (30) bounding a main fluid flow path, and a cooling nozzle (38) provided upstream of the main fluid flow exhaust nozzle (30) in the main fluid flow path. The cooling nozzle (38) is arranged to provide cooling air to a surface (36) of the main fluid flow exhaust nozzle (30), the cooling nozzle (38) comprises first and second outlets (44, 46). The first outlet (44) is located adjacent the main fluid flow exhaust nozzle surface (36) and is spaced from the main fluid flow path by the second outlet (46). The second outlet (46) comprises a convergent divergent nozzle configured to accelerate cooling air exhausted from the second outlet (46) to a velocity greater than air exhausted from the first outlet (44).
    Type: Grant
    Filed: June 22, 2017
    Date of Patent: March 31, 2020
    Assignee: Rolls-Royce plc
    Inventor: David Steele
  • Patent number: 10605253
    Abstract: A compressor system is provided with an impeller disposed to rotate in a compressor chamber. A diffuser extends around the impeller to collect fluid leaving the impeller. Main flow is discharged from the diffuser through an exit providing an opening that extends circumferentially around the compressor. A bleed annulus extends around the compressor and has a consistent cross-sectional area. A bleed port that opens the diffuser to the bleed annulus and that is configured to divert a bleed flow of the fluid from the main flow before discharge through the exit. The bleed port has a circumference around the compressor and a flow size that varies around the circumference. Variation in the flow size of the bleed port maintains a uniform flow distribution around the exit.
    Type: Grant
    Filed: November 28, 2017
    Date of Patent: March 31, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Robert Hoover, Greg Ockenfels, Paul Zonneveld, Keith Sangston
  • Patent number: 10598095
    Abstract: Systems and methods for starting an engine on an aircraft are provided. One example aspect of the present disclosure is directed to an integrated starter for starting an engine on an aircraft. The integrated starter includes an air turbine starter. The integrated starter includes a starter air valve integrated with the air turbine starter. The integrated starter includes a controller configured to control the starter air valve. The starter air valve can be movable between a first position and at least a second position to regulate the flow of fluid into the air turbine starter. An output torque of the air turbine starter can be dependent at least in part on the flow of fluid into the air turbine starter.
    Type: Grant
    Filed: October 11, 2016
    Date of Patent: March 24, 2020
    Assignee: Unison Industries, LLC
    Inventors: Brian Christopher Kemp, Theodore Scott Puterbaugh
  • Patent number: 10590849
    Abstract: A cooling system for a turbine engine including a heat exchanger in fluid communication with a first fluid inlet stream and disposed upstream and in fluid communication with a core engine. The heat exchanger operative to cool the first fluid inlet stream. The heat exchanger including a heat exchanger inlet for input of a heat exchanging medium for exchange of heat from the first fluid inlet stream to the heat exchanging medium. The heat exchanger further including a heat exchanger outlet for discharge of a heated output stream into one of a turbine of a downstream engine, an augmentor or a combustor of the core engine. The heated output stream provides an additional flow to the downstream engine. A turbine engine including the cooling system is disclosed.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: March 17, 2020
    Assignee: General Electric Company
    Inventors: Ross Hartley Kenyon, Narendra Digamber Joshi
  • Patent number: 10591163
    Abstract: A combustor for a gas turbine engine includes an annular combustor shell, the annular combustor shell defining a combustion chamber, and a fuel injector extending at least partially into the combustion chamber, and configured to deliver a flow of fuel and a flow of combustion air into the combustion chamber for combustion. The fuel injector includes a swirler with a swirler exit having a circumferential width along a circumferential axis greater than a radial width along a radial axis. A swirler for a gas turbine engine includes a swirler entrance and a swirler exit. The swirler exit has a circumferential width along a curvilinear circumferential axis greater than a radial width along a radial axis.
    Type: Grant
    Filed: July 21, 2017
    Date of Patent: March 17, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Steven D. Porter, Cara M. Redding
  • Patent number: 10578207
    Abstract: One aspect of a cooling system includes a gas source connected to a component to be cooled. The gas source continuously supplies compressed gas to the component in response to an input. The cooling system also includes a controller connected to the gas source, the controller to provide the input to the gas source to continuously supply the compressed gas to the component.
    Type: Grant
    Filed: July 24, 2014
    Date of Patent: March 3, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Brian S. Modrzejewski, Monte McGlaun, Travis Jurell
  • Patent number: 10578306
    Abstract: A liquid fuel cartridge unit for a gas turbine combustor includes a cartridge tip having an aft plate and a side wall circumscribing the aft plate. First injection ports are defined through the side wall, and second injection ports are defined through the side wall upstream of the first injection ports, relative to fuel flow through the cartridge tip. Nested conduits extend into the cartridge tip with the concentric conduits defining therebetween respective flow passages. The first injection ports are in fluid communication with a first flow passage, and the second injection ports are in fluid communication with a second flow passage. A method of assembling the liquid fuel cartridge unit is also provided.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: March 3, 2020
    Assignee: General Electric Company
    Inventors: Timothy James Purcell, Ronald James Chila, Lucas John Stoia
  • Patent number: 10570780
    Abstract: An exhaust assembly may include an exhaust body and a pivoting attachment feature. The exhaust body, such as a center body or a nozzle, may be configured to direct an annular exhaust stream exiting from a gas turbine engine. The pivoting attachment feature may be coupled the exhaust body and may be configured to pivotally couple the exhaust body to an engine flange. The pivoting attachment feature may be one of a plurality of attachment features circumferentially distributed around the exhaust body. The exhaust body may be a center body and the plurality of attachment features may be coupled to a radially inward surface the center body. The pivoting attachment feature may enable a degree of relative thermal expansion movement between the engine flange/turbine exhaust case and the exhaust body while mitigating detrimental thermal loads, according to various embodiments.
    Type: Grant
    Filed: November 3, 2017
    Date of Patent: February 25, 2020
    Assignee: ROHR, INC.
    Inventors: Jihad Ramlaoui, Pablo T. Sanz Martinez
  • Patent number: 10570823
    Abstract: A heat recovery unit for generating a heated fluid by a hot exhaust gas includes a housing having an inlet for introducing hot exhaust gas and an outlet for discharging treated exhaust gas, and arranged in the housing at least one heat exchanger for heat exchange between the hot exhaust gas and a fluid, and an auxiliary combustor for combusting fuel with hot exhaust gas. The auxiliary combustor is provided with a fuel supply, which auxiliary combustor is arranged downstream of the at least one heat exchanger in the housing. An exhaust gas bypass for a part of the hot exhaust gas is provided, having an inlet for exhaust gas, and being positioned upstream of the at least one heat exchanger, and having an outlet in direct fluid communication with the auxiliary combustor.
    Type: Grant
    Filed: September 24, 2015
    Date of Patent: February 25, 2020
    Assignee: Stork Thermeq B.V.
    Inventors: Eric Robert Stevenson, Stephan Cornelis Gerardus Bergmans
  • Patent number: 10571128
    Abstract: Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary fuel cartridge assembly may comprise first and second fuel manifolds which are connected to respective fuel circuits which supply fuel, such as liquid fuel, through a plurality of fuel passages within the fuel cartridge assembly or to other locations within an associated combustor. The fuel cartridge assembly may further include a plurality of fuel injector tips located at a tip plate of the fuel cartridge assembly through which fuel may be supplied to an associated combustor.
    Type: Grant
    Filed: June 27, 2016
    Date of Patent: February 25, 2020
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Stephen W. Jorgensen, Joshua R. McNally, Douglas Pennell, Donald Gauthier, Pawel Matys, Marc Paskin, Thomas R. Ruck, Peter John Stuttaford, Bernard Tam-Yen Sam