Varying dilution hole design for combustor liners
Granted: December 10, 2024
Patent Number:
12163660
A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.
Leading edge protection for a wind turbine blade
Granted: December 10, 2024
Patent Number:
12163502
A wind turbine blade includes a leading edge protection element attached to the leading edge of the wind turbine blade. The leading edge protection element extends in a longitudinal direction between an outboard end and an inboard end and includes an attachment surface mounted to an exterior surface of the blade, an exterior surface opposite the attachment surface, a first section extending from the leading edge and along a part of the pressure side of the wind turbine blade to a first…
Additive manufacturing build units with process gas inertization systems
Granted: December 10, 2024
Patent Number:
12162221
A build unit for additively manufacturing three-dimensional objects may include an energy beam system having one or more irradiation devices respectively configured to direct one or more energy beams onto a region of a powder bed, and an inertization system including an irradiation chamber defining an irradiation plenum, one or more supply manifolds, and a return manifold. The one or more supply manifolds may include a downflow manifold configured to provide a downward flow of a process…
Systems and methods for direct laser melting of metals using non-diffracting laser beams
Granted: December 3, 2024
Patent Number:
12158597
A system includes a first group of optic lenses within a focusing unit positioned along the propagation direction of a collimated laser beam, the first group of optic lenses separated by a predetermined fixed distance. The first group of optic lenses in conjunction cause the collimated beam to form as an annular beam as it passes through the first group of optic lenses. An axicon lens located distal from the first group of optic lenses along the propagation direction, the axicon lens…
Gas turbine engine combustor with a set of dilution passages
Granted: December 3, 2024
Patent Number:
12158270
A combustor comprising a dome wall, an annular liner, a combustion chamber, a set of fuel cups, and a set of dilution passages for each fuel cup of the set of fuel cups. The set of fuel cups circumferentially spaced along the dome wall relative to the combustor centerline. The set of dilution passages terminating in a plurality of slots spaced about the corresponding fuel cup in the set of fuel cups.
Turbomachinery engines with high-speed low-pressure turbines
Granted: December 3, 2024
Patent Number:
12158113
A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
Conformal structure for a gas turbine engine
Granted: December 3, 2024
Patent Number:
12158104
A gas turbine engine is provided defining an axial direction, a radial direction, and a circumferential direction. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order; a fan section including a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an oil tank positioned within the nacelle, wherein the oil tank defines an effective length (LT) along the axial direction, a circumference…
Fairing assembly
Granted: December 3, 2024
Patent Number:
12158087
Fairing assemblies and methods for assembling gas turbine engine fairing assemblies are provided. For example, a fairing assembly comprises a plurality of fairings, an annular inner band defining a plurality of inner pockets, and an annular outer band defining a plurality of outer pockets. Each fairing has an inner end radially spaced apart from an outer end. Each inner pocket is shaped complementary to each fairing inner end and has forward and aft ends. Each outer pocket is shaped…
Turbine engine with composite airfoils
Granted: December 3, 2024
Patent Number:
12158082
A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
Method of extracting technical information from a technical manual
Granted: November 26, 2024
Patent Number:
12153598
A method of extracting information from a technical manual. The method includes extracting selected keywords from the technical manual, appending the selected keywords to a table to provide master data, receiving a portion of the master data and a first table of labels corresponding to a portion of the master data, applying a Machine Learning model or a Natural Language Processing (NLP) model to generate a second table of labels corresponding to an entire master data, processing labels…
System and method for additively printing extension segments on workpieces
Granted: November 26, 2024
Patent Number:
12151431
A method for additively printing extension segments on workpieces using an additive manufacturing machine includes controlling, with a computing system, an operation of a print head of the machine such that a region of interest of a build plate of the machine is scanned with an electromagnetic radiation beam. Additionally, the method includes receiving, with the computing system, data associated with reflections of the beam off of the build plate as the region interest is scanned.…
Method of supplying fuel and air to a combustor with an ignition tube
Granted: November 26, 2024
Patent Number:
12152780
A method of supplying a first fuel and air mixture and a second fuel and air mixture to a combustor. The combustor having a combustion chamber, a dome wall at least partially defining the combustion chamber, at least one fuel cup provided in the dome wall, and at least one ignition tube having an outlet exhausting to the combustion chamber. The method comprising supplying a first flow of compressed air to only the at least one ignition tube, igniting the first fuel and air mixture,…
Combustor
Granted: November 26, 2024
Patent Number:
12152779
A combustor having a main chamber and a trapped vortex cavity. The main chamber includes an outer liner and an inner liner. The trapped vortex cavity extends from at least one of the outer liner or the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the trapped vortex cavity to produce combustion gases. The trapped vortex cavity injects the combustion gases into the main chamber. A steam system is in fluid communication with the main chamber. The…
Combustion liner
Granted: November 26, 2024
Patent Number:
12152778
A liner for a combustor in a gas turbine engine. The liner includes a liner body having a cold side and a hot side, a dilution opening extending through the liner body, a first passage positioned adjacent the dilution opening and extending through the liner body from the cold side to the hot side, and a second passage positioned adjacent the dilution opening and extending through the liner body from the cold side to the hot side, the second passage being separate from the first passage…
Combustor for a gas turbine engine
Granted: November 26, 2024
Patent Number:
12152777
A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one…
Method for operating a wind farm and a wind farm
Granted: November 26, 2024
Patent Number:
12152567
A method for operating a wind farm having a string (S1-S3) of wind turbines (100-100c) which are electrically connectable with each other and a grid (510, 550) is disclosed. Each wind turbine includes a rotor (106) with rotor blades (108), a power conversion system (118, 210, 238) mechanically connected with the rotor (106), and at least one auxiliary subsystem (105, 109). The method includes operating the wind turbines of the string in an island operating mode in which the wind turbines…
Vibrations in wind turbines
Granted: November 26, 2024
Patent Number:
12152565
The present disclosure relates to wind turbines comprising a rotor 18 including one or more blades 20, a control module 110 configured to operate the wind turbine according to a first operational setpoint, determine an adjusted setpoint for the wind turbine at least partially based on vibrations in blades and transition to the adjusted setpoint. Further, the control module 110 is also configured to determine remaining vibrations in blades and determine a new setpoint for the wind turbine…
Turbomachinery engines with high-speed low-pressure turbines
Granted: November 26, 2024
Patent Number:
12152537
A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
Composite component modifications
Granted: November 26, 2024
Patent Number:
12152500
Composite components and methods for adding a composite material to a composite component are provided. For example, a method comprises positioning a composite material segment against the composite component to form a component layup; applying an insulating material around at least a portion of the component layup to form an insulated layup; and densifying the insulated layup, where the composite component was previously densified before positioning the composite material segment…
Sealing system including a seal assembly between components
Granted: November 26, 2024
Patent Number:
12152492
A sealing system for sealing between components. The sealing system includes a first component, a second component, and a seal assembly including a seal member. The first component includes a first component surface, and the second component includes a second component surface. The second component surface is oriented in a direction transverse to the first contact surface. The seal member has a plurality of contact surfaces including a first contact surface and a second contact surface.…
