Patents Examined by Elton K Wong
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Patent number: 11536200Abstract: A non-contact seal assembly for sealing a gap between relatively rotatable components in a gas turbine engine is presented. The non-contact seal assembly includes a primary seal having a radially movable seal shoe, a mid-plate, an aft secondary seal radially movable along with the seal shoe, a forward secondary seal and a U-shaped seal carrier for holding the components together using pins. The seal shoe includes a plurality of seal shoe segments. The aft secondary seal includes a plurality of aft secondary seal segments. Each aft secondary seal segment is attached to each seal shoe segment. Each aft secondary seal segment includes at least a notch at outer radial side to receive the pin for accommodating radial movement of the seal shoe segment.Type: GrantFiled: June 5, 2020Date of Patent: December 27, 2022Assignee: Siemens Energy Global GmbH & Co. KGInventors: Amit K. Paspulati, Abdullatif M. Chehab, Kai Kadau
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Patent number: 11536147Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.Type: GrantFiled: March 30, 2021Date of Patent: December 27, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Jon E. Sobanski, Bryan P. Dube
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Patent number: 11536148Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a first platform radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the first platform radial flange. A thermal insulation element is situated adjacent the first platform radial flange. The support hardware supports the airfoil piece through the thermal insulation element.Type: GrantFiled: November 24, 2020Date of Patent: December 27, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Raymond Surace, Mark F. Zelesky
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Patent number: 11530613Abstract: The present invention provides a bladed rotor wheel for a gas turbine engine comprising at least a rotatable forged disc, the rotatable forged disc comprising a front surface and a back surface, at least one rim surface, and a plurality of projections located on at least a portion of at least one of the front or back surface and/or on the rim surface; wherein the projections are 3D printed features protruding outwards from the front, back and/or rim surface; the projections are arranged forming a pattern so that a heat transfer capability is created at the front, back and/or rim surface; and the ratio of the distance between projections to the forged disc external radius is lower than 0.15. Furthermore, the present invention also provides a method for manufacturing a rotatable forged disc for a bladed rotor wheel.Type: GrantFiled: March 29, 2021Date of Patent: December 20, 2022Assignee: ITP ENGINES UK LTDInventors: Quentin Luc Balandier, Vinod Kakade
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Patent number: 11525361Abstract: A wall of a hot gas component includes a hot and a cold-gas sided surface, one film cooling hole extending from an inlet in the cold-gas sided surface to an outlet in the hot-gas sided surface and with a metering section of constant cross-section and a diffuser section extending from the metering section. The diffuser section is bordered by a diffuser bottom and two opposing diffuser side walls, has a leading region, which extends from the metering section to the outlet, lies opposite the diffuser bottom and has a constant cross-section over its entire length corresponding to an elongation of a leading region of the metering section up to the outlet. The diffuser section has two diffuser arms dividing the flow into two subflows, generating delta-vortices, a v-shaped outlet, and a v-shaped outlet opening.Type: GrantFiled: August 28, 2018Date of Patent: December 13, 2022Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventor: Sebastian Hohenstein
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Patent number: 11525367Abstract: Assembly including a rotor disc, an adjacent stator and a plurality of sealing elements secured to the rotor disc, the stator including an inner platform and a root bearing at least one abradable element configured to cooperate with the sealing elements, the sealing elements being placed in an enclosure formed by the abradable element, the enclosure being open to the inside and delimited axially by an upstream abradable edge and a downstream abradable edge, the enclosure being delimited radially by an outer abradable edge, at least one of the sealing elements including a first lip configured to cooperate with the upstream abradable edge or the downstream abradable edge, and a second, separate lip configured to cooperate with the outer abradable edge.Type: GrantFiled: November 6, 2019Date of Patent: December 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Xavier Trappier, Joao Antonio Amorim, Maxime Aurelien Rotenberg
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Patent number: 11525366Abstract: The invention concerns a flow straightener unit (1) for a fan module of a turbomachine, the straightener unit (1) comprising a plurality of blades (2) distributed about an axis of rotation, each blade (2) is made of a composite material and comprises an aerofoil (21) and a root (22) intended to be assembled on a hub (4) of the turbomachine. The unit (1) comprises a centring and attachment plate (3) of the blade (2) on the turbomachine intended to be attached to the hub (4) at a determined azimuthal position and to the root (22) of the blade (2), the plate (3) is designed to be screwed to the hub (4) by screws (51a) that are longitudinal with respect to the axis of rotation of the unit (1) and screwed to the root (22) of the blade (2) by screws (52) that are radial with respect to the axis of rotation of the unit (1).Type: GrantFiled: November 8, 2019Date of Patent: December 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Alexandre Bernard Marie Boisson, Kaëlig Merwen Orieux
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Patent number: 11525456Abstract: An axial fan has an inner-rotor motor which includes a drive end, a non-drive end and a shaft which extends axially from the drive end; and an impeller which includes a cylindrical impeller cup and a number of impeller blades that extend radially from the impeller cup. The impeller cup has an open upstream end and a closed downstream end which is connected to the shaft. In operation, the motor spins the impeller to generate an airflow in a direction from the non-drive end of the motor to the drive end of the motor. The impeller cup is configured to receive the motor therein and surround the drive end of the motor but not the non-drive end of the motor. As a result, the non-drive end of the motor is exposed to the airflow during operation of the fan.Type: GrantFiled: July 8, 2016Date of Patent: December 13, 2022Assignee: Bascom Hunter Technologies, Inc.Inventors: John Decker, Ralph Carl, David Gonzales Campos
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Patent number: 11525365Abstract: A front fan turbomachine includes an annular separating wall having a slat for separating an air flow between a primary flow and a secondary flow, the slat having a leading edge; inlet guide vanes (IGV) for guiding the primary flow and outlet guide vanes (OGV) blades for guiding the secondary flow. The leading edge of the slat has a serrated profile having a succession of teeth and depressions.Type: GrantFiled: February 15, 2019Date of Patent: December 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Fernando Gea Aguilera, Matthieu Fiack, Mathieu Simon Paul Gruber
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Patent number: 11519274Abstract: The invention relates to an assembly for a turbomachine (1) extending about an axis (X) comprising: —an inner annular platform (13) and an outer annular platform (14) delimiting a flow channel (3) for a flow flowing from upstream to downstream, and —at least one fixed blade (12) extending radially between the inner annular platform (13) and the outer annular platform (14), said fixed blade (12) being profiled with a leading edge (15), characterized in that the inner annular platform (13) and/or the outer annular platform (14) comprises, upstream of the leading edge (15) of the fixed blade (12), a furrow (21) for channeling the fluid flowing in the channel (3), having a segment forming an upstream limit (22) and a segment forming a downstream limit (23), the length of the upstream limit (22) being greater than the length of the downstream limit (23).Type: GrantFiled: August 19, 2019Date of Patent: December 6, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventor: Vianney Christophe Marie Maniere
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Patent number: 11519283Abstract: A component for a gas turbine engine includes a component body formed of ceramic matrix composite lamina and has at least one hook. The at least one hook has an attachment region radially inward of the at least one hook. The attachment region is radially thinner from a hook end of the at least one hook to a remote end, and then becomes radially thicker. A slot is formed through a radial thickness of the at least one hook from the hook end in a remote direction, such that there are two sections of the attachment region. A gas turbine engine is also disclosed.Type: GrantFiled: March 25, 2021Date of Patent: December 6, 2022Assignee: Raytheon Technologies CorporationInventors: Carson A. Roy Thill, Thomas E. Clark, Danielle Mahoney, Andrew D. Keene
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Patent number: 11519280Abstract: A vane assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart radially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends radially between and interconnects the outer platform and the inner platform.Type: GrantFiled: September 30, 2021Date of Patent: December 6, 2022Inventors: Robert S. Bainbridge, Oliver D. A. O'Carroll, Afzal Ali, Rachel Woodfield, Michael J. Whittle
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Patent number: 11512605Abstract: The invention relates to an assembly comprising a turbomachine casing (7) and a nozzle made of ceramic matrix composite material having a blade (21), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part (31) of the nozzle to the casing (7), said connecting part (31) extending substantially radially outwards, the blade (21) and said connecting part (31) being formed in one piece, said assembly being characterized in that the connecting part (31) is fastened to a first radial wall (51) integral with the casing (7) by fastening means (53).Type: GrantFiled: July 31, 2019Date of Patent: November 29, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Matthieu Arnaud Gimat, Lucien Henri Jacques Quennehen, Gilles Gérard Claude Lepretre, Nicolas Paul Tableau
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Patent number: 11506069Abstract: A vane arc segment includes an airfoil fairing that has an airfoil wall that defines a fairing platform and a hollow airfoil section. A spar has a spar platform adjacent the fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg is spaced from the airfoil wall in the hollow airfoil section such that there is a first gap. The spar platform is spaced from the fairing platform such that there is a second gap. A support platform is secured to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform. There is a spring seal between the spar platform and the fairing platform. The spring seal biases the airfoil fairing toward the support platform and seals the first gap from the second gap.Type: GrantFiled: March 3, 2021Date of Patent: November 22, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Robert A. White, III, Benjamin B. Simpson
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Patent number: 11499432Abstract: A method of altering the twisting relationship for the aerodynamic surface of a fan blade of a gas turbine engine, wherein the following steps are performed: establishing, for a portion of the aerodynamic surface of the fan blade, an alteration relationship defined by variation of a pitch angle of the blade as a function of radial height along the blade, the alteration relationship including alterations that are each defined by a height along with the radial height of the fan blade and by an amplitude; and applying the alteration relationship as established in this way to an initial twisting relationship of the fan blade so as to obtain an altered twisting relationship for the fan blade, the initial twisting relationship being defined by a polynomial for the radial height of the fan blade as a function of its pitch angle.Type: GrantFiled: July 1, 2016Date of Patent: November 15, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vivien Mickaël Courtier, Adrien Louis Nicolas Laurenceau, Dominique Gerhadt Mayhew, Jonathan Evert Vlastuin
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Patent number: 11499447Abstract: A gas turbine engine has: an engine shaft rotatable about a rotation axis; at least two bearings spaced apart from one another along the rotation axis, the at least two bearings having inner races for rotation with the engine shaft, outer races, and rolling elements disposed radially between the inner races and the outer races; a bearing support extending axially along the rotation axis from one of the at least two bearings to the other, the bearing support secured to both of the outer races of the at least two bearings, the bearing support secured to a structural case of the gas turbine engine via frangible tabs.Type: GrantFiled: January 15, 2020Date of Patent: November 15, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Guy Lefebvre, François Doyon
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Patent number: 11499441Abstract: A compressor stator vane unit includes multiple compressor stator vanes disposed at a certain interval in a circumferential direction; and an annular joint member connected with inner ends of the multiple compressor stator vanes; wherein the annular joint member constitutes an outer diameter side surface of a leakage fluid flow path provided in an inner diameter side of the joint member to communicate a high-pressure space with a low-pressure space respectively located downstream and upstream of the multiple compressor stator vanes in a fluid flow direction, and D/P is set to 0.05?D/P?0.2, wherein D is defined as a distance in an axial direction between an upstream end surface of the annular joint member and an upstream edge of the multiple compressor stator vanes in the fluid flow direction and P is defined as a pitch between the adjacent compressor stator vanes in the circumferential direction.Type: GrantFiled: February 11, 2020Date of Patent: November 15, 2022Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventor: Ryosuke Seki
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Patent number: 11492919Abstract: A vane segment includes a blade ring, a plurality of vanes, and a caulking member. The blade ring includes a blade ring groove and a storage space forming portion. The blade ring groove includes a convex portion projecting from a second groove side surface of the blade ring groove to the first side. The storage space forming portion, in combination with an outer shroud, forms a storage space into which the caulking member enters. The caulking member is accommodated within the storage space, contacts with the blade ring groove and the outer shroud, and is exposed from an inner opening of the storage space.Type: GrantFiled: October 23, 2018Date of Patent: November 8, 2022Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Yuichiro Waki, Shouhei Danno, Yuki Yamamoto
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Patent number: 11480064Abstract: A turbine of a turbo engine includes a casing and a nozzle stage including an outer metal shroud secured to the casing, an inner metal shroud, and a plurality of ring sectors made of ceramic-matrix composite material each having an internal platform, an external platform and at least one blade extending between the external platform and the internal platform and secured thereto. The internal platform of each sector includes a first and a second tab protruding radially inwardly from respectively an upstream end and a downstream end of the internal platform, and the inner shroud includes a shoulder protruding radially outwardly and being in abutment upstream against the first tab, and a clamp downstream of the shoulder including two jaws extending radially outwardly and held under stress towards each other against the second tab.Type: GrantFiled: April 15, 2019Date of Patent: October 25, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Jarrossay, Sébastien Serge Francis Congratel, Antoine Claude Michel Etienne Danis, Clément Jean Pierre Duffau, Lucien Henri Jacques Quennehen
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Patent number: 11473435Abstract: A vane for a turbine engine turbine includes a blade and at least one platform that radially extends the blade, and a system for reducing vortices including at least one circuit including a duct extending from at least one air intake orifice formed in the platform upstream of the leading edge as far as at least one air exhaust slot formed on the trailing edge.Type: GrantFiled: June 14, 2019Date of Patent: October 18, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Ludovic Pintat, Eric Roger Schwartz