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公开(公告)号：US20220243599A1
公开(公告)日：2022-08-04
申请号：US17568025
申请日：2022-01-04
发明人： Iurii GOROSHCHAK , Jin Bong HA
IPC分类号： F01D5/32
摘要： A rotary machine is provided. The rotary machine includes a rotor disk including a plurality of slots, a plurality of blades mounted on an outer circumferential surface of the rotor disk, each of the blades having a root part inserted into an associated one of the slots, and a retainer restraining axial movement of the plurality of blades, wherein the retainer includes an inner fixing member inserted into a bottom of the slot, an outer fixing member inserted into a lower surface of the root part to abut against the inner fixing member, and a spacer inserted between the outer fixing member and the bottom of the slot to prevent the outer fixing member from being separated.
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公开(公告)号：US11319824B2
公开(公告)日：2022-05-03
申请号：US17044828
申请日：2019-04-16
发明人： Harald Hoell , Kevin Kampka , Peter Schröder
摘要： A rotor for a gas turbine having a rotor disk on which there are a plurality of rotor components distributed around the circumference. The rotor disk has a circumferential securing shoulder with a contact face. Retaining faces come to bear against the contact face, each of the retaining faces have a retaining shoulder of the respective rotor component and are designed with a form that complements the contact face. In order to optimize the bearing stresses between the retaining shoulder and the securing shoulder, the retaining face has a smaller radius than the contact face, namely the retaining radius is at least 0.99 times and at most 0.995 times the contact radius. Also provided is an axially extending aperture in the rotor component, the width of which in the circumferential direction is 25% to 75% of the rotor component width in the circumferential direction.
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公开(公告)号：US11306735B2
公开(公告)日：2022-04-19
申请号：US16654496
申请日：2019-10-16
摘要： A turbine nozzle includes an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US11209012B2
公开(公告)日：2021-12-28
申请号：US16393577
申请日：2019-04-24
发明人： Laurent Jablonski , Philippe Gérard Edmond Joly , Christophe Perdrigeon , Damien Merlot , Hervé Pohier
IPC分类号： F04D29/32 , F01D5/34 , F01D5/14 , F01D5/30 , F01D5/32 , F04D19/00 , F04D29/02 , F04D29/053 , F04D29/38
摘要： The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream at the radially inner ends of the leading edges of the fan blades, divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.
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5.发明授权公开(公告)号：US11174743B2
公开(公告)日：2021-11-16
申请号：US16723183
申请日：2019-12-20
摘要： An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a blade track segment. The assembly includes a mounting system for coupling the blade track segment to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.
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公开(公告)号：US11053805B2
公开(公告)日：2021-07-06
申请号：US16234481
申请日：2018-12-27
发明人： Joo Hwan Kwak
摘要： A vane ring assembly capable of preventing vibration of a vane, and wear damage caused thereby, by fixing the vane to a ring through a strong contact therebetween. The vane ring assembly includes a retaining ring having an inner peripheral surface in which a dovetail groove is formed; a vane including a dovetail inserted into the dovetail groove and an airfoil protruding from the dovetail in a radial direction of the retaining ring; and a locking key disposed between the dovetail and the dovetail groove and configured to press the dovetail into the dovetail groove. A method of assembling the vane ring assembly includes steps of inserting the dovetail into the dovetail groove; and forcibly pushing the locking key between the dovetail groove and the bottom surface of the dovetail.
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公开(公告)号：US10968745B2
公开(公告)日：2021-04-06
申请号：US16506991
申请日：2019-07-09
发明人： Victor Shemyatovskiy
摘要： A turbine, a gas turbine, and a method of disassembling turbine blades, capable of ensuring stable sealing performance as well as facilitating disassembly of turbine blades are provided. The turbine may include a rotor disk including a plurality of slots formed therein, a plurality of turbine blades spaced apart from each other by a predetermined distance in a circumferential direction of the rotor disk on an outer peripheral surface, each of the turbine blades being inserted into an associated one of the slots, and a retainer sealing a cooling passage defined between the rotor disk and the turbine blade, wherein the turbine blade includes an airfoil-shaped blade part, a root part inserted into the rotor disk, and a platform part located between the blade part and the root part, and the root part includes a blade hook protruding therefrom to support the retainer.
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公开(公告)号：US10738626B2
公开(公告)日：2020-08-11
申请号：US15791469
申请日：2017-10-24
摘要： A turbine engine including: rotor blades circumferentially arrayed about a rotor wheel; a connection assembly by which each of the rotor blades connects to the rotor wheel, the connection assembly including: an axially oriented slot formed through a perimeter face of the rotor wheel; a root of the rotor blade installed within the slot, the root being shaped in relation to the slot such that the installation therein forms an axially extending shim cavity between opposing exterior surfaces of the root and the slot; and a shim installed within the shim cavity for restraining movement of the rotor blade relative to the rotor wheel in a radial direction.
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公开(公告)号：US10598033B2
公开(公告)日：2020-03-24
申请号：US15509063
申请日：2015-09-03
摘要： Relates to a vane for a turbomachine. The vane (12′) has a blade (13′) and a root (18′) to be engaged in an axial groove in a disc of the turbomachine. The upstream end (450′) of the root is connected to a radially internal end (430′) of the leading edge (431′) of the blade by the upstream end of a connecting zone having a discontinuity towards the downstream end, so that said radially internal end of the leading edge of the blade is situated further downstream than the upstream end of the root.
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公开(公告)号：US10570756B2
公开(公告)日：2020-02-25
申请号：US15547630
申请日：2016-01-19
发明人： Uwe Sieber , Dimitri Zelmer
摘要： A closing assembly for closing a blade ring inserted into a circumferential T-groove of a blade support of a turbomachine, having two insertion elements, each has a C-shaped basic form having a resting leg, retention leg, and connection leg connecting the resting leg and the retention leg and is designed to reach around a ridge of the T-groove. The resting leg reaches over the ridge and the retention leg reaches under the ridge, and an intermediate element, is positioned between the insertion elements to prevent the insertion elements from moving to the center of the T-groove. The intermediate element reaches below the retention legs of the insertion elements in the assembled state, and a positioning element is associated with the intermediate element, which is supported between the groove base of the T-groove and the intermediate element and to position the intermediate element at a desired distance from the groove base.
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