公开(公告)号：US12116904B2

公开(公告)日：2024-10-15

申请号：US17597982

申请日：2020-07-29

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Bertrand Guillaume Robin Pellaton ,  Lucas Benassis

IPC: F01D5/22 ,  F01D11/00 ,  F01D11/10 ,  F01D11/12

CPC classification number: F01D5/22 ,  F01D5/225 ,  F01D11/001 ,  F01D11/10 ,  F01D11/122 ,  F01D11/127 ,  F05D2220/323 ,  F05D2240/55 ,  F05D2250/283

Abstract: Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for receiving a first minor gas flow (f1), this circuit (16) comprising a supply cavity (17) opening at the root (9) via at least one inlet opening (18), characterised in that the circuit (16) comprises at least two channels (19) connected with the supply cavity (17) and each opening on an outer surface of the first seal (14) via a discharge opening such that a gas jet (J) of the first minor gas flow (f1) is capable of being discharged from each discharge opening, each channel (19) being oriented such that the corresponding gas jet (J) is capable of being projected towards a second minor gas flow (f2) escaping between the heel (8) and a directly adjacent member (22).

公开(公告)号：US12055047B2

公开(公告)日：2024-08-06

申请号：US17781219

申请日：2020-12-01

Applicant: MTU Aero Engines AG

Inventor： Alexander Klötzer

IPC: F01D11/12

CPC classification number: F01D11/127 ,  F05D2220/323 ,  F05D2240/55 ,  F05D2250/283

Abstract: The invention relates to a seal carrier for a turbomachine, in particular a gas turbine, having a carrier base and at least one seal body, wherein the at least one seal body is connected to the carrier base, and wherein the at least one seal body is formed by a plurality of cavities arranged next to one another, in particular uniformly, in the peripheral direction and in the axial direction, wherein the cavities extend out from the carrier base in the radial direction and are delimited by a cavity wall. According to the invention, the seal body has a plurality of damping portions which are designed to locally damp or disrupt the flow of force in the seal body, wherein the carrier base is continuous in the region of the damping portions.

公开(公告)号：US20230296032A1

公开(公告)日：2023-09-21

申请号：US18079133

申请日：2022-12-12

Applicant: ITP NEXT GENERATION TURBINES S.L.

Inventor： Roderick M TOWNES ,  Joseba LEORRI LÓPEZ

IPC: F01D25/14 ,  F01D9/04 ,  F01D11/12

CPC classification number: F01D25/14 ,  F01D9/041 ,  F01D11/127 ,  F05D2240/14 ,  F05D2240/55 ,  F05D2260/22141

Abstract: A turbine arrangement includes a turbine rotor arrangement, a turbine seal arrangement and a turbine outlet stator vane arrangement. Turbine rotor arrangement includes a rotor and a plurality of turbine blades that extend radially. Each turbine blade has a turbine shroud. Turbine seal arrangement is spaced radially around the turbine shrouds. Turbine outlet stator vane arrangement includes radially inner and outer annular members arranged coaxially and a plurality of vanes extending radially between the radially inner and outer annular members. The vanes are arranged downstream of the turbine blades. Liner is spaced radially inwardly from a radially inner surface of the annular member to define a chamber. Turbine shrouds and the upstream end of the liner are arranged such that in operation any leakage flow of gas between the turbine shrouds and the turbine seal arrangement flows into the chamber to manage the temperature of the radially outer annular member.

公开(公告)号：US20180355745A1

公开(公告)日：2018-12-13

申请号：US15974821

申请日：2018-05-09

Applicant: General Electric Company

Inventor： Paul MATHEW ,  Mohandas NAYAK ,  Krishnendu SAHA ,  Deoras PRABHUDHARWADKAR

IPC: F01D11/12 ,  F01D11/00 ,  B22F7/08 ,  B22F1/00

CPC classification number: F01D11/125 ,  B22F1/0059 ,  B22F7/08 ,  B22F2301/15 ,  B22F2302/45 ,  B22F2998/10 ,  B22F2999/00 ,  F01D11/001 ,  F01D11/127 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/40 ,  F05D2300/224 ,  F05D2300/228 ,  F05D2300/43 ,  B22F7/04 ,  B22F7/002 ,  B22F2007/066 ,  B22F3/10

Abstract: A filled abradable seal component, an associated method of manufacturing, and a turbomachine including the filled abradable seal component are disclosed. The method includes positioning the abradable seal component including a plurality of honeycomb cells, applying a filler material on the abradable seal component to fill the plurality of honeycomb cells, and curing the filler material at a temperature below 250 degrees Celsius to produce the filled abradable seal component. The filler material includes an abradable material, a binder material, and a fluid catalyst. The abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate. The fluid catalyst includes a solvent having hydroxyl groups.

公开(公告)号：US10012101B2

公开(公告)日：2018-07-03

申请号：US14574846

申请日：2014-12-18

Applicant: ANSALDO ENERGIA IP UK LIMITED

Inventor： Carlos Simon-Delgado ,  Christoph Didion ,  Marc Widmer ,  Martin Schaefer ,  Guenter Filkorn

IPC: F01D11/18 ,  F01D11/00 ,  F01D11/02 ,  F01D11/12

CPC classification number: F01D11/18 ,  F01D11/001 ,  F01D11/025 ,  F01D11/122 ,  F01D11/127 ,  F05D2250/283

Abstract: The invention pertains to a seal system for a passage between a turbine stator and a turbine rotor, including: a first arm extending radially outwards from the turbine rotor and toward the first seal arranged on the stator, and terminating short of the first seal thereby creating a first gap between the first seal and the first arm. The seal system further includes a second seal arranged on the turbine stator, and a second arm extending axially from the turbine rotor towards the second seal base, and terminating short of the second seal thereby creating a second gap between the second seal and the second arm. The invention further refers to a gas turbine including such a seal system.

公开(公告)号：US09926800B2

公开(公告)日：2018-03-27

申请号：US15188108

申请日：2016-06-21

Applicant: General Electric Company

Inventor： Xiaoqing Zheng ,  Bernard Arthur Couture, Jr. ,  Michael John Bowman ,  William Edward Adis ,  Michael Dennis Mack ,  Kim James Clark

IPC: F16J15/3288 ,  F01D11/12 ,  F01D11/00

CPC classification number: F01D11/127 ,  F01D11/001 ,  F05D2220/31 ,  F05D2220/32 ,  F05D2240/56 ,  F16J15/3288 ,  Y02T50/672

Abstract: A seal includes a housing having a back plate and a front plate. A supporting bristle layer is disposed adjacent to the back plate, and bristles in the supporting bristle layer have a first diameter. A sealing bristle layer is disposed adjacent to the supporting bristle layer, and bristles in the sealing bristle layer have a second diameter. A shielding/protecting bristle layer is disposed adjacent to the sealing bristle layer, and bristles in the shielding/protecting bristle layer have a third diameter. The second diameter is smaller than both the first diameter and the third diameter.

公开(公告)号：US09903217B2

公开(公告)日：2018-02-27

申请号：US14852032

申请日：2015-09-11

Applicant: ROLLS-ROYCE PLC

Inventor： Jeffrey Allen ,  Adrian Wright ,  Anthony Grassby ,  Barry Lowe ,  Kevin O'Sullivan ,  Philip Carroll ,  Philip Gordon Minion

IPC: F01D11/12 ,  B23K26/342 ,  F01D25/12 ,  F16J15/44

CPC classification number: F01D11/12 ,  B23K26/342 ,  F01D11/122 ,  F01D11/127 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/234 ,  F05D2230/30 ,  F05D2240/55 ,  F16J15/44

Abstract: A sealing element for positioning radially outwardly of aerofoil blades of a gas turbine engine is provided. A radially inner surface region of the sealing element includes a seal structure having one or more inwardly projecting walls formed by additive layer, powder fed, laser weld deposition. The walls form a plurality of curved profile shapes which are arranged in a repeating pattern across the radially inner surface region. None of the walls intersects with any other wall. The curved profile shapes have no radii of curvature less than 0.5 mm.

公开(公告)号：US09879786B2

公开(公告)日：2018-01-30

申请号：US14418231

申请日：2013-08-23

Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.

Inventor： Yoshihiro Kuwamura ,  Koichi Ishizaka ,  Yoshiyuki Okabe ,  Kazuyuki Matsumoto ,  Hiroharu Oyama ,  Hidekazu Uehara ,  Yoshinori Tanaka ,  Shin Nishimoto

IPC: F01D11/08 ,  F16J15/3292 ,  F16J15/447 ,  F16J15/44 ,  F01D11/12 ,  F15D1/10 ,  F01D5/22

CPC classification number: F16J15/3292 ,  F01D5/225 ,  F01D11/08 ,  F01D11/127 ,  F05D2240/59 ,  F15D1/10 ,  F16J15/444 ,  F16J15/447

Abstract: A rotary machine includes turbine moving blades (50); a casing (10) covering the turbine moving blades (50) so as to define a gap at an outer circumferential side of the turbine moving blades; a leaf seal (70) having a seal body (71) that is disposed in the gap so as to protrude radially inward from the casing (10) and is capable of coming into contact with the turbine moving blades (50), and a high-pressure-side plate member (73) that is disposed along a face facing a high pressure side of the seal body (71); and a swirling flow inhibitor (80) that is provided on the high pressure side of the leaf seal (70) in the gap and inhibits a swirl flow flowing through the gap in a circumferential direction.

公开(公告)号：US09822659B2

公开(公告)日：2017-11-21

申请号：US14289188

申请日：2014-05-28

Applicant: Mitsubishi Hitachi Power Systems, Ltd.

Inventor： Hideyuki Arikawa ,  Tadashi Kasuya ,  Yoshitaka Kojima ,  Yasuyuki Watanabe ,  Tadashi Murakata ,  Kunihiro Ichikawa ,  Takumi Konrai

IPC: F01D11/12

CPC classification number: F01D11/127 ,  F05D2250/283

Abstract: A gas turbine includes a compressor, a combustor, and a turbine. The turbine includes a honeycomb seal disposed so as to be secured to a casing side in a clearance between the casing and turbine blades rotating around a rotating shaft and a seal fin that is provided on an end face of each of the turbine blades facing the honeycomb seal. The seal fin extends in a direction perpendicular to the rotating shaft. The honeycomb seal is formed by a plurality of corrugated sheet metals overlapped with each other at walls of nodes thereof and the walls of the nodes are blazed with each other. Each of the corrugated sheet metals has trapezoids formed in alternating fashion. A longer direction of each wall of the nodes of the honeycomb seal is angled with respect to the rotational direction of the turbine blades.

公开(公告)号：US09810644B2

公开(公告)日：2017-11-07

申请号：US15255808

申请日：2016-09-02

Applicant: ROLLS-ROYCE plc

Inventor： Najib Bin Mohamed Salleh ,  João Paulo Siqueira Cezario

IPC: G01N21/00 ,  G01N21/956 ,  F01D11/12 ,  G01N1/28 ,  G01N21/88 ,  G01M13/00

CPC classification number: G01N21/95692 ,  F01D11/127 ,  F05D2220/32 ,  F05D2260/83 ,  F05D2270/8041 ,  G01M13/005 ,  G01N1/28 ,  G01N21/8806 ,  G01N21/954

Abstract: A method of inspecting a component comprising a cellular structure bonded to a carrier substrate to form a matrix of open-ended cells is described. The method comprises: submerging the component in an inspection liquid disposed within a pressure vessel; changing the pressure within the pressure vessel; withdrawing the component from the inspection liquid; and determining whether the cells of the component are filled with the inspection liquid. A corresponding inspection apparatus is also described.