公开(公告)号：US12005666B2

公开(公告)日：2024-06-11

申请号：US17634716

申请日：2020-08-07

Applicant: SAFRAN AERO COMPOSITE ,  SAFRAN AIRCRAFT ENGINES ,  SAFRAN AEROSPACE COMPOSITES

Inventor： Damien Vincent Le Cloarec ,  Clement Giacovelli ,  Jeffrey Steven Sherman ,  Mickaelle Lucie Alicia Thomas

IPC: B23P15/02 ,  B29D99/00 ,  G05D5/02 ,  F01D5/14

CPC classification number: B29D99/0025 ,  B23P15/02 ,  G05D5/02 ,  F01D5/141 ,  F05D2230/18 ,  Y10T29/49336 ,  Y10T29/49771

Abstract: A verification method for verifying whether the aerodynamic profile of a real blade for an aircraft turbine engine complies with a theoretical blade, the method including constructing a camber line of the theoretical blade and constructing a camber line of the real blade; constructing a relationship for the thickness of the theoretical blade and constructing a relationship for the thickness of the real blade, the thickness relationship of a blade corresponding to the curve plotting the thickness of the blade as a function of curvilinear length along the camber line from a leading edge of the blade to a trailing edge of the blade, where thickness is the dimension of the blade extending perpendicularly to the camber line at each point of the camber line; superposing the thickness relationship of the real blade on the thickness relationship of the theoretical blade; and extracting the leading-edge and trailing edge thicknesses.

公开(公告)号：US11841194B2

公开(公告)日：2023-12-12

申请号：US17257645

申请日：2019-06-24

Applicant: LINDE GMBH

Inventor： Manfred Schönberger ,  Roland Hiller ,  Christian Michael Herwerth

IPC: F28D7/02 ,  B21D11/06 ,  B21D53/06 ,  F28F9/00 ,  F28F9/013 ,  B23P15/26 ,  B23P15/02

CPC classification number: F28D7/024 ,  B21D11/06 ,  B21D53/06 ,  F28F9/005 ,  F28F9/013 ,  F28F9/0132 ,  B23P15/02 ,  F28F2265/32

Abstract: The invention relates to a device (1) for use in the production of a tube bundle (3) of a wound heat exchanger (100), wherein tubes (30) are wound in a plurality of tube layers (4) onto a core tube (300) running in an axial direction (z), webs (10) which run in the axial direction (z) being arranged between the tube layers (4). The invention further relates to a method for producing a tube bundle using said device (1).

公开(公告)号：US11708764B2

公开(公告)日：2023-07-25

申请号：US17292350

申请日：2019-10-25

Applicant: KABUSHIKI KAISHA TOYOTA JIDOSHOKKI

Inventor： Tatsuya Shimizu

IPC: F01D5/28 ,  B22F5/04 ,  B23P15/02 ,  B23P15/00 ,  B33Y40/20 ,  B22D21/00 ,  B22D25/02 ,  B22F3/105 ,  B23K101/00 ,  B23K103/14 ,  B23K26/00

CPC classification number: F01D5/28 ,  B22D21/005 ,  B22D25/02 ,  B22F3/105 ,  B22F5/04 ,  B23P15/006 ,  B23P15/02 ,  B22F2998/10 ,  B23K26/0006 ,  B23K2101/001 ,  B23K2101/006 ,  B23K2103/14 ,  F05D2220/40 ,  F05D2230/211 ,  F05D2230/234 ,  F05D2230/25 ,  F05D2300/174 ,  Y10T29/4932

Abstract: A method of manufacturing a TiAl alloy impeller includes a blank preparation step in which a blank of the TiAl alloy impeller is prepared, wherein the blank has a shaft portion and a plurality of blades, and a thickness of an outer edge of each of the blades of the blank is set so as to be larger than a thickness of an outer edge of a blade of the TiAl alloy impeller, and an additional work step in which an additional work is performed on each of the blades of the blank. In the additional work step, the additional work is performed on a first surface of a portion that includes at least the outer edge of each of the blades or the first surface and a second surface of the portion thereof.

公开(公告)号：US10071448B1

公开(公告)日：2018-09-11

申请号：US14494465

申请日：2014-09-23

Applicant: BlendTec, Inc.

Inventor： Joseph O. Jacobsen ,  C. David Voorhees ,  Thomas D. Dickson, Jr.

IPC: B23P15/02 ,  A47J43/07

CPC classification number: B23P15/02 ,  A47J43/0711 ,  A47J43/0716 ,  A47J43/0722 ,  A47J43/0727 ,  B01F7/00275

Abstract: A blade configured for use in a blending apparatus includes a body portion and a pair of wing portions extending from the body portion. At least a leading edge of the blade is forged to increase a hardness property. The leading edge may have a minimum thickness that provides a relatively blunt leading edge. The wing portions of the blade may be formed after forging the blade.

公开(公告)号：US20180223672A1

公开(公告)日：2018-08-09

申请号：US15426318

申请日：2017-02-07

Applicant: General Electric Company

Inventor： Matthew Thomas Beyer ,  Tingfan Pang

IPC: F01D5/18 ,  B22C7/02 ,  B22C9/10 ,  B22C9/24 ,  B22D25/02 ,  B22D29/00 ,  B23P15/02 ,  B23B35/00

CPC classification number: F01D5/186 ,  B22C7/02 ,  B22C9/10 ,  B22C9/24 ,  B22D25/02 ,  B22D29/002 ,  B23B35/00 ,  B23B39/161 ,  B23B2215/81 ,  B23P15/02 ,  B23P2700/06 ,  F01D5/187 ,  F05D2230/211 ,  F05D2240/304 ,  F05D2260/607 ,  Y02T50/676

Abstract: An apparatus and method for an investment casting core for forming a cast airfoil extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction, with an internal passage including at least one leach hole formed from the investment casting core.

公开(公告)号：US20180209285A1

公开(公告)日：2018-07-26

申请号：US15412710

申请日：2017-01-23

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Srikanth Chandrudu KOTTILINGAM ,  Brian Lee TOLLISON ,  Yan CUI

IPC: F01D9/06 ,  B22D21/00 ,  B22D19/00 ,  B22D17/00 ,  B33Y10/00 ,  B33Y80/00 ,  B23K1/00 ,  B23K31/02 ,  B23P15/02 ,  F01D25/00

CPC classification number: F01D9/065 ,  B22D17/00 ,  B22D19/0072 ,  B22D21/005 ,  B23K1/0018 ,  B23K31/02 ,  B23K2101/001 ,  B23P15/02 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/186 ,  F01D5/188 ,  F01D9/02 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2230/237

Abstract: A component including a channel and an insert is provided. The channel is configured to extend through a wall thickness of the component from an inner surface of the component to an outer surface of the component. The channel is defined by an inner channel surface. The insert is configured to permit flow cooling fluid such as air and has an outer insert surface corresponding to and attached to the inner channel surface. The component may be a turbine component. Also provided is a method for forming the component.

公开(公告)号：US09957842B2

公开(公告)日：2018-05-01

申请号：US14498264

申请日：2014-09-26

Applicant: ROLLS-ROYCE PLC

Inventor： Stewart Lowth ,  Christopher Faulkner

IPC: F01D5/00 ,  F01D25/28 ,  F01D5/30 ,  B23P15/02

CPC classification number: F01D25/285 ,  B23P15/02 ,  F01D5/005 ,  F01D5/3061 ,  F05D2230/10 ,  F05D2230/80 ,  Y10T29/49318

Abstract: A method of supporting a cantilevered component prior to machining the cantilevered component, wherein the cantilevered component is mounted on a hub, the method comprising the step of providing an adhesive carrier, applying adhesive to the carrier and adhering the carrier to the cantilevered component and allowing the adhesive to cure. The carrier may rigid and braced against adjacent blades or against another carrier located on an opposing side of the aerofoil. Alternatively, the carrier may be a flexible fabric that can be wrapped around the blade. Advantageously, the blade can be machined through the carrier.

公开(公告)号：US20180100210A1

公开(公告)日：2018-04-12

申请号：US15289530

申请日：2016-10-10

Applicant: General Electric Company

Inventor： Theodore Francis Majka

IPC: C21D9/00 ,  C21D6/00 ,  C21D1/52 ,  C21D1/42 ,  C21D1/18 ,  C22C38/52 ,  C22C38/44 ,  F04D29/38 ,  F04D29/02 ,  B23P15/02 ,  B21K3/04

CPC classification number: C21D9/0068 ,  B21K3/04 ,  B23P15/02 ,  C21D1/18 ,  C21D1/42 ,  C21D1/52 ,  C21D6/004 ,  C21D6/007 ,  C22C38/44 ,  C22C38/52 ,  F04D29/023 ,  F04D29/324 ,  F04D29/542 ,  F05D2230/25 ,  F05D2230/40 ,  F05D2230/41 ,  F05D2300/171 ,  Y02P10/253

Abstract: A method of manufacturing a component for a gas turbine engine. The method may include the steps of: providing a forged preform of the component that is made from a stainless steel alloy; identifying two non-overlapping portions of the component that together form a whole of the component: a target portion and a remainder portion; and treating the component with a regionally selective tempering process in which a treated region receives a tempering process while an untreated region is excluded from receiving the tempering process. The target portion may be the treated region while the remainder portion is the untreated region. The tempering process of the regionally selective tempering process may be configured to appreciably increase a hardness of the target portion of the component relative to a hardness of the remainder portion of the component.

公开(公告)号：US09919392B2

公开(公告)日：2018-03-20

申请号：US14650738

申请日：2013-12-18

Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.

Inventor： Kohei Hatano ,  Hiroharu Oyama ,  Motonari Machida ,  Hidetaka Haraguchi ,  Ken Ishii ,  Keisuke Kamitani ,  Takumi Matsumura ,  Takahiro Ota

IPC: B23P15/02 ,  B21K3/04 ,  F01D5/14

CPC classification number: B23P15/02 ,  B21K3/04 ,  F01D5/141 ,  F05D2220/31 ,  F05D2230/25

Abstract: A method for manufacturing a turbine rotor blade wherein warping, bending and twisting of the entire rotor blade, which is provided with an excess thickness portion after a forging step, can be suppressed. In the forging step in a process for manufacturing a rotor blade (23), the forging is hot-forged such that the distance (the excess thickness amount) from the blade surface of the blade section (23) to the surface of the excess thickness section is substantially uniform along the entire periphery of a cross section of the blade section (23) and the excess thickness section (31) perpendicular to the blade length direction, and such that the amount of the excess thickness in the blade length direction, which is the thickness of the excess thickness section (31), gradually increases toward the blade tip from a prescribed position.

公开(公告)号：US09896948B2

公开(公告)日：2018-02-20

申请号：US14133140

申请日：2013-12-18

Applicant: Rolls-Royce Corporation

Inventor： Roy David Fulayter ,  Jonathan Michael Rivers

IPC: F01D5/30 ,  F01D5/00 ,  F01D5/34 ,  B23P15/02 ,  B23K20/12

CPC classification number: F01D5/3061 ,  B23K20/12 ,  B23P15/02 ,  F01D5/005 ,  F01D5/34 ,  F05D2230/239 ,  Y10T29/49318 ,  Y10T29/49336

Abstract: In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface.