公开(公告)号：US12123324B2

公开(公告)日：2024-10-22

申请号：US18343013

申请日：2023-06-28

Applicant: GENERAL ELECTRIC COMPANY ,  General Electric Company Polska Sp. z o.o.

Inventor： Elzbieta Kryj-Kos ,  Piotr Jerzy Kulinski ,  Pawel Adam Lewicki ,  Ruolong Ma ,  Wendy Wenling Lin ,  Patrick Keene Clements

IPC: F01D9/02

CPC classification number: F01D9/02 ,  F05D2230/31 ,  F05D2240/121 ,  F05D2250/185

Abstract: A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.

公开(公告)号：US12091989B2

公开(公告)日：2024-09-17

申请号：US17595008

申请日：2020-04-24

Applicant: SAFRAN ,  SAFRAN AIRCRAFT ENGINES

Inventor： Léandre Ostino ,  Pierre Guillaume Auzillon ,  Michel Slusarz ,  Patrice Eneau ,  Thomas Olivier Michel Pierre De Rocquigny ,  Romain Pierre Cariou ,  Ba-Phuc Tang ,  Adrien Bernard Vincent Rollinger ,  Vianney Simon

IPC: F01D5/18 ,  B22C9/10

CPC classification number: F01D5/187 ,  B22C9/106 ,  F05D2220/30 ,  F05D2250/185 ,  F05D2260/20 ,  F05D2260/202

Abstract: A turbine vane includes a root carrying a blade terminated by a squealer tip, the blade having intrados and extrados walls, a leading edge, a trailing edge, and a tip wall delimiting a bottom of the squealer tip, by which the intrados wall is connected to the extrados wall. The blade also includes: a serpentine median circuit, including a first radial pipe that collects air at the root and is connected by a first bend to a second radial pipe that is connected by a second bend to a third radial pipe; a cavity under the squealer tip running along the extrados wall and extending from a central region of the squealer tip to the trailing edge; and a central radial pipe collecting air at the root and extending between at least two of the three pipes of the median circuit and directly supplying the cavity under the squealer tip.

公开(公告)号：US12000304B2

公开(公告)日：2024-06-04

申请号：US18137763

申请日：2023-04-21

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Yusuke Izumi ,  Yasuo Miyahisa ,  Shunsuke Torii

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/127 ,  F05D2250/185 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A turbine blade includes: a blade body; and a plurality of cooling passages each extending inside the blade body along a blade height direction and are connected to each other via return portions disposed at an end portion in the blade height direction to form a serpentine passage. The cooling passages include: an upstream passage disposed on an upstream side in a flow of a cooling fluid among the plurality of cooling passages; a downstream passage disposed on a downstream side in the flow of the cooling fluid among the plurality of cooling passages; and at least one intermediate passage disposed between the upstream passage and the downstream passage among the plurality of cooling passages. The upstream passage is disposed closest to a leading edge in a chord direction of the blade body among the plurality of cooling passages formed inside the blade body and extending along the height direction.

公开(公告)号：US11970954B2

公开(公告)日：2024-04-30

申请号：US17971938

申请日：2022-10-24

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  David R. Pack

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/188 ,  F01D5/141 ,  F05D2220/323 ,  F05D2240/301 ,  F05D2240/35 ,  F05D2250/185

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.

公开(公告)号：US20190101011A1

公开(公告)日：2019-04-04

申请号：US16089598

申请日：2016-03-31

Applicant: Siemens Aktiengesellschaft

Inventor： Jan H. Marsh ,  Paul A. Sanders ,  Evan C. Landrum

IPC: F01D5/18 ,  F01D9/04

CPC classification number: F01D5/189 ,  F01D5/186 ,  F01D5/188 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/127 ,  F05D2240/24 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2260/2212

Abstract: An airfoil (10) includes at least one internal cooling channel (A-F) extending in the radial direction and adjoined on opposite sides by an airfoil pressure sidewall (16) and an airfoil suction sidewall (18). An internal surface (16a) of the airfoil pressure sidewall (16) and an internal surface (18a) of the airfoil suction sidewall (18) define heat transfer surfaces in relation to a coolant flowing through the internal cooling channel (A-F). A flow splitter feature (90) is located in a flow path of the coolant in the internal cooling channel (A-F) between the pressure and suction sidewalls (16, 18). The flow splitter feature (90) is effective to create a flow separation region downstream of the flow splitter feature (90), whereby coolant flow velocity is locally increased along the internal surfaces (16a, 18a) of the pressure and suction sidewalls (16, 18).

公开(公告)号：US20180245472A1

公开(公告)日：2018-08-30

申请号：US15919253

申请日：2018-03-13

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Gina Cavallo

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2240/20 ,  F05D2250/184 ,  F05D2250/185 ,  F05D2250/75 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a wall that extends about a cooling cavity. The cooling cavity is a dual-fed cavity that is fed from at least two different locations. A rib separates the cooling cavity into a first portion and a second portion that is fluidly isolated from the first portion. The component is an airfoil. The first portion is fed with a first cooling fluid from a first coolant source, and the second portion is fed with a second, different cooling fluid from a second coolant source. The first and second coolant sources are separate and distinct from the component.

公开(公告)号：US10036258B2

公开(公告)日：2018-07-31

申请号：US14654676

申请日：2013-03-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dominic J. Mongillo ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Joel H. Wagner ,  Thomas N. Slavens

IPC: F01D5/18 ,  F01D5/14 ,  F01D11/08 ,  F01D9/02 ,  F01D25/24 ,  F02C7/18 ,  F01D25/08 ,  B23P15/26 ,  B22F3/105 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00

CPC classification number: F23R3/002 ,  B22F3/1055 ,  B23P15/26 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00 ,  F01D5/147 ,  F01D5/18 ,  F01D5/183 ,  F01D5/184 ,  F01D5/186 ,  F01D5/187 ,  F01D9/02 ,  F01D11/08 ,  F01D25/08 ,  F01D25/12 ,  F01D25/24 ,  F02C7/18 ,  F05D2250/185 ,  F05D2260/204 ,  F23R2900/03043 ,  Y10T29/49318 ,  Y10T29/49337 ,  Y10T29/49343 ,  Y10T29/49352 ,  Y10T428/249921

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure.

公开(公告)号：US09995148B2

公开(公告)日：2018-06-12

申请号：US13800426

申请日：2013-03-13

Applicant: General Electric Company

Inventor： Stephen Mark Molter ,  Steven Robert Brassfield ,  Shawn Michael Pearson ,  Mark Edward Stegemiller

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/18 ,  F01D5/186 ,  F01D5/188 ,  F05D2250/185 ,  F05D2260/20 ,  F05D2260/202 ,  F05D2260/203 ,  F05D2260/2212 ,  Y02T50/67 ,  Y02T50/676

Abstract: Apparatuses and methods are taught for cooling a turbine blade wherein at least one circuit is isolated along a cool suction side of the blade and the circuit turns aft toward a trailing edge.

公开(公告)号：US09976425B2

公开(公告)日：2018-05-22

申请号：US14977124

申请日：2015-12-21

Applicant: General Electric Company

Inventor： David Wayne Weber ,  Mehmet Suleyman Ciray ,  Jacob Charles Perry, II

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/187 ,  F01D5/147 ,  F05D2220/30 ,  F05D2240/127 ,  F05D2250/185 ,  F05D2260/22141

Abstract: A turbine blade cooling system according to an embodiment includes: a first turn for redirecting a first flow of gas flowing through a first channel of a turbine blade into a central plenum of the turbine blade; and a second turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum; wherein the first turn is offset from the second turn to reduce impingement of the first flow of gas and the second flow of gas in the central plenum.

公开(公告)号：US20180112539A1

公开(公告)日：2018-04-26

申请号：US15334454

申请日：2016-10-26

Applicant: General Electric Company

Inventor： David Wayne Weber ,  Robert Peter Hanet ,  Gregory Thomas Foster ,  Brendon James Leary

IPC: F01D5/18 ,  F02C3/04 ,  F01D5/14

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D9/041 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2240/35 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/205

Abstract: A trailing edge cooling system for a multi-wall blade, including: a set of outward legs extending toward a trailing edge of the multi-wall blade and fluidly coupled to a coolant feed; a set of return legs extending away from the trailing edge of the multi-wall blade and fluidly coupled to a coolant collection passage; and a connecting system for fluidly coupling the set of outward legs and the set of return legs; wherein the set of outward legs is radially offset from the set of return legs along a radial axis of the multi-wall blade.