公开(公告)号：US20240076993A1

公开(公告)日：2024-03-07

申请号：US18269037

申请日：2021-01-06

Applicant: SIEMENS ENERGY GLOBAL GMBH & CO. KG

Inventor： Daniel Joo ,  Ching-Pang Lee ,  Gm Salam Azad ,  Sin Chien Siw

IPC: F01D9/06 ,  F01D25/12

CPC classification number: F01D9/06 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/20

Abstract: A turbine vane in a gas turbine engine includes an inner platform, an outer platform, and a vane airfoil positioned therebetween. The vane airfoil includes a first cooling passage extending between the outer platform and the inner platform, and a second cooling passage extending between the outer platform and the inner platform. The second cooling passage is arranged downstream of the first cooling passage with respect to a flow direction. The turbine vane includes a jumper tube disposed between the second cooling passage and the inner platform. The jumper tube includes an inlet, an outlet, and a tube wall enclosing a hollow interior. The inlet is positioned a distance within the second cooling passage. The outlet is positioned at least partially through an aperture of the inner platform.

公开(公告)号：US20210301664A1

公开(公告)日：2021-09-30

申请号：US17261712

申请日：2018-07-23

Applicant: Siemens Energy Global GmbH & Co. KG

Inventor： Peter Schröder ,  Christopher W. Ross ,  Santiago R. Salazar ,  Patrick M. Pilapil ,  Roger Matthews ,  Kevin Kampka ,  Joana Verheyen ,  Ching-Pang Lee ,  Javan Albright ,  James McCoy ,  Sin Chien Siw ,  Kok-Mun Tham

IPC: F01D5/08 ,  F01D5/30

Abstract: A flow inducer assembly and a method for cooling turbine blades of a gas turbine engine are presented. The gas turbine engine includes a rotor disk having circumferentially distributed disk grooves and turbine blades. Each turbine blade includes a blade root inserted into blade mounting section of the disk groove. Seal plates are attached to aft side circumference of the rotor disk. The flow inducer assembly is integrated to each seal plate at a side facing away from the rotor disk. The flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from blade root for cooling the turbine blade.

公开(公告)号：US11415000B2

公开(公告)日：2022-08-16

申请号：US16623824

申请日：2018-06-04

Applicant: Siemens Energy Global GmbH & Co. KG

Inventor： Ching-Pang Lee ,  Jae Y. Um ,  Sin Chien Siw ,  Anthony Waywood ,  Harry Holloman ,  Steven Koester

IPC: F01D5/18 ,  B22C9/10

Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.

公开(公告)号：US12116906B2

公开(公告)日：2024-10-15

申请号：US18269037

申请日：2021-01-06

Applicant: SIEMENS ENERGY GLOBAL GMBH & CO. KG

Inventor： Daniel Joo ,  Ching-Pang Lee ,  Gm Salam Azad ,  Sin Chien Siw

IPC: F01D9/06 ,  F01D25/12

CPC classification number: F01D9/06 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/20

Abstract: A turbine vane in a gas turbine engine includes an inner platform, an outer platform, and a vane airfoil positioned therebetween. The vane airfoil includes a first cooling passage extending between the outer platform and the inner platform, and a second cooling passage extending between the outer platform and the inner platform. The second cooling passage is arranged downstream of the first cooling passage with respect to a flow direction. The turbine vane includes a jumper tube disposed between the second cooling passage and the inner platform. The jumper tube includes an inlet, an outlet, and a tube wall enclosing a hollow interior. The inlet is positioned a distance within the second cooling passage. The outlet is positioned at least partially through an aperture of the inner platform.

公开(公告)号：US11377956B2

公开(公告)日：2022-07-05

申请号：US17261712

申请日：2018-07-23

Applicant: Siemens Energy Global GmbH & Co. KG

Inventor： Peter Schröder ,  Christopher W. Ross ,  Santiago R. Salazar ,  Patrick M. Pilapil ,  Roger Matthews ,  Kevin Kampka ,  Joana Verheyen ,  Ching-Pang Lee ,  Javan Albright ,  James McCoy ,  Sin Chien Siw ,  Kok-Mun Tham

IPC: F01D5/08 ,  F01D5/30

Abstract: A flow inducer assembly and a method for cooling turbine blades of a gas turbine engine are presented. The gas turbine engine includes a rotor disk having circumferentially distributed disk grooves and turbine blades. Each turbine blade includes a blade root inserted into blade mounting section of the disk groove. Seal plates are attached to an aft side circumference of the rotor disk. The flow inducer assembly is integrated to each seal plate at a side facing away from the rotor disk. The flow inducer assembly is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from the blade root for cooling the turbine blade.

公开(公告)号：US11319819B2

公开(公告)日：2022-05-03

申请号：US16616100

申请日：2018-05-01

Applicant: Siemens Energy Global GmbH & Co. KG

Inventor： Kok-Mun Tham ,  Ching-Pang Lee ,  Li Shing Wong ,  Sin Chien Siw

IPC: F01D5/20 ,  F01D5/28 ,  F01D5/18

Abstract: A blade (10) for a turbine engine that includes an internal cooling system (56) formed from at least one cavity (58) positioned within a generally elongated airfoil (12). A squealer tip (36) and at least one densified oxide dispersion strengthened layer (38) extend radially from a radially outer tip cap (70) of the blade (10), the tip cap (70) having a tip cap upper surface (50).