-
公开(公告)号：US09932838B2
公开(公告)日：2018-04-03
申请号：US14977228
申请日：2015-12-21
Applicant: General Electric Company
CPC classification number: F01D5/187 , F02C3/04 , F05D2220/32 , F05D2240/305 , F05D2240/307 , F05D2250/185 , F05D2260/202
Abstract: A cooling system according to an embodiment includes: a three-pass serpentine cooling circuit; and an air feed cavity for supplying cooling air to the three-pass serpentine cooling circuit; wherein the three-pass serpentine cooling circuit extends radially outward from and at least partially covers at least one central plenum and a first set of near wall cooling channels of a multi-wall blade.
-
公开(公告)号：US09909427B2
公开(公告)日：2018-03-06
申请号：US14978235
申请日：2015-12-22
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , David Wayne Weber
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/304 , F05D2260/201 , F05D2260/203 , F05D2260/22141 , Y02T50/676
Abstract: One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.
-
公开(公告)号：US20180051576A1
公开(公告)日：2018-02-22
申请号：US15239985
申请日：2016-08-18
Applicant: General Electric Company
Inventor： David Wayne Weber , Lana Maria Osusky
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D9/02 , F01D25/12 , F02C3/04 , F05D2220/32 , F05D2240/121 , F05D2240/125 , F05D2240/303 , F05D2240/307 , F05D2240/35 , F05D2250/185 , F05D2260/202
Abstract: A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the pressure and suction side cavities; and a second leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the second leading edge cavity located forward of the first leading edge cavity.
-
公开(公告)号：US20180051575A1
公开(公告)日：2018-02-22
申请号：US15239968
申请日：2016-08-18
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D5/186 , F01D9/02 , F01D25/12 , F02C3/04 , F05D2220/32 , F05D2240/303 , F05D2240/35 , F05D2260/201 , F05D2260/202
Abstract: A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the first leading edge cavity with a second leading edge cavity.
-
公开(公告)号：US20170328218A1
公开(公告)日：2017-11-16
申请号：US15152690
申请日：2016-05-12
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D9/041 , F05D2240/121 , F05D2240/303 , F05D2250/18 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/676
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
-
Patent Agency Ranking
公开(公告)号：US09771816B2
公开(公告)日：2017-09-26
申请号：US14271823
申请日：2014-05-07
Applicant: General Electric Company
Inventor： David Wayne Weber
CPC classification number: F01D9/065 , F01D5/187 , F01D25/12 , F05D2240/81 , F05D2250/292 , F05D2260/201
Abstract: A blade cooling circuit feed and exhaust duct and related cooling structure are provided. The feed duct may include a feed chamber having a feed entrance fluidly coupled to a cooling fluid source and a feed exit to an elongate entrance to the cooling circuit, the feed exit including a ramped wall maintaining a flow velocity of the cooling fluid along the elongated entrance to the cooling circuit. The exhaust duct may include a substantially concave exhaust chamber including an exhaust entrance at a wider end of the exhaust chamber and in fluid communication with an elongated exit from the cooling circuit, and an exhaust exit at a narrower end of the exhaust chamber, the exhaust exit including an opening to an exhaust passageway from the exhaust chamber.
-
公开(公告)号：US09759081B2
公开(公告)日：2017-09-12
申请号：US14049020
申请日：2013-10-08
Applicant: General Electric Company
Inventor： Victor John Morgan , Gregory Thomas Foster , Neelesh Nandkumar Sarawate , David Wayne Weber
CPC classification number: F01D11/08 , F01D9/041 , F01D11/003 , F05D2230/60 , F05D2260/38 , Y10T29/4932
Abstract: A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.
-
公开(公告)号：US20170175545A1
公开(公告)日：2017-06-22
申请号：US14977200
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Gregory Thomas Foster , Elisabeth Kraus Black , Michelle Jessica Iduate , Brendon James Leary , Jacob Charles Perry, II , David Wayne Weber
CPC classification number: F01D5/187 , F05D2230/10 , F05D2240/81 , F05D2260/202
Abstract: A cooling system for a turbine bucket including a multi-wall blade and a platform. A cooling circuit for the multi-wall blade includes: an outer cavity circuit and a central cavity for collecting cooling air from the outer cavity circuit; a platform core air feed for receiving the cooling air from the central cavity; and an air passage for fluidly connecting the platform core air feed to a platform core of the platform.
-
公开(公告)号：US20170175543A1
公开(公告)日：2017-06-22
申请号：US14977152
申请日：2015-12-21
Applicant: General Electric Company
Inventor： David Wayne Weber , Fred Thomas Willett, JR.
CPC classification number: F01D5/187 , F01D5/147 , F01D5/188 , F05D2220/30 , F05D2240/127 , F05D2250/185 , F05D2260/2214
Abstract: A turbine blade cooling system according to an embodiment includes: a first arcuate 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 arcuate turn for redirecting a second flow of gas flowing through a second channel of the turbine blade into the central plenum of the turbine blade, wherein the first and second arcuate turns reduce impingement of the first flow of gas and the second flow of gas in the central plenum of the turbine blade.
-
公开(公告)号：US20170175541A1
公开(公告)日：2017-06-22
申请号：US14977102
申请日：2015-12-21
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Gary Michael Itzel , Brendon James Leary , Joseph Anthony Weber
CPC classification number: F01D5/187 , F01D5/18 , F01D5/186 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2240/127 , F05D2240/307 , F05D2240/35 , F05D2260/202 , F05D2260/22141
Abstract: A cooling system according to an embodiment includes: a pin fin bank cooling circuit; and an air feed cavity for supplying cooling air to the pin fin bank cooling circuit; wherein the pin fin bank cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade and a first set of near wall cooling channels of the multi-wall blade.
-
-
-
-
-
-
-
-
-
Search Results
105
records
(took 0.029 seconds)
