-
公开(公告)号：US20180363485A1
公开(公告)日：2018-12-20
申请号：US15623657
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A turbine shroud assembly including an outer shroud arranged within a turbine and further comprising opposed extending portions. The turbine shroud assembly further including an inner shroud shielding the outer shroud from a gas flowing along a gas path within the turbine during operation of the turbine and comprising opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The turbine shroud assembly further including a spline seal extending between the first and second arcuate portions and positioned between the inner shroud and the outer shroud. The turbine shroud assembly further including at least one of the inner shroud, the outer shroud and the spline seal including at least one protrusion for maintaining positive retention of the spline seal during non-operation of the turbine.
-
公开(公告)号：US20180363483A1
公开(公告)日：2018-12-20
申请号：US15623696
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy HAFNER , John McConnell DELVAUX , Glenn Curtis TAXACHER
IPC: F01D9/04
Abstract: A turbine component includes an outer shroud arranged within a turbine and further including opposed extending portions. The component further provides an inner shroud shielding the outer shroud from a gas path within the turbine during operation of the turbine and including opposed arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The component further provides a load path forming region at least partially extending between facing surfaces of each arcuate portion and corresponding extending portion. During operation of the turbine, load path forming regions extend into direct contact between at least a portion of the facing surfaces of each arcuate portion and corresponding extending portion, resulting in formation of a loading arrangement having generally evenly distributed radial load forces at the load path forming regions.
-
Patent Agency Ranking
公开(公告)号：US20180363478A1
公开(公告)日：2018-12-20
申请号：US15623842
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Joshua Lee MARGOLIES , Victor John MORGAN , Matthew Troy HAFNER
CPC classification number: F01D5/288 , F01D9/02 , F01D9/023 , F01D25/005 , F01D25/007 , F01D25/24 , F05D2240/11 , F05D2240/122 , F05D2240/304 , F05D2240/35 , F05D2240/80 , F05D2250/292 , F05D2300/175 , F05D2300/6033 , F05D2300/611 , F23R3/002 , F23R3/007
Abstract: A method for forming a coated turbine component and a coated turbine component is provided. The method includes a step of providing a component having a substrate comprising a trailing edge face. The method further includes a step of applying a thermal barrier coating or environmental barrier coating selectively to the substrate to form a discontinuous transition from a hot gas path surface at the trailing edge face to discourage hot gas flow along the trailing edge face.
-
公开(公告)号：US20180223680A1
公开(公告)日：2018-08-09
申请号：US15425545
申请日：2017-02-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy HAFNER
CPC classification number: F01D9/041 , F01D5/282 , F01D5/284 , F01D9/044 , F01D25/005 , F05D2220/32 , F05D2230/232 , F05D2240/128 , F05D2250/121 , F05D2250/141 , F05D2250/60 , F05D2300/174 , F05D2300/175 , F05D2300/6033
Abstract: A nozzle assembly is disclosed, including a CMC nozzle shell, a nozzle spar, and an endwall. The CMC nozzle shell includes a CMC composition and an interior cavity. The nozzle spar is partially disposed within the interior cavity and includes a metallic composition, a cross-sectional conformation, a plurality of spacers protruding from the cross-sectional conformation, the plurality of spacers contacting the CMC nozzle shell, and a spar cap. The endwall includes at least one surface in lateral contact with the spar cap and maintains a lateral orientation of the CMC nozzle shell and the nozzle spar relative to the endwall. The lateral orientation maintains a predetermined throat area of the nozzle assembly. A method for forming the nozzle assembly includes inserting the nozzle spar into the interior cavity, rotating the CMC nozzle shell and the nozzle spar laterally relative to the endwall, and maintaining the lateral orientation.
-
公开(公告)号：US20170350260A1
公开(公告)日：2017-12-07
申请号：US15174271
申请日：2016-06-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip DUTTA , James ZHANG , Gary Michael ITZEL , John McConnell DELVAUX , Matthew Troy HAFNER
CPC classification number: F01D5/187 , F01D5/147 , F01D5/282 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2230/22 , F05D2230/237 , F05D2230/31 , F05D2240/122 , F05D2240/304 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2260/20 , F05D2260/204 , F05D2300/175 , F05D2300/6033
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.
-
公开(公告)号：US20170328203A1
公开(公告)日：2017-11-16
申请号：US15150573
申请日：2016-05-10
Applicant: GENERAL ELECTRIC COMPANY
Inventor： James ZHANG , James Tyson BALKCUM, III , John McConnell DELVAUX , Matthew Troy HAFNER
IPC: F01D1/04
CPC classification number: F01D1/04 , F01D11/001 , F01D11/008 , F05D2240/11 , F05D2240/55
Abstract: A turbine assembly includes a rotary component rotatable about an axis of a turbine, a plurality of inner wall segments coupled to the rotary component circumferentially around the rotary component and rotatable with the rotary component, a non-rotary component circumferentially surrounding the rotary component, a plurality of outer wall segments coupled to the non-rotary component and disposed to extend toward the rotary component, and a plurality of nozzles extending from each of the outer wall segments, each nozzle having a tip distal from the outer wall segment such that the tips form a seal with the inner wall segments at an inner flow path of the turbine. An inner wall assembly and a turbine assembly method are also disclosed.
-
公开(公告)号：US20170276021A1
公开(公告)日：2017-09-28
申请号：US15080201
申请日：2016-03-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy HAFNER , Gary Michael ITZEL , John McConnell DELVAUX , Sandip DUTTA
Abstract: An apparatus is disclosed including a first and second article, a first interface volume disposed between and enclosed by the first article and second article, a cooling fluid supply, and at least one cooling fluid channel in fluid communication with the cooling fluid supply and the first interface volume. The first article includes a first material composition. The second article includes a second material composition. The at least one cooling fluid channel includes a heat exchange portion disposed in at least one of the first and second article downstream of the cooling fluid supply and upstream of the first interface volume. A turbine shroud is disclosed wherein the first and second articles are an outer and inner shroud. A turbine nozzle is disclosed wherein the first and second articles are an endwall and fairing.
-
-
-
-
-
-
Search Results
27
records
(took 0.024 seconds)
