-
公开(公告)号：US11867402B2
公开(公告)日：2024-01-09
申请号：US17207193
申请日：2021-03-19
发明人： San Quach , Thomas N. Slavens
CPC分类号： F23R3/42 , F02C3/00 , F23R3/002 , F23R3/007 , F23R3/06 , F05D2220/32 , F05D2240/35 , F05D2300/6033
摘要： In one exemplary embodiment, a combustor liner includes a first portion extending in a substantially axial direction and a second portion that extending in the substantially axial direction. A step connects the first portion and the second portion. The step is arranged at an angle to the second portion that is less than 90°. The step has a step height defined as a distance between the first portion and the second portion. The first portion, second portion, and step are formed as a unitary ceramic component. A slot extends through the step, and a ratio of a height of the slot to a height of the step is greater than 0.66.
-
公开(公告)号：US11808154B2
公开(公告)日：2023-11-07
申请号：US17952693
申请日：2022-09-26
CPC分类号： F01D11/005 , F01D5/147 , F01D9/042 , F05D2240/12 , F05D2300/6033
摘要： In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.
-
公开(公告)号：US11492914B1
公开(公告)日：2022-11-08
申请号：US17080969
申请日：2020-10-27
发明人： San Quach , Adam P. Generale , Raymond Surace , Lucas Dvorozniak
摘要： A gas turbine engine includes a blade outer air seal, a ceramic vane, and a cooling passage circuit that extends through a first internal passage in the blade outer air seal and a second internal passage in the ceramic vane.
-
公开(公告)号：US11286789B2
公开(公告)日：2022-03-29
申请号：US16920014
申请日：2020-07-02
发明人： Jaime G Ghigliotty , David J Candelori , San Quach
摘要： An airfoil for a gas turbine engine is disclosed. In various embodiments, the airfoil includes a cooling passage; an outer wall separating a core flow path from the cooling passage; a diffuser in fluid communication with the cooling passage and opening into the core flow path, the diffuser being characterized by a linear ridge on a downstream end of the diffuser; and a thermal barrier coating covering the outer wall and the linear ridge.
-
公开(公告)号：US11085305B2
公开(公告)日：2021-08-10
申请号：US16415199
申请日：2019-05-17
摘要： A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.
-
公开(公告)号：US20210017863A1
公开(公告)日：2021-01-21
申请号：US17009936
申请日：2020-09-02
摘要： A gas turbine engine component includes a wall that has an inner surface and an outer surface. An inlet is defined by the inner surface. At least one non-rectangular slot is defined by the outer surface and includes at least one protrusion extending into the slot. A slot passage fluidly connects the inlet to the at least one non-rectangular slot. The slot passage comprises an inlet portion that extends through the wall from the inlet to an intermediate portion. An outlet portion extends through the wall from the intermediate portion to the at least one non-rectangular slot.
-
公开(公告)号：US20230057881A1
公开(公告)日：2023-02-23
申请号：US17978315
申请日：2022-11-01
摘要： A gas turbine engine includes a ceramic wall for bounding an engine core gas path. The ceramic wall has a ceramic wall first side that faces the engine core gas path and a ceramic wall second side that faces away from the engine core gas path. There is a metallic wall adjacent the ceramic wall second side. The metallic wall has a metallic wall first side that faces the ceramic wall and a metallic wall second side that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel there between. There is a seal on the ceramic wall second side, and the metallic wall has at least one cooling hole adjacent the seal for emitting cooling air to cool the seal.
-
公开(公告)号：US10684014B2
公开(公告)日：2020-06-16
申请号：US15228029
申请日：2016-08-04
发明人： San Quach , Brian T. Hazel , Kaitlin M. Tomeo , Robert Selinsky, Jr. , Aaron S. Butler , John S. Tu , William F. Werkheiser , Jessica L. Serra
摘要： A heat shield panel for a gas turbine engine includes a substrate layer having a first substrate surface and a second substrate surface opposite the first substrate surface. The first substrate surface and the second substrate surface define a substrate layer thickness therebetween. One or more thermally protective coating layers are applied to the first substrate surface of the substrate layer. The one or more coating layers have a constant coating layer thickness and the substrate layer thickness tapers along an axial length of the heat shield panel.
-
公开(公告)号：US11661853B2
公开(公告)日：2023-05-30
申请号：US17482478
申请日：2021-09-23
CPC分类号： F01D5/187 , F01D5/147 , F01D5/186 , F01D5/20 , F05D2220/32 , F05D2260/202 , F05D2260/221 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y02T50/60
摘要： A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.
-
公开(公告)号：US11486256B2
公开(公告)日：2022-11-01
申请号：US17113166
申请日：2020-12-07
发明人： San Quach , Tyler G. Vincent , Cheng Gao , Howard J. Liles
摘要： A vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the flange. There is a conformal thermal insulation blanket disposed on the flange.
-
-
-
-
-
-
-
-
-
搜索结果
28 条记录 (耗时 0.017 秒)
