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公开(公告)号：US20180363468A1
公开(公告)日：2018-12-20
申请号：US15622266
申请日：2017-06-14
摘要： An apparatus and method for cooling an airfoil or engine component can include an outer wall defining an interior. A cooling circuit can be provided in the interior for directing flow of fluid and defining a flow direction. A plurality of cooling conduits can be arranged in the cooling circuit and organized into two or more sets of rows.
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公开(公告)号：US20180298765A1
公开(公告)日：2018-10-18
申请号：US15487981
申请日：2017-04-14
摘要： An apparatus and method for a replaceable tip element of an airfoil in a turbine engine. The airfoil has an outer wall defining an interior and including a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction, with the tip having a replaceable tip element.
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公开(公告)号：US11946415B2
公开(公告)日：2024-04-02
申请号：US17470032
申请日：2021-09-09
发明人： Jeffrey Douglas Rambo , Brandon Wayne Miller , William Joseph Bowden , Matthew Thomas Beyer , Michael John Simonetti
IPC分类号： F02C7/10
CPC分类号： F02C7/10 , F05D2220/32 , F05D2260/213
摘要： A gas turbine engine having a waste heat recovery system is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.
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公开(公告)号：US20180347375A1
公开(公告)日：2018-12-06
申请号：US15609488
申请日：2017-05-31
摘要： An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail at the tip. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.
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公开(公告)号：US10718217B2
公开(公告)日：2020-07-21
申请号：US15622266
申请日：2017-06-14
摘要： An apparatus and method for cooling an airfoil or engine component can include an outer wall defining an interior. A cooling circuit can be provided in the interior for directing flow of fluid and defining a flow direction. A plurality of cooling conduits can be arranged in the cooling circuit and organized into two or more sets of rows.
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公开(公告)号：US10400608B2
公开(公告)日：2019-09-03
申请号：US15360529
申请日：2016-11-23
摘要： A tip cooling apparatus for a turbine airfoil includes: a tip cap; a pair of spaced-apart tip walls connected to, extending around, and projecting outwardly from the tip cap so as to surround a central portion of the tip cap; a pocket defined by the tip walls; at least one feed hole passing through the tip cap or tip walls, communicating with the pocket; and a cooling matrix disposed in the pocket, the cooling matrix being an organized structure including an inlet surface having a plurality of inlets communicating with the pocket, and an outlet surface having a plurality of outlets, and further comprising a plurality of interior passages interconnecting the inlets to the outlets, with no line-of-sight therebetween.
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公开(公告)号：US20180223672A1
公开(公告)日：2018-08-09
申请号：US15426318
申请日：2017-02-07
发明人： Matthew Thomas Beyer , Tingfan Pang
CPC分类号： F01D5/186 , B22C7/02 , B22C9/10 , B22C9/24 , B22D25/02 , B22D29/002 , B23B35/00 , B23B39/161 , B23B2215/81 , B23P15/02 , B23P2700/06 , F01D5/187 , F05D2230/211 , F05D2240/304 , F05D2260/607 , Y02T50/676
摘要： An apparatus and method for an investment casting core for forming a cast airfoil extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction, with an internal passage including at least one leach hole formed from the investment casting core.
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公开(公告)号：US20230076757A1
公开(公告)日：2023-03-09
申请号：US17470032
申请日：2021-09-09
发明人： Jeffrey Douglas Rambo , Brandon Wayne Miller , William Joseph Bowden , Matthew Thomas Beyer , Michael John Simonetti
IPC分类号： F02C7/10
摘要： A gas turbine engine having a waste heat recovery system is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.
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公开(公告)号：US20180355728A1
公开(公告)日：2018-12-13
申请号：US15615869
申请日：2017-06-07
CPC分类号： F01D5/18 , F01D9/065 , F05D2230/21 , F05D2260/20
摘要： A method for making a cooled component for a turbine engine includes casting an airfoil assembly having an airfoil with an airfoil cooling passage and extending from a platform with at least one platform cooling passage, and forming a connecting passage between the airfoil cooling air passage and the platform cooling air passage.
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公开(公告)号：US20180347374A1
公开(公告)日：2018-12-06
申请号：US15609430
申请日：2017-05-31
IPC分类号： F01D5/18
摘要： An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.
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