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公开(公告)号：US11927348B2
公开(公告)日：2024-03-12
申请号：US17535027
申请日：2021-11-24
申请人： RTX Corporation
发明人： Steven D. Porter , Jon E. Sobanski
CPC分类号： F23R3/002 , B21D25/00 , B21D31/005 , F01D11/005 , F02C3/04 , F23M5/04 , F23R3/60 , F23R2900/00018
摘要： An aerodynamic component of a gas turbine engine is provided and is fittable to a shell having a shell shape. The aerodynamic component includes a body having a component shape initially deviating from the shell shape prior to an assembly operation in which the aerodynamic component is to be fit to the shell. Deviation of the component shape from the shell shape aids in an establishment of a final desired shape of the aerodynamic component following the assembly operation.
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公开(公告)号：US11850688B2
公开(公告)日：2023-12-26
申请号：US17081751
申请日：2020-10-27
发明人： Rich Giaramita , David Watts
IPC分类号： F27D1/14 , F23M5/04 , B23K9/20 , B23K9/23 , F27D1/16 , B23K103/04 , B23K101/12
CPC分类号： B23K9/201 , B23K9/208 , B23K9/23 , F27D1/14 , F27D1/16 , B23K2101/12 , B23K2103/05
摘要： A Y-shaped refractory anchor, a plurality of Y-shaped refractory anchors, and a method of installing a plurality of Y-shaped refractory anchors in a hexagonal pattern is disclosed. The Y-shaped refractory anchor comprises a singular rectangular folded metal plate comprising a stem that comprises at least one tapered triangular section to be welded to a backing surface and a folded stem base and a branch section comprising two branches, wherein the singular metal plate is folded together at the stem base, such that the stem of the Y-shaped anchor is twice as thick as the two individual branches.
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公开(公告)号：US10935244B2
公开(公告)日：2021-03-02
申请号：US16167873
申请日：2018-10-23
发明人： Stanislav Kostka , Frank J. Cunha
摘要： A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.
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公开(公告)号：US10753610B2
公开(公告)日：2020-08-25
申请号：US15562905
申请日：2016-03-29
发明人： Egidio Pucci , Michele Provenzale
摘要： A gas turbine combustor is disclosed, comprising: a combustor liner; a combustor casing, at least partly housing the combustor liner, and a liner support arrangement. The liner support arrangement comprises individual support elements located between the combustor liner and the combustor casing. Each support element comprises a liner support member fixed to the combustor liner and a casing support member fastened to the combustor casing. Each casing support member comprises a casing stop seat fixed on the combustor casing and a replaceable casing stop, detachably coupled to the casing stop seat.
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5.发明授权公开(公告)号：US10655853B2
公开(公告)日：2020-05-19
申请号：US15348639
申请日：2016-11-10
发明人： Steven W. Burd
摘要： A combustor for a gas turbine engine including a forward liner panel mounted to a support shell via a multiple of studs, the forward liner panel including an aft non-linear circumferential edge and an aft liner panel mounted to the support shell via a multiple of studs, the aft liner panel including a forward non-linear circumferential edge that is complementary to the aft non-linear circumferential edge.
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公开(公告)号：US10330318B2
公开(公告)日：2019-06-25
申请号：US14898138
申请日：2014-06-27
发明人： Daniel Vogtmann , Sabine Grendel , Claus Krusch , Andre Kluge , Hartwig Dümler , Christopher Grandt , Andreas Bottcher , Tobias Krieger , Patrick Lapp
摘要： A heat shield with support structure and a number of heat shield blocks secured thereto, having a cold side facing the support structure and a hot side opposite the cold side. At least one recess is arranged in at least one heat shield block circumferential face, connecting the cold to hot side. An opening connecting the recess to the cold side runs in the circumferential face perpendicularly to the cold side. A securing bolt inserted into the opening secures the heat shield block to the support structure. A bolt head protrudes at least partly into the recess. The securing bolt passes through an angled plate having first limb extending substantially parallel to the circumferential face and second limb extending into the recess. The angled plate has a reinforcing device extending beyond the pure angular shape to increase a resistance of the angled plate against bending due to the securing bolt.
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公开(公告)号：US10281150B2
公开(公告)日：2019-05-07
申请号：US14907083
申请日：2014-06-23
发明人： Bojan Zivanovic
摘要： The invention relates to a refractory ceramic lining brick and a corresponding ceramic refractory lining.
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公开(公告)号：US10215411B2
公开(公告)日：2019-02-26
申请号：US15062440
申请日：2016-03-07
摘要： A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.
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公开(公告)号：US20180231248A1
公开(公告)日：2018-08-16
申请号：US15348568
申请日：2016-11-10
发明人： Steven W. Burd
CPC分类号： F23M5/04 , F01D9/023 , F23M5/085 , F23R3/002 , F23R3/06 , F23R3/42 , F23R3/50 , F23R3/60 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a forward section and an aft section that defines an angle therebetween in the axial profile between the forward section and the aft section.
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公开(公告)号：US09903590B2
公开(公告)日：2018-02-27
申请号：US14559320
申请日：2014-12-03
申请人： ROLLS-ROYCE PLC
CPC分类号： F23R3/44 , F23M5/04 , F23R3/002 , F23R3/007 , F23R3/06 , F23R3/60 , F23R2900/00017 , F23R2900/00018
摘要： A double wall structured combustor having an outer wall having an inner surface and an outer surface and an inner wall comprising a plurality of tiles. Each tile has at least one interlocking member at a first wall and at least one interengaging member at a second wall. The interlocking member extending through an aperture in the outer wall, and the interengaging member at the second wall engaging with a cutaway section in the first wall of an adjacent tile. On assembly of the combustion chamber, the interlocking members and interengaging members of the tiles ensure lower profile fixings and an overall reduction in number of conventional fasteners used.
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