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公开(公告)号：US12044136B2
公开(公告)日：2024-07-23
申请号：US17663507
申请日：2022-05-16
发明人： Louis Kobielski , Baris Uygun , Adam C. Felton
CPC分类号： F01D25/145 , F04D17/10 , F05D2220/40 , F05D2240/15
摘要： A rotary assembly is provided that may be operably connected to an engine. The rotary assembly may include a rotary device comprising a turbine wheel, a shaft connected to the turbine wheel, and a case that houses the shaft and the turbine wheel. The turbine wheel may receive exhaust gas from the engine which causes rotation of the turbine wheel and the shaft. The case may include an interior surface that defines a hollow volume in which the turbine wheel and the shaft are located. The case has a radial thickness extending from the interior surface to an exterior surface of the case. The case may include a lattice structure integrated within the radial thickness of the case. The lattice structure may include a repeating three-dimensional array of frame segments connected to one another at junctions and defining interstitial spaces between the frame segments.
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公开(公告)号：US20240117754A1
公开(公告)日：2024-04-11
申请号：US17961987
申请日：2022-10-07
发明人： Connor C. Perry , Xiaomei Fang , Bradley L. Paquin , Jacob Yochimowitz , Sushruth G. Kamath , Jun Cao
CPC分类号： F01D25/005 , F01D9/02 , F01D25/08 , F01D25/145 , F05D2220/32 , F05D2230/31 , F05D2240/10 , F05D2240/128 , F05D2240/14 , F05D2240/15 , F05D2260/231 , F05D2300/211
摘要： A gas turbine engine component includes a structural component having a surface, the structural component having an organic matrix composite material; and a cured thermal barrier layer on the surface, wherein the cured thermal barrier layer is a pre-ceramic layer including inorganic matrix containing silicon oxides reinforced with glass or quartz fibers.
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公开(公告)号：US20230407793A1
公开(公告)日：2023-12-21
申请号：US18068031
申请日：2022-12-19
发明人： Mohan Kannaiah Raju , Subramani Adhiachari , Ravindra Shankar Ganiger , Arvind Namadevan , Prasant Bilaiya , Scott Alan Schimmels
CPC分类号： F02C7/24 , F02C7/222 , F02C7/06 , F05D2240/15 , F05D2260/231 , F05D2300/603
摘要： An insulation assembly for use in a gas turbine engine is provided. The insulation assembly defines a hot side and an insulated side and includes: a heat shield layer positioned proximate the hot side; and a thermal absorption layer positioned proximate the insulated side, the thermal absorption layer comprising a phase change material, the insulation assembly defining an air gap positioned between the heat shield layer and the thermal absorption layer.
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公开(公告)号：US20180363502A1
公开(公告)日：2018-12-20
申请号：US15625465
申请日：2017-06-16
发明人： Aaron Michael Dziech
CPC分类号： F01D25/243 , F01D9/04 , F01D9/065 , F01D25/12 , F01D25/14 , F01D25/246 , F05D2220/32 , F05D2240/15 , F05D2260/30 , F05D2260/606 , F05D2300/6033
摘要： Retention assemblies and retention assembly cooling methods are provided. An exemplary retention assembly comprises an annular baffle, an annular attachment bracket comprising a gas turbine engine component, and first and second cooling passages defined by the baffle and attachment bracket. The first cooling passage is configured to receive a first airflow and the second cooling passage is configured to receive a second airflow. The first airflow has a lower pressure than the second airflow. An exemplary method comprises flowing a first airflow to a first cooling passage defined by a baffle and an attachment bracket of a retention assembly, and flowing a second airflow to a second cooling passage defined by the baffle and the attachment bracket. The second cooling passage is separate from the first cooling passage. The first airflow cools radially outward structures of the retention assembly, and the attachment bracket comprises a CMC component.
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公开(公告)号：US20180334926A1
公开(公告)日：2018-11-22
申请号：US15649622
申请日：2017-07-13
发明人： Marcel Schmidt
CPC分类号： F01D25/145 , F01D9/04 , F01D25/162 , F01D25/24 , F01D25/246 , F02C7/24 , F05D2220/32 , F05D2230/642 , F05D2240/12 , F05D2240/15 , F05D2250/75 , F05D2260/231
摘要： A subassembly of a gas turbine engine includes a heat shield and carrier subassembly for a turbine section are disclosed. The carrier includes support features to couple to an engine casing. The upstream end of the carrier includes a radially inward arm extending toward to an engine axis. The outer end of the radially floating heat shield is coupled to the radially inward arm via a pin-and-slot joint configured to allow movement of the heat shield relative to the radially inward arm of the carrier. In response to thermal expansion and contraction of the vane, the heat shield is configured to move radially outward and inward, respectively, relative to the radially inward arm to maintain contact with the outer platform of the vane.
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公开(公告)号：US10060445B2
公开(公告)日：2018-08-28
申请号：US14924210
申请日：2015-10-27
发明人： Brandon W. Spangler , Gina Cavallo
IPC分类号： F04D29/58 , F23R3/02 , F01D25/12 , F23R3/04 , F02C7/18 , F04D29/16 , F04D29/52 , F04D29/54 , F04D29/64 , F23R3/00 , F23R3/06 , F01D5/18 , F01D9/06
CPC分类号： F04D29/582 , F01D5/186 , F01D9/065 , F01D25/12 , F02C7/18 , F04D29/164 , F04D29/526 , F04D29/542 , F04D29/644 , F05D2220/32 , F05D2230/10 , F05D2240/11 , F05D2240/12 , F05D2240/15 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/672 , Y02T50/675 , Y02T50/676
摘要： A surface structure having a filmhole pattern is disclosed. The filmhole pattern may be an offset herringbone pattern. For instance, the surface structure may have rows of filmholes arranged in filmrows, each filmrow divided into groups of filmholes. A first group may be oriented to direct cooling air generally outward over a surface of the surface structure and a second group may be oriented to direct cooling air generally inward over a surface of the surface structure. Between the first group and the second group of filmholes in each filmrow, a transition region exists. The adjacent filmrows are arranged to enhance the effectiveness of the convective cooling proximate to the transition regions by causing each filmrow to direct cooling air over the transition region of an adjacent filmrow.
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公开(公告)号：US20180202659A1
公开(公告)日：2018-07-19
申请号：US15409635
申请日：2017-01-19
发明人： Michael Alan Stieg , Valeria Proano Cadena , Aaron Michael Dziech , Michael Todd Radwanski , Donald Michael Corsmeier
IPC分类号： F23R3/00
CPC分类号： F23R3/007 , F05D2240/15 , F05D2240/35 , F05D2240/55 , F23R3/002 , F23R3/10 , F23R3/60 , F23R2900/00012 , F23R2900/00018
摘要： Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.
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公开(公告)号：US09976484B2
公开(公告)日：2018-05-22
申请号：US14981229
申请日：2015-12-28
CPC分类号： F02C7/12 , B64D29/00 , F01D25/145 , F02C3/04 , F02C7/25 , F02C7/28 , F02K3/06 , F05D2220/323 , F05D2240/15 , F05D2240/91 , F05D2260/605 , F05D2260/608 , Y02T50/671 , Y02T50/675
摘要： A core compartment ventilation device is provided. The core compartment ventilation device comprises a fireproof sealing member for substantially sealing a core compartment in a nacelle for a gas turbine engine and a chimney configured to be in fluid communication with the fireproof sealing member for conducting hot air from the core compartment to the external atmosphere via the fireproof sealing member. A gas turbine engine and nacelle including the core compartment ventilation device are also provided.
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公开(公告)号：US09863271B2
公开(公告)日：2018-01-09
申请号：US14377888
申请日：2013-02-27
发明人： Per Granberg , Janos Szijarto
IPC分类号： F04D29/58 , F01D25/12 , F01D9/04 , F02C7/24 , B23K26/388 , F01D25/14 , B23K26/382
CPC分类号： F01D25/12 , B23K26/388 , B23K26/389 , F01D9/04 , F01D9/041 , F01D25/14 , F02C7/24 , F05D2230/40 , F05D2240/15 , F05D2260/202 , F05D2300/17 , F05D2300/175 , F05D2300/177 , Y10T29/49323
摘要： An arrangement for a turbomachine is provided. The arrangement includes a vane for directing a hot gas during the operation of the turbomachine, a stator ring for securing the vane, a heat shield for protecting the stator ring from the hot gas flow wherein the heat shield is arranged in downstream direction of the hot gas flow in front of the stator ring characterized in that the heat shield comprises a plurality of channels formed therein for directing a cooling air.
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公开(公告)号：US20170335704A1
公开(公告)日：2017-11-23
申请号：US15162069
申请日：2016-05-23
CPC分类号： F01D11/005 , F01D11/003 , F01D11/08 , F05D2220/32 , F05D2240/15 , F05D2240/55 , F05D2250/75 , F16J15/024 , F16J15/0887 , F16J15/44
摘要： An annular ring for sealing a flow includes an inner ring and a tab. The tab extends radially and is configured to restrict axial movement of the seal.
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