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公开(公告)号：US20170321560A1
公开(公告)日：2017-11-09
申请号：US15147954
申请日：2016-05-06
Applicant: United Technologies Corporation
Inventor： Peter Balawajder , Benjamin F. Hagan , Jeffrey Michael Jacques
CPC classification number: F01D5/3007 , F01D9/02 , F01D9/042 , F01D11/00 , F01D11/005 , F01D25/243 , F01D25/246 , F05D2220/32 , F05D2240/57 , F05D2240/80 , F05D2260/941
Abstract: A vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.
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公开(公告)号：US20170268366A1
公开(公告)日：2017-09-21
申请号：US15071320
申请日：2016-03-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Peter Balawajder , David Richard Griffin , Benjamin F. Hagan
Abstract: A blade outer air seal support includes, at least one arc body having a first portion and a second portion, a blade outer air seal mounting region defined at least partially between the first portion and the second portion, and an interface feature interfacing the first portion and the second portion. The interface feature is configured such that axially aligned forces are communicated between the first and second portions through the interface feature, bypassing the blade outer air seal mounting region.
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13.发明申请公开(公告)号：US20160341075A1
公开(公告)日：2016-11-24
申请号：US15106615
申请日：2014-08-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Shu Liu , Robert Russell Mayer , Paul W. Palmer , Peter Balawajder , Igor S. Garcia , David C. Pimenta , Stephanie Ernst , Fernando K. Grant , Eric Baker , Andrew S. Miller
CPC classification number: F01D25/26 , F01D21/045 , F01D25/24 , F02C3/04 , F02K3/06 , F04D29/522 , F04D29/526 , F05D2220/32 , F05D2250/283 , F05D2250/29 , F05D2300/506 , F23R3/002
Abstract: A gas turbine engine includes a core assembly with a core case having a containment section for containing liberated compressor and turbine blades and blade fragments. The containment section includes first and second containment layers and the containment section is configured to have a non-linear rate of energy dissipation across the first and second containment layers, thereby to improve containment of blades and blade fragments.
Abstract translation: 燃气涡轮发动机包括具有芯壳的芯组件，所述芯壳具有用于容纳释放的压缩机和涡轮叶片和叶片碎片的容纳部分。 容纳部分包括第一和第二容纳层，并且容纳部分被配置为具有穿过第一和第二容纳层的非线性能量消耗速率，从而改善叶片和叶片碎片的收容。
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公开(公告)号：US10578026B2
公开(公告)日：2020-03-03
申请号：US15895058
申请日：2018-02-13
Applicant: United Technologies Corporation
Inventor： Nicholas Lefevre , John J. Korzendorfer , Peter Balawajder , Paul W. Palmer , Paul J. Colucci , Mahamoud Coulibaly
Abstract: A seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier.
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Patent Agency Ranking
公开(公告)号：US10422241B2
公开(公告)日：2019-09-24
申请号：US15071320
申请日：2016-03-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael G. McCaffrey , Peter Balawajder , David Richard Griffin , Benjamin F. Hagan
Abstract: A blade outer air seal support includes, at least one arc body having a first portion and a second portion, a blade outer air seal mounting region defined at least partially between the first portion and the second portion, and an interface feature interfacing the first portion and the second portion. The interface feature is configured such that axially aligned forces are communicated between the first and second portions through the interface feature, bypassing the blade outer air seal mounting region.
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公开(公告)号：US10385705B2
公开(公告)日：2019-08-20
申请号：US15147954
申请日：2016-05-06
Applicant: United Technologies Corporation
Inventor： Peter Balawajder , Benjamin F. Hagan , Jeffrey Michael Jacques
Abstract: A vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.
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公开(公告)号：US10208602B2
公开(公告)日：2019-02-19
申请号：US14697329
申请日：2015-04-27
Applicant: United Technologies Corporation
Inventor： Lane Thornton , Ryan Alan Waite , Peter Balawajder , Benjamin F. Hagan
Abstract: A film cooled component may comprise a cooling chamber and a first ligament centered about a first axis. The first ligament may be in fluid communication with the cooling chamber. A first meter may be disposed at an end of the first ligament. A first diffuser may extend from the first meter to a surface of the film cooled component. The first diffuser may comprise a first tapered sidewall oriented at an angle of between 5 degrees to 15 degrees relative to the first axis. The first diffuser may further comprise a first non-tapered sidewall oriented at an angle less than 5 degrees relative to the first axis.
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18.发明申请公开(公告)号：US20160341070A1
公开(公告)日：2016-11-24
申请号：US15106566
申请日：2014-08-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Igor S. Garcia , Shu Liu , Robert Russell Mayer , Eric Baker , Stephanie Ernst , Fernando K. Grant , Andrew S. Miller , Peter Balawajder , Paul W. Palmer
Abstract: A gas turbine engine includes a containment ring to contain liberated compressor and turbine blades and blade fragments within a core assembly. The combination of a containment gap between the core case and the containment ring and a containment layer disposed in the gap helps dissipate the energy generated by loose body impacts on the core assembly. The containment layer deforms, deflects, and/or redirects the impact energy acting in a radial direction, thereby to improve containment.
Abstract translation: 燃气涡轮发动机包括容纳环，以容纳释放的压缩机和涡轮叶片以及芯组件内的叶片碎片。 芯壳与容纳环之间的容纳间隙和设置在间隙中的容纳层的组合有助于消散由芯体组件上的松动的身体撞击产生的能量。 容纳层使沿径向作用的冲击能量变形，偏转和/或重定向，从而改善容纳。
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公开(公告)号：US20140290213A1
公开(公告)日：2014-10-02
申请号：US14150385
申请日：2014-01-08
Applicant: United Technologies Corporation
Inventor： Nicholas Lefevre , John J. Korzendorfer , Peter Balawajder , Paul W. Palmer , Paul J. Colucci , Mahamoud Coulibaly
CPC classification number: F02C7/28 , F02K3/075 , F04D19/02 , F04D27/0215 , F04D29/083 , F05D2220/90 , Y02T50/672
Abstract: A seal system for a gas turbine engine includes an annular seal carrier and an annular compliant seal mounted around the annular seal carrier, the compliant seal includes a multiple of legs in cross-section.
Abstract translation: 用于燃气涡轮发动机的密封系统包括环形密封载体和围绕环形密封载体安装的环形柔性密封件，柔性密封件包括多个横截面的腿部。
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