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公开(公告)号：US10815832B2
公开(公告)日：2020-10-27
申请号：US16012396
申请日：2018-06-19
Applicant: United Technologies Corporation
Inventor： Peter Staffier , Paul W. Palmer , Anders C. Olson , Nicholas W. Kantany , Eric Baker
Abstract: A turbine exhaust case is provided for a gas turbine engine. This turbine exhaust case includes a first gas turbine engine exhaust case, a second gas turbine engine exhaust case, a strut and a fastener. The second gas turbine engine exhaust case includes a flange and a bracket. The strut is coupled to the first case and the second case. The fastener fastens the flange and the strut. The second gas turbine engine exhaust case is co-axial with the first gas turbine engine exhaust case. The strut contacts the bracket when the engine is powered-on.
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公开(公告)号：US09605596B2
公开(公告)日：2017-03-28
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.
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公开(公告)号：US20190383170A1
公开(公告)日：2019-12-19
申请号：US16012396
申请日：2018-06-19
Applicant: United Technologies Corporation
Inventor： Peter Staffier , Paul W. Palmer , Anders C. Olson , Nicholas W. Kantany , Eric Baker
Abstract: A turbine exhaust case is provided for a gas turbine engine. This turbine exhaust case includes a first gas turbine engine exhaust case, a second gas turbine engine exhaust case, a strut and a fastener. The second gas turbine engine exhaust case includes a flange and a bracket. The strut is coupled to the first case and the second case. The fastener fastens the flange and the strut. The second gas turbine engine exhaust case is co-axial with the first gas turbine engine exhaust case. The strut contacts the bracket when the engine is powered-on.
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公开(公告)号：US20180179959A1
公开(公告)日：2018-06-28
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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公开(公告)号：US09976435B2
公开(公告)日：2018-05-22
申请号：US14884015
申请日：2015-10-15
Applicant: United Technologies Corporation
Inventor： Mark Borja , Paul W. Palmer
CPC classification number: F01D11/18 , F01D5/02 , F01D25/24 , F05D2220/32 , F05D2230/21 , F05D2230/22 , F05D2230/30 , F05D2240/24 , F05D2240/307
Abstract: A rotating blade tip clearance system includes a control ring carrier defining a centerline axis. The control ring carrier has a connecting portion, a retaining portion radially inward of the connecting portion, and a flange connecting radially between the connecting portion and the retaining portion. The flange isolates the retaining portion of the control ring carrier from the thermal deflection of a case and assists in keeping the control ring carrier aligned about centerline axis A during thermal deflection. The retaining portion includes radially inner and outer diameter sides defining a retaining cavity therebetween. The system includes a control ring within the retaining cavity. The control ring has a different thermal response rate from the control ring carrier so that the control ring thermally deflects slower than the control ring carrier, thereby controlling the rate and/or extent of thermal deflection of the control ring carrier.
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Patent Agency Ranking
6.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：US20190136707A1
公开(公告)日：2019-05-09
申请号：US14619419
申请日：2015-02-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul W. Palmer
IPC: F01D11/18
Abstract: A clearance control system for a gas turbine engine includes a full hoop blade outer air seal carrier ring, a full hoop thermal control ring at least partially contained within the full hoop blade outer air seal blade outer air seal carrier ring to form an interference fit therebetween, and a multiple of blade outer air seals mounted to the full hoop blade outer air seal carrier ring.
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公开(公告)号：US20150337732A1
公开(公告)日：2015-11-26
申请号：US14818392
申请日：2015-08-05
Applicant: United Technologies Corporation
Inventor： Robert Russell Mayer , George J. Kramer , Paul W. Palmer
Abstract: A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.
Abstract translation: 燃气涡轮发动机包括与风扇流体连接的风扇和压缩机部。 压缩机包括高压压缩机和低压压缩机。 燃烧器流体地连接到压缩机部分。 涡轮部分流体地连接到燃烧器。 涡轮部分包括经由第一轴联接到高压压缩机的高压涡轮机。 低压涡轮机经由第二轴联接到低压压缩机。 齿轮架构在第二轴和风扇之间互连。 燃气涡轮发动机是具有大于六（6）的旁路比的高旁路齿轮飞机发动机。 低压涡轮机具有大于5的压力比，并且齿轮架构包括大于2.5:1的齿轮减速比。
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公开(公告)号：US20140290269A1
公开(公告)日：2014-10-02
申请号：US14150411
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
IPC: F02C7/28
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 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.
Abstract translation: 用于燃气涡轮发动机的密封系统包括具有径向凸缘的盖板; 靠近盖板的密封托架; 由密封载体支撑的外部柔顺密封件; 由密封载体支撑的内部柔顺密封件，与径向凸缘接合的内部柔性密封件; 以及盖板和密封托架之间的弹簧。
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公开(公告)号：US10753279B2
公开(公告)日：2020-08-25
申请号：US14818392
申请日：2015-08-05
Applicant: United Technologies Corporation
Inventor： Robert Russell Mayer , George J. Kramer , Paul W. Palmer
IPC: F02C1/00 , F02C7/06 , F02C3/045 , F02C7/36 , F02C7/20 , F01D25/24 , F01D25/16 , F23R3/00 , F23R3/60
Abstract: A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.
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