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公开(公告)号：US20200025030A1
公开(公告)日：2020-01-23
申请号：US16286970
申请日：2019-02-27
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Todd A. Davis , Gregory E. Reinhardt , Enzo DiBenedetto
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.
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公开(公告)号：US09790855B2
公开(公告)日：2017-10-17
申请号：US13955385
申请日：2013-07-31
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , James B. Coffin , Todd A. Davis
CPC classification number: F02C7/06 , F01D25/164 , F01D25/20 , F05D2260/96
Abstract: A method for distributing liquid in a gas turbine engine is disclosed. The method includes rotating a fan shaft coupled to a spool via a fan drive gear system. The spool drives rotation of the fan shaft through the fan drive gear system during operation of the gas turbine engine. A pump is driven via the fan shaft. Liquid is supplied from a sump to the pump under a first operating condition. Liquid is supplied from an auxiliary reservoir to the pump under a second operating condition. Liquid is pumped to a damper.
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3.发明授权Forward compartment service system for a geared architecture gas turbine engine 有权用于齿轮架构燃气涡轮发动机的前车厢服务系统公开(公告)号：US09410447B2
公开(公告)日：2016-08-09
申请号：US13693733
申请日：2012-12-04
Applicant: United Technologies Corporation
Inventor： James B. Coffin , Todd A. Davis , Enzo DiBenedetto
CPC classification number: F01D25/16 , F01D9/065 , F01D25/162 , F01D25/18
Abstract: A gas turbine engine includes a jumper tube that extends through a first passage and a second passage.
Abstract translation: 燃气涡轮发动机包括延伸穿过第一通道和第二通道的跳线管。
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公开(公告)号：US09322291B2
公开(公告)日：2016-04-26
申请号：US13714788
申请日：2012-12-14
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto
CPC classification number: F01D25/02 , F01D9/065 , F02C7/047 , F05D2260/31 , Y10T29/49321
Abstract: Disclosed is a gas turbine engine including a plurality of inlet guide vanes. The gas turbine engine further includes an inlet case supporting each of the plurality of inlet guide vanes, and the inlet case is provided with at least one passageway in communication with a source of fluid. The at least one passageway is configured to communicate the fluid to each of the plurality of inlet guide vanes.
Abstract translation: 公开了一种包括多个入口导向叶片的燃气涡轮发动机。 燃气涡轮发动机还包括支撑多个入口引导叶片中的每一个的入口壳体，并且入口壳体设置有与流体源连通的至少一个通道。 至少一个通道构造成将流体连通到多个入口导叶中的每一个。
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公开(公告)号：US20140230403A1
公开(公告)日：2014-08-21
申请号：US14012576
申请日：2013-08-28
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Todd A. Davis , Gregory E. Reinhardt , Enzo DiBenedetto
CPC classification number: F01D25/162 , F01D25/16 , F02C7/06 , F02C7/36 , F02K3/04 , Y02T50/671
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.
Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 第一轴支撑轴向设置在入口壳体流动路径和中间壳体流动路径之间的低压压缩机部分。 第一轴承相对于入口壳体支撑第一轴。 第二轴承相对于中间壳体支撑第二轴。 低压压缩机毂安装在第一轴上。 低压压缩机毂在第一轴承和第二轴承之间延伸到低压压缩机部分。
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Patent Agency Ranking
公开(公告)号：US20140169934A1
公开(公告)日：2014-06-19
申请号：US13714788
申请日：2012-12-14
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto
CPC classification number: F01D25/02 , F01D9/065 , F02C7/047 , F05D2260/31 , Y10T29/49321
Abstract: Disclosed is a gas turbine engine including a plurality of inlet guide vanes. The gas turbine engine further includes an inlet case supporting each of the plurality of inlet guide vanes, and the inlet case is provided with at least one passageway in communication with a source of fluid. The at least one passageway is configured to communicate the fluid to each of the plurality of inlet guide vanes.
Abstract translation: 公开了一种包括多个入口导向叶片的燃气涡轮发动机。 燃气涡轮发动机还包括支撑多个入口引导叶片中的每一个的入口壳体，并且入口壳体设置有与流体源连通的至少一个通道。 至少一个通道构造成将流体连通到多个入口导叶中的每一个。
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公开(公告)号：US20140165530A1
公开(公告)日：2014-06-19
申请号：US13719688
申请日：2012-12-19
Applicant: United Technologies Corporation
Inventor： Robert C. Stutz , Enzo DiBenedetto
IPC: F01D25/18
CPC classification number: F01D25/18 , F01M2005/028 , F02C7/06 , F16N7/30 , F16N29/02 , F16N2260/00 , Y02T50/671
Abstract: A bi-directional auxiliary lubrication system which allows lubricant to be supplied to moving engine components after a loss of lubricant pressure from a main lubricant tank is disclosed. In a gas turbine engine, the lubrication system may siphon compressed air from a compressor to draw lubricant from a reserve lubricant tank and deliver that lubricant to the engine components. The same conduits used by the lubrication during normal operations are utilized in an opposite direction to provide the flow of lubricant from the reserve lubricant tank during such auxiliary or low-lubricant-pressure operations.
Abstract translation: 公开了一种双向辅助润滑系统，其允许在从主润滑剂罐失去润滑剂压力之后将润滑剂供应到移动的发动机部件。 在燃气涡轮发动机中，润滑系统可以从压缩机吸入压缩空气以从储备润滑剂罐抽出润滑剂，并将该润滑剂输送到发动机部件。 在正常操作期间通过润滑使用的相同管道在相反方向上被利用，以在这种辅助或低润滑剂压力操作期间提供来自储备润滑剂罐的润滑剂的流动。
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8.发明申请FORWARD COMPARTMENT SERVICE SYSTEM FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE 有权用于齿轮式建筑燃气涡轮发动机的前向舱室服务系统公开(公告)号：US20140030088A1
公开(公告)日：2014-01-30
申请号：US13693733
申请日：2012-12-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James B. Coffin , Todd A. Davis , Enzo DiBenedetto
IPC: F01D25/16
CPC classification number: F01D25/16 , F01D9/065 , F01D25/162 , F01D25/18
Abstract: A gas turbine engine includes a jumper tube that extends through a first passage and a second passge.
Abstract translation: 燃气涡轮发动机包括延伸穿过第一通道和第二通道的跳线管。
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公开(公告)号：US12037910B2
公开(公告)日：2024-07-16
申请号：US16724865
申请日：2019-12-23
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Enzo DiBenedetto
CPC classification number: F01D11/08 , C23C4/134 , F01D5/12 , F01D11/12 , F01D25/24 , F05D2220/32 , F05D2230/31 , F05D2230/90 , F05D2300/173 , F05D2300/212
Abstract: A seal comprises a housing. A coating has at least two layers with a bond layer to be positioned between a housing and a second hard layer. The second hard layer is formed to be harder than the bond layer. The bond layer has a bond strength greater than or equal to 200 psi and less than or equal to 2000 psi. A gas turbine engine, and a method of forming a coating layer are also disclosed.
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10.发明申请公开(公告)号：US20210172332A1
公开(公告)日：2021-06-10
申请号：US16704642
申请日：2019-12-05
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , Paul E. Coderre
Abstract: A compressor case to blade tip clearance system comprising a rotor having blades with tips, the case including an inner case comprising at least one surface feature fluidly coupled to a distribution manifold disposed in a cooling air passageway, the at least one surface feature configured to interact with the cooling air, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of the cooling air over the at least one surface feature.
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