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公开(公告)号：US10513942B2
公开(公告)日：2019-12-24
申请号：US15037127
申请日：2014-11-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher W. Strock , Enzo DiBenedetto
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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公开(公告)号：US09995217B2
公开(公告)日：2018-06-12
申请号：US14765738
申请日：2014-02-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Enzo DiBenedetto
Abstract: Disclosed is a gas turbine engine including a compressor section in communication with a bleed flow path. A rotary valve is provided in communication with the bleed flow path to selectively regulate a flow of fluid within the bleed flow path.
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13.发明申请公开(公告)号：US20180051706A1
公开(公告)日：2018-02-22
申请号：US15240248
申请日：2016-08-18
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto
IPC: F04D29/051 , F04D29/056 , F04D29/059 , F04D29/08 , F04D29/66 , F16C33/66
CPC classification number: F01D25/164 , F01D25/162 , F01D25/18 , F02C3/04 , F05D2220/32 , F05D2240/52 , F05D2240/53 , F05D2240/54 , F16C27/045 , F16C33/6637 , F16C33/6659 , F16C2360/23
Abstract: A gas turbine engine includes a bearing support ring with a first annular body and a second annular body disposed radially inward of the first annular body. A radial spring is connected to the first annular body and the second annular body. The gas turbine engine includes a frame with a case that extends around the first annular body. The frame includes an annular member connected to the case and positioned radially between the radial spring and the second annular body. A fluid port extends radially through the annular member. A seal is disposed around the annular member and forward of the fluid port. A first fluid passage extends through the case. A second fluid passage is formed between the bearing support ring and the frame and extends from the first fluid passage to the fluid port. A bearing outer race is disposed inward of the second annular body.
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公开(公告)号：US09765643B2
公开(公告)日：2017-09-19
申请号：US13719688
申请日：2012-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Robert C. Stutz , Enzo DiBenedetto
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.
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15.发明申请APPARATUS AND METHOD FOR PROVIDING DAMPER LIQUID IN A GAS TURBINE ENGINE 有权用于在气体涡轮发动机中提供阻尼器液体的装置和方法公开(公告)号：US20130305733A1
公开(公告)日：2013-11-21
申请号：US13955385
申请日：2013-07-31
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , James B. Coffin , Todd A. Davis
IPC: F02C7/06
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.
Abstract translation: 公开了一种在燃气轮机中分配液体的方法。 该方法包括通过风扇驱动齿轮系旋转联接到线轴的风扇轴。 在燃气涡轮发动机的运行期间，阀芯驱动风扇轴通过风扇驱动齿轮系的旋转。 泵通过风扇轴驱动。 在第一操作条件下，液体从贮槽供应到泵。 在第二操作条件下，液体从辅助容器供应到泵。 液体被泵送到阻尼器。
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Patent Agency Ranking
公开(公告)号：US11486269B2
公开(公告)日：2022-11-01
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：US10927706B2
公开(公告)日：2021-02-23
申请号：US16177991
申请日：2018-11-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Enzo DiBenedetto
IPC: F01D25/12
Abstract: A thermal management system for a component of a gas turbine engine is disclosed. In various embodiments, the thermal management system includes a manifold extending circumferentially about a longitudinal axis and defining a plenum; a cooling fluid transfer tube disposed within the plenum and configured to transfer a component cooling fluid from a component cooling fluid source to the component; and a cooling fluid passageway connected to the manifold and configured to transfer a plenum cooling fluid from a plenum cooling fluid source to the plenum.
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公开(公告)号：US10415465B2
公开(公告)日：2019-09-17
申请号：US15851285
申请日：2017-12-21
Applicant: United Technologies Corporation
Inventor： Matthew E Bintz , Enzo DiBenedetto
Abstract: An auxiliary compressor for a gas turbine engine is disclosed. The auxiliary compressor includes a first axial rotor, a second axial rotor positioned downstream of the first axial rotor, and a centrifugal impeller positioned intermediate the first axial rotor and the second axial rotor and operably coupled to the first axial rotor.
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公开(公告)号：US20190195127A1
公开(公告)日：2019-06-27
申请号：US15851285
申请日：2017-12-21
Applicant: United Technologies Corporation
Inventor： Matthew E Bintz , Enzo DiBenedetto
CPC classification number: F02C3/08 , F02C6/08 , F02C7/28 , F02C9/18 , F05D2220/32 , F05D2220/3218 , F05D2240/20
Abstract: An auxiliary compressor for a gas turbine engine is disclosed. The auxiliary compressor includes a first axial rotor, a second axial rotor positioned downstream of the first axial rotor, and a centrifugal impeller positioned intermediate the first axial rotor and the second axial rotor and operably coupled to the first axial rotor.
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公开(公告)号：US20160341068A1
公开(公告)日：2016-11-24
申请号：US14880519
申请日：2015-10-12
Applicant: United Technologies Corporation
Inventor： Thomas J. Robertson, JR. , Enzo DiBenedetto , Nathan F. Champion , Niloofar Haghbin , Barry William Spaulding, III
CPC classification number: F01D17/14 , F01D9/041 , F01D9/042 , F01D17/162 , F04D29/563 , F04D29/644 , F05D2220/32 , F05D2230/30 , F05D2230/60 , F05D2230/644 , F05D2240/80 , F05D2260/30
Abstract: A fixed-variable vane assembly includes a vane that has a fixed airfoil section and a variable airfoil section next to the fixed airfoil section. The variable airfoil section is pivotably mounted at an end thereof in a joint with a variable joint gap that controls a size of an airfoil gap between the fixed airfoil section and the variable airfoil section. A potting material is located in the variable joint gap. The potting material locks the variable joint gap and locks in the size of the airfoil gap.
Abstract translation: 固定式叶片组件包括具有固定翼型部分和与固定翼型部分相邻的可变翼型部分的叶片。 可变翼型部分在其端部可枢转地安装在具有可变接头间隙的接头中，该可变接缝间隙控制固定翼型部分和可变翼型部分之间的翼型间隙的尺寸。 灌封材料位于可变接缝间隙中。 灌封材料锁定可变接缝间隙并锁定翼型间隙的尺寸。
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