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公开(公告)号：US10830078B2
公开(公告)日：2020-11-10
申请号：US16131145
申请日：2018-09-14
Applicant: United Technologies Corporation
Inventor： Brad E. Fiore , James B. Coffin , Christopher M. Valva
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a tower shaft rotatable about an axis, an engine component rotatable with the tower shaft about the axis, and a seal assembly. The engine component extends axially along the axis to an end surface. The seal assembly includes a carbon seal element, where the carbon seal element circumscribes the tower shaft and axially engages the end surface.
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公开(公告)号：US10662812B2
公开(公告)日：2020-05-26
申请号：US15789469
申请日：2017-10-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Joseph D. Walker , James B. Coffin
Abstract: A lubricant scoop is disclosed. The lubricant scoop includes an annular body configured for engagement with a shaft rotating about a central axis. The annular body includes a first annular portion and a second annular portion disposed adjacent the first annular portion. The first annular portion includes a radially oriented entrance surface and a first axially oriented transition surface. The second annular portion includes a second axially oriented transition surface, a primary redirection member spaced radially outward from the second axially oriented transition surface, a radially oriented exit surface and an exit conduit having an opening positioned on the radially oriented exit surface.
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3.发明授权公开(公告)号：US10041498B2
公开(公告)日：2018-08-07
申请号：US14912105
申请日：2014-08-21
Applicant: United Technologies Corporation
Inventor： John R. Otto , James B. Coffin , Jason Husband
IPC: F02K3/06 , F04D25/04 , F02C3/107 , F01D5/02 , F01D15/12 , F04D25/02 , F04D27/00 , F04D29/32 , F02C7/36
Abstract: A turbofan engine is disclosed that includes a fan rotatable about an axis, a compressor section including a high pressure compressor, a medium pressure compressor and a low pressure compressor and a turbine section including a high pressure turbine, an intermediate turbine and a fan drive turbine. A fan drive gear system is driven by the fan drive turbine for driving the fan. A compressor drive gear system is driven by the intermediate turbine for driving the low pressure compressor. A gear controller controls rotation of at least one of the fan drive gear system and the compressor drive gear system relative to a static structure to vary an effective speed reduction ratio of one of the fan drive gear system and the compressor drive gear system.
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公开(公告)号：US20170298828A1
公开(公告)日：2017-10-19
申请号：US15497590
申请日：2017-04-26
Applicant: United Technologies Corporation
Inventor： James B. Coffin , Alessio Pescosolido
CPC classification number: F02C7/20 , B64D27/26 , B64D2027/266 , F01D21/045 , F01D25/16 , F02C7/36 , F05D2220/36 , F05D2260/40311 , Y10T29/49318
Abstract: A gas turbine engine includes a fan, an engine static structure, a geared architecture to drive the fan and supported relative to the static structure, a fan drive turbine to drive the geared architecture, a first member secured to the geared architecture, and a second member secured to the engine static structure and configured to cooperate with the first member to limit movement of the geared architecture relative to the static structure. A fan drive gear system and method are also disclosed.
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公开(公告)号：US20160138477A1
公开(公告)日：2016-05-19
申请号：US14902058
申请日：2014-07-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John R. Otto , James B. Coffin , Jason Husband
CPC classification number: F02C7/36 , F02C3/10 , F02C3/107 , F02K3/06 , F05D2240/40 , F05D2260/40311
Abstract: A turbofan engine includes a fan rotatable about an axis and a compressor section including a high pressure compressor and a low pressure compressor. A turbine section includes a high pressure turbine, an intermediate turbine and a fan drive turbine. The high pressure turbine is coupled to drive the high pressure compressor. A fan drive gear system is driven by the fan drive turbine for driving the fan and a compressor drive gear system is driven by the intermediate turbine for driving the low pressure compressor.
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Patent Agency Ranking
公开(公告)号：US09328818B2
公开(公告)日：2016-05-03
申请号：US13727868
申请日：2012-12-27
Applicant: United Technologies Corporation
Inventor： James B. Coffin , Michael E. McCune , William G. Sheridan
CPC classification number: F16H57/0467 , F01D25/18 , F02C7/36 , F05D2220/32 , F05D2260/30 , F05D2260/31 , F05D2260/40311 , F05D2260/98 , F16H57/025 , F16H57/0479
Abstract: An example epicyclic gear train assembly includes a flexure pin received by a carrier. The flexure pin and the carrier respectively include first and second pin apertures configured to receive a retainer pin. The flexure pin further includes a lubricant conduit separate from the first pin aperture.
Abstract translation: 示例性行星齿轮系组件包括由载体接收的挠曲销。 挠曲销和托架分别包括构造成接收保持销的第一和第二销孔。 挠曲销还包括与第一销孔分开的润滑剂导管。
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公开(公告)号：US20150152746A1
公开(公告)日：2015-06-04
申请号：US14459988
申请日：2014-08-14
Applicant: United Technologies Corporation
Inventor： Alexander J. Maret , James B. Coffin , Jonathan Logan Miller
CPC classification number: F01D25/186 , F01D25/183 , F05D2260/98 , F16C33/6677 , F16J15/162 , F16J15/324
Abstract: A seal assembly for a gas turbine engine, may be manufactured in two pieces, the first piece is a seal plate with a cavity around its inner wall and the second piece is a sleeve that mounts in the cavity of the seal plate. The sleeve may have oil distribution channels that deliver oil to subsequent components and apertures that deliver oil to the seal plate. The volume of oil delivered to the seal plate can be set by the number of apertures and related radial holes in the sleeve. Because the sleeve delivers oil through the apertures and radial holes to an annulus in the cavity of the seal plate, cooling bores in the seal plate need only be drilled into the annulus and the number of cooling bores can be independent of the number of radial holes in the sleeve.
Abstract translation: 用于燃气涡轮发动机的密封组件可以制造成两片，第一件是围绕其内壁的空腔的密封板，第二件是安装在密封板的空腔中的套筒。 套筒可以具有将油输送到向密封板输送油的后续部件和孔的油分配通道。 输送到密封板的油的体积可以通过套筒中的孔的数量和相关的径向孔来设定。 因为套管将油通过孔和径向孔传递到密封板的空腔中的环形空间，所以密封板中的冷却孔仅需要钻入环形空间中，并且冷却孔的数量可以与径向孔的数量无关 在袖子里。
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公开(公告)号：US20140064932A1
公开(公告)日：2014-03-06
申请号：US14036927
申请日：2013-09-25
Applicant: United Technologies Corporation
Inventor： James B. Coffin , John R. Otto
IPC: F01D15/12
CPC classification number: F01D15/12 , F01D25/04 , F02C7/36 , F02K3/06 , F05D2260/40311 , F05D2260/96 , Y10T74/19642
Abstract: A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A viscous damper is provided between the torque frame and the flex support at the location.
Abstract translation: 燃气涡轮发动机包括风扇部分。 涡轮机部分通过齿轮架构耦合到风扇部分。 齿轮架构包括在一个位置处彼此间隔开的扭矩框架和柔性支撑件。 齿轮系由转矩架支撑。 在位置处的扭矩框架和柔性支撑件之间设置粘性阻尼器。
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公开(公告)号：US11286854B2
公开(公告)日：2022-03-29
申请号：US16535454
申请日：2019-08-08
Applicant: United Technologies Corporation
Inventor： James B. Coffin , Joseph D. Walker , Todd A. Davis
Abstract: A gas turbine engine includes a rotating shaft. An oil scoop rotates with the rotating shaft. The oil scoop has end walls spaced axially along an axis of rotation of the rotating shaft and an axially central recess. A duct is spaced radially outwardly of the oil scoop. The duct has an oil inlet, with an oil supply nozzle to supply oil into the oil inlet in the duct. The oil inlet is then connected to supply oil into the recess. The oil scoop has an inner hole to allow oil to flow from the recess to an outer periphery of the shaft.
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公开(公告)号：US11143111B2
公开(公告)日：2021-10-12
申请号：US16516430
申请日：2019-07-19
Applicant: United Technologies Corporation
Inventor： John R. Otto , James B. Coffin
Abstract: A fan drive gear system for a turbofan engine includes a geared architecture and a gear controller supporting the geared architecture and controlling rotation of the geared architecture relative a static structure.
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