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公开(公告)号：US10436050B2
公开(公告)日：2019-10-08
申请号：US15484190
申请日：2017-04-11
Applicant: United Technologies Corporation
Inventor： Victor G. Filipenco , Michael C. Firnhaber
Abstract: An inlet section for a gas turbine engine according to an example of the present disclosure includes, among other things, an outer case extending about a rotor that is rotatable about an engine axis. The rotor carries a plurality of airfoils. A plurality of guide vanes are operable to guide flow from an engine inlet toward the plurality of airfoils relative to the engine axis. A plurality of spokes are mechanically attached to the outer case. Each of the plurality of spokes is received in a respective one of the plurality of guide vanes, and at least one of the plurality of spokes define a fluid passage in flow communication with a bearing assembly.
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公开(公告)号：US20200080432A1
公开(公告)日：2020-03-12
申请号：US16128973
申请日：2018-09-12
Applicant: United Technologies Corporation
Inventor： Victor G. Filipenco
Abstract: A gas turbine engine includes a fan section. A splitter is downstream of the fan section and at least partially defines a secondary flow path on a radially outer side and an inner flow path on a radially inner side. A variable pitch rotor blade assembly is located at an inlet to the inner flow path and includes a plurality of variable pitch rotor blades.
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公开(公告)号：US11125187B2
公开(公告)日：2021-09-21
申请号：US16052022
申请日：2018-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Victor G. Filipenco
Abstract: A gas turbine engine includes a case assembly, a splitter, an upstream blade row, and a transition duct. The case assembly defines an outer flow path wall and an inner flow path wall. The splitter is disposed between the outer flow path wall and the inner flow path wall. The splitter has a first surface and a second surface disposed opposite the first surface. The transition duct is defined by the outer flow path and the inner flow path and extends between the upstream blade row and the leading edge of the splitter.
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公开(公告)号：US10113561B2
公开(公告)日：2018-10-30
申请号：US15153578
申请日：2016-05-12
Applicant: United Technologies Corporation
Inventor： Victor G. Filipenco , Jordan T. Wall
IPC: F01D25/12 , F04D29/54 , F04D29/32 , F04D29/52 , F04D29/58 , F01D5/08 , F01D9/04 , F02K3/06 , F04D27/02
Abstract: A stage of a fan for a gas turbine engine may include a rotor blade and a stator vane disposed aft of the rotor blade. A baffle may be coupled to the stator vane. The baffle may define a secondary airflow path from aft of the stator vane to forward of the rotor blade. The baffle may further define the secondary airflow path from aft of the stator vane to forward of the stator vane.
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公开(公告)号：US20200040847A1
公开(公告)日：2020-02-06
申请号：US16052022
申请日：2018-08-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Victor G. Filipenco
Abstract: A gas turbine engine includes a case assembly, a splitter, an upstream blade row, and a transition duct. The case assembly defines an outer flow path wall and an inner flow path wall. The splitter is disposed between the outer flow path wall and the inner flow path wall. The splitter has a first surface and a second surface disposed opposite the first surface. The transition duct is defined by the outer flow path and the inner flow path and extends between the upstream blade row and the leading edge of the splitter.
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Patent Agency Ranking
公开(公告)号：US10287904B2
公开(公告)日：2019-05-14
申请号：US15035258
申请日：2014-11-04
Applicant: United Technologies Corporation
Inventor： Victor G. Filipenco , Anthony R. Bifulco
Abstract: A turbine engine is disclosed and includes an airflow passage including an inner surface defined by a main shroud and a shroud extension. A flow splitter is disposed radially outward of the inner surface and axially overlapping the shroud extension. The turbine engine further includes a rotor including a blade proximate the shroud extension and an annular gap defined between the shroud extension and the blade of a first axial length less than a second axial length between the blade and an end of the flow splitter.
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公开(公告)号：US20180291753A1
公开(公告)日：2018-10-11
申请号：US15484190
申请日：2017-04-11
Applicant: United Technologies Corporation
Inventor： Victor G. Filipenco , Michael C. Firnhaber
CPC classification number: F01D9/065 , F01D5/02 , F01D9/041 , F01D11/001 , F01D17/162 , F01D25/162 , F01D25/18 , F05D2220/32 , F05D2230/60
Abstract: An inlet section for a gas turbine engine according to an example of the present disclosure includes, among other things, an outer case extending about a rotor that is rotatable about an engine axis. The rotor carries a plurality of airfoils. A plurality of guide vanes are operable to guide flow from an engine inlet toward the plurality of airfoils relative to the engine axis. A plurality of spokes are mechanically attached to the outer case. Each of the plurality of spokes is received in a respective one of the plurality of guide vanes, and at least one of the plurality of spokes define a fluid passage in flow communication with a bearing assembly.
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公开(公告)号：US20170328378A1
公开(公告)日：2017-11-16
申请号：US15153578
申请日：2016-05-12
Applicant: United Technologies Corporation
Inventor： Victor G. Filipenco , Jordan T. Wall
CPC classification number: F04D29/542 , F01D5/082 , F01D9/041 , F02K3/06 , F04D27/0215 , F04D29/325 , F04D29/522 , F04D29/582 , F04D29/584 , F05D2260/20 , F05D2260/608 , Y02T50/672 , Y02T50/676
Abstract: A stage of a fan for a gas turbine engine may include a rotor blade and a stator vane disposed aft of the rotor blade. A baffle may be coupled to the stator vane. The baffle may define a secondary airflow path from aft of the stator vane to forward of the rotor blade. The baffle may further define the secondary airflow path from aft of the stator vane to forward of the stator vane.
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公开(公告)号：US20160273373A1
公开(公告)日：2016-09-22
申请号：US15035258
申请日：2014-11-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Victor G. Filipenco , Anthony R. Bifulco
CPC classification number: F01D11/001 , F01D5/02 , F01D9/02 , F01D9/04 , F01D25/24 , F01D25/243 , F01D25/246 , F02C3/04 , F02C7/04 , F05D2220/32 , F05D2230/60 , F05D2230/64 , F05D2230/642 , F05D2240/11 , F05D2260/30
Abstract: A turbine engine is disclosed and includes an airflow passage including an inner surface defined by a main shroud and a shroud extension. A flow splitter is disposed radially outward of the inner surface and axially overlapping the shroud extension. The turbine engine further includes a rotor including a blade proximate the shroud extension and an annular gap defined between the shroud extension and the blade of a first axial length less than a second axial length between the blade and an end of the flow splitter.
Abstract translation: 涡轮发动机被公开并且包括气流通道，其包括由主护罩和护罩延伸部限定的内表面。 分流器设置在内表面的径向外侧并且轴向地与护罩延伸部重叠。 涡轮发动机还包括转子，其包括靠近护罩延伸部的叶片和限定在护罩延伸部和叶片之间的环形间隙，第一轴向长度小于叶片与分流器的端部之间的第二轴向长度。
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公开(公告)号：US20160229543A1
公开(公告)日：2016-08-11
申请号：US14615543
申请日：2015-02-06
Applicant: United Technologies Corporation
Inventor： James J. McPhail , Isaac Jon Hogate , Victor G. Filipenco
CPC classification number: B64D15/00 , F01D5/02 , F01D25/02 , F02C7/04 , F05D2220/32 , F05D2250/713 , F05D2300/10 , F05D2300/512 , F05D2300/611
Abstract: A gas turbine engine is provided having a nose cone, wherein the nose cone is symmetrically disposed about an axis. The nose cone includes a leading edge and a base. A forward section is disposed between the leading edge and the base and has a radius at any axial location defined by a first equation. A transition section is disposed between the forward section and the base and has a radius at any axial location defined by a second equation. The first equation is different than the second equation.
Abstract translation: 提供了一种具有鼻锥体的燃气涡轮发动机，其中鼻锥体围绕轴线对称设置。 鼻锥包括前缘和底座。 前进部分设置在前缘和基座之间，并且在由第一等式限定的任何轴向位置处具有半径。 过渡部分设置在前部和基部之间，并且在由第二等式限定的任何轴向位置处具有半径。 第一个方程与第二个方程不同。
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