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公开(公告)号：US10443736B2
公开(公告)日：2019-10-15
申请号：US14872640
申请日：2015-10-01
Applicant: United Technologies Corporation
Inventor： Philip Robert Rioux
Abstract: A sealing system for a gas turbine engine includes a first surface and a second surface spaced a dimension away from the first surface defining a gap through which a fluid can flow. At least one recess is formed in one of the first surface and the second surface and is oriented such that the fluid flow through the gap crosses the at least one recess. The recess is configured to restrict the fluid flow through the gap in comparison to if the at least one recess were not present, all other things being equal.
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公开(公告)号：US10443426B2
公开(公告)日：2019-10-15
申请号：US14972893
申请日：2015-12-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Philip Robert Rioux , Nicholas R. Leslie , Richard K. Hayford
Abstract: A blade outer air seal according to an example of the present disclosure includes a seal body extending circumferentially about an axis and including at least one channel having a substantially solid radially outer surface. A substrate is radially inward of the at least one channel with respect to the axis. The substrate and the at least one channel form at least one cavity. A rotor rub strip is radially inward of the substrate.
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公开(公告)号：US20190309641A1
公开(公告)日：2019-10-10
申请号：US15945409
申请日：2018-04-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William R. Edwards , Philip Robert Rioux , Mark David Ring
Abstract: A cantilevered mounted singlet vane includes a first outer shroud and a first airfoil. The first outer shroud is provided with a first body having a first body first side and a first body second side axially extending between a first body first end and a first body second end. The first outer shroud defines a first slot axially extends from the first body first end towards a first body end wall disposed at the second end. The first airfoil radially extends from the first outer shroud.
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公开(公告)号：US10428670B2
公开(公告)日：2019-10-01
申请号：US15149246
申请日：2016-05-09
Applicant: United Technologies Corporation
Inventor： Philip Robert Rioux
Abstract: An arrangement of a rotating component and a stationary component of a gas turbine engine includes a rotating component, a stationary component positioned to define an actual gap between the rotating component and the stationary component, and a flow restriction feature formed at one of the stationary component or the rotating component. The flow restriction feature is configured to induce a recirculation flow at the actual gap, thereby defining an effective gap between the rotating component and the stationary component to reduce a leakage flow therebetween, while maintaining the actual gap greater than the effective gap.
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公开(公告)号：US10197069B2
公开(公告)日：2019-02-05
申请号：US14947494
申请日：2015-11-20
Applicant: United Technologies Corporation
Inventor： Nicholas R. Leslie , Mark J. Rogers , Philip Robert Rioux
Abstract: An airseal for sealing between a rotating component and a stationary component of a turbine engine includes a sealing surface defining a spacing between the airseal and a rotating component of the turbine engine and a mounting flange to secure the airseal to a stationary component of the turbine engine. An airseal body extends between the sealing surface and the mounting flange. The airseal body includes a cavity configured to absorb thermal energy transferred into the airseal from a flowpath of the turbine engine. A gas turbine engine includes a rotating component and a stationary component located radially outboard of the rotating component. An airseal is located therebetween and includes a sealing surface and a mounting flange to secure the airseal to the stationary component. An airseal body extends between the sealing surface and the mounting flange and includes a cavity to absorb thermal energy transferred into the airseal.
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Patent Agency Ranking
公开(公告)号：US10184354B2
公开(公告)日：2019-01-22
申请号：US14787320
申请日：2014-05-30
Applicant: United Technologies Corporation
Inventor： Philip Robert Rioux , Nicholas R. Leslie , Neil L. Tatman
Abstract: A heat shield includes a first end configured to connect to an inner engine case at an inner connecting point, and a second end configured to connect to an outer engine case at an outer connecting point. The heat shield also includes a bulge extending in an aft direction from a radially upstream portion. A compressor section and a gas turbine engine including the heat shield are also disclosed.
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公开(公告)号：US10132187B2
公开(公告)日：2018-11-20
申请号：US14910341
申请日：2014-08-07
Applicant: United Technologies Corporation
Inventor： Neil L. Tatman , Philip Robert Rioux
Abstract: A clearance control assembly for a gas turbine engine includes a clearance control ring to position a blade outer air seal assembly radially relative to a blade tip. The clearance control ring is compression fit to the blade outer air seal assembly.
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公开(公告)号：US10018118B2
公开(公告)日：2018-07-10
申请号：US14762092
申请日：2013-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Philip Robert Rioux , Rishon Saftler
CPC classification number: F02C7/18 , F01D25/243 , F01D25/246 , F02C6/08 , F05D2240/12 , Y10T29/49828
Abstract: A splitter for protecting parts of a gas turbine engine is provided. The splitter segregates the flow of hot and cold gases into the air bleed manifold around the high compressor section to reduce maximum temperatures and minimize the temperature gradients of engine parts, especially inner case flanges The splitter divides the air bleed manifold into an annular inner cavity and an outer cavity. The splitter directs relatively cold air from the high compressor bleed ducts into the inner cavity and relatively hot air from the aft hub into the outer cavity, away from the inner case flanges.
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公开(公告)号：US20170226876A1
公开(公告)日：2017-08-10
申请号：US15017798
申请日：2016-02-08
Applicant: United Technologies Corporation
Inventor： Philip Robert Rioux , Paul M. Lutjen
CPC classification number: F01D9/041 , F01D5/12 , F01D5/225 , F01D9/00 , F01D11/005 , F01D11/08 , F01D25/12 , F05D2220/32
Abstract: A static component for a gas turbine engine includes an axially extending body comprising a forward end and an aft end disposed axially downstream from the forward end. A rib is formed on at least one of the forward end and the aft end of the axially extending body and extending axially from the axially extending body. A recess is formed in the rib.
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公开(公告)号：US20170146024A1
公开(公告)日：2017-05-25
申请号：US14947494
申请日：2015-11-20
Applicant: United Technologies Corporation
Inventor： Nicholas R. Leslie , Mark J. Rogers , Philip Robert Rioux
CPC classification number: F04D29/526 , F01D11/08 , F01D11/12 , F01D11/122 , F01D11/18 , F01D11/24 , F04D29/164 , F04D29/321 , F05D2220/32
Abstract: An airseal for sealing between a rotating component and a stationary component of a turbine engine includes a sealing surface defining a spacing between the airseal and a rotating component of the turbine engine and a mounting flange to secure the airseal to a stationary component of the turbine engine. An airseal body extends between the sealing surface and the mounting flange. The airseal body includes a cavity configured to absorb thermal energy transferred into the airseal from a flowpath of the turbine engine. A gas turbine engine includes a rotating component and a stationary component located radially outboard of the rotating component. An airseal is located therebetween and includes a sealing surface and a mounting flange to secure the airseal to the stationary component. An airseal body extends between the sealing surface and the mounting flange and includes a cavity to absorb thermal energy transferred into the airseal.
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