-
公开(公告)号：US20160003158A1
公开(公告)日：2016-01-07
申请号：US14790951
申请日：2015-07-02
Applicant: United Technologies Corporation
Inventor： Joe Ott , Stanley J. Funk , Roger O. Coffey , Shawn Stempinski , John J. Rup, JR. , Lyutsia Dautova , Dennis M. Moura
CPC classification number: F02C7/222 , F05D2220/32 , F23N1/00 , F23N2035/16 , F23R3/14 , F23R3/28 , F23R3/36 , F23R2900/00001
Abstract: A fluid dispensing apparatus that may be additive manufactured as one unitary piece and may be a fuel injector for a gas turbine engine includes a radial displacement bellows having an outer surface that faces and may be exposed to a surrounding environment and an interior surface that faces and may define at least in-part a flowpath extending along a centerline. The radial displacement bellows is constructed and arranged to move between an expanded state when a pressure differential between the environment and the flowpath is low to a restricted state when the pressure differential is high.
Abstract translation: 可以作为一个整体件制成的并且可以是用于燃气涡轮发动机的燃料喷射器的流体分配装置包括径向位移波纹管，其具有面向并可能暴露于周围环境的外表面和面向和 可以至少部分地限定沿着中心线延伸的流路。 当压差高时，径向位移波纹管被构造和布置成当环境和流路之间的压差低到受限状态时在膨胀状态之间移动。
-
12.发明授权公开(公告)号：US11415319B2
公开(公告)日：2022-08-16
申请号：US16208993
申请日：2018-12-04
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Carey Clum
Abstract: A gas turbine engine component assembly is provided. The gas turbine engine component assembly, comprising: a first component having a first surface, a second surface opposite the first surface, and a cooling hole extending from the second surface to the first surface through the first component; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow from the particulate.
-
公开(公告)号：US20200292172A1
公开(公告)日：2020-09-17
申请号：US16799083
申请日：2020-02-24
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Jonathan J. Eastwood , Lee E. Bouldin , Monica Pacheco-Tougas
Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.
-
公开(公告)号：US10731858B2
公开(公告)日：2020-08-04
申请号：US14913795
申请日：2014-09-16
Applicant: United Technologies Corporation
Inventor： Lee E. Bouldin , Jonathan J. Eastwood , Dennis M. Moura , Monica Pacheco-Tougas
Abstract: A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity. The first impingement cavity operates at a first pressure and the second impingement cavity operates at a second pressure that is different than the first pressure.
-
公开(公告)号：US10683952B2
公开(公告)日：2020-06-16
申请号：US15825947
申请日：2017-11-29
Applicant: United Technologies Corporation
Inventor： Joe Ott , Dennis M. Moura , Stanley J. Funk , Shawn Stempinski , Roger O. Coffey , John J. Rup, Jr. , Gary A. Schirtzinger , Lexia Kironn
Abstract: A method is provided involving an additive manufacturing system. This method includes a step of forming a first fluid conduit using the additive manufacturing system. The method also includes a step of providing a fluid coupling. The fluid coupling includes the first fluid conduit and a second fluid conduit. The first fluid conduit is connected to and fluidly coupled with the second fluid conduit. The first fluid conduit has a first configuration. The second fluid conduit has a second configuration that is different than the first configuration.
-
Patent Agency Ranking
公开(公告)号：US10508759B2
公开(公告)日：2019-12-17
申请号：US15661791
申请日：2017-07-27
Applicant: United Technologies Corporation
Inventor： Joe Ott , John J. Rup, Jr. , Shawn Stempinski , Stanley J. Funk , Dennis M. Moura , Lexia Kironn , Roger O. Coffey
IPC: F16L9/18 , B33Y10/00 , B23P15/00 , F23R3/28 , B33Y80/00 , B22F3/105 , F16L59/14 , F02C7/22 , B22F5/10
Abstract: A flowpath assembly has a first conduit defining a flowpath radially inward, and a second conduit spaced radially outward from the first conduit. A void defined between the first and second conduits contains an insulating material that may have a greater porosity than the first and second conduits. The assembly may be additive manufactured generally as one unitary piece with the raw material of the conduits being melted and solidified on a slice-by-slice basis and the insulating material being selectively bypassed by an energy gun of an additive manufacturing system.
-
17.发明申请公开(公告)号：US20190186739A1
公开(公告)日：2019-06-20
申请号：US16210434
申请日：2018-12-05
Applicant: United Technologies Corporation
Inventor： Dennis M. Moura , Carey Clum
CPC classification number: F23R3/002 , F01D5/189 , F01D9/065 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/607 , F23M5/08 , F23R3/005 , F23R2900/00004 , F23R2900/03042 , F23R2900/03044
Abstract: A gas turbine engine component assembly comprising: a first component having a first surface, a second surface opposite the first surface, a first cooling hole located in a first section of the first component extending from the second surface to first surface, and a second cooling hole located in a second section of the first component extending from the second surface to first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; wherein the first cooling hole is configured to direct at least one of the airflow and the particulate to impinge upon the second surface of the second component at first directional flow angle.
-
公开(公告)号：US20190078785A1
公开(公告)日：2019-03-14
申请号：US15698967
申请日：2017-09-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A. Propheter-Hinckley , Atul Kohli , Benjamin D. Bellows , Brandon W. Spangler , David J. Hyland , Dennis M. Moura , Dustin W. Davis , Mark F. Zelesky , Ricardo Trindade , Stephen K. Kramer , Steven Bruce Gautschi , Trevor Rudy
CPC classification number: F23R3/60 , F23R3/002 , F23R3/06 , F23R3/54 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.
-
公开(公告)号：US20190063323A1
公开(公告)日：2019-02-28
申请号：US15690555
申请日：2017-08-30
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Shawn M. McMahon , Kevin Zacchera , Noah Wadsworth , Christopher Whitfield , Sean D. Bradshaw , Dennis M. Moura
Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.
-
公开(公告)号：US10208673B2
公开(公告)日：2019-02-19
申请号：US14790951
申请日：2015-07-02
Applicant: United Technologies Corporation
Inventor： Joe Ott , Stanley J. Funk , Roger O. Coffey , Shawn Stempinski , John J. Rup, Jr. , Lyutsia Dautova , Dennis M. Moura
Abstract: A fluid dispensing apparatus that may be additive manufactured as one unitary piece and may be a fuel injector for a gas turbine engine includes a radial displacement bellows having an outer surface that faces and may be exposed to a surrounding environment and an interior surface that faces and may define at least in-part a flowpath extending along a centerline. The radial displacement bellows is constructed and arranged to move between an expanded state when a pressure differential between the environment and the flowpath is low to a restricted state when the pressure differential is high.
-
-
-
-
-
-
-
-
-
Search Results
73
records
(took 0.021 seconds)
