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公开(公告)号：US11781439B2
公开(公告)日：2023-10-10
申请号：US16571678
申请日：2019-09-16
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Brandon W. Spangler , Lane Thornton
CPC classification number: F01D11/006 , F01D11/005 , F01D25/246 , F05D2240/11 , F05D2240/57 , F05D2250/182 , Y02T50/60
Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
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公开(公告)号：US10808552B2
公开(公告)日：2020-10-20
申请号：US16010776
申请日：2018-06-18
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo, Jr.
Abstract: A gaspath component for a gas turbine engine includes a platform having at least one internal cooling passage. The at least one internal cooling passage has a plurality of trip strips extending into the cooling passage from at least one internal surface of the cooling passage. Each of the trip strips is defined by a z-shaped configuration.
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公开(公告)号：US10794195B2
公开(公告)日：2020-10-06
申请号：US15671328
申请日：2017-08-08
Applicant: United Technologies Corporation
Inventor： Carey Clum , Dominic J. Mongillo, Jr.
Abstract: Airfoils including an airfoil body having leading and trailing edges and root and tip regions, wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from root to tip, a forward-flowing serpentine flow path formed within the airfoil body defined by a first serpentine cavity, a second serpentine cavity, and a third serpentine cavity, wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity, a tip flag cavity extending aftward from proximate the leading edge to the trailing edge along the tip region, and at least one shielding cavity located between a portion of the forward-flowing serpentine flow path and an external surface of the airfoil body.
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公开(公告)号：US10704396B2
公开(公告)日：2020-07-07
申请号：US15876579
申请日：2018-01-22
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Ricardo Trindade , Dominic J. Mongillo, Jr.
Abstract: Components for gas turbine engines are provided. The components include a hot external wall that is exposed to hot gaspath air when installed within a gas turbine engine, and an interior impingement wall, wherein the interior impingement wall defines a feed cavity and at least one impingement cavity is defined between the impingement wall and the external wall. The impingement wall includes a plurality of impingement holes that fluidly connect the feed cavity to the at least one impingement cavity, the external wall includes a plurality of film holes that fluidly connect the at least one impingement cavity to an exterior surface of the external wall, and wherein the only source of cooling air within the at least one impingement cavity is the feed cavity.
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公开(公告)号：US10697307B2
公开(公告)日：2020-06-30
申请号：US15875500
申请日：2018-01-19
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Ricardo Trindade , Dominic J. Mongillo, Jr.
Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a first platform and a second platform, a first platform feed cavity defined by the first platform, a second platform exit cavity defined by the second platform, a first hybrid skin core cooling cavity passage formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity, and at least one purge aperture formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform. The airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body.
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Patent Agency Ranking
46.发明授权公开(公告)号：US10662780B2
公开(公告)日：2020-05-26
申请号：US15865883
申请日：2018-01-09
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Dominic J. Mongillo, Jr.
Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. A airfoil skin cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The airfoil skin cooling passage extends to a platform skin cooling passage arranged in the platform. The platform skin cooling passage resupplied by a backside of the platform.
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公开(公告)号：US10655496B2
公开(公告)日：2020-05-19
申请号：US15852198
申请日：2017-12-22
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Adam P. Generale
Abstract: Component for gas turbine engines are provided. The components include a platform, the platform defining a platform cavity on a first side, an airfoil extending from a second side of the platform, wherein the airfoil comprises at least one airfoil cavity located within the airfoil, the at least one airfoil cavity fluidly connected to the platform cavity through an airfoil cavity inlet, and a platform flow turning element positioned on the first side of the platform, the platform flow turning element having a turning portion and a tapering portion, wherein the turning portion directs incoming air to turn from the platform cavity into the airfoil cavity and the tapering portion extends through the airfoil cavity inlet and into the airfoil cavity.
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公开(公告)号：US10458253B2
公开(公告)日：2019-10-29
申请号：US15864456
申请日：2018-01-08
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr.
IPC: F01D5/18
Abstract: Components for gas turbine engines are provided. The components include a hybrid skin core cooling cavity defined by a cold wall and a hot wall, wherein the hot wall is exposed to an exterior environment of the component and a resupply hole is formed in the cold wall and fluidly connects a cold core cavity and the cooling cavity. The resupply hole extends between an inlet on a side of the cold wall exposed to the cold core cavity and an outlet on a side of the cold wall exposed to the cooling cavity. The cavity resupply hole is angled relative to the cold wall at an injection angle such that air passing through the cavity resupply hole is injected into the cooling cavity at the injection angle and at least partially parallel to a direction of flow within the hybrid skin core cooling cavity.
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公开(公告)号：US10408071B2
公开(公告)日：2019-09-10
申请号：US15022725
申请日：2014-08-26
Applicant: United Technologies Corporation
Inventor： Scott D. Lewis , Dominic J. Mongillo, Jr. , Mark F. Zelesky , Bret M. Teller , Russell Deibel , Matthew S. Gleiner
Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port.
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公开(公告)号：US10329923B2
公开(公告)日：2019-06-25
申请号：US14633677
申请日：2015-02-27
Applicant: United Technologies Corporation
Inventor： Thomas N. Slavens , Dominic J. Mongillo, Jr. , Matthew A. Devore
Abstract: An example gas turbine engine component includes an airfoil having a leading edge area, a first circuit to cool a first section of the leading edge area, and a second circuit to cool a second section of the leading edge area. The first circuit separate and distinct from the second circuit within the airfoil.
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