公开(公告)号：US20210062667A1

公开(公告)日：2021-03-04

申请号：US16571678

申请日：2019-09-16

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo, JR. ,  Brandon W. Spangler ,  Lane Thornton

IPC: F01D11/00 ,  F01D25/24

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.

公开(公告)号：US20200018174A1

公开(公告)日：2020-01-16

申请号：US16562630

申请日：2019-09-06

Applicant: United Technologies Corporation

Inventor： Carey Clum ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  B22C9/10 ,  B22C9/04 ,  F01D25/12 ,  F01D9/02

Abstract: Core assemblies for manufacturing airfoils and airfoils made therefrom are described. The core assemblies having a leading edge hybrid skin core positioned relative to a plurality of core bodies and configured to define a leading edge cavity at a leading edge of the manufactured airfoil. The leading edge hybrid skin core extends from a root region toward a tip region in a radial direction, the leading edge hybrid skin core extends above at least one of the plurality of core bodies to define an exit in a tip region of the manufactured airfoil, and the leading edge hybrid skin core has a height-to-width ratio of about 0.8 or less.

公开(公告)号：US20190383149A1

公开(公告)日：2019-12-19

申请号：US16010776

申请日：2018-06-18

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08

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.

公开(公告)号：US20190310030A1

公开(公告)日：2019-10-10

申请号：US16280179

申请日：2019-02-20

Applicant: United Technologies Corporation

Inventor： Michael A. Disori ,  William P. Stillman ,  Alexander Broulidakis ,  Dave J. Hyland ,  Jeremy Styborski ,  Adam J. Diener ,  Matthew A. Devore ,  Dominic J. Mongillo, JR.

IPC: F28F3/06 ,  F28F13/06

Abstract: A featured embodiment of a cast plate heat exchanger assembly includes a cast plate including a plate portion defining a plurality of internal passages. A plurality of fin portions extend from the plate portion. First augmentation structures are disposed on surfaces of the fin portions for conditioning cooling airflow to enhance transfer of thermal energy. A method is also disclosed.

公开(公告)号：US20190226344A1

公开(公告)日：2019-07-25

申请号：US15875500

申请日：2018-01-19

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco ,  Ricardo Trindade ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  F01D9/06

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.

公开(公告)号：US20190211688A1

公开(公告)日：2019-07-11

申请号：US15865883

申请日：2018-01-09

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/04 ,  F02C3/04

CPC classification number: F01D5/186 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F02C3/04 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2240/81 ,  F05D2250/75 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2260/22141

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.

公开(公告)号：US20190169994A1

公开(公告)日：2019-06-06

申请号：US15832430

申请日：2017-12-05

Applicant: United Technologies Corporation

Inventor： Christopher Whitfield ,  Carey Clum ,  Dominic J. Mongillo, JR.

IPC: F01D5/18

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 core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin 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 core passage and the skin passage are configured to have a same direction of fluid flow. A slot extends longitudinally in the skin passage. A resupply hole fluidly interconnects the core passage and the slot.

公开(公告)号：US20190112942A1

公开(公告)日：2019-04-18

申请号：US15783318

申请日：2017-10-13

Applicant: United Technologies Corporation

Inventor： Carey Clum ,  Dominic J. Mongillo, JR.

IPC: F01D25/12 ,  F01D5/18 ,  F01D9/04

Abstract: A component for a gas turbine engine includes an outer surface bounding a hot gas path of the gas turbine engine, and a cooling passage configured to deliver a cooling airflow therethrough. The cooling passage includes a passage wall located opposite the outer surface to define a component thickness and a plurality of protrusions located along the passage wall. Each protrusion has a protrusion height extending from the passage wall and a protrusion streamwise width extending along the passage wall in a flow direction of the cooling airflow through the cooling passage. One or more cooling holes extend from the passage wall to the outer surface. A cooling hole inlet of a cooling hole is located at the passage wall, in a protrusion wake region downstream of a protrusion of the plurality of protrusions.

公开(公告)号：US20190071979A1

公开(公告)日：2019-03-07

申请号：US15790505

申请日：2017-10-23

Applicant: United Technologies Corporation

Inventor： Shawn M. McMahon ,  Christopher Whitfield ,  Kristopher K. Anderson ,  Jason B. Moran ,  Brett Alan Bartling ,  Christopher Perron ,  Justin M. Aniello ,  Stephanie Tanner ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  F01D9/04 ,  B23H1/00 ,  B23P15/02

Abstract: A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.

公开(公告)号：US20180355731A1

公开(公告)日：2018-12-13

申请号：US16049987

申请日：2018-07-31

Applicant: United Technologies Corporation

Inventor： Benjamin F. Hagan ,  Ryan Alan Waite ,  Bryan P. Dube ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D5/14 ,  F01D9/06 ,  F01D5/22

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/18 ,  F01D5/225 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/22141

Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots. The platform includes a rib that is elongated in a length direction between the platform leading and trailing ends. The rib divides two of the cooling passages such that the two cooling passages are fluidly unconnected with each other in the platform.