公开(公告)号：US20190277144A1

公开(公告)日：2019-09-12

申请号：US15912906

申请日：2018-03-06

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco

IPC: F01D5/18 ,  F01D25/12

Abstract: A component for a gas turbine engine, includes a component outer surface exposed to flowpath gases of the gas turbine engine, a cooling channel located in the component, and at least one channel rib located in the cooling channel extending across the cooling channel from a channel inner surface to a channel outer surface. A cooling slot extends from the cooling channel to a slot outlet at the component outer surface. The slot outlet has a radial width greater than an axial length.

公开(公告)号：US10364683B2

公开(公告)日：2019-07-30

申请号：US15036833

申请日：2014-11-05

Applicant: United Technologies Corporation

Inventor： Brooks E. Snyder ,  Thomas N. Slavens ,  Nicholas M. LoRicco ,  James T. Auxier

IPC: F01D5/18

Abstract: A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.

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：US20190211707A1

公开(公告)日：2019-07-11

申请号：US15863101

申请日：2018-01-05

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco

IPC: F01D25/12 ,  F01D9/02 ,  F01D17/10

CPC classification number: F01D25/12 ,  F01D5/18 ,  F01D5/188 ,  F01D9/02 ,  F01D17/105 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212

Abstract: An airfoil for a gas turbine engine includes a cavity including an internal surface of an outer wall. A baffle is disposed within the cavity and spaced apart from the internal surface. A partition is disposed between the baffle and the internal surface to divide a space between the baffle and the internal surface into at least a first passage and a second passage. A gas turbine engine is also disclosed.

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：US20190211686A1

公开(公告)日：2019-07-11

申请号：US15863289

申请日：2018-01-05

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco

IPC: F01D5/18 ,  F02C3/04

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D5/188 ,  F02C3/04 ,  F05D2240/126 ,  F05D2260/202

Abstract: A gas turbine engine component includes an airfoil that includes a trailing edge feed cavity. A baffle is located in the trailing edge feed cavity and includes a plurality of pressure side cooling openings in fluid communication with a corresponding one of a plurality of pressure side cooling passages. A plurality of suction side cooling openings are in fluid communication with a corresponding one of a plurality of suction side cooling passages.

公开(公告)号：US20190203602A1

公开(公告)日：2019-07-04

申请号：US15856182

申请日：2017-12-28

Applicant: United Technologies Corporation

Inventor： Shawn M. McMahon ,  Christopher Whitfield ,  Nicholas M. LoRicco ,  Steven Bruce Gautschi ,  Vincent E. Simms ,  Justin M. Aniello ,  Thomas Allwood ,  Richard M. Salzillo ,  Jeffery Scott Hembree, SR.

IPC: F01D5/18 ,  F01D9/04

CPC classification number: F01D5/186 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/12 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202

Abstract: A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.

公开(公告)号：US10273820B2

公开(公告)日：2019-04-30

申请号：US15295268

申请日：2016-10-17

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco ,  Mark A. Boeke ,  Jeffrey J. DeGray ,  Richard M. Salzillo ,  Dominic J. Mongillo

IPC: F01D9/06

Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

公开(公告)号：US10259039B2

公开(公告)日：2019-04-16

申请号：US14766061

申请日：2014-01-16

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Lane Thornton ,  Sasha M. Moore ,  Nicholas M. LoRicco

IPC: B22D19/00 ,  B22D29/00 ,  B22C9/10 ,  B22C9/04 ,  F01D5/18 ,  F01D9/02 ,  F23R3/00

Abstract: A method of manufacturing a component that includes providing a core structure, casting a component about the core structure, removing a first portion of the core structure from the cast component, and leaving a second portion of the core structure in the cast component to provide a reduced cross-section in the cast component.

公开(公告)号：US09957814B2

公开(公告)日：2018-05-01

申请号：US14827453

申请日：2015-08-17

Applicant: United Technologies Corporation

Inventor： Clifford J. Musto ,  Sasha M. Moore ,  Thomas N. Slavens ,  San Quach ,  Nicholas M. LoRicco ,  Timothy J. Jennings ,  John McBrien

IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D9/023 ,  F01D9/041 ,  F01D9/065 ,  F01D11/08 ,  F02K1/822 ,  F04D29/324 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/314 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a pocket that faces the interior flow path and extends substantially in a longitudinal direction. The film cooling hole has a portion downstream from the pocket and is arranged at an angle relative to the longitudinal direction and extends to the exterior surface.