公开(公告)号：US10954815B2

公开(公告)日：2021-03-23

申请号：US16589290

申请日：2019-10-01

Applicant: United Technologies Corporation

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

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

Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.

公开(公告)号：US10648363B2

公开(公告)日：2020-05-12

申请号：US15856232

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: F01D25/12 ,  F01D9/02

Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

公开(公告)号：US10533425B2

公开(公告)日：2020-01-14

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

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：US10480347B2

公开(公告)日：2019-11-19

申请号：US15874070

申请日：2018-01-18

Applicant: United Technologies Corporation

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

IPC: F01D9/04 ,  F01D25/08 ,  F01D25/12

Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.

公开(公告)号：US20160201475A1

公开(公告)日：2016-07-14

申请号：US14854606

申请日：2015-09-15

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F01D9/04 ,  F04D29/32 ,  F01D25/12

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F04D29/321 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/127 ,  F05D2240/30 ,  F05D2240/81 ,  F05D2260/202 ,  F23R2900/03041 ,  F23R2900/03042 ,  Y02T50/676

Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.

Abstract translation: 燃气涡轮发动机部件包括具有围绕内部空腔的壁的主体。 墙壁与内部和外部表面相对。 内表面具有多个冷却剂入口，并且外表面具有限定在其中的冷却剂出口。 冷却剂导管在冷却剂入口和冷却剂出口之间延伸，并且被构造和适于在冷却剂中引导二次流动涡流，所述冷却剂穿过冷却剂管道以及在组件主体的外表面的一部分上的粘附冷却剂膜中。

公开(公告)号：US10465530B2

公开(公告)日：2019-11-05

申请号：US15102335

申请日：2014-11-17

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D5/18 ,  F01D5/28 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F23R3/00

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a body, a wall extending inside of the body and a plurality of vortex promoting features arranged in a helical pattern along the wall.

公开(公告)号：US20190218932A1

公开(公告)日：2019-07-18

申请号：US15874070

申请日：2018-01-18

Applicant: United Technologies Corporation

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

IPC: F01D25/12 ,  F01D9/04

CPC classification number: F01D25/12 ,  F01D5/18 ,  F01D5/188 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/126 ,  F05D2260/202

Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.

公开(公告)号：US20190211687A1

公开(公告)日：2019-07-11

申请号：US15863441

申请日：2018-01-05

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco

IPC: F01D5/18 ,  F01D9/04 ,  F01D5/14

CPC classification number: F01D5/18 ,  F01D5/183 ,  F01D5/188 ,  F01D5/189 ,  F05D2240/126

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a first cavity, a second cavity, and a rib extending from a suction sidewall to a pressure sidewall and separating the first cavity from the second cavity. The rib includes a central portion, a first edge portion extending from the pressure sidewall to the central portion, and a second edge portion extending from the suction sidewall to the central portion. The rib defines one or more communication openings from the first cavity to the second cavity in the first or second edge portion.

公开(公告)号：US20190186291A1

公开(公告)日：2019-06-20

申请号：US15845727

申请日：2017-12-18

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco ,  Steven Bruce Gautschi

IPC: F01D25/12 ,  F02C7/18 ,  F01D9/04

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 skin core 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 skin core cooling passage is divided by a wall into two discrete first and second skin core cooling passages each supplied with cooling fluid from opposing sides.

公开(公告)号：US20190176228A1

公开(公告)日：2019-06-13

申请号：US16275468

申请日：2019-02-14

Applicant: United Technologies Corporation

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

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

Abstract: A gas turbine engine includes a structure that has walls that provide a cooling passage and a cooling surface. A non-ferrous obstruction is relative to the walls. The obstruction includes a portion spaced from the cooling surface to provide a gap which is configured to receive a cooling fluid.