公开(公告)号：US09714580B2

公开(公告)日：2017-07-25

申请号：US14907461

申请日：2014-07-24

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D11/00 ,  F04D29/08 ,  F04D29/54 ,  F16J15/06 ,  F16J15/08

CPC classification number: F01D11/008 ,  F01D11/006 ,  F04D29/083 ,  F04D29/542 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2250/75 ,  F16J15/06 ,  F16J15/062 ,  F16J15/0887

Abstract: This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal provided between the mate face of the first engine component and the mate face of the second engine component. The seal includes least one trough.

公开(公告)号：US11261739B2

公开(公告)日：2022-03-01

申请号：US15863441

申请日：2018-01-05

Applicant: United Technologies Corporation

Inventor： Nicholas M. LoRicco

IPC: F01D5/18 ,  F01D5/14 ,  F01D9/04

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：US11243158B2

公开(公告)日：2022-02-08

申请号：US16706211

申请日：2019-12-06

Applicant: United Technologies Corporation

Inventor： Xuan Liu ,  Zhong Ouyang ,  Andrew DeBiccari ,  Nicholas M. LoRicco ,  William J. Brindley ,  Kathryn Macauley ,  Christopher J. Bischof

IPC: G01R33/00 ,  G01N17/04 ,  B64F5/60 ,  B64D27/12 ,  G01R33/12

Abstract: A method is provided that involves rotational equipment that includes a case and a first rotor blade within the case. During the method, a probe is arranged within the case adjacent the first rotor blade. A magnetic characteristic of the first rotor blade is measured using the probe. Presence of internal corrosion within the first rotor blade is determined based on the measured magnetic characteristic.

公开(公告)号：US10648343B2

公开(公告)日：2020-05-12

申请号：US15886054

申请日：2018-02-01

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F01D9/06 ,  F01D9/04 ,  F01D25/12 ,  F02C3/04

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. An 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. A resupply hole fluidly connects the main-body core cooling passage and at least one of the airfoil skin cooling passage and the platform skin cooling passage.

公开(公告)号：US10415394B2

公开(公告)日：2019-09-17

申请号：US15102890

申请日：2014-12-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Mosheshe Camara-Khary Blake ,  Timothy J. Jennings ,  Nicholas M. LoRicco ,  Sasha M. Moore ,  Clifford J. Musto

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/20 ,  F01D5/28

Abstract: A blade for a gas turbine engine includes an airfoil that extends a span from a root to a tip. The airfoil is provided by a first portion near the root and has a metallic alloy. A third portion near the tip has a refractory material. A second portion joins the first and third portions and has a functional graded material.

公开(公告)号：US10196902B2

公开(公告)日：2019-02-05

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 ,  F01D25/12 ,  F04D29/32 ,  F01D9/06

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.

公开(公告)号：US10006371B2

公开(公告)日：2018-06-26

申请号：US14827050

申请日：2015-08-14

Applicant: United Technologies Corporation

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

IPC: F02C7/18 ,  F01D5/18 ,  F01D9/06 ,  F01D9/02 ,  F02C3/04 ,  F23R3/00

CPC classification number: F02C7/18 ,  F01D5/186 ,  F01D9/023 ,  F01D9/065 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/005 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine component is described. The component includes a component wall having an internal surface that is adjacent a flow of coolant and an external surface that is adjacent a flow of gas. The component wall includes a cooling hole that has an inlet defined by the internal surface and an outlet defined by the external surface. The cooling holes also has a metering location having the smallest cross-section area of the cooling hole, an internal diffuser positioned between the inlet and the metering location, an accumulation diverter portion of the internal diffuser and an accumulator portion of the internal diffuser.

公开(公告)号：US20170136531A1

公开(公告)日：2017-05-18

申请号：US14943787

申请日：2015-11-17

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Nicholas M. LoRicco

IPC: B22D17/20

CPC classification number: B22D17/2038 ,  B22D17/2023 ,  B22D17/203

Abstract: A die casting plunger tip assembly includes a first portion having a closed end defining an outer surface, and a tip cover disposed on the outer surface of the closed end.

公开(公告)号：US20160177737A1

公开(公告)日：2016-06-23

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 ,  F01D11/08 ,  F04D29/32 ,  F04D29/54 ,  F01D9/04 ,  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.

Abstract translation: 燃气涡轮发动机部件包括提供外表面和内部流路表面的壁。 薄膜冷却孔延伸穿过壁并构造成将内部流动通道表面流体连接到外部表面。 薄膜冷却孔具有面向内部流动路径并且基本上在纵向方向上延伸的凹部。 薄膜冷却孔具有从凹部下游的部分，并且相对于纵向方向以一定角度布置并延伸到外表面。

公开(公告)号：US20160108739A1

公开(公告)日：2016-04-21

申请号：US14852896

申请日：2015-09-14

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  B22C9/10

CPC classification number: F01D5/186 ,  B22C9/10 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/187 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2240/127 ,  F05D2260/202 ,  F05D2260/2212 ,  Y02T50/676

Abstract: A wall of a gas turbine engine is provided. The wall may comprise an external surface adjacent a gas path and an internal surface adjacent an internal flow path. A film hole may have an inlet at the internal surface and an outlet at the external surface. A flow accumulator adjacent the inlet may protrude from the internal surface. A method of making an engine component is also provided and comprises the step of forming a component wall comprising an accumulator on an internal surface and a film hole defined by the component wall. The film hole may include an opening adjacent the accumulator and defined by the internal surface.

Abstract translation: 提供燃气涡轮发动机的壁。 壁可以包括邻近气体通道的外表面和与内部流动路径相邻的内部表面。 薄膜孔可以在内表面具有入口，在外表面可以具有出口。 靠近入口的流动蓄能器可从内表面突出。 还提供了一种制造发动机部件的方法，包括在内表面上形成包括蓄能器的部件壁和由部件壁限定的薄膜孔的步骤。 薄膜孔可以包括邻近蓄电池并由内表面限定的开口。