公开(公告)号：US11591914B2

公开(公告)日：2023-02-28

申请号：US16426036

申请日：2019-05-30

Applicant: United Technologies Corporation

Inventor： Dipanjan Saha ,  Brooks E. Snyder ,  Thomas N. Slavens

IPC: F01D5/18 ,  B23K26/34 ,  B33Y80/00 ,  B33Y10/00 ,  F01D9/04 ,  F01D25/12 ,  B22F5/04 ,  B22F7/08 ,  B23K101/00 ,  B22F10/20

Abstract: A gas turbine engine assembly according to an example of the present disclosure includes, among other things, an endwall having a first material composition, an airfoil extending in a radial direction from the endwall, and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. A method of forming an endwall is also disclosed.

公开(公告)号：US10960460B2

公开(公告)日：2021-03-30

申请号：US15112009

申请日：2015-01-23

Applicant: United Technologies Corporation

Inventor： Brooks E. Snyder ,  Thomas N. Slavens ,  Mark F. Zelesky ,  James T. Auxier

IPC: B22C9/04 ,  B33Y80/00 ,  B22C7/02 ,  B22C9/10 ,  B22F5/00 ,  B22F3/105 ,  B22F7/06 ,  B22C21/14 ,  B33Y10/00 ,  B22C1/00 ,  B29L31/00 ,  B29C64/153

Abstract: A mold for manufacturing a casted workpiece is, at least in-part, manufactured utilizing an additive manufacturing process. The mold may have a core having non-line-of-sight features that are additively manufactured and in contact with an outer shell of a wax mold and/or an outer shell of a casting mold of the mold. The outer shell of either the wax or casting molds may also be additively manufactured, and the shell of the casting mold may be additively manufactured as one unitary piece to the core.

公开(公告)号：US20190316474A1

公开(公告)日：2019-10-17

申请号：US16426036

申请日：2019-05-30

Applicant: United Technologies Corporation

Inventor： Dipanjan Saha ,  Brooks E. Snyder ,  Thomas N. Slavens

IPC: F01D5/18 ,  B33Y10/00 ,  B33Y80/00 ,  F01D9/04 ,  F01D25/12 ,  B23K26/34

Abstract: A gas turbine engine assembly according to an example of the present disclosure includes, among other things, an endwall having a first material composition, an airfoil extending in a radial direction from the endwall, and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. A method of forming an endwall is also disclosed.

公开(公告)号：US20160177740A1

公开(公告)日：2016-06-23

申请号：US14923511

申请日：2015-10-27

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Brooks E. Snyder

IPC: F01D5/18 ,  F01D11/08 ,  F23R3/00 ,  F02C3/04 ,  F02C7/18 ,  F01D9/04 ,  F01D25/12

CPC classification number: F01D5/187 ,  F01D5/143 ,  F05D2200/263 ,  F05D2230/21 ,  F05D2240/81 ,  F05D2250/322 ,  F05D2250/71 ,  F05D2260/202 ,  F23R3/002 ,  Y02T50/673 ,  Y02T50/676

Abstract: A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a first portion connected to a second portion via a curved surface. An inlet is formed in or near one of the first and second portions to receive a cooling air flow. An outlet is formed in or near the other of the first and second portions to direct cooling flow along a surface of the gas turbine engine component. At least one cooling path extends between the inlet and the outlet and has at least one cooling path portion that conforms in shape to the curved surface. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.

Abstract translation: 用于燃气涡轮发动机的冷却回路包括燃气涡轮发动机部件，其具有通过弯曲表面连接到第二部分的第一部分。 入口形成在第一和第二部分中的一个中或其附近，以接收冷却空气流。 出口形成在第一和第二部分中的另一个中或其附近，以沿着燃气涡轮发动机部件的表面引导冷却流。 至少一个冷却通道在入口和出口之间延伸，并且具有至少一个冷却通道部分，其形状与弯曲表面一致。 还公开了一种燃气涡轮发动机和形成燃气涡轮发动机的冷却回路的方法。

公开(公告)号：US10436039B2

公开(公告)日：2019-10-08

申请号：US15032736

申请日：2014-10-10

Applicant: United Technologies Corporation

Inventor： Brooks E. Snyder ,  Thomas N. Slavens

IPC: F01D5/18 ,  F01D5/20 ,  B22F3/105 ,  B22F5/04 ,  B22F7/08 ,  B23K26/342 ,  B22D25/02 ,  B23K15/00 ,  B33Y10/00 ,  B33Y80/00

Abstract: A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang.

公开(公告)号：US10344597B2

公开(公告)日：2019-07-09

申请号：US14828063

申请日：2015-08-17

Applicant: United Technologies Corporation

Inventor： Dipanjan Saha ,  Brooks E. Snyder ,  Thomas N. Slavens

IPC: B22F5/04 ,  B22F7/08 ,  F01D5/18 ,  F01D9/04 ,  B22F3/105 ,  B23K26/34 ,  B33Y10/00 ,  B33Y80/00 ,  F01D25/12 ,  B23K101/00

Abstract: An exemplary method of forming an endwall with a contour includes casting an endwall with at least one cooling channel having an opening from the endwall, and covering the opening with a cupped contour formed on the endwall. An exemplary gas turbine engine blade assembly includes an endwall with a plurality of cooling channels, an airfoil extending radially from the endwall to a tip, and a cupped contour formed on the endwall to provide a cooling chamber between the cupped contour and a radially facing surface of the endwall.

公开(公告)号：US10094229B2

公开(公告)日：2018-10-09

申请号：US14811122

申请日：2015-07-28

Applicant: United Technologies Corporation

Inventor： Brooks E. Snyder ,  Michael G. McCaffrey ,  Thomas N. Slavens

IPC: F01D5/08 ,  F01D9/02 ,  F02C7/18 ,  F01D17/16 ,  F01D9/06

Abstract: A cooling system integrated into a stator assembly of a gas turbine engine has an on-board injector or cooling nozzle located for cooling of a rotor assembly. The nozzle may be generally annular and may contain a plurality of pivoting airfoils circumferentially spaced from one-another for directing cooling air flow from the nozzle and generally toward a plurality of holes in a cover of the rotor assembly. The pivoting airfoils are adapted to move between a spoiled state where the mass flow of cooling air is reduced, and to an optimal state where the mass flow is increased. The system may further include a plurality of fixed airfoils in the nozzle with adjacent fixed airfoils defining a discharge orifice in the nozzle. Each one of the plurality of pivoting airfoils may be located in a respective discharge orifice.

公开(公告)号：US20170314398A1

公开(公告)日：2017-11-02

申请号：US15140093

申请日：2016-04-27

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Brooks E. Snyder

IPC: F01D5/18 ,  B33Y80/00 ,  B33Y10/00

CPC classification number: F01D5/187 ,  B33Y10/00 ,  B33Y80/00 ,  F05D2250/314 ,  F05D2250/71 ,  F05D2250/75 ,  F05D2260/22141 ,  Y02T50/676

Abstract: An internally cooled component of a gas turbine engine is provided. The component may include a cooling passage at least partially defined by a first wall and a second wall with a first pedestal extending from the first wall to the second wall. The first pedestal may have a chevron geometry. A second pedestal may extend from the first wall to the second wall and also have a chevron geometry. A gap may be defined by the first pedestal and the second pedestal with the gap oriented between the first pedestal and the second pedestal.

公开(公告)号：US20160318072A1

公开(公告)日：2016-11-03

申请号：US15109020

申请日：2015-01-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Martin ,  Alexander Staroselsky ,  Sergey Mironets ,  Thomas N. Slavens ,  Brooks E. Snyder

IPC: B07B7/08 ,  B23K15/00 ,  B29C67/00 ,  B23K26/342

CPC classification number: B07B7/08 ,  B07B4/025 ,  B07B7/01 ,  B07B13/04 ,  B07B13/07 ,  B07B13/10 ,  B07B13/16 ,  B07B13/18 ,  B22F3/1055 ,  B22F2003/1056 ,  B22F2003/1059 ,  B23K15/0086 ,  B23K26/342 ,  B29C64/153 ,  B29C64/20 ,  B29C64/35 ,  B29K2105/251 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y40/00 ,  Y02P10/295

Abstract: A aerodynamic particle separator for an Additive Manufacturing System (AMS) has an air supply device to entrain a mixed powder in an airstream flowing through a housing. Each particle in the mixed powder is imparted with a momentum dependent upon the particle weight and size. Utilizing this momentum characteristic, the heavier particles are capable of crossing streamlines of the airstream at a bend portion of the housing and the lighter particles generally stay within the streamlines. Utilizing this dynamic characteristic, the particles of specific weight ranges are collected through respective offtake holes in the housing and controllably fed to a spreader of the AMS.

Abstract translation: 用于添加剂制造系统（AMS）的空气动力学粒子分离器具有空气供应装置，以将混合粉末夹带在流过壳体的气流中。 赋予混合粉末中的每个颗粒具有取决于颗粒重量和尺寸的动量。 利用这种动量特征，较重的颗粒能够在壳体的弯曲部分处穿过气流的流线，并且较轻的颗粒通常保持在流线内。 利用该动态特性，通过壳体中的相应的出口孔收集特定重量范围的颗粒，并且可控地馈送到AMS的撒布机。

公开(公告)号：US20160273365A1

公开(公告)日：2016-09-22

申请号：US15035837

申请日：2014-11-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Brooks E. Snyder

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/02

CPC classification number: F01D5/187 ,  F01D5/18 ,  F01D5/186 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages. The first cooling passage is arranged near the leading edge. A radially extending trench is in the leading edge. An impingement hole is provided in the interior wall and is configured to direct a cooling fluid from the second cooling passage to the first cooling passage and onto the exterior wall at the leading edge.

Abstract translation: 燃气涡轮发动机翼型件包括翼型结构，其包括由具有前缘的外壁提供的外表面。 翼型结构内的径向延伸的内壁分隔第一和第二径向冷却通道。 第一个冷却通道设置在前缘附近。 径向延伸的沟槽位于前缘。 冲击孔设置在内壁中并且构造成将冷却流体从第二冷却通道引导到第一冷却通道并且在前缘处引导到外壁上。