公开(公告)号：US20180283189A1

公开(公告)日：2018-10-04

申请号：US15473222

申请日：2017-03-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew B. Estes ,  Bryan P. Dube

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F04D29/666 ,  F05D2250/38 ,  F05D2250/73 ,  F05D2260/961 ,  Y02T50/672 ,  Y02T50/673

Abstract: An asymmetric vane assembly includes a high count vane section including a first plurality of vanes oriented in a first position. The asymmetric vane assembly also includes a low count vane section including a second plurality of vanes oriented in a second position, a total number of vanes in the first plurality of vanes being greater than a total number of vanes in the second plurality of vanes, and each vane of the high count vane section and each vane of the low count vane section having substantially similar internal core geometry.

公开(公告)号：US20160230593A1

公开(公告)日：2016-08-11

申请号：US15022039

申请日：2014-08-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mark F. Zelesky ,  Bryan P. Dube ,  Jesse R. Christophel

IPC: F01D25/00 ,  F01D25/12 ,  F02C3/04 ,  F01D9/04

CPC classification number: F01D25/005 ,  F01D5/189 ,  F01D5/284 ,  F01D9/041 ,  F01D25/12 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2300/17 ,  F05D2300/176 ,  F05D2300/20 ,  F05D2300/5023

Abstract: An airfoil assembly includes an airfoil that has an exterior wall that defines an interior cavity. The exterior wall extends between a leading end and a trailing end and an open inboard end and an open outboard end. The exterior wall is formed of a high temperature-resistant material selected from refractory metal-based alloys, ceramic-based material or combinations thereof. A support frame extends in the interior cavity and protrudes from the interior cavity through at least one of the open inboard end and the open outboard end.

Abstract translation: 机翼组件包括具有限定内部空腔的外壁的翼型件。 外壁在前端和后端之间延伸，内侧开放，外侧开放。 外壁由选自耐火金属基合金，陶瓷基材料或其组合的耐高温材料形成。 支撑框架在内部空腔中延伸并且通过开放的内侧端部和敞开的外侧端部中的至少一个从内部空腔突出。

公开(公告)号：US20160146040A1

公开(公告)日：2016-05-26

申请号：US14933497

申请日：2015-11-05

Applicant: United Technologies Corporation

Inventor： Alex J. Simpson ,  Bryan P. Dube ,  John E. Paul

IPC: F01D25/06 ,  F04D29/32 ,  F01D5/02 ,  F01D9/04

CPC classification number: F01D25/06 ,  F01D9/041 ,  F04D29/544 ,  F04D29/666 ,  F05D2260/961

Abstract: A vane assembly for a gas turbine engine may include a plurality of vanes being arranged in vane groupings symmetrically spaced circumferentially from each other. Each vane grouping may include at least a first and a second vane. The at least first and second vanes may be spaced from each other at a first pitch. Each vane grouping may be spaced from each other at a second pitch. The first pitch may be dissimilar from the second pitch.

Abstract translation: 用于燃气涡轮发动机的叶片组件可以包括多个叶片，其布置在叶片组中，彼此对称地间隔开。 每个叶片组可包括至少第一和第二叶片。 所述至少第一和第二叶片可以以第一间距彼此间隔开。 每个叶片组可以以第二间距彼此间隔开。 第一音调可能与第二音高不同。

公开(公告)号：US20160076383A1

公开(公告)日：2016-03-17

申请号：US14856512

申请日：2015-09-16

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Jesse M. Carr ,  Bryan P. Dube ,  Yongxiang D. Xue

IPC: F01D5/18 ,  F01D25/12 ,  F23R3/00 ,  F02C7/24 ,  F23R3/06 ,  F01D11/08 ,  F02C7/18

CPC classification number: F01D5/186 ,  F01D9/065 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F02C7/24 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2250/14 ,  F05D2260/202 ,  F05D2300/16 ,  F05D2300/20 ,  F05D2300/6033 ,  F23R3/002 ,  F23R3/06 ,  Y02T50/672 ,  Y02T50/676

Abstract: A film cooled component includes multiple film cooling holes. At least one of the film cooling holes has an elliptical cross sectional opening along the exterior surface of the film cooled component.

Abstract translation: 膜冷却部件包括多个膜冷却孔。 薄膜冷却孔中的至少一个具有沿着薄膜冷却部件的外表面的椭圆形横截面开口。

公开(公告)号：US09038700B2

公开(公告)日：2015-05-26

申请号：US13708036

申请日：2012-12-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Bryan P. Dube ,  Ryan Shepard Levy ,  Richard H. Page

IPC: B22C9/00 ,  B22C9/10 ,  B22C9/04 ,  F01D5/18 ,  B22D29/00

CPC classification number: B22C9/10 ,  B22C9/04 ,  B22C9/108 ,  B22D29/001 ,  F01D5/187 ,  F05D2230/00 ,  F05D2230/21 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/185 ,  F05D2300/13

Abstract: The present disclosure is directed to a refractory metal core for use in forming varying thickness microcircuits in turbine engine components, a process for forming the refractory metal core, and a process for forming the turbine engine components. The refractory metal core is used in the casting of a turbine engine component. The core is formed by a sheet of refractory metal material having a curved trailing edge portion integrally formed with a leading edge portion.

Abstract translation: 本公开涉及用于在涡轮发动机部件中形成变化的厚度微电路的难熔金属芯，用于形成耐火金属芯的方法以及用于形成涡轮发动机部件的工艺。 耐火金属芯用于涡轮发动机部件的铸造。 芯由具有与前缘部一体形成的弯曲后缘部的耐火金属材料片形成。

公开(公告)号：US11352894B2

公开(公告)日：2022-06-07

申请号：US16690959

申请日：2019-11-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Alyson T. Burdette ,  Bryan P. Dube ,  Rutva A. Patel ,  Nicholas Broulidakis

IPC: F01D9/02

Abstract: An airfoil piece includes at least one inner ceramic matrix composite ply which defines an internal cavity of an airfoil section and first and second collar projections. At least one inner ceramic matrix composite ply is continuous through the airfoil section and first and second collar projections, first and second platforms at the first and second ends of the airfoil section. The first and second collar projections extend radially past the first and second platforms, respectively. A vane for a gas turbine engine and a method of assembling a vane are also disclosed.

公开(公告)号：US11280214B2

公开(公告)日：2022-03-22

申请号：US14878555

申请日：2015-10-08

Applicant: United Technologies Corporation

Inventor： Jesse M. Carr ,  Bryan P. Dube

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

Abstract: A gas turbine engine component includes an exterior pressure side with a plurality of cooling holes located in the exterior pressure side. A relief cut surrounds at least one of the plurality of cooling holes.

公开(公告)号：US11268401B2

公开(公告)日：2022-03-08

申请号：US15022039

申请日：2014-08-21

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky ,  Bryan P. Dube ,  Jesse R. Christophel

IPC: F01D25/00 ,  F01D5/28 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F02C3/04

Abstract: An airfoil assembly includes an airfoil that has an exterior wall that defines an interior cavity. The exterior wall extends between a leading end and a trailing end and an open inboard end and an open outboard end. The exterior wall is formed of a high temperature-resistant material selected from refractory metal-based alloys, ceramic-based material or combinations thereof. A support frame extends in the interior cavity and protrudes from the interior cavity through at least one of the open inboard end and the open outboard end.

公开(公告)号：US11242762B2

公开(公告)日：2022-02-08

申请号：US16690989

申请日：2019-11-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Alyson T. Burdette ,  Bryan P. Dube ,  Rutva A. Patel ,  Nicholas Broulidakis

IPC: F01D9/04 ,  F01D5/14 ,  B28B11/00

Abstract: An airfoil piece includes a first vane platform, a second vane platform, and a hollow airfoil section that joins the first vane platform and the second vane platform. The hollow airfoil section includes a collar projection which extends past the first vane platform. The collar projection includes at least one radial tab projecting therefrom. An airfoil assembly and a method of assembling a vane are also disclosed.

公开(公告)号：US20210262354A1

公开(公告)日：2021-08-26

申请号：US16797133

申请日：2020-02-21

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Bryan P. Dube

IPC: F01D5/28 ,  F01D5/14 ,  B28B1/00

Abstract: Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The fibrous core has a three dimensional braided structure and cooling passages. A method of making the ceramic matrix component is also disclosed.