公开(公告)号：US20150337661A1

公开(公告)日：2015-11-26

申请号：US14761360

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew G. Alarcon ,  Christopher M. Quinn ,  James Glaspey ,  Matthew A. Turner

IPC: F01D5/02 ,  F01D5/30

CPC classification number: F01D5/02 ,  F01D5/025 ,  F01D5/30 ,  F01D5/3053 ,  F01D11/008 ,  F05D2220/10 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/80 ,  F05D2260/30 ,  Y02T50/671 ,  Y10T29/49334

Abstract: Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.

Abstract translation: 提供了用于燃气涡轮发动机的风扇部分中的平台的防旋转突出部。 防旋转翼片与旋转器的后缘接合，从而防止平台旋转和扭转。

公开(公告)号：US10329925B2

公开(公告)日：2019-06-25

申请号：US14903076

申请日：2014-06-26

Applicant: United Technologies Corporation

Inventor： Sreenivasa R. Voleti ,  Christopher M. Quinn

IPC: F01D5/16 ,  F01D5/26 ,  F04D29/02 ,  F04D29/32 ,  F01D5/28 ,  F01D9/04

Abstract: A turbine engine component (100) comprises a fiber structure (125, 126) forming at least a portion of an airfoil (102). A matrix (128) embeds the fiber structure. A carbon nanotube filler (130) is in the matrix.

公开(公告)号：US10018048B2

公开(公告)日：2018-07-10

申请号：US14761360

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew G. Alarcon ,  Christopher M. Quinn ,  James Glaspey ,  Matthew A. Turner

IPC: F01D5/02 ,  F01D5/30 ,  F01D11/00

CPC classification number: F01D5/02 ,  F01D5/025 ,  F01D5/30 ,  F01D5/3053 ,  F01D11/008 ,  F05D2220/10 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/80 ,  F05D2260/30 ,  Y02T50/671 ,  Y02T50/673 ,  Y10T29/49334

Abstract: Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.

公开(公告)号：US20150226130A1

公开(公告)日：2015-08-13

申请号：US14428379

申请日：2013-02-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Keith T. Salamon ,  Matthew A. Turner ,  Christopher M. Quinn

IPC: F02C7/28 ,  F01D9/02 ,  F02C3/10

CPC classification number: F02C7/28 ,  F01D9/02 ,  F01D11/001 ,  F02C3/10 ,  F05D2220/36

Abstract: A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.

Abstract translation: 燃气涡轮发动机包括核心发动机，联接成由发动机驱动的风扇，围绕铁芯发动机的第一壳体结构和围绕风扇的第二壳体结构。 第一壳体结构和第二壳体结构在其间限定旁路通道。 叶片结构包括在第一壳体结构和第二壳体结构之间径向延伸的翼型件。 密封件构造成控制旁通通道和核心发动机之间的泄漏。

公开(公告)号：US20150218966A1

公开(公告)日：2015-08-06

申请号：US14426252

申请日：2013-09-17

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Charles W. Brown ,  Christopher M. Quinn ,  Shelton O. Duelm ,  Peter V. Tomeo ,  Corey L. Hubbert

IPC: F01D25/28 ,  F01D25/24 ,  F02C3/10

CPC classification number: F01D25/28 ,  F01D11/008 ,  F01D25/24 ,  F02C3/10 ,  Y02T50/671 ,  Y10T29/4932

Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.

Abstract translation: 一种用于燃气涡轮发动机的风扇轮毂组件，其包括被配置为围绕轴线旋转的风扇轮毂。 风扇毂具有轴向延伸的孔和平台。 紧固件以滑动配合关系容纳在孔中，以将平台固定到风扇毂。

公开(公告)号：US20180100408A1

公开(公告)日：2018-04-12

申请号：US15836254

申请日：2017-12-08

Applicant: United Technologies Corporation

Inventor： Darin S. Lussier ,  Sreenivasa R. Voleti ,  Thomas J. Robertson, JR. ,  Christopher M. Quinn

IPC: F01D21/04 ,  B29C70/22

CPC classification number: F01D21/045 ,  B29C70/202 ,  B29C70/226 ,  B29C70/228 ,  B29C70/32 ,  B29D99/006 ,  B29L2031/7504 ,  F02C7/04 ,  F05D2300/6012 ,  F05D2300/603

Abstract: A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.