公开(公告)号：US10458433B2

公开(公告)日：2019-10-29

申请号：US15185573

申请日：2016-06-17

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier ,  James F. O'Brien

IPC: F04D29/52 ,  F04D29/66 ,  F04D29/02 ,  B29C70/72 ,  B29C70/02 ,  F01D21/04 ,  F01D5/28 ,  F01D25/24 ,  B29C70/86 ,  B29C70/88

Abstract: A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.

公开(公告)号：US20190162119A1

公开(公告)日：2019-05-30

申请号：US15823229

申请日：2017-11-27

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier ,  David R. Lyders

IPC: F02C7/20 ,  F01D5/14 ,  F02K3/062

Abstract: A reinforced component in accordance with various embodiments includes a metal lug configured to be attached to a secondary component. The reinforced component further includes a composite material integrally formed around the metal lug and configured to be retained in place relative to the secondary component via an attachment between the metal lug and the secondary component.

公开(公告)号：US09651059B2

公开(公告)日：2017-05-16

申请号：US13728200

申请日：2012-12-27

Applicant: United Technologies Corporation

Inventor： Thomas J. Robertson, Jr. ,  Darin S. Lussier ,  Kirk D. Stackhouse ,  Johan Santana

IPC: F04D29/52 ,  F04D29/02 ,  F01D11/12

CPC classification number: F04D29/526 ,  F01D11/122 ,  F01D11/127 ,  F04D29/023 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2250/283 ,  F05D2300/431 ,  F05D2300/501 ,  F05D2300/50212 ,  Y02T50/672

Abstract: A section of a gas turbine engine includes a case structure and a liner. The liner is attached to the case structure by a compliant adhesive. The adhesive covers at least a portion of the liner surface area, and can have interruptions used to tune the compliance of the adhesive layer.

公开(公告)号：US20160160678A1

公开(公告)日：2016-06-09

申请号：US14958548

申请日：2015-12-03

Applicant: United Technologies Corporation

Inventor： Darin S. Lussier

IPC: F01D21/04 ,  F01D25/24

CPC classification number: F01D21/04 ,  F01D25/24 ,  F01D25/28 ,  F05D2300/603 ,  Y02T50/672

Abstract: The present disclosure relates generally to a system for handling a gas turbine engine fan case. The system includes a composite fan containment case including a case outer surface, a case inner surface, and at least one main case aperture extending from the case outer surface through the case inner surface, and at least one shear puck, the at least one shear puck including a shear puck protrusion; wherein the shear puck protrusion of each of the at least one shear pucks is disposed within a respective one of each of the at least one main case apertures.

Abstract translation: 本公开总体上涉及一种用于处理燃气涡轮发动机风扇壳体的系统。 该系统包括复合风扇容纳壳体，其包括壳体外表面，壳体内表面以及从壳体外表面穿过壳体内表面延伸的至少一个主壳体孔，以及至少一个剪切盘，所述至少一个剪切 圆盘包括剪切弹弓突起; 其中所述至少一个剪切圆盘中的每一个的剪切圆盘突起设置在所述至少一个主壳体孔中的每一个中的相应一个中。

公开(公告)号：US20160032831A1

公开(公告)日：2016-02-04

申请号：US14693488

申请日：2015-04-22

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier

IPC: F02C7/04 ,  B29C43/02 ,  F02C3/04

CPC classification number: F02C7/04 ,  B29C43/021 ,  B29C2043/026 ,  B29K2101/00 ,  B29L2031/7504 ,  B64C11/14 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2240/20 ,  F05D2240/35 ,  F05D2300/43 ,  Y02T50/671

Abstract: A spinner for a fan assembly of a gas turbine engine, a method of fabricating a spinner for a fan assembly of a gas turbine engine, and a gas turbine engine are disclosed. The fan section may include a nosecap. The spinner may include a forward end, an aft end, and a return flange associated with the forward end. The return flange may include a forward flange extending forward towards the nosecap and an aft flange extending aft towards the aft end.

Abstract translation: 公开了一种用于燃气涡轮发动机的风扇组件的旋转器，制造用于燃气涡轮发动机的风扇组件的旋转器和燃气涡轮发动机的方法。 风扇部分可以包括nosecap。 旋转器可以包括前端，后端和与前端相关联的返回凸缘。 返回凸缘可以包括向前朝向鼻尖延伸的前凸缘和向后端向后延伸的后凸缘。

公开(公告)号：US20160024969A1

公开(公告)日：2016-01-28

申请号：US14875627

申请日：2015-10-05

Applicant: United Technologies Corporation

Inventor： Larry Foster ,  Darin S. Lussier

IPC: F01D25/24 ,  B65H81/02

CPC classification number: F01D25/24 ,  B29C70/222 ,  B32B1/08 ,  B32B5/08 ,  B32B5/26 ,  B65H81/02 ,  D04C1/00 ,  F01D21/045 ,  F01D25/243 ,  F02C7/04 ,  F02K1/78 ,  F04D29/023 ,  F04D29/40 ,  F04D29/522 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/30 ,  F05D2300/6012 ,  F05D2300/603 ,  Y02T50/672 ,  Y10T428/13

Abstract: A preform sheet for a composite component comprises a body section and a flange section. The preform body section includes a plurality of axial tows braided with at least a plurality of first bias tows and a plurality of second bias tows. The preform flange section includes a first braided flange layer and a second braided flange layer. The first braided flange layer is defined by the first and second braided bias tows of the preform body section extending into the flange section. Neither the first nor second braided flange layers have axial tows.

Abstract translation: 用于复合部件的预制片材包括主体部分和凸缘部分。 预成型体主体部分包括编织有至少多个第一偏置丝束和多个第二偏置丝束的多个轴向丝束。 预成型件凸缘部分包括第一编织凸缘层和第二编织法兰层。 第一编织凸缘层由延伸到凸缘部分中的预成型体主体部分的第一和第二编织偏压丝束限定。 第一和第二编织凸缘层都不具有轴向丝束。

公开(公告)号：US20140286748A1

公开(公告)日：2014-09-25

申请号：US13714821

申请日：2012-12-14

Applicant: United Technologies Corporation

Inventor： Mark W. Costa ,  Thomas J. Robertson, JR. ,  Darin S. Lussier

IPC: F01D21/04

CPC classification number: F01D21/045 ,  F05D2300/121 ,  F05D2300/431 ,  F05D2300/501 ,  F05D2300/502 ,  Y02T50/672

Abstract: A fan section of a gas turbine engine includes a fan containment case assembly includes an outer case of an aluminum alloy. The outer case extends circumferentially around an axial centerline. A thermally conforming liner assembly is located inwardly of the outer case. The thermally conforming liner assembly includes a circumferential liner of an aluminum alloy. A ballistic liner is located between the outer case and the thermally conforming liner assembly.

Abstract translation: 燃气涡轮发动机的风扇部分包括具有铝合金外壳的风扇收容箱组件。 外壳围绕轴向中心线周向延伸。 热适应衬套组件位于外壳的内侧。 热适应衬套组件包括铝合金的圆周衬套。 弹道衬套位于外壳和热适应衬套组件之间。