公开(公告)号：US10227884B2

公开(公告)日：2019-03-12

申请号：US14909471

申请日：2014-08-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew G. Alarcon

IPC: F01D11/00 ,  F02K3/06 ,  F01D5/30 ,  F01D5/02

Abstract: A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a leading edge to a trailing edge, and between a suction wall and a pressure wall. A circumferential direction is defined between the suction wall and the pressure wall. A tab extend circumferentially outward of one of the suction and pressure walls from the platform. The tab has a circumferentially outermost portion which will abut an inner surface of an adjacent platform when the platform is mounted. A fan section and a gas turbine engine are also disclosed.

公开(公告)号：US09194299B2

公开(公告)日：2015-11-24

申请号：US13724226

申请日：2012-12-21

Applicant: United Technologies Corporation

Inventor： Andrew G. Alarcon

IPC: B23P15/00 ,  F02C7/32 ,  F01D21/04

CPC classification number: F02C7/32 ,  F01D21/045 ,  F01D25/246 ,  F05D2220/36 ,  F05D2230/642 ,  Y02T50/672 ,  Y10T29/49245

Abstract: An anti-torsion assembly for positioning and securing a thermally conforming liner within a fan containment case is provided. The anti-torsion assembly minimizes the amount of machining that must be done prior to assembly. The anti-torsion assembly comprises a torque block with outwardly-opposing side surfaces and a pair of L-brackets. Each L-bracket has a bracket surface that faces one of the outwardly-opposing side surfaces of the torque block. A wear pad is affixed to each bracket surface. The L-brackets are positioned onto the thermally conforming liner using a spacer having a spacer width within a predetermined tolerance. A method of assembling a fan case assembly is also provided.

Abstract translation: 提供了一种用于在风扇容纳壳体内定位和固定热适应衬套的抗扭转组件。 抗扭转组件将组装前必须进行的加工量最小化。 抗扭转组件包括具有向外相对的侧表面的扭矩块和一对L形托架。 每个L形支架具有面向扭矩块的向外相对的侧表面之一的托架表面。 每个支架表面贴有耐磨垫。 使用具有在预定公差内的间隔物宽度的间隔件将L形托架定位在热适应衬垫上。 还提供了组装风扇壳组件的方法。

公开(公告)号：US20150330255A1

公开(公告)日：2015-11-19

申请号：US14443424

申请日：2013-12-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew G. Alarcon

IPC: F01D25/28 ,  F01D25/24

CPC classification number: F01D25/28 ,  F01D21/045 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2230/644 ,  F05D2260/30 ,  F05D2260/36 ,  Y02T50/672 ,  Y10T29/49828

Abstract: An anti-torsion assembly for positioning and securing a thermally conforming liner within a fan containment case is provided. The anti-torsion assembly minimizes relative movement of the thermally conforming liner and the fan containment case by providing a wedge shaped torque block and complimentary shaped L-brackets. A method of assembling a fan case assembly is also provided.

Abstract translation: 提供了一种用于在风扇容纳壳体内定位和固定热适应衬套的抗扭转组件。 抗扭转组件通过提供楔形扭矩块和互补的形状的L形托架来使热适应衬套和风扇容纳壳体的相对运动最小化。 还提供了组装风扇壳组件的方法。

公开(公告)号：US20180195402A1

公开(公告)日：2018-07-12

申请号：US15116713

申请日：2014-12-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew A. Turner ,  Andrew G. Alarcon ,  Shari L. Bugaj

IPC: F01D11/00 ,  F02K3/06 ,  F04D29/32 ,  F01D25/00

CPC classification number: F01D11/008 ,  F01D25/005 ,  F02K3/06 ,  F04D29/329 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/20 ,  F05D2230/31 ,  F05D2230/80 ,  F05D2240/80 ,  F05D2300/434 ,  F05D2300/436 ,  F05D2300/603 ,  Y02T50/672

Abstract: A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path between the plurality of airfoils. The platform may be configured to be disposable during a life of the gas turbine engine.

公开(公告)号：US20160341071A1

公开(公告)日：2016-11-24

申请号：US15113310

申请日：2014-12-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew G. Alarcon ,  Royce E. Tatton ,  Barry M. Ford ,  Linda S. Li ,  Matthew A. Turner

IPC: F01D25/00 ,  B29C70/12 ,  F04D29/32 ,  F01D11/00 ,  F02K3/06

CPC classification number: F01D25/005 ,  B29C70/12 ,  B29D99/0025 ,  B29K2105/12 ,  F01D11/008 ,  F02K3/06 ,  F04D29/325 ,  F05D2220/36 ,  F05D2240/30 ,  F05D2240/80 ,  F05D2300/123 ,  F05D2300/2102 ,  F05D2300/224 ,  F05D2300/434 ,  F05D2300/436 ,  F05D2300/603 ,  Y02T50/672

Abstract: The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.

Abstract translation: 本公开一般涉及用于燃气涡轮发动机的风扇叶片平台领域。 更具体地，本公开涉及一种用于燃气涡轮发动机的压缩的短切纤维风扇叶片平台。

公开(公告)号：US20160258319A1

公开(公告)日：2016-09-08

申请号：US14546752

申请日：2014-11-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew A. Turner ,  Andrew G. Alarcon ,  Shari L. Bugaj

IPC: F01D25/00 ,  F01D9/04

CPC classification number: F01D9/041 ,  F05D2300/2102 ,  F05D2300/224 ,  F05D2300/434 ,  F05D2300/436 ,  F05D2300/6031 ,  F05D2300/614 ,  Y02T50/672

Abstract: The present disclosure relates generally to the field of guide vanes for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber composite inlet guide vane for a gas turbine engine.

Abstract translation: 本公开一般涉及用于燃气涡轮发动机的导向叶片领域。 更具体地，本公开涉及一种用于燃气涡轮发动机的压缩短切纤维复合材料入口引导叶片。

公开(公告)号：US20150117804A1

公开(公告)日：2015-04-30

申请号：US14522885

申请日：2014-10-24

Applicant: United Technologies Corporation

Inventor： Andrew G. Alarcon

IPC: F01D25/16 ,  F16C33/08 ,  F16C17/02

CPC classification number: F16C33/08 ,  F01D5/3053 ,  F05D2220/36 ,  F16C17/02 ,  F16C2360/23 ,  Y02T50/672 ,  Y10T29/49236

Abstract: A gas turbine engine bushing includes a flange area, and an insert area to be received within an aperture. The insert area includes channels and a bond rib. The channels extend axially a channel distance. The bond rib extends axially a bond rib distance. The channel distance is eater than the bond rib distance.

Abstract translation: 燃气涡轮发动机衬套包括凸缘区域和待接收在孔内的插入区域。 插入区域包括通道和接合肋。 通道沿轴向延伸通道距离。 接合肋轴向延伸接合肋距离。 通道距离远远超过键肋距离。

公开(公告)号：US20140169979A1

公开(公告)日：2014-06-19

申请号：US13715388

申请日：2012-12-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew G. Alarcon ,  Royce E. Tatton

IPC: F01D5/14

CPC classification number: F01D11/008 ,  F01D5/3007 ,  F05D2220/36 ,  F05D2250/75 ,  F05D2300/437 ,  Y02T50/673

Abstract: A fan section for a gas turbine engine includes a fan blade having an airfoil with an exterior surface. A platform seal is adhered to the airfoil. A fan section for a gas turbine engine includes a fan hub having a slot. A fan blade includes an airfoil extending from a root to a tip. The root is received in the slot. A platform is secured to the fan hub and is arranged between adjacent fan blades. A seal has a base secured to opposing sides of the fan blade and a flap integral with and extending from the base portion and canted toward the root and engaging the platform to provide a sealed inner flow path.

Abstract translation: 用于燃气涡轮发动机的风扇部分包括具有具有外表面的翼型的风扇叶片。 平台密封件粘附在翼型件上。 用于燃气涡轮发动机的风扇部分包括具有槽的风扇毂。 风扇叶片包括从根部延伸到尖端的翼型件。 根被收到在插槽中。 平台被固定到风扇轮毂并且布置在相邻的风扇叶片之间。 密封件具有固定到风扇叶片的相对侧的基部和与基部一体并且从基部延伸并且朝向根部倾斜并与平台接合以提供密封的内部流动路径的翼片。