公开(公告)号：US20160333733A1

公开(公告)日：2016-11-17

申请号：US15107591

申请日：2015-01-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Robertson, JR.

IPC: F01D25/00 ,  B29C45/14 ,  F01D9/04 ,  B33Y80/00 ,  B22F7/08 ,  B22F5/04 ,  B33Y10/00

CPC classification number: F01D25/005 ,  B22F3/1055 ,  B22F5/04 ,  B22F7/08 ,  B22F2999/00 ,  B29C45/14819 ,  B29C70/68 ,  B29K2705/00 ,  B29L2031/082 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y80/00 ,  F01D5/147 ,  F01D9/041 ,  F01D17/162 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2250/11 ,  F05D2250/75 ,  F05D2300/43 ,  F05D2300/436 ,  F05D2300/44 ,  F05D2300/603 ,  Y02P10/295

Abstract: A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for use in a gas turbine engine are also disclosed.

Abstract translation: 用于燃气涡轮发动机的部件包括由塑料形成的翼型体。 加强部分具有由金属材料形成并且延伸到翼型中的腹板。 还公开了一种燃气涡轮发动机，以及形成用于燃气轮机的部件的方法。

公开(公告)号：US20190353040A1

公开(公告)日：2019-11-21

申请号：US15982648

申请日：2018-05-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Robertson, JR. ,  Carney R. Anderson ,  Peter T. Schutte

IPC: F01D5/28 ,  B29C33/12

Abstract: An airfoil bonding system may comprise a mold tool configured to support an airfoil assembly during a bonding process. The bonding process may include applying heat and pressure to the airfoil assembly. A surface of the mold tool may complement a preselected airfoil parameter. The mold tool may maintain the airfoil assembly in the preselected airfoil parameter during the application of heat and pressure to the airfoil assembly.

公开(公告)号：US20160201505A1

公开(公告)日：2016-07-14

申请号：US14914840

申请日：2014-08-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven C. Clarkson ,  Thomas J. Robertson, JR. ,  Michael Parkin

IPC: F01D25/00 ,  F01D11/08 ,  F01D25/24

CPC classification number: F01D25/005 ,  F01D11/08 ,  F01D21/045 ,  F01D25/243 ,  F02C7/20 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/14 ,  F05D2300/43 ,  F05D2300/603 ,  F05D2300/614 ,  Y02T50/672

Abstract: A turbine engine fan case (48) comprises a composite body member (300) circumscribing an axis (500) and having an annular mounting portion (310, 410), a segmented polymer member (320, 330, 420, 440) along the annular mounting portion, and integrated therewith.

Abstract translation: 涡轮发动机风扇壳体（48）包括围绕轴线（500）并具有环形安装部分（310,410）的复合主体部件（300），沿着环形部分的分段聚合物部件（320,330,420,440） 安装部分，并与其一体化。

公开(公告)号：US20150023780A1

公开(公告)日：2015-01-22

申请号：US14322527

申请日：2014-07-02

Applicant: United Technologies Corporation

Inventor： Mark W. Costa ,  Thomas J. Robertson, JR. ,  David A. Welch

IPC: F04D29/52 ,  F04D29/64 ,  F04D29/66

CPC classification number: F04D29/526 ,  F01D11/18 ,  F01D25/246 ,  F02C7/045 ,  F04D29/644 ,  F05D2230/642 ,  Y02T50/672 ,  Y10T29/49229

Abstract: A gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface. A hole extends axially into the forward end of the liner between the radially outer surface and the radially inner surface, and an engagement member is partially disposed in the hole and extends axially forward from the forward end of the liner.

Abstract translation: 燃气涡轮发动机包括围绕流路设置的衬套。 衬套具有前端，径向外表面和径向内表面。 孔在径向外表面和径向内表面之间轴向延伸到衬垫的前端，并且接合构件部分地设置在孔中并且从衬套的前端轴向向前延伸。

公开(公告)号：US20160169044A1

公开(公告)日：2016-06-16

申请号：US14969608

申请日：2015-12-15

Applicant: United Technologies Corporation

Inventor： Steven Clarkson ,  Thomas J. Robertson, JR.

IPC: F01D25/24 ,  F01D25/00

CPC classification number: F01D25/24 ,  F01D21/045 ,  F01D25/005 ,  F02K3/06 ,  F05D2230/60 ,  F05D2250/15 ,  F05D2250/25 ,  F05D2300/603 ,  Y02T50/672

Abstract: A method of making a liner for a turbomachinery case includes overlaying a reinforcing layer and a release layer. The method also includes spiral coiling the reinforcing layer and the release layer about the axis of the liner such that a radially inner surface of the release layer radially overlays a radially outer surface of the reinforcing layer.

Abstract translation: 制造用于涡轮机械壳体的衬套的方法包括覆盖增强层和释放层。 该方法还包括围绕衬套的轴线螺旋卷绕增强层和释放层，使得释放层的径向内表面径向覆盖加强层的径向外表面。

公开(公告)号：US20150345326A1

公开(公告)日：2015-12-03

申请号：US14728779

申请日：2015-06-02

Applicant: United Technologies Corporation

Inventor： Thomas J. Robertson, JR. ,  Steven Clarkson

IPC: F01D25/00 ,  F01D25/24

CPC classification number: F01D25/005 ,  F01D21/045 ,  F01D25/24 ,  F02C7/05 ,  F05D2240/14 ,  F05D2300/603 ,  Y02T50/672

Abstract: A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a containment case and a cartridge liner carried therein. A ballistic liner encircles at least a portion of the cartridge liner and is attached thereto.

Abstract translation: 涡轮风扇发动机具有具有圆周阵列的风扇叶片的风扇。 风扇外壳包围风扇。 至少有一个压缩机部分，燃烧器和至少一个涡轮部分。 风扇壳体包括容纳在其中的容纳壳体和筒衬套。 弹道衬垫围绕筒衬的至少一部分并且附接到其上。

公开(公告)号：US20150275692A1

公开(公告)日：2015-10-01

申请号：US14432356

申请日：2013-02-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Robertson, JR. ,  Sreenivasa R. Voleti ,  Mark W. Costa ,  Steven Clarkson

IPC: F01D25/24 ,  F01D5/14 ,  F01D25/30 ,  F01D5/02

CPC classification number: F01D25/24 ,  F01D5/021 ,  F01D5/147 ,  F01D5/28 ,  F01D21/045 ,  F01D25/30 ,  F05D2220/30 ,  F05D2240/24 ,  F05D2250/283 ,  F05D2300/121 ,  F05D2300/173 ,  F05D2300/612 ,  Y02T50/672

Abstract: A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.

Abstract translation: 叶片容纳系统包括多个周向布置的可旋转叶片。 每个刀片具有刀片顺应性。 围绕可旋转叶片设置环形容纳结构。 密封结构包括具有衬垫柔顺性的衬垫。 叶片顺应性和衬套顺应性被构造成使得在与衬套撞击时在相应的一个叶片上引起的应变小于阈值临界应变，超过该临界应变可旋转叶片断裂。

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。

公开(公告)号：US20180171826A1

公开(公告)日：2018-06-21

申请号：US15888493

申请日：2018-02-05

Applicant: United Technologies Corporation

Inventor： Thomas J. Robertson, JR. ,  Mark W. Costa ,  Steven Clarkson

IPC: F01D25/28 ,  G01D11/30 ,  F01D25/24

CPC classification number: F01D25/28 ,  F01D25/24 ,  F05D2230/60 ,  F05D2240/90 ,  F05D2300/121 ,  F05D2300/603 ,  G01D11/30 ,  Y02T50/672

Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.

公开(公告)号：US20160108821A1

公开(公告)日：2016-04-21

申请号：US14857886

申请日：2015-09-18

Applicant: United Technologies Corporation

Inventor： Thomas J. Robertson, JR. ,  Nathan F. Champion ,  Steven J. Feigleson

IPC: F02C9/54 ,  F02C7/32 ,  F01D25/24 ,  F01D17/14 ,  F01D25/26 ,  F02C3/04 ,  F01D9/04

Abstract: A split case assembly for a gas turbine engine includes an outer diameter case defining a partial case structure for a gas turbine engine and multiple fixed-variable vanes attached to an inner diameter surface of the outer diameter case. Each of the fixed-variable vanes protrudes radially inward from the outer diameter case. Each of the fixed-variable vanes in the plurality of fixed-variable vanes is interfaced with one of a plurality of inner diameter boxes at a radially inward end of the fixed-variable vane, such that the inner diameter boxes define an inner diameter of a flow path and the outer diameter case defines an outer diameter flow path. Each of the fixed-variable vanes are interfaced with the one of the plurality of inner diameter boxes through at least one inner diameter shoe in a plurality of inner diameter shoes.

Abstract translation: 用于燃气涡轮发动机的分体式壳体组件包括限定用于燃气涡轮发动机的部分壳体结构的外径壳体和附接到外径壳体的内径表面的多个固定可变叶片。 每个固定可变叶片从外径壳体径向向内突出。 多个固定可变叶片中的每个固定可变叶片与固定可变叶片的径向内侧端部的多个内径盒中的一个接合，使得内径盒限定内径 流动路径和外径壳体限定外径流动路径。 每个固定可变叶片通过多个内径鞋中的至少一个内径鞋与多个内径盒中的一个相接合。