公开(公告)号：US20200011348A1

公开(公告)日：2020-01-09

申请号：US16555322

申请日：2019-08-29

Applicant: United Technologies Corporation

Inventor： Thomas J. Robertson ,  Mark W. Costa

IPC: F04D29/64 ,  F04D29/52

Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.

公开(公告)号：US10480530B2

公开(公告)日：2019-11-19

申请号：US15686255

申请日：2017-08-25

Applicant: United Technologies Corporation

Inventor： Mark W. Costa

IPC: F04D29/52 ,  F02K3/06 ,  F01D21/04 ,  F01D11/12 ,  F04D29/02

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan containment case assembly that has an outer case extending about an axis, and a thermally conforming liner assembly radially inward of the outer case. The liner assembly has a shell, a wrap radially outward of the shell, and a ballistic liner between the outer case and the wrap. The wrap has a first fiber construction, and the ballistic liner has a second fiber construction that differs from the first fiber construction in stiffness.

公开(公告)号：US20190128136A1

公开(公告)日：2019-05-02

申请号：US15797178

申请日：2017-10-30

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier ,  Mark W. Costa

IPC: F01D21/04 ,  B29C63/34 ,  F01D25/24 ,  B29C53/56

CPC classification number: F01D21/045 ,  B29C53/562 ,  B29C63/34 ,  F01D21/04 ,  F01D25/24 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2250/15 ,  F05D2300/603

Abstract: A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.

公开(公告)号：US20160076395A1

公开(公告)日：2016-03-17

申请号：US14946175

申请日：2015-11-19

Applicant: United Technologies Corporation

Inventor： Steven Clarkson ,  Mark W. Costa

IPC: F01D25/02 ,  B29C70/06 ,  B29C65/00 ,  F01D25/24

Abstract: The present disclosure relates to methods of manufacturing ice panel segments for turbofan engines. An ice panel material may be wrapped around a mandrel. The ice panel material may include an inner fiberglass layer, a plurality of KEVLAR® layers, and an outer fiberglass layer. The ice panel material may be bagged and cured into a rigid molded cylinder. The rigid molded cylinder may be radially cut into ice panel cylinders. The ice panel cylinders may be axially cut into ice panel segments. The ice panel segments may be bonded to an inner surface of a fan case.

Abstract translation: 本公开涉及制造用于涡轮风扇发动机的冰面板段的方法。 冰面板材料可以缠绕在心轴上。 冰面板材料可以包括内玻璃纤维层，多个KEVLAR层和外玻璃纤维层。 冰块材料可以装袋并固化成刚性模制圆筒。 刚性模制圆柱体可以径向切割成冰面板圆筒。 冰面板圆柱体可以轴向切割成冰块段。 冰面板段可以结合到风扇壳体的内表面。

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：US11236769B2

公开(公告)日：2022-02-01

申请号：US16555322

申请日：2019-08-29

Applicant: United Technologies Corporation

Inventor： Thomas J. Robertson ,  Mark W. Costa

IPC: F04D29/64 ,  F01D25/24 ,  F01D9/04 ,  F04D29/52

Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.

公开(公告)号：US10669936B2

公开(公告)日：2020-06-02

申请号：US14774035

申请日：2014-03-12

Applicant: United Technologies Corporation

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

IPC: F02C7/04 ,  B64D33/02 ,  F02C7/045 ,  F01D11/12

Abstract: A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.

公开(公告)号：US09909458B2

公开(公告)日：2018-03-06

申请号：US14613755

申请日：2015-02-04

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01B25/26 ,  F01D25/28 ,  F01D25/24 ,  G01D11/30

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：US20150275689A1

公开(公告)日：2015-10-01

申请号：US14161860

申请日：2014-01-23

Applicant: United Technologies Corporation

Inventor： Darin S. Lussier ,  Thomas J. Robertson, JR. ,  Mark W. Costa ,  Sreenivasa R. Voleti ,  Rajiv A. Naik

IPC: F01D25/00 ,  F02K3/06 ,  F01D25/24

CPC classification number: F01D25/005 ,  F01D21/045 ,  F01D25/243 ,  F02K3/06 ,  F05D2230/50 ,  F05D2240/14 ,  F05D2300/603 ,  Y02T50/672

Abstract: A fan case for a gas turbine engine includes a composite fan containment case that includes an outer surface. The composite fan containment case includes multiple composite layers that define a generally cylindrical case. An attachment flange extends radially outward from the cylindrical case. The attachment flange comprises a portion of the composite layers. A metallic backing ring is secured to the attachment flange by rivets.

Abstract translation: 用于燃气涡轮发动机的风扇壳体包括包括外表面的复合风扇容纳壳体。 复合风扇容纳箱包括限定大致圆柱形壳体的多个复合层。 连接凸缘从圆柱形壳体径向向外延伸。 附接凸缘包括一部分复合层。 金属背衬环通过铆钉固定到附件凸缘上。

公开(公告)号：US10724403B2

公开(公告)日：2020-07-28

申请号：US16036513

申请日：2018-07-16

Applicant: United Technologies Corporation

Inventor： Mark W. Costa

IPC: F01D11/12 ,  F01D25/24 ,  F04D29/52 ,  F01D11/08 ,  F01D21/04

Abstract: A fan case assembly for a gas turbine engine includes a honeycomb structure. The fan case assembly also includes a septum operatively coupled to the honeycomb structure and located radially inward of the honeycomb structure. The fan case assembly further includes a rubstrip in contact with the septum and located radially inward of the septum.