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公开(公告)号：US20200018185A1
公开(公告)日：2020-01-16
申请号：US16036513
申请日：2018-07-16
Applicant: United Technologies Corporation
Inventor： Mark W. Costa
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.
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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
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。
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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。
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公开(公告)号：US10731511B2
公开(公告)日：2020-08-04
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
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.
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公开(公告)号：US10533450B2
公开(公告)日：2020-01-14
申请号：US15797178
申请日：2017-10-30
Applicant: United Technologies Corporation
Inventor： Colin J. Kling , Darin S. Lussier , Mark W. Costa
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.
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Patent Agency Ranking
公开(公告)号：US10436612B2
公开(公告)日：2019-10-08
申请号：US14919225
申请日：2015-10-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Kevin Ford , Eli Warren , Corey A. Benoit , Edward F Dreger , Erik D. Rice , Mark W. Costa
IPC: G01D5/241 , G01B7/14 , F01D17/02 , F01D5/02 , F01D21/00 , F01D25/24 , F04D29/32 , G01M15/14 , F01D11/20
Abstract: A capacitance probe monitors the distance between a blade tip and a fan, compressor or turbine case. The capacitance probe may be attached to a liner, and may travel with the liner as it radially expands due to thermal changes. The capacitance probe may include a circuit board sensor with a metallic plate, and one or more capacitors. The metallic plate may be encapsulated within an insulating material. A plurality of soft leads may be in electrical communication with the circuit board sensor, allowing a lower lead weight, reduced size and increased flexibility. The soft leads may also be embedded in the liner. In this way, the capacitance probe can record more accurate distance measurements and promote a gas turbine engine's continued and efficient operation.
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公开(公告)号：US20190063460A1
公开(公告)日：2019-02-28
申请号：US15686255
申请日：2017-08-25
Applicant: United Technologies Corporation
Inventor： Mark W. Costa
CPC classification number: F04D29/526 , F01D11/122 , F01D21/045 , F02K3/06 , F04D29/023 , F05D2220/323 , F05D2220/36 , F05D2230/60 , F05D2240/14 , F05D2240/15 , F05D2240/20 , F05D2250/283 , F05D2300/603
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.
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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
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.
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公开(公告)号：US09702375B2
公开(公告)日：2017-07-11
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
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.
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公开(公告)号：US09482111B2
公开(公告)日：2016-11-01
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
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。
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