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公开(公告)号：US20210222576A1
公开(公告)日：2021-07-22
申请号：US16746229
申请日：2020-01-17
Applicant: United Technologies Corporation
Inventor： Peter Karkos , Darin S. Lussier
IPC: F01D11/00
Abstract: A turbine fan fairing platform is disclosed. The turbine fan fairing platform includes a platform body including a first side portion arranged to abut a first fan blade, a second side portion arranged to abut a second fan blade, and a central portion extending between the first side portion and the second side portion. A seal member is disposed over the platform body. The seal member includes a first side portion over the platform body first side portion, a central portion over the platform body the central portion, and a second side portion over the platform body second side portion. An erosion protection layer is disposed over the seal member over the central portion of the platform body.
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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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公开(公告)号：US20190085856A1
公开(公告)日：2019-03-21
申请号：US15707165
申请日：2017-09-18
Applicant: United Technologies Corporation
Inventor： Colin J. Kling , Darin S. Lussier
IPC: F04D29/02 , F01D21/04 , F04D29/52 , F02C3/04 , B32B15/092
Abstract: A hybrid composite-metallic containment system may comprise a first composite layer, a first metallic layer, a second composite layer and a resin. The hybrid composite-metallic containment system may further comprise a second metallic layer. The first composite layer may be proximate the first metallic layer and the second composite layer may be proximate the second metallic layer. The first metallic layer may comprise a perforation.
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公开(公告)号：US10107202B2
公开(公告)日：2018-10-23
申请号：US14933743
申请日：2015-11-05
Applicant: United Technologies Corporation
Inventor： Darin S. Lussier
Abstract: A fan housing assembly of a turbofan engine and method of manufacture includes a fan housing that defines a flowpath radially inward, and a groove structure attached to and located aft of the housing for connection to a stationary portion of an outer shell of a thrust reverser. The groove structure includes a base portion concentrically located about an engine axis, and aft and leading legs spaced axially apart from one another and projecting radially outward from the base portion. The fan housing, the base portion, and the aft and leading legs are made of a one-piece composite material.
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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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Patent Agency Ranking
公开(公告)号：US20160281738A1
公开(公告)日：2016-09-29
申请号：US15075245
申请日：2016-03-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Peter Finnigan , Sreenivasa R. Voleti , Larry Foster , Darin S. Lussier , Gulperi Aksel
CPC classification number: F04D29/526 , B29C70/24 , F01D21/045 , F05D2220/32 , F05D2300/224 , F05D2300/6012 , F05D2300/6031 , F05D2300/6034 , F05D2300/614 , Y02T50/672
Abstract: A fan containment case for a gas turbine engine includes a first inner layer and a second layer outside the first inner layer, where the second layer is made of a first material having a first fabric architecture. The fan containment case also includes a third layer outside of the second layer, where the third layer is made of a second material having a second fabric architecture, and at least one of the first material and the first fabric architecture of the second layer is different from the second material and the second architecture, respectively, of the third layer. A fourth outer layer is located outside of the third layer.
Abstract translation: 用于燃气涡轮发动机的风扇容纳箱包括第一内层和第一内层外的第二层，其中第二层由具有第一织物结构的第一材料制成。 风扇容纳壳体还包括在第二层外侧的第三层，其中第三层由具有第二织物结构的第二材料制成，并且第二层的第一材料和第一织物结构中的至少一个是不同的 分别来自第三层的第二材料和第二结构。 第四外层位于第三层的外侧。
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公开(公告)号：US11156126B2
公开(公告)日：2021-10-26
申请号：US16369376
申请日：2019-03-29
Applicant: United Technologies Corporation
Inventor： Colin J. Kling , Darin S. Lussier
Abstract: A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture.
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公开(公告)号：US20200025034A1
公开(公告)日：2020-01-23
申请号：US16369376
申请日：2019-03-29
Applicant: United Technologies Corporation
Inventor： Colin J. Kling , Darin S. Lussier
Abstract: A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture.
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公开(公告)号：US10260374B2
公开(公告)日：2019-04-16
申请号：US14875627
申请日：2015-10-05
Applicant: United Technologies Corporation
Inventor： Larry Foster , Darin S. Lussier
IPC: F01D25/24 , B32B5/08 , B32B1/08 , D04C1/00 , F04D29/40 , F04D29/02 , F04D29/52 , B32B5/26 , B65H81/02 , F01D21/04 , F02K1/78 , F02C7/04 , B29C70/22
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.
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公开(公告)号：US20180100408A1
公开(公告)日：2018-04-12
申请号：US15836254
申请日：2017-12-08
Applicant: United Technologies Corporation
CPC classification number: F01D21/045 , B29C70/202 , B29C70/226 , B29C70/228 , B29C70/32 , B29D99/006 , B29L2031/7504 , F02C7/04 , F05D2300/6012 , F05D2300/603
Abstract: A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.
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