-
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.
-
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.
-
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。
-
公开(公告)号：US10724397B2
公开(公告)日：2020-07-28
申请号：US15836254
申请日：2017-12-08
Applicant: United Technologies Corporation
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.
-
公开(公告)号：US09822665B2
公开(公告)日：2017-11-21
申请号：US14560334
申请日：2014-12-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas J. Robertson, Jr. , Steven Clarkson
CPC classification number: F01D25/24 , F01D21/045 , F01D25/32 , F05D2260/602 , Y02T50/671
Abstract: A core for a fan containment includes an intermediate core segment and a plenum for fluid passage defined through the intermediate core segment. The intermediate core segment has an axial inlet side, an axial outlet side opposed to the axial inlet side, a radially inner side, and a radially outer side opposed to the radially inner side. The radially outer side is configured to be operatively connected to a cylindrical outer case and the radially inner side is configured to be operatively connected to at least one arcuate panel to form a liner assembly. The plenum extends through the intermediate core segment proximate the radially outer side for fluid passage between the axial inlet side and the axial outlet side.
-
Patent Agency Ranking
公开(公告)号：US20160032776A1
公开(公告)日：2016-02-04
申请号：US14776268
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sreenivasa R. Voleti , Thomas J. Robertson, Jr. , Darin S. Lussier
CPC classification number: F01D25/24 , B32B27/38 , B32B2260/021 , B32B2260/046 , F01D21/045 , F01D25/28 , F02C7/32 , F05D2220/32 , F05D2220/36 , F05D2300/43 , F05D2300/501 , F05D2300/603 , F05D2300/614 , Y02T50/672
Abstract: A composite assembly comprises a first composite wall, a second composite wall spaced radially inward from the first outer wall, and a composite reinforcement ring attached to an outer surface of the second composite wall. The composite reinforcement ring includes at least one sidewall having an accessory mounting port formed therethrough.
Abstract translation: 复合组件包括第一复合壁，与第一外壁径向向内隔开的第二复合壁，以及附接到第二复合壁的外表面的复合增强环。 复合加强环包括至少一个侧壁，其具有穿过其形成的附件安装端口。
-
公开(公告)号：US09651059B2
公开(公告)日：2017-05-16
申请号：US13728200
申请日：2012-12-27
Applicant: United Technologies Corporation
Inventor： Thomas J. Robertson, Jr. , Darin S. Lussier , Kirk D. Stackhouse , Johan Santana
CPC classification number: F04D29/526 , F01D11/122 , F01D11/127 , F04D29/023 , F05D2220/36 , F05D2230/23 , F05D2250/283 , F05D2300/431 , F05D2300/501 , F05D2300/50212 , Y02T50/672
Abstract: A section of a gas turbine engine includes a case structure and a liner. The liner is attached to the case structure by a compliant adhesive. The adhesive covers at least a portion of the liner surface area, and can have interruptions used to tune the compliance of the adhesive layer.
-
公开(公告)号：US11248538B2
公开(公告)日：2022-02-15
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
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.
-
公开(公告)号：US11073027B2
公开(公告)日：2021-07-27
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
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：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
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.
-
-
-
-
-
-
-
-
-
Search Results
14
records
(took 0.025 seconds)
