-
11.发明申请公开(公告)号：US20160032833A1
公开(公告)日：2016-02-04
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: F02C7/045
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.
Abstract translation: 用于燃气涡轮发动机的风扇壳体的盒包括与热适应衬套部分一体化的入口声学衬垫部分。
-
公开(公告)号：US20160010503A1
公开(公告)日：2016-01-14
申请号：US14613755
申请日：2015-02-04
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.
Abstract translation: 公开了一种通过燃气涡轮发动机的风扇壳体的壁安装安装孔的方法。 该方法可以包括：1）以垂直于壁的外表面的角度，通过风扇壳体的壁安装导向孔，2）将凸台穿过导向孔，3）将凸台粘合到 风扇壳体，以及4）相对于垂直于壁的外表面的角度以离轴角度安装安装孔。
-
公开(公告)号：US20150377070A1
公开(公告)日：2015-12-31
申请号：US14765486
申请日：2013-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas J. Robertson, JR. , Marc R. Sauerhoefer
CPC classification number: F01D25/28 , F01D25/24 , F02C7/32 , F05D2220/32 , F05D2230/60 , F05D2260/30 , F16B11/006 , F16L3/08
Abstract: A mount assembly is described. The mount assembly may comprise a base unit having a surface, an extension unit stacked on and connected to the surface, and a clamp unit stacked on and connected to the extension unit.
Abstract translation: 描述了安装组件。 安装组件可以包括具有表面的基座单元，堆叠在表面上并连接到表面的延伸单元，以及堆叠在延伸单元上并连接到延伸单元的夹紧单元。
-
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.
-
Patent Agency Ranking
公开(公告)号：US20160341068A1
公开(公告)日：2016-11-24
申请号：US14880519
申请日：2015-10-12
Applicant: United Technologies Corporation
Inventor： Thomas J. Robertson, JR. , Enzo DiBenedetto , Nathan F. Champion , Niloofar Haghbin , Barry William Spaulding, III
CPC classification number: F01D17/14 , F01D9/041 , F01D9/042 , F01D17/162 , F04D29/563 , F04D29/644 , F05D2220/32 , F05D2230/30 , F05D2230/60 , F05D2230/644 , F05D2240/80 , F05D2260/30
Abstract: A fixed-variable vane assembly includes a vane that has a fixed airfoil section and a variable airfoil section next to the fixed airfoil section. The variable airfoil section is pivotably mounted at an end thereof in a joint with a variable joint gap that controls a size of an airfoil gap between the fixed airfoil section and the variable airfoil section. A potting material is located in the variable joint gap. The potting material locks the variable joint gap and locks in the size of the airfoil gap.
Abstract translation: 固定式叶片组件包括具有固定翼型部分和与固定翼型部分相邻的可变翼型部分的叶片。 可变翼型部分在其端部可枢转地安装在具有可变接头间隙的接头中，该可变接缝间隙控制固定翼型部分和可变翼型部分之间的翼型间隙的尺寸。 灌封材料位于可变接缝间隙中。 灌封材料锁定可变接缝间隙并锁定翼型间隙的尺寸。
-
公开(公告)号：US20160258445A1
公开(公告)日：2016-09-08
申请号：US15032161
申请日：2014-05-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas J. Robertson, JR. , Steven Clarkson
CPC classification number: F04D29/522 , F01D25/02 , F02C7/047 , F02C7/05 , F04D29/023 , F05D2220/32 , F05D2300/434 , F05D2300/436 , F05D2300/603
Abstract: An ice liner assembly for a fan containment case for a turbofan gas turbine engine is disclosed. The disclosed ice liner assembly includes a plurality of arcuate panels arranged end to end to form a cylindrical liner that is disposed within the fan containment case and aft of the fan and abradable strip liner that circumscribes the fan. Because the plurality of arcuate panels are arranged end to end fashion, the ice liner assembly includes a plurality of splice joints, or a joint between two abutting ends of two arcuate panels. The splice joints are reinforced with molded polymeric splice support cores that are substantially lighter and less expensive than currently employed
Abstract translation: 公开了一种用于涡轮风扇燃气涡轮发动机的风扇容纳箱的冰套组件。 所公开的冰盖组件包括多个弧形面板，其端对端布置以形成圆柱形衬套，该圆柱形衬套设置在风扇容纳壳体内，风扇后部和可磨损的带状衬套限定风扇。 由于多个弧形面板以端对端的方式布置，所以冰套组件包括多个接合接头，或两个弧形面板的两个邻接端之间的接头。 接头接头用模制的聚合物接头支撑芯加强，其基本上比当前使用的更轻且更便宜
-
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
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：US20150159508A1
公开(公告)日：2015-06-11
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.
Abstract translation: 用于风扇容纳的芯部包括中间芯段和用于通过中间芯段确定的用于流体通道的增压室。 中间芯段具有轴向入口侧，与轴向入口侧相对的轴向出口侧，径向内侧和与径向内侧相对的径向外侧。 径向外侧构造成可操作地连接到圆柱形外壳，并且径向内侧构造成可操作地连接到至少一个弓形面板以形成衬套组件。 气室在靠近径向外侧延伸穿过中间芯段，用于在轴向入口侧和轴向出口侧之间流体通过。
-
公开(公告)号：US20140186165A1
公开(公告)日：2014-07-03
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
IPC: F04D29/52
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.
Abstract translation: 燃气涡轮发动机的一部分包括壳体结构和衬套。 衬里通过柔性粘合剂附接到壳体结构。 粘合剂覆盖衬垫表面积的至少一部分，并且可以具有用于调节粘合剂层的柔顺性的中断。
-
-
-
-
-
-
-
-
Search Results
19
records
(took 0.018 seconds)
