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Patent Agency Ranking
公开(公告)号：US10113444B2
公开(公告)日：2018-10-30
申请号：US14708819
申请日：2015-05-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jianming Huang , Brian C. Lund , Zhen Wu
Abstract: A heated inlet guide vane is disclosed. The disclosed guide vane may include a body having an inlet cavity disposed alongside of an outlet cavity wherein the outlet cavity is disposed alongside the leading edge of the vane. The inlet cavity is in communication with a source of heated air. The inlet cavity is in communication with the outlet cavity by way of a plurality of impingement holes spaced along the inner wall disposed between the two cavities. Bleed holes are spaced along the length of the outlet cavity. Fresh, heated air enters the outlet cavity along the entire length of the outlet cavity and quickly exits the outlet cavity with minimal cooling so that a uniform d-icing capability is provided along the entire leading edge of the inlet guide vane.
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公开(公告)号：US09920691B2
公开(公告)日：2018-03-20
申请号：US14611316
申请日：2015-02-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael Thomas Tall, Jr. , Brian C. Lund , Jianming Huang
CPC classification number: F02C7/047 , F01D17/162 , F01D25/02 , F04D29/563 , F05D2240/121 , F05D2250/611
Abstract: A manifold for a gas turbine engine includes oppositely facing first and second walls that extend from an annular wall. An undulating wall oppositely faces the annular wall and couples the first wall to the second wall. The walls collectively form a plurality of first chambers in fluid communication with a plurality of second chambers so that each of the second chambers intersperse adjacent first chambers. Each first chamber has a first volume that is greater that a second volume of each second chamber.
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公开(公告)号：US20150345327A1
公开(公告)日：2015-12-03
申请号：US14708819
申请日：2015-05-11
Applicant: United Technologies Corporation
Inventor： Jianming Huang , Brian C. Lund , Zhen Wu
CPC classification number: F01D25/12 , F01D5/021 , F01D9/02 , F01D9/065 , F01D25/02 , F01D25/24 , F02C7/047 , F05D2220/32 , F05D2260/201 , Y02T50/676
Abstract: A heated inlet guide vane is disclosed. The disclosed guide vane may include a body having an inlet cavity disposed alongside of an outlet cavity wherein the outlet cavity is disposed alongside the leading edge of the vane. The inlet cavity is in communication with a source of heated air. The inlet cavity is in communication with the outlet cavity by way of a plurality of impingement holes spaced along the inner wall disposed between the two cavities. Bleed holes are spaced along the length of the outlet cavity. Fresh, heated air enters the outlet cavity along the entire length of the outlet cavity and quickly exits the outlet cavity with minimal cooling so that a uniform d-icing capability is provided along the entire leading edge of the inlet guide vane.
Abstract translation: 公开了一种加热入口引导叶片。 所公开的引导叶片可以包括具有设置在出口腔旁边的入口腔体的主体，其中出口空腔沿着叶片的前缘设置。 入口腔与加热空气源连通。 入口腔通过沿着设置在两个空腔之间的内壁间隔开的多个冲击孔与出口腔连通。 排出的孔沿着出口腔的长度间隔开。 新鲜的加热空气沿出口腔的整个长度进入出口腔，并以最小的冷却快速离开出口腔，从而沿入口导流叶片的整个前缘提供均匀的除冰能力。
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公开(公告)号：US20150330305A1
公开(公告)日：2015-11-19
申请号：US14611316
申请日：2015-02-02
Applicant: United Technologies Corporation
Inventor： Michael Thomas Tall, JR. , Brian C. Lund , Jianming Huang
IPC: F02C7/047
CPC classification number: F02C7/047 , F01D17/162 , F01D25/02 , F04D29/563 , F05D2240/121 , F05D2250/611
Abstract: A manifold for a gas turbine engine includes oppositely facing first and second walls that extend from an annular wall. An undulating wall oppositely faces the annular wall and couples the first wall to the second wall. The walls collectively form a plurality of first chambers in fluid communication with a plurality of second chambers so that each of the second chambers intersperse adjacent first chambers. Each first chamber has a first volume that is greater that a second volume of each second chamber.
Abstract translation: 用于燃气涡轮发动机的歧管包括从环形壁延伸的相对面对的第一和第二壁。 波浪壁相对地面向环形壁并将第一壁耦合到第二壁。 所述壁共同形成与多个第二室流体连通的多个第一室，使得每个第二室分散相邻的第一室。 每个第一腔室具有比第二腔室的第二容积更大的第一容积。
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公开(公告)号：US20140090397A1
公开(公告)日：2014-04-03
申请号：US13630561
申请日：2012-09-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brian C. Lund , Thomas W. Stowe , Christopher St. Mary
CPC classification number: F02C6/08 , F04D29/053 , F04D29/321 , F04D29/584 , Y10T29/49236
Abstract: An anti-vortex assembly for a gas turbine engine includes a support ring including a seat surrounding an opening and a bleed tube including a base with a bearing face sealing against the seat. A retaining ring is mounted within the support ring and engages the base of the bleed air tube to hold the bleed tube within the support ring.
Abstract translation: 用于燃气涡轮发动机的防涡流组件包括支撑环，该支撑环包括围绕开口的座和包括具有密封抵靠座的轴承面的底座的排放管的支撑环。 保持环安装在支撑环内并与放气管的底部接合以将放气管保持在支撑环内。
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