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公开(公告)号：US11035243B2
公开(公告)日：2021-06-15
申请号：US15995328
申请日：2018-06-01
Applicant: United Technologies Corporation
Inventor： Thomas E. Clark , Kevin D. Tracy
Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a support mountable to an engine static structure. The support has a main body extending axially between leading and trailing edge portions and circumferentially between opposed mate faces, and the main body includes a pair of opposed retention hooks extending inwardly from the leading and trailing edge portions to bound an elongated groove extending circumferentially between the opposed mate faces. A seal has a sealing portion that extends from an engagement portion. The sealing portion has a sealing face that extends circumferentially between first and second mate faces. An overwrap has one or more plies that follow a perimeter of the engagement portion to define an interface between the retention hooks and the engagement portion. A method of sealing is also disclosed.
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公开(公告)号：US20170044931A1
公开(公告)日：2017-02-16
申请号：US14826498
申请日：2015-08-14
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Carson A. Roy Thill , Dominic J. Mongillo, JR. , Kevin D. Tracy , Jeffrey A. Perry , Thurman C. Dabbs
CPC classification number: F01D25/12 , F01D11/08 , F05D2220/32 , F05D2240/11 , F05D2240/24 , F05D2250/74 , F05D2260/20
Abstract: A gas turbine engine includes a turbine section including a plurality of blade outer air seals (BOAS) disposed therein, the BOAS including a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in at least one of Table 1 and Table 2.
Abstract translation: 燃气涡轮发动机包括涡轮部分，其包括设置在其中的多个叶片外部空气密封件（BOAS），所述BOAS包括BOAS主体，该BOAS主体包括基本上符合一组笛卡尔坐标定义的多个冷却孔，至少如 表1和表2之一。
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公开(公告)号：US20200024967A1
公开(公告)日：2020-01-23
申请号：US16052730
申请日：2018-08-02
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Kevin D. Tracy , Dominic J. Mongillo, JR.
Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body having a leading edge and a trailing edge extending in a radial direction, a cooling cavity defined within the airfoil body at the trailing edge, and a plurality of angled pedestals arranged along the trailing edge, wherein the plurality of angled pedestals define a plurality of angled trailing edge slots therebetween. Adjacent angled pedestals of the plurality of angled pedestals define a meter section of a respective angled trailing edge slot and a diffuser section of the respective angled trailing edge slot, wherein the meter section is defined by parallel sides of the adjacent angled pedestals, wherein the parallel sides of the adjacent angled pedestals are oriented at a bleed direction that is less than 90° with respect to a feed direction through the cooling cavity.
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公开(公告)号：US09869202B2
公开(公告)日：2018-01-16
申请号：US14826498
申请日：2015-08-14
Applicant: United Technologies Corporation
Inventor： Paul M. Lutjen , Carson A. Roy Thill , Dominic J. Mongillo, Jr. , Kevin D. Tracy , Jeffrey A. Perry , Thurman C. Dabbs
CPC classification number: F01D25/12 , F01D11/08 , F05D2220/32 , F05D2240/11 , F05D2240/24 , F05D2250/74 , F05D2260/20
Abstract: A gas turbine engine includes a turbine section including a plurality of blade outer air seals (BOAS) disposed therein, the BOAS including a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in at least one of Table 1 and Table 2.
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