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公开(公告)号：US10774685B2
公开(公告)日：2020-09-15
申请号：US15966760
申请日：2018-04-30
摘要： A heat shield for a gas turbine engine includes a radial heat shield flange that extends in a circumferential direction and forms a ring. A plurality of bosses extend from a first axial side of the radial heat shield flange. There is a plurality of guide pins. One of the plurality of guide pins extends from a corresponding one of the plurality of bosses.
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公开(公告)号：US11268402B2
公开(公告)日：2022-03-08
申请号：US15950549
申请日：2018-04-11
发明人： Adam Lee Hart , Brian Levy , Luis Miguel Ayalde , Jose R. Paulino , Patrick Scheelk , Nicolas Bueno
摘要： A blade outer air seal (BOAS) for a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion; and a multitude of cooling fins disposed around the radially outer face of the seal body, at least one of the multitude of cooling fins having at least one aperture.
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公开(公告)号：US20190331002A1
公开(公告)日：2019-10-31
申请号：US15966760
申请日：2018-04-30
摘要： A heat shield for a gas turbine engine includes a radial heat shield flange that extends in a circumferential direction and forms a ring. A plurality of bosses extend from a first axial side of the radial heat shield flange. There is a plurality of guide pins. One of the plurality of guide pins extends from a corresponding one of the plurality of bosses.
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公开(公告)号：US10746049B2
公开(公告)日：2020-08-18
申请号：US15941041
申请日：2018-03-30
发明人： Jonathan Jeffery Eastwood , Adam Lee Hart , Brian Levy , Luis Miguel Ayalde , Brian Craig , Jose R. Paulino , Esref Yaylagan
摘要： An example case for a gas turbine engine includes a bearing compartment, a radially outer ring, and a radially inner ring. The radially outer ring and radially inner ring are connected by a plurality of circumferentially spaced apart struts and define an annular flow path therebetween. The radially inner ring includes a first flange that extends radially outward from the bearing compartment. The first flange includes an undulation that extends axially away from the plurality of struts, and defines a load path between the bearing compartment and the radially outer ring.
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公开(公告)号：US20190316485A1
公开(公告)日：2019-10-17
申请号：US15950549
申请日：2018-04-11
发明人： Adam Lee Hart , Brian Levy , Luis Miguel Ayalde , Jose R. Paulino , Patrick Scheelk , Nicolas Bueno
摘要： A blade outer air seal (BOAS) for a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion; and a multitude of cooling fins disposed around the radially outer face of the seal body, at least one of the multitude of cooling fins having at least one aperture.
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公开(公告)号：US20190301302A1
公开(公告)日：2019-10-03
申请号：US15941041
申请日：2018-03-30
发明人： Jonathan Jeffery Eastwood , Adam Lee Hart , Brian Levy , Luis Miguel Ayalde , Brian Craig , Jose R. Paulino , Esref Yaylagan
摘要： An example case for a gas turbine engine includes a bearing compartment, a radially outer ring, and a radially inner ring. The radially outer ring and radially inner ring are connected by a plurality of circumferentially spaced apart struts and define an annular flow path therebetween. The radially inner ring includes a first flange that extends radially outward from the bearing compartment. The first flange includes an undulation that extends axially away from the plurality of struts, and defines a load path between the bearing compartment and the radially outer ring.
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