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公开(公告)号：US20230374935A1
公开(公告)日：2023-11-23
申请号：US17747497
申请日：2022-05-18
CPC分类号： F02C3/067 , F02C6/00 , F02C7/36 , F05D2220/76
摘要： A turbine section for a gas turbine engine defines a radial direction and includes a low-pressure (LP) turbine that includes a first plurality of LP turbine blades that includes a first stage having first stage LP turbine blades that rotate in a first direction at a first speed, a second plurality of LP turbine blades that includes a plurality of stages of LP turbine blades disposed downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed, a first LP turbine spool connected to the first plurality of LP turbine blades on an inner side of the first plurality of LP turbine blades in the radial direction, and a second LP turbine spool connected to the second plurality of LP turbine blades on an inner side of the second plurality of LP turbine blades in the radial direction
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公开(公告)号：US12071889B2
公开(公告)日：2024-08-27
申请号：US17713649
申请日：2022-04-05
发明人： Paul Hadley Vitt , Lyle Douglas Dailey , Matteo Renato Usseglio , Andreas Peters , Jonathan Ong
CPC分类号： F02C3/067 , F02C7/141 , F02C7/36 , F05D2220/60 , F05D2260/213 , F05D2260/40311
摘要： A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.
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公开(公告)号：US20230340906A1
公开(公告)日：2023-10-26
申请号：US17713649
申请日：2022-04-05
发明人： Paul Hadley Vitt , Lyle Douglas Dailey , Matteo Renato Usseglio , Andreas Peters , Jonathan Ong
CPC分类号： F02C3/067 , F02C7/141 , F02C7/36 , F05D2220/60 , F05D2260/213 , F05D2260/40311
摘要： A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.
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公开(公告)号：US20180306041A1
公开(公告)日：2018-10-25
申请号：US15496685
申请日：2017-04-25
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F05D2220/32 , F05D2240/12 , F05D2240/14 , F05D2240/20
摘要： A turbine vane frame apparatus includes: an annular inner band disposed about a centerline axis and defining an inner flowpath surface; an annular outer band surrounding the inner band and defining an outer flowpath surface; and an array of axial-flow airfoil-shaped vanes disposed between the inner and outer flowpath surfaces, wherein the vanes have at least three different chord dimensions.
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公开(公告)号：US20210310376A1
公开(公告)日：2021-10-07
申请号：US16838345
申请日：2020-04-02
摘要： Aspects of the disclosure generally relate to a turbine center frame for a turbine engine through which a flow path extends. The turbine center frame can include an inner wall radially spaced from an outer wall, with the inner and outer walls extending between an inlet and an outlet, and with the outlet downstream of the inlet with respect to the flow path. A set of circumferentially-spaced airfoils can extend between the inner wall and the outer wall.
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公开(公告)号：US11242770B2
公开(公告)日：2022-02-08
申请号：US16838345
申请日：2020-04-02
摘要： Aspects of the disclosure generally relate to a turbine center frame for a turbine engine through which a flow path extends. The turbine center frame can include an inner wall radially spaced from an outer wall, with the inner and outer walls extending between an inlet and an outlet, and with the outlet downstream of the inlet with respect to the flow path. A set of circumferentially-spaced airfoils can extend between the inner wall and the outer wall.
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