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公开(公告)号：US20160319685A1
公开(公告)日：2016-11-03
申请号：US14697765
申请日：2015-04-28
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Victor John Morgan , Jacob John Kittleson , Neelesh N. Sarawate
CPC classification number: F01D11/005 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2240/55 , F05D2260/20 , F16J15/064
Abstract: The present application provide a seal for use between components engine facing a high pressure cooling air flow and a hot gas path in a gas turbine. The seal may include a first shim, a second shim with an air exit hole, one or more middle layers positioned between the first shim and the second shim, and one or more cooling pathways extending through the middle layers for the high pressure cooling air flow to pass therethrough and exit via the air exit hole into the hot gas path.
Abstract translation: 本申请提供了在面向高压冷却空气流的部件发动机和燃气涡轮机中的热气体路径之间使用的密封件。 密封件可以包括第一垫片，具有空气出口孔的第二垫片，位于第一垫片和第二垫片之间的一个或多个中间层，以及延伸穿过用于高压冷却空气流的中间层的一个或多个冷却路径 通过空气出口孔流入热气路径。
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公开(公告)号：US20230235680A1
公开(公告)日：2023-07-27
申请号：US17649030
申请日：2022-01-26
Applicant: General Electric Company
Inventor： Valeria Andreoli , Thomas W. Vandeputte , Neelesh N. Sarawate
CPC classification number: F01D11/20 , F01D7/00 , F01D25/005
Abstract: A rotor blade system includes a rotor, a casing radially spaced apart from the rotor, and a plurality of blades coupled to the rotor and positioned between the rotor and the casing. The one or more of the plurality of blades have a radial length different from a remaining one or more of the plurality of blades so as to vary a tip gap between a tip of the one or more of the plurality of blades and the casing to break up a frequency content of a leakage vortex at the tip to modify natural frequencies of the plurality of blades and mode shapes to reduce or substantially eliminate flutter.
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公开(公告)号：US09581037B2
公开(公告)日：2017-02-28
申请号：US14697765
申请日：2015-04-28
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Victor John Morgan , Jacob John Kittleson , Neelesh N. Sarawate
CPC classification number: F01D11/005 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2240/55 , F05D2260/20 , F16J15/064
Abstract: The present application provide a seal for use between components engine facing a high pressure cooling air flow and a hot gas path in a gas turbine. The seal may include a first shim, a second shim with an air exit hole, one or more middle layers positioned between the first shim and the second shim, and one or more cooling pathways extending through the middle layers for the high pressure cooling air flow to pass therethrough and exit via the air exit hole into the hot gas path.
Abstract translation: 本申请提供了在面向高压冷却空气流的部件发动机和燃气涡轮机中的热气体路径之间使用的密封件。 密封件可以包括第一垫片，具有空气出口孔的第二垫片，位于第一垫片和第二垫片之间的一个或多个中间层，以及延伸穿过用于高压冷却空气流的中间层的一个或多个冷却路径 从而通过空气出口孔流入热气路径。
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