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Patent Agency Ranking
公开(公告)号：US20170356344A1
公开(公告)日：2017-12-14
申请号：US15687598
申请日：2017-08-28
Applicant: General Electric Company
Inventor： Sarah Lori Crothers , Matthew Durham Collier , Scott Edward Sherman , Joseph Vincent Citeno
CPC classification number: F02C7/24 , F01D25/04 , F01D25/06 , F02C9/18 , F05D2260/96 , F05D2270/083 , F05D2270/10 , F05D2270/14 , F23R2900/00013
Abstract: Systems and methods for frequency separation in a gas turbine engine are provided herein. The systems and methods for frequency separation in a gas turbine engine may include determining a hot gas path natural frequency, determining a combustion dynamic frequency, and modifying a compressor discharge temperature to separate the combustion dynamic frequency from the hot gas path natural frequency. Specifically, the compressor discharge temperature may be modified by adjusting the inlet guide vanes of the compressor or by adjusting a temperature of air entering the compressor.
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公开(公告)号：US20150110629A1
公开(公告)日：2015-04-23
申请号：US14061221
申请日：2013-10-23
Applicant: General Electric Company
Inventor： Lee Larned Brozyna , Matthew Durham Collier , Christopher William Kester , Alexander Stein
CPC classification number: F01D5/141 , F01D5/143 , F05D2250/74 , Y02E20/16 , Y02T50/673
Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.
Abstract translation: 本发明的各种实施例包括涡轮机桶和采用这种铲斗的系统。 各种具体实施例包括涡轮机桶，其具有：具有吸力侧的翼型件; 与吸力侧相对的压力侧; 位于压力侧和吸力侧之间的前缘; 以及与前缘相对并跨越压力侧和吸力侧的后缘; 以及与所述翼型件的所述翼型件的第一端沿着所述吸入侧，压力侧，后缘和所述前缘连接的底座，所述底座包括靠近所述基座和所述翼型之间的连接处的非轴对称轮廓。
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公开(公告)号：US09745896B2
公开(公告)日：2017-08-29
申请号：US13777724
申请日：2013-02-26
Applicant: General Electric Company
Inventor： Sarah Lori Crothers , Matthew Durham Collier , Scott Edward Sherman , Joseph Vincent Citeno
CPC classification number: F02C7/24 , F01D25/04 , F01D25/06 , F02C9/18 , F05D2260/96 , F05D2270/083 , F05D2270/10 , F05D2270/14 , F23R2900/00013
Abstract: Systems and methods for frequency separation in a gas turbine engine are provided herein. The systems and methods for frequency separation in a gas turbine engine may include determining a hot gas path natural frequency, determining a combustion dynamic frequency, and modifying a compressor discharge temperature to separate the combustion dynamic frequency from the hot gas path natural frequency.
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公开(公告)号：US09638041B2
公开(公告)日：2017-05-02
申请号：US14061221
申请日：2013-10-23
Applicant: General Electric Company
Inventor： Lee Larned Brozyna , Matthew Durham Collier , Christopher William Kester , Alexander Stein
CPC classification number: F01D5/141 , F01D5/143 , F05D2250/74 , Y02E20/16 , Y02T50/673
Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.
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公开(公告)号：US20140238033A1
公开(公告)日：2014-08-28
申请号：US13777724
申请日：2013-02-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sarah Lori Crothers , Matthew Durham Collier , Scott Edward Sherman , Joseph Vincent Citeno
CPC classification number: F02C7/24 , F01D25/04 , F01D25/06 , F02C9/18 , F05D2260/96 , F05D2270/083 , F05D2270/10 , F05D2270/14 , F23R2900/00013
Abstract: Systems and methods for frequency separation in a gas turbine engine are provided herein. The systems and methods for frequency separation in a gas turbine engine may include determining a hot gas path natural frequency, determining a combustion dynamic frequency, and modifying a compressor discharge temperature to separate the combustion dynamic frequency from the hot gas path natural frequency.
Abstract translation: 本文提供了一种用于燃气涡轮发动机中的频率分离的系统和方法。 燃气涡轮发动机中用于频率分离的系统和方法可以包括确定热气体路径固有频率，确定燃烧动态频率，以及修改压缩机排放温度，以将燃烧动态频率与热气体路径固有频率分离。
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