-
公开(公告)号：US09988916B2
公开(公告)日：2018-06-05
申请号：US14801412
申请日：2015-07-16
Applicant: General Electric Company
CPC classification number: F01D9/041 , F01D5/187 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2240/122 , F05D2240/128 , F05D2240/81 , F05D2260/2214
Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade, including: an endwall coupled to a radial end of an airfoil; a chamber positioned within the endwall and radially displaced from a radially outer end of the trailing edge of the airfoil, wherein the chamber includes a pair of opposing chamber walls, one of the pair of opposing chamber walls being positioned proximal to the pressure side surface of the airfoil and the other of the pair of opposing chamber walls being positioned proximal to the suction side surface and the trailing edge of the airfoil, and wherein the cooling fluid in the chamber is in thermal communication with least a portion of the endwall positioned proximal to the pressure side surface and the trailing edge of the airfoil; and a plurality of thermally conductive fixtures positioned within the chamber.
-
公开(公告)号：US10221710B2
公开(公告)日：2019-03-05
申请号：US15019502
申请日：2016-02-09
Applicant: General Electric Company
IPC: F01D9/04
Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle 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 at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.
-
Patent Agency Ranking
3.发明申请公开(公告)号：US20170037731A1
公开(公告)日：2017-02-09
申请号：US14818695
申请日：2015-08-05
Applicant: General Electric Company
Inventor： Victor John Morgan , George Andrew Gergely , Frederic Woodrow Roberts, JR. , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , B23P15/02 , F01D9/065 , F05D2240/81 , F05D2250/314 , F05D2250/75 , F05D2260/2212 , F05D2260/2214
Abstract: Embodiments of the present disclosure provide components for hot gas path (HGP) components and methods of forming the same. A structure according to the present disclosure can include: an HGP component extending radially from a rotor axis of a turbomachine, the HGP component including a tapered edge; a plurality of first passages in fluid communication with a preliminary cooling zone of the HGP component, and extending through a sidewall positioned between the preliminary cooling zone and the tapered edge; and a plurality of second passages extending through at least the tapered edge, wherein each of the plurality of second passages is in fluid communication with the flow path for the operative fluid and at least one passage of the plurality of first passages, and wherein at least one of the plurality of second passages is radially displaced from each passage of the plurality of first passages.
Abstract translation: 本公开的实施例提供了用于热气路径（HGP）部件的部件及其形成方法。 根据本公开的结构可以包括：HGP部件，其从涡轮机的转子轴线径向延伸，所述HGP部件包括锥形边缘; 多个第一通道，其与HGP部件的预冷却区域流体连通，并且延伸穿过位于预冷却区域和锥形边缘之间的侧壁; 以及多个第二通道，其至少延伸穿过所述锥形边缘，其中所述多个第二通道中的每一个与所述操作流体的流动路径和所述多个第一通道的至少一个通道流体连通，并且其中至少 多个第二通道中的一个从多个第一通道的每个通道径向移位。
-
公开(公告)号：US10012091B2
公开(公告)日：2018-07-03
申请号：US14818695
申请日：2015-08-05
Applicant: General Electric Company
Inventor： Victor John Morgan , George Andrew Gergely , Frederic Woodrow Roberts, Jr. , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , B23P15/02 , F01D9/065 , F05D2240/81 , F05D2250/314 , F05D2250/75 , F05D2260/2212 , F05D2260/2214
Abstract: Embodiments of the present disclosure provide components for hot gas path (HGP) components and methods of forming the same. A structure according to the present disclosure can include: an HGP component extending radially from a rotor axis of a turbomachine, the HGP component including a tapered edge; a plurality of first passages in fluid communication with a preliminary cooling zone of the HGP component, and extending through a sidewall positioned between the preliminary cooling zone and the tapered edge; and a plurality of second passages extending through at least the tapered edge, wherein each of the plurality of second passages is in fluid communication with the flow path for the operative fluid and at least one passage of the plurality of first passages, and wherein at least one of the plurality of second passages is radially displaced from each passage of the plurality of first passages.
-
公开(公告)号：US20170016339A1
公开(公告)日：2017-01-19
申请号：US14801412
申请日：2015-07-16
Applicant: General Electric Company
CPC classification number: F01D9/041 , F01D5/187 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2240/122 , F05D2240/128 , F05D2240/81 , F05D2260/2214
Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade, including: an endwall coupled to a radial end of an airfoil; a chamber positioned within the endwall and radially displaced from a radially outer end of the trailing edge of the airfoil, wherein the chamber includes a pair of opposing chamber walls, one of the pair of opposing chamber walls being positioned proximal to the pressure side surface of the airfoil and the other of the pair of opposing chamber walls being positioned proximal to the suction side surface and the trailing edge of the airfoil, and wherein the cooling fluid in the chamber is in thermal communication with least a portion of the endwall positioned proximal to the pressure side surface and the trailing edge of the airfoil; and a plurality of thermally conductive fixtures positioned within the chamber.
Abstract translation: 本公开的实施例提供了一种用于固定叶片的冷却结构，包括：连接到翼型件的径向端的端壁; 定位在端壁内并且从翼型的后缘的径向外端径向偏移的腔室，其中腔室包括一对相对的腔室壁，一对相对的腔室壁中的一个位于靠近压力侧面的 所述翼型件和所述一对相对的室壁中的另一个位于所述翼型件的吸入侧表面和所述后缘附近，并且其中所述腔室中的冷却流体与所述端壁的至少一部分位于 翼面的压力侧表面和后缘; 以及多个位于腔室内的导热固定件。
-
公开(公告)号：US10583489B2
公开(公告)日：2020-03-10
申请号：US15497825
申请日：2017-04-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Victor John Morgan , George Andrew Gergely
IPC: B22F5/04 , B33Y10/00 , B33Y80/00 , B22F3/105 , B22F3/24 , B23K15/00 , B23K26/342 , B23K26/70 , B22F5/00 , C23C26/00 , C22C19/07 , C22C19/05 , C22C30/02 , B22D21/00 , B22D25/02 , F01D25/12 , B23P15/04 , F01D5/18 , F01D9/02 , B23K101/00
Abstract: A method of providing cooling structure for a component including forming a first cavity in the component and forming a first passageway in the first cavity in fluid communication with a second cavity positioned inside the component, the second cavity in fluid communication with a cooling air source. The method includes forming a unitary insert including a first surface, a second surface, the insert having an inlet formed in the first surface and an outlet formed in the second surface. A second passageway is in fluid communication with the inlet and the outlet. The method includes positioning the insert in the first cavity into fluid communication with the first passageway, the first surface facing the first cavity; and rigidly attaching the insert in the first cavity.
-
公开(公告)号：US20170226880A1
公开(公告)日：2017-08-10
申请号：US15019502
申请日：2016-02-09
Applicant: General Electric Company
IPC: F01D9/04
CPC classification number: F01D9/041 , F01D5/143 , F05D2220/31 , F05D2220/32 , F05D2240/128 , F05D2240/80 , F05D2250/73 , F05D2250/74 , Y02T50/673
Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle 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 at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.
-
-
-
-
-
-
Search Results
7
records
(took 0.014 seconds)
