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31.发明授权公开(公告)号：US09518478B2
公开(公告)日：2016-12-13
申请号：US14064867
申请日：2013-10-28
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , David Wayne Weber
CPC classification number: F01D25/12 , F01D9/04 , F01D11/003 , F01D11/005 , F01D11/008 , F05D2240/11 , F05D2240/57
Abstract: A gas turbine stator component includes a composite, segmented ring made up of an annular array of arcuate segments, each having end faces formed with respective seal slots, with radial gaps formed between opposed end faces of adjacent arcuate segments. A seal is located between each pair of opposed seal slots to thereby seal the gaps, and a channel is provided in each of said arcuate segments adapted to be supplied with cooling air, the channel connecting to a passage extending between the channel and a respective one of the seal slots or radial gaps, on a lower-pressure side of the seal.
Abstract translation: 燃气涡轮机定子部件包括由圆弧段的环形阵列组成的复合分段环，每个圆形段具有形成有相应密封槽的端面，在相邻弧形段的相对端面之间形成径向间隙。 密封件位于每对相对的密封槽之间，从而密封间隙，并且在每个所述弧形段中设置有适于被供应冷却空气的通道，所述通道连接到在通道和相应的密封槽之间延伸的通道 的密封槽或径向间隙，位于密封件的低压侧。
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32.发明授权公开(公告)号：US09518475B2
公开(公告)日：2016-12-13
申请号：US14064918
申请日：2013-10-28
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Aaron Ezekiel Smith
CPC classification number: F01D11/24 , F01D9/04 , F01D11/005 , F05D2240/11 , F05D2240/81 , F05D2260/205
Abstract: In one example, an arcuate segment for a ring-shaped, rotary machine component such as a stator nozzle or bucket shroud, includes a segment body having an end face formed with a circumferentially-facing seal slot adapted to receive a seal extending between the segment body and a corresponding seal slot in an adjacent segment body to seal a radially-extending gap between the adjacent segment bodies. A cooling channel is provided in the segment body in proximity to the seal slot, and is adapted to be supplied with cooling air. A passage extends from the cooling channel into the seal slot, at a location where the cooling air can be supplied to the higher pressure area on the radially-outer side of the seal.
Abstract translation: 在一个示例中，用于环形旋转机器部件（例如定子喷嘴或铲斗护罩）的弧形段包括段体，其具有形成有面向周向的密封槽的端面，其适于接收在段 主体和相邻的分段体中相应的密封槽，以密封相邻分段体之间的径向延伸的间隙。 冷却通道设置在分段主体中，靠近密封槽，并且适于供应冷却空气。 通道从冷却通道延伸到密封槽中，在冷却空气可被供应到密封件的径向外侧上的较高压力区域的位置处。
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公开(公告)号：US20150184537A1
公开(公告)日：2015-07-02
申请号：US14143490
申请日：2013-12-30
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith
IPC: F01D25/12
CPC classification number: F01D25/12 , F01D5/186 , F01D5/187 , Y02T50/676
Abstract: A turbine blade having an airfoil defined by outer walls in which a concave shaped pressure side outer wall and a convex shaped suction side outer wall connect along leading and trailing edges and form a chamber for receiving the flow of a coolant. The turbine blade may include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include a rib having a wavy profile that opposes a target surface across one of the flow passages. Relative to the target surface, the wavy profile of the rib may include a ridge portion and a furrow portion. The rib may include impingement apertures formed through the ridge portion.
Abstract translation: 具有由外壁限定的翼型的涡轮叶片，其中凹形压力侧外壁和凸形吸入侧外壁沿着前缘和后缘连接并形成用于接收冷却剂流动的室。 涡轮叶片可以包括将腔室分隔成径向延伸的流动通道的肋构型。 肋构造可以包括具有与横过其中一个流动通道的目标表面相对的波状轮廓的肋。 相对于目标表面，肋的波状轮廓可以包括脊部分和沟槽部分。 肋可以包括通过脊部形成的冲击孔。
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公开(公告)号：US20150013345A1
公开(公告)日：2015-01-15
申请号：US13939727
申请日：2013-07-11
Applicant: General Electric Company
Inventor： Christopher Donald Porter , Gregory Thomas Foster , Aaron Ezekiel Smith , David Wayne Weber , Michelle J. Rogers
IPC: F01D25/12
CPC classification number: F01D25/12 , F01D11/24 , F05D2240/11 , F05D2260/201 , F05D2260/202 , Y02T50/676
Abstract: A shroud segment for a casing of gas turbine includes a body configured for attachment to the casing proximate a localized critical process location within the casing. The body has a leading edge, a trailing edge, and two side edges. The critical process location is located between the leading edge and the trailing edge when the body is attached to the casing. A cooling passage is defined in the body along one of the side edges with one of an inlet or an outlet proximate the critical process location. The cooling passage is configured large enough to cool the one side edge adjacent the cooling passage to a desired level during operation of the gas turbine. The critical process locations may be related to temperatures, pressures or other measurable features of the gas turbine environment when in use.
Abstract translation: 用于燃气涡轮机壳体的护罩段包括构造成用于附接到壳体内的主体，该主体靠近壳体内的局部临界过程位置。 主体具有前缘，后缘和两个侧边。 当主体连接到壳体时，临界过程位置位于前缘和后缘之间。 冷却通道在主体中沿着一个侧边缘限定，其中一个入口或出口靠近临界过程位置。 冷却通道被构造成足够大以在燃气轮机的操作期间将邻近冷却通道的一侧边缘冷却到期望的水平。 关键过程位置可能与使用中的燃气轮机环境的温度，压力或其他可测量特征有关。
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公开(公告)号：US11655718B2
公开(公告)日：2023-05-23
申请号：US17316026
申请日：2021-05-10
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Nicholas William Rathay , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , F01D5/141 , F01D5/20 , F01D5/3007 , F05D2220/323 , F05D2240/307 , F05D2260/201 , F05D2260/202 , F05D2260/205
Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.
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Patent Agency Ranking
公开(公告)号：US11008889B2
公开(公告)日：2021-05-18
申请号：US16356491
申请日：2019-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jonathan Russell Ratzlaff , Aaron Ezekiel Smith
Abstract: A hanger for a turbine engine can include a first surface confronting a cooling airflow, a second surface facing a heated airflow, and a third surface radially outward of the first surface. The hanger can also include a cyclonic separator with a dirty air inlet and a clean air outlet, as well as a cooling air circuit extending through the cyclonic separator.
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公开(公告)号：US10781698B2
公开(公告)日：2020-09-22
申请号：US16046066
申请日：2018-07-26
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster
Abstract: A cooling system according to an embodiment includes: a leading edge cooling circuit including a pressure side serpentine circuit and a suction side serpentine circuit; a first mid-blade cooling circuit including a suction side serpentine circuit; a second mid-blade cooling circuit including a pressure side serpentine circuit; a trailing edge cooling circuit; and at least one air feed for supplying cooling air to the leading edge cooling circuit, the first mid-blade cooling circuit, the second mid-blade cooling circuit, and the trailing edge cooling circuit.
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公开(公告)号：US10605098B2
公开(公告)日：2020-03-31
申请号：US15648541
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Nicholas William Rathay , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.
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公开(公告)号：US10508548B2
公开(公告)日：2019-12-17
申请号：US15481628
申请日：2017-04-07
Applicant: General Electric Company
Inventor： James Michael Hoffman , Weston Nolan Dooley , Aaron Ezekiel Smith , Steven Robert Brassfield
Abstract: An airfoil assembly for a turbine engine can comprise a platform having first and second opposing surfaces, an airfoil extending from the first surface, a base extending from the second surface, and a platform cooling circuit including a feed tube, a first branch, a second branch, and a flow divider.
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公开(公告)号：US10364681B2
公开(公告)日：2019-07-30
申请号：US14884057
申请日：2015-10-15
Applicant: General Electric Company
Inventor： Matthew Lee Krumanaker , Robert Frederick Bergholz , Aaron Ezekiel Smith , Weston Nolan Dooley
IPC: F01D5/18
Abstract: An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.
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