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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：US11199098B2
公开(公告)日：2021-12-14
申请号：US16669756
申请日：2019-10-31
Applicant: General Electric Company
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
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公开(公告)号：US10605096B2
公开(公告)日：2020-03-31
申请号：US15152690
申请日：2016-05-12
Applicant: General Electric Company
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
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公开(公告)号：US10240465B2
公开(公告)日：2019-03-26
申请号：US15334454
申请日：2016-10-26
Applicant: General Electric Company
Inventor： David Wayne Weber , Robert Peter Hanet , Gregory Thomas Foster , Brendon James Leary
Abstract: A trailing edge cooling system for a multi-wall blade, including: a set of outward legs extending toward a trailing edge of the multi-wall blade and fluidly coupled to a coolant feed; a set of return legs extending away from the trailing edge of the multi-wall blade and fluidly coupled to a coolant collection passage; and a connecting system for fluidly coupling the set of outward legs and the set of return legs; wherein the set of outward legs is radially offset from the set of return legs along a radial axis of the multi-wall blade.
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公开(公告)号：US20180363470A1
公开(公告)日：2018-12-20
申请号：US15624252
申请日：2017-06-15
Applicant: General Electric Company
Inventor： Zachary John Snider , Daniel Burnos , Lana Maria Osusky , Brian Gene Brzek , Gregory Thomas Foster
IPC: F01D5/18
Abstract: A turbine airfoil includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a cooling air supply cavity disposed within the turbine airfoil, and a near wall cooling cavity disposed within the turbine airfoil and fluidly coupled to the cooling air supply cavity to receive cooling air. In addition, the near wall cooling cavity partially extends along the suction side wall from adjacent the leading edge to a location more proximal the trailing edge. Moreover, the near wall cooling cavity provides near wall cooling to a high heat load region along the suction side wall.
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Patent Agency Ranking
公开(公告)号：US10119406B2
公开(公告)日：2018-11-06
申请号：US15152698
申请日：2016-05-12
Applicant: General Electric Company
Inventor： Brendon James Leary , Elisabeth Kraus Black , Gregory Thomas Foster , Michelle Jessica Iduate , Jacob Charles Perry, II
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and forming a radially extending coolant receiving chamber. A rib partitions the radially extending chamber into a first passage on a first side of the rib and an adjacent second passage on an opposing second side of the rib. Each passage is enclosed at an end of the radially extending chamber by an end member of the radially extending chamber. A turn opening is defined in an end of the rib through which the coolant passes between the first passage and the second passage within the end member of the radially extending chamber. A bulbous projection extends along the end of the rib and on opposing radially extending sides of the turn opening to reduce stress in the rib and/or connecting fillets.
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公开(公告)号：US10060269B2
公开(公告)日：2018-08-28
申请号：US14977270
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster
CPC classification number: F01D5/187 , F01D5/186 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/202 , F05D2260/204 , Y02T50/676
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：US09879547B2
公开(公告)日：2018-01-30
申请号：US14143472
申请日：2013-12-30
Applicant: General Electric Company
Inventor： Brian Denver Potter , Gregory Thomas Foster
CPC classification number: F01D5/187 , F01D5/188 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/22141 , Y02T50/676
Abstract: A turbine blade that includes an airfoil and a radially extending chamber therein for a coolant. The turbine blade may also include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include: a camber line rib that defines a near-wall flow chamber; and traverse ribs extending between the camber line rib and one of the outer walls so to divide the near-wall flow chamber into successively stacked flow passages that each include a segment of the camber line rib. The segment of the camber line rib of one of the flow passages may have a narrowing profile that includes a profile that narrows from opposing ends toward a neck disposed therebetween.
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公开(公告)号：US20170175580A1
公开(公告)日：2017-06-22
申请号：US14971383
申请日：2015-12-16
Applicant: General Electric Company
Inventor： Marc Lionel Benjamin , Benjamin Paul Lacy , Gregory Thomas Foster , San Jason Nguyen
CPC classification number: F01D25/14 , F01D9/04 , F01D11/08 , F01D25/24 , F01D25/246 , F02C3/04 , F02C7/12 , F02C7/18 , F04D29/522 , F04D29/584 , F05D2220/32 , F05D2240/11 , F05D2240/35 , F05D2250/75 , F05D2260/202 , F05D2260/204 , Y02T50/676
Abstract: A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes a first channel disposed within the body having a first end portion and a second end portion and a second channel disposed within the body having a third end portion and a fourth end portion. The first and second channels are configured to receive the cooling fluid from the cavity to cool the body. The first end portion and the fourth end portion each include a hook-shaped portion having a free end.
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公开(公告)号：US20170175549A1
公开(公告)日：2017-06-22
申请号：US14978224
申请日：2015-12-22
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , F01D9/041 , F05D2220/32 , F05D2240/304 , F05D2260/20 , F05D2260/2212 , Y02T50/676
Abstract: One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; and a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section.
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