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公开(公告)号：US20120251295A1
公开(公告)日：2012-10-04
申请号：US13408251
申请日：2012-02-29
IPC分类号： F01D5/18
CPC分类号： F23R3/002 , F01D11/24 , F05D2240/11 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F23R2900/03041
摘要： A component of a gas turbine engine is provided. The component includes an external wall which, in use, is exposed on one surface thereof to working gas flowing through the engine. The component further includes effusion cooling holes formed in the external wall. In use, cooling air blows through the cooling holes to form a cooling film on the surface of the external wall exposed to the working gas. The component further includes an air inlet arrangement which receives the cooling air for distribution to the cooling holes. The component further includes a plurality of metering feeds and a plurality of supply plena. The metering feeds meter the cooling air from the air inlet arrangement to respective of the supply plena, which in turn supply the metered cooling air to respective portions of the cooling holes.
摘要翻译： 提供燃气涡轮发动机的部件。 该组件包括外壁，其在使用中在其一个表面上暴露于流过发动机的工作气体。 该部件还包括形成在外壁中的排出冷却孔。 在使用中，冷却空气吹过冷却孔，在暴露于工作气体的外壁的表面上形成冷却膜。 该部件还包括一个空气入口装置，其接收用于分配到冷却孔的冷却空气。 该组件还包括多个计量馈送和多个供应斑点。 计量供给将来自进气装置的冷却空气测量到供应凹槽的相应位置，该供应凹槽又将计量的冷却空气供应到冷却孔的相应部分。
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公开(公告)号：US08662825B2
公开(公告)日：2014-03-04
申请号：US12861560
申请日：2010-08-23
申请人： Peter T. Ireland , Howoong Namgoong
发明人： Peter T. Ireland , Howoong Namgoong
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2250/324 , F05D2270/17
摘要： An aerofoil blade or vane suitable for the turbine of a gas turbine engine includes an extending aerofoil portion having facing wall parts interconnected by a divider member to partially define first and second cooling fluid passage portions. The first and second passage portions are interconnected in a series fluid flow relationship by a bend passage portion. The first passage portion directs cooling fluid to the bend portion and the second passage portion exhausts cooling fluid from the bend portion. The divider member provides a localised contraction of the downstream end of the first passage portion to accelerate the cooling fluid flow before it enters the bend passage portion. The divider member provides a localised progressive series narrowing and opening of the upstream end of the second passage portion in the general direction of cooling fluid flow.
摘要翻译： 适合于燃气涡轮发动机的涡轮机的机翼叶片或叶片包括延伸的机翼部分，其具有通过分隔件互连的面对的壁部分，以部分地限定第一和第二冷却流体通道部分。 第一和第二通道部分由弯曲通道部分以串联流体流动关系相互连接。 第一通道部分将冷却流体引导到弯曲部分，第二通道部分从弯曲部分排出冷却流体。 分隔构件提供第一通道部分的下游端的局部收缩，以在其进入弯曲通道部分之前加速冷却流体流动。 分隔构件提供沿着冷却流体流动的大致方向的第二通道部分的上游端的局部渐进式系列变窄和打开。
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公开(公告)号：US20110058958A1
公开(公告)日：2011-03-10
申请号：US12861560
申请日：2010-08-23
申请人： Peter T. IRELAND , Howoong NAMGOONG
发明人： Peter T. IRELAND , Howoong NAMGOONG
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2250/185 , F05D2250/324 , F05D2270/17
摘要： An aerofoil blade or vane (1) suitable for the turbine of a gas turbine engine includes a longitudinally extending aerofoil portion (7) having facing wall parts (20, 22). The wall parts being interconnected by a generally longitudinally extending divider member (17) to partially define first and second cooling fluid passage portions (11, 15) disposed in side-by-side generally longitudinally extending relationship. The first and second passage portions being interconnected in series fluid flow relationship by a bend passage portion (13). The first passage portion is adapted to direct cooling fluid to the bend portion and the second passage portion being adapted to exhaust cooling fluid from the bend portion. The divider member has a first local thickening (33) in the region of the bend portion to provide a localised contraction of the downstream end of the first passage portion to accelerate the cooling fluid flow before it enters the bend passage portion. The divider member has a second local thickening (31) in the region of the bend portion to provide a localised progressive series narrowing and opening of the upstream end of the second passage portion in the general direction of cooling fluid flow.
摘要翻译： 适用于燃气涡轮发动机的涡轮机的机翼叶片或叶片（1）包括具有相对的壁部分（20,22）的纵向延伸的机翼部分（7）。 壁部分通过大致纵向延伸的分隔构件（17）互连，以部分地限定并排布置成大致纵向延伸的第一和第二冷却流体通道部分（11,15）。 第一和第二通道部分由弯曲通道部分（13）以串联的流体流动关系相互连接。 第一通道部分适于将冷却流体引导到弯曲部分，并且第二通道部分适于从弯曲部分排出冷却流体。 分隔构件在弯曲部分的区域中具有第一局部增厚（33），以提供第一通道部分的下游端的局部收缩，以在其进入弯曲通道部分之前加速冷却流体流动。 分隔构件在弯曲部分的区域中具有第二局部增厚（31），以提供在冷却流体流动的大致方向上的第二通道部分的上游端的局部渐进式变窄和打开。
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公开(公告)号：US07399160B2
公开(公告)日：2008-07-15
申请号：US11188881
申请日：2005-07-26
申请人： Neil W Harvey , Peter T Ireland , John P C W Ling
发明人： Neil W Harvey , Peter T Ireland , John P C W Ling
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/187 , F01D25/12 , F05D2250/25 , F05D2260/2212 , Y02T50/676
摘要： A turbine component such as a turbine blade has a cooling chamber that is tapered. The taper induces and maintains a helical swirl that improves the cooling efficiency of the cooling process and enables the turbine component to operate at higher temperatures.
摘要翻译： 诸如涡轮叶片的涡轮机部件具有锥形的冷却室。 锥度引起并保持螺旋涡流，提高了冷却过程的冷却效率，并使得涡轮机部件能够在更高的温度下运行。
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公开(公告)号：US06418806B1
公开(公告)日：2002-07-16
申请号：US09433953
申请日：1999-11-04
IPC分类号： G01K1116
CPC分类号： G01N25/50
摘要： The fire resistance of components normally subject to a standard flame test is evaluated using low temperature model tests. Reynolds number, Froude number, the pressure ratio of the flame to the surrounding atmosphere are matched in the modelling parameters and account is taken of the Prandtl number. Also, the model flow is controlled so as to match the change of momentum flux ratio in the flow through the burner used in a standard flame test. The method allows testing of easily produced model components at temperatures less than 90° C., with savings of cost and time.
摘要翻译： 通常使用低温模型试验来评估通常进行标准火焰试验的部件的耐火性。 雷诺数，弗劳德数，火焰与周围大气的压力比在建模参数中匹配，并考虑了普朗特数。 此外，模型流量被控制以便匹配在通过标准火焰测试中使用的燃烧器的流动中的动量通量比的变化。 该方法允许在低于90℃的温度下测试易于生产的模型组件，节省成本和时间。
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公开(公告)号：US20100232947A1
公开(公告)日：2010-09-16
申请号：US12708207
申请日：2010-02-18
IPC分类号： F02C7/18
摘要： There is disclosed an impingement cooling arrangement for a gas turbine engine (6), and an engine provided with such an arrangement. The cooling arrangement comprises at least part of a casing (21) configured to define a flowpath for the passage of hot gases through the engine, and a manifold (22) configured to direct cooling air against an outer surface (23) of the casing for impingement cooling thereof. The arrangement is characterised by said manifold (22) being configured to direct a primary flow of cooling air (65) against is a first area (64) of the casing outer surface (23) for impingement cooling of said first area, and to recirculate (66) at least a portion of said primary flow of cooling air after impingement against said first area (64) and to direct at least a portion of the recirculated flow against a second area (67) of the casing outer surface (23) for impingement cooling of said second area (67). In a preferred arrangement, is the manifold (22) is spaced from said casing (21) so as to define a space (41) between the manifold and the outer surface (23) of the casing, and the manifold (22) further comprises a baffle (46) extending at least partially across said space, substantially towards said casing (21), so as to at least partially divide said space (41) into a first region (58) adjacent said first area (64), and a second region (59) adjacent said second area (67).
摘要翻译： 公开了一种用于燃气涡轮发动机（6）的冲击冷却装置和具有这种装置的发动机。 冷却装置包括构造成限定用于使热气体通过发动机的流路的壳体（21）的至少一部分，以及构造成将冷却空气引导到壳体的外表面（23）的歧管（22），用于 冲击冷却。 该装置的特征在于，所述歧管（22）构造成引导冷却空气（65）的主流抵抗壳体外表面（23）的第一区域（64），用于冲击冷却所述第一区域，并且再循环 （66）在冲击所述第一区域（64）之后的所述主要冷却空气流的至少一部分并且将所述再循环流的至少一部分引导到所述壳体外表面（23）的第二区域（67） 所述第二区域（67）的冲击冷却。 在优选的布置中，歧管（22）与所述壳体（21）间隔开，以便在歧管和壳体的外表面（23）之间限定空间（41），并且歧管（22）还包括 至少部分地跨过所述空间延伸的挡板（46），基本上朝向所述壳体（21）延伸，以便至少部分地将所述空间（41）分隔成与所述第一区域（64）相邻的第一区域（58），以及 邻近所述第二区域（67）的第二区域（59）。
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公开(公告)号：US07137781B2
公开(公告)日：2006-11-21
申请号：US10701560
申请日：2003-11-06
申请人： Neil W Harvey , Chi W J P Ling , Peter T Ireland
发明人： Neil W Harvey , Chi W J P Ling , Peter T Ireland
CPC分类号： F01D5/187 , F05D2240/126 , F05D2250/25 , F05D2260/2212 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine component, such as a turbine blade 1, 21, has a coolant supply passage 4, 24 and a cooling chamber 3, 23 connected by an injection passage 5, 25. The cooling chamber 3, 23 includes flow guides in the form of vanes 7, 8 or grooves 37 which act to create a coolant flow in a spiral direction. Thus, there is limited coolant flow impingement and greater cooling effect to allow the turbine component to operate at higher temperatures.
摘要翻译： 涡轮机部件，例如涡轮叶片1,2，具有通过喷射通道5,25连接的冷却剂供应通道4,24和冷却室3,23。 冷却室3,23包括叶片7,8形式的流动引导件或用于在螺旋方向产生冷却剂流的槽37。 因此，存在有限的冷却剂流冲击和更大的冷却效果，以允许涡轮机部件在较高温度下运行。
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公开(公告)号：US08414255B2
公开(公告)日：2013-04-09
申请号：US12708207
申请日：2010-02-18
摘要： There is disclosed an impingement cooling arrangement for a gas turbine engine (6), and an engine provided with such an arrangement. The cooling arrangement comprises at least part of a casing (21) configured to define a flowpath for the passage of hot gases through the engine, and a manifold (22) configured to direct cooling air against an outer surface (23) of the casing for impingement cooling thereof. The arrangement is characterized by said manifold (22) being configured to direct a primary flow of cooling air (65) against a first area (64) of the casing outer surface (23) for impingement cooling of said first area, and to recirculate (66) at least a portion of said primary flow of cooling air after impingement against said first area (64) and to direct at least a portion of the recirculated flow against a second area (67) of the casing outer surface (23) for impingement cooling of said second area (67). In a preferred arrangement, the manifold (22) is spaced from said casing (21) so as to define a space (41) between the manifold and the outer surface (23) of the casing, and the manifold (22) further comprises a baffle (46) extending at least partially across said space, substantially towards said casing (21), so as to at least partially divide said space (41) into a first region (58) adjacent said first area (64), and a second region (59) adjacent said second area (67).
摘要翻译： 公开了一种用于燃气涡轮发动机（6）的冲击冷却装置和具有这种装置的发动机。 冷却装置包括构造成限定用于使热气体通过发动机的流路的壳体（21）的至少一部分，以及构造成将冷却空气引导到壳体的外表面（23）的歧管（22），用于 冲击冷却。 该装置的特征在于，所述歧管（22）构造成将冷却空气（65）的主流引导到壳体外表面（23）的第一区域（64）上，用于冲击冷却所述第一区域，并使 66）在冲击所述第一区域（64）之后的所述主要冷却空气流的至少一部分并且将所述再循环流的至少一部分引导到所述壳体外表面（23）的用于冲击的第二区域（67） 所述第二区域（67）的冷却。 在优选的布置中，歧管（22）与所述壳体（21）间隔开，以便在歧管和壳体的外表面（23）之间限定一个空间（41），而歧管（22）还包括一个 挡板（46）至少部分地延伸穿过所述空间，基本上朝向所述壳体（21）延伸，以便至少部分地将所述空间（41）分隔成与所述第一区域（64）相邻的第一区域（58），并且第二 邻近所述第二区域（67）的区域（59）。
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公开(公告)号：US08240994B2
公开(公告)日：2012-08-14
申请号：US12149165
申请日：2008-04-28
IPC分类号： F01D5/18
CPC分类号： F01D5/186
摘要： An aerofoil for a gas turbine engine comprising a pressure wall and a suction wall and defining leading and trailing edges, the walls define a passage into which is supplied a cooling fluid, an array of cooling holes is provided through at least one of the walls to allow the cooling fluid to flow from an interior surface to an exterior surface. The array of holes comprise two groups, the holes of each group are angled to intersect the holes of the other group and are characterized in that the holes of at least one of the groups comprises two or more holes at different angles to one another to vary the porosity of the wall to account for otherwise varying wall temperatures. This arrangement also allows either less coolant mass flow to maintain a constant metal temperature, or a lower metal temperature for a given coolant mass flow.
摘要翻译： 一种用于燃气涡轮发动机的机翼，包括压力壁和吸力壁并限定前缘和后缘，壁限定了供给冷却流体的通道，冷却孔阵列通过至少一个壁提供到 允许冷却流体从内表面流到外表面。 孔阵列包括两组，每组的孔的角度与另一组的孔相交，并且其特征在于，至少一个组的孔包括彼此不同角度的两个或多个孔，以改变 墙壁的孔隙度，以解决另外变化的壁温。 这种布置还允许更少的冷却剂质量流量保持恒定的金属温度，或者给定冷却剂质量流量的较低金属温度。
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公开(公告)号：US20080286116A1
公开(公告)日：2008-11-20
申请号：US12149165
申请日：2008-04-28
IPC分类号： F01D5/08
CPC分类号： F01D5/186
摘要： An aerofoil for a gas turbine engine comprising a pressure wall and a suction wall and defining leading and trailing edges, the walls define a passage into which is supplied a cooling fluid, an array of cooling holes is provided through at least one of the walls to allow the cooling fluid to flow from an interior surface to an exterior surface. The array of holes comprise two groups, the holes of each group are angled to intersect the holes of the other group and are characterised in that the holes of at least one of the groups comprises two or more holes at different angles to one another to vary the porosity of the wall to account for otherwise varying wall temperatures. This arrangement also allows either less coolant mass flow to maintain a constant metal temperature, or a lower metal temperature for a given coolant mass flow.
摘要翻译： 一种用于燃气涡轮发动机的机翼，包括压力壁和吸力壁并限定前缘和后缘，壁限定了供给冷却流体的通道，冷却孔阵列通过至少一个壁提供到 允许冷却流体从内表面流到外表面。 孔阵列包括两组，每组的孔的角度与另一组的孔相交，并且其特征在于，至少一个组的孔包括彼此不同角度的两个或多个孔，以改变 墙壁的孔隙度，以解决另外变化的壁温。 这种布置还允许更少的冷却剂质量流量保持恒定的金属温度，或者给定冷却剂质量流量的较低金属温度。
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