CN106150562A - 具有外扩末梢的转子叶片 - Google Patents
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/29—Three-dimensional machined; miscellaneous
- F05D2250/294—Three-dimensional machined; miscellaneous grooved
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/324—Arrangement of components according to their shape divergent
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- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
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Abstract
本发明涉及具有外扩末梢的转子叶片。具体而言,一种转子叶片包括具有叶片末梢的翼型件和形成在叶片末梢处的末梢腔。末梢腔包括末梢帽,其从末梢沿径向向内凹入并由翼型件的压力和吸力侧壁连续地环绕。末梢帽还包括孔口,其延伸穿过末梢帽且设置为用于限定在翼型件内的内部腔和末梢腔之间的流体连通。排气端口设置为用于穿过压力侧壁、吸力侧壁或后缘中的一者离开末梢腔的流体连通。限定末梢腔的吸力侧壁或压力侧壁中的至少一者的一部分从末梢腔关于径向方向斜向朝外延伸。
Description
技术领域
本发明大体涉及用于涡轮的转子叶片。更特别地,本发明涉及具有配置成用于冷却转子叶片的后缘部分的外扩末梢的转子叶片。
背景技术
在摄取空气的涡轮机械(例如,燃气涡轮)中,空气通过压缩机加压且然后与燃料混合,并在环状阵列的燃烧器内点燃以产生燃烧气体。热气体传送通过内衬且进入限定在涡轮机械的涡轮区段内的热气体路径。动能经由连接到转子轴的一排或多排涡轮转子叶片从燃烧气体获取。获取的动能引起转子轴旋转,从而做功。
涡轮转子叶片或叶片大体在非常高温的环境中操作。为了达到足够的使用寿命,叶片典型地包括各种内部冷却通路或腔。在燃气涡轮的操作期间,诸如压缩空气的冷却介质传送通过内部冷却通路。冷却介质的一部分可通过沿着叶片表面限定的各种冷却孔传送到内部冷却通路外,从而降低高的表面温度。对于经由冷却介质有效地冷却来说通常有挑战性的区域是涡轮转子叶片的叶片末梢部分,更特别地是叶片末梢的后缘区域。
叶片末梢大体限定在涡轮转子叶片的径向末端处,且从围绕叶片排的涡轮护罩沿径向朝内定位。涡轮护罩限定热气体路径的径向朝外的边界。叶片末梢与涡轮护罩的接近使得叶片末梢难以冷却。护罩和叶片末梢的邻近最大限度减少经过末梢的热操作流体的泄漏,这相应地改善涡轮效率。
在特定叶片设计中,通过凹入末梢帽形成的末梢腔以及压力侧壁和吸力侧壁提供用于获得最小末梢间隙的手段,同时确保足够的叶片末梢冷却。压力侧壁和吸力侧壁从末梢帽沿径向朝外延伸。吸力侧壁和压力侧壁中的至少一者的至少一部分是外扩的,或者关于叶片的径向中线朝外倾斜。压力侧壁在叶片的前缘部分与吸力侧壁相交。然而,压力侧壁不在后缘处与吸力侧壁相交,从而在其间形成开口。该配置大体是由于叶片沿着后缘缺乏适当的壁厚。
在操作中,冷却介质从内部通路穿过末梢帽中的孔排出到末梢腔中,因此有效地冷却压力和吸力侧壁以及末梢帽表面。然而,还可期望有效地冷却翼型件的前缘和后缘。因此存在对于具有改进的叶片末梢后缘冷却的叶片末梢设计的需要。
发明内容
本发明的方面和优点下面在以下描述中阐述,或者可从该描述显而易见,或者可通过实践本发明被教导。
本发明的一个实施例为一种转子叶片。该转子叶片包括翼型件,翼型件具有前缘和后缘的、连接在前缘和后缘处的压力侧壁和吸力侧壁、具有在前缘和后缘之间沿着压力侧壁和吸力侧壁延伸的径向外表面的叶片末梢,以及用于接收冷却介质的内部腔。翼型件还包括形成在叶片末梢处的末梢腔。末梢腔包括末梢帽,末梢腔从径向外表面径向向内凹入并由压力侧壁和吸力侧壁连续地环绕。末梢帽还包括延伸穿过末梢帽的内表面和径向相对的顶表面的孔口。孔口设置为用于内部腔和末梢腔之间的流体连通。排气端口设置为用于从末梢腔穿过后缘、压力侧壁或吸力侧壁的流体连通。限定末梢腔的吸力侧壁或压力侧壁中的至少一者的一部分从末梢腔关于径向方向斜向朝外延伸。
本发明的另一个实施例为一种燃气涡轮。该燃气涡轮包括,以串行流顺序,压缩机区段、燃烧区段和涡轮区段。涡轮区段包括转子轴和联接到转子轴的多个转子叶片。每个转子叶片包括翼型件,翼型件具有前缘和后缘、连接在前缘和后缘处的压力侧壁和吸力侧壁、具有在前缘和后缘之间沿着压力侧壁和吸力侧壁延伸的径向外表面的叶片末梢,以及用于接收冷却介质的内部腔。翼型件还包括形成在叶片末梢处的末梢腔。末梢腔包括末梢帽,末梢腔从径向外表面沿径向向内凹入并由压力侧壁和吸力侧壁连续地环绕。末梢帽还包括延伸穿过末梢帽的内表面和径向相对的顶表面的孔口。孔口设置为用于内部腔和末梢腔之间的流体连通。排气端口设置为用于从末梢腔穿过后缘、压力侧壁或吸力侧壁的流体连通。限定末梢腔的吸力侧壁或压力侧壁中的至少一者的一部分从末梢腔关于径向方向斜向朝外延伸。
技术方案1.一种转子叶片,包括:
翼型件,其具有前缘和后缘、连接在所述前缘和所述后缘处的压力侧壁和吸力侧壁、具有在所述前缘和所述后缘之间沿着所述压力侧壁和所述吸力侧壁延伸的径向外表面的叶片末梢,以及用于接收冷却介质的内部腔,所述翼型件还包括:
形成在所述叶片末梢处的末梢腔,所述末梢腔包括末梢帽,所述末梢帽从所述径向外表面沿径向向内凹入并所述压力侧壁和所述吸力侧壁连续地环绕,其中所述末梢帽还包括孔口,所述孔口延伸穿过所述末梢帽的内表面和径向相对的顶表面且设置为用于所述内部腔和所述末梢腔之间的流体连通,以及排气端口,所述排气端口设置为用于从所述末梢腔穿过所述后缘、所述压力侧壁或所述吸力侧壁的流体连通;
其中限定所述末梢腔的所述吸力侧壁或所述压力侧壁中的至少一者的一部分从所述末梢腔关于径向方向斜向朝外延伸。
技术方案2.根据技术方案1所述的转子叶片,其中,所述排气端口在所述末梢帽的顶表面和所述叶片末梢的径向外表面之间延伸穿过所述后缘。
技术方案3.根据技术方案1所述的转子叶片,其中,所述排气端口接近所述后缘在所述末梢帽的顶表面和所述叶片末梢的径向外表面之间延伸穿过所述吸力侧壁。
技术方案4.根据技术方案1所述的转子叶片,其中,所述排气端口接近所述后缘在所述末梢帽的顶表面和所述叶片末梢的径向外表面之间延伸穿过所述压力侧壁。
技术方案5.根据技术方案1所述的转子叶片,其中,所述末梢帽沿着所述末梢帽的外围连接到所述压力侧壁和所述吸力侧壁。
技术方案6.根据技术方案1所述的转子叶片,其中,所述转子叶片还包括限定在所述末梢帽的顶表面内的槽。
技术方案7.根据技术方案6所述的转子叶片,其中,所述槽沿着所述翼型件的拱弧线延伸。
技术方案8.根据技术方案6所述的转子叶片,其中,所述槽沿着所述翼型件的拱弧线从所述翼型件的后缘朝前缘延伸。
技术方案9.根据技术方案1所述的转子叶片,其中,延伸穿过所述末梢帽的内表面和顶表面的所述孔口朝所述翼型件的后缘成角度。
技术方案10.根据技术方案1所述的转子叶片,其中,限定所述末梢腔的所述压力侧壁的内表面或所述吸力侧壁的内表面中的至少一者从所述末梢帽关于所述径向方向斜向朝外延伸。
技术方案11.根据技术方案1所述的转子叶片,其中,所述转子叶片还包括沿着所述翼型件的后缘限定且沿径向定位在所述末梢帽下方的孔,其中所述孔与所述内部腔流体连通。
技术方案12.根据技术方案1所述的转子,其中,所述排气端口在所述翼型件的后缘处延伸穿过所述叶片末梢的径向外表面,其中所述排气端口与所述末梢腔流体连通。
技术方案13.一种燃气涡轮,包括:
压缩机区段;
燃烧区段;和
涡轮区段,所述涡轮区段具有转子轴和联接到所述转子轴的多个转子叶片,每个转子叶片包括:
翼型件,其具有前缘和后缘、连接在所述前缘和所述后缘处的压力侧壁和吸力侧壁、具有在所述前缘和所述后缘之间沿着所述压力侧壁和所述吸力侧壁延伸的径向外表面的叶片末梢,以及用于接收冷却介质的内部腔,所述翼型件还包括:
形成在所述叶片末梢处的末梢腔,所述末梢腔包括末梢帽,所述末梢腔从所述径向外表面沿径向向内凹入并由所述压力侧壁和吸力侧壁连续地环绕,其中所述末梢帽还包括孔口,所述孔口延伸穿过所述末梢帽的内表面和径向相对的顶表面且设置为用于所述内部腔和所述末梢腔之间的流体连通,以及排气端口,所述排气端口设置为用于从所述末梢腔穿过所述后缘、所述压力侧壁或所述吸力侧壁的流体连通;
其中限定所述末梢腔的所述吸力侧壁或所述压力侧壁中的至少一者的一部分从所述末梢腔关于径向方向斜向朝外延伸。
技术方案14.根据技术方案13所述的燃气涡轮,其中,所述排气端口在所述末梢帽的顶表面和所述叶片末梢的径向外表面之间延伸穿过后缘。
技术方案15.根据技术方案13所述的燃气涡轮,其中,所述排气端口接近所述后缘在所述末梢帽的顶表面和所述叶片末梢的径向外表面之间延伸穿过所述吸力侧壁。
技术方案16.根据技术方案13所述的燃气涡轮,其中,所述排气端口接近所述后缘在所述末梢帽的顶表面和所述叶片末梢的径向外表面之间延伸穿过所述压力侧壁。
技术方案17.根据技术方案13所述的燃气涡轮,其中,所述燃气涡轮还包括限定在所述末梢帽的顶表面内的槽,其中所述槽沿着所述翼型件的拱弧线从所述翼型件的后缘朝前缘延伸。
技术方案18.根据技术方案13所述的燃气涡轮,其中,限定所述末梢腔的所述压力侧壁的内表面或限定所述末梢腔的所述吸力侧壁的内表面中的至少一者从所述末梢帽关于所述径向方向斜向朝外延伸。
技术方案19.根据技术方案13所述的燃气涡轮,其中,所述燃气涡轮还包括沿着所述翼型件的后缘限定且沿径向定位在所述末梢帽下方的孔,其中所述孔与所述末梢腔流体连通。
技术方案20.根据技术方案13所述的燃气涡轮,其中,所述排气端口在所述翼型件的后缘处延伸穿过所述叶片末梢的径向外表面,其中所述排气端口与所述末梢腔流体连通。
本领域普通技术人员在阅读该说明书后将更好地理解这些实施例的特征和方面等。
附图说明
包括其对于本领域技术人员的最佳模式的本发明的完整和开放的公开在说明书的其余部分中更具体地阐述,包括对附图的参考,在附图中:
图1示出如可结合本发明的至少一个实施例的示例性燃气涡轮的功能图;
图2是如可结合在图1中示出的燃气涡轮中以及如可结合本公开的各种实施例的示例性转子叶片的透视图;
图3是根据本发明的至少一个实施例的示例性翼型件的一部分的透视图;
图4是根据本发明的至少一个实施例的示例性翼型件的一部分的透视图;
图5是根据本发明的至少一个实施例沿着如图4中所示的截面线A-A截取的翼型件的一部分的截面侧视图;
图6是根据本发明的至少一个实施例的示例性翼型件的一部分的透视图;
图7是根据本发明的至少一个实施例沿着如图6中所示的截面线B-B截取的翼型件的一部分的截面侧视图;
图8是根据本发明的至少一个实施例沿着如图6中所示的截面线C-C截取的翼型件的截面视图;
图9是根据本发明的至少一个实施例的示例性翼型件的一部分的透视图;
图10是根据本发明的至少一个实施例沿着如图9中所示的截面线D-D截取的翼型件的一部分的截面侧视图;
图11是根据本发明的至少一个实施例的示例性翼型件的一部分的透视图;以及
图12是根据本发明的至少一个实施例沿着如图11中所示的截面线E-E截取的翼型件的一部分的截面侧视图。
部件列表
10 燃气涡轮
12 入口区段
14 压缩机区段
16 燃烧区段
18 涡轮区段
20 排气区段
22 轴
24 转子轴
26 转子盘
28 转子叶片
30 外壳
32 热气体路径
34 热气体
35-99 未使用
100 转子叶片
102 安装/柄部部分
104 安装本体
106 翼型件
108 径向方向
110 平台
112 外表面
114 压力侧壁
116 吸力侧壁
118 根部
120 末梢
122 径向外表面
124 前缘
126 后缘
128 中线/拱弧线
130 冷却介质
132 内部腔
134 末梢腔
136 末梢帽
138 内表面-压力侧
140 内表面-吸力侧壁
142 外围
144 孔/孔口
146 内表面
148 顶表面
150 排气端口
152 孔口
154 排气端口
156 排气端口
158 孔
160 入口
162 出口
164 沟/缝/槽
166 排气端口。
具体实施方式
现在将详细参考本发明存在的实施例,其一个或多个示例在附图中示出。详细描述使用数字和字母标记来参考附图中的特征。附图和描述中类似或相似的标记用于指出本发明的类似或相似的部分。如本文中所用,用语“第一”、“第二”和“第三”可互换地使用以区别一个部件与另一个部件,且不意在表示单个部件的位置或重要性。用语“上游”和“下游”指出关于流体路径中的流体流的相对方向。例如,“上游”指的是流体从其流动的方向,且“下游”指的是流体流到其的方向。用语“径向”指的是大致垂直于特定部件的轴向中心线和/或大致垂直于涡轮机械的轴向中心线的相对方向,且用语“轴向”指的是与特定部件的轴向中心线和/或涡轮机械的轴向中心线大致平行和/或同轴对准的相对方向。
每个示例通过解释本发明而不是限制本发明的方式提供。事实上,对于本领域技术人员将显而易见的是,在不脱离本发明的范围或精神的情况下,可在本发明中做出修改和变型。例如,图示或描述为一个实施例的部分的特征可用在另一实施例上以产生更进一步的实施例。因此,意在使本发明覆盖落在所附权利要求及其等同物的范围内的这些修改和变型。尽管在本文中示出和描述了工业或陆基燃气涡轮,但是如本文所示和所述的本发明不受限于陆基和/或工业燃气涡轮,除非在权利要求中另外规定。例如,如本文中所述的本发明可用于任何类型的涡轮,包括但不限于蒸汽涡轮或船用燃气涡轮。
现在参考附图,图1示出燃气涡轮10的一个实施例的图解视图。燃气涡轮10大体包括入口区段12、布置在入口区段12下游的压缩机区段14、布置在压缩机区段14下游的燃烧器区段16内的多个燃烧器、布置在燃烧器区段16下游的涡轮区段18以及布置在涡轮区段18下游的排气区段20。另外,燃气涡轮10可包括联接在压缩机区段14和涡轮区段18之间的一个或多个轴22。
涡轮区段18可大体包括转子轴24,其具有多个转子盘26(示出其中一个)和从转子盘26沿径向朝外延伸且与其互连的多个转子叶片28。每个转子盘26继而可联接到延伸通过涡轮区段18的转子轴24的一部分。涡轮区段18还包括外壳30,其沿周向围绕转子轴24和转子叶片28,从而至少部分地限定通过涡轮区段18的热气体路径32。
在操作期间,诸如空气的工作流体流过入口区段12且流到压缩机区段14中,空气在压缩机区段14中逐步压缩,因此提供加压空气至燃烧区段16的燃烧器。加压空气与燃料混合,且在各个燃烧器内燃烧以产生燃烧气体34。燃烧气体34从燃烧器区段16流动通过热气体路径32到涡轮区段18中,其中,能量(动能和/或热能)从燃烧气体34传递至转子叶片28,因此引起转子轴24旋转。机械旋转能然后可用来为压缩机区段14提供动力和/或发电。离开涡轮区段18的燃烧气体34然后可经由排气区段20从燃气涡轮10排出。
图2是如可结合本发明的一个或多个实施例且如可代替图1中所示的转子叶片28结合到燃气涡轮10的涡轮区段18中的示例性转子叶片100的透视图。如图2中所示,转子叶片100大体包括具有安装本体104的安装或柄部部分102,以及沿径向方向108从转子叶片100的平台部分110朝外延伸的翼型件106。平台110大体用作用于流动通过涡轮区段18的热气体路径32(图1)的燃烧气体34的径向朝内的边界。如图2中所示,安装或柄部部分102的安装本体104可从平台110沿径向朝内延伸且可包括根部结构,诸如燕尾件,其配置成使转子叶片100和转子盘26互相连接或将转子叶片100紧固至转子盘26(图1)。
翼型件106包括围绕翼型件106的外表面112。外表面112至少部分地由压力侧壁114和相对的吸力侧壁116限定。压力侧壁114和吸力侧壁116在从翼型件106的根部118到翼型件106的叶片末梢或末梢120的跨距中从平台110大致沿径向朝外延伸。翼型件106的根部118可限定在翼型件106和平台110之间的交叉处。叶片末梢120与根部118径向相对地布置。因此,叶片末梢120的径向外表面122可大体限定转子叶片100的径向最外部部分。
压力侧壁114和吸力侧壁116在翼型件106的前缘124处接合在一起或互连,前缘124定向到燃烧气体34的流中。压力侧壁114和吸力侧壁116还在翼型件106的后缘126处接合在一起或互连,后缘126在下游与前缘124间隔开。压力侧壁114和吸力侧壁116在后缘126附近连续。压力侧壁114大体凹入,且吸力侧壁116大体凸起。翼型件106的弦是连接前缘114和后缘116的直线的长度,且从前缘114到后缘116的方向典型地描述为弦向方向。对分压力侧壁114和吸力侧壁116的弦向线典型地称为翼型件106的中线或拱弧线128。
涡轮转子叶片的内部冷却是公知的且典型地利用冷却介质,如通过实线和虚线箭头130指示地,诸如从燃气涡轮发动机10的压缩机区段14(图1)放出的相对冷的压缩空气,其适当地引导通过转子叶片100的安装或柄部部分102且到内部腔或通路132中,内部腔或通路132在压力侧壁114和吸力侧壁116之间至少部分地限定在翼型件106内。
内部腔132可采取任何常规的形式,且典型地为蜿蜒通路的形式。冷却介质130从安装或柄部部分102进入内部腔132,且传送通过内部腔132以用于使翼型件106从流过其外表面112的燃烧气体34的加热效应适当地冷却。薄膜冷却孔(未示出)可布置在压力侧壁114和/或吸力侧壁116上,以用于常规地薄膜冷却翼型件106的外表面112。
在各种实施例中,末梢腔或压室134形成在叶片末梢120处或其内。末梢腔134至少部分地通过末梢帽136形成。如图2中所示,末梢帽136从叶片末梢120和/或叶片末梢120的顶表面122沿径向朝内凹入,且形成末梢腔134的基底部分。末梢帽136由压力侧壁114和吸力侧壁116连续围绕。
末梢帽136连接到密封件和/或形成密封件,该密封件在翼型件106的前缘124和后缘126之间沿着末梢帽136的外围142抵靠压力侧壁114的内表面或侧138以及吸力侧壁116的内表面或侧140。末梢帽136还包括多个孔或孔口144,其延伸穿过末梢帽136的内表面或侧146以及顶表面或侧148且提供用于内部腔132和末梢腔134之间的流体连通。
图3提供了根据本发明的至少一个实施例的包括叶片末梢120的翼型件106的一部分的透视图。图4提供了根据本发明的至少一个实施例的包括叶片末梢120的翼型件106的一部分的透视图。图5提供了根据至少一个实施例沿着如图4中所示的截面线A-A截取的翼型件106的一部分的截面侧视图。
在特定实施例中,如图3中所示,限定末梢腔134的吸力侧壁116或压力侧壁114中的至少一者的一部分从末梢腔134关于径向方向108和/或关于翼型件106的外表面112斜向朝外延伸。径向方向108可大致垂直于末梢帽136的顶表面148。
在各种实施例中,如图3中所示,限定末梢腔134的吸力侧壁116的一部分和限定末梢腔134的压力侧壁114的一部分从末梢腔134关于径向方向108和/或关于翼型件106的外表面112斜向朝外延伸。在各种实施例中,限定末梢腔134的吸力侧壁116的一部分从末梢腔134关于径向方向108和/或关于翼型件106的外表面112斜向朝外延伸。在各种实施例中,限定末梢腔134的压力侧壁114的一部分从末梢腔134关于径向方向108和/或关于翼型件106的外表面112斜向朝外延伸。
限定末梢腔134的吸力侧壁116的内表面或侧140的一部分可从末梢腔134关于径向方向108斜向朝外延伸,因此增加末梢腔134的总体积。另外或备选地,如图3中所示,限定末梢腔134的压力侧壁114的内表面或侧138的一部分可关于径向方向108从末梢腔134斜向朝外延伸,因此增加末梢腔134的总体积。
在各种实施例中,如图3中所示,至少一个排气端口150设置为用于冷却介质从末梢腔穿过后缘126、压力侧壁114或吸力侧壁116的流体连通。翼型件106可包括任何数量的排气端口150且不限于提供的附图中所示和本文所描述的特定数量的排气端口150,或者特定位置的排气端口150,除非权利要求中特别地提供。
在各种实施例中,如图3所示,翼型件106包括延伸通过后缘126的排气端口150。排气端口150可大体限定和/或定位在末梢帽136的顶表面146和叶片末梢120的径向外表面122之间。在一个实施例中,排气端口150沿着翼型件106的拱弧线128(图2)或者与其对齐延伸穿过后缘122。排气端口150可为圆形的或者椭圆形的或者其他任何合适的截面形状。
如图3中所示,多个孔口144的至少一个孔口152可接近和/或邻接排气端口150延伸穿过末梢帽136的内表面146和顶表面148。孔口152设置为用于内部腔132和末梢腔134在排气端口150上游的区域中的流体连通。
在各种实施例中,如图4中所示,翼型件106可包括一个或多个排气端口154,其接近和/或邻近后缘126在末梢帽136的顶表面148和叶片末梢120的径向外表面122之间延伸穿过吸力侧壁116。另外或作为备选,翼型件106可包括一个或多个排气端口156,其接近和/或邻近后缘126在末梢帽136的顶表面148和叶片末梢120的径向外表面122之间延伸穿过压力侧壁114。
在特定实施例中,如图4和图5中所示,孔口152朝翼型件106的后缘126成角度。在特定实施例中,一个或多个孔158径向地在末梢帽136的下方和/或径向地在排气端口150的下方沿着翼型件106的后缘126限定。一个或多个孔158可与内部腔132流体连通。在各种实施例中,如图5中所示,排气端口150可为渐缩的或定形为使得排气端口150的入口160相比排气端口150的出口162较小或者具有较小的截面积。
图6提供了根据本发明至少一个实施例的包括叶片末梢120的翼型件106的一部分的透视图。图7提供了根据本发明的至少一个实施例沿如图6中所示的截面线B-B截取的翼型件106的一部分的截面侧视图。图8提供了根据本发明的至少一个实施例沿图6中所示的截面线C-C截取的翼型件106的一部分的截面视图。
在特定实施例中,如图6-图8中共同示出的那样,表面凹口(诸如槽、缝或凹槽164)限定在末梢帽136的顶表面148内。槽164可限定为接近排气端口150。在特定实施例中,槽164从翼型件106的后缘126朝着前缘124延伸。在特定实施例中,槽164沿着翼型件106的拱弧线128(图2)延伸。在特定实施例中,槽164可至少部分地限定排气端口150。
图9提供了根据本发明的至少一个实施例的包括叶片末梢120的翼型件106的一部分的透视图。图10提供了根据本发明的至少一个实施例沿如图9中所示的截面线D-D截取的翼型件106的一部分的截面侧视图。在特定实施例中,如图9和图10中共同示出的那样,翼型件106可包括接近后缘126沿着吸力侧壁116定位的排气端口154,其设置为用于离开末梢腔134的流体连通。另外或作为备选,翼型件106可包括接近后缘126沿着压力侧壁114定位的排气端口156,其设置为用于离开末梢腔134的流体连通。在特定实施例中,如图9和图10中所示,翼型件106可包括沿着后缘126定位的一个或多个孔158。
图11提供了根据本发明的至少一个实施例的包括叶片末梢120的翼型件106的一部分的透视图。图12提供了根据本发明的至少一个实施例的沿着如图11中所示的截面线E-E截取的翼型件106的一部分的截面侧视图。在特定实施例中,如图11和图12中共同示出的那样,翼型件106可包括排气端口166,其在翼型件106的后缘126处延伸穿过叶片末梢120的径向外表面122。如图12中所示,排气端口166的一部分在沿径向向上转向之前可沿弦向延伸,并穿透径向外表面122。这样,排气端口166可引导一部分冷却介质从叶片末梢120沿径向向外地朝向燃气涡轮10的护罩(未示出)。如图12中所示,排气端口166与末梢腔134流体连通。
该书面描述使用示例来公开本发明,包括最佳模式,并且还使本领域技术人员能够实践本发明,包括制造和使用任何装置或系统以及执行任何包含的方法。本发明可申请专利的范围由权利要求限定,并且可包括本领域技术人员想到的其它示例。如果这些其它示例具有不与权利要求的字面语言不同的结构要素,或者如果它们包括与权利要求的字面语言无实质差异的等同结构要素,则意在使这些其它示例处于权利要求的范围内。
Claims (10)
1.一种转子叶片,包括:
翼型件,其具有前缘和后缘、连接在所述前缘和所述后缘处的压力侧壁和吸力侧壁、具有在所述前缘和所述后缘之间沿着所述压力侧壁和所述吸力侧壁延伸的径向外表面的叶片末梢,以及用于接收冷却介质的内部腔,所述翼型件还包括:
形成在所述叶片末梢处的末梢腔,所述末梢腔包括末梢帽,所述末梢帽从所述径向外表面沿径向向内凹入并由所述压力侧壁和所述吸力侧壁连续地环绕,其中所述末梢帽还包括孔口,所述孔口延伸穿过所述末梢帽的内表面和径向相对的顶表面且设置为用于所述内部腔和所述末梢腔之间的流体连通,以及排气端口,所述排气端口设置为用于从所述末梢腔穿过所述后缘、所述压力侧壁或所述吸力侧壁的流体连通;
其中限定所述末梢腔的所述吸力侧壁或所述压力侧壁中的至少一者的一部分从所述末梢腔关于径向方向斜向朝外延伸。
2.根据权利要求1所述的转子叶片,其特征在于,所述排气端口在所述末梢帽的顶表面和所述叶片末梢的径向外表面之间延伸穿过所述后缘。
3.根据权利要求1所述的转子叶片,其特征在于,所述排气端口接近所述后缘在所述末梢帽的顶表面和所述叶片末梢的径向外表面之间延伸穿过所述吸力侧壁。
4.根据权利要求1所述的转子叶片,其特征在于,所述排气端口接近所述后缘在所述末梢帽的顶表面和所述叶片末梢的径向外表面之间延伸穿过所述压力侧壁。
5.根据权利要求1所述的转子叶片,其特征在于,所述末梢帽沿着所述末梢帽的外围连接到所述压力侧壁和所述吸力侧壁。
6.根据权利要求1所述的转子叶片,其特征在于,所述转子叶片还包括限定在所述末梢帽的顶表面内的槽。
7.根据权利要求6所述的转子叶片,其特征在于,所述槽沿着所述翼型件的拱弧线延伸。
8.根据权利要求6所述的转子叶片,其特征在于,所述槽沿着所述翼型件的拱弧线从所述翼型件的后缘朝前缘延伸。
9.根据权利要求1所述的转子叶片,其特征在于,延伸穿过所述末梢帽的内表面和顶表面的所述孔口朝所述翼型件的后缘成角度。
10.根据权利要求1所述的转子叶片,其特征在于,限定所述末梢腔的所述压力侧壁的内表面或所述吸力侧壁的内表面中的至少一者从所述末梢帽关于所述径向方向斜向朝外延伸。
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JP2016211547A (ja) | 2016-12-15 |
CN106150562B (zh) | 2021-02-12 |
EP3088675B1 (en) | 2022-02-23 |
EP3088675A1 (en) | 2016-11-02 |
JP6885677B2 (ja) | 2021-06-16 |
US10107108B2 (en) | 2018-10-23 |
US20160319673A1 (en) | 2016-11-03 |
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