CN1963156A - 涡轮叶片 - Google Patents

涡轮叶片 Download PDF

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CN1963156A
CN1963156A CNA2006101288986A CN200610128898A CN1963156A CN 1963156 A CN1963156 A CN 1963156A CN A2006101288986 A CNA2006101288986 A CN A2006101288986A CN 200610128898 A CN200610128898 A CN 200610128898A CN 1963156 A CN1963156 A CN 1963156A
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trailing edge
aperture
blade
mentioned
hole
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W·A·克卢斯
S·J·芬克
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Raytheon Technologies Corp
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United Technologies Corp
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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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B42—BOOKBINDING; ALBUMS; FILES; SPECIAL PRINTED MATTER
    • B42D—BOOKS; BOOK COVERS; LOOSE LEAVES; PRINTED MATTER CHARACTERISED BY IDENTIFICATION OR SECURITY FEATURES; PRINTED MATTER OF SPECIAL FORMAT OR STYLE NOT OTHERWISE PROVIDED FOR; DEVICES FOR USE THEREWITH AND NOT OTHERWISE PROVIDED FOR; MOVABLE-STRIP WRITING OR READING APPARATUS
    • B42D9/00—Bookmarkers; Spot indicators; Devices for holding books open; Leaf turners
    • B42D9/001—Devices for indicating a page in a book, e.g. bookmarkers
    • B42D9/002—Devices for indicating a page in a book, e.g. bookmarkers permanently attached to the book
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/13—Manufacture by removing material using lasers
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/19—Two-dimensional machined; miscellaneous
    • F05D2250/191—Two-dimensional machined; miscellaneous perforated
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/19—Two-dimensional machined; miscellaneous
    • F05D2250/192—Two-dimensional machined; miscellaneous bevelled
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

本发明提出了一种叶片，它具有：一个平台；和一个翼面，该翼面具有：一个位于上述平台处的叶根，一个具有减压区的叶尖，前缘和后缘，和一条内部冷却通道网路，该网路包括：至少一个后缘内空穴，多个从上述后缘延伸至上述后缘内空穴的后缘小孔，和多个从上述叶尖延伸至上述后缘内空穴的叶尖小孔，所述减压区仅部分地穿越所述叶尖小孔的出口。

Description

涡轮叶片
本申请是申请号为200410002544.8、申请日为2004年1月20日、名称为涡轮叶片的专利申请的分案申请。
技术领域
本发明涉及涡轮机，尤其涉及冷却的涡轮叶片。
背景技术
热的控制是涡轮叶片设计和制造技术中的一个重要考虑。涡轮叶片通常做成具有内部冷却通道网路，普通的冷却通道网路接收经叶片平台的冷却空气，该冷却空气经回旋状流道流过翼面，至少有一部分冷却空气经翼面上的孔而离开叶片。这些孔包括例如沿翼面的压力侧和负压侧表面分布的“气膜孔”和位于前缘和后缘上这些表面接合处的小孔。另外在叶尖上也可设置小孔。在普通的制造技术中，涡轮叶片的主要部分通过铸造和机加工工艺制成。在铸造过程中，采用一种牺牲型芯来形成冷却通道网路的主要部分。上述型芯通过其在铸件尖部突出的部分正确地支承在叶片尖部，当型芯脱除后便留下相应的孔洞。因此，通常制出带有一种叶尖部空腔的叶片铸件，并在上述尖部空腔内置入一种板盖以便至少部分地阻塞由型芯留下的孔洞。这就可按需要调节流过叶尖的气流量和分布，以达到理想的性能。美国专利No.3533712、3885886、3982851、4010531、4073599、和5564902公开过上述结构的实例。在多种这类叶片中，上述的板件置于上述铸件尖部空腔内部低于叶尖顶表面之处而形成叶片尖部空穴或者说叶尖充气区。
发明内容
本发明提出了一种具有一个平台和一个翼面的叶片，该翼面具有：一个位于上述平台处的叶根，一个具有减压区的叶尖，前缘和后缘，和一条内部冷却通道网路，该网路包括：至少一个后缘内空穴，多个从上述后缘延伸至上述后缘内空穴的后缘小孔，和多个从上述叶尖延伸至上述后缘内空穴的叶尖小孔，所述减压区仅部分地穿越所述叶尖小孔的出口。
本发明还提出了一种制造叶片的方法，包含如下步骤：铸出一种涡轮叶片毛胚，该毛胚具有一个平台，和一个翼面，该翼面沿着从上述平台处的叶根附近至叶片末端的长度延伸；该翼面具有将压力侧和负压侧分隔开的前缘和后缘，和具有一条包括至少一个后缘内空穴的冷却通道网路；在翼面上加工出从后缘延伸至上述后缘内空穴的第一组小孔；在翼面上加工出从叶尖延伸至上述后缘内空穴的第二组小孔；和沿着所述叶尖的压力侧形成一个浅槽，该浅槽仅部分地穿过上述第二组小孔的出口。
本发明的一个方面是提供一种叶片，该叶片具有一个平台和一个带有一个位于上述平台处的叶根和一个叶尖的翼面，该翼面具有前缘和后缘以及一条包括至少一个后缘内空穴的内部冷却通道网路。有多个后缘小孔从叶片后缘延伸至后缘内空穴处，还有多个叶尖小孔从叶尖延伸至后缘内空穴处，每个叶尖小孔可具有圆柱形表面，其长度至少比小孔直径大5倍。
在各种设计方案中，上述的叶尖小孔和叶片末端的一组后缘小孔可以从上述后缘内空穴向外分叉。叶尖小孔的横截面可以是圆形的，直径可为0.3～2.0mm。上述叶尖小孔的数目可以是2～6，每个叶尖小孔可穿过叶片铸件。该叶片可具有一个本体和一个叶尖盖板，并可具有一个与内部冷却通道网路连通的叶尖充气区，该充气区可由铸件的沿翼面之压力侧和负压侧延伸的壁部及下沉于该壁部的边缘的盖板之外侧表面所界定。上述的叶片壁沿上述充气区的跨越压力侧和负压侧的后部是不间断的。叶尖可具有一个沿压力侧设置的减压区，该减压区可部分地穿越叶尖小孔的出口。
在下面的附图和说明中示出了本发明的一个或多个实施例的细节。从下面的说明和附图，人们将明白本发明的其他特征、目的和优点。
附图说明
图1是按照本发明的原理的涡轮叶片的透视图；
图2是图1的涡轮叶片的叶尖后缘部分的局部剖视图；
图3是图1的涡轮叶片的负压侧的叶尖后缘部分的局部视图。
在各附图中相同的标号和名称表示相同的部件。
具体实施方式
图1示出一种涡轮叶片20，它具有一个沿着从内侧平台26处附近的叶部24至叶片末端叶尖28的长度延伸的翼面22。可将多个上述的涡轮叶片20以它们各自的内侧平台26彼此并排地装配在一起形成一个界定气流通路内侧部分的环圈。在一个示例性实施例中，叶片20的主要部分由合金制成(例如制成一种铸件)，这种铸件制成带有一个可在低于叶尖平面之处固定安装一个独立的盖板58的叶尖隔室而形成一个叶尖充气区30。
翼面22从前缘40延伸至后缘42，该前缘和后缘分隔叶片的压力侧表面44和负压侧表面46。为了冷却叶片，该叶片内部具有与平台26内的孔口(未示出)相连接的冷却通道网路。示例性的冷却通道网路包括一系列大致沿翼面长度方向延伸的内部空穴。最前沿的空穴规定为大致平行于前缘40延伸的前缘内空穴。最后沿的空穴48(图2)规定为大致平行于后缘42延伸的后缘内空穴48。上述的空穴可在它们的一端或两端和/或沿其长度上的一些部位上互相连接起来。冷却通道网路还包括许多从内部伸向压力侧44和负压侧46的小孔，用于进一步冷却叶片，保护其表面免受外部高温的损害。上述的小孔包括一排从后缘内空穴48延伸至靠近后缘的部位的后缘小孔90。
在示例性实施例中，叶片20的主要部分通过铸造方法和机加工制成。铸件用一种可脱除的型芯来形成其冷却通道网路，典型的铸造方法做出的铸件具有上面所述的可固定装入盖板58的铸造叶尖隔室30(图2)，该隔室30具有一个带有形成叶尖隔室底座的外侧面的腹板60，上述外侧面位于具有由叶片铸件之压力侧和负压侧向上延伸形成的壁式结构之凸缘62的下方。上述腹板60做出有多个孔，这些孔是由可脱除的型芯的安装在外模型上用于支承的部分形成的，并与上述通道网路相连通，这些孔可认为是不希望有的通道，因为它造成叶片中冷却空气的损失。因此，最好用盖板58完全地或部分地将这些孔中的一些或全部堵塞住。上述盖板可以安置在铸造隔室的适当位置上并将其焊接在铸件上而安装起来。在工作中，上述凸缘62(要经受下面所述的开浅槽)大致处于紧靠着邻近于发动机护罩的内表面之处(例如相隔10mm左右)。
图2示出典型的后缘小孔50，它们是轴线标号为500的圆柱形孔，均从后缘42延伸至后缘内空穴48的后端68。一组小孔50大致彼此平行排列，其间距较为均匀，第二组小孔(位于叶片末端处的50A，50B，50C，50D，50E和50F)是不平行排列的，而是从后缘内空穴48呈扇形向外展开排列的。在所示实施例中，后缘小孔50A～50F是包括叶尖小孔70A，70B，70C和70D在内的在端部连续地呈扇形展开排列的一系列小孔中的一部分，上述叶尖小孔的进入端(入口)沿后缘内空穴48的后端68分布，出口端(出口)则沿叶尖分布。典型小孔的截面为圆形，直径为D，典型小孔50A～50F和70A～70D的入口沿后缘内空穴的后端68分布，它们的间距S1基本均匀。该间距S1最好稍小于其余小孔50之间的典型间距(例如邻近一组小孔50的间距S2)。上述的小孔逐渐向外呈扇形展开排列，故它们的轴线500与沿后缘内空穴后端68的内侧方向之间的夹角θ逐渐减小，其θ值从最后一个非扇开展开排列的小孔50的刚超过90°逐渐减小到最后的小孔70D的45°左右。上述的小孔呈扇形展开排列和间距减小比仅仅连续平行排列的小孔更有利于加强叶片后缘尖部的冷却。在典型实施例中，叶尖小孔70A～70D的出口沿隔室30的凸缘62后面的后部72分布。在典型实施例中，凸缘后部72具有一个位于压力侧的浅槽80，该浅槽80至少部分地穿过小孔70A～70D的出口，它用于使叶尖的一个部位凹入到低于后缘部分72的负压侧的不开浅槽的部位82。在涡轮工作中，上述的不开浅槽部位82平行于且紧密地靠近相邻的发动机护罩内表面，由浅槽80形成的凹处导引气流沿浅槽80的表面从小孔70A～70D的出口向后流出而冷却叶尖的邻近于后缘的压力侧。
在一个示例性叶片制造方法中，小孔50，50A～50F和70A～70D可通过钻孔法(例如激光打孔法)加工出来。这项工作在叶片铸出之后或用其他方法制造出之后进行，也可以在最初的铸后加工工序后进行。至少上述的呈扇形展开排列的小孔可通过使单刃(single-bit)钻头(或在激光打孔的情况下是单光束钻头)连续而渐进地不断改变钻头取向的方法钻出来。小孔钻出之后，作为精加工的一部分对凸缘62磨削出浅槽80，由该浅槽80形成的凹部可防止叶尖小孔堵塞。在没有这种凹部的情况下，凸缘后部72与发动机护罩之间的偶然接触可能磨出的材料会进入叶尖小孔而将它们堵塞。通过至少使小孔出口的在压力侧的部分凹进到低于不开浅槽的部位82，就可防止上述的小孔堵塞现象。典型的浅槽80是凹形的，其在压力侧的相对于不开浅槽部位82的深度为R1，在压力侧的叶尖小孔70A～70D的出口与浅槽80交叉处的深度为R2。在典型实施例中，上述深度R1，R2从后缘向前缘逐渐稍稍增加。典型的深度R1约0.5～3.0倍于小孔直径，而典型的深度R2约0.2 5～2.0倍于小孔直径。
在示例性实施例中，叶尖小孔最好为2～6个，而呈扇形展开排列的后缘小孔最好为2～10个。根据一些因素(包括尺寸)不同，小孔数目也可能更多些，在较为狭义的实施例中，叶尖小孔为3～5个，呈扇形展开排列的后缘小孔为4～8个。典型的小孔直径为0.3～2.0mm。示例性的小孔长度为10～30倍于小孔直径(较为狭义的实施例中为15～25倍于小孔直径)。在示例性实施例中，呈扇形展开排列的小孔的上述夹角θ从非扇形展形排列的小孔50起从60°逐渐减小至30°。
上面已经说明了本发明的一个或多个实施例，然而，应当明白，在不违背本发明的精神和范围的情况下还可以进行各种各样的改型。

Claims (10)

1.一种叶片，它具有：
一个平台；和
一个翼面，该翼面具有：
一个位于上述平台处的叶根；
一个具有减压区的叶尖；
前缘和后缘；和
一条内部冷却通道网路，该网路包括：
至少一个后缘内空穴；
多个从上述后缘延伸至上述后缘内空穴的后缘小孔；和
多个从上述叶尖延伸至上述后缘内空穴的叶尖小孔，所述减压区仅部分地穿越所述叶尖小孔的出口。
2.根据权利要求1所述的叶片，其特征在于，所述减压区沿着压力侧设置。
3.根据权利要求1所述的叶片，其特征在于，所述减压区是凹形的。
4.一种涡轮叶片，它具有：
一个平台；和
一个翼面，该翼面具有：
一个位于上述平台处的叶根；
一个具有凸缘的叶尖；
前缘和后缘；和
一条内部冷却通道网路，该网路具有：
一个后缘内空穴；和
多个从后缘内空穴延伸到所述凸缘的叶尖小孔；以及用
于防止上述叶尖小孔因接触而堵塞的结构。
5.根据权利要求4的涡轮叶片，其特征在于，所述多个叶尖小孔从上述的后缘内空穴向外分叉到上述后缘和叶尖。
6.一种制造叶片的方法，包含如下步骤：
铸出一种涡轮叶片毛胚，该毛胚具有
一个平台；和
一个翼面，
该翼面沿着从上述平台处的叶根附近至叶片末端的长度延伸；
具有将压力侧和负压侧分隔开的前缘和后缘；和
具有一条包括至少一个后缘内空穴的冷却通道网路；
在翼面上加工出从后缘延伸至上述后缘内空穴的第一组小孔；
在翼面上加工出从叶尖延伸至上述后缘内空穴的第二组小孔；和
沿着所述叶尖的压力侧形成一个浅槽，该浅槽仅部分地穿过上述第二组小孔的出口。
7.根据权利要求6的方法，其特征在于，第一组小孔和第二组小孔加工成在端部连续地呈扇形展开排列的小孔。
8.根据权利要求6的方法，其特征在于，所述浅槽是凹形浅槽。
9.根据权利要求6的方法，其特征在于，上述的加工第二组小孔的步骤包括连续渐进地改变钻头取向，以便钻出从后缘内空穴分叉的所述第二组小孔。
10.根据权利要求6的方法，其特征在于，上述的加工第一组小孔和加工第二组小孔的步骤包括激光钻孔。
CNA2006101288986A 2003-01-31 2004-01-30 涡轮叶片 Pending CN1963156A (zh)

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