CN101008327A - 薄膜冷却方法和孔的制造 - Google Patents

薄膜冷却方法和孔的制造 Download PDF

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CN101008327A
CN101008327A CNA2007100061734A CN200710006173A CN101008327A CN 101008327 A CN101008327 A CN 101008327A CN A2007100061734 A CNA2007100061734 A CN A2007100061734A CN 200710006173 A CN200710006173 A CN 200710006173A CN 101008327 A CN101008327 A CN 101008327A
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chamber
passage
parts
post
cooling
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B·J·卢查克
E·L·库奇
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Raytheon Technologies Corp
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United Technologies Corp
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    • 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
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    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/186—Film cooling
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    • B22—CASTING; POWDER METALLURGY
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    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
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    • 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
    • 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
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
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    • F05D2230/00—Manufacture
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    • F05D2230/13—Manufacture by removing material using lasers
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    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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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    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
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    • 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
    • F05D2240/303—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 leading edge of a rotor blade
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    • F05D2260/00—Function
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Abstract

一种冷却的铸造部件具有外表面。冷却通道系统从至少一个入口延伸到数个出口。通道系统包括通到至少一个第一出口和围绕至少一个柱的第一通道。系统包括通到至少一个第二出口从至少一个柱通过的第二通道。

Description

薄膜冷却方法和孔的制造
技术领域
本发明涉及对高温部件的冷却。更具体地，本发明涉及对燃气涡轮发动机部件的薄膜冷却。
背景技术
在航空航天工业中，在对部件诸如燃气涡轮发动机部件的冷却方面存在有已经发展成熟的技术。示例性的部件有燃气涡轮发动机动叶片和静叶片。示例性的动叶片和静叶片由被引导流过动叶片或静叶片翼型并且从翼型表面中的冷却孔排出的空气流来冷却。冷却机制可以包括当空气流通过翼型流动时的直接冷却和当空气流已经从翼型上排出之后但是通过靠近翼型表面下游时的薄膜冷却。
发明内容
为了提供有效地薄膜冷却，要求使薄膜冷却空气的预先排出的热量达到最小。这可能涉及到采用第一空气流来冷却通过第二空气流的通道，使得第二空气流在比没有第一空气流存在时更低的温度下流出。
相应地，本发明的一个方面涉及一种具有外表面的冷却的铸造部件。冷却通道系统从至少一个入口延伸到数个出口。该通道系统包括通到至少一个第一出口和围绕至少一个柱(post)的第一通道。该系统包括通到至少一个第二出口从该至少一个柱通过的第二通道。
本发明的一个或多个实施例的细节在附图和以下的说明中给出。从该说明和附图以及从权利要求中可以清楚理解本发明的其它特征、目的和优点。
附图说明
图1是燃气涡轮发动机叶片的视图。
图2是图1的叶片沿着线2-2截取的剖面视图。
图3是形成用于铸造图1的叶片的型模(pattern)的组芯和制模模子的剖面视图。
图4是图3的组芯的耐高温金属芯(RMC)的前视图。
图5是图4的RMC的后视图。
图6是图4的RMC的翼展方向的端视图。
图7是图4的RMC的平面视图。
图8是图1的叶片的中间铸件的剖面视图。
图9是一种备选的组芯的平面视图。
图10是图9的组芯在制模模子中的剖面视图。
相同的标号和符号在各图中表示相同的部件。
具体实施方式
图1示出了简化的燃气涡轮发动机叶片20。该示例性叶片由单一铸件形成并且包括在内缘板24和外围带板26之间沿翼展方向延伸的翼型22。示例性缘板和围带板是环形段的，使得由各个边缘对边缘安装的/密封的缘板和围带板可以形成叶片的周向阵列。翼型22具有前缘30和后缘32。压力侧34和吸入侧36在前缘和后缘之间沿着流向延伸。
示例性翼型由通过在缘板和围带板之一或两者中的一个或多个开口38流入并且从沿着翼型的孔阵列流出的空气冷却。图1的示例性翼型包括一系列沿着或靠近前缘30的翼展方向的第一孔/出口40和沿着压力侧34紧接着前缘30的下游的第二孔/出口42。翼型可以具有其它孔，如沿着压力侧和吸入侧和后缘出口(未示出)的附加的薄膜冷却孔(未示出)。
图2示出了在前缘30附近的区域。所示翼型具有壁体50，其在局部上具有限定翼展方向的前缘供给通道54的内表面52。跨过前缘和具有主要部分56的冷却送气腔(plenum)55设置在壁体内部。出口42是送气腔55在相关联的压力出口通道57的末端处的出口。翼展方向的一系列对应的入口58通过对应的入口通道59对送气腔进行供给。因此，第一空气流60从入口58流过送气腔55和从出口42排出，从而沿着压力侧34流向下游。第一空气流60由此提供对与送气腔相邻的壁体50的直接冷却并且也可以提供沿着压力侧34在出口42的下游对壁体50的薄膜冷却。
在前缘30附近的冷却可能是尤其重要的。为了提供附加的冷却，一系列的出口通道62从相关联的入口64沿着供给通道54直接地延伸到出口40。空气流61从通道62中流过并且从出口40流出。通道62穿过送气腔主要部分56中的柱66。柱66跨在壁体50的内部分和外部分之间。每个柱的周界表面70由空气流60冷却。该冷却限制了当第二空气流在入口64和出口40之间通过时对第二空气流61的加热。因此，空气流61在从出口40排出时可以相对较冷和由此提供了特别增强的薄膜冷却效果。
叶片20或其它冷却的部件可以采用熔模铸造法形成。一种示例性工艺采用耐高温金属芯(RMC)100(图3)来铸造送气腔55和采用陶瓷供给芯102来铸造供给通道54。图3示出了组装到熔模104内的供给芯102上的RMC100。示例性模子104包括具有内表面110的一副半模或拉模106和108，其被定位成限定出空腔112，用于在组芯上模制要牺牲(sacrificial)的型模材料(例如，天然蜡或合成蜡)。在模制之后，型模可以从模子上取出并且制成壳型(例如，在多级熔模工艺中)。该壳型可以被脱蜡和烧制(fired)以形成在其中铸造熔融金属的模子。在铸造之后，壳型和组芯可以被取出(例如，通过机械方式断开壳型和通过化学方式取出组芯)。铸件可以进行机加工和附加的处理，包括施加保护涂层。
图4-7示出了示例性RMC100的进一步的细节。RMC100具有从第一翼展方向末端122延伸到第二翼展方向末端124的主体120。主体120的形状做成可以铸造送气腔主要部分56。相应地，主体120具有翼展方向的孔口阵列126，其被定位和成形成可以铸造柱66。孔口126在内芯表面128和外芯表面130之间延伸。主体120具有第一边缘140，从其上延伸出翼展方向的凸片阵列142。主体120具有第二边缘144，从其上延伸出翼展方向的凸片阵列146。凸片142的近端部分被定位和构造成可铸造送气腔出口通道57。凸片142的远端部分可以被容纳在模子中的对应的隔间中以便将RMC相对于模子对齐。凸片142的远端部分随后可以插入壳型中以便在铸造期间保持/定位RMC。凸片146的近端部分被定位和构造成可铸造入口通道59。凸片146的远端部分构造成可被容纳在供给芯102中的一个或多个对应的隔间中以便将RMC相对于供给芯固定和对齐。
图8示出了在钻出通道62和它们的出口孔40之前的铸造态的部件。示例性的钻孔可以是机械钻孔、激光钻孔或放电加工(EDM)。或者，通道62可以被铸造。在一个示例中，图9和10示出了用于形成通道62和出口40的第二RMC150。示例性RMC150是梳子状的，其具有脊柱152和从脊柱上延伸的翼展方向的齿尖阵列154。齿尖154的近端部分构造成和定位得可以穿过第一RMC100中的孔口126。远端部分被定位和构造成可以被陶瓷供给芯160容纳(图10)，该供给芯160其它方面可以与供给芯102类似。在示例性组芯序列中，第一RMC100被组装到供给芯160上。然后，第二RMC150通过将其齿尖154插入并且穿过孔口126和进入供给芯160中的一个或多个狭口或其它不通的隔间而被组装到供给芯上。组芯然后被放置到制模模子170中。
已经描述了本发明的一个或多个实施例。但可以理解的是在不偏离本发明的精神和范围下可以作出各种修改。例如当在重新设计基线部件中进行实施时，基线部件的细节可以影响任何特定实施方案的细节。虽然示例性的柱是圆形截面的并且围绕它们的周边的整体与相邻的送气腔壁隔开，但是其它的构造也是可能的。类似地通过柱的孔的各种形状和分布也是可能的。因此，其它的实施例包含在后面的权利要求的范围内。

Claims (20)

1.一种冷却的铸造部件，包括：
外表面；和
从至少一个入口延伸到数个出口的冷却通道系统，
其中该通道系统包括：
通到至少一个第一出口和围绕至少一个柱的第一通道；和
通到至少一个第二出口和穿过至少一个柱的第二通道。
2.如权利要求1所述的部件，其特征在于，该部件主要包括带涂层的铸件。
3.如权利要求1所述的部件，其特征在于，该部件是以下部件之一：
燃气涡轮发动机静叶片；
燃气涡轮发动机动叶片；
燃气涡轮发动机动叶片外侧空气密封件；和
燃气涡轮发动机燃烧器部件。
4.如权利要求1所述的部件，其特征在于，该部件包括镍基超级合金铸件。
5.如权利要求1所述的部件，其特征在于，该部件是涡轮发动机翼型元件，其中所述第一通道是前缘冷却送气腔。
6.如权利要求5所述的部件，其特征在于，设有翼展方向的至少五个所述柱的阵列。
7.一种制造冷却的部件的方法，包括：
形成数个供给通道；
形成与所述供给通道中的至少一个供给通道连通的和具有数个柱的送气腔；
形成通过该数个柱并且与至少一个所述供给通道连通的出口通道。
8.如权利要求7的方法，其特征在于，包括：
在组芯上进行铸造和然后破坏地取出该组芯，其中该组芯的第一部分基本上形成所述供给通道和该组芯的第二部分形成围绕所述柱的送气腔的至少一部分。
9.如权利要求7的方法，其特征在于，所述形成出口通道包括通过所述柱进行钻孔。
10.如权利要求7的方法，其特征在于，所述形成送气腔包括采用具有限定所述柱的孔口的耐高温金属基的芯进行铸造。
11.如权利要求10所述的方法，其特征在于，所述形成出口通道包括通过所述柱进行钻孔。
12.如权利要求10所述的方法，其特征在于，所述形成出口通道包括采用具有通过所述孔口延伸的齿尖的第二耐高温金属芯进行所述铸造。
13.如权利要求7的方法，其特征在于，该方法用于铸造涡轮发动机翼型元件，其中送气腔的形成使该送气腔定位为前缘送气腔。
14.一种燃气涡轮发动机翼型元件，包括：
翼型，其具有：
第一末端和第二末端；
前缘和后缘；
压力侧和吸入侧；和
内部冷却通道系统，该系统包括具有数个第一出口的前缘送气腔，
其中：
设有至少一个在前缘送气腔上延伸的柱；和
通过所述至少一个柱延伸到至少一个第二出口的至少一个出口通道。
15.如权利要求14所述的元件，其特征在于，该元件是叶片，其中所述第一末端和第二末端分别位于内围带板段处和外围带板段处。
16.如权利要求14所述的元件，其特征在于，设有数个所述柱，每个柱具有相关联的所述出口通道。
17.一种用于冷却铸造部件表面的方法，包括：
使第一冷却流通过所述铸造部件中的腔室，所述第一冷却流围绕所述腔室内的一个或多个柱流动并且从一个或多个第一出口流出；和
使第二冷却流通过所述一个或多个柱以便从一个或多个第二出口流出和沿着所述铸造部件的表面提供薄膜冷却。
18.如权利要求17所述的方法，其特征在于，使第一冷却流和第二冷却流从单一通道中通过。
19.如权利要求17所述的方法，其特征在于，使第一冷却流和第二冷却流从单一通道中通过，该通道是涡轮发动机动叶片或静叶片的冲击通道或供给通道中之一。
20.如权利要求17所述的方法，其特征在于，所述腔室是沿着翼型的前缘部分的送气腔；和设有通过所述第二冷却流的数个所述柱。
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