CN106958467B - 使用内部气室的被冷却的包容箱体 - Google Patents

使用内部气室的被冷却的包容箱体 Download PDF

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CN106958467B
CN106958467B CN201710020862.4A CN201710020862A CN106958467B CN 106958467 B CN106958467 B CN 106958467B CN 201710020862 A CN201710020862 A CN 201710020862A CN 106958467 B CN106958467 B CN 106958467B
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G.勒菲弗尔
R.辛诺特
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Pratt and Whitney Canada 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • 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
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • 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
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/35—Combustors or associated equipment
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

本发明涉及使用内部气室的被冷却的包容箱体。一种用于涡轮区段的箱体组件具有结构性外箱体，所述结构性外箱体在结构上连接到燃气发生器和排气箱体，所述燃气发生器在所述外箱体上游，所述排气箱体在所述外箱体下游。所述组件还包括包容环部，所述包容环部安装在所述外箱体内并且围绕轴向间隔开的多个涡轮级。所述包容环部的内表面限定了多个围带接收部分。环形气室被限定在所述外箱体和所述包容环部之间。所述气室具有进口和出口，所述进口连接到加压冷却剂的源，所述出口周向地且轴向地分布并且被限定成穿过所述包容环部。所述出口在所述环形气室和所述轴向间隔开的多个涡轮级之间提供了流动连通。

Description

使用内部气室的被冷却的包容箱体
相关申请的交叉引用
本申请要求2016年1月12日提交的美国临时专利申请No.62/277,622的优先权，该临时专利申请的全部内容通过引用被合并到本文中。
技术领域
本申请一般地涉及燃气涡轮发动机，并且更具体地，涉及用于涡轮区段的包容箱体的冷却布置。
背景技术
通常，使用多个外部管道分别将冷却剂引到燃气涡轮发动机的每个涡轮级。每个涡轮级一般由恰当数量的、周向间隔开的外部管道来供给。这种多个外部管道围绕发动机壳体的布置不仅增加了部件数，而且提高了冷却空气发生泄漏的风险。而且，在发动机运转期间，涡轮区段暴露于高温，因为没有在外侧对围绕涡轮机叶片的包容箱体进行冷却，所以必须使该箱体更厚以便承受所述高温。这导致额外的重量。
发明内容
在一方面中，提供了一种用于燃气涡轮发动机的涡轮区段的箱体组件，所述箱体组件包括：结构性外箱体，所述结构性外箱体被构造成在结构上连接到燃气发生器箱体并且在结构上连接到排气箱体；包容环部，所述包容环部安装在所述结构性外箱体内并且被构造成围绕轴向间隔开的多个涡轮级，所述包容环部的内表面限定了多个围带接收部分；环形气室，所述环形气室被限定在所述结构性外箱体和所述包容环部之间，所述环形气室具有进口和出口，所述进口能够连接到加压冷却剂的源，所述出口周向地且轴向地分布并且被限定成穿过所述包容环部，所述出口在所述环形气室和所述轴向间隔开的多个涡轮级之间提供了流动连通。
在另一方面中，提供了一种燃气涡轮发动机的机箱组件，所述机箱组件相对于燃气流动方向沿上游到下游的顺序包括燃气发生器箱体、结构性外箱体以及排气箱体，所述结构性外箱体在结构上连接到所述燃气发生器箱体并且在结构上连接到所述排气箱体，所述排气箱体支撑轴承，所述轴承支撑发动机轴，所述组件还包括包容环部，所述包容环部同轴地设置在所述外箱体内并且围绕轴向间隔开的多个涡轮级，所述外箱体和所述包容环部在它们之间限定了环形气室，所述环形气室具有进口和出口，所述进口被构造成用于接收加压冷却空气，所述出口周向地且轴向地分布在所述包容环部上，所述出口在所述轴向间隔开的涡轮级和所述环形气室之间提供了流体流动连通。
在又一方面中，提供了一种用于降低箱体组件上的热致应力的方法，所述箱体组件围绕燃气涡轮发动机的多个涡轮级，所述方法包括：在所述箱体组件内限定环形气室，所述箱体组件包括外箱体，所述外箱体在结构上连接到燃气发生器箱体并且在结构上连接到排气箱体，所述环形气室被限定在所述外箱体和包容环部之间；允许所述包容环部相对于所述外箱体且相对于所述多个涡轮级发生径向和轴向热膨胀；将所述多个涡轮级与加压冷却剂的源流体地连接，所述加压冷却剂循环通过所述环形气室。
附图说明
现在参考附图，在附图中：
图1是燃气涡轮发动机的截面图，该燃气涡轮发动机具有涡轮区段，该涡轮区段包括使用内部气室的被冷却的包容箱体；
图2是图1所示的燃气涡轮发动机的下游部分的放大截面图，并且示出了包容箱体，该包容箱体安装在燃气发生器箱体和排气箱体之间；
图3是图1所示的燃气涡轮发动机的下游部分的动力涡轮区段的放大截面图，并且示出了包容箱体的冷却布置；
图4是图3的截面图的上游部分的放大图。
具体实施方式
图1示出了涡轮轴类型的燃气涡轮发动机10的示意图，其适于驱动可转动负载，例如直升机主旋翼。发动机10包括输出轴12、压缩机区段14、燃烧器16以及涡轮区段18，压缩机区段14用于对空气进行加压，经压缩的空气在燃烧器16中与燃料混合并且被点燃从而产生热燃烧气体的环状流，涡轮区段10用于从该燃烧气体提取能量。
参照图1和2，可以理解的是，压缩机区段14包括低压（LP）压缩机14a和高压（HP）压缩机14b（在所示出的示例中为叶轮），低压（LP）压缩机14a包括给定数量的级（在所示出的示例中为3级）。涡轮区段18包括HP涡轮20B、压缩机涡轮20A和动力涡轮22。在示例性实施例中，动力涡轮22包括3级。
HP涡轮20B经由HP轴21B传动性地连接到HP压缩机14B。HP涡轮20B、HP压缩机14B以及HP轴21B形成HP转轴（spool），该HP转轴能够绕发动机轴线29转动。
压缩机涡轮20A经由压缩机驱动轴21A传动性地连接到LP压缩机14A。LP压缩机14A、压缩机涡轮20A以及压缩机驱动轴21A形成第二转轴，该第二转轴能够独立于HP转轴绕轴线29转动。
动力涡轮22传动性地连接到动力涡轮轴21C，动力涡轮轴21C进而经由减速齿轮箱（RGB）23传动性地连接到输出轴12（图1）。动力涡轮轴21C在压缩机驱动轴21A和HP轴21B内同心地延伸，并且动力涡轮轴21C能够相对于压缩机驱动轴21A和HP轴21B独立地转动。
如图3最佳地示出，每个动力涡轮级S1、S2、S3包括定子和转子，该定子和转子分别包括一组周向间隔开的翼叶（vane）V1、V2、V3和一组周向间隔开的叶片（blade）B1、B2、B3。可理解地，在不偏离本公开的范围的情况下，动力涡轮22可以包括多于或少于三级。
动力涡轮级S1、S2和S3被包容箱体100围绕，包容箱体100安装在燃气发生器箱体104和排气箱体102之间，排气箱体102相对于穿过发动机的燃气流从包容箱体100向下游伸出。包容箱体100包括结构性外箱体108，结构性外箱体108具有在其轴向相对端部处的安装凸缘108A和108B。结构性外箱体108的下游端部处的凸缘108A在结构上连接到排气箱体102的对应安装凸缘102E。结构性外箱体108的上游端部处的凸缘108B在结构上连接到燃气发生器箱体104的下游端部处的对应凸缘104A。在一个实施例中，凸缘108A和108B借助于螺栓120分别附接到排气箱体102和燃气发生器箱体104的对应凸缘。可以使用其他适合的方式来替代该螺栓。外箱体108在燃气发生器箱体104和排气箱体102之间形成负载通道。在运转中，外箱体108支撑轴向和径向负载。
如图2所示，排气箱体102包括内轴承支撑部102A，内轴承支撑部102A由多个径向延伸的结构性支杆102b在结构上连接到外环部102C。内轴承支撑部102A支撑轴承101，轴承101进而向动力涡轮轴21C的下游端部提供支撑。在运转中，负载从轴21C传递到轴承支撑部102A并且经过支杆102b传递到外环部102C。这些负载随后被传递到外环部102c所安装到的外箱体108。所述负载包括径向和轴向负载。外箱体108必须能够承受那些负载。结构性外箱体108被构造为负载通道以便在燃气发生器箱体104和排气箱体102之间传递负载。
包容箱体100还包括包容环部110，包容环部110同轴地安装在结构性外箱体108内。包容环部110被构造成围绕动力涡轮22的轴向间隔开的多个涡轮级S1、S2和S3。包容环部110适于容纳失效叶片或叶片碎片，以使得万一涡轮的转动部件发生脱落，则将避免该脱落的转动部件穿过发动机机箱。
在一个实施例中，包容环部110包括两个区段，即上游区段110A和下游区段110B，以便获得紧凑并且低重量的结构。然而，要理解的是包容环部110 可以具有单体构造。
同时参照图3和4，包容环部110的径向内表面限定了多个围带接收部分110C。围带接收部分110C可以例如采取钩状体的形式以便与对应的钩状体相接合，该对应的钩状体从翼叶V1、V2和V3的径向外围带114伸出。围带接收部分110C还可以用于关于动力涡轮叶片B1、B2和B3的尖端来定位叶片围带115。在一个实施例中，叶片围带115包括可磨耗表面115A以便使叶片B1、B2和B3的尖端泄漏最小化。叶片围带可以被设置成上游翼叶的围带的轴向延伸部，如在图3中关于第三动力涡轮级S3所例示的。
包容箱体100还限定了在结构性外箱体108和包容环部110之间的环形气室（plenum）112。环形气室112具有进口112A，进口112A被限定成在凸缘108B的径向内侧以便接收来自歧管109的空气，歧管109被限定在燃气发生器箱体104中并且连接到管道44。在一个实施例中，从气室提供冷却剂，该气室被供给有经HP 14b压缩的空气。替代地，可以从低压压缩机14A的级中的一个获取经压缩的空气。经加压的空气可以经由管道44输送到环形气室112。相比动力涡轮22的燃气通道中的压力，将来自压缩机的排出空气选择为处于更高的压力以便提供围绕整个动力涡轮燃气通道的密封。
包容环部110还限定了出口110D，该出口110D以孔的形式周向地且轴向地分布并且被限定为穿过包容环部110。对该孔的样式进行选择以便获得沿着包容环部的长度跨过涡轮级S1、S2、S3的期望流量分布。出口110D在环形气室112和轴向间隔开的多个涡轮级S1、S2、S3之间提供了流动连通。更具体地，出口110D使空气沿着轴向间隔开的多个腔室C1、C2、C3和C4分布，该多个腔室C1、C2、C3和C4被限定在包容环部110和围带114之间，围带114被构造成用于支撑带围带的翼叶V1、V2和V3。在另一实施例中，可以使出口110D定向成朝围带114、115的某些关键部分提供冲击冷却。
在一个实施例中，可以在结构性外箱体108的周向外表面的周围提供隔热层106。该隔热层用于确保使动力涡轮区段周围的表面温度保持在适航规章所允许的最大外机箱温度之下。
在使用中，经由进口112A将压缩机排出空气引导进入气室112，压缩机排出空气随着其轴向地绕包容环部110流动使该包容环部110冷却。在每个涡轮级S1、S2、S3处根据沿包容环部110设置的孔110D所限定的预定比率从气室112排放压缩机排出空气的一部分。随后，压缩机排出空气用于使腔室C1、C2、C3和C4冷却并且使腔室C1、C2、C3和C4加压以便避免在其中发生热燃气回吞（即密封腔室以防燃气通道泄漏）。
在图4所示的一个实施例中，保持环116阻止了包容环部110的上游区段110A从外箱体108的轴向撤回，保持环116可拆装地安装在周向槽中，该周向槽限定在外箱体108的内表面中。部件110A上的定位肩部117a被构造成轴向地邻接抵靠对应的定位肩部117b从而相对于外箱体108轴向地定位上游区段110A。而且，爪槽布置被设置在包容环部110和外箱体108之间，以便相对于外箱体周向地且轴向地定位包容环部而同时允许在包容环部和外箱体之间发生相对的热生长。爪槽布置可以包括凸块108C，凸块108C从结构性外箱体108径向向内伸出以便与槽110F接合，槽110F被限定在上游区段110A的径向外表面中。槽110F和凸块108C周向地分布。包容环部的上游部件110A可以从所插入的外箱体108的下游端部轴向插入，并且转动从而以类似卡销的方式将凸块108C锁定在槽110F中。如图4所示，上游区段110A的上游端部还可以包括径向向内朝向的槽111以便与从翼叶V1径向向外延伸的凸块113接合。
包容环部110的下游区段110B可以被经由螺栓连接到外箱体108或者以其他适合的方式在结构上连接到外箱体108。在所示出的实施例中，下游区段110B具有径向向外延伸的凸缘110C，凸缘110C夹在外箱体凸缘108A和排气箱体102的凸缘102E之间。
弹簧加载的密封构件118（例如W形密封件）被使用在包容环部110的上游和下游区段110A、110B之间，并且被使用在包容环部110和燃气发生器箱体104之间。密封构件118允许包容环部110的径向和轴向热致膨胀，而同时限制燃气通道和气室112之间的冷却剂泄漏。
通过利用包容环部110和外箱体108之间的、经加压的冷却空气的环带来如此地冷却包容环部110和外箱体108，可以将包容环部110和外箱体108制造得更薄，这可以导致显著地节省重量。而且，上述冷却方式有助于改善叶片尖端间隙，因为包容环部110更少地发生热生长。此外，当包容环部110被用于支撑并且径向地定位翼叶V1、V2、V3以及围带114和115时，上述冷却方式改善了燃气通道，这还是因为包容环部110并且从而围带114和115更少地发生热生长。上述冷却方式还导致了更少的部件，因为不再需要不同的外部管道组来将冷却空气引到每个涡轮级。气室112使空气沿着包容环部108的整个轴向长度更均匀地分布。
还公开了一种用于降低围绕燃气涡轮发动机的多个涡轮级S1、S2、S3的箱体组件100上的热致应力的方法。该方法包括：在箱体组件100内限定环形气室112。箱体组件100包括外箱体108，外箱体108在结构上连接到燃气发生器箱体104并且在结构上连接到排气箱体102。环形气室112被限定在外箱体108和包容环部110之间，包容环部110围绕所述涡轮级。
该方法还包括允许包容环部110相对于外箱体108且相对于多个涡轮级S1、S2、S3发生径向和轴向热膨胀。这可以使用凸块108C来实现，该凸块108C从结构性外箱体108向内突出并且被构造成接合限定在包容环部110中的槽110F。也可以使用保持构件（例如弹性挡圈116）将包容环部110轴向地保持在外箱体108内。
另外，该方法包括将多个涡轮级S1、S2、S3与加压冷却剂的源流体地连接，该加压冷却剂循环通过环形气室112。在一个实施例中，冷却剂是从低压压缩机14A提取的经加压的空气。因此，该方法还可以包括使压缩机排出空气并且将该排出的空气输送通过管道44。
上面的描述仅意图是示例性的，并且本领域的技术人员将意识到在不偏离本发明所公开的范围的情况下可以对所描述的实施例作出改变。此外，根据对本公开的回顾，本领域的技术人员将明白落入本发明的范围内的其他修改，并且此类修改意图落入所附权利要求内。

Claims (17)

1.一种用于燃气涡轮发动机的涡轮区段的箱体组件，包括：
结构性外箱体，所述结构性外箱体被构造成在结构上连接到燃气发生器箱体并且在结构上连接到排气箱体；
包容环部，所述包容环部安装在所述结构性外箱体内并且被构造成围绕轴向间隔开的多个涡轮级，所述轴向间隔开的多个涡轮级中的至少两个各自具有转子和定子，所述包容环部的内表面限定了多个围带接收部分；
环形气室，所述环形气室被限定在所述结构性外箱体和所述包容环部之间，所述环形气室具有进口和出口，所述进口能够连接到加压冷却剂的源，所述环形气室与所述涡轮区段的所述轴向间隔开的多个涡轮级中的至少两个的定子和转子二者重叠，以允许所述加压冷却剂从一个涡轮级经过所述包容环部的外表面流动到下一个涡轮级，所述出口周向地且轴向地分布并且被限定成穿过所述包容环部，所述出口在所述环形气室和所述轴向间隔开的多个涡轮级之间提供了流动连通。
2.如权利要求1所述的箱体组件，其中，所述包容环部包括上游区段和下游区段，所述上游和下游区段分别安装到所述结构性外箱体。
3.如权利要求2所述的箱体组件，其中，所述上游区段和下游区段在它们之间限定了轴向间隙。
4.如权利要求3所述的箱体组件，其中，密封件被设置在所述轴向间隙内。
5.如权利要求1所述的箱体组件，其中，所述加压冷却剂是从低压压缩机提取的空气。
6.如权利要求1所述的箱体组件，其中，所述包容环部的外表面限定了周向分离的槽，所述周向分离的槽被周向分离的凸块接合，所述周向分离的凸块从所述结构性外箱体向内突出。
7.如权利要求1所述的箱体组件，还包括隔热层，所述隔热层被周向地设置在所述结构性外箱体周围。
8.一种燃气涡轮发动机的箱体组件，所述箱体组件相对于燃气流动方向沿上游到下游的顺序包括燃气发生器箱体、结构性外箱体以及排气箱体，所述结构性外箱体在结构上连接到所述燃气发生器箱体并且在结构上连接到所述排气箱体，所述排气箱体支撑轴承，所述轴承支撑发动机轴，所述箱体组件还包括包容环部，所述包容环部同轴地设置在所述结构性外箱体内并且围绕轴向间隔开的多个涡轮级，所述轴向间隔开的多个涡轮级中的至少两个各自具有转子和定子，所述结构性外箱体和所述包容环部在它们之间限定了环形气室，所述环形气室具有进口和出口，所述进口被构造成用于接收加压冷却剂，所述出口周向地且轴向地分布在所述包容环部上，所述轴向间隔开的多个涡轮级中的至少两个的定子和转子二者被所述环形气室围绕，所述出口在所述轴向间隔开的涡轮级和所述环形气室之间提供了流体流动连通。
9.如权利要求8所述的箱体组件，其中，所述包容环部包括上游区段和下游区段，所述上游区段和下游区段在它们之间限定了轴向间隙，并且其中，密封件被设置在所述轴向间隙内。
10.如权利要求8所述的箱体组件，其中，所述加压冷却剂是从所述燃气涡轮发动机的压缩机区段提取的空气。
11.如权利要求8所述的箱体组件，其中，所述包容环部的外表面限定了周向分离的槽，所述周向分离的槽被周向分离的凸块接合，所述周向分离的凸块从所述结构性外箱体向内突出。
12.如权利要求8所述的箱体组件，还包括隔热层，所述隔热层被周向地设置在所述结构性外箱体周围。
13.一种用于降低箱体组件上的热致应力的方法，所述箱体组件围绕燃气涡轮发动机的多个涡轮级，所述多个涡轮级中的至少两个各自具有转子和定子，所述方法包括：
在所述箱体组件内限定环形气室，所述环形气室在所述多个涡轮级中的至少两个的转子和定子二者周围延伸，所述箱体组件包括外箱体，所述外箱体在结构上连接到燃气发生器箱体并且在结构上连接到排气箱体，所述环形气室被限定在所述外箱体和包容环部之间；
允许所述包容环部相对于所述外箱体且相对于所述多个涡轮级发生径向和轴向热膨胀；并且
将所述多个涡轮级与加压冷却剂的源流体地连接，所述加压冷却剂循环通过所述环形气室。
14.如权利要求13所述的方法，其中，所述加压冷却剂的源是所述燃气涡轮发动机的低压压缩机，所述方法还包括使所述低压压缩机排出气体的步骤。
15.如权利要求13所述的方法，还包括采用隔热层围绕所述外箱体。
16.如权利要求13所述的方法，还包括在所述包容环部的尾区段和前区段之间设置柔性密封构件。
17.如权利要求13所述的方法，还包括使用柔性密封构件将所述包容环部的上游端部与所述燃气发生器箱体密封地接合。
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US10975721B2 (en) 2021-04-13
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