CN104379906A - 用于设置燃气涡轮发动机的风扇驱动齿轮系统的齿轮比的方法 - Google Patents

用于设置燃气涡轮发动机的风扇驱动齿轮系统的齿轮比的方法 Download PDF

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CN104379906A
CN104379906A CN201380003371.9A CN201380003371A CN104379906A CN 104379906 A CN104379906 A CN 104379906A CN 201380003371 A CN201380003371 A CN 201380003371A CN 104379906 A CN104379906 A CN 104379906A
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fan
gear
gas turbine
turbine engine
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W.G.谢里丹
K.L.哈塞尔
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Raytheon Technologies Corp
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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
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
    • 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
    • F01D25/162—Bearing supports
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/068—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type being characterised by a short axial length relative to the diameter
    • 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
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • 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
    • F05D2240/24—Rotors for 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
    • F05D2240/50—Bearings
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Retarders (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Gears, Cams (AREA)

Abstract

根据本公开的一个示例性方面的燃气涡轮发动机，除了别的以外，包括风扇部分，该风扇部分包括可绕着轴线旋转的风扇和与该风扇连通的减速设备。减速设备包括带有至少为1.5的星形齿轮比的星形驱动齿轮系统。风扇的风扇叶片尖端速度小于1400fps。

Description

用于设置燃气涡轮发动机的风扇驱动齿轮系统的齿轮比的方法
背景技术
本公开涉及燃气涡轮发动机，并且更具体地涉及用于设置燃气涡轮发动机的风扇驱动齿轮系统的齿轮比的方法。
 燃气涡轮发动机可包括风扇部分、压缩机部分、燃烧器部分和涡轮机部分。进入压缩机部分的空气被压缩并被传递到燃烧器部分内，在那里空气与燃料混合并被点燃以产生高速废气气体流。高速废气气体流膨胀通过涡轮机部分以驱动压缩机和风扇部分。除了别的变化以外，压缩机部分可包括低压和高压压缩机，并且涡轮机部分可包括低压和高压涡轮机。
 通常，高压涡轮机通过外轴杆驱动高压压缩机以形成高轴，并且低压涡轮机通过内轴杆驱动低压压缩机以形成低轴。风扇部分也可由内轴杆驱动。直接驱动燃气涡轮发动机可包括由低轴驱动的风扇部分，使得低压压缩机、低压涡轮机、和风扇部分沿共同的方向以共同的速度旋转。
 减速设备，其可以是风扇驱动齿轮系统或其它的机构，可被用于驱动风扇部分，使得风扇部分可以不同于涡轮机部分的速度旋转。这允许发动机的推进效率的整体增加。在这种发动机架构中，由涡轮机部分中之一驱动的轴杆提供了到减速设备的输入，该减速设备以减小的速度驱动风扇部分，使得涡轮机部分和风扇部分可以更接近最优速度的速度旋转。
 尽管利用了变速机构的燃气涡轮发动机通常被认为是能够相对于传统的发动机改善推进效率，但是燃气涡轮发动机制造商继续寻求对发动机性能的进一步改善，这包括对热效率、传输效率和推进效率的改善。
发明内容
 根据本公开的一个示例性方面的燃气涡轮发动机，除了别的以外，包括风扇部分，该风扇部分包括可绕着轴线旋转的风扇和与该风扇连通的减速设备。减速设备包括带有至少为1.5的星形齿轮比的星形驱动齿轮系统。风扇的风扇叶片尖端速度小于1400fps。
 在前述燃气涡轮发动机的另一非限定性实施例中，该减速设备包括至少为2.6的星形齿轮系统齿轮比。
 在前述燃气涡轮发动机任一个的另一非限定性实施例中，减速设备包括小于或等于4.1的系统齿轮比。
 在前述燃气涡轮发动机中任一个的另一非限定性实施例中，包括大于约6.0的函道比。
在前述燃气涡轮发动机中任一个的另一非限定性实施例中，函道比在约11.0和约22.0之间。
在前述燃气涡轮发动机中任一个的另一非限定性实施例中，星形系统包括太阳齿轮、多个星形齿轮、齿圈、和齿轮架。
在前述燃气涡轮发动机中任一个的另一非限定性实施例中，多个星形齿轮中的每一个都包括至少一个轴承。
在前述燃气涡轮发动机中任一个的另一非限定性实施例中，齿轮架被固定而不能旋转。
在前述燃气涡轮发动机中任一个的另一非限定性实施例中，低压涡轮机被机械地附接到太阳齿轮。
在前述燃气涡轮发动机中任一个的另一非限定性实施例中，风扇部分被机械地附接到齿圈。
在前述燃气涡轮发动机中任一项的另一非限定性实施例中，减速设备的输入端可沿第一方向旋转，而减速设备的输出端可沿与第一方向相反的第二方向旋转。
在前述燃气涡轮发动机中任一个的另一非限定性实施例中，低压涡轮机部分与减速设备连通。该低压涡轮机部分包括至少三个级且不多于四个级。
在前述燃气涡轮发动机中任一个的另一非限定性实施例中，风扇的风扇叶片尖端速度大于1000fps。
根据本公开的另一示例性方面的改善燃气涡轮发动机的性能的方法，除了别的以外，包括确定风扇部分的至少一个风扇叶片的风扇尖端速度边界条件和确定低压涡轮机的转子的转子边界条件。应力水平利用低压涡轮机的转子和该至少一个风扇叶片中的约束来确定风扇部分和低压涡轮机的旋转速度是否会满足期望数量的运行循环。
在前述方法的另一非限定性实施例中，减速设备连接风扇部分和低压涡轮机并且包括至少为约1.5且不多于约4.1的星形齿轮比。
在前述方法中任一个的另一非限定性实施例中，风扇压力比低于1.7。
在前述方法中任一个的另一非限定性实施例中，风扇压力比低于1.48。
在前述方法中任一个的另一非限定性实施例中，函道比在约11和约22之间。
在前述方法中任一个的另一非限定性实施例中，所述至少一个风扇叶片的风扇叶片尖端速度小于1400fps。
在前述方法中任一个的另一非限定性实施例中，如果在转子或至少一个风扇叶片中的应力水平过高而不能满足期望数量的运行循环，那么齿轮减速设备的齿轮比就被降低并且增加低压涡轮机的级数。
在前述方法中任一个的另一非限定性实施例中，如果在转子或至少一个风扇叶片中的应力水平过高而不能满足期望数量的运行循环，那么齿轮减速设备的齿轮比就被降低并且增加低压涡轮机的环形面积。
本公开的各种特征和优点将通过下面具体描述使本领域技术人员易于理解。所述具体描述的附图可被简要地描述如下。
附图说明
图1是示例燃气涡轮发动机的示意横截面视图。
图2说明了可被包含在燃气涡轮发动机内的低速轴的一种构造的示意图。
图3说明了可被包含在燃气涡轮发动机内的风扇驱动齿轮系统。
具体实施方式
图1示意性地图示了燃气涡轮发动机20。燃气涡轮发动机20为两轴涡轮风扇发动机，其通常包括风扇部分22、压缩机部分24、燃烧器部分26和涡轮机部分28。其它的发动机除了其它系统或特征外还可包括增强器部分（未示出）。风扇部分22沿着函道流动路径B驱动空气，同时压缩机部分24沿着核心流动路径C驱动空气以实现压缩并传送到燃烧器部分26内。在燃烧器部分26内产生的热燃烧气体被膨胀通过涡轮机部分28。尽管在所公开的非限定实施例中被示出为两轴涡轮风扇燃气涡轮发动机，应该理解的是，本文中描述的概念不限于两轴涡轮风扇发动机，并且这些教导可延伸到其它类型的发动机，包括但不限于，三轴发动机架构。
燃气涡轮发动机20通常包括低速轴30和高速轴32，它们被安装成绕着发动机中心纵轴线A旋转。低速轴30和高速轴32可通过若干轴承系统31相对于发动机静止结构33被安装。应该理解的是，替换地或附加地可提供其它的轴承系统31，并且轴承系统31的定位可在适合应用时而变化。
低速轴30通常包括内轴杆34，其将风扇36、低压压缩机38和低压涡轮机39互连。内轴杆34可通过变速机构被连接到风扇36，该变速机构在示例性燃气涡轮发动机20中被示出为齿轮传动架构45，例如风扇驱动齿轮系统50（见图2和3）。变速机构以比低速轴30更低的速度驱动风扇36。高速轴32包括外轴杆35，其将高压压缩机37和高压涡轮机40互连。在这个实施例中，内轴杆34和外轴杆35在各种不同的轴向位置处由定位在发动机静止结构33中的轴承系统31支撑。
燃烧器42在示例性燃气涡轮机20被布置在高压压缩机37和高压涡轮机40之间。中间涡轮机框架44可被大致布置在高压涡轮机40和低压涡轮机39之间。中间涡轮机框架44可支撑涡轮机部分28的一个或多个轴承系统31。中间涡轮机框架44可包括一个或多个在核心流动路径C内延伸的翼型46。应该意识到，风扇部分22、压缩机部分24、燃烧器部分26、涡轮机部分28和风扇驱动齿轮系统50的位置中的每一个都可被改变。例如，齿轮系统50可被定位在燃烧器部分26的后面或者设置是在涡轮机部分28的后面，并且风扇部分22可被定位在齿轮系统50的位置的前面或后面。
内轴杆34和外轴杆35是同心的并且通过轴承系统31绕发动机中心纵向轴线A旋转，其与它们的纵向轴线共线。核心空气流先被低压压缩机38压缩接着被高压压缩机37压缩，与燃料混合后在燃烧器42内燃烧，接着膨胀通过高压涡轮机40和低压涡轮机39。高压涡轮机40和低压涡轮机39响应于该膨胀旋转驱动相应的高速轴32和低速轴30。
在非限定性实施例中，燃气涡轮发动机20是高旁通齿轮传动飞机发动机。在另一示例中，燃气涡轮发动机20函道比大于约六（6：1）。齿轮传动架构45可包括周转齿轮系，例如行星齿轮系统、星形齿轮系统、或其它齿轮系统。齿轮传动架构45能使低速轴30以更高的速度运行，这能增加低压压缩机38和低压涡轮机39的运行效率，并且在更少数量的级中产生增加的压力。
低压涡轮机39的压力比可以是在低压涡轮机39的进口之前测得的压力与在低压涡轮机39的出口处并在燃气涡轮发动机20的废气喷嘴之前的压力的比。在一个非限定性实施例中，燃气涡轮发动机20的函道比大于约十（10：1），风扇直径显著大于低压压缩机38的直径，并且低压涡轮机39具有大于约五（5：1）的压力比。在另一非限定性实施例中，函道比大于11且小于22，或者大于13且小于20。不过，应该理解，上面的参数对齿轮传动架构发动机或使用变速机构的其它发动机来说只是示例性的，并且本公开可应用于其它的燃气涡轮发动机，包括直接驱动涡轮风扇。在一个非限定性实施例中，低压涡轮机39包括至少一个级且不多于八个级，或者至少三个级且不多于六个级。在另一非限定性实施例中，低压涡轮机39包括至少三个级且不多于四个级。
在示例性燃气涡轮发动机20的这个实施例中，大量的推力是由旁通流动路径B提供的，这是由于高函道比。燃气涡轮发动机20的风扇部分22被设计用于特定的飞行条件——通常在约35000英尺的高度处以约0.8马赫巡航。由于燃气涡轮发动机20处于其最佳燃料消耗，这个飞行条件也被称为桶巡航针对推力的燃料消耗（TSFC）。TSFC是每单位推力的燃料消耗的行业标准参数。
风扇压力比是在没有使用风扇出口引导定子叶片系统的情况下横跨风扇部分22的叶片的压力比。根据示例燃气涡轮发动机20的一个非限定性实施例的低风扇压力比小于1.45。在示例燃气涡轮发动机20的另一个非限定性实施例中，风扇压力比小于1.38且大于1.25。在另一个非限定性实施例中，风扇压力比小于1.48。在另一个非限定性实施例中，风扇压力比小于1.52。在另一个非限定性实施例中，风扇压力比小于1.7。低修正风扇尖端速度是实际风扇尖端速度除以行业标准温度修正                                                ，其中T代表以兰金度为单位的周围温度。根据示例燃气涡轮发动机20的一个非限定性实施例的低修正风扇尖端速度小于约1150fps（351m/s)。根据示例燃气涡轮发动机20的另一个非限定性实施例的低修正风扇尖端速度小于约1400fps（427 m/s)。根据示例燃气涡轮发动机20的另一个非限定性实施例的低修正风扇尖端速度大于约1000fps（305 m/s)。
图2示意性地说明了燃气涡轮发动机20的低速轴30。低速轴30包括风扇36、低压压缩机38和低压涡轮机39。内轴杆34将风扇36、低压压缩机38和低压涡轮机39互连。内轴杆34通过风扇驱动齿轮系统50被连接到风扇36。在这个实施例中，风扇驱动齿轮系统50可实现低压涡轮机39和风扇36的反向旋转。例如，风扇36沿第一方向D1旋转，而低压涡轮机39也沿与第一方向D1相反的第二方向D2旋转。
图3说明了被包含在燃气涡轮发动机20内以能够实现风扇36和低压涡轮机39的反向旋转的风扇驱动齿轮系统50的一个示例性实施例。在这个实施例中，风扇驱动齿轮系统50包括具有太阳齿轮52、围绕太阳齿轮52设置的齿圈54、和多个星形齿轮56的星形齿轮系统，星形齿轮56具有定位在太阳齿轮52和齿圈54之间的轴颈轴承57。固定的齿轮架58承载星形齿轮56中的每一个并被附接到其上。在这个实施例中，固定的齿轮架58不旋转并且被连接到燃气涡轮发动机20的固定结构55。
太阳齿轮52从低压涡轮机39接收输入（见图2）并且沿第一方向D1旋转，由此沿着与第一方向D1相反的第二方向D2转动多个星形齿轮56。该多个星形齿轮56的运动被传输到齿圈54，齿圈54沿着与太阳齿轮52的第一方向D1相反的第二方向D2旋转。齿圈54被连接到风扇36以沿第二方向D2旋转风扇36（见图2）。
风扇驱动齿轮系统50的星形系统齿轮比通过测量齿圈54的直径并将该直径除以太阳齿轮52的直径确定。在一个实施例中，齿轮传动架构45的星形系统齿轮比是在1.5和4.1之间。在另一个实施例中，风扇驱动齿轮系统50的系统齿轮比是在2.6和4.1之间。当星形系统齿轮比低于1.5时，太阳齿轮52与星形齿轮56相比相对大得多。这种尺寸差减少了星形齿轮56能够承载的载荷，这是因为星形齿轮轴颈轴承57的尺寸的减小。当星形系统齿轮比高于4.1时，太阳齿轮52与星形齿轮56相比相对小得多。这种尺寸差增加了星形齿轮56的轴颈轴承57的尺寸，但是减少了太阳齿轮52能够承载的载荷，这是因为其齿的尺寸和数量都减小了。替换地，滚子轴承可被用来替代轴颈轴承57。
改善燃气涡轮发动机20的性能开始于通过确定风扇36的至少一个风扇叶片的风扇尖端速度边界条件以定义风扇叶片的尖端的速度。最大风扇直径是基于从平衡发动机效率、通过旁通流动路径B的空气质量、和由风扇叶片的尺寸引起的发动机重量的增加得到的预计燃料燃烧确定的。
此后确定低压涡轮机39的每一级的转子的边界条件以基于低压涡轮机39和低压压缩机38的效率定义转子尖端的速度和定义低压涡轮机39中的转子尺寸和级数。
利用关于转子和风扇叶片中的应力水平的约束来确定风扇36和低压涡轮机39的旋转速度是否将满足期望数量的运行寿命循环。如果在转子或风扇叶片内的应力水平过高，那么风扇驱动齿轮系统50的齿轮比可被降低并且可增加低压涡轮机39的级数或低压涡轮机39的环形面积。
尽管不同的非限定性实施例被示出为具有具体的部件，但是本公开的实施例不限于这些特定的组合。可以将来自非限定实施例中任一个的一些部件或特征与来自其它非限定实施例中任一个的特征或部件组合使用。
应当理解的是，在所有这些附图中相同的参见数字指示对应的或类似的元件。还应该理解的是，尽管在这些示例性实施例中公开并说明了特定的部件布置，但是其它的布置也可受益于本公开的教导。
前面的描述应该被理解为是说明性的而不是限定性的。本领域技术人员将理解某些改进也落入本公开的范围内。由于这些原因，应当研读下面的权利要求以确定本公开的真实的范围和内容。

Claims (21)

1.一种燃气涡轮发动机，其包括：
       风扇部分，其包括可绕着轴线旋转的风扇；以及
       与所述风扇连通的减速设备，其中该减速设备包括星形驱动齿轮系统，该齿轮系统带有至少为1.5的星形齿轮比，
其中风扇的风扇叶片尖端速度小于1400fps。
2.如权利要求1所述的燃气涡轮发动机，其中所述减速设备包括至少为2.6的星形齿轮系统齿轮比。
3.如权利要求2所述的燃气涡轮发动机，其中所述减速设备包括小于或等于4.1的系统齿轮比。
4.如权利要求3所述的燃气涡轮发动机，包括大于约6.0的函道比。
5.如权利要求3所述的燃气涡轮发动机，其中函道比在约11.0和约22.0之间。
6.如权利要求1所述的燃气涡轮发动机，其中所述星形系统包括太阳齿轮、多个星形齿轮、齿圈和齿轮架。
7.如权利要求6所述的燃气涡轮发动机，其中所述多个星形齿轮中的每一个都包括至少一个轴承。
8.如权利要求6所述的燃气涡轮发动机，其中所述齿轮架被固定而不能旋转。
9.如权利要求6所述的燃气涡轮发动机，其中低压涡轮机被机械地附接到太阳齿轮。
10.如权利要求6所述的燃气涡轮发动机，其中风扇部分被机械地附接到齿圈。
11.如权利要求1所述的燃气涡轮发动机，其中减速设备的输入端可沿第一方向旋转，而减速设备的输出端可沿与第一方向相反的第二方向旋转。
12.如权利要求1所述的燃气涡轮发动机，包括与所述减速设备连通的低压涡轮机部分，其中低压涡轮机部分包括至少三个级且不多于四个级。
13.如权利要求12所述的燃气涡轮发动机，其中风扇的风扇叶片尖端速度大于1000fps。
14.一种改善燃气涡轮发动机的性能的方法，包括：
确定风扇部分的至少一个风扇叶片的风扇尖端速度边界条件；
确定低压涡轮机的转子的转子边界条件；以及
在低压涡轮机的转子和所述至少一个风扇叶片中利用应力水平约束，以确定风扇部分和低压涡轮机的旋转速度是否将满足期望数量的运行循环。
15.如权利要求14所述的方法，其中减速设备连接风扇部分和低压涡轮机并且包括至少为约1.5且不多于约4.1的星形齿轮比。
16.如权利要求15所述的方法，其中风扇压力比低于1.7。
17.如权利要求15所述的方法，其中风扇压力比低于1.48。
18.如权利要求16所述的方法，其中函道比在约11和约22之间。
19.如权利要求14所述的方法，其中所述至少一个风扇叶片的风扇叶片尖端速度小于1400fps。
20.如权利要求14所述的方法，其中如果在转子或所述至少一个风扇叶片中的应力水平过高而不能满足期望数量的运行循环，那么齿轮减速设备的齿轮比就被降低并且增加低压涡轮机的级数。
21.如权利要求14所述的方法，其中如果在转子或所述至少一个风扇叶片中的应力水平过高而不能满足期望数量的运行循环，那么齿轮减速设备的齿轮比就被降低并且增加低压涡轮机的环形面积。
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