CN103987941A - 基础齿轮系统结构 - Google Patents

基础齿轮系统结构 Download PDF

Info

Publication number
CN103987941A
CN103987941A CN201380002920.0A CN201380002920A CN103987941A CN 103987941 A CN103987941 A CN 103987941A CN 201380002920 A CN201380002920 A CN 201380002920A CN 103987941 A CN103987941 A CN 103987941A
Authority
CN
China
Prior art keywords
gear
gear train
fans drive
lubrication system
fan
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN201380002920.0A
Other languages
English (en)
Other versions
CN103987941B (zh
Inventor
W.G.谢里丹
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=49487663&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=CN103987941(A) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to CN201710217558.9A priority Critical patent/CN106968802B/zh
Publication of CN103987941A publication Critical patent/CN103987941A/zh
Application granted granted Critical
Publication of CN103987941B publication Critical patent/CN103987941B/zh
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/36Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18Lubricating arrangements
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/06Arrangements of bearings; Lubricating
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K3/00Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02Plants 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
    • F02K3/04Plants 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
    • F02K3/06Plants 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/40Transmission of power
    • F05D2260/403Transmission of power through the shape of the drive components
    • F05D2260/4031Transmission of power through the shape of the drive components as in toothed gearing
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft

Abstract

用于燃气涡轮发动机的风扇驱动齿轮系统包括在风扇驱动涡轮机和风扇之间提供减速的齿轮系统和弹性地支撑该齿轮系统的多个部分的座。支撑该风扇驱动齿轮系统的润滑系统提供润滑剂到齿轮系统并移除由该齿轮系统产生的热能。润滑系统包括移除等于少于输入到齿轮系统的动力的约2%的热能的能力。

Description

基础齿轮系统结构
 相关申请的交叉引用
本申请要求2012年5月31日提交的美国临时申请61/653,731的优先权。
背景技术
燃气涡轮发动机通常包括风扇部分、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。压缩机部分通常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。
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。减速设备,例如周转齿轮组件,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,从而增加该发动机的整体推进效率。齿轮组件传输动力时的效率是齿轮驱动风扇的开发中的一个应考虑因素。未通过齿轮箱传输的动力或能量通常导致了热的生成,该热由润滑系统移除。生成的热越多,润滑系统就越大和越重。
虽然齿轮传动结构能提供改善的推进效率,但其它的因素,包括热移除和润滑在内,可能减损该改善的推进效率。因此,涡轮发动机制造商一直寻找对发动机性能的进一步改善,其中包括对热、传输和推进效率的改善。
发明内容
根据本公开的示例性实施例的用于燃气涡轮发动机的风扇驱动齿轮系统,除了其它可能的东西以外,还包括在风扇驱动涡轮机和风扇之间提供减速的齿轮系统,弹性地支撑该齿轮系统的部分的座,和提供润滑剂到该齿轮系统并移除由该齿轮系统产生的热能的润滑系统,其中该润滑系统包括移除等于小于该齿轮系统的动力输入的约2%的热能的能力。
在前述风扇驱动齿轮系统的另一个实施例中,其中该齿轮系统以大于约98%的效率将动力输入从风扇驱动涡轮机传输到风扇。
在前述风扇驱动齿轮系统的任一个的另一实施例中,其中润滑系统包括移除等于小于该齿轮系统的动力输入的约1%的热能的能力。
在前述风扇驱动齿轮系统中任一个的另一实施例中,其中润滑系统包括提供润滑剂流给齿轮系统的主润滑系统和响应于来自主润滑系统的润滑剂流的中断而提供润滑剂给齿轮系统的备用润滑系统。
在前述风扇驱动齿轮系统中任一个的另一实施例中,其中所述座包括载荷限制器,其限制了齿轮系统的响应于失衡条件的移动。
在前述风扇驱动齿轮系统中任一个的另一实施例中,其中齿轮系统包括由风扇驱动涡轮机驱动的太阳齿轮,不能转动的齿轮架,被支撑在该齿轮架上的且由太阳齿轮驱动的多个星齿轮和围绕所述多个星齿轮的齿圈。
在前述风扇驱动齿轮系统中任一个的另一实施例中,其中所述座包括在由风扇驱动涡轮机驱动的输入轴和太阳齿轮之间的第一弹性联接,在固定结构和齿轮架之间的第二弹性联接。
在前述风扇驱动齿轮系统中任一个的另一实施例中,其中齿轮系统包括由风扇驱动涡轮机驱动的太阳齿轮,能转动的齿轮架,被支撑在该齿轮架上的且由太阳齿轮驱动的多个行星齿轮和围绕所述多个行星齿轮的齿圈。
在前述风扇驱动齿轮系统中任一个的另一实施例中,其中所述座包括在由风扇驱动涡轮机驱动的输入轴和太阳齿轮之间的第一弹性联接,和在固定结构和齿圈之间的第二弹性联接。    
根据本公开的示例性实施例的燃气涡轮发动机,除了其它可能的东西以外,还包括:包括能绕着轴线旋转的多个风扇叶片的风扇、压缩机部分、与该压缩机部分流体连通的燃烧器、与该燃烧器连通的风扇驱动涡轮机、在该风扇驱动涡轮机和风扇之间提供减速的齿轮系统,该齿轮系统以大于约98%的效率将动力输入从风扇驱动涡轮机传输到该风扇、弹性地支撑该齿轮系统的部分的座、以及提供润滑剂到该齿轮系统并从该齿轮系统移除由该齿轮系统产生的热能的润滑系统。
在前述燃气涡轮发动机的另一实施例中,其中润滑系统包括移除等于小于该齿轮系统的动力输入的约2%的热能的能力。
在前述燃气涡轮发动机中任一个的另一实施例中,其中润滑系统包括移除等于小于该齿轮系统的动力输入的约1%的热能的能力。
在前述燃气涡轮发动机中任一个的另一实施例中,其中润滑系统包括提供润滑剂流给齿轮系统的主润滑系统和响应于来自主润滑系统的润滑剂流的中断而提供润滑剂给齿轮系统的备用润滑系统。
在前述燃气涡轮发动机中任一项的另一实施例中,其中齿轮系统包括由风扇驱动涡轮机驱动的太阳齿轮、不能旋转的齿轮架、支撑在该齿轮架上且由太阳齿轮驱动的多个星齿轮和围绕该多个星齿轮的齿圈,并且所述座包括在由风扇驱动涡轮机驱动的输入轴和太阳齿轮之间的第一弹性联接和在固定结构和齿轮架之间的第二弹性联接。
在前述燃气涡轮发动机中任一项的另一实施例中,其中齿轮系统包括由风扇驱动涡轮机驱动的太阳齿轮、能旋转的齿轮架、支撑在该齿轮架上且由太阳齿轮驱动的多个行星齿轮和围绕该多个行星齿轮的齿圈,并且所述座包括在由风扇驱动涡轮机驱动的输入轴和太阳齿轮之间的第一弹性联接和在固定结构和齿圈之间的第二弹性联接。
在前述燃气涡轮发动机中任一个的另一实施例中,其中所述座包括载荷限制器,其限制了齿轮系统的响应于失衡条件的移动。
在前述燃气涡轮发动机中任一项的另一实施例中,其中齿轮系统包括具有大于约2.3的齿轮比的齿轮减速装置。
在前述燃气涡轮发动机中任一项的另一实施例中,其中所述风扇传递一部分空气进入函道管道,并且函道比被定义为被传递进入函道管道内的空气部分除以被传递到压缩机部分内的空气量,该函道比大于约6.0。
在前述燃气涡轮发动机中任一项的另一实施例中,其中跨过风扇的风扇压力比小于约1.5。
在前述燃气涡轮发动机中任一项的另一实施例中,其中所述风扇具有26个或更少的叶片。
虽然不同的示例具有图示中示出的具体的部件,但是本发明的实施例不限于这些特定的组合。可以将来自其中一个示例的一些部件或特征与来自另一个示例的特征或部件组合使用。
可从下面的说明和附图最佳地理解本文公开的这些和其它特征,附图是简要描述。
附图说明
图1是示例燃气涡轮发动机的示意图。
图2是包括星形周转齿轮传动结构的示例风扇驱动齿轮系统的示意图。
图3是包括行星周转齿轮传动结构的示例风扇驱动齿轮系统的示意图。
具体实施方式
图1示意地说明了示例性的燃气涡轮发动机20,其包括风扇部分22、压缩机部分24、燃烧器部分26和涡轮机部分28。另外的发动机可除了其它的系统和特征外还包括增强器部分(未示出)。风扇部分22沿着函道流动路径B驱动空气而压缩机部分24沿着核心流动路径C吸入空气,在那里空气被压缩并传输到燃烧器部分26。在燃烧器部分26中,空气与燃料混合并被点燃以产生高压废气气体流,该废气气体流膨胀通过涡轮机部分28,在那里能量被提取并被用于驱动风扇部分22和压缩机部分24。
尽管所公开的非限定性实施例描述了涡轮风扇燃气涡轮发动机,但应该理解,本文描述的概念不限于与涡轮风扇发动机一起使用,因为这些教导可被应用到其它类型的涡轮发动机;例如,包括三轴结构的涡轮发动机,其中三个轴绕着公共轴线同心地旋转并且其中低轴使低压涡轮机通过齿轮箱驱动风扇,中间轴使中等压力涡轮机能驱动压缩机部分的第一压缩机,而高轴使高压涡轮机能驱动压缩机部分的高压压缩机。
示例发动机20通常包括低速轴30和高速轴32,它们安装成用于通过若干轴承系统38相对于发动机静止结构36绕发动机中心纵向轴线A旋转。应当理解的是,可替换地或附加地在各种位置提供各种轴承系统38。
低速轴30通常包括连接风扇42和低压(或第一)压缩机部分44到低压(或第一)涡轮机部分46的内轴杆40。内轴杆40通过变速设备驱动风扇42,例如齿轮传动结构48,从而以比低速轴30低的速度驱动风扇42。高速轴32包括将高压(或第二)压缩机部分52和高压(或第二)涡轮机部分54互连的外轴杆50。内轴杆40和外轴杆50是同心的且通过轴承系统38绕发动机中心纵向轴线A旋转。
燃烧器56被布置在高压压缩机52和高压涡轮机54之间。在一个示例中,高压涡轮机54包括至少两个级,从而提供双级高压涡轮机54。在另一个实施例中,高压涡轮机54仅包括单个级。在本文所用时,“高压”压缩机或涡轮机经历比对应的“低压”压缩机或涡轮机更高的压力。
示例低压涡轮机46具有大于约5的压力比。该示例低压涡轮机46的压力比是在低压涡轮机46的进口之前相对于在废气喷嘴之前的低压涡轮机46的出口处测量的压力测量的。
发动机静止结构36的涡轮机中间的框架58被大致布置在高压涡轮机54和低压涡轮机46之间。涡轮机中间的框架58还支撑在涡轮机部分28内的轴承系统38以及设置进入低压涡轮机46的空气流。
核心空气流C由低压压缩机44压缩接着由高压压缩机52压缩,在燃烧器56内与燃料混合并被点燃以产生高速废气气体,该废气气体接着被膨胀通过高压涡轮机54和低压涡轮机46。涡轮机中间的框架58包括定子叶片60,其在核心空气流路径内并且起到低压涡轮机46的进口引导定子叶片的作用。将涡轮机中间的框架58的定子叶片60利用为低压涡轮机46的进口引导定子叶片减少了低压涡轮机46的长度,而不增加涡轮机中间的框架58的轴向长度。减少或消除在低压涡轮机46内的定子叶片的数量缩短了涡轮机部分28的轴向长度。因此,燃气涡轮发动机20的紧凑性得到提高并且可实现了更高的动力密度。
在一个示例中公开的燃气涡轮发动机20是高函道齿轮传动飞行器发动机。在另一个示例中,燃气涡轮发动机20包括大于约六(6)的函道比,在一个示例实施例中大于约十(10)。示例齿轮传动结构48是周转齿轮系,例如行星齿轮系统,星形齿轮系统和其它已知的齿轮系统,带有大于约2.3的齿轮减速比。
在一个公开的实施例中,燃气涡轮发动机20包括了大于约十(10:1)的函道比并且风扇直径显著大于低压压缩机44的外直径。不过,应该理解,上面的参数在包括齿轮传动结构的燃气涡轮发动机的一个实施例中仅是示例性的并且本公开可应用于其它的燃气涡轮发动机。
显著量的推力由因高函道比产生的函道流B提供。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英尺以约0.8马赫巡航。0.8马赫和35000英尺的飞行条件,由于发动机处于其最佳的燃料消耗—也称为“桶巡航推力比燃料消耗(TSFC)”,是处于最小点的每小时燃烧的燃料磅质量(lbm)除以发动机产生的推力的磅力(lbf)的行业标准参数。
“低风扇压力比”是仅跨过风扇叶片的压力比,不包括风扇出口导流叶片(FEGV)系统。本文公开的根据一个非限制性实施例的低风扇压力比是小于约1.50。在另一个非限定性实施例中,低风扇压力比小于约1.45。
“低修正风扇尖端速度”是以ft/sec为单位的实际风扇尖端速度除以行业标准温度修正                                                。本文公开的根据一个非限制性实施例的“低修正风扇尖端速度”是小于约1150ft/秒。
示例燃气涡轮发动机包括风扇42,该风扇42在一个非限定性实施例包括少于约26个的风扇叶片。在另一个非限定性实施例中,风扇部分22包括少于约20个的风扇叶片。另外,在一个公开的实施例中,低压涡轮机46包括不多于约6个的涡轮机转子,其被示意地标记为34。在另一个非限定性实施例中,低压涡轮机46包括约3个涡轮机转子。在风扇叶片42的数量和低压涡轮机转子的数量之间的比在约3.3和约8.6之间。示例低压涡轮机46提供驱动动力以旋转风扇部分22并因此在低压涡轮机46中的涡轮机转子34的数量和在风扇部分22中的叶片42的数量的关系公开了具有提高的动力传输效率的示例燃气涡轮发动机20。
示例燃气涡轮发动机包括润滑系统98。润滑系统98提供润滑剂流给燃气涡轮发动机的旋转部件,包括轴承系统38和齿轮传动结构48。润滑系统98还用于实现移除在各种不同的轴承系统和齿轮传动结构48中的热。
示例润滑系统98包括在燃气涡轮发动机的正常运行条件下提供润滑的主系统80。还包括备用系统82以补充主润滑系统80的操作。润滑系统90的大小和重量与其从齿轮传动结构48移除热的能量直接相关。对热移除的要求越高,润滑系统98就变得越大和越重。由齿轮传动结构48产生的热的量因此是在风扇驱动齿轮系统的构造中重要的应考虑因素。
参照图2并继续参照图1,示例齿轮传动结构48是风扇驱动齿轮系统70的一部分。示例齿轮传动结构48包括齿轮部件65,该齿轮部件65包括由风扇驱动涡轮机46驱动的太阳齿轮62。在这个示例中,风扇驱动涡轮机是低压涡轮机46。太阳齿轮62进而驱动通过轴颈轴承安装在齿轮架74上的中间齿轮64。齿轮架74被固定到静止发动机结构36并且因此中间齿轮64不围绕太阳齿轮62作圆圈运动。中间齿轮64与联接到风扇轴杆68的齿圈66互相啮合并驱动齿圈66以驱动风扇42。
齿轮组件65被弹性地安装使得其可被与可能干扰齿轮62、64和66之间的对齐的振动的且瞬间的运动隔离开。在这个示例中,弹性座76支撑齿轮架74并且吸收了在齿轮组件65和发动机静止结构36之间的相对运动。该示例弹性座76包括适应在风扇驱动齿轮系统70的正常操作期间发生的偏转的弹簧率。
通过风扇驱动涡轮机46的内轴杆40的动力输入被通过弹性联接72传输。弹性联接72还包括弹簧率,其允许定义量的偏转和错位以使得齿轮组件65的部件不被驱动得不对齐。
尽管一些相对运动由弹性联接72和弹性座76补偿,但是超过期望限制的运动可有害地影响在齿轮之间的啮合接合并且因此提供了载荷限制设备78作为齿轮箱安装结构的一部分。载荷限制设备78约束了齿轮箱65的运动。限制器78还提供了对齿轮箱65上的失衡载荷作出反应的止挡。因此,限制器阻止了径向失衡载荷和/或扭曲过载荷损害燃气涡轮发动机20。
示例风扇驱动齿轮系统70由润滑系统98支撑。润滑系统98可实现齿轮62、64和66以及支撑这些齿轮的旋转的轴承的润滑和冷却。期望尽可能快地循环润滑剂以维持期望的温度。升高的温度为有害地影响通过齿轮箱65的动力传输效率。
在这个示例中,润滑系统98包括通过由线88示意说明的多个导管提供进出齿轮箱65的期望的润滑剂流的主系统80。主油系统80还传输热,由箭头92示意地表示,远离齿轮箱65以维持期望的温度。
  润滑系统98还包括备用油系统82,其响应于来自主油系统80的润滑剂流的暂时中断而提供油流给齿轮箱65。
示例齿轮箱65以及整个齿轮传动结构48的效率是相对于向风扇轴杆68的由箭头96示意指示的动力输出的通过轴杆40的由箭头94示意地指示的动力输入的函数。与动力输出96的量相比的动力输入94是对齿轮箱效率的体现。示例齿轮箱65以大于约98%的效率运行。在另一公开的示例中,示例齿轮箱65以高于约99%的效率运行。
所公开的效率是被具体传输到风扇轴杆68以旋转风扇42的动力94的量的体现。未通过齿轮箱65传输的动力以热被损失并且减少了风扇驱动齿轮系统70的整体效率。在输入动力94和输出动力96之间的任何差导致了热的产生。因此,在这个示例中,在输入动力94和输出动力96之间的在1-2%之间的差产生热。换句话说,在输入动力94的1%和2%之间被转换成热能,这个热能必须由润滑系统98容纳以维持工作润滑剂温度在操作极限内。
示例润滑系统98可实现等于或小于来自低压涡轮机46的输入动力94的约2%的热能的移除。在示例风扇驱动齿轮系统70的另一非限定性实施例中,齿轮箱65的效率大于约99%使得来自低压涡轮机46的动力输入的仅1%被转换为必须由润滑系统98处理的热能。
如应意识到的,处理和移除热能的能力越大,润滑系统98就越大且越重。在这个示例中,主油系统包括容纳在齿轮箱65内生成的热92的换热器90。换热器90是润滑系统98的一个元件的示例,其是与移除热能的期望能力成比例的。如意识到的,其它元件,例如润滑剂泵、导管尺寸以及润滑系统98内的整体润滑剂量,也将在大小和重量方面有所增加以提供增强的冷却能力。因此,期望增加动力传输效率以减少所要求的润滑系统98的整体热转移能力。
 在这个示例中,示例齿轮箱65的高效率能实现相对小且轻的润滑系统98。示例润滑系统98包括了能够容纳由不多于输入动力94的约2%生成的热能的特征。换句话说,润滑系统98具有的整体最大能力能移除等于不超过由低压涡轮机46提供的输入动力的约2%的热能。
移除热能的能力的量越大就导致了润滑系统98的大小和重量方面的整体增加。要求移除多于输入动力94的约2%的润滑系统需要更大的润滑系统98,而该润滑系统98可能有害地影响整体发动机效率并减损由风扇速度的减少所提供的推进效率。
参照图3并继续参照图1,公开了另一示例周转齿轮箱85,该齿轮箱包括行星构造。在行星构造中,行星齿轮84被支撑在齿轮架86上,该齿轮架可绕发动机轴线A旋转。太阳齿轮62保持由内轴杆40和低压涡轮机46驱动。齿圈66被安装到固定结构36使得其不绕该轴线旋转。因此,太阳齿轮62的旋转在齿圈66内驱动行星齿轮84。行星齿轮84被支撑在可旋转的齿轮架86上,齿轮架进而驱动风扇轴杆68。在这个构造中,风扇轴杆68和太阳齿轮62沿共同方向旋转,而行星齿轮84各自沿与太阳齿轮62相反的方向旋转但是全都绕着太阳齿轮62沿与太阳齿轮62的旋转相同的方向旋转。
在图3中示出的示例行星齿轮箱包括齿圈66,该齿圈由弹性座76支撑。弹性座76允许齿轮箱85的一些移动以维持在齿轮62、84、66的啮合齿之间的期望对齐。限制器78阻止行星齿轮箱85的超过期望极限的移动以防止由径向失衡和/或扭曲载荷引起的潜在的损害。
示例低压涡轮机46输入动力94以驱动齿轮箱85。如在前面的示例中一样,示例齿轮箱85传输多于输入动力94的约98%作为输出动力96到风扇驱动轴杆68。在另一示例中,齿轮箱85传输多于输入动力94的约99%作为输出动力96到风扇驱动轴杆68。
在输入动力94和输出动力96之间的差被转换为热能,该热能由润滑系统98移除。在这个示例中,润滑系统98具有移除不多于由来自低压涡轮机46的输入动力94的约2%产生的热92的能力。在另一示例中。润滑系统98具有移除由不多于输入动力94的约1%生成的热92的能力。因此,由示例齿轮箱85提供的效率使润滑系统98的尺寸能够不减损由以单独的且更接近最优速度转动风扇部分22和低压涡轮机46所实现的推进效率。
因此,示例风扇驱动齿轮系统可通过限制以热能形式的损失,并由此使得能够利用更低能力和大小的润滑系统来实现推进效率的改善和实现。
虽然已经公开的示例实施例,但是本领域技术人员将认识到某些改进也在本公开的范围内。由此,应当研读下面的权利要求以确定本公开的范围和内容。

Claims (20)

1.一种用于燃气涡轮发动机的风扇驱动齿轮系统,包括:
       齿轮系统,其提供了在风扇驱动涡轮机和风扇之间的减速;
       座,其弹性地支撑该齿轮系统的多个部分;以及
       润滑系统,其提供润滑剂到该齿轮系统并且移除由该齿轮系统产生的热能,其中润滑系统包括用于移除等于少于输入到该齿轮系统的动力的约2%的热能的能力。
2.如权利要求1中所述的风扇驱动齿轮系统,其中该齿轮系统将来自风扇驱动涡轮机的动力输入以高于约98%的效率传输到风扇。
3.如权利要求1中所述的风扇驱动齿轮系统,其中润滑系统包括用于移除等于少于输入到齿轮系统的动力的约1%的热能的能力。
4.如权利要求1中所述的风扇驱动齿轮系统,其中润滑系统包括提供润滑剂流给齿轮系统的主润滑系统和响应于来自主润滑系统的润滑剂流的中断而提供润滑剂给齿轮系统的备用润滑系统。
5.如权利要求1中所述的风扇驱动齿轮系统,其中所述座包括载荷限制器,用于限制该齿轮系统的响应于失衡条件的移动。
6.如权利要求1中所述的风扇驱动齿轮系统,其中齿轮系统包括由风扇驱动涡轮机驱动的太阳齿轮,不能转动的齿轮架,被支撑在该齿轮架上的且由太阳齿轮驱动的多个星齿轮和围绕所述多个星齿轮的齿圈。
7.如权利要求6中所述的风扇驱动齿轮系统,其中所述座包括在由风扇驱动涡轮机驱动的输入轴和太阳齿轮之间的第一弹性联接,和在固定结构和齿轮架之间的第二弹性联接。
8.如权利要求1中所述的风扇驱动齿轮系统,其中齿轮系统包括由风扇驱动涡轮机驱动的太阳齿轮,能转动的齿轮架,被支撑在该齿轮架上的且由太阳齿轮驱动的多个行星齿轮和围绕所述多个行星齿轮的齿圈。
9.如权利要求8中所述的风扇驱动齿轮系统,其中所述座包括在由风扇驱动涡轮机驱动的输入轴和太阳齿轮之间的第一弹性联接,和在固定结构和齿圈之间的第二弹性联接。
10.一种燃气涡轮发动机,其包括:
能绕轴线旋转的包括多个风扇叶片的风扇;
压缩机部分;
与压缩机部分流体连通的燃烧器;
与该燃烧器连通的风扇驱动涡轮机;
       齿轮系统,其提供在风扇驱动涡轮机和风扇之间的减速,该齿轮系统将来自风扇驱动涡轮机的动力输入以大于约98%的效率传输到该风扇;     
       座,其弹性地支撑该齿轮系统的多个部分;以及
润滑系统,其提供润滑剂到齿轮系统并从该齿轮系统移除由该齿轮系统产生的热能。
11.如权利要求10中所述的燃气涡轮发动机,其中润滑系统包括用于移除等于少于输入到齿轮系统的动力的约2%的热能的能力。
12.如权利要求10中所述的燃气涡轮发动机,其中润滑系统包括用于移除等于少于输入到齿轮系统的动力的约1%的热能的能力。
13.如权利要求10中所述的燃气涡轮发动机,其中润滑系统包括提供润滑剂流给齿轮系统的主润滑系统和响应于来自主润滑系统的润滑剂流的中断而提供润滑剂给齿轮系统的备用润滑系统。
14.如权利要求10中所述的燃气涡轮发动机,其中齿轮系统包括由风扇驱动涡轮机驱动的太阳齿轮、不能旋转的齿轮架、支撑在该齿轮架上且由太阳齿轮驱动的多个星齿轮和围绕该多个星齿轮的齿圈,并且所述座包括在由风扇驱动涡轮机驱动的输入轴和太阳齿轮之间的第一弹性联接和在固定结构和齿轮架之间的第二弹性联接。
15.如权利要求10中所述的燃气涡轮发动机,其中齿轮系统包括由风扇驱动涡轮机驱动的太阳齿轮、能旋转的齿轮架、支撑在该齿轮架上且由太阳齿轮驱动的多个行星齿轮和围绕该多个行星齿轮的齿圈,并且所述座包括在由风扇驱动涡轮机驱动的输入轴和太阳齿轮之间的第一弹性联接和在固定结构和齿圈之间的第二弹性联接。
16.如权利要求10中所述的燃气涡轮发动机,其中所述座包括载荷限制器,用于限制该齿轮系统的响应于失衡条件的移动。
17.如权利要求10中所述的燃气涡轮发动机,其中该齿轮系统包括具有大于约2.3的齿轮比的齿轮减速装置。
18.如权利要求10中所述的燃气涡轮发动机,其中所述风扇传递一部分空气进入函道管道,并且函道比被定义为被传递进入函道管道内的空气部分除以被传递到压缩机部分内的空气量,该函道比大于约6.0。
19.如权利要求10中所述的燃气涡轮发动机,其中跨过风扇的风扇压力比小于约1.5。
20.如权利要求10中所述的燃气涡轮发动机,其中所述风扇具有26个或更少的叶片。
CN201380002920.0A 2012-05-31 2013-05-20 一种用于燃气涡轮发动机的风扇驱动齿轮系统及燃气涡轮发动机 Active CN103987941B (zh)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710217558.9A CN106968802B (zh) 2012-05-31 2013-05-20 燃气涡轮发动机及其风扇驱动齿轮系统

Applications Claiming Priority (7)

Application Number Priority Date Filing Date Title
US201261653731P 2012-05-31 2012-05-31
US61/653,731 2012-05-31
US61/653731 2012-05-31
US13/557,614 US8572943B1 (en) 2012-05-31 2012-07-25 Fundamental gear system architecture
US13/557614 2012-07-25
US13/557,614 2012-07-25
PCT/US2013/041761 WO2014028085A2 (en) 2012-05-31 2013-05-20 Fundamental gear system architecture

Related Child Applications (1)

Application Number Title Priority Date Filing Date
CN201710217558.9A Division CN106968802B (zh) 2012-05-31 2013-05-20 燃气涡轮发动机及其风扇驱动齿轮系统

Publications (2)

Publication Number Publication Date
CN103987941A true CN103987941A (zh) 2014-08-13
CN103987941B CN103987941B (zh) 2017-05-03

Family

ID=49487663

Family Applications (2)

Application Number Title Priority Date Filing Date
CN201380002920.0A Active CN103987941B (zh) 2012-05-31 2013-05-20 一种用于燃气涡轮发动机的风扇驱动齿轮系统及燃气涡轮发动机
CN201710217558.9A Active CN106968802B (zh) 2012-05-31 2013-05-20 燃气涡轮发动机及其风扇驱动齿轮系统

Family Applications After (1)

Application Number Title Priority Date Filing Date
CN201710217558.9A Active CN106968802B (zh) 2012-05-31 2013-05-20 燃气涡轮发动机及其风扇驱动齿轮系统

Country Status (8)

Country Link
US (5) US8572943B1 (zh)
EP (1) EP2751410A4 (zh)
JP (1) JP5711431B2 (zh)
CN (2) CN103987941B (zh)
BR (1) BR112014007754B1 (zh)
CA (1) CA2852141C (zh)
RU (2) RU2608511C2 (zh)
WO (1) WO2014028085A2 (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108138658A (zh) * 2015-10-05 2018-06-08 赛峰飞机发动机公司 具有风扇和在动力涡轮轴上的减速装置的涡轮发动机

Families Citing this family (58)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10287914B2 (en) 2012-01-31 2019-05-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US8572943B1 (en) * 2012-05-31 2013-11-05 United Technologies Corporation Fundamental gear system architecture
US20150308351A1 (en) * 2012-05-31 2015-10-29 United Technologies Corporation Fundamental gear system architecture
WO2014151356A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Geared architecture turbofan engine thermal management system and method
SG10201403358XA (en) * 2013-09-24 2015-04-29 United Technologies Corp Fundamental gear system architecture
WO2015094607A1 (en) 2013-12-20 2015-06-25 United Technologies Corporation Geared turbofan with improved gear system maintainability
PL3097291T3 (pl) 2014-01-20 2021-07-19 United Technologies Corporation Silnik turbospalinowy z przekładnią redukcyjną ze zmniejszoną wielkością zbiornika oleju
US10458330B2 (en) 2014-01-20 2019-10-29 United Technologies Corporation Auxiliary oil system for geared gas turbine engine
US10196926B2 (en) 2014-04-11 2019-02-05 United Technologies Corporation Lubricating a rotating component during forward and/or reverse rotation
FR3020658B1 (fr) * 2014-04-30 2020-05-15 Safran Aircraft Engines Capot de recuperation d'huile de lubrification pour un equipement de turbomachine
US9869190B2 (en) 2014-05-30 2018-01-16 General Electric Company Variable-pitch rotor with remote counterweights
US10072510B2 (en) 2014-11-21 2018-09-11 General Electric Company Variable pitch fan for gas turbine engine and method of assembling the same
EP3109416A1 (en) * 2015-06-22 2016-12-28 United Technologies Corporation Fundamental gear system architecture
US10119465B2 (en) 2015-06-23 2018-11-06 United Technologies Corporation Geared turbofan with independent flexible ring gears and oil collectors
US10578017B2 (en) 2015-06-23 2020-03-03 United Technologies Corporation Windmill and negative-G oil system for geared turbofan engines
FR3039132B1 (fr) * 2015-07-20 2017-08-11 Airbus Operations Sas Ensemble moteur a helice a axe horizontal pour aeronef
US10495004B2 (en) 2015-09-17 2019-12-03 General Electric Company Multi-directional gearbox deflection limiter for a gas turbine engine
US10100653B2 (en) 2015-10-08 2018-10-16 General Electric Company Variable pitch fan blade retention system
US10281025B2 (en) 2015-10-19 2019-05-07 United Technologies Corporation Fixed support and oil collector system for ring gear
US10590854B2 (en) * 2016-01-26 2020-03-17 United Technologies Corporation Geared gas turbine engine
IT201600071644A1 (it) * 2016-07-08 2018-01-08 Nuovo Pignone Tecnologie Srl Trasmissione a velocita' variabile con azionatore ausiliario e sistema che la utilizza
US20180171815A1 (en) * 2016-12-16 2018-06-21 United Technologies Corporation Traction drive transmission for gas turbine engine accessory gearbox
US10669948B2 (en) 2017-01-03 2020-06-02 Raytheon Technologies Corporation Geared turbofan with non-epicyclic gear reduction system
EP3354882B1 (en) 2017-01-30 2021-03-17 GE Avio S.r.l. Method and system of connecting a turbine engine gearbox to engine core
EP3354847B1 (en) 2017-01-30 2023-03-08 GE Avio S.r.l. Flexible coupling shaft for turbine engine
FR3071547B1 (fr) * 2017-09-27 2019-09-13 Safran Aircraft Engines Ensemble d'un support palier et des paliers d'un arbre de rotor dans une turbomachine
GB201807265D0 (en) * 2018-05-03 2018-06-20 Rolls Royce Plc Oil tank system
US11236672B2 (en) * 2018-06-14 2022-02-01 Raytheon Technologies Corporation Oil thermal management system for cold weather operations of a gas turbine engine
FR3082553B1 (fr) * 2018-06-18 2020-09-25 Safran Aircraft Engines Ensemble pour turbomachine d'aeronef comportant un systeme ameliore de lubrification d'un reducteur d'entrainement de soufflante en cas d'autorotation de la soufflante
EP3587774A1 (en) * 2018-06-27 2020-01-01 Rolls-Royce plc Gas turbine
US11578667B2 (en) 2018-08-30 2023-02-14 Rolls-Royce Corporation Efficiency-based machine control
US11041444B2 (en) * 2018-11-02 2021-06-22 Pratt & Whitney Canada Corp. Gas turbine engine with differential gearbox
US20200158213A1 (en) * 2018-11-21 2020-05-21 United Technologies Corporation Hybrid electric propulsion with superposition gearbox
FR3088968B1 (fr) * 2018-11-27 2021-12-03 Safran Aircraft Engines Agencement de turboréacteur double flux à réducteur épicycloïdal ou planétaire
US10634233B1 (en) 2018-11-29 2020-04-28 Rolls-Royce Corporation Efficiency based gearbox cooling control
US11168617B2 (en) * 2019-01-30 2021-11-09 Raytheon Technologies Corporation Electric enhanced transmission for multi-spool load-sharing turbofan engine
CN110286699B (zh) * 2019-05-28 2020-12-15 东南大学 一种无线传感网数据采集中基于实际模型的无人机最优速度调度方法
US11162575B2 (en) 2019-11-20 2021-11-02 Raytheon Technologies Corporation Geared architecture for gas turbine engine
IT202000000652A1 (it) * 2020-01-15 2021-07-15 Ge Avio Srl Turbomacchina e gruppo ingranaggi
US11242770B2 (en) 2020-04-02 2022-02-08 General Electric Company Turbine center frame and method
GB202005022D0 (en) 2020-04-06 2020-05-20 Rolls Royce Plc Gearboxes for aircraft gas turbine engines
GB202005028D0 (en) * 2020-04-06 2020-05-20 Rolls Royce Plc Gearboxes for aircraft gas turbine engines
GB202005033D0 (en) 2020-04-06 2020-05-20 Rolls Royce Plc Gearboxes for aircraft gas turbine engines
GB202005025D0 (en) 2020-04-06 2020-05-20 Rolls Royce Plc Gearboxes for aircraft gas turbine engines
US11674440B2 (en) * 2021-02-09 2023-06-13 Raytheon Technologies Corporation Geared gas turbine engine with combined spray bar and scavenge component
US11359576B1 (en) 2021-04-02 2022-06-14 Ice Thermal Harvesting, Llc Systems and methods utilizing gas temperature as a power source
US11486370B2 (en) 2021-04-02 2022-11-01 Ice Thermal Harvesting, Llc Modular mobile heat generation unit for generation of geothermal power in organic Rankine cycle operations
US11421663B1 (en) 2021-04-02 2022-08-23 Ice Thermal Harvesting, Llc Systems and methods for generation of electrical power in an organic Rankine cycle operation
US11644015B2 (en) 2021-04-02 2023-05-09 Ice Thermal Harvesting, Llc Systems and methods for generation of electrical power at a drilling rig
US11480074B1 (en) 2021-04-02 2022-10-25 Ice Thermal Harvesting, Llc Systems and methods utilizing gas temperature as a power source
US11493029B2 (en) 2021-04-02 2022-11-08 Ice Thermal Harvesting, Llc Systems and methods for generation of electrical power at a drilling rig
US11592009B2 (en) 2021-04-02 2023-02-28 Ice Thermal Harvesting, Llc Systems and methods for generation of electrical power at a drilling rig
US11293414B1 (en) 2021-04-02 2022-04-05 Ice Thermal Harvesting, Llc Systems and methods for generation of electrical power in an organic rankine cycle operation
US11255315B1 (en) 2021-04-02 2022-02-22 Ice Thermal Harvesting, Llc Controller for controlling generation of geothermal power in an organic Rankine cycle operation during hydrocarbon production
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system
US11655768B2 (en) * 2021-07-26 2023-05-23 General Electric Company High fan up speed engine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2826255A (en) * 1951-06-14 1958-03-11 Gen Motors Corp Propeller drives
US5433674A (en) * 1994-04-12 1995-07-18 United Technologies Corporation Coupling system for a planetary gear train
US6223616B1 (en) * 1999-12-22 2001-05-01 United Technologies Corporation Star gear system with lubrication circuit and lubrication method therefor
US20050257528A1 (en) * 2004-05-19 2005-11-24 Dunbar Donal S Jr Retractable afterburner for jet engine
US20100236216A1 (en) * 2006-10-12 2010-09-23 Michael Winter Turbofan engine with variable area fan nozzle and low spool generator for emergency power generation and method for providing emergency power
US20100296947A1 (en) * 2009-05-22 2010-11-25 United Technologies Corporation Apparatus and method for providing damper liquid in a gas turbine

Family Cites Families (297)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3111005A (en) 1963-11-19 Jet propulsion plant
US2258792A (en) 1941-04-12 1941-10-14 Westinghouse Electric & Mfg Co Turbine blading
US2426792A (en) 1943-10-29 1947-09-02 Du Pont Process for preparing a mercury oxide catalyst
US2608821A (en) 1949-10-08 1952-09-02 Gen Electric Contrarotating turbojet engine having independent bearing supports for each turbocompressor
US3021731A (en) 1951-11-10 1962-02-20 Wilhelm G Stoeckicht Planetary gear transmission
US2748623A (en) 1952-02-05 1956-06-05 Boeing Co Orbit gear controlled reversible planetary transmissions
US2936655A (en) 1955-11-04 1960-05-17 Gen Motors Corp Self-aligning planetary gearing
US3033002A (en) 1957-11-08 1962-05-08 Fairfield Shipbuilding And Eng Marine propulsion steam turbine installations
US3185857A (en) 1960-02-01 1965-05-25 Lear Siegler Inc Control apparatus for the parallel operation of alternators
US3194487A (en) 1963-06-04 1965-07-13 United Aircraft Corp Noise abatement method and apparatus
US3363419A (en) 1965-04-27 1968-01-16 Rolls Royce Gas turbine ducted fan engine
US3287906A (en) 1965-07-20 1966-11-29 Gen Motors Corp Cooled gas turbine vanes
US3352178A (en) 1965-11-15 1967-11-14 Gen Motors Corp Planetary gearing
US3412560A (en) 1966-08-03 1968-11-26 Gen Motors Corp Jet propulsion engine with cooled combustion chamber, fuel heater, and induced air-flow
US3390527A (en) * 1967-07-19 1968-07-02 Avco Corp High bypass ratio turbofan
GB1135129A (en) 1967-09-15 1968-11-27 Rolls Royce Gas turbine engine
US3664612A (en) 1969-12-22 1972-05-23 Boeing Co Aircraft engine variable highlight inlet
GB1350431A (en) 1971-01-08 1974-04-18 Secr Defence Gearing
GB1309721A (en) 1971-01-08 1973-03-14 Secr Defence Fan
US3892358A (en) 1971-03-17 1975-07-01 Gen Electric Nozzle seal
US3765623A (en) 1971-10-04 1973-10-16 Mc Donnell Douglas Corp Air inlet
US3747343A (en) 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
GB1418905A (en) 1972-05-09 1975-12-24 Rolls Royce Gas turbine engines
US3779345A (en) 1972-05-22 1973-12-18 Gen Electric Emergency lubrication supply system
US3861139A (en) 1973-02-12 1975-01-21 Gen Electric Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition
US3843277A (en) 1973-02-14 1974-10-22 Gen Electric Sound attenuating inlet duct
US3988889A (en) 1974-02-25 1976-11-02 General Electric Company Cowling arrangement for a turbofan engine
US3932058A (en) 1974-06-07 1976-01-13 United Technologies Corporation Control system for variable pitch fan propulsor
US3935558A (en) 1974-12-11 1976-01-27 United Technologies Corporation Surge detector for turbine engines
US4020632A (en) * 1975-07-17 1977-05-03 The United States Of America As Represented By The United States National Aeronautics And Space Administration Office Of General Counsel-Code Gp Oil cooling system for a gas turbine engine
US4130872A (en) 1975-10-10 1978-12-19 The United States Of America As Represented By The Secretary Of The Air Force Method and system of controlling a jet engine for avoiding engine surge
SE402147B (sv) 1975-12-05 1978-06-19 United Turbine Ab & Co Gasturbinanleggning med tre i samma gaspassage anordnade koaxiella turbinrotorer
GB1516041A (en) 1977-02-14 1978-06-28 Secr Defence Multistage axial flow compressor stators
US4358969A (en) * 1977-05-18 1982-11-16 Silvestri Giovanni J High pressure air turbine and gear train system
US4136286A (en) 1977-07-05 1979-01-23 Woodward Governor Company Isolated electrical power generation system with multiple isochronous, load-sharing engine-generator units
US4240250A (en) 1977-12-27 1980-12-23 The Boeing Company Noise reducing air inlet for gas turbine engines
GB2041090A (en) 1979-01-31 1980-09-03 Rolls Royce By-pass gas turbine engines
US4233555A (en) 1979-04-05 1980-11-11 Dyna Technology, Inc. Alternating current generator for providing three phase and single phase power at different respective voltages
US4284174A (en) 1979-04-18 1981-08-18 Avco Corporation Emergency oil/mist system
US4220171A (en) 1979-05-14 1980-09-02 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Curved centerline air intake for a gas turbine engine
US4405892A (en) 1979-07-19 1983-09-20 Brunswick Corporation Regulator for a generator energized battery
US4289360A (en) 1979-08-23 1981-09-15 General Electric Company Bearing damper system
DE2940446C2 (de) 1979-10-05 1982-07-08 B. Braun Melsungen Ag, 3508 Melsungen Züchtung von tierischen Zellen in Suspensions- und Monolayerkulturen in Fermentationsgefäßen
GB2080486B (en) 1980-07-15 1984-02-15 Rolls Royce Shafts
GB2130340A (en) 1981-03-28 1984-05-31 Rolls Royce Gas turbine rotor assembly
FR2506840A1 (fr) 1981-05-29 1982-12-03 Onera (Off Nat Aerospatiale) Turboreacteur a roues contra-rotatives
US4478551A (en) 1981-12-08 1984-10-23 United Technologies Corporation Turbine exhaust case design
US4423333A (en) * 1982-02-02 1983-12-27 Rossman Wendell E Horizontal axis wind energy conversion system with aerodynamic blade pitch control
US4660376A (en) 1984-04-27 1987-04-28 General Electric Company Method for operating a fluid injection gas turbine engine
US5252905A (en) 1985-12-23 1993-10-12 York International Corporation Driving system for single phase A-C induction motor
US4722357A (en) 1986-04-11 1988-02-02 United Technologies Corporation Gas turbine engine nacelle
US4696156A (en) 1986-06-03 1987-09-29 United Technologies Corporation Fuel and oil heat management system for a gas turbine engine
GB8630754D0 (en) 1986-12-23 1987-02-04 Rolls Royce Plc Turbofan gas turbine engine
DE3714990A1 (de) 1987-05-06 1988-12-01 Mtu Muenchen Gmbh Propfan-turbotriebwerk
GB2207191B (en) 1987-07-06 1992-03-04 Gen Electric Gas turbine engine
US4808076A (en) 1987-12-15 1989-02-28 United Technologies Corporation Rotor for a gas turbine engine
US4879624A (en) 1987-12-24 1989-11-07 Sundstrand Corporation Power controller
US5168208A (en) 1988-05-09 1992-12-01 Onan Corporation Microprocessor based integrated generator set controller apparatus and method
FR2644844B1 (fr) 1989-03-23 1994-05-06 Snecma Suspension du rotor de la turbine basse pression d'une turbomachine a double corps
US4979362A (en) 1989-05-17 1990-12-25 Sundstrand Corporation Aircraft engine starting and emergency power generating system
GB2234035B (en) * 1989-07-21 1993-05-12 Rolls Royce Plc A reduction gear assembly and a gas turbine engine
US5081832A (en) 1990-03-05 1992-01-21 Rolf Jan Mowill High efficiency, twin spool, radial-high pressure, gas turbine engine
US5046306A (en) * 1990-07-23 1991-09-10 General Motors Corporation Secondary oil system
US5058617A (en) 1990-07-23 1991-10-22 General Electric Company Nacelle inlet for an aircraft gas turbine engine
US5182464A (en) 1991-01-09 1993-01-26 Techmatics, Inc. High speed transfer switch
US5141400A (en) 1991-01-25 1992-08-25 General Electric Company Wide chord fan blade
US5102379A (en) 1991-03-25 1992-04-07 United Technologies Corporation Journal bearing arrangement
US5160251A (en) 1991-05-13 1992-11-03 General Electric Company Lightweight engine turbine bearing support assembly for withstanding radial and axial loads
US5317877A (en) 1992-08-03 1994-06-07 General Electric Company Intercooled turbine blade cooling air feed system
GB9306898D0 (en) 1993-04-01 1993-05-26 Ang Swee C Implantable prosthetic patellar components
US5447411A (en) 1993-06-10 1995-09-05 Martin Marietta Corporation Light weight fan blade containment system
US5466198A (en) 1993-06-11 1995-11-14 United Technologies Corporation Geared drive system for a bladed propulsor
US5361580A (en) 1993-06-18 1994-11-08 General Electric Company Gas turbine engine rotor support system
GB9313905D0 (en) 1993-07-06 1993-08-25 Rolls Royce Plc Shaft power transfer in gas turbine engines
US5307622A (en) 1993-08-02 1994-05-03 General Electric Company Counterrotating turbine support assembly
US5524847A (en) 1993-09-07 1996-06-11 United Technologies Corporation Nacelle and mounting arrangement for an aircraft engine
US5388964A (en) 1993-09-14 1995-02-14 General Electric Company Hybrid rotor blade
RU2082824C1 (ru) 1994-03-10 1997-06-27 Московский государственный авиационный институт (технический университет) Способ защиты жаропрочных материалов от воздействия агрессивных сред высокоскоростных газовых потоков (варианты)
JPH07286503A (ja) 1994-04-20 1995-10-31 Hitachi Ltd 高効率ガスタービン
US5625276A (en) 1994-09-14 1997-04-29 Coleman Powermate, Inc. Controller for permanent magnet generator
US5778659A (en) 1994-10-20 1998-07-14 United Technologies Corporation Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems
JP3489106B2 (ja) 1994-12-08 2004-01-19 株式会社サタケ ブラシレス三相同期発電機
AU1183997A (en) 1994-12-14 1997-01-15 United Technologies Corporation Compressor stall and surge control using airflow asymmetry measurement
US5729059A (en) 1995-06-07 1998-03-17 Kilroy; Donald G. Digital no-break power transfer system
KR0154049B1 (ko) * 1995-08-22 1998-10-15 전성원 차량용 자동변속기의 유압제어시스템
JP2969075B2 (ja) 1996-02-26 1999-11-02 ジャパンゴアテックス株式会社 脱気装置
US5734255A (en) 1996-03-13 1998-03-31 Alaska Power Systems Inc. Control system and circuits for distributed electrical power generating stations
US5754033A (en) 1996-03-13 1998-05-19 Alaska Power Systems Inc. Control system and circuits for distributed electrical-power generating stations
US5634767A (en) 1996-03-29 1997-06-03 General Electric Company Turbine frame having spindle mounted liner
US5806303A (en) 1996-03-29 1998-09-15 General Electric Company Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle
EP0817350B1 (en) 1996-06-24 2008-03-26 SANYO ELECTRIC Co., Ltd. Power-supply system involving system interconnection
US5857836A (en) 1996-09-10 1999-01-12 Aerodyne Research, Inc. Evaporatively cooled rotor for a gas turbine engine
US5809843A (en) * 1997-01-07 1998-09-22 Bbn Corporation Active cancellation of noise at gear mesh frequencies for a gear assembly under load
GB2322914B (en) 1997-03-05 2000-05-24 Rolls Royce Plc Ducted fan gas turbine engine
US5949153A (en) 1997-03-06 1999-09-07 Consolidated Natural Gas Service Company, Inc. Multi-engine controller
US5791789A (en) 1997-04-24 1998-08-11 United Technologies Corporation Rotor support for a turbine engine
DE19838443A1 (de) * 1997-08-26 1999-03-04 Luk Getriebe Systeme Gmbh Druckmittelanlage
US5975841A (en) 1997-10-03 1999-11-02 Thermal Corp. Heat pipe cooling for turbine stators
US6260004B1 (en) * 1997-12-31 2001-07-10 Innovation Management Group, Inc. Method and apparatus for diagnosing a pump system
FR2775734B1 (fr) * 1998-03-05 2000-04-07 Snecma Procede et dispositif d'inversion de poussee pour moteur a tres grand taux de dilution
US5985470A (en) 1998-03-16 1999-11-16 General Electric Company Thermal/environmental barrier coating system for silicon-based materials
US6209311B1 (en) 1998-04-13 2001-04-03 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
JP2002512337A (ja) 1998-04-16 2002-04-23 3カー−ヴァルナー・トゥルボズュステームズ・ゲーエムベーハー ターボチャージ付内燃機関
US6230480B1 (en) 1998-08-31 2001-05-15 Rollins, Iii William Scott High power density combined cycle power plant
US6104171A (en) 1998-11-23 2000-08-15 Caterpillar Inc. Generator set with redundant bus sensing and automatic generator on-line control
US6260351B1 (en) 1998-12-10 2001-07-17 United Technologies Corporation Controlled spring rate gearbox mount
US6196790B1 (en) * 1998-12-17 2001-03-06 United Technologies Corporation Seal assembly for an intershaft seal in a gas turbine engine
US6517341B1 (en) 1999-02-26 2003-02-11 General Electric Company Method to prevent recession loss of silica and silicon-containing materials in combustion gas environments
US6410148B1 (en) 1999-04-15 2002-06-25 General Electric Co. Silicon based substrate with environmental/ thermal barrier layer
USH2032H1 (en) 1999-10-01 2002-07-02 The United States Of America As Represented By The Secretary Of The Air Force Integrated fan-core twin spool counter-rotating turbofan gas turbine engine
US6668629B1 (en) 1999-11-26 2003-12-30 General Electric Company Methods and apparatus for web-enabled engine-generator systems
US6315815B1 (en) 1999-12-16 2001-11-13 United Technologies Corporation Membrane based fuel deoxygenator
US6318070B1 (en) 2000-03-03 2001-11-20 United Technologies Corporation Variable area nozzle for gas turbine engines driven by shape memory alloy actuators
US6444335B1 (en) 2000-04-06 2002-09-03 General Electric Company Thermal/environmental barrier coating for silicon-containing materials
US6647707B2 (en) 2000-09-05 2003-11-18 Sudarshan Paul Dev Nested core gas turbine engine
US6631310B1 (en) 2000-09-15 2003-10-07 General Electric Company Wireless engine-generator systems digital assistant
US6555929B1 (en) 2000-10-24 2003-04-29 Kohler Co. Method and apparatus for preventing excessive reaction to a load disturbance by a generator set
US6657416B2 (en) 2001-06-15 2003-12-02 Generac Power Systems, Inc. Control system for stand-by electrical generator
US6653821B2 (en) 2001-06-15 2003-11-25 Generac Power Systems, Inc. System controller and method for monitoring and controlling a plurality of generator sets
US6789522B2 (en) * 2001-07-23 2004-09-14 John Seymour Engine for aeronautical applications
JP2003097669A (ja) 2001-09-27 2003-04-03 Jatco Ltd トルクスプリット式変速比無限大無段変速機
US6669393B2 (en) 2001-10-10 2003-12-30 General Electric Co. Connector assembly for gas turbine engines
US6708482B2 (en) 2001-11-29 2004-03-23 General Electric Company Aircraft engine with inter-turbine engine frame
US6639331B2 (en) 2001-11-30 2003-10-28 Onan Corporation Parallel generator power system
US6663530B2 (en) 2001-12-14 2003-12-16 Pratt & Whitney Canada Corp. Zero twist carrier
US6735954B2 (en) 2001-12-21 2004-05-18 Pratt & Whitney Canada Corp. Offset drive for gas turbine engine
US6914763B2 (en) 2002-01-15 2005-07-05 Wellspring Heritage, Llc Utility control and autonomous disconnection of distributed generation from a power distribution system
AU2003224622A1 (en) 2002-02-25 2003-09-09 General Electric Company Configuring a centrally controlled circuit breaker protection system
US6732502B2 (en) 2002-03-01 2004-05-11 General Electric Company Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor
US6619030B1 (en) 2002-03-01 2003-09-16 General Electric Company Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors
US6966174B2 (en) 2002-04-15 2005-11-22 Paul Marius A Integrated bypass turbojet engines for air craft and other vehicles
US20030235523A1 (en) 2002-06-24 2003-12-25 Maxim Lyubovsky Method for methane oxidation and, apparatus for use therewith
US6607165B1 (en) 2002-06-28 2003-08-19 General Electric Company Aircraft engine mount with single thrust link
US6763653B2 (en) 2002-09-24 2004-07-20 General Electric Company Counter rotating fan aircraft gas turbine engine with aft booster
US6814541B2 (en) 2002-10-07 2004-11-09 General Electric Company Jet aircraft fan case containment design
US7021042B2 (en) 2002-12-13 2006-04-04 United Technologies Corporation Geartrain coupling for a turbofan engine
US6847297B2 (en) 2003-01-06 2005-01-25 General Electric Company Locator devices and methods for centrally controlled power distribution systems
US7600971B2 (en) * 2003-03-21 2009-10-13 Vestas Wind Systems A/S Methods of moving the rotating means of a wind turbine during transportation or stand still, method of controlling the moving of the rotating means, nacelle, auxiliary device, control and monitoring system and use hereof
US6709492B1 (en) 2003-04-04 2004-03-23 United Technologies Corporation Planar membrane deoxygenator
CN101208509A (zh) 2003-04-28 2008-06-25 马里厄斯·A·保罗 具有真实卡诺循环的涡轮火箭发动机
US7055306B2 (en) 2003-04-30 2006-06-06 Hamilton Sundstrand Corporation Combined stage single shaft turbofan engine
US6895741B2 (en) 2003-06-23 2005-05-24 Pratt & Whitney Canada Corp. Differential geared turbine engine with torque modulation capability
US7104918B2 (en) 2003-07-29 2006-09-12 Pratt & Whitney Canada Corp. Compact epicyclic gear carrier
US7019495B2 (en) 2003-08-28 2006-03-28 C.E. Neihoff & Co. Inter-regulator control of multiple electric power sources
GB0321139D0 (en) 2003-09-10 2003-10-08 Short Brothers Plc A device
US7216475B2 (en) 2003-11-21 2007-05-15 General Electric Company Aft FLADE engine
FR2866387B1 (fr) 2004-02-12 2008-03-14 Snecma Moteurs Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante
US7338259B2 (en) 2004-03-02 2008-03-04 United Technologies Corporation High modulus metallic component for high vibratory operation
GB0406174D0 (en) 2004-03-19 2004-04-21 Rolls Royce Plc Turbine engine arrangement
DE102004016246A1 (de) 2004-04-02 2005-10-20 Mtu Aero Engines Gmbh Turbine, insbesondere Niederdruckturbine, einer Gasturbine, insbesondere eines Flugtriebwerks
US7144349B2 (en) 2004-04-06 2006-12-05 Pratt & Whitney Canada Corp. Gas turbine gearbox
US7168949B2 (en) 2004-06-10 2007-01-30 Georgia Tech Research Center Stagnation point reverse flow combustor for a combustion system
US7328580B2 (en) 2004-06-23 2008-02-12 General Electric Company Chevron film cooled wall
DE102004042739A1 (de) 2004-09-03 2006-03-09 Mtu Aero Engines Gmbh Fan für ein Flugtriebwerk sowie Flugtriebwerk
US7458202B2 (en) 2004-10-29 2008-12-02 General Electric Company Lubrication system for a counter-rotating turbine engine and method of assembling same
US7334392B2 (en) 2004-10-29 2008-02-26 General Electric Company Counter-rotating gas turbine engine and method of assembling same
US7409819B2 (en) 2004-10-29 2008-08-12 General Electric Company Gas turbine engine and method of assembling same
US7269938B2 (en) 2004-10-29 2007-09-18 General Electric Company Counter-rotating gas turbine engine and method of assembling same
US7195446B2 (en) 2004-10-29 2007-03-27 General Electric Company Counter-rotating turbine engine and method of assembling same
GB0425137D0 (en) 2004-11-13 2004-12-15 Rolls Royce Plc Blade
EP1828573B1 (en) 2004-12-01 2010-06-16 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
FR2879720B1 (fr) 2004-12-17 2007-04-06 Snecma Moteurs Sa Systeme de compression-evaporation pour gaz liquefie
US7309210B2 (en) 2004-12-17 2007-12-18 United Technologies Corporation Turbine engine rotor stack
CN1332500C (zh) 2005-02-04 2007-08-15 艾纯 小型二极单相发电机
US20060177302A1 (en) 2005-02-04 2006-08-10 Berry Henry M Axial flow compressor
US7845902B2 (en) 2005-02-15 2010-12-07 Massachusetts Institute Of Technology Jet engine inlet-fan system and design method
GB0506685D0 (en) 2005-04-01 2005-05-11 Hopkins David R A design to increase and smoothly improve the throughput of fluid (air or gas) through the inlet fan (or fans) of an aero-engine system
US7476086B2 (en) 2005-04-07 2009-01-13 General Electric Company Tip cambered swept blade
US7374403B2 (en) 2005-04-07 2008-05-20 General Electric Company Low solidity turbofan
US7151332B2 (en) 2005-04-27 2006-12-19 Stephen Kundel Motor having reciprocating and rotating permanent magnets
US7500365B2 (en) 2005-05-05 2009-03-10 United Technologies Corporation Accessory gearbox
US7513102B2 (en) 2005-06-06 2009-04-07 General Electric Company Integrated counterrotating turbofan
US7594388B2 (en) 2005-06-06 2009-09-29 General Electric Company Counterrotating turbofan engine
US8220245B1 (en) 2005-08-03 2012-07-17 Candent Technologies, Inc. Multi spool gas turbine system
WO2007038673A1 (en) 2005-09-28 2007-04-05 Entrotech Composites, Llc Linerless prepregs, composite articles therefrom, and related methods
US7685808B2 (en) 2005-10-19 2010-03-30 General Electric Company Gas turbine engine assembly and methods of assembling same
US7513103B2 (en) 2005-10-19 2009-04-07 General Electric Company Gas turbine engine assembly and methods of assembling same
US7493753B2 (en) 2005-10-19 2009-02-24 General Electric Company Gas turbine engine assembly and methods of assembling same
JP4910375B2 (ja) 2005-11-22 2012-04-04 日本精工株式会社 無段変速装置
DE102006001984A1 (de) 2006-01-16 2007-07-19 Robert Bosch Gmbh Verfahren und Vorrichtung zur Bereitstellung einer Versorgungsspannung mittels parallel geschalteter Generatoreinheiten
US7591754B2 (en) 2006-03-22 2009-09-22 United Technologies Corporation Epicyclic gear train integral sun gear coupling design
US7610763B2 (en) 2006-05-09 2009-11-03 United Technologies Corporation Tailorable design configuration topologies for aircraft engine mid-turbine frames
BE1017135A3 (nl) 2006-05-11 2008-03-04 Hansen Transmissions Int Een tandwielkast voor een windturbine.
US7600370B2 (en) 2006-05-25 2009-10-13 Siemens Energy, Inc. Fluid flow distributor apparatus for gas turbine engine mid-frame section
US20080003096A1 (en) 2006-06-29 2008-01-03 United Technologies Corporation High coverage cooling hole shape
JP4911344B2 (ja) 2006-07-04 2012-04-04 株式会社Ihi ターボファンエンジン
US8585538B2 (en) 2006-07-05 2013-11-19 United Technologies Corporation Coupling system for a star gear train in a gas turbine engine
US9194255B2 (en) 2006-07-05 2015-11-24 United Technologies Corporation Oil baffle for gas turbine fan drive gear system
US7926260B2 (en) 2006-07-05 2011-04-19 United Technologies Corporation Flexible shaft for gas turbine engine
US7704178B2 (en) 2006-07-05 2010-04-27 United Technologies Corporation Oil baffle for gas turbine fan drive gear system
US7765788B2 (en) 2006-07-06 2010-08-03 United Technologies Corporation Cooling exchanger duct
JP4551916B2 (ja) * 2006-07-12 2010-09-29 川崎重工業株式会社 トラクション変速機構付き発電・スタータ装置
US7658060B2 (en) 2006-07-19 2010-02-09 United Technologies Corporation Lubricant cooling exchanger dual intake duct
US7594405B2 (en) 2006-07-27 2009-09-29 United Technologies Corporation Catenary mid-turbine frame design
US7594404B2 (en) 2006-07-27 2009-09-29 United Technologies Corporation Embedded mount for mid-turbine frame
US7694505B2 (en) 2006-07-31 2010-04-13 General Electric Company Gas turbine engine assembly and method of assembling same
US8939864B2 (en) 2006-08-15 2015-01-27 United Technologies Corporation Gas turbine engine lubrication
EP3128164B1 (en) 2006-08-22 2019-07-10 Rolls-Royce North American Technologies, Inc. Gas turbine engine with intermediate speed booster
US7815417B2 (en) 2006-09-01 2010-10-19 United Technologies Corporation Guide vane for a gas turbine engine
US7632064B2 (en) 2006-09-01 2009-12-15 United Technologies Corporation Variable geometry guide vane for a gas turbine engine
US7816813B2 (en) 2006-09-28 2010-10-19 Asco Power Technologies, L.P. Method and apparatus for parallel engine generators
EP2066872B1 (en) 2006-10-12 2014-06-18 United Technologies Corporation Method and device to avoid turbofan instability in a gas turbine engine.
US7662059B2 (en) 2006-10-18 2010-02-16 United Technologies Corporation Lubrication of windmilling journal bearings
US7832193B2 (en) 2006-10-27 2010-11-16 General Electric Company Gas turbine engine assembly and methods of assembling same
US7841165B2 (en) 2006-10-31 2010-11-30 General Electric Company Gas turbine engine assembly and methods of assembling same
US7966806B2 (en) 2006-10-31 2011-06-28 General Electric Company Turbofan engine assembly and method of assembling same
US8205427B2 (en) 2006-11-09 2012-06-26 United Technologies Corporation Interdependent lubrication systems in a turbine engine
US7841163B2 (en) 2006-11-13 2010-11-30 Hamilton Sundstrand Corporation Turbofan emergency generator
US8215454B2 (en) 2006-11-22 2012-07-10 United Technologies Corporation Lubrication system with tolerance for reduced gravity
US8020665B2 (en) 2006-11-22 2011-09-20 United Technologies Corporation Lubrication system with extended emergency operability
US7882693B2 (en) 2006-11-29 2011-02-08 General Electric Company Turbofan engine assembly and method of assembling same
US7797946B2 (en) 2006-12-06 2010-09-21 United Technologies Corporation Double U design for mid-turbine frame struts
US20080148708A1 (en) 2006-12-20 2008-06-26 General Electric Company Turbine engine system with shafts for improved weight and vibration characteristic
US20080148881A1 (en) 2006-12-21 2008-06-26 Thomas Ory Moniz Power take-off system and gas turbine engine assembly including same
US7716914B2 (en) 2006-12-21 2010-05-18 General Electric Company Turbofan engine assembly and method of assembling same
US7791235B2 (en) 2006-12-22 2010-09-07 General Electric Company Variable magnetic coupling of rotating machinery
FR2912181B1 (fr) 2007-02-07 2009-04-24 Snecma Sa Turbine a gaz a turbines hp et bp contra-rotatives
US7721549B2 (en) 2007-02-08 2010-05-25 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system
US7942079B2 (en) 2007-02-16 2011-05-17 Hamilton Sundstrand Corporation Multi-speed gearbox for low spool driven auxiliary component
US8015828B2 (en) 2007-04-03 2011-09-13 General Electric Company Power take-off system and gas turbine engine assembly including same
US8017188B2 (en) 2007-04-17 2011-09-13 General Electric Company Methods of making articles having toughened and untoughened regions
FR2915175B1 (fr) 2007-04-20 2009-07-17 Airbus France Sa Mat d'accrochage de moteur pour aeronef disposant d'une poutre d'attache moteur arriere deportee du caisson
US7557544B2 (en) 2007-04-23 2009-07-07 Cummins Power Generation Ip, Inc. Zero crossing detection for an electric power generation system
US20080318066A1 (en) 2007-05-11 2008-12-25 Asml Holding N.V. Optical Component Fabrication Using Coated Substrates
RU2346176C1 (ru) 2007-06-04 2009-02-10 Открытое акционерное общество "Авиадвигатель" Двухконтурный газотурбинный двигатель с приводом вентилятора через простой соосный редуктор с внутренним зацеплением
RU2347928C1 (ru) 2007-06-04 2009-02-27 Открытое акционерное общество "Авиадвигатель" Редуктор привода однорядного вентилятора газотурбинного двигателя
US8262817B2 (en) 2007-06-11 2012-09-11 Honeywell International Inc. First stage dual-alloy turbine wheel
US7950237B2 (en) 2007-06-25 2011-05-31 United Technologies Corporation Managing spool bearing load using variable area flow nozzle
US8104265B2 (en) 2007-06-28 2012-01-31 United Technologies Corporation Gas turbines with multiple gas flow paths
US7882691B2 (en) 2007-07-05 2011-02-08 Hamilton Sundstrand Corporation High to low pressure spool summing gearbox for accessory power extraction and electric start
KR100876254B1 (ko) 2007-07-20 2008-12-26 삼성에스디아이 주식회사 파우치형 이차전지
RU2358375C2 (ru) 2007-07-24 2009-06-10 Государственное образовательное учреждение высшего профессионального образования Военная академия Ракетных войск стратегического назначения имени Петра Великого Электропривод на базе планетарного циклоидального редуктора с упругим зацеплением - эп пцр-у
US8347633B2 (en) 2007-07-27 2013-01-08 United Technologies Corporation Gas turbine engine with variable geometry fan exit guide vane system
US20120124964A1 (en) 2007-07-27 2012-05-24 Hasel Karl L Gas turbine engine with improved fuel efficiency
US8256707B2 (en) 2007-08-01 2012-09-04 United Technologies Corporation Engine mounting configuration for a turbofan gas turbine engine
US7942635B1 (en) 2007-08-02 2011-05-17 Florida Turbine Technologies, Inc. Twin spool rotor assembly for a small gas turbine engine
US8074440B2 (en) 2007-08-23 2011-12-13 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US9957918B2 (en) 2007-08-28 2018-05-01 United Technologies Corporation Gas turbine engine front architecture
US8973374B2 (en) 2007-09-06 2015-03-10 United Technologies Corporation Blades in a turbine section of a gas turbine engine
US8075261B2 (en) 2007-09-21 2011-12-13 United Technologies Corporation Gas turbine engine compressor case mounting arrangement
US8205432B2 (en) 2007-10-03 2012-06-26 United Technologies Corporation Epicyclic gear train for turbo fan engine
US8104289B2 (en) 2007-10-09 2012-01-31 United Technologies Corp. Systems and methods involving multiple torque paths for gas turbine engines
US7656060B2 (en) 2007-10-31 2010-02-02 Caterpillar Inc. Power system with method for adding multiple generator sets
US8015798B2 (en) 2007-12-13 2011-09-13 United Technologies Corporation Geared counter-rotating gas turbofan engine
CN101903619B (zh) 2007-12-20 2014-06-11 沃尔沃航空公司 燃气涡轮发动机
US8826641B2 (en) * 2008-01-28 2014-09-09 United Technologies Corporation Thermal management system integrated pylon
JP5419251B2 (ja) 2008-02-20 2014-02-19 富士フイルム株式会社 微粒子製造方法及び微粒子製造装置
US7762086B2 (en) 2008-03-12 2010-07-27 United Technologies Corporation Nozzle extension assembly for ground and flight testing
US20090265049A1 (en) 2008-04-22 2009-10-22 Honeywell International, Inc. Aircraft system emissions and noise estimation mechanism
GB0807775D0 (en) 2008-04-29 2008-06-04 Romax Technology Ltd Methods for model-based diagnosis of gearbox
DE102008023990A1 (de) 2008-05-16 2009-11-19 Rolls-Royce Deutschland Ltd & Co Kg Zwei-Wellen-Triebwerk für eine Fluggasturbine
US8807477B2 (en) 2008-06-02 2014-08-19 United Technologies Corporation Gas turbine engine compressor arrangement
US8128021B2 (en) * 2008-06-02 2012-03-06 United Technologies Corporation Engine mount system for a turbofan gas turbine engine
US8210800B2 (en) 2008-06-12 2012-07-03 United Technologies Corporation Integrated actuator module for gas turbine engine
US8973364B2 (en) 2008-06-26 2015-03-10 United Technologies Corporation Gas turbine engine with noise attenuating variable area fan nozzle
US20100005810A1 (en) 2008-07-11 2010-01-14 Rob Jarrell Power transmission among shafts in a turbine engine
US8266889B2 (en) 2008-08-25 2012-09-18 General Electric Company Gas turbine engine fan bleed heat exchanger system
US7997868B1 (en) 2008-11-18 2011-08-16 Florida Turbine Technologies, Inc. Film cooling hole for turbine airfoil
US8166748B2 (en) 2008-11-21 2012-05-01 General Electric Company Gas turbine engine booster having rotatable radially inwardly extending blades and non-rotatable vanes
US8061969B2 (en) 2008-11-28 2011-11-22 Pratt & Whitney Canada Corp. Mid turbine frame system for gas turbine engine
US20100132377A1 (en) 2008-11-28 2010-06-03 Pratt & Whitney Canada Corp. Fabricated itd-strut and vane ring for gas turbine engine
US8091371B2 (en) 2008-11-28 2012-01-10 Pratt & Whitney Canada Corp. Mid turbine frame for gas turbine engine
US8177488B2 (en) 2008-11-29 2012-05-15 General Electric Company Integrated service tube and impingement baffle for a gas turbine engine
US8106633B2 (en) 2008-12-18 2012-01-31 Caterpillar Inc. Generator set control system
US8191352B2 (en) 2008-12-19 2012-06-05 General Electric Company Geared differential speed counter-rotatable low pressure turbine
US7970556B2 (en) * 2009-01-30 2011-06-28 General Electric System and method for monitoring the condition of a gear assembly
US8216108B2 (en) 2009-02-05 2012-07-10 Friede & Goldman, Ltd. Gear assembly with tapered flex pin
US8307626B2 (en) 2009-02-26 2012-11-13 United Technologies Corporation Auxiliary pump system for fan drive gear system
US8181441B2 (en) 2009-02-27 2012-05-22 United Technologies Corporation Controlled fan stream flow bypass
GB0903423D0 (en) 2009-03-02 2009-04-08 Rolls Royce Plc Variable drive gas turbine engine
FR2944558B1 (fr) 2009-04-17 2014-05-02 Snecma Moteur a turbine a gaz double corps pourvu d'un palier de turbine bp supplementaire.
US8246503B2 (en) 2009-06-10 2012-08-21 United Technologies Corporation Epicyclic gear system with improved lubrication system
US8172716B2 (en) 2009-06-25 2012-05-08 United Technologies Corporation Epicyclic gear system with superfinished journal bearing
US8375695B2 (en) 2009-06-30 2013-02-19 General Electric Company Aircraft gas turbine engine counter-rotatable generator
US8176725B2 (en) 2009-09-09 2012-05-15 United Technologies Corporation Reversed-flow core for a turbofan with a fan drive gear system
US8457126B2 (en) 2009-10-14 2013-06-04 Vss Monitoring, Inc. System, method and apparatus for distributing captured data packets including tunneling identifiers
US8672801B2 (en) 2009-11-30 2014-03-18 United Technologies Corporation Mounting system for a planetary gear train in a gas turbine engine
JP5282731B2 (ja) 2009-12-22 2013-09-04 株式会社安川電機 電力変換装置
US9170616B2 (en) 2009-12-31 2015-10-27 Intel Corporation Quiet system cooling using coupled optimization between integrated micro porous absorbers and rotors
US8905713B2 (en) 2010-05-28 2014-12-09 General Electric Company Articles which include chevron film cooling holes, and related processes
US9006930B2 (en) 2010-07-08 2015-04-14 Delta Electronics Inc. Power supply having converters with serially connected inputs and parallel connected outputs
JP2013545081A (ja) * 2010-10-08 2013-12-19 ロールス−ロイス・コーポレーション 駆動列内の故障状態を、トルク振動データを用いて検出するシステムおよび方法
US8568099B2 (en) * 2010-12-17 2013-10-29 Vestas Wind Systems A/S Apparatus for harvesting energy from a gearbox to power an electrical device and related methods
US8366385B2 (en) 2011-04-15 2013-02-05 United Technologies Corporation Gas turbine engine front center body architecture
US8172717B2 (en) 2011-06-08 2012-05-08 General Electric Company Compliant carrier wall for improved gearbox load sharing
US9631558B2 (en) 2012-01-03 2017-04-25 United Technologies Corporation Geared architecture for high speed and small volume fan drive turbine
US9133729B1 (en) 2011-06-08 2015-09-15 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US8297917B1 (en) * 2011-06-08 2012-10-30 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US8508059B2 (en) * 2011-08-25 2013-08-13 Von L. Burton Thrust reaction utilization method and system
US9498823B2 (en) 2011-11-07 2016-11-22 United Technologies Corporation Metal casting apparatus, cast work piece and method therefor
BR102012027097B1 (pt) 2011-11-23 2022-01-04 United Technologies Corporation Motor de turbina a gás
US8935913B2 (en) 2012-01-31 2015-01-20 United Technologies Corporation Geared turbofan gas turbine engine architecture
US9816442B2 (en) 2012-01-31 2017-11-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section
US20130192266A1 (en) 2012-01-31 2013-08-01 United Technologies Corporation Geared turbofan gas turbine engine architecture
US8572943B1 (en) 2012-05-31 2013-11-05 United Technologies Corporation Fundamental gear system architecture
US20150308351A1 (en) 2012-05-31 2015-10-29 United Technologies Corporation Fundamental gear system architecture
US8756908B2 (en) 2012-05-31 2014-06-24 United Technologies Corporation Fundamental gear system architecture

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2826255A (en) * 1951-06-14 1958-03-11 Gen Motors Corp Propeller drives
US5433674A (en) * 1994-04-12 1995-07-18 United Technologies Corporation Coupling system for a planetary gear train
US6223616B1 (en) * 1999-12-22 2001-05-01 United Technologies Corporation Star gear system with lubrication circuit and lubrication method therefor
US20050257528A1 (en) * 2004-05-19 2005-11-24 Dunbar Donal S Jr Retractable afterburner for jet engine
US20100236216A1 (en) * 2006-10-12 2010-09-23 Michael Winter Turbofan engine with variable area fan nozzle and low spool generator for emergency power generation and method for providing emergency power
US20100296947A1 (en) * 2009-05-22 2010-11-25 United Technologies Corporation Apparatus and method for providing damper liquid in a gas turbine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108138658A (zh) * 2015-10-05 2018-06-08 赛峰飞机发动机公司 具有风扇和在动力涡轮轴上的减速装置的涡轮发动机
CN108138658B (zh) * 2015-10-05 2020-11-20 赛峰飞机发动机公司 具有风扇和在动力涡轮轴上的减速装置的涡轮发动机

Also Published As

Publication number Publication date
CN103987941B (zh) 2017-05-03
US11125167B2 (en) 2021-09-21
US8572943B1 (en) 2013-11-05
CA2852141A1 (en) 2014-02-20
CA2852141C (en) 2015-10-27
RU2608511C2 (ru) 2017-01-19
EP2751410A4 (en) 2014-11-26
WO2014028085A3 (en) 2014-05-15
US10221770B2 (en) 2019-03-05
BR112014007754B1 (pt) 2022-04-19
EP2751410A2 (en) 2014-07-09
WO2014028085A2 (en) 2014-02-20
US20180156134A1 (en) 2018-06-07
JP2014528537A (ja) 2014-10-27
US20210381442A1 (en) 2021-12-09
RU2016148904A (ru) 2018-11-02
US20190195140A1 (en) 2019-06-27
RU2014113686A (ru) 2015-10-20
US11773786B2 (en) 2023-10-03
US20140178180A1 (en) 2014-06-26
BR112014007754A2 (pt) 2017-04-04
JP5711431B2 (ja) 2015-04-30
CN106968802A (zh) 2017-07-21
CN106968802B (zh) 2018-10-23
RU2016148904A3 (zh) 2020-04-21

Similar Documents

Publication Publication Date Title
CN103987941A (zh) 基础齿轮系统结构
US9840969B2 (en) Gear system architecture for gas turbine engine
US8756908B2 (en) Fundamental gear system architecture
US8209952B2 (en) Gas turbine engine with intermediate speed booster
CN100564831C (zh) 燃气轮机装置及其装配方法
EP2855882B1 (en) Lubrication arrangement for a gas turbine engine gear assembly
EP3159576A1 (en) Double row cylindrical roller bearing with high length to diameter ratio rollers
EP2199568A2 (en) Geared differential speed counter-rotatable low pressure turbine
US11339723B2 (en) Geared turbofan high gearbox power density
EP3020953B1 (en) Gas turbine engine
JP2008111437A (ja) ガスタービンエンジン組立体
JP2014152778A (ja) ガスタービンエンジンおよびガスタービンエンジンの性能改善方法
US10669947B2 (en) Geared gas turbine engine
US11220960B2 (en) Superposition gearbox for engine performance
EP3109416A1 (en) Fundamental gear system architecture
CA2854728C (en) Fundamental gear system architecture

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant