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公开(公告)号：JP2014234822A
公开(公告)日：2014-12-15
申请号：JP2014042229
申请日：2014-03-05
Applicant: ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation , United Technologies Corp
, ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation Inventor： MCCUNE MICHAEL E , JASON HUSBAND , FREDERICK M SCHWARZ , DANIEL BERNARD KUPRATIS , SUCIU GABRIEL L , WILLIAM K ACKERMANN
CPC classification number: F01D25/16 , F02C7/36 , F02K3/06 , F05D2260/40311 , Y02T50/671
Abstract: 【課題】歯車の噛合部における整列のずれを防止しつつ、エンジンの効率を向上させる。【解決手段】ガスタービンエンジン20が、ファン42を駆動するファンシャフト76と、このファンシャフト76を支持するフレーム82と、ファンシャフト76を駆動する複数の歯車とを備えている。可撓性支持部78が、複数の歯車を少なくとも部分的に支持する。第1のタービンセクション46は、第1の出口点401において第1の出口面積を有するとともに、第1の速度で回転する。第2のタービンセクション54は、第2の出口点400において第2の出口面積を有するとともに、第1の速度よりも高速の第2の速度で回転する。第1の性能量が、第1の速度の二乗と第1の出口面積との積として定義される。第2の性能量が、第2の速度の二乗と第2の出口面積との積として定義される。第2の性能量に対する第1の性能量の比は、約0.5〜約1.5である。【選択図】図1D
Abstract translation: 要解决的问题：为了防止齿轮啮合网格的错位，提高发动机效率。解决方案：燃气轮机发动机20具有驱动风扇42的风扇轴76，支撑风扇轴76的框架82和多个齿轮 驱动风扇轴76.柔性支撑件78至少部分支撑多个齿轮。 第一涡轮机部分46在第一出口点401处具有第一出口区域并以第一速度旋转。 第二涡轮部分54在第二出口点处具有第二出口区域，并以比第一速度快的第二速度旋转。 第一性能数量被定义为第一速度平方和第一出口区域的乘积。 第二性能量被定义为第二速度平方和第二出口区的乘积。 第一性能量与第二性能量的比率在约0.5至约1.5之间。
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公开(公告)号：JP2013181542A
公开(公告)日：2013-09-12
申请号：JP2013038267
申请日：2013-02-28
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , MCCUNE MICHAEL E , MAGGE SHANKAR S
CPC classification number: F02C3/107 , F01D1/26 , F02C3/067 , F02C7/36 , F02K3/072 , F05D2250/44 , F05D2260/40311 , Y02T50/671
Abstract: PROBLEM TO BE SOLVED: To shorten the low shaft of an engine while increasing the output density of the engine.SOLUTION: A gas turbine engine 20 includes a low shaft 40, a counter-rotating low-pressure compressor 60, and a counter-rotating low-pressure turbine 62. The counter-rotating low-pressure turbine 62 includes inside blade sets 120 which are connected to the low shaft 40 via a gear device 116, and an outside blade set 122 which is inserted between the inside blade sets 120. The outside blade set 122 is fixed to an outside rotor 126; a front end of the outside rotor 126 is supported on a central turbine frame 134 by a bearing 150; and a rear end of the outside rotor 126 is supported on the low shaft 40 by the bearing 152. In addition, the gear device 116 comprises a sun gear 140, a splitter gear 142 which is meshed with the sun gear 140, and a ring gear 148 which is meshed with the splitter gear 142.
Abstract translation: 要解决的问题：在增加发动机的输出密度的同时缩短发动机的低轴。解决方案：燃气涡轮发动机20包括低轴40，反向旋转低压压缩机60和反向旋转 低压涡轮机62.反向旋转的低压涡轮机62包括通过齿轮装置116连接到低轴40的内部叶片组120和插入在内部叶片组120之间的外部叶片组122。 外侧刀片组122固定在外侧转子126上; 外转子126的前端由轴承150支撑在中心涡轮机框架134上; 并且外转子126的后端由轴承152支撑在低轴40上。此外，齿轮装置116包括太阳齿轮140，与太阳齿轮140啮合的分动齿轮142和环 与分动齿轮142啮合的齿轮148。
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公开(公告)号：WO2014011245A2
公开(公告)日：2014-01-16
申请号：PCT/US2013033207
申请日：2013-03-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MCCUNE MICHAEL E , SHERIDAN WILLIAM G , PORTLOCK LAWRENCE E
CPC classification number: F02K3/06 , F01D25/18 , F02C3/107 , F05D2260/40311 , F16H57/0471 , F16H57/0479 , Y02T50/671
Abstract: A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine stage drives the first compressor stage as part of a low spool. A gear train drives the fan with the low spool, such that the fan and first compressor stage rotate in the same direction. The high spool operates at higher pressures than the low spool. A lubrication system is also disclosed.
Abstract translation: 燃气涡轮发动机具有风扇，第一和第二压缩机级，第一和第二涡轮机级。 第一个涡轮机级以高速驱动第二压缩机级。 第二涡轮级驱动第一压缩机级作为低阀芯的一部分。 齿轮系用低速轴驱动风扇，使得风扇和第一压缩机级以相同的方向旋转。 高阀芯在比低阀芯更高的压力下运行。 还公开了一种润滑系统。
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公开(公告)号：WO2015147948A3
公开(公告)日：2015-12-10
申请号：PCT/US2015010016
申请日：2015-01-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHERIDAN WILLIAM G , MCCUNE MICHAEL E
CPC classification number: F02C7/36 , F01D25/20 , F02C7/06 , F02K3/06 , F05D2260/40311 , F05D2260/608 , F05D2260/98 , F16H57/04 , F16H57/0427 , F16H57/0479 , F16H57/0486 , F16H57/08 , Y02T50/671
Abstract: A gas turbine engine comprises a fan drive turbine for driving a gear reduction, which drives a fan rotor. A lubrication system supplies oil to the gear reduction. An oil tank is relatively small. The lubrication system operates to allow oil to remain in the oil tank for a dwell time of less than or equal to five seconds. A method of designing a gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机包括用于驱动齿轮减速的风扇驱动涡轮机，其驱动风扇转子。 润滑系统为齿轮减速器供油。 油箱比较小。 润滑系统操作以允许油保持在油箱中停留时间小于或等于5秒。 还公开了一种设计燃气涡轮发动机的方法。
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公开(公告)号：WO2014099087A2
公开(公告)日：2014-06-26
申请号：PCT/US2013062220
申请日：2013-09-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MCCUNE MICHAEL E , SHERIDAN WILLIAM G
CPC classification number: F02C7/36 , F05D2230/60 , F05D2260/40311 , F16H57/023 , F16H57/082 , Y02T50/671
Abstract: A method of assembling an epicyclic gear train includes the steps of providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced apart apertures provided at an outer circumference of the carrier. Gear pockets are provided between the walls and extend to the apertures, and a central opening in at least one of the walls. A plurality of intermediate gears is inserted through the central opening and move the intermediate gears radially outwardly into the gear pockets to extend through the apertures. A sun gear is inserted through the central opening. The plurality of intermediate gears is moved radially inwardly to engage the sun gear. A gear reduction is also disclosed.
Abstract translation: 一种组装行星齿轮系的方法包括以下步骤：提供具有中心轴线的整体载体，该中心轴线包括设置在载体的外圆周处的间隔开的壁和周向间隔开的孔。 齿轮槽设置在壁之间并延伸到孔，以及在至少一个壁中的中心开口。 多个中间齿轮通过中心开口插入并将中间齿轮径向向外移动到齿轮槽中以延伸穿过孔。 太阳齿轮穿过中央开口插入。 多个中间齿轮径向向内移动以接合太阳齿轮。 还公开了齿轮减速。
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Patent Agency Ranking6.发明申请
公开(公告)号：WO2015156885A3
公开(公告)日：2015-11-12
申请号：PCT/US2015012346
申请日：2015-01-22
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MCCUNE MICHAEL E , HUSBAND JASON
IPC: F01D15/12
CPC classification number: F02C3/107 , F01D25/162 , F02C7/36 , F05D2260/40311 , Y02T50/671
Abstract: A gas turbine engine includes a fan shaft and a support which supports at least a portion of the fan shaft. The support defines at least one of a support transverse and a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines at least one of a flexible support transverse and a flexible support lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. An input to the gear system defines at least one of an input transverse and an input lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机包括风扇轴和支撑风扇轴的至少一部分的支撑件。 支撑件限定支撑横向和支撑横向刚度中的至少一个。 齿轮系驱动风扇轴。 柔性支撑件至少部分地支撑齿轮系统，并且相对于支撑横向和支撑横向刚度中的至少一个限定柔性支撑横向和柔性支撑横向刚度中的至少一个。 相对于支撑横向和支撑横向刚度中的至少一个，齿轮系统的输入限定了输入横向刚度和输入横向刚度中的至少一个。 还公开了一种设计燃气涡轮发动机的方法。
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公开(公告)号：WO2013172906A3
公开(公告)日：2014-01-09
申请号：PCT/US2013027553
申请日：2013-02-25
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , MCCUNE MICHAEL E , MAGGE SHANKAR S
CPC classification number: F02C3/107 , F01D1/26 , F02C3/067 , F02C7/36 , F02K3/072 , F05D2250/44 , F05D2260/40311 , Y02T50/671
Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.
Abstract translation: 燃气涡轮发动机包括限定旋转轴线的轴。 外涡轮转子直接驱动轴并且包括外部一组叶片。 内部涡轮转子具有与外部组叶片交替散布的内部一组叶片。 内涡轮转子被构造成围绕与外涡轮转子的旋转轴线相反的方向旋转。 分动齿轮系统将内涡轮转子与轴连接，并且构造成以比外套叶片更快的速度旋转内组叶片。
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公开(公告)号：WO2013158179A3
公开(公告)日：2014-01-09
申请号：PCT/US2013023356
申请日：2013-01-28
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MCCUNE MICHAEL E , AHMET KAHRAMAN
IPC: F16H35/06
CPC classification number: F01D15/12 , F02C7/36 , F02K3/06 , F05D2220/323 , F05D2230/10 , F05D2250/25 , F05D2260/40 , F05D2260/40311 , F05D2260/96 , F16H55/082 , F16H57/0006 , F16H2001/2881 , Y02T50/671 , Y10T74/19098 , Y10T74/1956
Abstract: An example method of controlling performance of gearbox of a gas turbine engine includes establishing a gear characteristic of a plurality of double helical gears each disposed about a respective axis in a gearbox. Performance of the plurality of double helical gears is controlled by selecting a circumferential offset distance between a first plurality of gear teeth spaced apart from a second plurality of gear teeth on each of the plurality of double helical gears in response to the established gear characteristic.
Abstract translation: 一种控制燃气涡轮发动机的变速箱性能的示例性方法包括建立多个双螺旋齿轮的齿轮特性，每个双螺旋齿轮围绕齿轮箱中的相应轴线设置。 通过选择在多个双斜齿轮中的每一个上与第二多个齿轮齿间隔开的第一多个齿轮齿之间的周向偏移距离来控制多个双斜齿轮的性能。
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公开(公告)号：CA3060753C
公开(公告)日：2022-08-09
申请号：CA3060753
申请日：2019-10-29
Applicant: UNITED TECHNOLOGIES CORP
Inventor： LEQUE NICHOLAS D , MCCUNE MICHAEL E , POLLY JOSEPH H
Abstract: A gas turbine engine includes a core engine, a fan section, and a superposition gearbox that includes a sun gear. A plurality of intermediate gears are engaged to the sun gear and supported in a carrier and a ring gear circumscribing the intermediate gears. The core engine drives the sun gear and an output from the superposition gearbox driving the fan section. An electric motor is coupled to a portion of the superposition gearbox to provide a portion of power to drive the fan section through the superposition gearbox.
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10.发明专利
公开(公告)号：PL3097291T3
公开(公告)日：2021-07-19
申请号：PL15769798
申请日：2015-01-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHERIDAN WILLIAM G , MCCUNE MICHAEL E
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