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1.发明申请GAS TURBINE ENGINE WITH COOLING SCHEME FOR DRIVE GEAR SYSTEM AND PITCH CONTROL 审中-公开具有用于驱动齿轮系统和调节控制的冷却方案的燃气涡轮发动机
公开(公告)号：WO2014092750A1
公开(公告)日：2014-06-19
申请号：PCT/US2013/026807
申请日：2013-02-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel L. , EPSTEIN, Alan H. , LORD, Wesley K. , CHANDLER, Jesse M.
CPC classification number: F02C7/36 , B64D33/02 , B64D33/10 , B64D2033/022 , F02C7/052 , F05D2220/324 , F05D2220/325 , F05D2250/44 , F05D2260/20 , Y02T50/675
Abstract: A gas turbine engine comprises an outer nacelle. A nose cone is spaced radially inward of the outer nacelle. The nose cone defines a particle separator for directing an outer air flow and an inner airflow. The inner airflow is directed through a core inlet to a compressor. The engine further comprises a drive gear system for driving at least one propeller. A variable pitch control system may alter a pitch angle of the at least one propeller. Some of the outer air flow is directed to at least one of the drive gear system and the pitch control system.
Abstract translation: 燃气涡轮发动机包括外部机舱。 鼻锥在外部机舱的径向内侧间隔开。 鼻锥限定了用于引导外部空气流和内部空气流的颗粒分离器。 内部气流被引导通过压缩机的核心入口。 发动机还包括用于驱动至少一个螺旋桨的驱动齿轮系统。 可变桨距控制系统可以改变至少一个螺旋桨的桨距角。 一些外部气流被引导到驱动齿轮系统和俯仰控制系统中的至少一个。
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2.发明申请GEARED TURBOFAN WITH THREE TURBINES WITH FIRST TWO CO-ROTATING AND THIRD ROTATING IN AN OPPOSED DIRECTION 审中-公开具有三次涡轮机的三轮涡轮机具有第一次双向旋转和三次旋转的方向
公开(公告)号：WO2014007897A3
公开(公告)日：2015-01-08
申请号：PCT/US2013034539
申请日：2013-03-29
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , KUPRATIS DANIEL BERNARD
IPC: F02C3/04
CPC classification number: F01D1/24 , F01D15/12 , F02C3/067 , F02C3/107 , F02C7/36 , F05D2250/44 , F05D2260/4031
Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool rotating in the same direction as the intermediate speed spool. The fan drive turbine rotates in an opposed direction as the intermediate speed spool.
Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩到比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二涡轮驱动压缩机转子。 风扇驱动涡轮机位于第二涡轮转子的下游。 风扇驱动涡轮驱动风扇通过齿轮减速。 第一压缩机转子和第二涡轮机转子作为中间速度卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速滑阀。 高速卷轴以与中间速度卷轴相同的方向旋转。 风扇驱动涡轮机以与中间速度卷轴相反的方向旋转。
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公开(公告)号：WO2014018141A2
公开(公告)日：2014-01-30
申请号：PCT/US2013037674
申请日：2013-04-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , SCHWARZ FREDERICK M
CPC classification number: F02C3/107 , F01D1/10 , F01D1/26 , F01D5/06 , F01D15/12 , F02C3/06 , F02C3/067 , F02C3/073 , F05D2220/32 , F05D2250/44 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool and the fan drive turbine configured to rotate in the same first direction. The intermediate speed spool rotates in an opposed, second direction.
Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩到比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二涡轮驱动压缩机转子。 风扇驱动涡轮机位于第二涡轮转子的下游。 风扇驱动涡轮驱动风扇通过齿轮减速。 第一压缩机转子和第二涡轮机转子作为中间速度卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速滑阀。 所述高速线轴和所述风扇驱动涡轮机构造成沿相同的第一方向旋转。 中间速度卷轴以相对的第二方向旋转。
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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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5.发明申请COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO MID TURBINE FRAME 审中-公开具有安装在中间涡轮机框架上的齿轮系统的逆转低压涡轮机
公开(公告)号：WO2013172905A2
公开(公告)日：2013-11-21
申请号：PCT/US2013/027549
申请日：2013-02-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel, L. , MERRY, Brian, D.
CPC classification number: F02C3/107 , F01D1/26 , F01D25/162 , F02C3/067 , F02C7/06 , F02C7/36 , F02K3/072 , F05D2250/36 , F05D2250/44 , F05D2260/4031 , 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 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. The gear system is mounted to a mid-turbine frame.
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。 齿轮系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。 齿轮系统安装到中涡轮机架。
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Patent Agency Ranking6.发明申请GEARED ANNULAR AIRFLOW ACTUATION SYSTEM FOR VARIABLE CYCLE GAS TURBINE ENGINES 审中-公开变速循环燃气轮机发动机的减速环形气流驱动系统
公开(公告)号：WO2015030858A2
公开(公告)日：2015-03-05
申请号：PCT/US2014/014847
申请日：2014-02-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： IZQUIERDO, Felix
IPC: F02C7/057
CPC classification number: F01D17/162 , F02C9/20 , F02K3/075 , F02K3/077 , F05D2240/12 , F05D2250/44 , F05D2260/4031 , F05D2260/53 , F05D2260/79
Abstract: An annular airflow control system for a gas turbine engine includes a sync ring rotatable to move the multiple of contra-rotatable variable vanes through a respective multiple of geared interfaces to throttle an airflow through the multiple of contra-rotatable variable vanes.
Abstract translation: 用于燃气涡轮发动机的环形气流控制系统包括同步环，所述同步环可旋转以使所述多个可反向旋转的可变叶片移动通过相应的多个齿轮接口以限制通过所述多个反向旋转阀的气流， 可旋转的可变叶片。
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7.发明申请GEARED TURBOFAN WITH THREE TURBINES WITH FIRST TWO CO-ROTATING AND THIRD ROTATING IN AN OPPOSED DIRECTION 审中-公开具有三轮涡轮机的三轮涡轮机具有第一次双向旋转和三次旋转的方向
公开(公告)号：WO2014007897A2
公开(公告)日：2014-01-09
申请号：PCT/US2013/034539
申请日：2013-03-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SCHWARZ, Frederick M. , KUPRATIS, Daniel Bernard
CPC classification number: F01D1/24 , F01D15/12 , F02C3/067 , F02C3/107 , F02C7/36 , F05D2250/44 , F05D2260/4031
Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool rotating in the same direction as the intermediate speed spool. The fan drive turbine rotates in an opposed direction as the intermediate speed spool.
Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩到比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二涡轮驱动压缩机转子。 风扇驱动涡轮机位于第二涡轮转子的下游。 风扇驱动涡轮驱动风扇通过齿轮减速。 第一压缩机转子和第二涡轮机转子作为中间速度卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速滑阀。 高速卷轴以与中间速度卷轴相同的方向旋转。 风扇驱动涡轮机以与中间速度卷轴相反的方向旋转。
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公开(公告)号：WO2013154649A2
公开(公告)日：2013-10-17
申请号：PCT/US2013/022388
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel L. , ACKERMANN, William K. , KUPRATIS, Daniel Bernard , SCHWARZ, Frederick M.
IPC: F02K3/02
CPC classification number: F02K3/06 , F02C3/107 , F02C7/36 , F05D2220/323 , F05D2250/44
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
Abstract translation: 燃气涡轮发动机包括超高速低压涡轮机，使得由低压涡轮机的出口面积所限定的量乘以低压涡轮机转速的平方与相同的参数 因为高压涡轮机的比率在大约0.5和大约1.5之间。
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9.发明申请GEARED ANNULAR AIRFLOW ACTUATION SYSTEM FOR VARIABLE CYCLE GAS TURBINE ENGINES 审中-公开用于可变循环气体涡轮发动机的齿轮式气流启动系统
公开(公告)号：WO2015030858A3
公开(公告)日：2015-05-07
申请号：PCT/US2014014847
申请日：2014-02-05
Applicant: UNITED TECHNOLOGIES CORP
Inventor： IZQUIERDO FELIX
CPC classification number: F01D17/162 , F02C9/20 , F02K3/075 , F02K3/077 , F05D2240/12 , F05D2250/44 , F05D2260/4031 , F05D2260/53 , F05D2260/79
Abstract: An annular airflow control system for a gas turbine engine includes a sync ring rotatable to move the multiple of contra-rotatable variable vanes through a respective multiple of geared interfaces to throttle an airflow through the multiple of contra-rotatable variable vanes.
Abstract translation: 用于燃气涡轮发动机的环形气流控制系统包括可旋转的同步环，以通过相应的多个齿轮传动接口移动多个可反转的可变叶片，以节流通过多个可逆转可变叶片的气流。
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公开(公告)号：WO2013154649A3
公开(公告)日：2014-03-20
申请号：PCT/US2013022388
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , ACKERMANN WILLIAM K , KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
IPC: F02K3/02
CPC classification number: F02K3/06 , F02C3/107 , F02C7/36 , F05D2220/323 , F05D2250/44
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
Abstract translation: 燃气涡轮发动机包括非常高速的低压涡轮机，使得由低压涡轮机的出口面积所规定的数量乘以低压涡轮转速的平方，与高压涡轮机的相同参数相比是在 在约0.5和约1.5之间。
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