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公开(公告)号：US20180274483A1
公开(公告)日：2018-09-27
申请号：US15889304
申请日：2018-02-06
Applicant: United Technologies Corporation
Inventor： Constantine Baltas
CPC classification number: F02K1/15 , F02C3/107 , F02K1/06 , F02K1/12 , F02K1/1207 , F02K1/30 , F02K3/06 , F02K3/075 , F05D2220/326 , F05D2220/327
Abstract: A gas turbine engine includes a core engine defined about an axis, a gear system driven by the core engine, and a pylon variable area flow system. A fan is driven by the gear system. The variable area flow system operates to effect the bypass flow.
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公开(公告)号：US20160138416A1
公开(公告)日：2016-05-19
申请号：US15008508
申请日：2016-01-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Constantine Baltas , Amr Ali
CPC classification number: F01D17/14 , B64C9/38 , F01D5/02 , F01D9/02 , F01D17/105 , F01D25/24 , F02C3/04 , F02K1/08 , F02K1/085 , F02K1/12 , F02K1/1207 , F02K1/386 , F02K1/46 , F02K1/48 , F02K3/00 , F02K3/04 , F02K3/06 , F02K3/075 , F03G7/065 , F05D2220/36 , F05D2240/128 , F05D2240/24 , F05D2240/35 , F05D2260/606 , F05D2300/174 , F05D2300/177 , F05D2300/505
Abstract: A gas turbine engine includes a fan, a nacelle arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow from the fan. A nozzle associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.
Abstract translation: 燃气涡轮发动机包括风扇，围绕风扇布置的机舱和至少部分地在机舱内的发动机芯。 在机舱和燃气涡轮发动机之间的风扇下游的风扇旁路通道从风扇传送旁路气流。 与风扇旁路通道相关联的喷嘴可操作以控制旁路气流。 喷嘴包括具有对应于第一喷嘴位置的第一固态相和对应于第二喷嘴位置的第二固态相的形状记忆材料。
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公开(公告)号：US10184340B2
公开(公告)日：2019-01-22
申请号：US14769408
申请日：2014-02-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Constantine Baltas , Jonathan Gilson
IPC: F01D5/14
Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.
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公开(公告)号：US10287987B2
公开(公告)日：2019-05-14
申请号：US14204983
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： Constantine Baltas , Oliver V. Atassi
Abstract: A gas turbine engine includes a first airflow structure and a second airflow structure disposed aft of the first airflow structure. The second airflow structure includes a leading edge region. A thickness of the leading edge region is based on a thickness of a wake in the airflow produced by the first airflow structure when the airflow passes between the first airflow structure and the second airflow structure.
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公开(公告)号：US10066548B2
公开(公告)日：2018-09-04
申请号：US14766267
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： Jonathan Gilson , Constantine Baltas
CPC classification number: F02C7/045 , F01D25/24 , F02C3/107 , F02C7/24 , F02K1/827 , F05D2240/40 , F05D2250/00 , F05D2250/283 , F05D2250/37 , F05D2260/963
Abstract: A geared turbofan engine includes a first rotor, a fan, a second rotor, a gear train, a fan casing, a nacelle and a plurality of discrete acoustic liner segments. The fan is connected to the first rotor and is capable of rotation at frequencies between 200 and 6000 Hz and has a fan pressure ratio of between 1.25 and 1.60. The gear train connects the first rotor to the second rotor. The fan casing and nacelle are arranged circumferentially about a centerline and define a bypass flow duct in which the fan is disposed. The plurality of discrete acoustic liner segments with varied geometric properties are disposed along the bypass flow duct.
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Patent Agency Ranking
公开(公告)号：US20140348630A1
公开(公告)日：2014-11-27
申请号：US14204983
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： Constantine Baltas , Oliver V. Atassi
CPC classification number: F02C7/24 , F02K1/09 , F02K3/06 , F05D2260/96
Abstract: A gas turbine engine includes a first airflow structure and a second airflow structure disposed aft of the first airflow structure. The second airflow structure includes a leading edge region. A thickness of the leading edge region is based on a thickness of a wake in the airflow produced by the first airflow structure when the airflow passes between the first airflow structure and the second airflow structure.
Abstract translation: 燃气涡轮发动机包括第一气流结构和设置在第一气流结构后面的第二气流结构。 第二气流结构包括前缘区域。 前缘区域的厚度基于当第一气流结构和第二气流结构之间的气流通过时由第一气流结构产生的气流中的尾流的厚度。
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7.发明申请GEARED GAS TURBINE ENGINE INTEGRATED WITH A VARIABLE AREA FAN NOZZLE WITH REDUCED NOISE 审中-公开齿轮气体涡轮发动机与可变区域风扇喷嘴集成，减少噪音公开(公告)号：US20150252751A1
公开(公告)日：2015-09-10
申请号：US14430952
申请日：2013-03-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Constantine Baltas
CPC classification number: F02K1/06 , B64D33/06 , F02C3/04 , F02C3/107 , F02C7/24 , F02C7/36 , F02K1/827 , F02K3/06 , F05D2250/283 , F05D2260/40311 , F05D2260/963
Abstract: A gas turbine engine includes a spool and a turbine coupled to drive the spool. A fan is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the fan and the spool such that rotation of the spool drives the fan at a different speed than the spool. A fan nozzle is located downstream from the fan. The fan nozzle includes a variable area nozzle configured to change an exit area of the fan nozzle. An acoustic liner partially lines the fan nozzle.
Abstract translation: 燃气涡轮发动机包括阀芯和联接以驱动阀芯的涡轮机。 风扇被联接以由涡轮机通过卷轴驱动。 齿轮组件联接在风扇和阀芯之间，使得阀芯的旋转以与阀芯不同的速度驱动风扇。 风扇喷嘴位于风扇的下游。 风扇喷嘴包括构造成改变风扇喷嘴的出口区域的可变区域喷嘴。 声学衬垫部分地将风扇喷嘴排成线。
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公开(公告)号：US20150233298A1
公开(公告)日：2015-08-20
申请号：US14428392
申请日：2013-02-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Constantine Baltas
Abstract: A turbine engine system mounted on an aircraft wing includes a gas turbine engine having a spool, a turbine coupled with the spool, a fan coupled to be rotated about an axis through the spool, and a gear assembly coupled between the fan and spool such that rotation of the spool results in rotation of the fan at a different speed than the spool. The gas turbine engine is operable to discharge a jet plume that interacts with a flap of the aircraft wing. The gas turbine engine defines a design fan pressure ratio of 1.25-1.50 to control sound resulting from the jet plume that interacts with the flap.
Abstract translation: 安装在飞行器机翼上的涡轮发动机系统包括燃气涡轮发动机，其具有阀芯，与阀芯联接的涡轮，联接成围绕轴线旋转通过阀芯的风扇，以及联接在风扇和阀芯之间的齿轮组件，使得 阀芯的旋转导致风扇以与阀芯不同的速度旋转。 燃气涡轮发动机可操作地排出与飞行器机翼的翼片相互作用的喷射羽流。 燃气涡轮发动机定义了1.25-1.50的设计风扇压力比，以控制与翼片相互作用的喷射羽流产生的声音。
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公开(公告)号：US10371001B2
公开(公告)日：2019-08-06
申请号：US15008508
申请日：2016-01-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Constantine Baltas , Amr Ali
IPC: F02K1/46 , F02K1/48 , F02K1/38 , F01D17/14 , F02K1/08 , F02K3/075 , F03G7/06 , F01D5/02 , F01D9/02 , F01D17/10 , F01D25/24 , F02C3/04 , B64C9/38 , F02K1/12 , F02K3/00 , F02K3/04 , F02K3/06
Abstract: A gas turbine engine includes a fan, a nacelle arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow from the fan. A nozzle associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.
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10.发明申请Geared Turbofan Engine Having a Reduced Number of Fan Blades and Improved Acoustics 审中-公开具有减少风扇叶片数量和改进声学的齿轮涡轮风扇发动机公开(公告)号：US20160003049A1
公开(公告)日：2016-01-07
申请号：US14769408
申请日：2014-02-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Constantine Baltas , Jonathan Gilson
IPC: F01D5/14
CPC classification number: F01D5/141 , F05D2220/36 , Y02T50/671 , Y02T50/673
Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.
Abstract translation: 转子叶片包括从根部到尖端部分径向延伸并且从前缘到后缘的轴向延伸的翼型件，前缘和后缘在它们之间限定曲率。 基于在翼型的前缘处的入射流速和在相对跨度高度处的旋转速度，曲率确定根部和尖端部分之间相对跨度高度处的相对出射角。 在转子叶片的操作中，相对出口角度确定了从75％到95％的相对跨度高度的基本上平坦的出口压力比分布，其中出口压力比分布是恒定的，在公差范围内的最大值的10％ 出口压力比。
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