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公开(公告)号：US20150361881A1
公开(公告)日：2015-12-17
申请号：US14689337
申请日：2015-04-17
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Frederick M. Schwarz
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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392.发明申请公开(公告)号：US20150360787A1
公开(公告)日：2015-12-17
申请号：US14600235
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Jesse M. Chandler , Gabriel L. Suciu
CPC classification number: B64D27/12 , B64C3/10 , B64D35/04 , F02C3/10 , F02C7/36 , F02K1/52 , F05D2240/40 , F05D2260/4031 , F05D2260/532
Abstract: A gas turbine engine includes a gas generator that has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of the at least one gas generator turbine rotor. The fan drive turbine drives a driveshaft and the driveshaft engages gears to drive at least three fan rotors. The driveshaft extends away from the gas generator such that at least one of the fan rotors that is positioned remotely from the fan drive turbine on the driveshaft is spaced to be either more forward or more rearward of the fan drive turbine relative to at least one of the fan rotors positioned closer to the fan drive turbine. An aircraft is also disclosed.
Abstract translation: 燃气涡轮发动机包括具有至少一个压缩机转子，至少一个气体发生器涡轮机转子和燃烧部分的气体发生器。 风扇驱动涡轮机位于至少一个气体发生器涡轮机转子的下游。 风扇驱动涡轮驱动驱动轴，驱动轴接合齿轮以驱动至少三个风扇转子。 驱动轴远离气体发生器延伸，使得远离驱动轴上的风扇驱动涡轮机定位的风扇转子中的至少一个相对于风扇驱动涡轮机中的至少一个与风扇驱动涡轮机相距更远或更靠后 风扇转子靠近风扇驱动涡轮机定位。 还披露了一架飞机。
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公开(公告)号：US20150336655A1
公开(公告)日：2015-11-26
申请号：US14440895
申请日：2013-03-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jesse M. Chandler , Gabriel L. Suciu
CPC classification number: B64C3/14 , B64C5/06 , B64C39/068 , B64C39/10 , B64C39/12 , B64D27/14 , B64D33/04 , F02K1/56 , F02K1/78
Abstract: An aircraft including a fuselage having a forward portion and an aft portion with a propulsion system mounted within the aft portion of the fuselage. A burst zone is defined that extends outward from the propulsion system. The aircraft includes a box wing extending from the aft portion of the fuselage to a forward portion of the fuselage that is disposed outside of the burst zone.
Abstract translation: 一种飞机，包括具有前部和后部的机身，其具有安装在机身后部的推进系统。 定义了从推进系统向外延伸的爆破区域。 飞机包括从机身的后部延伸到设置在爆破区域外部的机身的前部的箱翼。
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公开(公告)号：US20150322854A1
公开(公告)日：2015-11-12
申请号：US14806809
申请日：2015-07-23
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Nathan Snape , Christopher M. Dye
CPC classification number: F02C3/04 , F01D25/12 , F01D25/18 , F02C7/06 , F02C7/12 , F02C7/14 , F02C7/32
Abstract: A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A combustor section is arranged axially between the compressor section and the turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. A heat exchanger is secured to the oil tank and arranged in the core compartment.
Abstract translation: 燃气涡轮发动机包括包括压缩机部分和涡轮机部分的发动机静态结构壳体。 燃烧器部分轴向布置在压缩机部分和涡轮部分之间。 一个核心机舱包围发动机静态结构以提供一个核心隔间。 油箱布置在芯部隔室中并与压缩机部分轴向对准。 热交换器被固定到油箱并且布置在核心隔间中。
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公开(公告)号：US20150315977A1
公开(公告)日：2015-11-05
申请号：US14755366
申请日：2015-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
CPC classification number: F02K3/06 , B64D27/26 , B64D2027/266 , B64D2027/268 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/24 , F01D25/28 , F02C3/107 , F02C7/20 , F02C7/36 , F02C9/18 , F02C9/20 , F02K1/15 , F05D2220/32 , F05D2220/36 , F05D2260/4031 , F05D2260/40311 , F05D2270/42
Abstract: A gas turbine engine includes a core nacelle defined about an engine axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A gear train is defined along an engine axis. The gear train defines a gear reduction ratio of greater than or equal to about 2.3. A fan drive turbine along the engine axis which drives the gear train. The fan drive turbine includes three to six (3-6) stages. A fan is configured for rotation within the fan nacelle for operation at a fan pressure ratio less than about 1.45. A fan variable area nozzle is axially movable relative to said fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation. A high bypass gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机包括围绕发动机轴线限定的核心机舱。 风扇机舱至少部分地安装在核心机舱周围，以限定用于风扇旁路气流的风扇旁路气流路径。 齿轮系沿发动机轴线定义。 齿轮系确定齿轮减速比大于或等于约2.3。 沿着发动机轴线的驱动齿轮系的风扇驱动涡轮机。 风扇驱动轮机包括三到六（3-6）个阶段。 风扇被配置为在风扇机舱内旋转，以便在小于约1.45的风扇压力比下操作。 风扇可变区域喷嘴可相对于所述风扇机舱轴向移动，以改变风扇喷嘴出口区域，并且在发动机运行期间调节风扇旁路气流的压力比。 还公开了一种高旁路燃气涡轮发动机。
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Patent Agency Ranking
公开(公告)号：US20150300293A1
公开(公告)日：2015-10-22
申请号：US14441633
申请日：2013-03-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse Chandler
Abstract: A gas turbine engine has a fan inlet and a fan configured to deliver air to an exhaust nozzle. A core gas turbine engine. including in serial order extending further into the engine, a core turbine section, a combustor and a core compressor section. A core engine inlet duct is spaced from the fan inlet. A method is also described.
Abstract translation: 燃气涡轮发动机具有风扇入口和风扇，其构造成将空气输送到排气喷嘴。 核心燃气轮机。 包括进一步延伸到发动机中的串联顺序，核心涡轮部分，燃烧器和核心压缩机部分。 核心发动机入口管道与风扇入口间隔开。 还描述了一种方法。
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公开(公告)号：US20150298814A1
公开(公告)日：2015-10-22
申请号：US14440718
申请日：2013-03-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: An aircraft includes a fuselage including a propulsion system supported within an aft portion. A thrust reverser is mounted proximate to the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser directs thrust at an angle relative to a vertical plane to reduce interference on control surfaces and reduce generation of underbody lift.
Abstract translation: 一架飞机包括一个机身，包括一个支撑在后部的推进系统。 推力反向器安装在靠近推进系统的位置，用于将推力推向减速飞机的方向。 推力反向器相对于垂直平面以一定角度引导推力，以减少对控制表面的干扰，并减少底部升力的产生。
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公开(公告)号：US20150259059A1
公开(公告)日：2015-09-17
申请号：US14440887
申请日：2013-03-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jesse M. Chandler , Gabriel L. Suciu
CPC classification number: B64C1/26 , B64C1/06 , B64C5/02 , B64D25/00 , B64D27/20 , B64D33/02 , B64D2033/0286
Abstract: An aircraft assembly is disclosed and includes a fuselage including a turbine engine mounted within the aft fuselage. burst zone is defined about the turbine engine and a tail is disposed at least partially with the burst zone. The tail includes primary control surfaces and sacrificial control surfaces. The sacrificial control surfaces can break away in a defined manner to maintain integrity of the primary control surfaces outside of the burst zone.
Abstract translation: 公开了一种飞机组件，并且包括机身，其包括安装在后机身内的涡轮发动机。 突发区域围绕涡轮发动机定义，并且尾部至少部分地布置有爆裂区域。 尾部包括主控制面和牺牲控制面。 牺牲控制表面可以以限定的方式脱离，以保持主控制表面在爆破区之外的完整性。
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公开(公告)号：US20150247456A1
公开(公告)日：2015-09-03
申请号：US14608227
申请日：2015-01-29
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , James D. Hill , Jesse M. Chandler
CPC classification number: F02C3/14 , F02C3/06 , F02C3/10 , F02C6/02 , F02C7/05 , F02K3/12 , F05D2220/32 , F05D2250/314
Abstract: A gas turbine engine has a propulsion unit and a gas generating core. The propulsion unit includes a fan and a free turbine, wherein the free turbine is connected to drive the fan about a first axis. The gas generating core includes a compressor, a combustion section, and a gas generating core turbine. The compressor and the gas generating core turbine are configured to rotate about a second axis. An inlet duct is configured to deliver air from the fan to the gas generating core. The inlet duct has a crescent shaped cross-section near the fan.
Abstract translation: 燃气涡轮发动机具有推进单元和气体发生芯。 推进单元包括风扇和自由涡轮机，其中自由涡轮机被连接以围绕第一轴线驱动风扇。 气体发生芯包括压缩机，燃烧部分和气体发生芯涡轮机。 压缩机和气体发生芯涡轮机构造成围绕第二轴线旋转。 入口管道构造成将空气从风扇输送到气体生成芯。 入口管道在风扇附近具有月牙形横截面。
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400.发明申请公开(公告)号：US20150247424A1
公开(公告)日：2015-09-03
申请号：US14427664
申请日：2013-03-14
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu
CPC classification number: F01D25/24 , F01D25/243 , F02C3/10 , F02C6/08 , F02C7/36 , F05D2250/30 , F05D2260/40311
Abstract: A gas turbine engine has a compressor section, a compressor case substantially surrounding the compressor section, and a diffuser case attached at an attachment interface to the compressor case. The attachment interface is between a forward and an aft end of the compressor. A geared turbofan is also disclosed.
Abstract translation: 燃气涡轮发动机具有压缩机部分，基本上围绕压缩机部分的压缩机壳体和附接到压缩机壳体的附接界面处的扩散器壳体。 附件接口位于压缩机的前端和后端之间。 还披露了一种齿轮传动风扇。
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