-
公开(公告)号：US20160237906A1
公开(公告)日：2016-08-18
申请号：US14745539
申请日：2015-06-22
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Brian D. Merry , Nathan Snape
CPC classification number: F02C7/18 , F05D2260/213 , Y02T50/676
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. A core housing has an outer peripheral surface and a fan housing defining an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is received within the at least one bifurcation duct.
Abstract translation: 燃气涡轮发动机包括具有下游排出口的高压压缩机的主压缩机部分和更多的上游位置。 涡轮机部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 芯壳体具有外周表面和限定内周表面的风扇壳体。 至少一个分叉管在外周表面和内周表面之间延伸。 热交换器被容纳在至少一个分叉管内。
-
公开(公告)号：US20160237905A1
公开(公告)日：2016-08-18
申请号：US14695578
申请日：2015-04-24
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry
CPC classification number: F41A9/63 , F02C3/04 , F02C7/18 , F02C7/185 , F02C7/32 , F02K3/06 , F05D2260/211 , F05D2260/213 , F05D2260/4031 , F41A9/65 , Y02T50/676
Abstract: Aa gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.
Abstract translation: Aa燃气涡轮发动机包括具有具有下游排出口的高压压缩机和更多上游位置的主压缩机部分。 涡轮机部分具有高压涡轮机。 抽头从压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。 冷却压缩机压缩热交换器下游的空气，并将空气输送到高压涡轮机中。 还公开了一种用于燃气涡轮发动机的中间冷却系统。
-
公开(公告)号：US20160215699A1
公开(公告)日：2016-07-28
申请号：US14917396
申请日：2014-08-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A gas turbine engine includes a core engine including a central engine axis and a nacelle surrounding the core engine. At least a portion of the nacelle is axially movable relative to the core engine between open and fully closed positions. A ceramic-based liner is located at an aft portion of the core engine. The ceramic-based component mechanically interfaces with the movable portion of the nacelle when the nacelle is in the fully closed position. A turbine section and a method of accommodating thermally-induced dimensional change of engine components are also disclosed.
Abstract translation: 燃气涡轮发动机包括具有中心发动机轴线和围绕核心发动机的机舱的核心发动机。 机舱的至少一部分在开放位置和完全关闭位置之间相对于核心发动机可轴向移动。 陶瓷基衬套位于核心发动机的后部。 当机舱处于完全关闭位置时，陶瓷基部件与机舱的可移动部分机械地接合。 还公开了涡轮部分和容纳发动机部件的热致尺寸变化的方法。
-
194.发明授权Gas turbine engine having fan rotor driven by turbine exhaust and with a bypass 有权具有由涡轮排气驱动的风扇转子和旁路的燃气涡轮发动机公开(公告)号：US09352843B2
公开(公告)日：2016-05-31
申请号：US13731371
申请日：2012-12-31
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine. The fan rotor turbine is in the path of gases downstream from the core engine turbine. A bypass door is moveable from a closed position at which the gases from the core engine turbine pass over the fan rotor turbine, and moveable to a bypass position at which the gases are directed away from the fan rotor turbine. An aircraft is also disclosed.
Abstract translation: 燃气涡轮发动机具有并入有核心发动机涡轮机的核心发动机。 风扇转子由风扇转子涡轮机驱动。 风扇转子涡轮机处于来自核心发动机涡轮机下游的气体的路径。 旁路门可以从关闭位置移动，在该关闭位置，来自核心发动机涡轮机的气体通过风扇转子涡轮机，并且可移动到旁路位置，在该旁路位置，气体被引导离开风扇转子涡轮机。 还披露了一架飞机。
-
公开(公告)号：US20160061045A1
公开(公告)日：2016-03-03
申请号：US14842404
申请日：2015-09-01
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Stephen K. Kramer , Jesse M. Chandler
CPC classification number: F01D9/02 , F01D5/04 , F01D5/06 , F01D13/003 , F02C3/04 , F02C3/05 , F02C3/085 , F02C3/10 , F02C3/103 , F02C3/14 , F02C7/04 , F05D2220/32 , F05D2240/24 , F05D2240/35 , F05D2250/312 , F05D2250/314
Abstract: A decoupled gas turbine engine includes a high spool assembly and a low spool assembly each having a rotational axis that are spaced from one-another. The engine further includes a combustor that may have a centerline spaced from the rotational axes of each spool assembly. Turning ducts of the engine are configured to re-direct airflow from one spool assembly to the next and/or between one spool assembly and the combustor.
Abstract translation: 解耦燃气涡轮发动机包括一个高阀芯组件和一个低阀芯组件，每个都具有一个彼此间隔开的旋转轴线。 发动机还包括可具有与每个线轴组件的旋转轴线间隔开的中心线的燃烧器。 发动机的转向管道被配置为将气流从一个线轴组件重新引导到下一个和/或一个线轴组件和燃烧器之间。
-
Patent Agency Ranking
公开(公告)号：US20160040626A1
公开(公告)日：2016-02-11
申请号：US14773958
申请日：2014-03-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02K1/70 , F02K1/06 , F02K1/52 , F02K1/60 , F02K1/62 , F05D2220/323 , F05D2240/40
Abstract: A nozzle assembly for a dual gas turbine engine propulsion system includes a housing mountable proximate to a first bypass passage of a first gas turbine engine and a second bypass passage of a second gas turbine engine, first and second upper doors, and first and second lower doors. Each of the first and second upper doors and the first and second lower doors are pivotally mounted to the housing for movement between a stowed position and a deployed position in which airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second gas turbine engines.
Abstract translation: 一种用于双燃气涡轮发动机推进系统的喷嘴组件，包括靠近第一燃气涡轮发动机的第一旁通通道安装的壳体和第二燃气涡轮发动机的第二旁通通道，第一和第二上部门，以及第一和第二下部 门。 第一和第二上部门以及第一和第二下部门中的每一个都枢转地安装到壳体上，以在收起位置和展开位置之间移动，在该位置中，穿过第一和第二旁路通道的气流相对于相应的中心线 第一和第二燃气涡轮发动机。
-
公开(公告)号：US20150361880A1
公开(公告)日：2015-12-17
申请号：US14600487
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Wesley K. Lord , Jesse M. Chandler , Michael Winter , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机包括多个风扇转子。 气体发生器包括至少一个压缩机转子，至少一个气体发生器涡轮机转子，燃烧部分和在至少一个气体发生器涡轮机转子下游的风扇驱动涡轮机。 轴构造成由风扇驱动涡轮机驱动。 轴接合齿轮以驱动多个风扇转子。 系统控制提供给多个风扇转子的功率量。 还公开了一种操作燃气涡轮发动机的方法。
-
198.发明申请GAS TURBINE ENGINE WITH COOLING SCHEME FOR DRIVE GEAR SYSTEM AND PITCH CONTROL 有权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：US20150300265A1
公开(公告)日：2015-10-22
申请号：US14440953
申请日：2013-02-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Alan H. Epstein , Wesley K. Lord , Jesse M. Chandler
IPC: F02C7/36
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。
-
公开(公告)号：US20150284067A1
公开(公告)日：2015-10-08
申请号：US14440995
申请日：2013-10-17
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: B64C5/02 , B64C1/26 , B64C5/06 , B64C9/02 , B64C19/00 , B64D27/14 , B64D33/04 , F02K1/56 , F02K1/78
Abstract: An aircraft includes a tail extending from a fuselage. The tail defines a structural box having first and second vertical stabilizers that support a horizontal stabilizer. The tail includes at least one sacrificial control surface and at least one primary control surface. The primary control surfaces maintain aircraft controllability in the event that the sacrificial control surface becomes inoperable.
Abstract translation: 飞机包括从机身延伸的尾巴。 尾部限定了具有支撑水平稳定器的第一和第二垂直稳定器的结构箱。 尾部包括至少一个牺牲控制表面和至少一个主控制表面。 在牺牲控制表面变得不可操作的情况下，主要控制面保持飞行器的可控性。
-
公开(公告)号：US20150240745A1
公开(公告)日：2015-08-27
申请号：US14265856
申请日：2014-04-30
Applicant: United Technologies Corporation
Inventor： Wesley K. Lord , Jesse M. Chandler , Gabriel L. Suciu
CPC classification number: F01D13/003 , F01D13/006 , F02K3/04 , F05D2250/314
Abstract: A propulsion system for an aircraft includes a furcated nozzle that has at least a first duct that extends from a first propulsor to a first trailing end duct opening and a second duct that extends from a second propulsor to a second trailing end duct opening.
Abstract translation: 用于飞行器的推进系统包括分叉喷嘴，其具有从第一推进器延伸到第一尾端管道开口的至少第一管道和从第二推进器延伸到第二后端管道开口的第二管道。
-
-
-
-
-
-
-
-
-
Search Results
205
records
(took 0.023 seconds)
