公开(公告)号：US20150233302A1

公开(公告)日：2015-08-20

申请号：US14433444

申请日：2013-10-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Glenn Levasseur ,  Gabriel L. Suciu ,  Gary M. Stetson

IPC: F02C7/36 ,  F02C3/06 ,  F02C9/20 ,  F02C7/32

CPC classification number: F02C7/36 ,  F01D17/162 ,  F02C3/064 ,  F02C7/32 ,  F02C9/20 ,  F05D2220/32 ,  F05D2260/4031

Abstract: A gas turbine engine has a fan which includes a plurality of fan blades that are rotatable about an axis, and a compressor section, where the combustor section includes a first compressor and a second compressor aft of the first compressor. At least one first variable guide vane controls operation of the first compressor and at least one second variable guide vane controls operation of the second compressor. A combustor is in fluid communication with the compressor section and a turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

Abstract translation: 燃气涡轮发动机具有风扇，该风扇包括可围绕轴线旋转的多个风扇叶片和压缩机部分，其中燃烧器部分包括第一压缩机和第一压缩机的第二压缩机。 至少一个第一可变导向叶片控制第一压缩机的操作，并且至少一个第二可变导向叶片控制第二压缩机的操作。 燃烧器与压缩机部分流体连通，并且涡轮部分与燃烧器流体连通。 齿轮架构由涡轮部分驱动，用于围绕轴线旋转风扇。

公开(公告)号：US20150211444A1

公开(公告)日：2015-07-30

申请号：US14592950

申请日：2015-01-09

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02K3/075 ,  F02K1/66 ,  F02K1/72

CPC classification number: F02K1/66 ,  F02C7/36 ,  F02K3/062 ,  F02K3/072 ,  F05D2260/4031

Abstract: A gas turbine engine comprises an outer shroud. An inner core housing is positioned radially inwardly of the outer shroud, and has a core engine including at least one compressor rotor and at least one turbine rotor. A combustor section is intermediate the at least one compressor rotor and the at least one turbine rotor. A fan turbine is positioned downstream of the at least one turbine rotor. The fan turbine drives a gear reduction to, in turn, drive at least one fan blade positioned radially inwardly of the outer shroud.

Abstract translation: 燃气涡轮发动机包括外护罩。 内芯壳体位于外护罩的径向内侧，并且具有包括至少一个压缩机转子和至少一个涡轮转子的核心发动机。 燃烧器部分位于至少一个压缩机转子和至少一个涡轮转子之间。 风扇涡轮机位于至少一个涡轮转子的下游。 风扇涡轮驱动齿轮减速，从而驱动至少一个位于外护罩径向内侧的风扇叶片。

公开(公告)号：US20150176530A1

公开(公告)日：2015-06-25

申请号：US14134281

申请日：2013-12-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02K3/02 ,  F02C3/13 ,  F02K3/077 ,  F02K3/075 ,  F02C3/107

CPC classification number: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2250/30 ,  Y02T50/671

Abstract: A gas turbine engine comprises a first turbine rotor positioned upstream of a second intermediate turbine rotor and a third turbine rotor positioned downstream of the first and second turbine rotors. A fan rotor and three compressor rotors, with an upstream one of the compressor rotors are connected to rotate on a shaft with a fan drive turbine and a reduced speed fan rotor through a gear reduction. A second intermediate compressor rotor for being driven by the second intermediate turbine rotor, and a third compressor rotor downstream of the first and second compressor rotors and for being driven by the first turbine rotor.

Abstract translation: 燃气涡轮发动机包括位于第二中间涡轮机转子的上游的第一涡轮机转子和位于第一和第二涡轮转子下游的第三涡轮转子。 风扇转子和三个压缩机转子，其上游的一个压缩机转子被连接以在具有风扇驱动涡轮机的轴上和通过齿轮减速的减速风扇转子旋转。 用于由第二中间涡轮机转子驱动的第二中间压缩机转子和在第一和第二压缩机转子下游的第三压缩机转子，并由第一涡轮转子驱动。

公开(公告)号：US20150167676A1

公开(公告)日：2015-06-18

申请号：US14107273

申请日：2013-12-16

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F04D19/00

CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2250/30 ,  F05D2260/40311

Abstract: A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pressure ratio is defined across the upstream and downstream compressor rotors. A bypass ratio is defined as a volume of air delivered as bypass flow compared to a volume of air delivered into the core housing. The overall pressure ratio is greater than or equal to about 45.0, and the bypass ratio is greater than or equal to about 11.0.

Abstract translation: 燃气涡轮发动机包括用于将空气作为旁路流输送到旁通管道的风扇，作为核心流动进入到芯壳体中，其中壳体包含上游压缩机转子和下游压缩机转子。 整个压力比定义在上游和下游的压缩机转子之间。 旁路比定义为与输送到芯壳体中的空气体积相比作为旁通流量输送的空气体积。 总压力比大于或等于约45.0，旁路比大于或等于约11.0。

公开(公告)号：US20150125270A1

公开(公告)日：2015-05-07

申请号：US14187034

申请日：2014-02-21

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64D29/06 ,  F01D25/24

CPC classification number: B64D29/06 ,  F01D9/02 ,  F01D25/24 ,  F01D25/28 ,  F05D2220/32 ,  F05D2230/70 ,  F05D2230/72 ,  F05D2230/80 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/128 ,  F05D2240/1281 ,  F05D2240/14 ,  F05D2240/55 ,  F05D2240/91 ,  F05D2250/192 ,  F05D2250/292 ,  F05D2250/294 ,  F05D2250/34 ,  F05D2250/75 ,  F05D2260/96 ,  Y10T29/49721

Abstract: A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon connecting portion and extending in the aft direction from the first annular portion. A second annular portion, aft of the first annular portion and coupled to the rail, is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage with the first annular portion when the second annular portion is in the closed position, thereby providing access to the engine core. A guide pin extends forward from the second annular portion. A locking mechanism is disposed within the first annular portion for engaging the guide pin when the second annular portion is in the closed position.

Abstract translation: 燃气涡轮发动机机舱包括固定的并适于部分围绕发动机芯的第一环形部分。 第一环形部分包括前挂架连接部分。 轨道联接到前挂架连接部分并且在后方向上从第一环形部分延伸。 第一环形部分的后部并且联接到轨道的第二环形部分可沿着发动机芯心中心线在关闭位置和至少一个打开位置之间移动。 第二环形部分构造成当第二环形部分处于关闭位置时与第一环形部分接合，从而提供对发动机芯的通路。 引导销从第二环形部分向前延伸。 当第二环形部分处于关闭位置时，锁定机构设置在第一环形部分内用于接合引导销。

公开(公告)号：US20150121896A1

公开(公告)日：2015-05-07

申请号：US14190162

申请日：2014-02-26

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Brian D. Merry

IPC: F02C7/20 ,  F02K1/54

CPC classification number: F02C6/206 ,  F02C7/36 ,  F02K1/605 ,  F02K3/025 ,  F05D2250/314 ,  Y02T50/671

Abstract: A mounting arrangement for an aircraft engine includes a mounting structure attached to an aircraft body and not directly connected to an engine core of the aircraft engine, a propulsor mounted to the mounting structure, and a thrust reverser mounted directly to either the propulsor or mounting structure.

Abstract translation: 用于飞行器发动机的安装装置包括安装在飞行器主体上并且不直接连接到飞行器发动机的发动机芯的安装结构，安装到安装结构的推进器和直接安装在推进器或安装结构上的推力反向器 。

公开(公告)号：US20140260183A1

公开(公告)日：2014-09-18

申请号：US14142966

申请日：2013-12-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph B. Staubach

IPC: F02C7/057 ,  F02C7/055

CPC classification number: F02C7/057 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0286 ,  F02C3/10 ,  F02C7/042 ,  F02C7/052 ,  F02C7/055 ,  F02K3/077 ,  F05D2250/314

Abstract: A gas generator for a reverse core engine propulsion system has a variable cycle intake for the gas generator, which variable cycle intake includes a duct system. The duct system is configured for being selectively disposed in a first position and a second position, wherein free stream air is fed to the gas generator when in the first position, and fan stream air is fed to the gas generator when in the second position.

Abstract translation: 用于逆向核心发动机推进系统的气体发生器具有用于气体发生器的可变循环进气口，该可变循环进气口包括管道系统。 管道系统被配置为选择性地设置在第一位置和第二位置，其中当处于第一位置时，自由流空气被供给到气体发生器，并且当处于第二位置时，风扇流空气被供给到气体发生器。

公开(公告)号：US20140252167A1

公开(公告)日：2014-09-11

申请号：US14190178

申请日：2014-02-26

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Brian D. Merry

IPC: F02K1/70 ,  B64D33/04

CPC classification number: F02K1/70 ,  B64D29/06 ,  B64D33/04 ,  F05D2250/314 ,  Y02T50/671

Abstract: A gas turbine engine for mounting under a wing of an aircraft has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a horizontal deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

Abstract translation: 用于安装在飞行器的机翼下方的燃气涡轮发动机具有在第一轴线上旋转的推进器和包括压缩机部分，燃烧器部分和涡轮部分的发动机核心，其中涡轮机部分更靠近推进器， 压缩机部分。 发动机机芯与空气动力学连接，并具有第二轴。 机舱位于推进器和发动机内核周围。 机舱附着在飞机的机翼上。 机舱的下游端具有至少一个枢转门，其具有致动机构，以使门在收起位置和水平展开位置之间枢转，门中阻止流动以提供逆流。

公开(公告)号：US20140250863A1

公开(公告)日：2014-09-11

申请号：US14190171

申请日：2014-02-26

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Brian D. Merry

IPC: F02K1/62

CPC classification number: F02K1/60 ,  F05D2210/40 ,  F05D2250/314

Abstract: In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

Abstract translation: 在一个实施例中，用于安装到飞行器机身后部的燃气涡轮发动机具有在第一轴线上旋转的推进器，以及包括压缩机部分，燃烧器部分和涡轮部分的发动机芯，涡轮部分是 比压缩机部分更靠近推进器。 发动机机芯与空气动力学连接，并具有第二轴。 机舱位于推进器和发动机内核周围。 机舱附着在飞机的机翼上。 机舱的下游端具有至少一个枢转门，其具有致动机构，以使门在收起位置和垂直展开位置之间枢转，门中阻止流动以提供逆流。

公开(公告)号：US20140248129A1

公开(公告)日：2014-09-04

申请号：US14067354

申请日：2013-10-30

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Lisa I. Brilliant ,  Becky E. Rose ,  Yuan Dong ,  Stanley J. Balamucki

IPC: F02C3/13

CPC classification number: F02C3/13 ,  F01D5/143 ,  F01D25/162 ,  F02C7/36 ,  F02C9/18 ,  F02K3/04 ,  Y02T50/673

Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.

Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流路的入口壳体和中间壳体。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分布置在轴向上在入口壳体流动路径和中间壳体流动路径之间的芯流动路径中。 核心流路具有内径和外径。 内径的至少一部分相对于旋转轴具有增加的倾斜角。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。