公开(公告)号：US20170044991A1

公开(公告)日：2017-02-16

申请号：US15118565

申请日：2014-09-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C9/18 ,  F01D25/24 ,  F04D29/54 ,  F02C7/052 ,  F04D29/52 ,  F04D29/58

CPC classification number: F02C9/18 ,  F01D25/162 ,  F01D25/24 ,  F02C6/08 ,  F02C7/052 ,  F02C7/25 ,  F04D29/522 ,  F04D29/542 ,  F04D29/5853 ,  F04D29/701 ,  F05D2220/32 ,  F05D2240/15

Abstract: A compressor intermediate case for a gas turbine engine includes a plurality of intermediate case struts joining the compressor intermediate case to an inner engine structure. Each strut of the plurality of intermediate case struts includes a leading edge. A turning scoop is disposed at the leading edge of each strut of the plurality of intermediate case struts. A plurality of diffusers extends radially outwardly from the compressor intermediate case so that each diffuser of the plurality of diffusers engages with a corresponding turning scoop. A substantially annular structural fire wall extends radially outwardly from the compressor intermediate case. An environmental control system manifold is disposed on the compressor intermediate case. The environmental control system manifold includes an exit port.

Abstract translation: 用于燃气涡轮发动机的压缩机中间壳体包括将压缩机中间壳体连接到内部发动机结构的多个中间壳体支柱。 多个中间壳支柱的每个支柱包括前缘。 在多个中间壳支柱的每个支柱的前缘设置有转向铲。 多个扩散器从压缩机中间壳体径向向外延伸，使得多个扩散器的每个扩散器与相应的转向勺接合。 大致环形的结构防火墙从压缩机中间壳径向向外延伸。 环境控制系统歧管设置在压缩机中间壳体上。 环境控制系统歧管包括出口。

公开(公告)号：US20160333728A1

公开(公告)日：2016-11-17

申请号：US15111553

申请日：2015-01-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Federico Papa

IPC: F01D17/14 ,  F01D25/26 ,  F02C9/18 ,  F02C3/04 ,  F02C7/18

CPC classification number: F01D17/145 ,  F01D25/26 ,  F02C3/04 ,  F02C7/18 ,  F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/608 ,  Y02T50/675

Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.

Abstract translation: 一种燃气涡轮发动机包括一个核心发动机壳体。 机舱位于核心发动机壳体的径向外侧。 外部旁路外壳位于机舱的外侧。 至少有一个待冷却的附件定位在径向位于核心发动机壳体和机舱之间的腔室中。 歧管将冷却空气提供到腔室中，并且围绕核心发动机的中心轴线周向延伸。 机舱在圆周范围内具有不对称的流动横截面。

公开(公告)号：US20160298540A1

公开(公告)日：2016-10-13

申请号：US14685325

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Harold W. Hipsky ,  Thomas M. Zywiak

IPC: F02C7/04

CPC classification number: F02C7/04 ,  B64C11/14 ,  F01D25/12 ,  F02C7/14 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/213

Abstract: A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone.

Abstract translation: 公开了一种用于燃气涡轮发动机的鼻锥组件和在燃气涡轮发动机中循环空气的方法。 鼻锥组件包括鼻锥体，其具有将空气连通到鼻锥体的内部空间的孔口，以及将空气从鼻锥体延伸出来的排出构件。

公开(公告)号：US20160207631A1

公开(公告)日：2016-07-21

申请号：US14600946

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Wesley K. Lord ,  Jesse M. Chandler

IPC: B64D27/18 ,  F02C7/20 ,  B64D29/02 ,  B64D33/02 ,  B64C3/32

Abstract: An aircraft is provided that includes a wing and a pusher fan engine. The pusher fan engine is configured in the wing.

Abstract translation: 提供一种包括机翼和推进器风扇发动机的飞机。 推进器风扇发动机配置在机翼中。

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

IPC: B64D27/12 ,  B64D35/02 ,  B64C3/00 ,  F02C3/10 ,  F02C7/36

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。

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

IPC: B64C3/14 ,  B64C39/10 ,  B64C39/12

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。

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

IPC: B64D33/04 ,  F02K1/54 ,  B64C5/02

CPC classification number: B64D33/04 ,  B64C5/02 ,  B64C5/06 ,  B64D27/20 ,  F02K1/54 ,  F02K1/62

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。

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

IPC: B64C1/26 ,  B64C5/02 ,  B64C1/06

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。

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

IPC: F02C3/14 ,  F02C6/02 ,  F02C3/06

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。

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。