公开(公告)号：US20140183296A1

公开(公告)日：2014-07-03

申请号：US13731371

申请日：2012-12-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64D27/14 ,  F02K3/02

CPC classification number: B64D27/14 ,  B64D27/02 ,  F02K3/025 ,  F02K3/06 ,  F02K3/077

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：US20140117152A1

公开(公告)日：2014-05-01

申请号：US13662879

申请日：2012-10-29

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: B64D27/14 ,  F02K3/02

CPC classification number: B64D27/14 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles, with each of the nacelles receiving a fan rotor. The fan rotor is fixed to rotate with a tip turbine mounted at a radially outer location of the fan rotor, with the tip turbine being in the path of gases from the manifold. An aircraft is also disclosed.

Abstract translation: 燃气涡轮发动机具有并入涡轮机的核心发动机和位于涡轮机下游的歧管。 歧管将涡轮下游的气体输送到至少两个机舱中，其中每个机舱都接收风扇转子。 风扇转子被固定以与安装在风扇转子的径向外部位置处的尖端涡轮一起旋转，其中尖端涡轮机处于来自歧管的气体的路径中。 还披露了一架飞机。

公开(公告)号：US11808210B2

公开(公告)日：2023-11-07

申请号：US15978517

申请日：2018-05-14

Applicant: United Technologies Corporation

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

IPC: F02C7/18 ,  F02C3/04 ,  F02C7/32 ,  F02C9/18

CPC classification number: F02C7/185 ,  F02C3/04 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/323 ,  F05D2240/90 ,  F05D2260/213 ,  F05D2260/4031

Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A tap connects to the compressor section. A heat exchanger connects downstream of the tap. A cooling compressor connects downstream of the heat exchanger, and the cooling compressor connects to deliver air to at least one of the rotating components. A core housing has an outer peripheral surface and a fan housing defines an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is disposed within the at least one bifurcation duct.

公开(公告)号：US20210207530A1

公开(公告)日：2021-07-08

申请号：US16733504

申请日：2020-01-03

Applicant: United Technologies Corporation

Inventor： Marc J. Muldoon ,  Joseph B. Staubach ,  Jesse M. Chandler ,  Neil Terwilliger ,  Gabriel L. Suciu

IPC: F02C6/20

Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.

公开(公告)号：US10711631B2

公开(公告)日：2020-07-14

申请号：US14976876

申请日：2015-12-21

Applicant: United Technologies Corporation

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

IPC: F01D1/02 ,  F01D17/10 ,  F01D7/00 ,  F01D5/02 ,  F01D9/04 ,  F01D25/24 ,  F02C3/107 ,  F02C3/14

Abstract: A turbine engine such as a pusher fan engine is provided. This turbine engine includes a nacelle with a bypass flowpath. A fan rotor is configured to propel air out of the bypass flowpath. A plurality of guide vanes are configured to direct the air to the fan rotor.

公开(公告)号：US10443429B2

公开(公告)日：2019-10-15

申请号：US15111553

申请日：2015-01-20

Applicant: UNITED TECHNOLOGIES CORPORATION

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

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

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.

公开(公告)号：US20190309705A1

公开(公告)日：2019-10-10

申请号：US15945907

申请日：2018-04-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02K5/00 ,  F04D19/02 ,  F04D25/06

Abstract: A boundary layer ingestion engine includes a fan section configured to extend into a boundary layer of a full annulus of an aft end of a fuselage of an aircraft. The fan section includes a first fan stage and a second fan stage. The boundary layer ingestion engine also includes a differential planetary gear system is operable to transform rotation of an input shaft into counter rotation of a first shaft coupled to the first fan stage and a second shaft coupled to the second fan stage. The boundary layer ingestion engine further includes a motor operable to drive rotation of the input shaft.

公开(公告)号：US10428740B2

公开(公告)日：2019-10-01

申请号：US15373072

申请日：2016-12-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02C7/36 ,  B64D27/16 ,  B64D27/00 ,  B64D27/14 ,  B64D35/00 ,  F02K3/04 ,  B64D33/02

Abstract: A propulsion system for an aircraft has at least two fans with each fan having a fan drive shaft. A turboshaft gas turbine engine drives each of the at least two fans. The turboshaft engine drives an output shaft which drives a gear to, in turn, engage to drive a gear on a first intermediate shaft extending from the turboshaft gas turbine engine in a rearward direction toward an intermediate fan drive shaft. The intermediate fan drive shaft drives the fan drive shaft, and the at least two first intermediate drive shafts extending over a distance that is greater in an axial dimension defined between the turboshaft gas turbine engine and the fan than it is in a width dimension defined between the at least two fans.

公开(公告)号：US10421554B2

公开(公告)日：2019-09-24

申请号：US14874560

申请日：2015-10-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Wesley K. Lord ,  Alan H. Epstein ,  Steven M. O'Flarity

IPC: B64D35/06 ,  B64D27/20 ,  B64D27/14

Abstract: A drive arrangement for an aircraft comprises a pair of propulsor units each having a fan and a fan shaft for driving the fan. A core engine has a turbine driving a core engine shaft. A mechanical connection connects the core engine shaft to drive the fan shafts for each of the propulsor units. An aircraft also has such an arrangement.

公开(公告)号：US10414509B2

公开(公告)日：2019-09-17

申请号：US15439988

申请日：2017-02-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64D27/00 ,  B64D27/26 ,  B64D27/20 ,  B64D35/04

Abstract: A propulsor and mount arrangement comprises a propulsor rotor and a fan casing surrounding the propulsor rotor. The fan casing receives two side mounts and a thrust link pivotally attached to the fan casing at a location that will be within 10° of a vertically lowermost location when the propulsor is mounted on an aircraft, and the side mounts being at circumferentially opposed positions, and within a lower 270° when the propulsor is mounted on an aircraft. At least a portion of both the side mounts, and a pivot point connect the thrust link to the fan casing in a common plane defined perpendicular to a rotational axis of the propulsor rotor. An aircraft is also disclosed.