公开(公告)号：US09637218B2

公开(公告)日：2017-05-02

申请号：US14440753

申请日：2013-03-14

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: B64C39/12 ,  B64C5/02 ,  B64D33/04 ,  B64C5/06 ,  B64D27/20 ,  F02K1/62 ,  B64D41/00

CPC classification number: B64C5/02 ,  B64C5/06 ,  B64D27/20 ,  B64D33/04 ,  B64D41/00 ,  F02K1/62

Abstract: An aircraft includes a propulsor supported within an aft portion of the fuselage. A thrust reverser is supported proximate the propulsor for redirecting thrust forward to slow the aircraft upon landing. A tail extending from the aft portion of the fuselage is angled forward away from the aft portion and out of the discharge of airflow from the thrust reverser.

公开(公告)号：US09611034B1

公开(公告)日：2017-04-04

申请号：US14930712

申请日：2015-11-03

Applicant: United Technologies Corporation

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

IPC: B64C21/08 ,  B64D33/02 ,  B64D27/20

CPC classification number: B64C21/08 ,  B64C2230/06 ,  B64D27/20 ,  B64D33/02 ,  B64D2033/0226 ,  B64D2033/0253 ,  Y02T50/166

Abstract: An arrangement for reducing drag on the body of an aircraft with a relatively wide fuselage comprises a gas turbine engine. At least one duct is selectively moveable between a closed position and an open position, such that the at least one duct allows airflow to move toward a fan rotor in the gas turbine engine in the open position, but blocks airflow when in the closed position. An aircraft body is also disclosed.

公开(公告)号：US09574520B2

公开(公告)日：2017-02-21

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: F02K1/54 ,  F02K1/70 ,  B64D33/04 ,  B64D29/06

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：US20170044992A1

公开(公告)日：2017-02-16

申请号：US15292472

申请日：2016-10-13

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph Brent Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C9/18 ,  F01D11/12 ,  F02K3/06 ,  F02K3/075 ,  F02C7/36 ,  F02C3/107

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D11/122 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C7/20 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F04D19/02 ,  F05B2250/283 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

公开(公告)号：US20160348591A1

公开(公告)日：2016-12-01

申请号：US14566840

申请日：2014-12-11

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Frederick M. Schwarz

IPC: F02C7/36 ,  F04D29/32 ,  F02K3/06 ,  F01D9/04 ,  F01D25/24 ,  F02C3/04 ,  F04D25/04

CPC classification number: F02C7/36 ,  F01D9/041 ,  F01D9/042 ,  F01D25/16 ,  F01D25/168 ,  F01D25/246 ,  F01D25/28 ,  F02C3/04 ,  F02K3/06 ,  F04D25/045 ,  F04D29/321 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/40311 ,  F05D2260/606

Abstract: A gas turbine engine turbine comprises a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis. A low pressure turbine is configured to rotate with a low pressure compressor as a low pressure spool in a second direction about the central axis. A mid-turbine frame supports the high pressure turbine. The mid-turbine frame includes a first bearing supporting the high pressure turbine, and a strut supporting the first bearing at a location between the high pressure turbine and the low pressure turbine. A plurality of vanes are associated with a first stage of the low pressure turbine. The plurality of vanes are positioned within the mid-turbine frame.

Abstract translation: 燃气涡轮发动机涡轮机包括高压涡轮机，其构造成以围绕中心轴线的第一方向的高压压缩机作为高压压力机旋转。 低压涡轮机被构造成以低压压缩机作为低压阀芯在围绕中心轴线的第二方向上旋转。 中涡轮机架支撑高压涡轮机。 中间涡轮机框架包括支撑高压涡轮机的第一轴承和在高压涡轮机和低压涡轮机之间的位置处支撑第一轴承的支柱。 多个叶片与低压涡轮机的第一级相关联。 多个叶片位于中涡轮机框架内。

公开(公告)号：US20160341149A1

公开(公告)日：2016-11-24

申请号：US15230086

申请日：2016-08-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  T. David Bomzer

IPC: F02K1/60 ,  F02K1/62 ,  F02K1/76 ,  F01D25/24 ,  F02C3/04

CPC classification number: F02K1/605 ,  F01D25/24 ,  F02C3/04 ,  F02K1/60 ,  F02K1/62 ,  F02K1/625 ,  F02K1/64 ,  F02K1/70 ,  F02K1/72 ,  F02K1/763 ,  F02K1/766 ,  F05D2220/32 ,  F05D2230/72 ,  F05D2240/14 ,  F05D2270/051

Abstract: A gas turbine engine 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. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, arranged aft of the first portion and coupled to the rail. The second annular portion 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 the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion.

公开(公告)号：US20160326906A1

公开(公告)日：2016-11-10

申请号：US14704631

申请日：2015-05-05

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Gabriel L. Suciu

IPC: F01D25/12 ,  F01D25/18

CPC classification number: F01D25/12 ,  B64C11/14 ,  F01D25/18 ,  F02C7/04 ,  F02C7/06 ,  F02C7/14 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/40311 ,  F05D2260/98 ,  Y02T50/676

Abstract: An oil cooling system is provided. The system may comprise an oil inlet, a manifold fluidly coupled to the oil inlet, and a support strut comprising internal tubing fluidly coupled to the manifold. A heat exchanger may be fluidly coupled to the internal tubing of the support strut. A nose cone may be disposed forward of the heat exchanger and configured to rotate about an axis. The heat exchanger may be radially inward from a portion of the nose cone. A gas turbine engine is also provided. The gas turbine engine may comprise an epicyclic gear system and fan mechanically coupled to the epicyclic gear system. The fan may be configured to rotate about an axis. A nose cone may be coupled to the fan and configured to rotate about the axis. A heat exchanger may be aft of the fan and in fluid communication with the epicyclic gear system.

Abstract translation: 提供油冷却系统。 该系统可以包括油入口，流体地联接到油入口的歧管和包括流体地联接到歧管的内部管的支撑支柱。 热交换器可以流体地联接到支撑支柱的内部管道。 鼻锥可以设置在热交换器的前方并且被配置为围绕轴线旋转。 热交换器可以从鼻锥的一部分径向向内。 还提供燃气涡轮发动机。 燃气涡轮发动机可以包括机械地联接到行星齿轮系统的行星齿轮系统和风扇。 风扇可以被配置为绕轴线旋转。 鼻锥可以联接到风扇并且构造成围绕轴线旋转。 热交换器可以是风扇的后部并且与行星齿轮系统流体连通。

公开(公告)号：US20160298543A1

公开(公告)日：2016-10-13

申请号：US14685240

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  William G. Sheridan

IPC: F02C7/14 ,  F01D25/20 ,  F02C7/18

Abstract: A lubricant circulation system and method of circulating lubricant in a gas turbine engine are disclosed. The lubricant circulation system includes a nose cone having an aperture communicating air to an interior space of the nose cone, a heat exchanger disposed in the interior space, and a lubricant circulation pathway contained within a forward portion of the gas turbine engine and configured to circulate lubricant through the heat exchanger.

Abstract translation: 公开了一种在燃气轮机中循环润滑剂的润滑剂循环系统和方法。 润滑剂循环系统包括鼻锥体，其具有将空气连通到鼻锥体的内部空间的孔口，设置在内部空间中的热交换器和容纳在燃气涡轮发动机的前部中并被配置为循环的润滑剂循环路径 润滑剂通过热交换器。

公开(公告)号：US20160237909A1

公开(公告)日：2016-08-18

申请号：US14837009

申请日：2015-08-27

Applicant: United Technologies Corporation

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

IPC: F02C7/18 ,  F02K3/075 ,  F02K3/065 ,  F02C3/04 ,  F02K3/02

CPC classification number: F02C7/185 ,  F02C3/04 ,  F02C6/08 ,  F02C7/277 ,  F02C7/32 ,  F02K3/025 ,  F02K3/065 ,  F02K3/075 ,  F05D2260/213 ,  Y02T50/671 ,  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. The cooling compressor is connected to be driven with at least one rotor in the main compressor section. A source of pressurized air is selectively sent to the cooling compressor to drive a rotor of the cooling compressor to rotate, and to in turn drive the at least one rotor of the main compressor section at start-up of the gas turbine engine. An intercooling system is also disclosed.

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。 冷却压缩机被连接以在主压缩机部分中用至少一个转子驱动。 加压空气源被选择性地送到冷却压缩机以驱动冷却压缩机的转子旋转，并且在燃气涡轮发动机起动时又驱动主压缩机段的至少一个转子。 还公开了一种中间冷却系统。

公开(公告)号：US20160237908A1

公开(公告)日：2016-08-18

申请号：US14804534

申请日：2015-07-21

Applicant: United Technologies Corporation

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

IPC: F02C7/18

CPC classification number: F02C6/08 ,  F02C7/143 ,  F02C7/185 ,  F02C7/32 ,  F05D2260/213 ,  Y02T50/671 ,  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, passing 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. The heat exchanger also receives air to be delivered to an aircraft cabin. An intercooling system for a gas turbine engine is also disclosed.

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，使抽头的空气通过热交换器，然后通过冷却压缩机。 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。 热交换器还接收要传送到飞机机舱的空气。 还公开了一种用于燃气涡轮发动机的中间冷却系统。