公开(公告)号：WO2014078006A1

公开(公告)日：2014-05-22

申请号：PCT/US2013/065417

申请日：2013-10-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M.

IPC: B64C5/00 ,  B64C5/02 ,  B64D27/14 ,  B64C15/02

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，主要控制表面保持飞行器的可控性。

公开(公告)号：WO2014058710A1

公开(公告)日：2014-04-17

申请号：PCT/US2013/063288

申请日：2013-10-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： LEVASSEUR, Glenn ,  SUCIU, Gabriel L. ,  STETSON, Gary M.

IPC: F02C9/22 ,  F01D17/16

CPC classification number: F01D17/162 ,  F02C7/36 ,  F02C9/20 ,  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：WO2014007884A3

公开(公告)日：2014-01-09

申请号：PCT/US2013/034024

申请日：2013-03-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  PICKFORD, Simon ,  ACKERMANN, William K. ,  SNAPE, Nathan ,  HIPSKY, Harold W.

IPC: F02C7/18 ,  F02C7/12

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine. The nose cone provides an aperture that communicates air to an interior of the nose cone.

公开(公告)号：WO2013180788A3

公开(公告)日：2013-12-05

申请号：PCT/US2013/030123

申请日：2013-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian D. ,  GLAHN, Jorn A. ,  DYE, Christopher M.

IPC: F02C7/32 ,  F02C7/00 ,  F04D25/02

Abstract: A gas turbine engine has an impeller pump for delivering air to an environmental control system and a speed control pump connected to the impeller pump for driving the impeller pump at a constant speed.

公开(公告)号：WO2013130245A1

公开(公告)日：2013-09-06

申请号：PCT/US2013/025506

申请日：2013-02-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  ALVANOS, Ioannis

IPC: F01D9/02 ,  F01D25/08 ,  F02C7/12

CPC classification number: F02C6/08 ,  F01D5/08 ,  F02C7/08

Abstract: A gas turbine engine includes a heat exchanger, a diffuser case, a passageway and a nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The diffuser case includes a plenum that receives the conditioned airflow. The passageway is fluidly connected between the heat exchanger and the diffuser case, and the conditioned airflow is communicated through the passageway and into the plenum. The nozzle assembly is in fluid communication with the plenum of the diffuser case to receive the conditioned airflow from the plenum.

Abstract translation: 燃气涡轮发动机包括热交换器，扩散器壳体，通道和喷嘴组件。 热交换器与放气气流交换热量以提供调节气流。 扩散器壳体包括容纳调节气流的增压室。 通道流体地连接在热交换器和扩散器壳体之间，并且经调节的气流通过通道连通并进入通风室。 喷嘴组件与扩散器壳体的气室流体连通以接收来自气室的经调节的气流。

公开(公告)号：WO2013119535A1

公开(公告)日：2013-08-15

申请号：PCT/US2013/024720

申请日：2013-02-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  DYE, Christopher ,  STAUBACH, Joseph B.

IPC: F02K3/06 ,  F02K3/02 ,  F02K5/00 ,  F02C7/00

CPC classification number: F02K3/06 ,  F02C3/107 ,  F02C7/04 ,  F02C7/36 ,  F05D2210/40 ,  F05D2250/313 ,  F05D2250/314 ,  Y10T29/4932 ,  Y10T29/49323

Abstract: A separate propulsion unit incorporating a free turbine and a fan receives gases from a plurality of core engines. The core engines each include a compressor, a turbine and a combustion section. The core engines in combination pass gases across the free turbine. A method is also disclosed.

Abstract translation: 结合有自由涡轮机和风扇的单独的推进单元接收来自多个核心发动机的气体。 核心发动机各自包括压缩机，涡轮机和燃烧部分。 核心发动机组合通过自由涡轮机的气体。 还公开了一种方法。

公开(公告)号：WO2013116028A1

公开(公告)日：2013-08-08

申请号：PCT/US2013/022395

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  SCHWARZ, Frederick

IPC: F02C7/00

CPC classification number: F01D25/162 ,  F02C3/107 ,  F02C7/20 ,  F02K3/06 ,  F02K3/072 ,  Y02T50/671

Abstract: A mid-turbine frame is incorporated into a turbine section of a gas turbine engine intermediate a high pressure turbine and a low pressure turbine. The high pressure and low pressure turbines rotate in opposite directions. The mid-turbine frame carries a plurality of vanes to redirect the flow downstream of the high pressure turbine as it approaches the low pressure turbine. In another feature, a power density is defined as the thrust divided by the volume of a turbine section, and the power density is of about 1.5 lbf per in 3 .

Abstract translation: 中间涡轮机框架结合到高压涡轮机和低压涡轮机中间的燃气涡轮发动机的涡轮机部分中。 高压和低压涡轮机在相反方向旋转。 中间涡轮机框架承载多个叶片，以在高压涡轮机接近低压涡轮机时重新定向流向下游的流。 在另一个特征中，功率密度被定义为推力除以涡轮机部分的体积，并且功率密度约为每磅1/3磅。

公开(公告)号：WO2006060011A1

公开(公告)日：2006-06-08

申请号：PCT/US2004/040210

申请日：2004-12-01

Applicant: UNITED TECHNOLOGIES CORPORATION ,  SUCIU, Gabriel L. ,  MERRY, Brian ,  PORTLOCK, Lawrence

Inventor： SUCIU, Gabriel L. ,  MERRY, Brian ,  PORTLOCK, Lawrence

IPC: F02K3/068 ,  F02C3/08 ,  F02K3/02 ,  F02C3/073 ,  F02C7/36 ,  F02C7/32

CPC classification number: F02C7/32 ,  F02C3/073 ,  F02C3/08 ,  F02C7/36 ,  F02K3/02 ,  F02K3/068 ,  F05D2260/40311

Abstract: A non-rotating compartment along an engine centerline of a tip turbine engine is defined between an inner support housing, an outer support housing and an aft housing. The non-rotating compartment provides a space that may be utilized for a multitude of engine accessories and components including an engine lubricating fluid system.

Abstract translation: 沿着顶部涡轮发动机的发动机中心线的非旋转舱被限定在内部支撑壳体，外部支撑壳体和后部壳体之间。 非旋转隔室提供可用于多个发动机附件和部件的空间，包括发动机润滑流体系统。

公开(公告)号：WO2006060006A1

公开(公告)日：2006-06-08

申请号：PCT/US2004/040176

申请日：2004-12-01

Applicant: UNITED TECHNOLOGIES CORPORATION ,  SUCIU, Gabriel L. ,  NORRIS, James W. ,  MERRY, Brian

Inventor： SUCIU, Gabriel L. ,  NORRIS, James W. ,  MERRY, Brian

IPC: F02K1/04 ,  F02C3/073 ,  F02K3/068

CPC classification number: F02C3/073 ,  F02K1/04 ,  F02K3/068 ,  F05D2300/603 ,  F05D2300/614 ,  Y02T50/672 ,  Y10T29/49346

Abstract: A non-metallic tailcone (202) in a tip turbine engine includes a tapered wall structure disposed (208) about a central axis. The non-metallic tailcone is fastened to a structural frame (44) in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.

Abstract translation: 尖端涡轮发动机中的非金属尾筒（202）包括围绕中心轴线设置（208）的锥形壁结构。 非金属尾管紧固在顶端涡轮发动机的后部的结构框架（44）上。 尖端涡轮发动机产生来自第一输出源的第一温度气体流和来自第二输出源的第二温度气体流。 第二温度气体流是比第一温度气体流更低的温度。 第二温度气流在末端涡轮发动机的内径处在尾骨的外表面上排出。 在内径处排出较冷的第二温度气流允许非金属物质用于形成尾骨。

公开(公告)号：WO2006060004A1

公开(公告)日：2006-06-08

申请号：PCT/US2004/040171

申请日：2004-12-01

Applicant: UNITED TECHNOLOGIES CORPORATION ,  SUCIU, Gabriel L. ,  NORDEEN, Craig A. ,  KRAMER, Stephen

Inventor： SUCIU, Gabriel L. ,  NORDEEN, Craig A. ,  KRAMER, Stephen

IPC: F23R3/28

CPC classification number: F23R3/286 ,  F02C3/073 ,  F02K3/068 ,  F23R3/28 ,  F23R3/50

Abstract: A turbine engine includes an annular combustor having a combustion chamber defined between an annular outer wall and an annular inner wall. A diffuser case substantially encloses the annular outer and inner walls. A fuel nozzle extends through the diffuser case to an outlet that provides fuel to an interior chamber of the combustor. In one embodiment, front portions of the inner and outer walls curve toward one another and overlap to form an annular gap or manifold through which fuel is distributed to the combustion chamber.

Abstract translation: 涡轮发动机包括具有限定在环形外壁和环形内壁之间的燃烧室的环形燃烧器。 扩散器壳体基本上包围环形的外壁和内壁。 燃料喷嘴通过扩散器壳体延伸到向燃烧器的内部室提供燃料的出口。 在一个实施例中，内壁和外壁的前部部分彼此相对弯曲并重叠以形成环形间隙或歧管，燃料通过该间隙或歧管分配到燃烧室。