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公开(公告)号：WO2014018141A3
公开(公告)日：2014-01-30
申请号：PCT/US2013/037674
申请日：2013-04-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel, L. , SCHWARZ, Frederick, M.
Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool and the fan drive turbine configured to rotate in the same first direction. The intermediate speed spool rotates in an opposed, second direction.
Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩至比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二个涡轮驱动压缩机转子。 风扇驱动涡轮机定位在第二涡轮机转子的下游。 风扇驱动涡轮通过齿轮减速来驱动风扇。 第一压缩机转子和第二涡轮机转子作为中速卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速卷轴。 高速阀芯和风扇驱动涡轮被构造成以相同的第一方向旋转。 中速阀芯沿相反的第二方向旋转。
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公开(公告)号：WO2013138103A1
公开(公告)日：2013-09-19
申请号：PCT/US2013/029000
申请日：2013-03-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel, L. , ALVANOS, Ioannis , MERRY, Brian, D.
Abstract: A mount for a turbine engine has a semi-circular yoke with a first leg and a second leg. The mount also has a stanchion with a cylindrical section attached to the yoke, and a conical section attached to the cylindrical section. A mounting bracket is attached to the conical section.
Abstract translation: 用于涡轮发动机的安装座具有带有第一腿和第二腿的半圆形轭。 安装座还具有支柱，其具有附接到轭的圆柱形部分，以及附接到圆柱形部分的锥形部分。 安装支架连接到锥形部分。
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公开(公告)号：WO2014099365A1
公开(公告)日：2014-06-26
申请号：PCT/US2013/072993
申请日：2013-12-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel, L. , CHANDLER, Jesse, M. , MERRY, Brian, D.
CPC classification number: F01D5/225 , F01D5/34 , F01D21/045 , F04D29/023 , F04D29/321 , F05D2220/36 , F05D2230/53 , F05D2260/96 , F05D2300/121 , F05D2300/133 , F05D2300/173 , F05D2300/174 , F05D2300/603 , F05D2300/614 , Y02T50/672
Abstract: An integrally bladed rotor for use in a gas turbine engine includes a central hub; a plurality of airfoils extending from the central hub, each airfoil with a tip, a leading edge and a trailing edge; and a shroud with a metallic portion connecting to the tip of each airfoil to rotate with the airfoils.
Abstract translation: 用于燃气涡轮发动机的整体叶片转子包括中心毂; 从中心毂延伸的多个翼型件，每个翼型件具有尖端，前缘和后缘; 以及具有连接到每个翼型件的尖端以与翼型件一起旋转的金属部分的护罩。
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公开(公告)号：WO2014081493A9
公开(公告)日：2014-05-30
申请号：PCT/US2013/057080
申请日：2013-08-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SNAPE, Nathan , SUCIU, Gabriel, L. , PICKFORD, Simon , PENDA, Allan, R.
IPC: F02C7/141
Abstract: An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.
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公开(公告)号：WO2013162666A1
公开(公告)日：2013-10-31
申请号：PCT/US2013/025022
申请日：2013-02-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel, L. , ALVANOS, Ioannis
IPC: B64D27/00
CPC classification number: F02C7/20 , B64D27/26 , B64D2027/264
Abstract: A mounting apparatus for a turbine exhaust case (TEC) is provided. The mounting apparatus may include a neck, support links and a plurality of fastening pins. The neck may include an upper portion that is receivable within a pylon associated with the TEC and at least one neck aperture extending therethrough. The support links may downwardly extend from a lower portion of the neck. The support links may be configured to at least partially receive a section of the TEC. Each support link may include at least one link aperture extending therethrough. The fastening pins may include at least one neck pin extending through the neck aperture and at least one link pin extending through the link aperture of each support link.
Abstract translation: 提供了一种用于涡轮机排气箱（TEC）的安装装置。 安装设备可以包括颈部，支撑连杆和多个紧固销。 颈部可以包括可接收在与TEC相关联的挂架内的上部和延伸穿过其的至少一个颈孔。 支撑连杆可以从颈部的下部向下延伸。 支持链路可以被配置为至少部分地接收TEC的一部分。 每个支撑连杆可以包括延伸穿过其中的至少一个连杆孔。 紧固销可以包括延伸穿过颈部孔的至少一个颈销和延伸穿过每个支撑连杆的连杆孔的至少一个连杆销。
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Patent Agency Ranking
公开(公告)号：WO2006110122A2
公开(公告)日：2006-10-19
申请号：PCT/US2004/039989
申请日：2004-12-01
Applicant: UNITED TECHNOLOGIES CORPORATION , SUCIU, Gabriel, L. , PORTLOCK, Lawrence, E. , MERRY, Brian
Inventor： SUCIU, Gabriel, L. , PORTLOCK, Lawrence, E. , MERRY, Brian
IPC: F16K7/10 , F16K7/12 , F16K31/126 , F01D17/14 , F02C9/18
CPC classification number: F16K7/10 , F01D5/022 , F01D17/14 , F01D17/141 , F01D17/143 , F02C3/073 , F02C3/14 , F02C6/08 , F02C9/18 , F02K3/068 , F04D27/0215 , F04D27/023 , F05D2300/501 , F16K7/123 , F16K31/1266
Abstract: A compressor for a turbine engine includes an inflatable bleed valve that selectively bleeds core airflow from the compressor. The bleed valve has an inlet leading from the compressor and a passageway leading from the inlet. An inflatable valve selectively obstructs the passageway based upon a controlled supply of high pressure air to the inflatable valve. The supply of high pressure air may be compressed core airflow from an area downstream of the inlet to the bleed valve.
Abstract translation: 一种用于涡轮发动机的压缩机包括一个可充气放气阀，其选择性地从压缩机中排出核心气流。 排放阀具有从压缩机引出的入口和从入口通过的通道。 充气阀基于向可充气阀的受控供应高压空气来选择性地阻塞通道。 高压空气的供应可以是从入口下游到排放阀的压缩空气流。
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7.发明申请VARIABLE FAN INLET GUIDE VANE ASSEMBLY, TURBINE ENGINE WITH SUCH AN ASSEMBLY AND CORRESPONDING CONTROLLING METHOD 审中-公开可变风扇入口导向风扇组件，具有这种组件的涡轮发动机和相应的控制方法
公开(公告)号：WO2006060000A1
公开(公告)日：2006-06-08
申请号：PCT/US2004/040152
申请日：2004-12-01
Applicant: UNITED TECHNOLOGIES CORPORATION , SUCIU, Gabriel, L. , MERRY, Brian , NORRIS, James, W. , SIRICA, Steven, J.
Inventor： SUCIU, Gabriel, L. , MERRY, Brian , NORRIS, James, W. , SIRICA, Steven, J.
CPC classification number: F01D17/162 , F02C3/073 , F02K3/068
Abstract: A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.
Abstract translation: 涡轮发动机包括多个可变风扇入口导向叶片。 在涡轮发动机是顶端涡轮发动机的情况下，即使风扇 - 涡轮转子组件以固定的速率直接联接到轴向压缩机，可变风扇入口导叶允许控制发动机稳定性的能力。 风扇入口导向叶片可以从风扇入口导叶的内径致动。
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公开(公告)号：WO2015122934A1
公开(公告)日：2015-08-20
申请号：PCT/US2014/056200
申请日：2014-09-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel, L. , CHANDLER, Jesse, M.
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。
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公开(公告)号：WO2014035514A1
公开(公告)日：2014-03-06
申请号：PCT/US2013/044009
申请日：2013-06-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SHAH, Dilip, M. , CHIN, Herbert, A. , MARCIN, John, Joseph , REYNOLDS, Paul, L. , SUCIU, Gabriel, L. , GENEREUX, Paul, D.
CPC classification number: C21D9/085 , B22D27/045 , C21D1/26 , C21D8/105 , C22C19/03 , C22C19/056 , C22C38/00 , C22F1/10 , C30B29/52 , C30B33/02 , F01D5/02 , F05D2220/323 , F05D2230/40 , F05D2240/60 , F05D2300/171 , F05D2300/501 , F05D2300/606 , Y02T50/672
Abstract: High modulus turbine shafts and high modulus cylindrical articles are described as are the process parameters for producing these shafts and cylindrical articles. The shafts/articles have a high Young's modulus as a result of having high modulus crystal texture along the longitudinal axis of the shaft/article. The shafts are produced from directionally solidified seeded single crystal cylinders that are axisymmetrically hot worked before a limited recrystallization process is carried out at a temperature below the recrystallization temperature of the alloy. The disclosed process produces an intense singular texture and results in shaft or cylindrical article with a Young's modulus that is at least 40% greater than that of conventional nickel or iron alloys or conventional steels.
Abstract translation: 高模量涡轮轴和高模量圆柱形制品也被描述为用于生产这些轴和圆柱形制品的工艺参数。 轴/制品由于沿轴/制品的纵向轴线具有高模量<111>晶体结构而具有高的杨氏模量。 这些轴由在低于合金的再结晶温度的温度下进行有限再结晶过程之前轴对称加热的定向凝固的接种<111>单晶圆柱体制成。 所公开的方法产生强烈的单数<111>纹理，并导致具有比常规镍或铁合金或常规钢至少大40％的杨氏模量的轴或圆柱形制品。
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10.发明申请COUNTER ROTATING LOW PRESSURE COMPRESSOR AND TURBINE EACH HAVING A GEAR SYSTEM 审中-公开逆向压缩机和涡轮机，具有齿轮系统
公开(公告)号：WO2013187944A2
公开(公告)日：2013-12-19
申请号：PCT/US2013/027550
申请日：2013-02-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel, L. , MERRY, Brian, D.
CPC classification number: F02K3/072 , F02C3/113 , F02C7/36 , F05D2250/36 , F05D2260/40311 , Y02T50/671
Abstract: A compressor section includes a counter rotating low pressure compressor that includes outer and inner compressor blades interspersed with one another and are configured to rotate in an opposite direction than one another about an axis of rotation. A transmission couples at least one of the outer and inner compressor blades to a shaft. A turbine section includes a counter rotating low pressure turbine having an outer rotor that includes an outer set of turbine blades. An inner rotor has an inner set of turbine blades interspersed with the outer set of turbine blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system couples at least one of the outer and inner rotors to the shaft.
Abstract translation: 压缩机部分包括反向旋转的低压压缩机，该压缩机包括彼此分散的外部和内部压缩机叶片，并且构造成围绕旋转轴线沿彼此相反的方向旋转。 A变速器将外压缩机叶片和内压缩机叶片中的至少一个联接到轴。 涡轮部分包括具有包括外部涡轮叶片组的外转子的反转旋转低压涡轮机。 内转子具有与外部涡轮叶片组分布的内部涡轮叶片组。 外转子构造成围绕与内转子的旋转轴线相反的方向旋转。 齿轮系将至少一个外转子和内转子连接到轴上。
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