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161.发明申请公开(公告)号：US20160208713A1
公开(公告)日：2016-07-21
申请号：US14597442
申请日：2015-01-15
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu
CPC classification number: F02C9/18 , F01D5/082 , F01D5/084 , F01D5/088 , F01D25/12 , F02C3/10 , F02C7/18 , F05D2250/322 , F05D2260/20 , Y02T50/676
Abstract: A gas turbine engine includes a turbine section that includes a turbine rotor arranged in a plenum. A compressor section includes a compressor rotor assembly that has spaced apart inner and outer portions that provide an axially extending cooling channel. Compressor blades extend radially outward from the outer portion which provides an inner core flow path. A rotor spoke is configured to receive a first cooling flow and fluidly connect the outer portion to the cooling channel. The compressor rotor assembly has a coolant exit that is in fluid communication with the cooling channel. The compressor rotor assembly is configured to communicate the first cooling flow to the turbine rotor. A bleed source is configured to provide a second cooling flow. A combustor section includes an injector in fluid communication with the bleed source. The tangential onboard injector is configured to communicate the second cooling flow to the turbine rotor.
Abstract translation: 燃气涡轮发动机包括涡轮机部分，其包括布置在增压室中的涡轮机转子。 压缩机部分包括具有间隔开的内部和外部部分的压缩机转子组件，其提供轴向延伸的冷却通道。 压缩机叶片从外部径向向外延伸，该外部部分提供内部核心流动路径。 转子轮辐被构造成接收第一冷却流并将外部部分流体连接到冷却通道。 压缩机转子组件具有与冷却通道流体连通的冷却剂出口。 压缩机转子组件构造成将第一冷却流通向涡轮转子。 排出源构造成提供第二冷却流。 燃烧器部分包括与排泄源流体连通的喷射器。 切向车载喷射器构造成将第二冷却流通向涡轮转子。
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162.发明申请公开(公告)号：US20160084090A1
公开(公告)日：2016-03-24
申请号：US14844082
申请日：2015-09-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill , Mark F. Zelesky
CPC classification number: F01D5/18 , F01D5/06 , F01D5/185 , F01D5/186 , F01D5/187 , F01D11/001 , F01D11/003 , F01D11/005 , F02C3/08 , F05D2220/32 , F05D2260/20 , Y02T50/676
Abstract: A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage.
Abstract translation: 涡轮部分包括包括内部冷却通道的转子组件。 分段密封件邻近转子组件并且包括与内部冷却通道流体连通的流体通道。
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公开(公告)号：US20160076381A1
公开(公告)日：2016-03-17
申请号：US14853392
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill , William K. Ackermann
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/066 , F01D5/084 , F01D5/085 , F04D29/321 , F04D29/584 , F05D2260/205 , F05D2260/221 , Y02T50/671 , Y02T50/676
Abstract: A rotor assembly of a gas turbine engine may be spoked and includes a rotor and a shell. The rotor has a rotor disk and a plurality of blades each having a platform attached to the rotor disk and with a first channel defined radially between the platforms and the rotor disk. The shell projects aft of the rotor and includes inner and outer walls with a passage defined therebetween. The passage is in fluid communication with the first channel and, together, form part of a secondary flowpath for cooling of adjacent components. The rotor assembly may further include a structure located radially inward of the rotor disk and shell. The structure defines a supply conduit for flowing air from the passage and into a rotor bore defined at least in part by adjacent rotor disks. The entering air, being pre-heated when flowing through the channel and passage, warms the bore and reduces thermal gradients, thus thermal fatigue, across the rotor disk.
Abstract translation: 燃气涡轮发动机的转子组件可以被喷射并且包括转子和壳体。 转子具有转子盘和多个叶片，每个叶片具有附接到转子盘的平台，并且在平台和转子盘之间径向地限定第一通道。 壳体在转子的后方突出并且包括具有在其间限定的通道的内壁和外壁。 通道与第一通道流体连通，并且一起形成用于冷却相邻部件的次级流路的一部分。 转子组件还可以包括位于转子盘和壳的径向内侧的结构。 该结构限定用于使空气从通道流入并至少部分地由相邻转子盘限定的转子孔的供应管道。 进入的空气在流过通道和通道时被预热，加热了孔，并降低了转子盘上的热梯度，从而导致热疲劳。
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公开(公告)号：US20160032828A1
公开(公告)日：2016-02-04
申请号：US14796209
申请日：2015-07-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
CPC classification number: F02K3/06 , B64D27/26 , B64D2027/266 , B64D2027/268 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/24 , F01D25/28 , F02C3/107 , F02C7/20 , F02C7/36 , F02C9/18 , F02C9/20 , F02K1/15 , F05D2220/32 , F05D2220/36 , F05D2260/4031 , F05D2260/40311 , F05D2270/42
Abstract: A gas turbine engine including a core nacelle defined about an engine axis. A fan nacelle is mounted at least partially around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A gear train is defined along an engine axis. The gear train defines a gear reduction ratio of greater than or equal to about 2.3. A spool along the engine axis drives the gear train. The spool includes a downstream turbine having six or fewer stages. A fan is driven through the gear train by the downstream turbine. A pressure ratio across the fan is less than about 1.45. A fan variable area nozzle is axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.
Abstract translation: 一种燃气涡轮发动机，包括围绕发动机轴线限定的核心机舱。 风扇机舱至少部分地安装在核心机舱周围，以限定用于风扇旁路气流的风扇旁路气流路径。 齿轮系沿发动机轴线定义。 齿轮系确定齿轮减速比大于或等于约2.3。 沿着发动机轴的线轴驱动齿轮系。 阀芯包括具有六个或更少级的下游涡轮机。 风扇由下游涡轮驱动通过齿轮系。 风扇的压力比小于约1.45。 风扇可变区喷嘴可相对于风扇机舱轴向移动，以改变风扇喷嘴出口区域，并调节发动机运行期间风扇旁路气流的压力比。
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165.发明申请公开(公告)号：US20150369130A1
公开(公告)日：2015-12-24
申请号：US14676513
申请日：2015-04-01
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
CPC classification number: F02C7/18 , F01D5/088 , F01D11/001 , F01D25/24
Abstract: Systems and methods are disclosed herein for distributing cooling air in gas turbine engines. A tangential on board injector (“TOBI”) may supply cooling air to a turbine section of a gas turbine engine. The cooling air may be split into a first cooling air path and a second cooling air path. The first cooling air path may fluidly connect the TOBI and the interior of a first stage rotor blade. The second cooling air path may fluidly connect the TOBI and a cavity. The cavity may be located between a first disk and a second disk. The cooling air paths from a single cooling air source may thermally isolate portions of the turbine section.
Abstract translation: 本文公开了用于在燃气涡轮发动机中分配冷却空气的系统和方法。 切向喷射器（“TOBI”）可以向燃气涡轮发动机的涡轮部分供应冷却空气。 冷却空气可以分成第一冷却空气通道和第二冷却空气通道。 第一冷却空气路径可以将TOBI和第一级转子叶片的内部流体连接。 第二冷却空气路径可以流体地连接TOBI和空腔。 空腔可以位于第一盘和第二盘之间。 来自单个冷却空气源的冷却空气路径可以热隔离涡轮机部分的部分。
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Patent Agency Ranking
公开(公告)号：US20150354455A1
公开(公告)日：2015-12-10
申请号：US14729473
申请日：2015-06-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , James D. Hill
CPC classification number: F01D5/088 , F01D5/08 , F01D5/081 , F01D5/082 , F01D5/084 , F01D5/085 , F01D5/087 , F01D11/00 , F01D11/001 , F01D11/02 , F01D25/12 , F02C3/04 , F02C3/14 , F02C7/12 , F02C7/18 , F02C7/28 , F05D2220/32 , F05D2260/231 , Y02T50/676
Abstract: A gas turbine engine includes a turbine section fluidly connected to a combustor by a primary flow path. The turbine section includes a first portion at a high pressure relative to a second portion. A thermally isolated cooling plenum is positioned radially inward of the primary flow path. The cooling plenum is defined by a forward wall, a shaft structure, an aft wall, and an inner diameter wall of the primary flow path. Air in the thermally isolated cooling plenum is thermally isolated from air in the primary flow path. At least one cooling air system is operable to provide cooling air to the thermally isolated cooling plenum.
Abstract translation: 燃气涡轮发动机包括通过主流路流体连接到燃烧器的涡轮部分。 涡轮部分包括相对于第二部分处于高压的第一部分。 热隔离的冷却增压室位于主流路径的径向内侧。 冷却气室由主流路的前壁，轴结构，后壁和内径壁限定。 热隔离冷却通风室中的空气与主流路中的空气热隔离。 至少一个冷却空气系统可操作以向热隔离的冷却通风室提供冷却空气。
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公开(公告)号：US20150300250A1
公开(公告)日：2015-10-22
申请号：US14647537
申请日：2013-05-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry
CPC classification number: F02C6/02 , F02C3/10 , F02C7/06 , F02K3/025 , F02K3/06 , F05D2220/324 , F05D2220/326 , F05D2250/31 , F05D2260/4031
Abstract: A method of configuring a plurality of gas turbine engines includes the steps of configuring each of the engines with respective ones of a plurality of propulsors. Each propulsor includes a propulsor turbine and one of a fan and a propeller. Each of the engines is configured with respective ones of a plurality of substantially mutually alike gas generators, with the respective propulsor turbine driven by products of combustion downstream of the gas generator.
Abstract translation: 配置多个燃气涡轮发动机的方法包括以下步骤：用多个推进器中的相应的发动机配置每个发动机。 每个推进器包括推进涡轮机和风扇和螺旋桨之一。 每个发动机配置有多个基本相互相似的气体发生器中的相应的发动机，相应的推进涡轮机由气体发生器下游的燃烧产物驱动。
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公开(公告)号：US20150300207A1
公开(公告)日：2015-10-22
申请号：US14755221
申请日：2015-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
CPC classification number: F02K3/06 , B64D27/26 , B64D2027/266 , B64D2027/268 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/24 , F01D25/28 , F02C3/107 , F02C7/20 , F02C7/36 , F02C9/18 , F02C9/20 , F02K1/15 , F05D2220/32 , F05D2220/36 , F05D2260/4031 , F05D2260/40311 , F05D2270/42
Abstract: A gas turbine engine comprises a gear train defined along an engine axis. A spool along the engine axis drives the gear train, and includes a low stage count downstream turbine. A fan rotates at a fan speed about the engine axis and drives the downstream turbine through the gear train. The fan speed is less than a speed of the downstream turbine. A core is surrounded by a core housing defined about the engine axis. A fan nacelle is mounted around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A bypass ratio defined by the fan bypass passage airflow divided by airflow through the core is greater than about ten (10).
Abstract translation: 燃气涡轮发动机包括沿发动机轴线限定的齿轮系。 沿着发动机轴线的线轴驱动齿轮系，并且包括低阶计数的下游涡轮机。 风扇以发动机轴线的风扇速度旋转，并通过齿轮系驱动下游涡轮机。 风扇速度小于下游涡轮机的速度。 一个铁芯围绕发动机轴线定义的铁芯壳体围绕。 风扇机舱安装在核心机舱周围，以确定风扇旁路气流的风扇旁路气流。 由风扇旁路通道气流除以通过芯的气流所限定的旁路比大于约十（10）。
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公开(公告)号：US08863491B2
公开(公告)日：2014-10-21
申请号：US14012773
申请日：2013-08-28
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Karl L. Hasel
CPC classification number: F02C7/06 , F01D25/162 , F02C3/04 , F02C3/107 , F02C7/36 , F02K3/00 , F02K3/04 , Y02T50/671 , Y10T29/4932
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged axially between the inlet case flow path and the intermediate case flow path. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 入口箱内设有齿轮架构。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分轴向地布置在入口壳体流动路径和中间壳体流动路径之间。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。
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公开(公告)号：US20140250862A1
公开(公告)日：2014-09-11
申请号：US14190144
申请日：2014-02-26
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry
IPC: F02K3/06
CPC classification number: F02K3/06 , F05D2210/40 , F05D2250/314 , Y02T50/671
Abstract: A gas turbine engine has a propulsor including a fan and a power turbine, an engine core aerodynamically connected to the propulsor by a transition duct, and a bypass valve in the transition duct that allows for air from the engine core to bypass the power turbine.
Abstract translation: 燃气涡轮发动机具有包括风扇和动力涡轮的推进器，通过过渡管道空气动力地连接到推进器的发动机核心，以及允许来自发动机芯的空气绕过动力涡轮机的过渡管道中的旁通阀。
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