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    GAS TURBINE ENGINE WITH HIGH SPEED AND TEMPERATURE SPOOL COOLING SYSTEM
    271.
    发明申请
    GAS TURBINE ENGINE WITH HIGH SPEED AND TEMPERATURE SPOOL COOLING SYSTEM 有权
    气体涡轮发动机具有高速和温度SPOOL冷却系统

    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

    IPC: F02C9/18 ,  F02C7/18 ,  F02C3/10

    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。

    SYSTEM AND APPARATUS FOR DIVERSIFIED GEARBOX
    272.
    发明申请
    SYSTEM AND APPARATUS FOR DIVERSIFIED GEARBOX 有权
    用于分散式齿轮箱的系统和装置

    公开(公告)号：US20160201567A1

    公开(公告)日：2016-07-14

    申请号：US14596692

    申请日：2015-01-14

    Applicant: United Technologies Corporation

    Inventor： Hung Duong ,  Nathan Snape ,  Gabriel L. Suciu

    IPC: F02C7/32 ,  F16H57/038 ,  F02C3/04 ,  F16H57/025

    CPC classification number: F02C7/32 ,  F01D15/12 ,  F02C3/04 ,  F02C7/36 ,  F05D2250/11 ,  F05D2250/314 ,  F05D2260/4031 ,  F05D2260/532 ,  F16H1/222 ,  F16H57/02 ,  F16H57/025 ,  F16H57/038

    Abstract: A gas turbine engine assembly comprising, a gearbox including a first housing that includes a first auxiliary gear drive on a first portion thereof, a second housing that includes a second auxiliary gear drive on a second portion thereof, and a third housing that includes a third auxiliary gear drive on a third portion thereof, the housings being interconnected so that the first portion of the first housing, the second portion of the second housing and the third portion of the third housing form a substantially triangular polyhedron shape, with the second portion of the second housing disposed between the first portion of the first housing and the third portion of the third housing. The first auxiliary gear drive, the second auxiliary gear drive and the third auxiliary gear drive project outwardly in mutually divergent directions.

    Abstract translation: 一种燃气涡轮发动机组件，包括：齿轮箱，包括第一壳体，所述第一壳体在其第一部分上包括第一辅助齿轮传动;第二壳体，其在其第二部分上包括第二副齿轮传动;第三壳体，包括第三壳体， 辅助齿轮传动在其第三部分上，所述壳体互连，使得第一壳体的第一部分，第二壳体的第二部分和第三壳体的第三部分形成大致三角形的多面体形状，第二部分 所述第二壳体设置在所述第一壳体的所述第一部分和所述第三壳体的第三部分之间。 第一辅助齿轮传动装置，第二辅助齿轮传动装置和第三辅助齿轮传动装置在相互发散的方向上向外突出。

    OFFSET CORES FOR GAS TURBINE ENGINES
    274.
    发明申请
    OFFSET CORES FOR GAS TURBINE ENGINES 审中-公开
    气体涡轮发动机偏心阀

    公开(公告)号：US20160115866A1

    公开(公告)日：2016-04-28

    申请号：US14921575

    申请日：2015-10-23

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  James D. Hill

    IPC: F02C3/14 ,  F01D25/30 ,  F01D25/24 ,  F02C3/04 ,  F02K3/00

    Abstract: A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine.

    Abstract translation: 燃气涡轮发动机包括具有动力涡轮机的推进器，从其延伸的动力涡轮机轴限定中心线轴线，以及由动力涡轮机轴驱动的风扇。 风扇与动力涡轮机前方的中心线轴线对准，并且可操作地连接以由动力涡轮机通过动力涡轮机轴驱动。 可操作地连接到推进器的气体发生器被包括在风扇的下游并且在动力涡轮机的前方，其中气体发生器限定了偏离中心线轴线的发电机轴线。 气体发生器可操作地连接到动力涡轮机，以供应用于驱动动力涡轮机的燃烧产物。

    SECONDARY FLOWPATH SYSTEM FOR A GAS TURBINE ENGINE
    276.
    发明申请
    SECONDARY FLOWPATH SYSTEM FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的二次流量系统

    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。

    METHOD AND APPARATUS FOR SELECTIVELY COLLECTING PRE-DIFFUSER AIRFLOW
    279.
    发明申请
    METHOD AND APPARATUS FOR SELECTIVELY COLLECTING PRE-DIFFUSER AIRFLOW 审中-公开
    用于选择预先扩散器空气流的方法和装置

    公开(公告)号：US20160003260A1

    公开(公告)日：2016-01-07

    申请号：US14771074

    申请日：2014-02-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  William K. Ackermann

    IPC: F04D29/54 ,  F01D25/24

    Abstract: A diffuser for a gas turbine engine is provided that includes an outer shroud, an inner shroud, a multiple of struts between said outer shroud and said inner shroud to define an annular flow path, and a mid-span pre-diffuser inlet in communication with said annular flow path.

    Abstract translation: 提供了一种用于燃气涡轮发动机的扩散器，其包括外护罩，内护罩，所述外护罩和所述内护罩之间的多个支柱，以限定环形流动路径，以及中跨预扩散器入口，其与 所述环形流动路径。

    SYSTEMS AND METHODS FOR DISTRIBUTING COOLING AIR IN GAS TURBINE ENGINES
    280.
    发明申请
    SYSTEMS AND METHODS FOR DISTRIBUTING COOLING AIR IN GAS TURBINE ENGINES 有权
    用于在气体涡轮发动机中分配冷却空气的系统和方法

    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

    IPC: F02C7/18 ,  F01D25/24

    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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