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    METHOD AND APPARATUS FOR SELECTIVELY COLLECTING PRE-DIFFUSER AIRFLOW
    62.
    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。

    Cooling System with a Bearing Compartment Bypass
    63.
    发明申请
    Cooling System with a Bearing Compartment Bypass 有权
    带有轴承舱的冷却系统旁路

    公开(公告)号：US20150285147A1

    公开(公告)日：2015-10-08

    申请号：US14594663

    申请日：2015-01-12

    Applicant: United Technologies Corporation

    Inventor： Justin J. Phillips ,  James D. Hill ,  William K. Ackermann ,  Chris J. Niggemeier ,  Gabriel L. Suciu ,  Anthony R. Bifulco ,  Julian Partyka

    IPC: F02C7/18 ,  F01D25/12

    CPC classification number: F02C7/185 ,  F01D5/081 ,  F01D5/082 ,  F01D5/186 ,  F01D5/187 ,  F01D9/06 ,  F01D9/065 ,  F01D25/08 ,  F01D25/12 ,  F01D25/125 ,  F02C6/08 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/221 ,  F05D2260/232 ,  Y02T50/671 ,  Y02T50/676

    Abstract: A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.

    Abstract translation: 公开了一种用于向燃气涡轮发动机的涡轮部分提供缓冲冷却的冷却空气的冷却系统。 冷却系统可以包括构造成将冷却空气朝向涡轮机部分传送的第一管道，被配置为冷却从第一管道转向以提供缓冲空气的排出气流的热交换器，以及配置成引导至少一部分 的缓冲空气通过绕过燃气涡轮发动机的轴承室的至少一个通道。 冷却系统还可以包括歧管，其配置成允许从第一导管排出的冷却空气和离开旁路导管的缓冲空气混合并提供缓冲冷却的冷却空气;以及喷嘴组件，其配置成将缓冲冷却的冷却空气输送到 涡轮段。

    Gas turbine engine buffer system
    64.
    发明授权
    Gas turbine engine buffer system 有权
    燃气轮机发动机缓冲系统

    公开(公告)号：US09027353B2

    公开(公告)日：2015-05-12

    申请号：US14219070

    申请日：2014-03-19

    Applicant: United Technologies Corporation

    Inventor： Jorn A. Glahn ,  Clifton J. Crawley, Jr. ,  Philip S. Stripinis ,  William K. Ackermann

    IPC: F02C6/08 ,  F01D25/00 ,  F02C7/18 ,  F01D11/04 ,  F01D25/16 ,  F02C7/06 ,  F02C7/12 ,  F02C7/28 ,  F02C9/18

    CPC classification number: F02C9/18 ,  F01D11/04 ,  F01D25/00 ,  F01D25/16 ,  F02C6/08 ,  F02C7/06 ,  F02C7/12 ,  F02C7/18 ,  F02C7/28 ,  F05D2260/601 ,  Y02T50/675 ,  Y10T29/49229

    Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan section configured to be driven by the turbine section via a geared architecture, and a buffer system that communicates buffer air to a portion of the gas turbine engine. The buffer system includes a first circuit configured to selectively mix a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to provide a first buffer supply air having an intermediate pressure compared to the first pressure and the second pressure.

    Abstract translation: 燃气涡轮发动机包括压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器流体连通的涡轮机部分，经由齿轮架构被涡轮部分驱动的风扇部分和缓冲系统， 将缓冲空气传送到燃气涡轮发动机的一部分。 缓冲系统包括第一回路，其被配置为选择性地混合具有第一压力的第一排放空气供应源和第二排气源，其具有大于第一压力的第二压力，以提供具有中间压力的第一缓冲器供应空气， 第一压力和第二压力。

    FUNDAMENTAL GEAR SYSTEM ARCHITECTURE
    66.
    发明申请
    FUNDAMENTAL GEAR SYSTEM ARCHITECTURE 有权
    基础系统架构

    公开(公告)号：US20140020404A1

    公开(公告)日：2014-01-23

    申请号：US14034720

    申请日：2013-09-24

    Applicant: United Technologies Corporation

    Inventor： William G. Sheridan ,  Michael E. McCune ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann ,  Jason Husband

    IPC: F02C7/06

    CPC classification number: F02C7/06 ,  F01D25/18 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/4031 ,  Y02T50/671

    Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing energy equal to less than about 2% of energy input into the gear system.

    Abstract translation: 用于燃气涡轮发动机的风扇驱动齿轮系统包括在风扇驱动涡轮机和风扇之间提供减速的齿轮系统和齿轮系统的柔性支撑部分的安装件。 支持风扇驱动齿轮系统的润滑系统为齿轮系统提供润滑剂，并去除由齿轮系产生的热能。 润滑系统包括能量消除等于输入到齿轮系统中的能量的小于约2％的能量。

    Compressor case clearance control logic
    68.
    发明授权
    Compressor case clearance control logic 有权

    公开(公告)号：US10927696B2

    公开(公告)日：2021-02-23

    申请号：US16165235

    申请日：2018-10-19

    Applicant: United Technologies Corporation

    Inventor： Christopher A. Eckett ,  William K. Ackermann

    IPC: F01D11/24 ,  F01D21/14

    Abstract: A gas turbine engine includes a compressor section having a first portion and an aft portion. A compressor case clearance (CCC) control system is configured to adjust an amount of bleed air delivered to the front portion and the aft portion based on an in-flight phase of an aircraft. In response to invoking a first mode, the CCC control system delivers air to both the front portion and the aft portion. In response to invoking a second mode, the CCC control system reduces the amount of air delivered to the aft portion prior to transitioning from the cruise phase to the descent phase. Accordingly, clearance areas within the compressor section can be selectively increased during specific portions of the flight to avoid contact between blade tips and the engine case.

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