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    METHOD AND APPARATUS FOR HANDLING PRE-DIFFUSER AIRFLOW FOR COOLING HIGH PRESSURE TURBINE COMPONENTS
    92.
    发明申请
    METHOD AND APPARATUS FOR HANDLING PRE-DIFFUSER AIRFLOW FOR COOLING HIGH PRESSURE TURBINE COMPONENTS 审中-公开
    用于处理高压涡轮机组件的预扩散器气流的方法和装置

    公开(公告)号：US20160010552A1

    公开(公告)日：2016-01-14

    申请号：US14771038

    申请日：2014-02-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Gabriel L. Suciu ,  William K. Ackermann

    IPC: F02C7/18 ,  F01D25/12

    Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section, a diffuser case module, a turbine section, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said turbine section.

    Abstract translation: 提供了一种燃气涡轮发动机，其包括压缩机部分，燃烧器部分，扩散器壳体模块，涡轮部分和歧管。 扩散器壳模块包括在从所述压缩机部分到所述燃烧器部分的环形流动路径内的多个支柱，其中所述多个支柱中的至少一个限定了与所述环形流动路径连通的中跨预扩散器入口。 歧管与所述中跨预扩散器入口和所述涡轮部分连通。

    MULTI-CIRCUIT BUFFER SYSTEM FOR A GAS TURBINE ENGINE
    95.
    发明申请
    MULTI-CIRCUIT BUFFER SYSTEM FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的多电路缓冲器系统

    公开(公告)号：US20140318143A1

    公开(公告)日：2014-10-30

    申请号：US14283610

    申请日：2014-05-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

    IPC: F02C6/08 ,  F02C7/14

    CPC classification number: F02C6/08 ,  F01D25/18 ,  F01D25/183 ,  F02C7/12 ,  F02C7/14 ,  F05D2260/601 ,  Y02T50/675

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a shaft, a first bearing structure and a second bearing structure that support the shaft. Each of the first bearing structure and the second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains the lubricant within the bearing compartments. A buffer system is configured to pressurize the seals to prevent the lubricant from escaping the bearing compartments. The buffer system includes a first circuit configured to supply a first buffer supply air to the first bearing structure, a second circuit configured to supply a second buffer supply air to the second bearing structure, and a controller configured to select between at least two bleed air supplies to communicate the first buffer supply air and the second buffer supply air.

    Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机尤其包括支撑轴的轴，第一轴承结构和第二轴承结构。 第一轴承结构和第二轴承结构中的每一个包括轴承室，其包含润滑剂和在轴承隔室内容纳润滑剂的密封件。 缓冲系统被配置为对密封件加压以防止润滑剂从轴承隔间逸出。 缓冲系统包括被配置为向第一轴承结构提供第一缓冲器供应空气的第一电路，被配置为将第二缓冲器供应空气供应到第二轴承结构的第二电路以及被配置为在至少两个放气 用于通信第一缓冲器供应空气和第二缓冲器供应空气。

    Bleed flow safety system
    97.
    发明授权
    Bleed flow safety system 有权

    公开(公告)号：US11739697B2

    公开(公告)日：2023-08-29

    申请号：US15601524

    申请日：2017-05-22

    Applicant: United Technologies Corporation

    Inventor： Jonathan Ortiz ,  Matthew P. Forcier ,  William K. Ackermann

    IPC: F02C9/18 ,  F01D9/06 ,  F02C7/18 ,  F01D17/02

    CPC classification number: F02C9/18 ,  F01D9/065 ,  F01D17/02 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2270/30

    Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed ports located at one or more axial locations of the gas turbine engine to divert a bleed airflow from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct in fluid communication with the bleed port and the configured to convey the bleed airflow from the bleed port to the bleed outlet. One or more safety sensors are configured to sense operational characteristics of the gas turbine engine, and a controller is operably connected to the one or more safety sensors and configured to evaluate the sensed operational characteristics for anomalies in operation of the bleed air cooling system.

    Integrated environmental control and buffer air system
    98.
    发明授权
    Integrated environmental control and buffer air system 有权

    公开(公告)号：US10774752B2

    公开(公告)日：2020-09-15

    申请号：US15089806

    申请日：2016-04-04

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  William K. Ackermann ,  Harold W. Hipsky

    IPC: F02C9/00 ,  F02C9/18 ,  F02C3/04 ,  F02C7/06 ,  F02C7/32 ,  B64D13/06 ,  F02C6/08

    Abstract: An environmental control system for an aircraft includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with an aircraft engine, and a lower pressure tap to be associated with a lower pressure location in the main compressor section associated with the aircraft engine. The lower pressure location being at a lower pressure than said higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A turbine outlet receives airflow exhausted from the turbine section. A compressor outlet receives airflow exhausted from the compressor section. A combined outlet receives airflow from the turbine outlet and the compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft. A buffer air outlet communicates airflow to an engine buffer air system. The buffer air outlet receives airflow supplied to the turbocompressor. A gas turbine engine is also disclosed.

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