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    TURBINE ENGINE WITH A TURBO-COMPRESSOR
    11.
    发明申请
    TURBINE ENGINE WITH A TURBO-COMPRESSOR 审中-公开
    涡轮发动机与涡轮压缩机

    公开(公告)号：US20160237894A1

    公开(公告)日：2016-08-18

    申请号：US14622523

    申请日：2015-02-13

    Applicant: United Technologies Corporation

    Inventor： Daniel B. Kupratis ,  William G. Sheridan

    IPC: F02C3/34 ,  F02K3/115 ,  F02C3/14

    CPC classification number: F02C3/34 ,  F01D13/006 ,  F02C3/073 ,  F02C3/145 ,  F02C7/08 ,  F02C7/36 ,  F02K3/115 ,  F05D2250/311 ,  F05D2250/36 ,  F05D2260/40311 ,  F05D2260/606

    Abstract: A turbine engine is provided that includes a turbo-compressor, a combustor section, a flow path and a recuperator. The turbo-compressor includes a compressor section and a turbine section. The combustor section includes a combustor and a plenum adjacent the combustor. The flow path extends through the compressor section, the combustor section and the turbine section. The recuperator is configured with the flowpath between the combustor section and the turbine section. An inlet duct to the recuperator is fluidly coupled with the flow path upstream of the plenum. An outlet duct from the recuperator is fluidly coupled with the plenum.

    Abstract translation: 提供了一种涡轮发动机，其包括涡轮压缩机，燃烧器部分，流路和换热器。 涡轮压缩机包括压缩机部分和涡轮部分。 燃烧器部分包括燃烧器和邻近燃烧器的增压室。 流路延伸穿过压缩机部分，燃烧器部分和涡轮部分。 换热器配置有燃烧器部分和涡轮部分之间的流路。 到换热器的入口管道与气室上游的流动路径流体耦合。 来自换热器的出口管与气室流体耦合。

    Engine bypass valve
    16.
    发明授权
    Engine bypass valve 有权

    公开(公告)号：US10161316B2

    公开(公告)日：2018-12-25

    申请号：US14685166

    申请日：2015-04-13

    Applicant: United Technologies Corporation

    Inventor： Daniel B. Kupratis ,  Christopher J. Hanlon ,  Walter A. Ledwith, Jr.

    IPC: F02K3/075 ,  F02K3/077 ,  F02C9/18 ,  F02C3/13

    Abstract: Aspects of the disclosure are directed to an engine of an aircraft. The engine may include a first fan configured to output a first air flow, a second fan configured to receive a first portion of the first air flow and output a second air flow, a core configured to receive a first portion of the second air flow and generate a first stream, and at least one valve configured to assume one of at least three states in association with a generation of a second stream and a third stream based on at least one of the first air flow and the second air flow.

    Reverse-flow core gas turbine engine with a pulse detonation system
    17.
    发明授权
    Reverse-flow core gas turbine engine with a pulse detonation system 有权

    公开(公告)号：US10094279B2

    公开(公告)日：2018-10-09

    申请号：US14764186

    申请日：2013-01-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Daniel B. Kupratis ,  Francis R Moon

    IPC: F02C3/14 ,  F02K3/11 ,  F23R7/00 ,  F02K3/06 ,  F02C5/02 ,  F02C7/06 ,  F02C7/36 ,  F23G7/06 ,  F02C3/107

    Abstract: The engine (10) includes a low spool (16) disposed aft of an air inlet (12) and a high spool (34) disposed aft of the low spool (16). An intake reverse-duct (44) is disposed radially outward of the high spool (34) and reverses direction of low pressure compressed air from the low spool (16) into a forward-flow high pressure compressor (40) of the high spool (34). A discharge reverse-manifold (48) directs flow of an exhaust gas stream (50} from a forward-flow low pressure turbine (20) into a rearward-flow direction and into at least one pulse detonation firing tube (54). An annular bypass air duct (72) directs cooling air along the engine (10)—The at least, one firing tube is positioned radially outward of the high spool (34), overlies the high spool (34) and is also positioned within the bypass air duct (72).

    GAS TURBINE ENGINE WITH A MULTI-SPOOL DRIVEN FAN
    20.
    发明申请
    GAS TURBINE ENGINE WITH A MULTI-SPOOL DRIVEN FAN 审中-公开
    燃气涡轮发动机与多风扇驱动风扇

    公开(公告)号：US20160208692A1

    公开(公告)日：2016-07-21

    申请号：US14600978

    申请日：2015-01-20

    Applicant: United Technologies Corporation

    Inventor： Christopher J. Hanlon ,  Daniel B. Kupratis ,  Walter A. Ledwith

    IPC: F02C3/107 ,  F02K3/06 ,  F02C9/18

    CPC classification number: F02C9/18 ,  F02K3/075 ,  F02K3/077 ,  Y02T50/671

    Abstract: A gas turbine engine includes low and high spools constructed and arranged to rotate about an engine axis. The low spool drives at least one leading stage of a fan section and the high spool drives an aft stage of the fan section. The aft stage may generally include a bypass duct for controllably flowing a bypass stream directly from the leading stage and controllably and/or selectively into an auxiliary flowpath and/or into a second flowpath both located radially outward from a core flowpath.

    Abstract translation: 燃气涡轮发动机包括构造和布置成围绕发动机轴线旋转的低和高线轴。 低阀芯驱动风扇部分的至少一个引导级，高阀芯驱动风扇部分的后级。 后段通常可以包括用于将旁路流直接从引导级可控地流动并且可选地和/或选择性地流入辅助流动路径的旁路管道和/或从核心流路径向向外定位的第二流路。

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