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    A three-spool gas turbine engine with second stream bypass flow
    2.
    发明专利
    A three-spool gas turbine engine with second stream bypass flow 未知

    公开(公告)号：GB2496301A

    公开(公告)日：2013-05-08

    申请号：GB201219481

    申请日：2012-10-30

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL B

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

    Abstract: A gas turbine engine 20 and a method of operating the gas turbine engine, the engine comprising a low spool 42 along an engine axis A with a first stage fan section 24 and a low pressure turbine section 36. The first stage fan section is in flow communication with a third stream bypass flow path 56, a second stream bypass flow path 58 and a core flow path 60. An intermediate spool 44 is additionally provided and comprises a second stage fan section 26, downstream of the first stream fan section, in communication with the second stream bypass flow path and the core flow path. A high spool 46 is additionally provided comprising a high pressure compressor section 28 and a high pressure turbine section 32 along the core flow path. A flow control mechanism 56F may be provided downstream of the first stage fan section, operable to throttle flow in the third stream bypass flow path.

    Gas turbine engine with variable pitch first stage fan section
    5.
    发明专利
    Gas turbine engine with variable pitch first stage fan section 未知

    公开(公告)号：GB2496297A

    公开(公告)日：2013-05-08

    申请号：GB201219409

    申请日：2012-10-29

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL B

    IPC: F02C9/18 ,  F02C9/58 ,  F02K3/075

    Abstract: A gas turbine engine 20 is provided, comprising a low spool 42 along an engine axis A with a variable pitch first fan section 24 and a low pressure turbine section 36. An intermediate spool 44 is also provided along the engine axis with a second stage fan section 26 and an intermediate pressure turbine section 34, said second stage fan section downstream of the variable pitch first stage fan section. A high spool 46 is also provided along the engine axis with a high pressure compressor section 28 and a high pressure turbine section 32. The variable pitch first stage fan section may be in communication with a core flow path 60, a second stream bypass flow path 58 and a third bypass flow path 56. A flow control mechanism 56F may be arranged downstream of the first stage fan section operable to choke a flow in the third stream bypass flow path. The second stage fan section may be in communication with the second stream bypass flow path and the core flow path.

    HYBRID TURBOFAN ENGINE
    6.
    发明公开
    HYBRID TURBOFAN ENGINE 有权
    混合魔术师 - TRIEBWERK

    公开(公告)号：EP2820278A4

    公开(公告)日：2015-10-28

    申请号：EP12869761

    申请日：2012-12-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL B

    IPC: F02K3/04 ,  F02C3/073 ,  F02K3/06 ,  F02K3/062 ,  F02K3/068 ,  F02K3/12

    CPC classification number: F02K3/06 ,  F02C3/073 ,  F02K3/062 ,  F02K3/068 ,  F02K3/12

    Abstract: A gas turbine engine has, in at least a first mode of operation, a core engine, a fan, and an auxiliary turbine engine coupled as follows. The core engine has, along a core flowpath, at least one compressor section, a combustor, and at least one turbine section. The fan is upstream of the core flowpath and drives air downstream along the core flowpath and along a bypass flowpath. The auxiliary turbine engine has an axial compressor, a fan, a combustor, and an axial turbine. The fan has fan blades and a continuation of the bypass flowpath extends sequentially downstream through the axial compressor and radially outward through passageways in the blades of the fan and a continuation of the core flowpath passes axially through the fan. The combustor is downstream of the fan along the continuation of the bypass flowpath. The axial turbine is downstream of the combustor along the continuation of the bypass flowpath and comprises at least one stage of blades rotating with the fan.

    Abstract translation: 燃气涡轮发动机在至少第一操作模式中具有如下耦合的核心发动机，风扇和辅助涡轮发动机。 核心发动机沿核心流路具有至少一个压缩机部分，燃烧器和至少一个涡轮部分。 风扇位于核心流路的上游，并沿核心流路沿着旁路流路驱动空气下游。 辅助涡轮发动机具有轴向压缩机，风扇，燃烧器和轴向涡轮机。 风扇具有风扇叶片，并且旁路流路的延续沿着轴向压缩机顺序地向下延伸，并且通过风扇叶片中的通道径向向外延伸，并且芯流路的延续轴向通过风扇。 燃烧器沿着旁路流路的延续在风扇的下游。 轴向涡轮机沿着旁路流路的延续在燃烧器的下游，并且包括与风扇一起旋转的至少一个叶片级。

    SYSTEMS AND METHODS CONTROLLING FAN PRESSURE RATIOS
    7.
    发明公开
    SYSTEMS AND METHODS CONTROLLING FAN PRESSURE RATIOS 审中-公开
    SYSTEME UND VERFAHREN ZUR STEUERUNG VONGEBLÄSEDRUCKVERHÄLTNISSEN

    公开(公告)号：EP3080426A4

    公开(公告)日：2017-07-26

    申请号：EP14870083

    申请日：2014-12-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KUPRATIS DANIEL B

    IPC: F02K3/075

    CPC classification number: F02K3/075 ,  F01D9/04 ,  F01D17/105 ,  F01D17/162 ,  F02K3/077 ,  F05D2220/36 ,  F05D2240/128 ,  F05D2240/55

    Abstract: A system for varying the fan pressure ratio of a gas turbine engine is provided. The system may comprise a stator having a variable area component. The variable area component may be configured to adjust the inlet area on the main fan bypass. In this regard, the variable area component may be configured to restrict flow to the main fan bypass and/or divert flow to the core flow from a fan section of a gas turbine engine.

    Abstract translation: 提供了一种用于改变燃气涡轮发动机的风扇压力比的系统。 该系统可以包括具有可变面积部件的定子。 可变面积部件可以被配置为调节主风扇旁路上的入口区域。 就这一点而言，可变区域部件可以被配置成限制流向主风扇旁路的流量和/或将流量从燃气涡轮发动机的风扇部分转移到核心流。

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