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    Flow diverter system for multiple streams for gas turbine engines
    3.
    发明授权
    Flow diverter system for multiple streams for gas turbine engines 失效
    用于燃气涡轮发动机的多个流的分流器系统

    公开(公告)号：US5816042A

    公开(公告)日：1998-10-06

    申请号：US773586

    申请日：1996-12-27

    申请人： Daniel P. Guinan ,  David E. Wendt

    发明人： Daniel P. Guinan ,  David E. Wendt

    IPC分类号： F02K1/06 ,  F02K1/82 ,  F02K3/04

    CPC分类号： F02K1/82 ,  F02K1/06

    摘要： A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine and afterburner sections and includes ports complementing the inlets in the offtakes to divert the core stream through the offtakes and passages to proportion the fan discharge air utilized for cooling purposes in the engine to cool the liner and walls of the offtakes and the engine components located downstream of the rotary drum while assuring separation of the core stream flow and fan air flow.

    摘要翻译： 用于具有推力反向或短起飞和垂直着陆或两者能力的涡轮风扇发动机的涡轮风扇发动机的双向管道换向或换向机构的分流机构包括安装在涡轮机和后燃器部分之间的旋转鼓，并且包括与在 将芯流转移通过出料口和通道的比例，用于在发动机中用于冷却目的的风扇排出空气，以冷却位于转鼓的下游的出料口和发动机部件的衬套和壁，同时确保芯部分离 流量和风扇空气流量。

    Inverter ducting for dual fan concept
    4.
    发明授权
    Inverter ducting for dual fan concept 有权
    双风扇概念逆变管道

    公开(公告)号：US06351940B1

    公开(公告)日：2002-03-05

    申请号：US09475877

    申请日：1999-12-30

    申请人： Daniel P. Guinan ,  David J. Huber ,  Gary M. Perkins

    发明人： Daniel P. Guinan ,  David J. Huber ,  Gary M. Perkins

    IPC分类号： F02K302

    CPC分类号： F02C7/04 ,  F02K3/065 ,  F02K3/077 ,  F04D25/166 ,  F04D29/545 ,  F05D2250/312 ,  Y02T50/671

    摘要： Accordingly, the present invention provides a ducting system for use on a gas turbine engine having two fans connected to a common shaft, and includes a primary inlet duct that is integral with a plurality of primary discharge ducts, a plurality of secondary inlet ducts that are integral with a secondary discharge duct, each of the ducts includes a port, the ports of the secondary inlet ducts are located radially outward of the port of the primary inlet duct, and the ports of the primary discharge ducts are located radially outward of the port of the secondary discharge duct.

    摘要翻译： 因此，本发明提供一种在燃气轮机发动机上使用的管道系统，其具有连接到公共轴的两个风扇，并且包括与多个主排放管道成一体的主入口管道，多个第二入口管道 与二次排放管道成一体，每个管道包括一个端口，第二入口管道的端口位于主入口管道的端口的径向外侧，并且主排放管道的端口位于端口的径向外侧 的二次排放管道。

    Flow diverter system for multiple streams for gas turbine engine
    5.
    发明授权
    Flow diverter system for multiple streams for gas turbine engine 失效
    用于燃气涡轮发动机的多个流的分流器系统

    公开(公告)号：US6102329A

    公开(公告)日：2000-08-15

    申请号：US087891

    申请日：1998-05-30

    申请人： Daniel P. Guinan ,  David E. Wendt

    发明人： Daniel P. Guinan ,  David E. Wendt

    IPC分类号： F02K1/06 ,  F02K1/82 ,  B64B1/24

    CPC分类号： F02K1/82 ,  F02K1/06

    摘要： A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine and afterburner sections and includes ports complementing the inlets in the offtakes to divert the core stream through the offtakes and passages to proportion the fan discharge air utilized for cooling purposes in the engine to cool the liner and walls of the offtakes and the engine components located downstream of the rotary drum while assuring separation of the core stream flow and fan air flow.

    摘要翻译： 用于具有推力反向或短起飞和垂直着陆或两者能力的涡轮风扇发动机的涡轮风扇发动机的双向管道换向或换向机构的分流机构包括安装在涡轮机和后燃器部分之间的旋转鼓，并且包括与在 将芯流转移通过出料口和通道的比例，用于在发动机中用于冷却目的的风扇排出空气，以冷却位于转鼓的下游的出料口和发动机部件的衬套和壁，同时确保芯部分离 流量和风扇空气流量。

    Seal assembly
    6.
    发明授权
    Seal assembly 失效
    密封组件

    公开(公告)号：US5305609A

    公开(公告)日：1994-04-26

    申请号：US61783

    申请日：1993-05-14

    申请人： Daniel P. Guinan ,  Donald R. Miehe

    发明人： Daniel P. Guinan ,  Donald R. Miehe

    IPC分类号： F01D9/06 ,  F02C7/22 ,  F16J15/16 ,  F23R3/28 ,  F02C1/00

    CPC分类号： F02C7/222 ,  F01D9/065 ,  F16J15/162 ,  F23R3/283 ,  Y10S277/93

    摘要： A fuel injector 14 passes through wall 10 to inject fuel into a hot supersonic air flow 12. Wedge seals 26, 28 seal against leakage in cooperation with injection air flow 37, being compressed within seal carrier 16. Face seals 30, 32 are compressed by cover plate 34. Inboard seals 26, 44 are preferably more porous than the outboard seals so that there is a leakage of cooling air through crevice 44.

    摘要翻译： 燃料喷射器14通过壁10以将燃料喷射到热的超音速气流12.楔形密封件26,28与注射空气流37协作密封以防止在密封载体16内压缩的泄漏。面密封件30,32被 内侧密封件26,44优选地比外侧密封件更多孔，使得冷却空气通过缝隙44泄漏。

    Variable geometry inlet design for scram jet engine
    10.
    发明授权
    Variable geometry inlet design for scram jet engine 失效
    用于冲击式发动机的可变几何入口设计

    公开(公告)号：US06883330B2

    公开(公告)日：2005-04-26

    申请号：US10264172

    申请日：2002-10-02

    申请人： Daniel P. Guinan ,  Alan Drake ,  Dean Andreadis ,  Stephen A. Beckel

    发明人： Daniel P. Guinan ,  Alan Drake ,  Dean Andreadis ,  Stephen A. Beckel

    IPC分类号： F02C7/042 ,  F02K7/14 ,  F02K7/08

    CPC分类号： F02K7/14

    摘要： The present invention relates to an improved variable geometry inlet for a scram jet engine having at least one combustor module. The variable geometry inlet comprises each combustor module having two sidewalls. Each of the sidewalls has a central portion with a thickness and a tapered profile forward of the central portion. The tapered profile terminates in a sharp leading edge. The variable geometry inlet further comprises each module having a lower wall and a movable cowl flap positioned forward of the lower wall. The movable cowl flap has a leading edge and the leading edges of the sidewalls intersect the leading edge of the cowl flap.

    摘要翻译： 本发明涉及一种用于具有至少一个燃烧器模块的冲击式发动机的改进的可变几何入口。 可变几何入口包括具有两个侧壁的每个燃烧器模块。 每个侧壁具有中心部分，该中心部分具有中心部分的前方的厚度和锥形轮廓。 锥形轮廓终止于锋利的前缘。 可变几何形状入口还包括每个模块，其具有位于下壁前方的下壁和可移动整流罩。 可移动整流罩具有前缘，并且侧壁的前缘与整流罩的前缘相交。