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    11.
    发明专利
    未知

    公开(公告)号：DE602005007829D1

    公开(公告)日：2008-08-14

    申请号：DE602005007829

    申请日：2005-10-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LORD WESLEY K ,  ZYSMAN STEVEN H ,  HOWLETT MATTHEW J

    IPC: B01F23/10 ,  B64C7/02 ,  B64D27/26

    Abstract: A fluid mixer for mixing two fluid streams (40, 42) includes a set of main lobes (26) defining alternating primary and secondary main chutes (30, 32) one or more auxiliary lobes (28) intermediate two of the main lobes (26), and an auxiliary fluid capture duct (62). The auxiliary lobes (28) are defined, at least in part, by the discharge end (66) of the duct (62). In operation, the duct (62) conveys secondary fluid to secondary chutes (36) defined by the lobes (28) thereby improving the performance of the mixer (24) despite the presence of an obstruction (18) that would otherwise impede thorough mixing of two fluid streams (40, 42).

    PASSIVELY DRIVEN ACOUSTIC JET CONTROLLING BOUNDARY LAYERS
    12.
    发明专利
    PASSIVELY DRIVEN ACOUSTIC JET CONTROLLING BOUNDARY LAYERS 未知

    公开(公告)号：CA2372295C

    公开(公告)日：2008-07-08

    申请号：CA2372295

    申请日：2000-02-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LORD WESLEY K ,  MCCORMICK DUANE C

    IPC: B64C21/04 ,  B64C23/00 ,  F01D11/08 ,  F01D11/10 ,  F04D29/16 ,  F04D29/66 ,  F15D1/06 ,  F15D1/12

    Abstract: Existing pressure oscillations created by axial or centrifugal fans in a diverging shroud are utilized to power a passive, acoustic jet, the nozzle of which directs high momentum flux gas particles essentially tangentially into the boundary layer of the flow in a diffuser, or a duct, the fluid particles in the resonant chamber of the passive acoustic jet being replenished with low momentum flux particles drawn from the fluid flow in a direction normal to the surface, thereby to provide a net time averaged flow of increased momentum flux particles to defer, even eliminate, the onset of boundary layer separation in the diffuser or duct. The passive acoustic jet is used in the vicinity of fan blade tips to alleviate undesirable flow effects in the tip region, such as leakage.

    13.
    发明专利
    未知

    公开(公告)号：DE69934757T2

    公开(公告)日：2007-04-26

    申请号：DE69934757

    申请日：1999-11-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZYSMAN STEVEN H ,  KOHLENBERG GREGORY A ,  LORD WESLEY K

    IPC: F02C7/045 ,  F02K1/46 ,  F02K1/38 ,  F02K1/48 ,  F02K3/02

    Abstract: The jet noise suppressor includes a nozzle (20; 30), having an arrangement thereon of trapezoidal tabs (40) disposed on the downstream end of the nozzle (20; 30), the tabs (40) having a length (L) and the angular offset with respect to the engine flow such that mixing occurs primarily at the interface of the engine flow and the ambient air. In addition, various construction details are developed for the tabs including tabs that are trapezoidal with tapered sides such that the tabs minimize adverse impact to engine performance.

    CENTRIFUGAL AIR FLOW CONTROL
    15.
    发明专利
    CENTRIFUGAL AIR FLOW CONTROL 未知

    公开(公告)号：CA2364321A1

    公开(公告)日：2000-08-31

    申请号：CA2364321

    申请日：2000-02-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LORBER PETER F ,  LORD WESLEY K

    IPC: B64C11/18 ,  B64C21/02 ,  B64C27/467 ,  F01D5/14 ,  F15D1/12 ,  B64C21/04

    Abstract: Blades, including helicopter rotor blades, gas turbine engine fan blades, ai r moving machinery fan blades, and the like, have an air inlet near the hub of the blade, which may be on the pressure side of the blade and/or near the leading edge or trailing edge nearer the tip of the blades, with an air plen um between the air inlet and the slots, whereby air is forced into the inlet, through the plenum and out of the slots into the flow adjacent the blades. T he slots may be through the suction surface of the blade, typically near the boundary layer separation point, so that air flowing out of the slots into t he boundary layer of suction surface of the blade, thereby delay or prevent the onset of the boundary layer separation, or to reduce supersonic shock. The inlet may be near the trailing edge of the blade, near the root, adjacent to the air inlet of the core of a jet engine, to suction off air and reduce fan wake blockage at the core inlet. The slots may be through the pressure surfa ce adjacent the blade tip edge of fan blades to reduce blade tip leakage effect s.

    TWO SPOOL GAS GENERATOR WITH IMPROVED AIR PORTING
    17.
    发明公开
    TWO SPOOL GAS GENERATOR WITH IMPROVED AIR PORTING 审中-公开
    ZWEISPULENGASGENERATOR MIT VERBESSERTER LUFTPORTIERUNG

    公开(公告)号：EP2943667A4

    公开(公告)日：2016-01-20

    申请号：EP13870920

    申请日：2013-05-10

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  CHANDLER JESSE M ,  LORD WESLEY K

    IPC: F02C3/04 ,  F02C3/13 ,  F02C3/14 ,  F02C6/04 ,  F02C6/08 ,  F02C9/16 ,  F02C9/18

    CPC classification number: F02C7/12 ,  F02C3/13 ,  F02C3/145 ,  F02C6/04 ,  F02C6/08 ,  F02C9/18 ,  F02K3/00 ,  F02K3/02 ,  F05D2220/3217 ,  F05D2220/3218

    Abstract: In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor rotor and the first turbine rotor is upstream of the second turbine rotor. An air mixing system taps air from a location upstream of the first compressor rotor for delivery to an environmental control system. The air mixing system receives air from a first air source and a second air source. The first air source includes air at a first pressure upstream of the first compressor rotor. The second air source includes air at a lower second pressure. At least one valve controls a mixture of air from the first and second sources to achieve a predetermined pressure for the environmental control system.

    Abstract translation: 在特征实施例中，燃气涡轮发动机具有由第一涡轮转子驱动的第一压缩机转子和由第二涡轮转子驱动的第二压缩机转子。 第二压缩机转子在第一压缩机转子的上游，第一涡轮转子位于第二涡轮转子的上游。 空气混合系统从第一压缩机转子的上游位置抽出空气，用于输送到环境控制系统。 空气混合系统从第一空气源和第二空气源接收空气。 第一空气源包括在第一压缩机转子的上游的第一压力下的空气。 第二空气源包括较低的第二压力的空气。 至少一个阀控制来自第一和第二源的空气的混合物以实现环境控制系统的预定压力。

    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE
    18.
    发明公开
    LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
    与小的压力比的风扇马达和之间的入口和风扇尺寸的尺寸关系

    公开(公告)号：EP3052789A4

    公开(公告)日：2016-11-09

    申请号：EP14850031

    申请日：2014-09-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LORD WESLEY K ,  MALECKI ROBERT E ,  QIU YUAN ,  ROSE BECKY E ,  GILSON JONATHAN

    IPC: F02C7/36 ,  F02C7/04 ,  F02K3/068

    CPC classification number: F02K3/068 ,  F01D25/24 ,  F02C7/04 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2260/40311 ,  F05D2260/96 ,  Y02T50/671

    Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is no more than 0.45.

    Abstract translation: 。根据实施例的示例，一种燃气涡轮发动机组件包括，除其他事项外，风扇确实具有风扇叶片的复数。 风扇的直径具有尺寸D做是基于所述风扇叶片的尺寸。 每个风扇叶片具有领先优势。 的入口部分向前风扇位于。 入口部分的长度具有至少一些风扇叶片的和在入口部分的前边缘的前缘的位置之间的尺寸L。 L的尺寸关系/ D是约0.2至约12:45之间。

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