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    CERAMIC MATRIX COMPOSITE SEAL SEGMENT FOR A GAS TURBINE ENGINE
    3.
    发明申请
    CERAMIC MATRIX COMPOSITE SEAL SEGMENT FOR A GAS TURBINE ENGINE 有权
    陶瓷基体复合材料密封段用于气体涡轮发动机

    公开(公告)号：US20160348528A1

    公开(公告)日：2016-12-01

    申请号：US14721705

    申请日：2015-05-26

    Applicant: Daniel Kent Vetters ,  David J. Thomas ,  Ted Freeman ,  Douglas David Dierksmeier ,  Jun Shi ,  Todd Engel

    Inventor： Daniel Kent Vetters ,  David J. Thomas ,  Ted Freeman ,  Douglas David Dierksmeier ,  Jun Shi ,  Todd Engel

    IPC: F01D11/08 ,  F01D25/24

    CPC classification number: F01D11/08 ,  F01D9/04 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2300/6033

    Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.

    Abstract translation: 一种陶瓷基体复合材料（CMC）密封段，用于分段涡轮机罩，用于在燃气涡轮发动机中径向包围涡轮机。 CMC密封段包括具有面向涡轮的表面的弧形凸缘和限定用于接收细长销的孔的部分，孔的长度为其中接收的细长销的长度的至少70％。 CMC密封段由载体承载，其中至少一个细长销被接收在孔内。 限定销接收孔的CMC密封段部分通过从弧形凸缘径向向外延伸的间隔凸缘与弓形凸缘径向间隔开。

    LIFT FAN FLOW PATH DEVICE
    4.
    发明申请
    LIFT FAN FLOW PATH DEVICE 有权
    提升风扇流路装置

    公开(公告)号：US20100166554A1

    公开(公告)日：2010-07-01

    申请号：US12630743

    申请日：2009-12-03

    Applicant: Douglas David Dierksmeier

    Inventor： Douglas David Dierksmeier

    IPC: B64C29/00

    CPC classification number: B64C29/0025

    Abstract: A flow path is disclosed that is capable of being deployed when needed and stowed in a relatively small space when not in use. The flow path device is flexible and may be made from a variety of materials. In an illustrative embodiment the flow path device is annular and transitions from an ellipsoidal annular shape to a quadrilateral annular shape. A vane box can be disposed at one end of the flow path device. Doors can be coupled to the vane box to cover the flow path device. The doors can be used to provide a structural load path for the flow path device and vane box. The doors and the flow path device can be moved together such that the doors uncover the flow path device as the device is deployed.

    Abstract translation: 公开了一种流动路径，其能够在不使用时在需要时被部署并存放在相对小的空间中。 流路装置是柔性的并且可以由各种材料制成。 在说明性实施例中，流动路径装置是环形的，并且从椭圆形环状形状转变为四边形环形。 叶片箱可以设置在流路装置的一端。 门可以连接到叶片箱以覆盖流路装置。 门可用于为流路装置和叶片箱提供结构载荷路径。 门和流路装置可以一起移动，使得当装置展开时，门露出流路装置。

    Compressor tip clearance control and gas turbine engine
    7.
    发明授权
    Compressor tip clearance control and gas turbine engine 有权
    压缩机顶端间隙控制和燃气轮机

    公开(公告)号：US09458855B2

    公开(公告)日：2016-10-04

    申请号：US13334607

    申请日：2011-12-22

    Applicant: Douglas David Dierksmeier ,  Steven Lester Grant ,  James Christopher Muskat

    Inventor： Douglas David Dierksmeier ,  Steven Lester Grant ,  James Christopher Muskat

    IPC: F04D29/58 ,  F01D25/14 ,  F02C6/08 ,  F04D29/16 ,  F01D11/24 ,  F01D11/14 ,  F01D11/20

    CPC classification number: F04D29/164 ,  F01D11/14 ,  F01D11/20 ,  F01D11/24 ,  F01D25/14 ,  F02C6/08 ,  F05D2240/11 ,  F05D2260/201 ,  Y02T50/676

    Abstract: A unique compressor includes a rotating compressor blade having a blade tip; a compressor case having a blade track disposed opposite the blade tip; and a tip clearance control system including a fluid impingement structure. This structure has a plurality of openings to impinge a fluid received from a diffuser onto the compressor case. The tip clearance control system is configured to control a clearance between the blade tip and the blade track by impinging the fluid onto the compressor case and modulating the same with a valve in fluid communication with the diffuser. A further form includes a unique gas turbine engine having a compressor with a compressor blade tip, a compressor case disposed opposite the blade tip, and a fluid impingement structure having openings to impinge a fluid onto the case. Also included are other apparatuses, systems, devices, hardware, methods, and combinations for compressor blade tip clearance control.

    Abstract translation: 独特的压缩机包括具有叶片尖端的旋转压缩机叶片; 压缩机壳体，其具有与叶片尖端相对设置的叶片轨道; 以及包括流体冲击结构的顶端间隙控制系统。 该结构具有多个开口以将从扩散器接收的流体冲击到压缩机壳体上。 顶端间隙控制系统构造成通过将流体冲击到压缩机壳体上并通过与扩散器流体连通的阀来调节其而控制叶片尖端和叶片轨道之间的间隙。 另外的形式包括具有压缩机的独特的燃气涡轮发动机，其具有压缩机叶片尖端，与叶片尖端相对设置的压缩机壳体和具有将流体冲击到壳体上的开口的流体冲击结构。 还包括用于压缩机叶片顶端间隙控制的其他装置，系统，装置，硬件，方法和组合。

    Lift fan flow path device
    8.
    发明授权
    Lift fan flow path device 有权
    提升风机流路装置

    公开(公告)号：US08336806B2

    公开(公告)日：2012-12-25

    申请号：US12630743

    申请日：2009-12-03

    Applicant: Douglas David Dierksmeier

    Inventor： Douglas David Dierksmeier

    IPC: B64C15/02

    CPC classification number: B64C29/0025

    Abstract: A flow path is disclosed that is capable of being deployed when needed and stowed in a relatively small space when not in use. The flow path device is flexible and may be made from a variety of materials. In an illustrative embodiment the flow path device is annular and transitions from an ellipsoidal annular shape to a quadrilateral annular shape. A vane box can be disposed at one end of the flow path device. Doors can be coupled to the vane box to cover the flow path device. The doors can be used to provide a structural load path for the flow path device and vane box. The doors and the flow path device can be moved together such that the doors uncover the flow path device as the device is deployed.

    Abstract translation: 公开了一种流动路径，其能够在不使用时在需要时被部署并存放在相对小的空间中。 流路装置是柔性的并且可以由各种材料制成。 在说明性实施例中，流动路径装置是环形的，并且从椭圆形环状形状转变为四边形环形。 叶片箱可以设置在流路装置的一端。 门可以连接到叶片箱以覆盖流路装置。 门可用于为流路装置和叶片箱提供结构载荷路径。 门和流路装置可以一起移动，使得当装置展开时，门露出流路装置。

    Apparatus and method for active control of blade tip clearance
    9.
    发明授权
    Apparatus and method for active control of blade tip clearance 有权
    用于主动控制叶片顶端间隙的装置和方法

    公开(公告)号：US07575409B2

    公开(公告)日：2009-08-18

    申请号：US11173345

    申请日：2005-07-01

    Applicant: Douglas David Dierksmeier ,  Tab Michael Heffernan

    Inventor： Douglas David Dierksmeier ,  Tab Michael Heffernan

    IPC: F01D25/24

    CPC classification number: F01D11/22

    Abstract: An active blade clearance control system for a gas turbine engine. The clearance between the tip of a rotatable blade and an inner surface of a blade track is adjusted by moving the blade track relative to the tip of the blades. A split control ring is manipulated to adjust tension therein and a resulting force is transmitted to an inner member. The plurality of blade tracks are coupled to the inner member and move in response to the force transmitted from the split control ring.

    Abstract translation: 一种用于燃气涡轮发动机的主动叶片间隙控制系统。 通过相对于叶片的尖端移动叶片轨道来调节可旋转叶片的尖端和叶片轨迹的内表面之间的间隙。 操纵分割控制环以调节其中的张力，并将所产生的力传递到内部构件。 多个叶片轨道联接到内部构件并且响应于从分离控制环传递的力而移动。

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