公开(公告)号：US20150219010A1

公开(公告)日：2015-08-06

申请号：US14415410

申请日：2011-12-20

Applicant: Marco Santini ,  Giorgio Marchetti

Inventor： Marco Santini ,  Giorgio Marchetti

IPC: F02C7/05 ,  B01D46/42 ,  B01D46/00 ,  F01D25/32

CPC classification number: F02C7/05 ,  B01D46/0087 ,  B01D46/4227 ,  F01D25/002 ,  F01D25/32 ,  F02C7/055 ,  Y10T29/49238

Abstract: A filtering chamber for a gas turbine having a combustor, compressor and air inlet duct, and a corresponding maintenance method is described. The filtering chamber includes a first chamber in an inlet plenum; a second chamber in the inlet plenum; and an air bypass mechanism configured to reduce a pressure difference across a final filter that separates the first chamber from the second chamber.

Abstract translation: 描述了一种用于具有燃烧器，压缩机和空气入口管道的燃气轮机的过滤室以及相应的维护方法。 过滤室包括在入口增压室中的第一室; 入口增压室中的第二个室; 以及空气旁路机构，其构造成减小跨越将第一室与第二室分离的最终过滤器的压力差。

公开(公告)号：US20150121821A1

公开(公告)日：2015-05-07

申请号：US14594747

申请日：2015-01-12

Applicant: Michael J. Kline

Inventor： Michael J. Kline

IPC: F02C7/055 ,  B29C45/00

CPC classification number: F02C7/055 ,  B29C45/0003 ,  B29L2031/3076 ,  B64D29/00 ,  C04B41/52 ,  C08F8/12 ,  C08F120/56 ,  F01D9/02 ,  F01D9/041 ,  F02C7/05 ,  F05D2250/15 ,  F05D2250/25 ,  Y02T50/672 ,  Y10T137/0536

Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

Abstract translation: 一种用于具有空气入口的结构的进气导流板。 偏转器可以在结构内伸缩，可以与结构一体地形成，并且可以防止结构物吸收诸如鸟的异物。 偏转器可以包括一系列可以从前到后的宽度和/或厚度变化的肋，轮辐或叶片，和/或可以在一个或多个视图平面中曲线，和/或可以作为入口的双重作用 用于重新定向入口空气的叶片。

公开(公告)号：US09003759B2

公开(公告)日：2015-04-14

申请号：US11719799

申请日：2004-12-01

Applicant: Gabriel Suciu ,  Gary D. Roberge ,  Brian Merry

Inventor： Gabriel Suciu ,  Gary D. Roberge ,  Brian Merry

IPC: F02G3/00 ,  F02C7/052 ,  F01D5/02 ,  F02C3/073 ,  F02C7/05 ,  F02K3/068

CPC classification number: F02C7/052 ,  F01D5/022 ,  F02C3/073 ,  F02C7/05 ,  F02K3/068 ,  F05D2250/71

Abstract: A particle separator (20) for a tip turbine engine (10) includes a generally conical inclined leading surface (24) leading to a maximum radius (25) and a tapered trailing surface (56) having a radius at all points therealong less than the maximum radius (25). The trailing surface (56) of the particle separator (20) is tapered and/or curved radially inwardly away from the maximum radius (25). Air flowing toward the core airflow inlet is first diverted radially outwardly by the inclined leading surface (24) of the particle separator (20) to the maximum radius (25) of the particle separator (20). The air then follows the trailing surface (56) radially inwardly to flow axially into the core airflow inlet. While the air can follow the contours of the particle separator (20) around the maximum radius (25) and into the core airflow inlet, any particles, such as dirt, will have more inertia and will pass radially outwardly of the core airflow inlet through the bypass fan.

Abstract translation: 用于尖端涡轮发动机（10）的颗粒分离器（20）包括通向圆锥形的倾斜前导表面（24），其导致最大半径（25）和锥形后表面（56），所述锥形后表面在所有点处具有小于 最大半径（25）。 颗粒分离器（20）的后表面（56）从最大半径（25）向内径向向内渐缩和/或弯曲。 首先通过颗粒分离器（20）的倾斜引导表面（24）向颗粒分离器（20）的最大半径（25）径向向外转向空气流向核心气流入口。 然后空气径向向内跟随后表面（56），从而轴向流入核心气流入口。 当空气可以沿着最大半径（25）和颗粒气流入口跟随颗粒分离器（20）的轮廓时，任何颗粒（例如污物）将具有更大的惯性并且将通过核心气流入口的径向向外通过 旁路风扇。

公开(公告)号：US20150063986A1

公开(公告)日：2015-03-05

申请号：US14475238

申请日：2014-09-02

Applicant: MTU Aero Engines AG

Inventor： Stefan SASSE ,  Norbert Schinko

IPC: F01D21/04

CPC classification number: F01D21/045 ,  F01D17/02 ,  F01D21/04 ,  F01D25/24 ,  F02C7/05 ,  F05D2260/311 ,  Y02T50/671

Abstract: An apparatus for absorption of an impact energy from at least one blade fragment is disclosed. The impact energy acts on an element that is inserted into an opening in a turbo-machine. The opening passes radially through a housing section in a region of a row of rotating blades. The apparatus has a holder for holding the element in an ideal position and releasing the element beyond a preset maximum load and has a cage at a rear to secure the element in a radially outward-directed displacement. A turbo-machine having such an apparatus, as well as a method for multistage energy absorption, is also disclosed.

Abstract translation: 公开了一种用于从至少一个叶片片段吸收冲击能量的装置。 冲击能作用在插入涡轮机的开口中的元件上。 开口在一排旋转叶片的区域中径向通过壳体部分。 该装置具有用于将元件保持在理想位置并将元件释放超过预设最大负载的保持器，并且在后部具有保持架以将元件固定在径向向外的位移。 还公开了具有这种装置的涡轮机，以及用于多级能量吸收的方法。

公开(公告)号：US20140356125A1

公开(公告)日：2014-12-04

申请号：US14104299

申请日：2013-12-12

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Eric S. Donovan ,  Daniel J. Vonderwell ,  Craig Heathco

IPC: F02C7/05 ,  F02C7/12

CPC classification number: F02C7/05 ,  F02C7/052 ,  F02C7/12 ,  F05D2260/205 ,  F05D2260/213 ,  Y02T50/675

Abstract: An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air. A scavenge air path conveys the scavenge air from the inlet particle separator to the heat transfer system. A heat exchange fluid path conveys a heat exchange fluid to the heat transfer system and a cooled heat exchange fluid away from the heat transfer system. The heat transfer system is configured to transfer heat from the heat exchange fluid path to the scavenge air path to cool the heat exchange fluid.

Abstract translation: 一种装置包括燃气涡轮发动机和传热系统。 燃气涡轮发动机包括将入口空气分离成清扫空气和清洁空气的入口颗粒分离器。 清扫空气路径将清除空气从入口颗粒分离器传送到传热系统。 热交换流体路径将热交换流体传送到传热系统和冷却的热交换流体远离热传递系统。 传热系统被配置成将热量从热交换流体路径传递到扫气通道以冷却热交换流体。

公开(公告)号：US20140345294A1

公开(公告)日：2014-11-27

申请号：US14452880

申请日：2014-08-06

Applicant: United Technologies Corporation

Inventor： Justin R. Urban ,  Anthony R. Bifulco

IPC: F02C6/08 ,  F02C7/05 ,  F02C7/047

CPC classification number: F02C6/08 ,  F01D17/105 ,  F02C6/18 ,  F02C7/047 ,  F02C7/05 ,  F02C7/052 ,  F02K3/06 ,  F04D27/023 ,  F04D29/545 ,  F05D2260/606 ,  F05D2260/607 ,  Y02T50/675 ,  Y10T29/49231

Abstract: A gas turbine engine includes a bleed structure which includes a forward wall and a rear structural wall to define a deposit space downstream of the bleed structure for a hail event of a predetermined duration.

Abstract translation: 燃气涡轮发动机包括排气结构，其包括前壁和后结构壁，以在出血结构的下游限定用于预定持续时间的冰雹事件的沉积空间。

公开(公告)号：US20140130468A1

公开(公告)日：2014-05-15

申请号：US13825731

申请日：2011-09-15

Applicant: Paul Jackson

Inventor： Paul Jackson

IPC: F02C7/05

CPC classification number: B01D46/0005 ,  B01D46/002 ,  B01D46/0023 ,  B01D46/02 ,  B01D2265/027 ,  B01D2265/028 ,  B01D2279/60 ,  F02C7/05 ,  F02C7/055

Abstract: A filter assembly (6) comprises a mounting support (11) defining a fluid outlet opening in the support, a filter device (9) extending across the opening, a fastening arrangement (12) operative to locate the filter device against a seat (11a) of the mounting support (11) so that the filter device (9) extends across the opening for filtering a fluid medium flowing through the outlet opening and the filter device (9), and a pre-filter device (8) secured, between the fastening arrangement (12) and the filter device (9), for pre-filtering fluid medium flowing successively through the upstream pre-filter (8) and downstream filter device (9). The pre-filter device (8) comprises a filter mounting plate (15) located upstream of the filter device (9) and held there by the fastening arrangement (12), relative to the fluid flow direction, and at least one filter element (16) removably mounted on the mounting plate (15).

Abstract translation: 过滤器组件（6）包括限定支撑件中的流体出口开口的安装支撑件（11），横过开口延伸的过滤器装置（9），用于将过滤装置定位在座椅（11a） ），使得过滤装置（9）跨过开口延伸，用于过滤流过出口开口和过滤装置（9）的流体介质，以及预过滤装置（8），其固定在 紧固装置（12）和过滤装置（9），用于预先过滤流过上游预过滤器（8）和下游过滤装置（9）的流体介质。 预过滤装置（8）包括位于过滤装置（9）上游的过滤器安装板（15），并且相对于流体流动方向由紧固装置（12）保持在其上，并且至少一个过滤元件 16）可拆卸地安装在安装板（15）上。

公开(公告)号：US20130142634A1

公开(公告)日：2013-06-06

申请号：US13817057

申请日：2011-08-23

Applicant: Jean-Luc Pierre Sahores ,  Carole Jaureguiberry ,  Jean-Maurice Casaux-Bic ,  Olivier Pierre Descubes

Inventor： Jean-Luc Pierre Sahores ,  Carole Jaureguiberry ,  Jean-Maurice Casaux-Bic ,  Olivier Pierre Descubes

IPC: F01D25/24 ,  B21K1/26

CPC classification number: F01D25/24 ,  B21K1/26 ,  F01D21/045 ,  F02C7/05 ,  F02K1/82 ,  F04D27/008 ,  F04D27/0261 ,  F04D29/522 ,  F04D29/526 ,  F05D2240/14 ,  Y10T29/49323

Abstract: A method and structure negating thermal inertia of a solid portion, such as shielding, which influences mechanical behavior of parts of an engine structure, by reducing forces transmitted to the engine structure during an event in which a turbine blade ruptures, while preserving mechanical strength and vibratory positioning. The structure includes a flexible fastener for a shield, enabling producing a fusible section. An assembly for mounting a shielding onto a casing of the engine structure of a turbine includes connection lugs and points for attachment to the casing and shielding. The attachment points are sufficiently spaced apart in accordance with curvature of the shielding and casing so connection between the lugs and the shielding or casing, and connection of the attachment points, are substantially tangential. The lugs are sized so the connection has sufficient flexibility to control vibratory positioning thereof and ensure sufficient mechanical strength under thermo-mechanical loads.

Abstract translation: 一种方法和结构通过在涡轮叶片破裂的事件期间减少传递到发动机结构的力同时保持机械强度而抵消固体部分（例如屏蔽）的热惯性，其影响发动机结构部件的机械性能， 振动定位。 该结构包括用于护罩的柔性紧固件，能够产生可熔部分。 用于将屏蔽件安装在涡轮机的发动机结构的壳体上的组件包括用于附接到壳体和屏蔽的连接凸耳和点。 附接点根据屏蔽和壳体的曲率充分间隔开，因此凸耳与屏蔽或壳体之间的连接以及连接点的连接基本上是切线的。 凸耳的尺寸使得连接具有足够的灵活性来控制其振动定位并且确保在热机械载荷下的足够的机械强度。

公开(公告)号：US08452516B1

公开(公告)日：2013-05-28

申请号：US13446326

申请日：2012-04-13

Applicant: Becky E. Rose ,  Lisa I. Brilliant

Inventor： Becky E. Rose ,  Lisa I. Brilliant

IPC: G06F19/00 ,  G06G7/70 ,  F02C7/05 ,  B64D33/02 ,  F01D5/14 ,  F01D5/12 ,  F01D25/00 ,  F01D13/02 ,  F01D17/00 ,  F03D11/00 ,  F03B11/00 ,  F04D29/38 ,  F01B25/00 ,  F01B25/02

CPC classification number: B64D45/00 ,  B64D2033/022 ,  F01D17/162 ,  F02C7/05 ,  F02C9/20 ,  F04D27/0292 ,  F04D29/563 ,  F05D2270/114

Abstract: A method of protecting a gas turbine engine according an exemplary aspect of the present disclosure includes, among other things, the steps of determining at least one flight condition of an aircraft and comparing the at least one flight condition to a programmed condition. The method further includes the steps of moving a plurality of inlet vanes of a low pressure compressor from a first position to a second position if the step of comparing the at least one flight condition to the programmed flight condition determines the programmed flight condition are met and deflecting any foreign objects with the plurality of inlet vanes.

Abstract translation: 根据本公开的示例性方面的保护燃气涡轮发动机的方法包括确定飞机的至少一个飞行状况并将至少一个飞行状况与编程状态进行比较的步骤。 该方法还包括以下步骤：如果将至少一个飞行条件与编程的飞行条件进行比较的步骤确定已满足编程的飞行条件，则将低压压缩机的多个入口叶片从第一位置移动到第二位置， 用多个入口叶片偏转任何异物。

公开(公告)号：US08397484B2

公开(公告)日：2013-03-19

申请号：US13028498

申请日：2011-02-16

Applicant: Sam D. Draper ,  Douglas S. Byrd ,  Carl G. Schott ,  Rahul J. Chillar ,  Amit S. Toprani

Inventor： Sam D. Draper ,  Douglas S. Byrd ,  Carl G. Schott ,  Rahul J. Chillar ,  Amit S. Toprani

IPC: F02G5/02 ,  F02G7/052 ,  F02G7/055 ,  F02M35/024 ,  F02M25/07 ,  B01D50/00

CPC classification number: F02C1/005 ,  F02C3/34 ,  F02C7/05 ,  F05D2270/08

Abstract: An embodiment of the present invention takes the form of a system that may recirculate a portion of the exhaust of at least one turbomachine where it may be mixed with the inlet air and re-enter the turbomachine without affecting reliability and availability of the unit. An embodiment of the present invention provides an inlet system for an exhaust gas recirculation system. This inlet system may take a variety of forms and may optimize the direction that the portion of the recirculated exhaust stream flows within the inlet system.