公开(公告)号：US11927143B2

公开(公告)日：2024-03-12

申请号：US16982289

申请日：2019-03-22

申请人： GE Avio S.r.l.

发明人： Giuseppe Donini ,  Stefano Ettorre ,  Pierpaolo Forte

IPC分类号： F02C9/58 ,  F02C9/28

CPC分类号： F02C9/58 ,  F02C9/28 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2270/021

摘要： An electronic control system (35) for a turbopropeller (2) having a gas turbine engine (20) and a propeller assembly (3) coupled to the gas turbine engine (20), the control system (35) having: a propeller control stage (35a), implementing a closed loop control for controlling operation of the propeller assembly (3) based on a scheduled propeller speed reference (Nrref) and a propeller speed measure (Nr); a gas turbine control stage (35b), implementing a closed loop control for controlling operation of the gas turbine engine (20) based on a scheduled reference (Ngdotref) and at least a feedback quantity. The control system (35) further envisages an auxiliary control stage (35c), coupling the propeller control stage (35a) and the gas turbine control stage (35b) and determining a limitation of the operation of the gas turbine engine (20), if a propeller speed overshoot is detected, with respect to the propeller speed reference (Nrref).

公开(公告)号：US20180045123A1

公开(公告)日：2018-02-15

申请号：US15666441

申请日：2017-08-01

申请人： Safran Aircraft Engines

发明人： Bogdan Christian LIACU

IPC分类号： F02C9/58

CPC分类号： F02C9/58 ,  F05D2220/32 ,  F05D2220/324 ,  F05D2240/35 ,  F05D2270/02 ,  F05D2270/053 ,  F05D2270/335

摘要： The present invention relates to a control system (10) of a turbopropeller (1) including: a centralized control (24) configured to slave the screw propeller power PRW of the turbopropeller (1) to the screw propeller power set point PRWref and the screw propeller rotation speed XNP of the turbopropeller (1) to the screw propeller rotation speed set point XNPref, the centralized control (24) supplying fuel flow rate WF and screw propeller pitch β controls for the turbopropeller (1); a screw propeller rotation speed error limiter (12) saturating the screw propeller rotation speed error ΔXNP with a limiting value Δ   XNP sat  ( min  /  max ) ; a screw propeller power error limiter (11) saturating the screw propeller power error ΔPRW with a limiting value Δ   PRW sat  ( min  /  max ) ;

公开(公告)号：US09650962B2

公开(公告)日：2017-05-16

申请号：US14143343

申请日：2013-12-30

申请人： Rolls-Royce Corporation

发明人： Michael Abraham Karam

IPC分类号： F02B27/04 ,  F02C7/24 ,  B64C11/48 ,  F01D5/14 ,  F02K3/02 ,  F02C3/067 ,  F02C6/20 ,  B64D27/00

CPC分类号： F02C7/24 ,  B64C11/48 ,  B64C2230/04 ,  B64C2230/14 ,  B64C2230/16 ,  B64C2230/28 ,  B64D2027/005 ,  F01D5/142 ,  F02C3/067 ,  F02C6/206 ,  F02K3/025 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2260/60 ,  F05D2260/96 ,  Y02T50/166 ,  Y02T50/66 ,  Y02T50/673

摘要： An apparatus is disclosed that includes a gas turbine engine including a first rotor blade axially adjacent a second rotor blade and an aperture formed in one of the first rotor blade and the second rotor blade and structured to emit a fluid therefrom. A fluid source is in flow communication with the aperture and configured to flow the fluid through the aperture.

公开(公告)号：US20160332736A1

公开(公告)日：2016-11-17

申请号：US15115213

申请日：2015-01-29

申请人： SNECMA ,  SAFRAN ,  MICROTURBO

发明人： Nicolas Claude PARMENTIER ,  Pierre FROMENT ,  Jean-Francois RIDEAU ,  Bruno THORAVAL

IPC分类号： B64D13/02 ,  B64D13/08 ,  B64D27/10 ,  B64D13/06

CPC分类号： B64D13/06 ,  B64D13/00 ,  B64D13/02 ,  B64D13/08 ,  B64D27/10 ,  B64D2013/0618 ,  B64D2013/0696 ,  F02C6/206 ,  F02C7/27 ,  F02C9/18 ,  F04D29/321 ,  F04D29/522 ,  F04D29/563 ,  F04D29/5833 ,  F05B2220/303 ,  F05B2260/20 ,  F05D2220/323 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2240/60 ,  F05D2260/4031 ,  Y02T50/56 ,  Y02T50/671 ,  Y02T50/675

摘要： The invention relates to an aircraft turboprop engine (310) comprising at least a low-pressure body (12) and a high-pressure body (14), possibly also an intermediate-pressure body, at least one of said bodies comprising a compressor, the low-pressure body driving a propeller by means of a first gearbox (16), the turboprop engine also comprising means for supplying air to an air-conditioning circuit of an aircraft cabin, characterised in that said supply means comprise at least one compressor (60) of which the rotor (61) is coupled to the low-pressure body, said load compressor (60) including an air inlet (62) connected to means (72) for bleeding air from the compressor of the turboprop engine when all of the aforementioned bodies comprise only a single compressor, or from the compressor of the low-pressure body or the compressor of the intermediate-pressure body of the turboprop engine when all of the bodies comprise at least two compressors.

摘要翻译： 本发明涉及一种飞机涡轮螺旋桨发动机（310），其包括至少一个低压主体（12）和高压体（14），也可能包括中压体，至少一个所述主体包括压缩机， 所述低压体通过第一齿轮箱（16）驱动螺旋桨，所述涡轮螺旋桨发动机还包括用于向飞机机舱的空调回路提供空气的装置，其特征在于，所述供给装置包括至少一个压缩机 60），其中转子（61）联接到低压体，所述负载压缩机（60）包括连接到装置（72）的空气入口（62），用于当涡轮螺旋桨发动机全部 当所有的主体包括至少两个压缩机时，上述主体仅包括单个压缩机，或者来自涡轮螺旋桨发动机的中压装置的低压主体的压缩机或压缩机。

公开(公告)号：US20160229547A1

公开(公告)日：2016-08-11

申请号：US15028611

申请日：2014-09-23

申请人： UNISON INDUSTRIES, LLC

发明人： Edward Aaron FISHER ,  Scott Brian WRIGHT ,  James Robert TURNER

IPC分类号： B64D31/06 ,  B64C11/30 ,  F04D29/36 ,  F01D5/02 ,  F04D27/00 ,  F04D29/32

CPC分类号： B64D31/06 ,  B64C11/303 ,  B64C11/305 ,  F01D5/02 ,  F02C9/00 ,  F04D27/004 ,  F04D29/325 ,  F04D29/362 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2220/36 ,  F05D2260/70 ,  F05D2270/02 ,  F05D2270/70

摘要： A turboprop control system 10 for use with a turboprop 2 having a turbine engine 12 operably coupled to and rotationally driving a propeller 14 having variable pitch blades 16 to control the engine speed, propeller speed, and propeller pitch. The pilot provides, by a single power control lever 30, the control input used to control the engine and propeller.

摘要翻译： 涡轮螺旋桨发动机控制系统10，其用于具有涡轮发动机12的涡轮螺旋桨发动机控制系统10，涡轮发动机12可操作地联接到旋转驱动具有可变桨距叶片16的螺旋桨14，以控制发动机速度，螺旋桨速度和螺旋桨桨距。 飞行员通过单个功率控制杆30提供用于控制发动机和螺旋桨的控制输入。

公开(公告)号：US09140126B2

公开(公告)日：2015-09-22

申请号：US13555166

申请日：2012-07-22

申请人： Anthony V. Hins

发明人： Anthony V. Hins

IPC分类号： B64C11/18 ,  B64C27/467 ,  F01D5/14

CPC分类号： F01D5/141 ,  B64C11/18 ,  B64C27/467 ,  F05D2220/324 ,  F05D2220/325 ,  Y02T50/673

摘要： A novel airfoil design comprising a reactionary front face that pushes into the flow of air with a high angle of attack and a vacuum-producing face which forces the early separation of the flow of air from the top side of the airfoil, creating an area of high negative pressure which pulls upward, contributing to lift.

摘要翻译： 一种新颖的翼型设计，其包括反作用的前表面，其以高冲击力推入空气流和产生真空的面，迫使空气流从翼型的顶侧提前分离，形成一个 高负压向上拉，有助于提升。

公开(公告)号：US08814505B2

公开(公告)日：2014-08-26

申请号：US13202924

申请日：2010-02-22

申请人： Mark J. E. Bellis

发明人： Mark J. E. Bellis

IPC分类号： F01D15/12 ,  F02C3/107 ,  B64C11/48 ,  B64C11/30 ,  B64D35/06 ,  B64D27/00

CPC分类号： F01D15/12 ,  B64C11/306 ,  B64C11/48 ,  B64D35/06 ,  B64D2027/005 ,  F02C3/107 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2260/40311 ,  Y02T50/66

摘要： A mechanical arrangement for an engine having two propeller stages, including: a first epicyclic gear stage including a sun gear, a planet gear, a planet carrier and an annulus, wherein the sun gear is driven by a shaft of the engine, the planet carrier is stationary and thereby permits static structure to be located there through, and the annulus outputs torque and/or drive; a second epicyclic gear stage including a second sun gear, a second planet gear, a second planet carrier and a second annulus, wherein the second sun gear is driven by the annulus of the first epicyclic gear stage and is annular to accommodate the static structure, the second planet carrier includes the output to one of the propeller stages and the second annulus includes the output to the other of the propeller stages; wherein the static structure provides mounting for static components on one or both sides of each epicyclic gear stage.

摘要翻译： 一种用于具有两个螺旋桨级的发动机的机械装置，包括：包括太阳齿轮的第一行星齿轮级，行星齿轮，行星架和环形空间，其中太阳齿轮由发动机的轴驱动，行星架 静止，从而允许静态结构位于那里，并且环带输出扭矩和/或驱动; 第二行星齿轮级，包括第二太阳齿轮，第二行星齿轮，第二行星架和第二环形空间，其中所述第二太阳齿轮由所述第一行星齿轮级的所述环带驱动并且环形以适应所述静态结构， 所述第二行星架包括到所述螺旋桨级中的一个的输出，并且所述第二环包括到所述螺旋桨级中另一个的输出; 其中所述静态结构为每个行星齿轮级的一侧或两侧上的静态部件提供安装。

公开(公告)号：US20140133982A1

公开(公告)日：2014-05-15

申请号：US14111940

申请日：2012-04-13

申请人： Clement Marcel, Maurice Dejeu ,  Sebastien Pascal ,  Jerome Talbotec ,  Michael Leborgne ,  Ingrid Irene, Catherine Lepot

发明人： Clement Marcel, Maurice Dejeu ,  Sebastien Pascal ,  Jerome Talbotec ,  Michael Leborgne ,  Ingrid Irene, Catherine Lepot

IPC分类号： F01D5/14

CPC分类号： F01D5/14 ,  B64C11/18 ,  B64C11/48 ,  B64D2027/005 ,  F02C3/067 ,  F02C3/10 ,  F05D2220/324 ,  F05D2220/325 ,  F05D2250/38 ,  Y02T50/66

摘要： A propulsion device including an unducted upstream propeller and a counter-rotating and coaxial downstream propeller. At least one blade of the upstream propeller is configured to generate a corotating secondary vortex for acting upstream of the downstream propeller to destabilize a blade tip vortex of the same at least one blade.

摘要翻译： 一种推进装置，包括未被引导的上游螺旋桨和反向旋转和同轴的下游螺旋桨。 上游螺旋桨的至少一个叶片被构造成产生用于作用于下游螺旋桨上游的共旋转次级涡流，以使相同的至少一个叶片的叶片尖端涡流不稳定。

公开(公告)号：US08425191B2

公开(公告)日：2013-04-23

申请号：US12130054

申请日：2008-05-30

申请人： Amr Ali

发明人： Amr Ali

IPC分类号： B64C11/24

CPC分类号： F02C6/206 ,  F02C7/24 ,  F05D2220/324 ,  F05D2260/96

摘要： A propfan assembly includes a plurality of blades that each include an internal cavity containing a noise attenuation structure. Acoustic energy is communicated to the internal cavity through a plurality of openings in the blade surfaces. The cavities include features for attenuating noise energy to reduce generation of noise emitted from the propfan assembly.

摘要翻译： 普罗班组件包括多个叶片，每个叶片包括包含噪声衰减结构的内腔。 声能通过叶片表面中的多个开口传递到内腔。 空腔包括用于衰减噪声能量以减少由Propfan组件发出的噪声的产生的特征。

公开(公告)号：US20120121417A1

公开(公告)日：2012-05-17

申请号：US13386173

申请日：2010-07-20

申请人： Laurent Lafont

发明人： Laurent Lafont

IPC分类号： F01D5/30 ,  F01D5/02 ,  F01D5/14

CPC分类号： F01D21/045 ,  B64C11/04 ,  B64C11/48 ,  B64D2027/026 ,  F01D5/3053 ,  F02C6/206 ,  F02K3/025 ,  F04D29/322 ,  F04D29/34 ,  F05D2220/324 ,  Y02T50/66 ,  Y02T50/673

摘要： An aircraft turbomachine propeller including multiple blades assembled on a hub rotating around an axis of rotation of the propeller, that can reduce risks of loss of the blade following impact of a foreign body. At least one blade includes a recess opening radially towards the inside in the area of the base of this blade. A retaining device includes a moving retaining mechanism positioned in the recess and configured to be moved from a retracted position to a deployed blade-retaining position, and vice versa.

摘要翻译： 一种包括多个叶片的飞机涡轮机螺旋桨，其组装在围绕螺旋桨旋转轴线旋转的轮毂上，这可以降低在异物撞击之后叶片损失的风险。 至少一个叶片包括在该叶片的基部的区域中径向朝向内侧开口的凹部。 保持装置包括位于凹部中并被构造成从缩回位置移动到展开的刀片保持位置的移动保持机构，反之亦然。