| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 对旋式螺旋桨发动机 | CN201110300962.5 | 2008-02-06 | CN102390523A | 2012-03-28 | A·B·帕里; N·霍沃思; M·D·泰勒 |
| 本发明提供一种对旋式螺旋桨发动机，其具有前螺旋桨和后螺旋桨(23，24)，所述前螺旋桨和后螺旋桨包括可变间距桨叶，所述前螺旋桨(23)具有至少9个桨叶(Nf＝9)和直径Df，所述后螺旋桨(24)具有的最大桨叶数目Nr＝Nf减去至少3，前螺旋桨和后螺旋桨(23，24)以轴向间隙x分开，其中根据等式比率x/Df介于0.15与0.4之间。 | ||||||
| 2 | 改进型螺旋桨同步移相器 | CN86106717 | 1986-09-30 | CN1011215B | 1991-01-16 | 克米特·伊凡·哈纳; 罗伊·威尔弗雷德·施奈德; 马克·林·哈里斯 |
| 一种改进型从属的螺旋桨同步移相器(10)包括一个对相位差信号(28)和相位差基准信号(26)起响应的第一控制器(14)，用以提供相位误差信号(112)和为调速器(46)提供螺旋桨速度基准偏差信号(40)，根据本发明也包括一对相位误差信号(112)起响应的第二控制器(12)，用以为发动机功率控制器提供发动机功率基准偏差信号(80)，以便在螺旋桨调速器的死区内提供一十分有限的量的螺旋桨微小的速度控制，而同时在根据要求的功率水准大体上保持发动机功率。 | ||||||
| 3 | 操作对旋式螺旋桨发动机进行降噪的方法和这种发动机 | CN200880004627.7 | 2008-02-06 | CN101657607A | 2010-02-24 | A·B·帕里; N·霍沃思; M·D·泰勒 |
| 本发明提供操作对旋式螺旋桨发动机的方法，这种对旋式螺旋桨发动机具有前螺旋桨和后螺旋桨。至少在起飞、爬升、巡航和进场阶段操作该发动机；在巡航阶段，发动机以大体上恒定的螺旋桨尖端速度操作。该方法包括以下步骤：操作发动机使得螺旋桨中的至少一个的尖端速度在起飞、爬升或进场中至少一个的期间处于比巡航尖端速度更大的尖端速度以减小由螺旋桨产生的总噪声。 | ||||||
| 4 | 改进型螺旋桨同步移相器 | CN86106717 | 1986-09-30 | CN86106717A | 1987-04-01 | 克米特·伊凡·哈纳; 罗伊·威尔弗雷德·; 施奈德; 马克·林·哈里斯 |
| 一种改进型从属的螺旋桨同步移相器(10)包括 一第一控制器(14)对相位差信号(28)和相位差基准 信号(26)起响应，用作提供相位误差信号(112)和用 作为调速器(46)提供螺旋桨速度基准偏差信号 (40)，根据本发明也包括一第二控制器(12)对相位 误差信号(112)起响应，用作为发动机功率控制器提 供发动机功率基准偏差信号(80)，用作在螺旋桨调 速器的死区内提供一十分有限的量的螺旋桨微小的 速度控制，而同时在根据要求的功率水准大体上保 持发动机功率。 | ||||||
| 5 | 操作对旋式螺旋桨发动机进行降噪的方法 | CN200880004627.7 | 2008-02-06 | CN101657607B | 2013-02-27 | A·B·帕里; N·霍沃思; M·D·泰勒 |
| 本发明提供操作对旋式螺旋桨发动机的方法，这种对旋式螺旋桨发动机具有前螺旋桨和后螺旋桨。至少在起飞、爬升、巡航和进场阶段操作该发动机；在巡航阶段，发动机以大体上恒定的螺旋桨尖端速度操作。该方法包括以下步骤：操作发动机使得螺旋桨中的至少一个的尖端速度在起飞、爬升或进场中至少一个的期间处于比巡航尖端速度更大的尖端速度以减小由螺旋桨产生的总噪声。 | ||||||
| 6 | 螺旋桨同步移相器 | CN86106719 | 1986-09-30 | CN1010206B | 1990-10-31 | 弗兰克·理查德·尼森; 罗伊·威尔; 弗雷德·施奈德 |
| 一种用于多螺旋桨飞机的改进型从螺旋桨同步移相器和模式逻辑。所指定的主螺旋桨至少有一个最初控制从螺旋桨的速度在主螺旋桨的选定恒定转数之内、相对于主螺旋桨有受控的速度和相位的辅助从螺旋桨，以致主和从螺旋桨周期地同相和然后转换至相位控制器用作在相位差信号具有绝对大小小于选定绝对大小的情况控制从螺旋桨的速度。从而主、从螺旋桨间选定的相位差关系可以在对从螺旋桨的速度有最小瞬变影响的情况下，实现主、从螺旋桨间选定的相位关系。 | ||||||
| 7 | 螺旋桨同步移相器和模式逻辑 | CN86106719 | 1986-09-30 | CN86106719A | 1987-04-01 | 弗兰克·理查德·尼森; 罗伊·威尔·弗雷德·施奈德 |
| 一种用于多螺旋桨飞机的改进型从螺旋桨同步移相器和模式逻辑。所指定的主螺旋桨至少有一个最初控制从螺旋桨的速度在主螺旋桨的选定恒定转数之内、相对于主螺旋桨有受控的速度和相位的辅助从螺旋桨，以致主和从螺旋桨周期地同相和然后转换至相位控制器用作在相位差信号具有绝对大小小于选定绝对大小的情况控制从螺旋桨的速度。从而主、从螺旋桨间选定的相位差关系可以在对从螺旋桨的速度有最小瞬变影响的情况下，实现主、从螺旋桨间选定的相位关系。 | ||||||
| 8 | Noise control device of the aircraft cabin | JP50373987 | 1987-06-23 | JP2620274B2 | 1997-06-11 | エリオツト，ステイーブン・ジヨン; ネルソン，フイリツプ・アーサー |
| In propeller or fan driven aircraft, cabin noise levels may be reduced by adjustment of the phase relationship between a reference propeller or fan and some or all of the other propellers or fans. An aircraft cabin (1) contains four microphones (2,3,4,5) and two loudspeakers (6,7) which form the active elements of a noise control system. The microphone outputs are fed via amplifiers (12, 13, 14, 15) to a digital signal processor (11) having an adaptation algorithm in a memory store. The processor generates an error signal which is used to adjust the synchrophase angle between the reference propeller (10) and a synchrophased propeller (9), controlled by a synchrophaser (8). Thus the synchrophase angle is varied dynamically during flight to minimise propeller noise in the cabin over a range of flying conditions. | ||||||
| 9 | Synchronous control device of propeller | JP9613690 | 1990-04-11 | JPH0314794A | 1991-01-23 | ROI DABURIYU SHIYUNAIDAA |
| PURPOSE: To eliminate discontinuity by controlling the rotation of master and slave propellers in consideration of the discontinuous change amount of phase calculated from the counted number of phase discontinuities in measuring a phase difference of master and slave propellers of an aircraft to be used for the rotational control of the master and slave propellers. CONSTITUTION: In a synchronous control device in a multi-engine propeller drive aircraft, a detecting means is provided for detecting a phase difference between a master propeller pulse and a slave propeller pulse, and a counting means is provided for detecting the occurrence time of phase discontinuties in the phase measurement value and counting the number of occurrence times of phase discontinuties. The count value of the phase change is multiplied by 360 degrees, and the multiplication result is divided by a pulse number per one turn of a propeller to calculate the phase discontinuty change amount. Further, the discontinuity change amount and the phase difference are added to calculate the total phase change amount between the master and slave propellers, and according to the total phase change amount, the rotation of the master and slave propellers is controlled. COPYRIGHT: (C)1991,JPO | ||||||
| 10 | JPS5318675B2 - | JP5692773 | 1973-05-23 | JPS5318675B2 | 1978-06-16 | |
| 11 | Aircraft engine | JP2009548734 | 2008-02-06 | JP5489727B2 | 2014-05-14 | パリー，アンソニー・ブライアン; ハワース，ニコラス; テイラー，マーク・デイヴィッド |
| 12 | JPH01502973A - | JP50373987 | 1987-06-23 | JPH01502973A | 1989-10-12 | |
| In propeller or fan driven aircraft, cabin noise levels may be reduced by adjustment of the phase relationship between a reference propeller or fan and some or all of the other propellers or fans. An aircraft cabin (1) contains four microphones (2,3,4,5) and two loudspeakers (6,7) which form the active elements of a noise control system. The microphone outputs are fed via amplifiers (12, 13, 14, 15) to a digital signal processor (11) having an adaptation algorithm in a memory store. The processor generates an error signal which is used to adjust the synchrophase angle between the reference propeller (10) and a synchrophased propeller (9), controlled by a synchrophaser (8). Thus the synchrophase angle is varied dynamically during flight to minimise propeller noise in the cabin over a range of flying conditions. | ||||||
| 13 | Rotating-speed measuring device | JP29172586 | 1986-12-09 | JPS62156565A | 1987-07-11 | POORU DENISU KOROPII; JIYOOJI WASHINTON BENETSUTO |
| 14 | Propeller synchrophaser and mode logic device | JP23106586 | 1986-09-29 | JPS6280198A | 1987-04-13 | FURANKU RICHIYAADO NIISEN; ROI UIRUFURETSUDO SHIYUNAIDAA |
| 15 | JPS4943084A - | JP5692773 | 1973-05-23 | JPS4943084A | 1974-04-23 | |
| 16 | Aeroengine | JP2013056075 | 2013-03-19 | JP2013144545A | 2013-07-25 | PARRY ANTHONY BRIAN; HOWARTH NICHOLAS; TAYLOR MARK DAVID |
| PROBLEM TO BE SOLVED: To provide a method of operating a counter-rotating propeller engine having front and rear propellers to decrease the whole noise generated by the propeller.SOLUTION: The engine 10 is operated during at least a take-off phase, a climb phase, a cruise phase and an approach phase; and during the cruise phase, the engine operates with a generally constant propeller tip speed. The method comprises the step of operating the engine such that the tip speed of at least one of the propellers 23 and 24, during at least one of the take-off phase, the climb phase or the approach phase, may greater the tip speed greater than the cruise phase tip speed to reduce the overall noise generated by the propellers. | ||||||
| 17 | Aircraft comprising an engine that is controlled by the phase sync | JP2011519219 | 2009-07-21 | JP2011529005A | 2011-12-01 | ソクレー ジャン−ミシェル; シャレイル フィリップ |
| 本発明の航空機（５０）は、二重反転回転翼を有するエンジンを少なくとも１つ備え、少なくとも１つのエンジンが少なくとも１つの楕円（７０）に関係する不均衡を有する。 上記航空機は、所定のエンジン速度で、楕円の、又は複数の楕円のうちの少なくとも１つの長軸（６８）の少なくとも１つの所定の共通方向において、上記ダンパの２つの端部に対する速度が該ダンパの他の配置における当該速度よりも大きいような配置で取り付けられた少なくとも１つの振動ダンパ（６４，６６）を含んでいる。
【選択図】図７ |
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| 18 | Aircraft engine | JP2009548734 | 2008-02-06 | JP2010517859A | 2010-05-27 | テイラー，マーク・デイヴィッド; パリー，アンソニー・ブライアン; ハワース，ニコラス |
| 【課題】前後のプロペラ（２３、２４）を持つ二重反転プロペラエンジンの作動方法を提供する。 エンジンは、少なくとも離陸段階、上昇段階、巡行段階、及び着陸進入段階に作動し、巡行段階、エンジンは、ほぼ一定のプロペラ先端速度で作動する。 本方法は、少なくとも一方のプロペラの先端速度を、少なくとも離陸段階、上昇段階、又は着陸進入段階のうちのひとつの段階に、巡行段階の先端速度よりも大きくし、プロペラが発生する騒音全体を減少するようにエンジンを作動する工程を含む。
【選択図】図１ |
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| 19 | Phase control device of the propeller | JP32321988 | 1988-12-21 | JP2733270B2 | 1998-03-30 | ANSONII NYUUMAN MAACHIN |
| 20 | Propeller phase control device | JP32321988 | 1988-12-21 | JPH01197200A | 1989-08-08 | ANSONII NIYUUMAN MAACHIN |
| PURPOSE: To improve navigation performance in an aircraft in which plural engines are mounted by providing a signal generating unit to generate speed and phase synchronism reference signals common to the engines in accordance with control navigation data of the engines. CONSTITUTION: In a propeller plane 11 in which engine 12, 14 respectively provided with propellers 15, 16 are mounted at a back part, in performing phase synchronism control of the propellers 15, 16 by a phase synchronism control device 10, a phase synchronism control device 10 is provided with a phase reference signal generating device 18 including two phase synchronism reference signal generating units corresponding to respective engines 12, 14. Speed and phase synchronism phase reference signals common to the engines 12, 14 are generated from the reference signal generating units in accordance with control navigation data indicating output performance of each engine. Rotation speed/ phase control devices 23, 24 are controlled by engine control devices 21, 22 based on the synchronism reference signals and output signals of a data inputting device 28 through electron switches 19, 20. COPYRIGHT: (C)1989,JPO | ||||||
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