| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | METHOD FOR DETECTING ROTATING STALL IN A COMPRESSOR | US12960024 | 2010-12-03 | US20110076131A1 | 2011-03-31 | Robert E. STABLEY; E. Curtis EICHELBERGER |
| A system and method is provided for detecting and controlling rotating stall in the diffuser region of a compressor. A pressure transducer is placed in the gas flow path downstream of the impeller, preferably in the compressor discharge passage or the diffuser, to measure the sound or acoustic pressure phenomenon. Next, the signal from the pressure transducer is processed either using analog or digital techniques to determine the presence of rotating stall. Rotating stall is detected by comparing the detected energy amount, which detected energy amount is based on the measured acoustic pressure, with a predetermined threshold amount corresponding to the presence of rotating stall. Finally, an appropriate corrective action is taken to change the operation of the compressor in response to the detection of rotating stall. | ||||||
| 182 | Method for detecting rotating stall in a compressor | US11690222 | 2007-03-23 | US07905702B2 | 2011-03-15 | Robert E. Stabley; E. Curtis Eichelberger, Jr. |
| A system and method is provided for detecting and controlling rotating stall in the diffuser region of a compressor. A pressure transducer is placed in the gas flow path downstream of the impeller, preferably in the compressor discharge passage or the diffuser, to measure the sound or acoustic pressure phenomenon. Next, the signal from the pressure transducer is processed either using analog or digital techniques to determine the presence of rotating stall. Rotating stall is detected by comparing the detected energy amount, which detected energy amount is based on the measured acoustic pressure, with a predetermined threshold amount corresponding to the presence of rotating stall. Finally, an appropriate corrective action is taken to change the operation of the compressor in response to the detection of rotating stall. | ||||||
| 183 | Turbine anti-rotating stall schedule | US11746860 | 2007-05-10 | US07972105B2 | 2011-07-05 | Timothy Dejoris; Michael J. Dutka; Nick Martin; Steven M. Schirle |
| A method of starting up a turbine with a compressor have an inlet guide vane, a number of bleed valves, and a number of blades so as to limit the duration in a rotating stall window. The method may include starting rotation of the blades, increasing the speed of the rotation of the blades, closing one or more bleed valves so as to shift the rotating stall window to a higher rotational speed, partially opening the inlet guide vane to a position outside the rotating stall window, and opening the bleed valves while partially closing the inlet guide vane such that the number of blades pass through the rotating stall window. | ||||||
| 184 | Turbine Anti-Rotating Stall Schedule | US11746860 | 2007-05-10 | US20080279676A1 | 2008-11-13 | Timothy Dejoris; Michael J. Dutka; Nick Martin; Steven M. Schirle |
| A method of starting up a turbine with a compressor have an inlet guide vane, a number of bleed valves, and a number of blades so as to limit the duration in a rotating stall window. The method may include starting rotation of the blades, increasing the speed of the rotation of the blades, closing one or more bleed valves so as to shift the rotating stall window to a higher rotational speed, partially opening the inlet guide vane to a position outside the rotating stall window, and opening the bleed valves while partially closing the inlet guide vane such that the number of blades pass through the rotating stall window. | ||||||
| 185 | METHOD FOR DETECTING ROTATING STALL IN A COMPRESSOR | EP08732524.7 | 2008-03-20 | EP2129921B1 | 2011-12-21 | STABLEY, Robert, E.; EICHELBERGER, E. Curtis |
| A system and method is provided for detecting and controlling rotating stall in the diffuser region of a compressor. A pressure transducer is placed in the gas flow path downstream of the impeller, preferably in the compressor discharge passage or the diffuser, to measure the sound or acoustic pressure phenomenon. Next, the signal from the pressure transducer is processed either using analog or digital techniques to determine the presence of rotating stall. Rotating stall is detected by comparing the detected energy amount, which detected energy amount is based on the measured acoustic pressure, with a predetermined threshold amount corresponding to the presence of rotating stall. Finally, an appropriate corrective action is taken to change the operation of the compressor in response to the detection of rotating stall. | ||||||
| 186 | Stall prediction method for axial flow compressor | US10165927 | 2002-06-10 | US06715984B2 | 2004-04-06 | Takurou Nakajima; Nobuyuki Tahara; Masahiro Kurosaki |
| In order to provide a stall prediction method for an axial flow compressor, a high response pressure sensor is provided in a duct wall adjacent to the leading edge of the rotor blade and a rotating stall is predicted by computing autocorrelation of pressure data obtained as a time history data. The initiation of rotating stall is determined when the autocorrelation of the time history data starts dropping rapidly. When it is determined that the rotating stall is imminent, generation of the rotating stall is prevented by taking necessary countermeasures such as to reduce the fuel supply. | ||||||
| 187 | Asymmetric compressor air extraction method | US11588389 | 2006-10-27 | US20080101922A1 | 2008-05-01 | Steven Mark Schirle; Donald Kasperski; Nick Martin; Robert M. Zacharias; Timothy E. Dejoris |
| A method to mistune rotating stall aerodynamics by preventing the formation of coherent unsteady loads. Compressor air is extracted in an asymmetric circumferential pattern. The asymmetric bleed pattern disrupts the rotating stall cell rotational pattern, preventing the formation of a coherent aerodynamic excitation. | ||||||
| 188 | Diffuser structure of fluid machine | JP2011005406 | 2011-01-14 | JP2012145064A | 2012-08-02 | FUKAO SHINJI; SANO TAKASHI; IINO MASANARI; KAWANE HIROSHI; WAKAI MUNEYA |
| PROBLEM TO BE SOLVED: To provide a diffuser structure of a fluid machine that improves low-flow-rate properties effectively by a simple structural change and both prevents rotating stall and reduces impact loss.SOLUTION: In a diffuser 12, of a pump or the like, having the even number of blades 11 with equal pitch, the blade thickness of at least a leading edge of the respective blades 11 is alternately varied. | ||||||
| 189 | Stall prediction method for axial flow compressor | US10165927 | 2002-06-10 | US20030007860A1 | 2003-01-09 | Takurou Nakajima; Nobuyuki Tahara; Masahiro Kurosaki |
| In order to provide a stall prediction method for an axial flow compressor, a high response pressure sensor is provided in a duct wall adjacent to the leading edge of the rotor blade and a rotating stall is predicted by computing autocorrelation of pressure data obtained as a time history data. The initiation of rotating stall is determined when the autocorrelation of the time history data starts dropping rapidly. When it is determined that the rotating stall is imminent, generation of the rotating stall is prevented by taking necessary countermeasures such as to reduce the fuel supply. | ||||||
| 190 | VERFAHREN UND VORRICHTUNG ZUR STABILISIERUNG EINES VERDICHTERSTROMS | PCT/EP2012/005308 | 2012-12-20 | WO2013107489A1 | 2013-07-25 | BINDL, Stefan; STÖSSEL, Marcel; NIEHUIS, Reinhard; MUTH, Bastian |
Ein Einblasesystem für das Verdichtersystem einer Turbomaschine, bei welchem ein rezirkulierter oder extern zugeführter Primärmassenstrom unter Ausnutzung des Ejektoreffekts einen Sekundärmassenstrom aus dem Außenbereich des Verdichtergehäuses fordert, ermöglicht eine wirksame Stabilisierung des Verdichterstromes und wirkt einer rotierenden Strömungsablösung an den Verdichterschaufeln entgegen. |
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| 191 | METHOD FOR THE ELIMINATION OF ROTATIONAL STALL IN A TURBINE ENGINE | US14002543 | 2012-02-28 | US20140075952A1 | 2014-03-20 | Cédrik Djelassi |
| A method for eliminating rotational stall in a compressor of a turbine engine, includes automatically detecting surge in the turbine engine; automatically shutting-down the turbine engine; in the event surge is detected, automatically restoring a surge margin; and automatically re-igniting the turbine machine. | ||||||
| 192 | A METHOD AND DEVICE FOR DETERMINING THE OCCURENCE OF ROTATING STALL IN A COMPRESSOR'S TURBINE BLADE II | PCT/NO2007/000026 | 2007-01-24 | WO2007086755A1 | 2007-08-02 | MOEN, Lyder |
A method and device for determining the occurrence of rotating stall in the turbine blade (3) of a compressor (1), in which the blade pass frequency of at least one compressor stage (2) and the associated vibration energy are monitored, the normal blade pass frequency being constituted by the operating speed of rotation of the compressor (1) multiplied by the number of turbine blades (3) in the stage (2), and in which incipient rotating stall in a compressor stage (2) is indicated when, at the normal blade pass frequency (34) of the compressor stage (2), the vibration energy (28) falls below a predetermined first value (40) at the same time as, at a blade pass frequency (42) above the normal blade pass frequency (34), the vibration energy (30) rises above a predetermined second value (44). |
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| 193 | DIAGNOSING AND CONTROLLING ROTATING STALL AND SURGE IN ROTATING MACHINERY | PCT/US1999/001490 | 1999-02-18 | WO99042240A1 | 1999-08-26 | |
| A method and apparatus is provided for diagnosing and correcting rotating stall and surge in rotating machines (20) by monitoring dynamic shaft precession as the machine approaches a destabilizing condition when indicated by the comparison step. Axial vibration monitoring means (26) is also provided for monitoring and comparing a dynamic axial vibration of the machine with a standard and altering the axial vibration as the machine approaches a destabilizing condition. Furthermore, the instant invention measures the complex dynamic stiffness of the machine and computes the direct dynamic stiffness and the quadrature dynamic stiffness for use as a destabilizing warning device by monitoring for a drop in direct dynamic stiffness and the quadrature dynamic stiffness components. One embodiment for altering the rotating stall and/or surge is by a controlled active servobearing (40). | ||||||
| 194 | Rotating stall preventing device for compressor | JP14534092 | 1992-06-05 | JPH05340385A | 1993-12-21 | ISHII HIROSHI; KASAHARA MASAYUKI; KASHIWABARA YASUNARI; KATO YASUHIRO; SASADA TETSUO |
| PURPOSE:To improve an unsteady flow field directly to expand a stable action range, and prevent rotating stall of a compressor by changing a flow condition of a compressor flow passage by drive control to a flow fairing blade based on a detection signal of a rotating stall sensor disposed in the compressor flow passage. CONSTITUTION:In a compressor, an inlet guide blade 7, a movable blade 8, a static blade 9, and an outlet guide blade 10 are installed in a casing 11, and a compressor flow passage is formed. In this case, a flow fairing blade 6 is disposed upstream of the inlet guide blade 7, and a rotating stall sensor 1 is disposed upstream thereof. A detection signal of the rotating stall sensor 1 is inputted through an amplifier 2 to a computation device 3, while a computation signal of the computation device 3 is outputted to a motor 5 through a servo amplifier 4. An installation angle of the flow fairing blade 6 is changeably controlled, and a flow condition of the compressor flow passage is regulated to be the optimum. An unsteady flow field is thus directly improved against the rotating stall of the compressor, thereby a stable action range is expanded, with the rotating stall prevented. | ||||||
| 195 | Method of operating a gas turbine power plant | EP06111737.0 | 2006-03-27 | EP1840355A1 | 2007-10-03 | Matz, Charles; Erb, Bernhard; Das Burma, Bikash; Beresini, Luca; Treiber, Dr. Martin Heinrich; Marx, Peter |
In a method of operating a gas turbine during shut down the gas turbine is decelerated and closure of compressor inlet guide vanes (1) is initiated at a shaft speed at least 5% above the shaft speed where a vibration peak occurs. The compressor inlet guide vanes (1) are closed by an angle in the range from 15°-35°, preferably at a rate between 5° and 10° per second. The method effects a reduction of the risk of rotational stall.
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| 196 | FLOW CONTROL METHOD AND MEANS | PCT/GB1991001407 | 1991-08-19 | WO1992003661A1 | 1992-03-05 | ROLLS ROYCE PLC |
| The invention provides a method of controlling gas flow in an axial flow compressor (C) in which the flow at least at one chosen station in the direction of flow through the compressor the flow is sensed at a series of circumferentially spaced positions. Flow variations above a predetermined limit are evaluated to give an actuating response if a disturbance above a predetermined acceptable level is detected. When such a disturbance is detected, higher pressure gas bled from further downstream is injected at said station to supplement the main gas flow there. An incipient rotating stall cell will appear as a variation occurring sequentially at the circumferentially spaced positions. By responding to such a condition with a pressure injection flow, it is found possible to suppress both rotating stall and surge conditions in the compressor before the disturbance develops fully. The same means can be arranged to counter steady state distortion. | ||||||
| 197 | COMPRESSOR MONITORING METHOD, APPARATUS AND COMPUTER READABLE MEDIUM | EP15191565.9 | 2015-10-27 | EP3018357A1 | 2016-05-11 | Elysee, David Andre |
A method of predicting the condition of a compressor with respect to rotating stall is disclosed. The method comprises the steps of: |
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| 198 | 遠心圧縮機 | PCT/JP2010/058831 | 2010-05-25 | WO2011070808A1 | 2011-06-16 | 枡谷 穣 |
旋回失速開始マージンを拡大し、旋回失速を防止しつつ、効率の低下を抑制することができる遠心圧縮機を提供する。インペラ（５Ａ）の出口側にベーンレスディフューザ（７Ａ）が設けられている遠心圧縮機（１）において、ベーンレスディフューザ（７Ａ）のハブ側ケーシング（２Ｂ）の壁面に流体入口（１２Ａ）が開口され、インペラ（５Ａ）のハブディスク（５Ｃ）の背面と対向するハブ側ケーシング（２Ｂ）の壁面に流体出口（１２Ｂ）が開口されているスリット状の流体循環路（１２）が設けられており、該スリット状流体循環路（１２）の流体入口（１２Ａ）は、開口部の中心がインペラ（５Ａ）の出口半径を（Ｒ２）としたとき、１．１（Ｒ２）ないし１．４（Ｒ２）の位置にあって、ベーンレスディフューザ（７Ａ）での旋回失速開始半径位置よりも半径方向外側位置に開口されている。 |
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| 199 | Method and equipment for detecting rotating stall and compressor | JP2012257002 | 2012-11-26 | JP2013122242A | 2013-06-20 | GALEOTTI DANIELE; ROSSI DAVID |
| PROBLEM TO BE SOLVED: To provide a method and equipment for detecting initial surge, namely rotating stall in a compressor accurately, simply and flexibly.SOLUTION: The compressor 1 includes one or more rotating rotors 2 and a stationary stator 3. The rotating stall is detected through a stage of measuring radial vibration of the rotor relative to the stator and generating a vibration measurement signal corresponding thereto, a stage of calculating a frequency spectrum of the vibration measurement signal, a stage of identifying a plurality of frequency bandwidths of the frequency spectrum, a stage of not neglecting all of the plurality of frequency bandwidths or neglecting one or more frequency bandwidths, a stage of determining the maximum magnitude of the spectrum in each of the non-neglected frequency bandwidths, and a stage of performing comparison between each determined maximum magnitude and a predetermined value. Rotating stall is considered occurring if at least one of the comparisons shows that the corresponding determined maximum magnitude is greater than the predetermined value. | ||||||
| 200 | Centrifugal blower | JP24900699 | 1999-09-02 | JP2001073991A | 2001-03-21 | MATSUO TAKAHIRO |
| PROBLEM TO BE SOLVED: To suppress the occurrence of a rotation stall of a centrifugal blower and to effectively suppress the generation of noise due to a pressure fluctuation of gas due to a rotation stall and the generation of vibration exerted on a structure. SOLUTION: A centrifugal blower is provided with an inlet damper 3 installed at the gas inflow port of an inlet box 2, a damper blade 4 situated at an inlet damper and regulating a gas flow rate, and an impeller 1 having a impeller vane 9 to boost gas, introduced from the inlet box, through centrifugal operation. A guide vane 11 is situated at the inlet box 2 in the vicinity of a gas introduction port to the impeller 1 and the guide vane 11 straightens a flow of gas flowing in the impeller 1 and gas revolution suited for the angle of the impeller vane 9 is exerted. COPYRIGHT: (C)2001,JPO | ||||||
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