US20100011846A1 - Stall and surge detection system and method - Google Patents
Stall and surge detection system and method Download PDFInfo
- Publication number
- US20100011846A1 US20100011846A1 US12/175,889 US17588908A US2010011846A1 US 20100011846 A1 US20100011846 A1 US 20100011846A1 US 17588908 A US17588908 A US 17588908A US 2010011846 A1 US2010011846 A1 US 2010011846A1
- Authority
- US
- United States
- Prior art keywords
- dynamic pressure
- pressure signal
- signal
- rotor
- compressor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/02—Arrangement of sensing elements
- F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
- F05D2270/101—Compressor surge or stall
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
Description
- The subject matter disclosed herein relates generally to monitoring health of rotating mechanical components, and more particularly, to stall and surge detection in a compressor of a turbine.
- In gas turbines used for power generation, compressors are typically allowed to operate at high pressure ratios in order to achieve higher efficiencies. During operation of a gas turbine, a phenomenon known as compressor stall may occur, when the pressure ratio of the turbine compressor exceeds a critical value at a given speed the compressor pressure ratio is reduced and the airflow that is delivered to the engine combustor is also reduced and in some circumstances may reverse direction. Compressor stalls have numerous causes. In one example, the engine is accelerated too rapidly. In another example, the inlet profile of air pressure or temperature becomes unduly distorted during normal operation of the engine. Compressor damage due to the ingestion of foreign objects or a malfunction of a portion of the engine control system may also cause a compressor stall and subsequent compressor degradation. If a compressor stall remains undetected and is permitted to continue, the combustor temperatures and the vibratory stresses induced in the compressor may become sufficiently high to cause damage to the turbine.
- One approach to compressor stall detection is to monitor the health of a compressor by measuring the air flow and pressure rise through the compressor. Pressure variations may be attributed to a number of causes such as, for example, unstable combustion, rotating stall, and surge events on the compressor itself. To determine these pressure variations, the magnitude and rate of change of pressure rise through the compressor may be monitored. This approach, however, does not offer prediction capabilities of rotating stall or surge, and fails to offer information to a real-time control system with sufficient lead time to proactively deal with such events.
- Briefly, a method for monitoring a compressor comprising a rotor is presented. The method comprises obtaining a dynamic pressure signal of the rotor, obtaining a blade passing frequency of the rotor, using the blade passing frequency signal for filtering the dynamic pressure signal, buffering the filtered dynamic pressure signal over a moving window time period, and analyzing the buffered dynamic pressure signal to predict a stall condition of the compressor.
- In another embodiment, a system for monitoring a compressor comprising a rotor is presented. The system comprises a pressure sensor configured for obtaining a dynamic pressure signal of the rotor, a speed sensor configured for obtaining a speed signal of the rotor, a controller configured for using the rotor speed signal for filtering the dynamic pressure signal, buffering the filtered dynamic pressure signal over a moving window time period, and analyzing the buffered dynamic pressure signal to predict a stall condition of the compressor.
- These and other features, aspects, and advantages of the present invention will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:
-
FIG. 1 is a cross sectional view of a compressor with sensors in accordance with one aspect of the invention; -
FIG. 2 illustrates a block diagram of a compressor monitoring and controlling system according to one embodiment of the invention; -
FIG. 3 is a block diagram illustrating monitoring and controlling of compressor health in accordance with one embodiment disclosed herein; and -
FIG. 4 is a Fast Fourier transform representation over a long time period. - As discussed in detail below, embodiments of the invention include a gas turbine system having a compressor and a system for monitoring the compressor. In an exemplary embodiment of the invention, an industrial gas turbine is used as part of a combined cycle configuration that also includes, for example, steam turbine and a generator to generate electricity from combustion of natural gas of other combustion fuel. The industrial gas turbine may be operated in combined cycle system or simple cycle system. However, in both the cycle systems it is a desirable goal to operate the industrial gas turbine at the highest operating efficiency to produce high electrical power output at relatively low cost. Typically, in a highly efficient industrial turbine system, a compressor should be operated to produce a cycle pressure ratio that corresponds to a high firing temperature. However, the compressor can experience aerodynamic instabilities, such as, for example, a stall and/or surge condition, as the compressor is used to produce the high firing temperature or the high cycle pressure ratio. It may be appreciated that the compressor experiencing such stall and/or surge may cause problems that affect the components and operational efficiency of the industrial gas turbine. Typically, to maintain stability, it is desirable to engage the industrial gas turbine within operational limits of cycle pressure ratio.
-
FIG. 1 illustrates a cross-sectional view of a compressor wherein sensors are installed at various locations within the compressor to sense compressor parameters. As illustrated thecompressor system 10 includes arotor 12 and astator 14. Further, thereference numeral 16 indicates the flow direction wherein working fluids are progressively compressed between 16 and 18. Typically such compressors use multi-stage compression wherein thestator 14 may be configured to prepare and/or redirect the flow from therotor 12 to a subsequent rotor or to the plenum. In one embodiment of the invention, location of sensors at 20 is better suited to sense the compressor parameters that indicate stall and/or surge condition. However, it may be noted that sensors are placed in various locations such as for example, 22 and 24 to sense the parameters. Sensors may include for example, speed sensors configured to detect rotational speed and pressure sensors configured to detect pressure dynamically. -
FIG. 2 is a diagrammatic representation of a compressor monitoring and control system as implemented in thecompressor system 10 ofFIG. 1 . The compressor monitoring andcontrol system 30 includes a controller. In an exemplary embodiment, the controller includes afilter 32, astorage medium 40, asignal processor 42, acomparator 44, a lookup table 46, and astall indicator 48. The system includes sensors for obtaining adynamic pressure signal 36 and obtaining a blade passing frequency from therotor speed signal 34 and using the blade passing frequency for filtering thedynamic pressure signal 36. Thefilter 32 is coupled to sensors (not shown). Corresponding to the compressor parameters, the sensors generate signals such asrotor speed signal 34 anddynamic pressure signal 36. In one embodiment of the invention, thefilter 32 is configured to filter the sensed parameters of the compressor such asrotor speed signal 34 anddynamic pressure signal 36. Further the filter is configured to remove undesired components such as for example, high frequency noise from the sensed parameters. According to a contemplated embodiment of the invention, the filter includes multiple configurations such as second order low pass, first order low frequency high pass, and sixth order Chebychev band pass filters. It may be appreciated by one skilled in the art, that such filters have configuration parameters such as pass band and cut off frequencies set appropriately depending on input parameters and desired output. - Buffering (or storing) of filtered data over a period of time is performed over a sample rate during a moving window. In one example, the moving window occurs over a period of at least four seconds. The
storage medium 40 is configured to store the filtered data and/or buffered data. The controller is further configured, in one embodiment, to shift the buffered dynamic pressure signal to a lower frequency domain.Signal processor 42 is coupled to thestorage medium 40 and configured to compute a fast Fourier transform of the buffered data. Thecomparator 44 is coupled to thesignal processor 42 and configured to compare the computed Fast Fourier Transform data with a pre-determined baseline value. The pre-determined baseline value is stored in a look up table 46 that is coupled to the comparator. It may be appreciated that the pre-determined baseline value is calculated by way of stall likelihood measurements and constants. Thesystem 30 further includes astall indicator 48 coupled to thecomparator 44 and configured to generate astall indication signal 50 based upon the comparison. Thestall indication signal 50 is coupled to the compressor for corrective action in case of stall likelihood. -
FIG. 3 is a more detailed block diagram illustrating various steps of monitoring and controlling of compressor health in accordance with embodiments of the invention. In an exemplary embodiment, thecompressor monitoring system 56 includes alow pass filter 58 that is configured to receiverotor speed signal 34 from sensors coupled to the compressor (not shown inFIG. 3 ). The low pass filter is configured, in a more specific embodiment to filter the rotor speed signal via a second order low pass filter. Typically the cut-off frequency is about 0.1 Hz. However, the cut-off frequency is dependent on speed control topology. - A speed to
frequency converter 60 is coupled to the low pass filter to convert the filtered rotor speed signal into ablade passing frequency 62. It may be noted that the blade passing frequency is a product of the mechanical speed and number of rotor blades. - In a presently contemplated embodiment of the invention, the compressor parameter such as pressure is monitored dynamically. The
dynamic pressure signal 36 is filtered via first order low frequency high pass filter to remove low frequency bias and may further be filtered via Chebychev band pass filter with both filters reference byfilter element 66 with attenuation outside the pass-band of about 40 dB to obtain filtereddynamic pressure signal 68. As will be appreciated by one skilled in the art, the band-pass should have a margin of few hundred hertz to factor in the variations in monitored parameter. Furthermore, the sampling rate of the dynamic pressure signal measurement is typically on the order of at least 2 or 3 times the band pass frequency. If the mechanical speed remains constant, the band pass filter constants may remain constant. If the location of the blade passing frequency changes, however, it is useful to update the band pass filter constants to reflect the new location of the blade passing frequency. - Root mean square (RMS)
converter 70 computes root mean square of thedynamic pressure signal 36. Then, theblade passing frequency 62 and filtereddynamic pressure signal 68 are combined atmultiplier 72 and fed asinput 73 to alow pass filter 74. Resulting filteredsignal 75 and root mean square of thedynamic pressure signal 70 are fed into asignal processor 76 configured to normalize the filteredsignal 75. In one embodiment of the normalization process, the normalization gain, which multiplies the filteredsignal 75, is an inverse of the RMSdynamic pressure signal 70 multiplied by 2.3. In an exemplary embodiment, theblock 60 is configured to compute a cosine of the band pass frequency minus a frequency that represents the new center frequency of the dynamic pressure signal measurement in the low frequency regime. Thedifference 62 is further multiplied with filtereddynamic pressure signal 68 at themultiplier 72. Theresultant product 73 is filtered via a sixth order (meaning sixth or high order) Chebychev low pass filter to obtain a shifteddynamic pressure signal 77 that represents a low frequency transformation of the original, high frequency, and dynamic pressure signal after the normalization at 76. In one embodiment, the pass band of the Chebychev low pass filter is twice the new center frequency of the frequency shifted dynamic pressure signal measurement (so as to reduce noise associated with frequency shifting). - A
data collector 78 buffers the shifted low frequency regimedynamic pressure signal 77 to facilitate further analysis. A storage medium may be configured to store the buffered dynamic pressure signal. An example of storage medium may include memory chip. Such buffered data (obtained from down sampling the shifted low frequency regime dynamic pressure signal) represents an appropriate time period of a dynamic pressure signal with frequency content centered around the blade passing frequency. In one embodiment, the time period is from a quarter of a second to eight seconds. In another embodiment, the time period is of the order of four seconds. Asignal processor 80 computes a Fast Fourier Transform of the down sampled buffered data stored indata collector 78. The blade passing frequency is filtered out from the transformedsignal 81 atfilter block 84. Power associated with a frequency range of about ±15 Hz around the blade passing frequency is set to zero atsource power block 86 and further multiplied by the transformedsignal 81.Power computer 88 calculates an average value of power and further calculates a square root of the average power value. Such average power typically represents astall measure 90 about the blade passing frequency. In an exemplary embodiment,such stall measure 90 indicates un-scaled stall likelihood. - The
un-scaled stall likelihood 90 and inlet guide valve scaling 94 are multiplied at 92. Inletguide valve measurements 87 are used in computing the inlet guide valve scaling 94. In one embodiment, a look up table 97 includes stall likelihood and stall measure. Thestall likelihood 96 is obtained via the look up table 97. As will be appreciated by one skilled in the art, a pre-determined value of stall likelihood is computed by multiple measurements. Such look table includes computational constants as applied to the measurements indicating constraints around which the look up table is built. Constants may be used in computation while using look up table. In one embodiment of the invention, a scaledstall likelihood 99 is obtained via scaling factor such as inlet guide valve scaling 94 andun-scaled stall likelihood 90. In another embodiment of the invention, computation of the scaled stall likelihood measure includes referring look up table having a stall margin remaining 98 as a scaling factor which is multiplied with thestall likelihood 96. It may be noted that stall margin remaining 98 may be obtained viacompressor pressure ratio 85. Thestall indicator 48 is configured to compute thestall indication signal 50 based upon the scaledstall likelihood 99. The stall indication signal is further coupled to the compressor. Based upon thestall indication signal 50, corrective action may be implemented on the compressor to prevent any stall and/or surge condition that may occur. -
FIG. 4 is graphical representation of a long termfast Fourier transform 100, having frequency on thehorizontal axis 102 and power on thevertical axis 104. TheFourier transform 100 includes various power spikes such as 106, 108, and 110 as illustrated. This long term fast Fourier transform is obtained after thesignal processor 80 has processed the buffered data over a long time period as referenced inFIG. 3 . Further thepower spike 106 that is representative of a blade passing frequency may be filtered atblock 84 as referenced inFIG. 3 . In about ±100 Hz around the blade passing frequency, certain power spikes such as 108 and 110 may be recorded. Such power spikes (108 and 110) typically are indicative of conditions that are deviating from the normal operating conditions and may indicate a potential stall and/or surge condition. Thepower computer 88 as referenced inFIG. 3 is configured to detect and calculate such power spike deviations. - Advantageously, long term fast Fourier transform analyses of compressor parameters alleviate shortcomings in present day analysis. Furthermore, Fourier transform analysis helps in capturing accurately the abnormal pressure perturbations and hence minimizes false pressure surges by way of using scaling factor and stall margin remaining in the analysis. Moreover, aforementioned advantages helps in predicting onset of stall and/or surge condition accurately, before the compressor stalls and/or surges, and protect the compressor from damages by way of controlling the operating parameters suitably based on the prediction.
- While only certain features of the invention have been illustrated and described herein, many modifications and changes will occur to those skilled in the art. It is, therefore, to be understood that the appended claims are intended to cover all such modifications and changes as fall within the true spirit of the invention.
Claims (21)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/175,889 US7650777B1 (en) | 2008-07-18 | 2008-07-18 | Stall and surge detection system and method |
FR0954518A FR2934019B1 (en) | 2008-07-18 | 2009-07-01 | SYSTEM AND METHOD FOR DETECTION OF LOCKING AND PUMPING |
DE102009026128A DE102009026128A1 (en) | 2008-07-18 | 2009-07-07 | System and method for detecting stall and surge |
JP2009166224A JP2010025106A (en) | 2008-07-18 | 2009-07-15 | Stall and surge detection system and method |
CN200910159616A CN101629572A (en) | 2008-07-18 | 2009-07-17 | Stall and surge detection system and method |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/175,889 US7650777B1 (en) | 2008-07-18 | 2008-07-18 | Stall and surge detection system and method |
Publications (2)
Publication Number | Publication Date |
---|---|
US20100011846A1 true US20100011846A1 (en) | 2010-01-21 |
US7650777B1 US7650777B1 (en) | 2010-01-26 |
Family
ID=41427442
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/175,889 Active 2028-09-08 US7650777B1 (en) | 2008-07-18 | 2008-07-18 | Stall and surge detection system and method |
Country Status (5)
Country | Link |
---|---|
US (1) | US7650777B1 (en) |
JP (1) | JP2010025106A (en) |
CN (1) | CN101629572A (en) |
DE (1) | DE102009026128A1 (en) |
FR (1) | FR2934019B1 (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2468571B (en) * | 2010-03-01 | 2011-01-26 | Flakt Woods Ltd | A method of detecting and controlling stall in an axial fan |
US8543341B2 (en) | 2010-06-29 | 2013-09-24 | General Electric Company | System and method for monitoring health of airfoils |
US8676514B2 (en) | 2010-06-29 | 2014-03-18 | General Electric Company | System and method for monitoring health of airfoils |
US20140260519A1 (en) * | 2009-11-09 | 2014-09-18 | Kulite Semiconductor Products, Inc. | Systems and methods for improved dynamic pressure measurements |
US20170370368A1 (en) * | 2016-06-22 | 2017-12-28 | General Electric Company | Predicting a Surge Event in a Compressor of a Turbomachine |
CN109632325A (en) * | 2018-12-17 | 2019-04-16 | 中国航发沈阳发动机研究所 | A kind of main chamber flow allocation method |
WO2020036805A1 (en) * | 2018-08-13 | 2020-02-20 | Carrier Corporation | System and method for predicting a surge of a centrifugal refrigeration compressor and air-conditioning unit |
CN114151320A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Identification algorithm for instability of compressor flow system |
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8013738B2 (en) | 2007-10-04 | 2011-09-06 | Kd Secure, Llc | Hierarchical storage manager (HSM) for intelligent storage of large volumes of data |
US7382244B1 (en) | 2007-10-04 | 2008-06-03 | Kd Secure | Video surveillance, storage, and alerting system having network management, hierarchical data storage, video tip processing, and vehicle plate analysis |
US8311684B2 (en) * | 2008-12-17 | 2012-11-13 | Pratt & Whitney Canada Corp. | Output flow control in load compressor |
US8342010B2 (en) * | 2010-12-01 | 2013-01-01 | General Electric Corporation | Surge precursor protection systems and methods |
US8471702B2 (en) * | 2010-12-22 | 2013-06-25 | General Electric Company | Method and system for compressor health monitoring |
US9068463B2 (en) * | 2011-11-23 | 2015-06-30 | General Electric Company | System and method of monitoring turbine engines |
US9702365B2 (en) * | 2012-05-31 | 2017-07-11 | Praxair Technology, Inc. | Anti-surge speed control |
JP6081118B2 (en) * | 2012-09-26 | 2017-02-15 | 三菱重工業株式会社 | Compressor, compressor operation control method |
CN103216461B (en) * | 2013-04-17 | 2016-01-13 | 南京航空航天大学 | The stall inception identification method of axial-flow compressor |
JP6741583B2 (en) * | 2014-03-11 | 2020-08-19 | ボーグワーナー インコーポレーテッド | How to identify compressor surge limits |
CN104295376B (en) * | 2014-08-15 | 2017-02-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Surge-eliminating control method of full-authority digital electrically controlled engine |
US20160363127A1 (en) * | 2015-06-09 | 2016-12-15 | General Electric Company | Systems and methods for monitoring a compressor |
CN105298889B (en) * | 2015-09-24 | 2017-02-01 | 西北工业大学 | Gas compressor surge detection method |
FR3059042B1 (en) * | 2016-11-22 | 2020-07-17 | Safran Aircraft Engines | METHOD FOR CONTROLLING A TURBOMACHINE VALVE |
FR3063782B1 (en) * | 2017-03-07 | 2021-06-18 | Safran Aircraft Engines | METHOD AND DEVICE FOR DETECTION OF CONDITIONS FRIENDLY TO THE APPEARANCE OF PUMPING WITH A VIEW TO PROTECTING A COMPRESSOR OF AN AIRCRAFT TURBOMACHINE |
CN107101834B (en) * | 2017-05-12 | 2019-05-21 | 哈尔滨工程大学 | Turbo-charger surge prediction meanss and prediction technique based on characteristic frequency |
CN107165850B (en) * | 2017-06-27 | 2018-11-23 | 西北工业大学 | A kind of rotating stall of axial flow compressor method for early warning based on the identification of frequency domain hump |
US10989210B2 (en) | 2017-07-10 | 2021-04-27 | Praxair Technology, Inc. | Anti-surge speed control for two or more compressors |
CN108362500A (en) * | 2017-12-26 | 2018-08-03 | 中国航发四川燃气涡轮研究院 | A kind of method that compressor quickly sentences asthma |
CN108612664A (en) * | 2018-05-04 | 2018-10-02 | 重庆江增船舶重工有限公司 | A kind of automatic detection of surge in centrifugal compressors, regulating system |
CN110005628B (en) * | 2019-03-27 | 2020-03-17 | 南京航空航天大学 | Online identification method and system for pneumatic instability of gas compressor based on ectopic variance analysis |
CN112443508B (en) * | 2019-09-02 | 2022-04-08 | 中国航发商用航空发动机有限责任公司 | Surge detection method and system for turbofan engine |
CN113482959B (en) * | 2021-06-16 | 2022-06-03 | 清华大学 | Centrifugal compressor capable of identifying working conditions and early warning and working condition identification method |
Citations (34)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3903216A (en) * | 1969-09-10 | 1975-09-02 | Respiratory Care | Inhalation therapy apparatus |
US4010748A (en) * | 1974-06-27 | 1977-03-08 | Dragerwerk Aktiengesellschaft | Breathing air humidifier for respiration devices |
US4036919A (en) * | 1974-06-26 | 1977-07-19 | Inhalation Therapy Equipment, Inc. | Nebulizer-humidifier system |
US4163371A (en) * | 1977-08-24 | 1979-08-07 | The Dow Chemical Company | Vaporizer |
US4319566A (en) * | 1980-07-21 | 1982-03-16 | John Hayward | Method and apparatus for inhalation rewarming |
US4463755A (en) * | 1981-05-18 | 1984-08-07 | Terumo Corporation | Breathing circuit |
US4652408A (en) * | 1985-04-04 | 1987-03-24 | The Boc Group Plc | Inhalation apparatus |
US4955372A (en) * | 1985-07-16 | 1990-09-11 | Transpirator Technologies, Inc. | Method and apparatus for pulmonary and cardiovascular conditioning of racehorses and competition animals |
US4982175A (en) * | 1989-08-25 | 1991-01-01 | Franklin Electric Co., Inc. | Telemetry circuit with noise immunization |
US5036847A (en) * | 1989-03-31 | 1991-08-06 | Georges Boussignac | Breathing aid |
US5065756A (en) * | 1987-12-22 | 1991-11-19 | New York University | Method and apparatus for the treatment of obstructive sleep apnea |
US5349946A (en) * | 1992-10-07 | 1994-09-27 | Mccomb R Carter | Microprocessor controlled flow regulated molecular humidifier |
US5367604A (en) * | 1992-04-24 | 1994-11-22 | Fisher & Paykel Limited | Humidifier apparatus and/or gases distribution chambers and/or temperature probe |
US5623922A (en) * | 1986-09-23 | 1997-04-29 | Smith; Charles A. | Insulated breathing tube |
US5823184A (en) * | 1994-04-18 | 1998-10-20 | Tyco International (Us) Inc. | Breathing circuit |
US6102037A (en) * | 1998-02-28 | 2000-08-15 | Drager Medizintechnik Gmbh | Respiration humidifier |
US6152132A (en) * | 1997-09-11 | 2000-11-28 | Siemens Elema Ab | Inspiratory tube for a ventilator |
US6231306B1 (en) * | 1998-11-23 | 2001-05-15 | United Technologies Corporation | Control system for preventing compressor stall |
US6256454B1 (en) * | 1999-12-11 | 2001-07-03 | Datex- Ohmeda, Inc. | Humidifier for infant warming apparatus |
US6397841B1 (en) * | 1997-06-18 | 2002-06-04 | Resmed Limited | Apparatus for supplying breathable gas |
US6438484B1 (en) * | 2001-05-23 | 2002-08-20 | General Electric Company | Method and apparatus for detecting and compensating for compressor surge in a gas turbine using remote monitoring and diagnostics |
US20020176567A1 (en) * | 2001-03-19 | 2002-11-28 | Cui Chen | Method and apparatus for dynamically adjusting receiver sensitivity over a phone line home network |
US6532433B2 (en) * | 2001-04-17 | 2003-03-11 | General Electric Company | Method and apparatus for continuous prediction, monitoring and control of compressor health via detection of precursors to rotating stall and surge |
US6536284B2 (en) * | 2001-06-12 | 2003-03-25 | General Electric Company | Method and apparatus for compressor control and operation via detection of stall precursors using frequency demodulation of acoustic signatures |
US6857845B2 (en) * | 2002-08-23 | 2005-02-22 | York International Corporation | System and method for detecting rotating stall in a centrifugal compressor |
US7003426B2 (en) * | 2002-10-04 | 2006-02-21 | General Electric Company | Method and system for detecting precursors to compressor stall and surge |
US7010002B2 (en) * | 2001-06-14 | 2006-03-07 | At&T Corp. | Broadband network with enterprise wireless communication method for residential and business environment |
US7027953B2 (en) * | 2002-12-30 | 2006-04-11 | Rsl Electronics Ltd. | Method and system for diagnostics and prognostics of a mechanical system |
US7116762B2 (en) * | 1998-06-24 | 2006-10-03 | Sbc Properties, L.P. | Home office communication system and method |
US7187694B1 (en) * | 2002-03-29 | 2007-03-06 | Pmc-Sierra, Inc. | Generic packet parser |
US7308322B1 (en) * | 1998-09-29 | 2007-12-11 | Rockwell Automation Technologies, Inc. | Motorized system integrated control and diagnostics using vibration, pressure, temperature, speed, and/or current analysis |
US7424823B2 (en) * | 2004-10-19 | 2008-09-16 | Techno-Sciences, Inc. | Method of determining the operating status of a turbine engine utilizing an analytic representation of sensor data |
US7530260B2 (en) * | 2007-04-19 | 2009-05-12 | Pratt & Whitney Canada Corp. | Surge detection in a gas turbine engine |
US7596953B2 (en) * | 2003-12-23 | 2009-10-06 | General Electric Company | Method for detecting compressor stall precursors |
-
2008
- 2008-07-18 US US12/175,889 patent/US7650777B1/en active Active
-
2009
- 2009-07-01 FR FR0954518A patent/FR2934019B1/en active Active
- 2009-07-07 DE DE102009026128A patent/DE102009026128A1/en not_active Ceased
- 2009-07-15 JP JP2009166224A patent/JP2010025106A/en active Pending
- 2009-07-17 CN CN200910159616A patent/CN101629572A/en active Pending
Patent Citations (34)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3903216A (en) * | 1969-09-10 | 1975-09-02 | Respiratory Care | Inhalation therapy apparatus |
US4036919A (en) * | 1974-06-26 | 1977-07-19 | Inhalation Therapy Equipment, Inc. | Nebulizer-humidifier system |
US4010748A (en) * | 1974-06-27 | 1977-03-08 | Dragerwerk Aktiengesellschaft | Breathing air humidifier for respiration devices |
US4163371A (en) * | 1977-08-24 | 1979-08-07 | The Dow Chemical Company | Vaporizer |
US4319566A (en) * | 1980-07-21 | 1982-03-16 | John Hayward | Method and apparatus for inhalation rewarming |
US4463755A (en) * | 1981-05-18 | 1984-08-07 | Terumo Corporation | Breathing circuit |
US4652408A (en) * | 1985-04-04 | 1987-03-24 | The Boc Group Plc | Inhalation apparatus |
US4955372A (en) * | 1985-07-16 | 1990-09-11 | Transpirator Technologies, Inc. | Method and apparatus for pulmonary and cardiovascular conditioning of racehorses and competition animals |
US5623922A (en) * | 1986-09-23 | 1997-04-29 | Smith; Charles A. | Insulated breathing tube |
US5065756A (en) * | 1987-12-22 | 1991-11-19 | New York University | Method and apparatus for the treatment of obstructive sleep apnea |
US5036847A (en) * | 1989-03-31 | 1991-08-06 | Georges Boussignac | Breathing aid |
US4982175A (en) * | 1989-08-25 | 1991-01-01 | Franklin Electric Co., Inc. | Telemetry circuit with noise immunization |
US5367604A (en) * | 1992-04-24 | 1994-11-22 | Fisher & Paykel Limited | Humidifier apparatus and/or gases distribution chambers and/or temperature probe |
US5349946A (en) * | 1992-10-07 | 1994-09-27 | Mccomb R Carter | Microprocessor controlled flow regulated molecular humidifier |
US5823184A (en) * | 1994-04-18 | 1998-10-20 | Tyco International (Us) Inc. | Breathing circuit |
US6397841B1 (en) * | 1997-06-18 | 2002-06-04 | Resmed Limited | Apparatus for supplying breathable gas |
US6152132A (en) * | 1997-09-11 | 2000-11-28 | Siemens Elema Ab | Inspiratory tube for a ventilator |
US6102037A (en) * | 1998-02-28 | 2000-08-15 | Drager Medizintechnik Gmbh | Respiration humidifier |
US7116762B2 (en) * | 1998-06-24 | 2006-10-03 | Sbc Properties, L.P. | Home office communication system and method |
US7308322B1 (en) * | 1998-09-29 | 2007-12-11 | Rockwell Automation Technologies, Inc. | Motorized system integrated control and diagnostics using vibration, pressure, temperature, speed, and/or current analysis |
US6231306B1 (en) * | 1998-11-23 | 2001-05-15 | United Technologies Corporation | Control system for preventing compressor stall |
US6256454B1 (en) * | 1999-12-11 | 2001-07-03 | Datex- Ohmeda, Inc. | Humidifier for infant warming apparatus |
US20020176567A1 (en) * | 2001-03-19 | 2002-11-28 | Cui Chen | Method and apparatus for dynamically adjusting receiver sensitivity over a phone line home network |
US6532433B2 (en) * | 2001-04-17 | 2003-03-11 | General Electric Company | Method and apparatus for continuous prediction, monitoring and control of compressor health via detection of precursors to rotating stall and surge |
US6438484B1 (en) * | 2001-05-23 | 2002-08-20 | General Electric Company | Method and apparatus for detecting and compensating for compressor surge in a gas turbine using remote monitoring and diagnostics |
US6536284B2 (en) * | 2001-06-12 | 2003-03-25 | General Electric Company | Method and apparatus for compressor control and operation via detection of stall precursors using frequency demodulation of acoustic signatures |
US7010002B2 (en) * | 2001-06-14 | 2006-03-07 | At&T Corp. | Broadband network with enterprise wireless communication method for residential and business environment |
US7187694B1 (en) * | 2002-03-29 | 2007-03-06 | Pmc-Sierra, Inc. | Generic packet parser |
US6857845B2 (en) * | 2002-08-23 | 2005-02-22 | York International Corporation | System and method for detecting rotating stall in a centrifugal compressor |
US7003426B2 (en) * | 2002-10-04 | 2006-02-21 | General Electric Company | Method and system for detecting precursors to compressor stall and surge |
US7027953B2 (en) * | 2002-12-30 | 2006-04-11 | Rsl Electronics Ltd. | Method and system for diagnostics and prognostics of a mechanical system |
US7596953B2 (en) * | 2003-12-23 | 2009-10-06 | General Electric Company | Method for detecting compressor stall precursors |
US7424823B2 (en) * | 2004-10-19 | 2008-09-16 | Techno-Sciences, Inc. | Method of determining the operating status of a turbine engine utilizing an analytic representation of sensor data |
US7530260B2 (en) * | 2007-04-19 | 2009-05-12 | Pratt & Whitney Canada Corp. | Surge detection in a gas turbine engine |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9500553B2 (en) * | 2009-11-09 | 2016-11-22 | Kulite Semiconductor Products, Inc. | Systems and methods for improved dynamic pressure measurements |
US20140260519A1 (en) * | 2009-11-09 | 2014-09-18 | Kulite Semiconductor Products, Inc. | Systems and methods for improved dynamic pressure measurements |
US9080575B2 (en) * | 2010-03-01 | 2015-07-14 | Howden Axial Fans Ab | Method of detecting and controlling stall in an axial fan |
US20120219398A1 (en) * | 2010-03-01 | 2012-08-30 | Flakt Woods Limited | Method of detecting and controlling stall in an axial fan |
GB2468571B (en) * | 2010-03-01 | 2011-01-26 | Flakt Woods Ltd | A method of detecting and controlling stall in an axial fan |
US8676514B2 (en) | 2010-06-29 | 2014-03-18 | General Electric Company | System and method for monitoring health of airfoils |
US8543341B2 (en) | 2010-06-29 | 2013-09-24 | General Electric Company | System and method for monitoring health of airfoils |
US20170370368A1 (en) * | 2016-06-22 | 2017-12-28 | General Electric Company | Predicting a Surge Event in a Compressor of a Turbomachine |
US10047757B2 (en) * | 2016-06-22 | 2018-08-14 | General Electric Company | Predicting a surge event in a compressor of a turbomachine |
WO2020036805A1 (en) * | 2018-08-13 | 2020-02-20 | Carrier Corporation | System and method for predicting a surge of a centrifugal refrigeration compressor and air-conditioning unit |
US11835053B2 (en) | 2018-08-13 | 2023-12-05 | Carrier Corporation | System and method for predicting a surge of a centrifugal refrigeration compressor and air-conditioning unit |
CN109632325A (en) * | 2018-12-17 | 2019-04-16 | 中国航发沈阳发动机研究所 | A kind of main chamber flow allocation method |
CN114151320A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Identification algorithm for instability of compressor flow system |
Also Published As
Publication number | Publication date |
---|---|
DE102009026128A1 (en) | 2010-01-21 |
CN101629572A (en) | 2010-01-20 |
US7650777B1 (en) | 2010-01-26 |
JP2010025106A (en) | 2010-02-04 |
FR2934019B1 (en) | 2016-11-11 |
FR2934019A1 (en) | 2010-01-22 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US7650777B1 (en) | Stall and surge detection system and method | |
US6438484B1 (en) | Method and apparatus for detecting and compensating for compressor surge in a gas turbine using remote monitoring and diagnostics | |
RU2326271C2 (en) | Method (variants) and system for detecting signs of compressor slowing down, stalling, and surging | |
US6536284B2 (en) | Method and apparatus for compressor control and operation via detection of stall precursors using frequency demodulation of acoustic signatures | |
US7409854B2 (en) | Method and apparatus for determining an operating status of a turbine engine | |
EP0654161B1 (en) | Process and device for monitoring and for controlling of a compressor | |
KR101670710B1 (en) | Centrifugal compressor apparatus and method for preventing surge therein | |
US8770913B1 (en) | Apparatus and process for rotor creep monitoring | |
US6059522A (en) | Compressor stall diagnostics and avoidance | |
EP2746885A1 (en) | Method of monitoring the condition of a wind turbine | |
JP2002371989A (en) | Monitoring and controlling method, and monitoring device for compressor | |
WO1994003863A1 (en) | Process for detecting fouling of an axial compressor | |
JP5898865B2 (en) | System and method for monitoring airfoil health | |
US6506010B1 (en) | Method and apparatus for compressor control and operation in industrial gas turbines using stall precursors | |
US8543341B2 (en) | System and method for monitoring health of airfoils | |
US8342010B2 (en) | Surge precursor protection systems and methods | |
KR100543674B1 (en) | Apparatus and Method of Rotating Stall Warning in Compressor using Traveling Wave Energy | |
Millsaps et al. | Analysis of Stall Precursors and Determination of Optimum Signal Processing Methods for an LM-2500 Gas Turbine | |
KR100296672B1 (en) | Processes and devices for detecting contamination of axial compressors | |
KR20050057775A (en) | Apparatus and method of rotating stall warning in compressor using spatial fourier coefficient |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:KROK, MICHAEL;BOLTON, JOHN;REEL/FRAME:021378/0787;SIGNING DATES FROM 20080730 TO 20080813 Owner name: GENERAL ELECTRIC COMPANY,NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:KROK, MICHAEL;BOLTON, JOHN;SIGNING DATES FROM 20080730 TO 20080813;REEL/FRAME:021378/0787 |
|
FEPP | Fee payment procedure |
Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
FPAY | Fee payment |
Year of fee payment: 4 |
|
FPAY | Fee payment |
Year of fee payment: 8 |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 12TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1553); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 12 |