CN104114874A - Method for avoiding pump surges in a compressor - Google Patents
Method for avoiding pump surges in a compressor Download PDFInfo
- Publication number
- CN104114874A CN104114874A CN201280069486.3A CN201280069486A CN104114874A CN 104114874 A CN104114874 A CN 104114874A CN 201280069486 A CN201280069486 A CN 201280069486A CN 104114874 A CN104114874 A CN 104114874A
- Authority
- CN
- China
- Prior art keywords
- compressor
- sensor
- surge
- special
- rotational noise
- 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.)
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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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Positive-Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
The invention relates to a method for avoiding pump surges in a compressor (2), wherein a plurality of parameters of the compressor (2) are monitored during operation and a desired value range for the plurality of parameters is predetermined, wherein a reaction (24, 26, 28) that counteracts the pump surge is triggered if a number of parameters from the desired value range are exceeded or fallen below. According to the invention, the method also reliably prevents pumping of the compressor during a comparatively high running performance. For said purpose, the plurality of parameters comprises a parameter assigned to the rotational noise of the compressor (2).
Description
Technical field
The present invention relates to a kind of for avoiding the method for the pump surge of compressor, wherein, when operation monitoring compressor a plurality of special parameters and preset the rating value scope for described a plurality of special parameters, wherein, at the numerical value of special parameter, during higher or lower than rating value scope, trigger the reaction of anti-pump surge.The invention still further relates to a kind of compressor and have the fluid machinery of compressor and control gear, this control gear is connected with a plurality of sensors that detect special parameter when moving that are designed at data inlet side.
Background technique
Compressor, especially combustion gas turbine are easy to surge under definite operating conditions.If back pressure is too large on flow direction, compressor can not be carried air again, flow direction part or even completely reversion.For local return, portion of air keeps being trapped in compressor and along with blade rotates together.It is exactly so-called mobile rotating separation (rotating stall).And when so-called compressor surge (dark surge), medium total reflux---this causes the fierceness collision contrary with direction of propulsion.
These two kinds of aerodynamics effects can have serious consequence.Rotating stall can cause Materials Fracture by strong vibration, and when pump surge, has the threat of whole blade burst fracture.Be which kind of situation has all been interrupted air to the flowing of the firing chamber of combustion gas turbine, this causes the cut-out of this Air Flow.
The general compressor characteristics curve that represents the relation of the pressure ratio between entrance and terminal pressure and quantity delivered, is divided into stable and unsettled region by surge line (Pumpgrenze).The reducing or occurring surge when rising (delivery head) by terminal pressure enters unstable region by quantity delivered (flow) in the operation point of compressor.
Conventionally, in the electron controls technology of the control gear of fluid machinery or control in software and define surge line distance, this surge line distance is separated by enough far with surge line when operation under design condition.Under physical condition, for example, in the low-calorie situation of the network reducing, higher ambient temperature and/or humidity of the air, fuel, but also because aging, pollution or the damage of compressor can cause surge line to arrive or even surpass performance curve.Therefore this causes compressor surge immediately.
Conventionally at the entrance (inlet cone) of compressor, locate to install one or more sensors that are designed to differential pressure switch, once the surge that is flowing in by compressor, interrupt, these sensors are just lower than a certain limiting value and cause combustion gas turbine to cut off immediately by cutting out of fuel valve.But surge protection pressure switch nonrecognition approach surge line, and only prevent the surge again of compressor and prevent that if desired compressor from interrupting due to fuel input the mechanical deterioration that causes immediately.
Therefore,, in expansion design, conventionally also use compressor pressure to compare limit regulator.The special parameter of this regulator considering compression machine (pressure ratio, network, leading leaf position and environmental conditions, as temperature and humidity of the air) and the License Value comparison with surge line indicatrix specific to compressor by it.If approach the present operating point of surge line, that is, when the rating value scope higher or lower than default, trigger the reaction of anti-pump surge.
But disadvantageously, they do not consider aging, huge pollution and or the damage of compressor therefore can not prevent reliably again the surge of compressor when the operating time of fluid machinery increases in described two kinds of methods.
In addition, for example known from US2009/0055071A1, pressure transducer and/or microphone arrangement in the space of burner upstream, compressed-air actuated state in their detection spaces.Then, its signal evaluation is for analyzing surge event immediately.Equally, EP2375081A2 suggestion, predicts surge with shock wave and other compressed-air actuated acoustic phenomenon.Also use MIC microphone or similar pressure transducer herein.But disadvantageously, this sensor only has the limited life-span in higher ambient temperature.
Summary of the invention
Therefore, technical problem to be solved by this invention is to provide a kind of for avoiding method and a kind of compressor or the fluid machinery of the pump surge of compressor, even if they also prevent reliably the surge of compressor under higher operate power.
With regard to method, this technical problem solves as follows by the present invention: a plurality of special parameters comprise the special parameter corresponding with the rotational noise of compressor.
At this, the thinking the present invention is based on is, even in order also to avoid reliably pump surge under the higher operate power of fluid machinery, should not only to, with reference to previous definite indicatrix and adjustable Operational Limits, also should use measurement parameter current, that be applicable to the pump surge of predictability identification menace.By corresponding measurement, recognizing and approaching rotating stall, that is during the surge line of rotational flow unpack format, can realize predictability identification.Here recognize, this flow separation is created in the vibration in compressor stage, and these vibrations cause the pressure pulse and the further vibration that increase.This pressure pulse and vibration change the rotational noise of compressor, so that the variation of rotational noise correspondingly predictably shows the surge of menace.Therefore, should measure the special parameter corresponding with the rotational noise of compressor and avoid pump surge with these characteristic parameters.
For the variation of identification rotational noise, can use multifrequency nature parameter and multiple sensors, they can be presented at the vibration in compressor.Therefore, for example high dynamic pressure transducer can be used, by this sensor, described pressure pulse can be surveyed.But herein disadvantageously, this pressure transducer is not long-time stable and and be not suitable for all working condition (the thundering of the pollution of increase, humidity, increase, compressor cleaning etc.) of fluid machinery.The special parameter corresponding with rotational noise compressor that therefore, record be amplitude and/or the vibration frequency of the parts of fluid machinery advantageously.Pressure pulse is also delivered on the parts of fluid machinery.The mechanical vibration of the corresponding part that therefore, rotational noise can be by combustion gas turbine are determined.At this, with it applicable sensor and prober to described operating conditions insensitive and therefore the life-span longer.
The parts that are provided with corresponding sensor are axle and/or the housing of turbo machine and/or compressor advantageously.According to the housing of turbo machine and/or compressor and/or shaft vibration, rotational noise is approaching surge line and can determine particularly well about menace just.
In addition, special parameter used advantageously comprises axle rotating speed, compressor terminal pressure and/or leading leaf position.Can further improve thus the predictability identification of surge because rotational noise by these additional special parameters for example for definite well by special parser during the special computer providing is provided.
In particularly advantageous organization plan, the reaction of anti-pump surge comprises rating value and/or the minimizing fuel mass flow that reduces turbine-exit temperature.In regulating the scope of fluid machinery, the rating value that reduces turbine-exit temperature causes leading blade adjustable, compressor to be opened.Expand thus the distance of surge line to.By reducing fuel mass flow, as far as possible promptly reduce compressor terminal pressure and therefore reduce compressor pressure ratio.As other measure, for example, can in compressor tail end, extract air by the frost valve of compressor.Then, air extracts and can at place, suction port of compressor, introduce with improvement again by frost valve.Reduced equally thus compressor pressure ratio.
Fluid machinery is advantageously provided with compressor and for carrying out the control gear of described method.
About have compressor with at data inlet side with a plurality of for detect the fluid machinery of the control gear that the sensor of special parameter is connected in when operation, this technical problem is solved by one of sensor being designed for to the detection special parameter corresponding with the rotational noise of compressor.
Each sensor is at this vibration transducer advantageously.This sensor is advantageously designed to vibrometer.Be particularly advantageously vibrometer, this vibrometer for example, with piezoelectricity basis acceleration measurement, the piezoelectric acceleration detector CA901 of Meggitt company herein.Long especially and relatively-high temperature of its life-span, a pollution and pressing mistake! Hyperlink is quoted invalid.Contracting machine is robust while cleaning.
In favourable organization plan, each sensor sets to the axle of turbo machine and/or compressor and/or housing.At this, corresponding sensor is advantageously installed at a plurality of positions in the periphery of compressor, ideally in outside, clock hole (Klingelbohrungen), that is, not in flow path.
Power station advantageously comprises described fluid machinery.
The advantage realizing by invention is especially, before there is actual surge, by measuring targetedly the rotational noise of the compressor of fluid machinery, can identify approaching or rotating stall surge line.This can realize by corresponding vibration detector especially simply, and the pressure of measuring the compressor operating blade rotating of one-level changes.By other prober (axle rotating speed, compressor terminal pressure, leading leaf position), can at control gear, for example, in computer, by special parser, determine the rotational noise of compressor.This also allows detection can cause the impurity of compressor flow path and the damage of its part.This impurity also causes the variation of rotational noise.Therefore avoided the indirect injury for the parts in compressor downstream.
Accompanying drawing explanation
Further set forth with reference to the accompanying drawings the present invention.Wherein, the section of the schematically illustrated compressor first half by combustion gas turbine of Fig. 1.
Embodiment
Fluid machinery 1 shown in local in this accompanying drawing is designed to combustion gas turbine.The compressor 2 of combustion gas turbine is only shown.This compressor 2 comprises and being fixed on housing 4 and therefore fixing guide vane 6, in the flow channel 8 of this guide vane 6 between suction port of compressor 10 and compressor outlet 12.The first guide vane 6 on the flow direction of air is designed to adjustable leading blade 14.Thus, the air quantity in flow channel 8 is inputted in adjustable and throttling.
On the flow direction of air, the rear of each guide vane 6,14 is provided with respectively working blade 18 on axle 16.Working blade 18 and guide vane 6,14 respectively star ring-type are arranged in flow channel 8.The ring consisting of guide vane 6,14 forms respectively the one-level of compressor 2 jointly with the ring consisting of working blade after on flow direction.
For identifying ahead of time the surge of menace, in compressor 2, be provided with a plurality of sensors that are not shown specifically.The vibration transducer 20 that is designed to piezoelectric acceleration sensor is especially arranged on the Zhong Kongzhong arranging to 90 ° of angles respectively, and this vibration transducer 20 can be surveyed mechanical vibration and therefore can obtain the image of the rotational noise of compressor 2.
Rotational noise by as software at the control gear shown in further, the parser 22 of for example carrying out on computer is determined.In parser, at this, except the vibration data of vibration transducer 20, also allow the data of other corresponding probers or sensor.These data comprise the hull vibration on the compressor pressure ratio between axle rotating speed, suction port of compressor 10 and compressor outlet 12, leading leaf position, shaft vibration and compressor and turbo machine.
If change owing to approaching the vibration mode of surge line rotational noise or existing vibration measuring device, computer transmitted signal (binary system or simulation), to implement to prevent the respective reaction of surge.
These reactions comprise opens frost valve 24, reduces turbine-exit temperature 26 and reduces fuel quantity 28.Can also stipulate other measure.This reaction can trigger the result definite according to parser 22 by demand.Therefore, can for example carry out the only single or multiple of described reaction.In addition, can notify staff 30.
If the flow channel 8 of trash flow overcompression machine 2, it is definite that this is passed rotational noise variation equally.Impurity effect same trigger notice manufacture control technology or staff 30.Then, manufacture control technology or personnel can determine the measure that will take, for example, stop and checking compressor 2 or fluid machinery 1.Therefore can survey and notify the impurity effect that causes less important damage or cause compressor part damage (appearance as long as they do not happen suddenly).And burst occurs, serious damage causes automatic measure when FOD 32 (foreign matter detection), as the cut-out of combustion gas turbine.
Claims (13)
1. for avoiding a method for the pump surge of compressor (2), wherein, be in operation and monitor a plurality of special parameters of described compressor (2) and preset the rating value scope for described a plurality of special parameters,
Wherein, at the numerical value of special parameter, during higher or lower than rating value scope, trigger the reaction (24 of the pump surge of anti-menace, 26,28), it is characterized in that, a plurality of special parameters comprise the special parameter corresponding with the rotational noise of described compressor (2), and
The special parameter corresponding to rotational noise of described and described compressor (2) is amplitude and/or the vibration frequency of the parts of described fluid machinery (2).
2. by method claimed in claim 1, wherein, detect the acceleration of described parts and determine rotational noise.
3. by the method described in claim 1 or 2, wherein, described parts are axle (16) and/or housings (4) of turbo machine and/or described compressor (2).
4. by the described method of one of aforementioned claim, wherein, a plurality of special parameters comprise axle rotating speed, compressor terminal pressure and/or leading leaf position.
5. by the described method of one of aforementioned claim, wherein, the reaction of described anti-pump surge comprises rating value and/or the minimizing fuel mass flow (28) that reduces turbine-exit temperature (26).
6. by the described method of one of aforementioned claim, wherein, described compressor (2) is the part of fluid machinery (1).
7. compressor (2) and an a kind of control gear, be designed for and carry out by the method one of claim 1 to 6 Suo Shu.
8. a compressor (2) and a kind of control gear, this control gear is connected with a plurality of sensors at data inlet side, the plurality of Sensor Design for detecting special parameter when moving, it is characterized in that, one of sensor is designed for and detects the special parameter corresponding with the rotational noise of compressor (2) and each sensor is the vibration transducer (20) being arranged on the parts of combustion gas turbine, by the mechanical vibration of this vibration transducer energy determining means.
9. by compressor claimed in claim 8, wherein, described sensor is arranged on the antitorque parts of combustion gas turbine.
10. by the compressor described in claim 8 or 9, wherein, described Sensor Design becomes acceleration sensor.
11. 1 kinds of fluid machineries (1) with the compressor (2) by claim 8,9 or 10.
12. by the fluid machinery (1) described in claim 11, and wherein, each sensor sets to the axle (16) of turbo machine and/or compressor (2) and/or housing (4).
13. 1 kinds have by the power station of the fluid machinery described in claim 11 or 12 (1).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP12154644.4 | 2012-02-09 | ||
| EP12154644.4A EP2626569A1 (en) | 2012-02-09 | 2012-02-09 | Method for reducing pumps in a compressor |
| PCT/EP2012/075248 WO2013117271A1 (en) | 2012-02-09 | 2012-12-12 | Method for avoiding pump surges in a compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104114874A true CN104114874A (en) | 2014-10-22 |
| CN104114874B CN104114874B (en) | 2016-08-31 |
Family
ID=47435935
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280069486.3A Active CN104114874B (en) | 2012-02-09 | 2012-12-12 | For the method avoiding the pump surge in compressor |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20150044020A1 (en) |
| EP (2) | EP2626569A1 (en) |
| JP (1) | JP6005181B2 (en) |
| CN (1) | CN104114874B (en) |
| WO (1) | WO2013117271A1 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109458324A (en) * | 2018-10-31 | 2019-03-12 | 重庆美的通用制冷设备有限公司 | Compressor surge recognition methods, apparatus and system |
| CN111120360A (en) * | 2019-12-22 | 2020-05-08 | 云南瑞斯德机械有限公司 | Structure and method for reducing surge phenomenon of centrifugal compressor and automatically adjusting flow |
| CN113945029A (en) * | 2021-10-19 | 2022-01-18 | 青岛海尔空调电子有限公司 | Method and device for controlling refrigerant circulation system and refrigerant circulation system |
| TWI773107B (en) * | 2021-01-29 | 2022-08-01 | 復盛股份有限公司 | Surge detection method and compression device |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3045676A1 (en) * | 2015-01-13 | 2016-07-20 | Siemens Aktiengesellschaft | Method for avoiding a rotating stall |
| CN114754020B (en) * | 2022-04-18 | 2024-02-02 | 合肥通用机械研究院有限公司 | Compressor surge monitoring system and monitoring method based on intake noise characteristics |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4399548A (en) * | 1981-04-13 | 1983-08-16 | Castleberry Kimberly N | Compressor surge counter |
| WO2003038282A1 (en) * | 2001-10-23 | 2003-05-08 | Mtu Aero Engines Gmbh | Warning before pump limit or in case of blade failure on a turbomachine |
| WO2007086755A1 (en) * | 2006-01-26 | 2007-08-02 | Dynatrend As | A method and device for determining the occurence of rotating stall in a compressor's turbine blade ii |
| CN101368515A (en) * | 2007-08-17 | 2009-02-18 | 通用电气公司 | Apparatus and method for monitoring compressor clearance and controlling a gas turbine |
| US20090055071A1 (en) * | 2007-08-22 | 2009-02-26 | Cleveland Electric Laboratories | Active surge control |
| CN201575861U (en) * | 2009-02-18 | 2010-09-08 | 长沙全程数字机电科技有限公司 | Integral vibration monitor |
| CN102213215A (en) * | 2010-04-08 | 2011-10-12 | 通用电气公司 | System and method for monitoring a compressor |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB822443A (en) * | 1955-03-24 | 1959-10-28 | United Aircraft Corp | Fuel control systems for gas turbine engines |
| JPH08503757A (en) * | 1992-08-10 | 1996-04-23 | ダウ、ドイチュラント、インコーポレーテッド． | Method and apparatus for monitoring and controlling a compressor |
| US6092029A (en) * | 1998-02-19 | 2000-07-18 | Bently Nevada Corporation | Method and apparatus for diagnosing and controlling rotating stall and surge in rotating machinery |
| JP4705732B2 (en) * | 2000-05-25 | 2011-06-22 | 本田技研工業株式会社 | Surge detector for aircraft gas turbine engine |
| US7003426B2 (en) * | 2002-10-04 | 2006-02-21 | General Electric Company | Method and system for detecting precursors to compressor stall and surge |
| US7282873B2 (en) * | 2004-11-16 | 2007-10-16 | Lenovo (Singapore) Pte. Ltd. | Mutual active cancellation of fan noise and vibration |
| US20060283190A1 (en) * | 2005-06-16 | 2006-12-21 | Pratt & Whitney Canada Corp. | Engine status detection with external microphone |
| US8091862B2 (en) * | 2006-09-29 | 2012-01-10 | Sikorsky Aircraft Corporation | Butterfly valves having sleeve inserts |
| US7905702B2 (en) * | 2007-03-23 | 2011-03-15 | Johnson Controls Technology Company | Method for detecting rotating stall in a compressor |
| US8074499B2 (en) * | 2009-12-22 | 2011-12-13 | General Electric Company | Method and system for detecting a crack on a turbomachine blade |
-
2012
- 2012-02-09 EP EP12154644.4A patent/EP2626569A1/en not_active Withdrawn
- 2012-12-12 JP JP2014555955A patent/JP6005181B2/en active Active
- 2012-12-12 US US14/376,426 patent/US20150044020A1/en not_active Abandoned
- 2012-12-12 EP EP12806422.7A patent/EP2805058B1/en active Active
- 2012-12-12 CN CN201280069486.3A patent/CN104114874B/en active Active
- 2012-12-12 WO PCT/EP2012/075248 patent/WO2013117271A1/en active Application Filing
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4399548A (en) * | 1981-04-13 | 1983-08-16 | Castleberry Kimberly N | Compressor surge counter |
| WO2003038282A1 (en) * | 2001-10-23 | 2003-05-08 | Mtu Aero Engines Gmbh | Warning before pump limit or in case of blade failure on a turbomachine |
| WO2007086755A1 (en) * | 2006-01-26 | 2007-08-02 | Dynatrend As | A method and device for determining the occurence of rotating stall in a compressor's turbine blade ii |
| CN101368515A (en) * | 2007-08-17 | 2009-02-18 | 通用电气公司 | Apparatus and method for monitoring compressor clearance and controlling a gas turbine |
| US20090055071A1 (en) * | 2007-08-22 | 2009-02-26 | Cleveland Electric Laboratories | Active surge control |
| CN201575861U (en) * | 2009-02-18 | 2010-09-08 | 长沙全程数字机电科技有限公司 | Integral vibration monitor |
| CN102213215A (en) * | 2010-04-08 | 2011-10-12 | 通用电气公司 | System and method for monitoring a compressor |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109458324A (en) * | 2018-10-31 | 2019-03-12 | 重庆美的通用制冷设备有限公司 | Compressor surge recognition methods, apparatus and system |
| CN111120360A (en) * | 2019-12-22 | 2020-05-08 | 云南瑞斯德机械有限公司 | Structure and method for reducing surge phenomenon of centrifugal compressor and automatically adjusting flow |
| TWI773107B (en) * | 2021-01-29 | 2022-08-01 | 復盛股份有限公司 | Surge detection method and compression device |
| CN113945029A (en) * | 2021-10-19 | 2022-01-18 | 青岛海尔空调电子有限公司 | Method and device for controlling refrigerant circulation system and refrigerant circulation system |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2015511288A (en) | 2015-04-16 |
| EP2626569A1 (en) | 2013-08-14 |
| CN104114874B (en) | 2016-08-31 |
| WO2013117271A1 (en) | 2013-08-15 |
| EP2805058B1 (en) | 2016-06-29 |
| EP2805058A1 (en) | 2014-11-26 |
| JP6005181B2 (en) | 2016-10-12 |
| US20150044020A1 (en) | 2015-02-12 |
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Effective date of registration: 20220111 Address after: Munich, Germany Patentee after: Siemens energy Global Ltd. Address before: Munich, Germany Patentee before: SIEMENS AG |
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