US20020094267A1 - Instability detecting device for turbo compressors - Google Patents

Instability detecting device for turbo compressors Download PDF

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Publication number
US20020094267A1
US20020094267A1 US09/888,712 US88871201A US2002094267A1 US 20020094267 A1 US20020094267 A1 US 20020094267A1 US 88871201 A US88871201 A US 88871201A US 2002094267 A1 US2002094267 A1 US 2002094267A1
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US
United States
Prior art keywords
compressor
detector
pressure
impeller
detecting device
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.)
Abandoned
Application number
US09/888,712
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English (en)
Inventor
Kwang Kim
You Shin
Jae Jeon
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Korea Advanced Institute of Science and Technology KAIST
Original Assignee
Korea Advanced Institute of Science and Technology KAIST
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Korea Advanced Institute of Science and Technology KAIST filed Critical Korea Advanced Institute of Science and Technology KAIST
Assigned to KOREA INSTITUTE OF SCIENCE AND TECHNOLOGY reassignment KOREA INSTITUTE OF SCIENCE AND TECHNOLOGY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: JEON, JAE HAK, KIM, KWANG HO, SHIN, YOU HWAN
Publication of US20020094267A1 publication Critical patent/US20020094267A1/en
Abandoned legal-status Critical Current

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Classifications

    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • 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
    • 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
    • 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
    • F05D2270/3011—Inlet 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
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F05D2270/3015—Pressure differential pressure

Definitions

  • the present invention relates to a device for detecting operational instability during an operation of turbo compressors and, more particularly, to an instability detecting device used for easily and simply detecting a rotating stall and/or a surge frequently occurring during an operation of a turbo compressor.
  • an object of the present invention is to provide an instability detecting device for turbo compressors, which easily, simply and reliably detects a rotating stall and/or a surge during an operation of such compressors while reducing the installation cost, maintenance cost and repairing cost of the compressors, different from the conventional detecting equipments, such as high-frequency pressure sensors, vibration sensors, or signal analyzing systems.
  • the present invention provides an instability detecting device for turbo compressors, comprising: a detector consisting of: a body; first and second pressure tubes axially set in the body while parallely extending on the same plane, with first and second pressure discharge ports of the first and second pressure tubes exposed to the outside of the body at an end surface of the body; and a partition wall arranged on the end surface of the body while crossing the end surface and separating the first and second pressure discharge ports of the pressure tubes from each other, whereby the detector is attached to the inlet suction port of a compressor's impeller such that the partition wall extends in parallel to a rotation axis of the impeller, and/or to an outlet discharge port of a compressor's impeller such that said partition wall extends in parallel to a discharge flow from impeller, the detector thus sensing a pressure difference between the first and second pressure discharge ports of the pressure tubes and detecting an operation of the compressor within an unstable operational region.
  • the detector may be connected to a monitor allowing an operator to know operational conditions of the compressor so as to detect an operation of the compressor within the unstable operational region.
  • the detector may be provided with a means for alerting the operator of an operation of the compressor within the unstable operational region.
  • the turbo compressor When the turbo compressor is operated within a stable operational region, the working fluid flows along the partition wall prior to being introduced into the suction port of the impeller and/or into the discharge port, and so any pressure difference between the first and second pressure discharge ports of the pressure tubes is not detected.
  • the compressor when the compressor is operated within an unstable operational region to form a rotating stall and/or a surge, the working fluid flows in a direction perpendicular to the partition wall prior to being introduced into the suction port of the impeller, and so a pressure difference between the first and second pressure discharge ports of the pressure tubes is detected. It occurs also if the detector is introduced into the discharge port of the impeller.
  • the detected pressure difference is applied to a U-shaped pressure tube, or is converted into an electric signal prior to being displayed on the monitor, thus allowing an operator to be informed of an operation of the compressor within the unstable operational region.
  • the detecting device of this invention also alerts the operator of the operation of the compressor within the unstable operational region through a visual signal or a voice signal.
  • FIG. 1 shows an instability detector included in the detecting device for turbo compressors in accordance with the preferred embodiment of the present invention, in a front view and a sectional view;
  • FIG. 2 is a view, showing the instability detector of this invention attached to a turbo compressor
  • FIG. 3 is a graph showing a standard pressure difference as a function of a rotating angle of the instability detector of this invention
  • FIG. 4 is a graph showing a static pressure rise coefficient as a function of a flow coefficient of the instability detecting device of this invention
  • FIG. 5 a is a graph showing a standard pressure difference as a function of a rotating angle of the instability detecting device of this invention within a stable operational region;
  • FIG. 5 b is a view, showing a flow of the working fluid of the instability detecting device of this invention within the stable operational region;
  • FIG. 6 a is a graph showing a standard pressure difference as a function of a rotating angle of the instability detecting device of this invention within an unstable operational region
  • FIG. 6 b is a view, showing a flow of the working fluid of the instability detecting device of this invention within the unstable operational region.
  • FIG. 1 shows an instability detector 20 included in the detecting device for turbo compressors in accordance with the preferred embodiment of the present invention, in a front view and a sectional view.
  • FIG. 2 is a view, showing the instability detector 20 attached to a turbo compressor.
  • the instability detecting device for turbo compressors of this invention includes a detector 20 , which is attached to the inlet suction port 14 of a turbo compressor's impeller 12 .
  • This detector 20 is used for detecting a pressure difference formed at the inlet suction ports 14 of the impeller 12 in accordance with the flowing direction of working fluid introduced into the inlet suction port 14 .
  • the instability detector 20 has a longitudinal cylindrical body 22 , with first and second pressure tubes 25 and 26 axially set in the body 22 while being spaced apart from each other.
  • the first and second pressure tubes 25 and 26 extend in parallel to each other, with a first pressure discharge port 25 a of the first pressure tube 25 and a second pressure discharge port 26 a of the second pressure tube 26 exposed to the outside of the body 22 at an end surface of the body 22 .
  • the two pressure tubes 25 and 26 are arranged on the same plane.
  • a partition wall 28 is diametrically arranged on the end surface of the body 22 while crossing the end surface and separating the two pressure discharge ports 25 a and 26 a of the pressure tubes 25 and 26 from each other.
  • Each of the two pressure tubes 25 and 26 has a pressure sensor (not shown) or a U-shaped pressure tube (not shown), which is used for sensing pressures of the tubes 25 and 26 and outputs electric signals or visual signals indicating the sensed pressures.
  • the instability detector 20 of this invention is attached to the inlet suction port 14 of the impeller 12 such that the partition wall 28 extends in parallel to the rotation axis of the impeller 12 .
  • the flow rate of the working fluid at the outlet port of the turbo compressor is cyclically changed while measuring the pressures P 1 and P 2 at the two pressure discharge ports 25 a and 26 a of the pressure tubes 25 and 26 .
  • the measured pressures P 1 and P 2 are shown in the graph of FIG. 3.
  • the detector 20 is rotatable at an angle of 360° in response to the outlet flow velocities of the working fluid at the two pressure discharge ports 25 a and 26 a .
  • a plurality of calibration curves according to the outlet flow velocities of the working fluid are formed prior to making the calibration curves dimensionless using both a total pressure Pt and a static pressure P s .
  • the calibration curves are similar to each other regardless of the outlet flow velocities. This means that the detector 20 of this invention is usable regardless of the capacity or the size of the turbo compressor or the rpm of the impeller 12 .
  • FIG. 4 is a graph showing a static pressure rise coefficient as a function of a flow coefficient of the instability detector 20 of this invention. This graph thus shows the operational performance of the turbo compressor within both a stable operational region 9 and an unstable operational region 10 .
  • FIG. 5 a is a graph showing the standard pressure difference as a function of the rotating angle of the instability detector 20 of this invention within the stable operational region 9 .
  • the reference characters “A”, “B” and “C” denote the operating points “A”, “B” and “C” of the turbo compressor of FIG. 4.
  • the turbo compressor accomplishes the same operational tendency regardless of the operating points within the stable operational region 9 .
  • the pressures at the two pressure discharge ports 25 a and 26 a within the stable operational region 9 are less likely to be different from each other when the instability detector 20 is attached to the inlet suction port 14 of the impeller 12 such that the partition wall 28 extends in parallel to the rotation axis of the impeller 12 so as to make a zero rotating angle of the detector 20 . That is, when the detector 20 is attached to the inlet suction port 14 of the impeller 12 as described above, the working fluid flows along the partition wall 28 , and applies the same pressure to the two pressure discharge ports 25 a and 26 a.
  • FIG. 6 a is a graph showing the standard pressure difference as a function of the rotating angle of the detector 20 of this invention within the unstable operation region 10 .
  • the reference characters “D” and “E” denote the operating points “D” and “E” of the turbo compressor of FIG. 4.
  • the turbo compressor accomplishes the same operational tendency regardless of the operating points within the unstable operational region 10 .
  • the operational tendency of the turbo compressor within the unstable operational region 10 is completely different from that of the compressor within the stable operational region 9 . As shown in FIG.
  • the pressure difference between the two pressure discharge ports 25 a and 26 a within the unstable operational region 10 is maximized when the detector 20 is attached to the inlet suction port 14 of the impeller 12 such that the partition wall 28 extends in parallel to the rotation axis of the impeller 12 so as to make a zero rotating angle of the detector 20 . That is, when the detector 20 is attached to the inlet suction port 14 of the impeller 12 as described above, the working fluid flows in a direction perpendicular to the partition wall 28 , thus maximizing the pressure difference between the two pressure discharge ports 25 a and 26 a.
  • the instability detecting device of this invention detects the pressure difference between the two pressure discharge ports 25 a and 26 a of the detector 20 , and displays the pressure difference on a monitor during an operation of a turbo compressor as shown in FIGS. 5 a and 6 a . Therefore, it is possible for an operator of the turbo compressor to easily check the operational conditions of the compressor.
  • the detector 20 of the present invention may be connected to a means for informing an operator of the turbo compressor of an unstable operation of the compressor through a visual alarm means, such as an alarm lamp, or a voice alarm means, such as a speaker. That is, during an operation of the turbo compressor, the instability detecting device logically compares the pressure difference between the two pressure discharge ports 25 a and 26 a of the detector 20 , and outputs an electric signal to the alarm means so as to allow the alarm means to inform the operator of an unstable operation of the compressor through a visual signal or a voice signal. In response to the visual or voice signal of the alarm means, the operator easily and quickly controls the compressor to change the operational region of the compressor from the unstable region to the stable region.
  • a visual alarm means such as an alarm lamp
  • a voice alarm means such as a speaker
  • the instability detector 20 is installed at the inlet port of the turbo compressor. However, it should be understood that the instability detector 20 may be installed at the outlet discharge port of the turbo compressor without affecting the functioning of the present invention.
  • the present invention provides an instability detecting device for turbo compressors.
  • This detecting device has a simple construction, thus being easily and simply produced at low cost.
  • the detecting device of this invention is not an electric or electronic equipment having a complex construction, and so it is easily and simply operated, maintained and repaired at low cost, thus being convenient to an operator. Furthermore, this detecting device has a high operational reliability.
  • the detecting device of this invention is easily operated even by an unskilled operator, and is usable with a conventional turbo compressor regardless of the capacity, size and rotational speed of the compressor.
  • the detecting device does not have any ill-effect on the operational performance of the turbo compressors.
  • the instability detecting device of this invention allows an operator of a turbo compressor to easily monitor the operational conditions of the compressor, thus allowing the operator to effectively control the operation of the compressor.
  • the instability detecting device of this invention When the instability detecting device of this invention is used with a conventional operation control system for turbo compressors, it is possible for the detecting device to quickly inform an operator of an unstable operation of the compressor, thus allowing the operator to quickly control the operation of the compressor to restore a stable operation. Therefore, the detecting device of this invention almost completely prevents a reduction in the operational performance of the turbo compressors, and protects the compressors from severe damage or breakage during an operation.

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  • 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)
US09/888,712 2001-01-17 2001-06-25 Instability detecting device for turbo compressors Abandoned US20020094267A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR2001-2697 2001-01-17
KR10-2001-0002697A KR100390862B1 (ko) 2001-01-17 2001-01-17 터보압축기 불안정성 감지장치

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US20020094267A1 true US20020094267A1 (en) 2002-07-18

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US09/888,712 Abandoned US20020094267A1 (en) 2001-01-17 2001-06-25 Instability detecting device for turbo compressors

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US (1) US20020094267A1 (ko)
JP (1) JP3787078B2 (ko)
KR (1) KR100390862B1 (ko)
DE (1) DE10134021A1 (ko)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050076656A1 (en) * 2003-10-10 2005-04-14 York International Corporation System and method for stability control in a centrifugal compressor
US7194382B2 (en) 2004-02-06 2007-03-20 Georgia Tech Research Corporation Systems and methods for detection of combustor stability margin
US20080034753A1 (en) * 2006-08-15 2008-02-14 Anthony Holmes Furman Turbocharger Systems and Methods for Operating the Same
US20080253877A1 (en) * 2003-10-10 2008-10-16 Bodell Mark R Control system
US7454892B2 (en) 2002-10-30 2008-11-25 Georgia Tech Research Corporation Systems and methods for detection and control of blowout precursors in combustors using acoustical and optical sensing
US20090150121A1 (en) * 2006-04-18 2009-06-11 Mitsubishi Heavy Industries, Ltd. Performance monitoring apparatus and system for fluid machinery

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101171894B1 (ko) 2005-12-17 2012-08-07 현대자동차주식회사 압축기의 능동 서지 및 스톨 제어 시스템

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4055994A (en) * 1975-08-12 1977-11-01 Nordisk Ventilator Co., A/S Method and a device for detecting the stall condition of an axial flow fan or compressor
US4103544A (en) * 1977-08-18 1978-08-01 United Technologies Corporation Turbine engine surge detector
US4430855A (en) * 1980-08-13 1984-02-14 Snecma Process for detection of rotating stall

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0819918B2 (ja) * 1990-04-05 1996-03-04 ダイキン工業株式会社 ターボ冷凍機のサージング防止装置
JPH0617788A (ja) * 1992-07-01 1994-01-25 Daikin Ind Ltd サージング発生予測装置
JPH06147189A (ja) * 1992-11-11 1994-05-27 Hitachi Ltd 圧縮機の旋回失速防止装置

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4055994A (en) * 1975-08-12 1977-11-01 Nordisk Ventilator Co., A/S Method and a device for detecting the stall condition of an axial flow fan or compressor
US4103544A (en) * 1977-08-18 1978-08-01 United Technologies Corporation Turbine engine surge detector
US4430855A (en) * 1980-08-13 1984-02-14 Snecma Process for detection of rotating stall

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7454892B2 (en) 2002-10-30 2008-11-25 Georgia Tech Research Corporation Systems and methods for detection and control of blowout precursors in combustors using acoustical and optical sensing
US20050076656A1 (en) * 2003-10-10 2005-04-14 York International Corporation System and method for stability control in a centrifugal compressor
US7356999B2 (en) 2003-10-10 2008-04-15 York International Corporation System and method for stability control in a centrifugal compressor
US20080253877A1 (en) * 2003-10-10 2008-10-16 Bodell Mark R Control system
US7905102B2 (en) 2003-10-10 2011-03-15 Johnson Controls Technology Company Control system
US7194382B2 (en) 2004-02-06 2007-03-20 Georgia Tech Research Corporation Systems and methods for detection of combustor stability margin
US20090150121A1 (en) * 2006-04-18 2009-06-11 Mitsubishi Heavy Industries, Ltd. Performance monitoring apparatus and system for fluid machinery
US7996183B2 (en) * 2006-04-18 2011-08-09 Mitsubishi Heavy Industries, Ltd. Performance monitoring apparatus and system for fluid machinery
US20080034753A1 (en) * 2006-08-15 2008-02-14 Anthony Holmes Furman Turbocharger Systems and Methods for Operating the Same

Also Published As

Publication number Publication date
KR100390862B1 (ko) 2003-07-10
JP2002242879A (ja) 2002-08-28
KR20020061751A (ko) 2002-07-25
JP3787078B2 (ja) 2006-06-21
DE10134021A1 (de) 2002-07-25

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Owner name: KOREA INSTITUTE OF SCIENCE AND TECHNOLOGY, KOREA,

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:KIM, KWANG HO;SHIN, YOU HWAN;JEON, JAE HAK;REEL/FRAME:011947/0298

Effective date: 20010601

STCB Information on status: application discontinuation

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