WO2006058848A1 - Verfahren zum betrieb eines turboverdichters - Google Patents
Verfahren zum betrieb eines turboverdichters Download PDFInfo
- Publication number
- WO2006058848A1 WO2006058848A1 PCT/EP2005/056051 EP2005056051W WO2006058848A1 WO 2006058848 A1 WO2006058848 A1 WO 2006058848A1 EP 2005056051 W EP2005056051 W EP 2005056051W WO 2006058848 A1 WO2006058848 A1 WO 2006058848A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- speed
- vorleitreihe
- compressor
- turbocompressor
- gas turbine
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims description 26
- 230000005284 excitation Effects 0.000 claims 1
- 230000001133 acceleration Effects 0.000 abstract description 6
- 238000011161 development Methods 0.000 description 6
- 230000018109 developmental process Effects 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000004590 computer program Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
- F04D27/02—Surge control
- F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
-
- 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
- F04D27/02—Surge control
-
- 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
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
-
- 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
- F04D27/02—Surge control
- F04D27/0292—Stop safety or alarm devices, e.g. stop-and-go control; Disposition of check-valves
Definitions
- the invention relates to a method for operating a turbocompressor according to claim 1.
- turbo-compressor turbocompressors are operated at very low pressure ratios during startup and due to the low RPM of unfavorable stage kinematics conditions.
- the front stages of an axial compressor have to cope with unfavorable angle of attack, whereas the rear compressor stages are operated at the limit of their ability to swallow. There are therefore undesirable and unfavorable flow instabilities within the compressor. From the prior art it is known to blow off partial mass flows during compression within a multi-stage axial compressor.
- One aspect of the present invention is directed to provide a method of the type mentioned above so that the disadvantages of the prior art are avoided.
- a A method of operating a turbo-compressor may be specified such that flow instabilities during startup and acceleration of the compressor are reduced and / or prevented.
- an aspect of the invention relates to turbocompressors having at least one Vorleit2-1 with an adjustable blade grid, and more specifically, the invention also relates to multi-stage axial turbocompressors.
- a more specific embodiment of the invention relates to gas turbine group compressors.
- the invention is thus based, according to one aspect thereof, during the
- Accelerating the compressor to change the position of an adjustable Vorleit marina refers in particular to the startup or start-up of the compressor, which is accelerated from a rest state or from a speed which is well below a desired operating speed of the compressor to the target operating speed.
- a static blade grid which is arranged upstream of the first compressor row, and the blades are rotatably mounted, for example, such that the outflow direction of the blade grid of Vorleit marina flowing fluid changed can be. It is known that by adjusting the Vorleit #2 under otherwise constant operating conditions, the mass flow of the compressor can be changed.
- the closing of the pilot row when the pilot row is adjusted in a direction which leads to a reduction of the mass flow.
- the Vorleit #2 is adjusted during acceleration, in particular when starting the compressor, to a closed position.
- the adjustment of the preliminary row takes place dynamically.
- the adjustment of the Vorleit marina with a predetermined gradient over the Time.
- the position of the preliminary row is represented for example as an angle by which the blades of the Vorleit marinangitters are rotated relative to a reference position.
- the adjustment therefore takes place at a constant angular velocity of the blade position.
- the pilot row of the turbocompressor is adjusted to a nominal fully open position.
- the speed of the turbo-compressor is increased and the pre-guide row is kept open up to a first speed.
- the speed of the turbocompressor is further increased up to a second speed, and during the speed increase from the first speed to the second speed, the position of the pilot row is varied such that the position of the pilot row reaches a nominally closed position at the second speed at the latest.
- the speed of the turbo-compressor is then further increased with closed Vorleit Research, for example up to a nominal speed or a stable operating speed.
- the nominal speed or operating speed are characteristics of the compressor, and as such can be readily defined by one skilled in the art.
- the nominal speed is particularly simple if the compressor is a compressor of a gas turbine group.
- the fully open position of the Vorleit colleges and the fully closed position of Vorleit colleges are also defined on a case by case basis in the operating concept of the compressor, which is also readily familiar to those skilled in the art.
- the fully open position of the pilot row is that which occupies the pilot row when the compressor is operated at rated power, or, when the turbo compressor is operated as a gas turbine group compressor, the position at nominal full load power of the gas turbine group.
- the fully closed position is the position that is determined by the normal operating regime of the Compressor at the lowest power or, for example, in the idle mode of a gas turbine group is specified.
- the first speed and the second speed are determined in one embodiment of the invention by performing experiments on a specific compressor or on a prototype of a compressor type in which the occurrence of flow instabilities is measured.
- a speed is experimentally determined, in which the instabilities start to exceed a certain limit value when the lead-in series is open. It is then defined this speed or a slightly lower speed than the first speed.
- a speed can be determined at which the flow instabilities disappear or at least fall below a threshold value when starting with a closed pilot row. This speed is then set as the second speed.
- the first speed below which the pilot row is kept open, is in an exemplary embodiment in the range of 25% to 50% of a nominal speed. In particular, it is also in the range of 25% to 40% of the nominal speed; Furthermore, this speed may be in the range of 30% to 40% of the nominal speed, and in particular embodiments, the first speed is also in the range of 30 to 35% of the nominal speed or in the range of 35% to 40% of the nominal speed. In a specific embodiment, the first speed is about 1400 rpm, and the nominal speed is 3600 rpm.
- the second speed is for example in the range of 50% to 70% of the nominal speed.
- the second speed depending on the specific circumstances, also be in the range of 50% to 60% or 60% to 70% of the nominal speed.
- the second speed is in the range of 50% to 55% of the nominal speed; in other specific embodiments, the second speed is in the range of 55% to 60% or in the range of 60% to 65% of the nominal speed.
- the second speed is 2080 rpm and the nominal speed is 3600 rpm.
- the Vorleitsch example 1400 1 / min to about 2000 1 / min is moved from the fully open to the fully closed position.
- the adjustment of the Vorleit plinth takes place in a development of the invention with a constant angular gradient over time; In another embodiment of the invention, the adjustment is carried out with a constant angle gradient over the speed.
- the control of the turbocompressor for carrying out the method for example, by means of a suitably configured control unit.
- the control unit comprises, for example, a processor which, by suitable programming, enables the control unit to operate the turbocompressor according to the method described above.
- the control unit is configured according to a further development by a digital code or a digital program, which is loaded into the control unit or stored in a memory within the control unit.
- the invention also relates to a control unit which is configured to cause a turbocompressor to carry out a method as described above, and a digital program code which is suitable for suitably configuring a control unit, the source code of such a computer program. and a disk on which the program code is stored as source code or executable code.
- the data carrier is to be understood by name also a non-volatile memory chip.
- Figure 1 shows a gas turbine group with an operable according to the invention turbo compressor
- Figure 2 shows an exemplary course of the position of the adjustable
- the gas turbine group comprises a compressor 11, a combustion chamber 12, and a turbine 13.
- a generator 14 is driven to generate electricity, which via the shaft 16 with the not explicitly shown rotor of the gas turbine group is coupled.
- the turbine 13 and the compressor 11 are arranged on a common shaft which is fixedly coupled to the drive shaft 16 of the generator 14.
- the speed of the gas turbine group is denoted by n and is set substantially constant in the power operation of the gas turbine group.
- the compressor of the gas turbine group which is designed as a multi-stage axial turbocompressor, comprises an adjustable Vorleit Herbert 15.
- the adjustable Vorleit Hor is also known from the prior art per se.
- the adjustable pilot row in the gas turbine group power mode serves to vary the mass flow of the gas turbine group.
- a control unit 4 is present for controlling and controlling the operation of the gas turbine group. This receives in addition to a variety of unillustrated other information about the current operating status of the gas turbine group information about the Speed n of the gas turbine group and the position VIGV of the adjustable pilot row. From this information, control variables for the operation of the gas turbine group are formed according to an operating concept, such as the manipulated variable Y-VIGV for the adjustable pilot row.
- the control unit 4 is configured in one embodiment of the invention by a digital program for controlling the gas turbine group, including the operation of the compressor and the position of the adjustable Vorleit marina, which is stored for example on an external disk 5 and is loaded into the control unit.
- a digital program for controlling the gas turbine group including the operation of the compressor and the position of the adjustable Vorleit marina, which is stored for example on an external disk 5 and is loaded into the control unit.
- a non-volatile memory module can also be arranged in the control unit 4, in which the code for configuring the control unit 4 is stored.
- the generator 14 is first operated by an electric motor. From a certain speed, the combustion chamber 12 is fired; The acceleration is further supported by the electric motor-driven generator 14.
- the compressor 11 passes through a speed range in which he is unable to work due to the principle or insufficient.
- the horizontal axis is the speed n, no is the rated speed of the gas turbo group, ni and n2 are the first and second speeds, which are determined according to the criteria described above.
- the pilot row is kept open up to the speed ni, and then closed so that the pilot row above the second speed n2 in the maximum closed position.
- the fully closed position is already at a speed below the second speed n2 ! reached; This is due to the fact that in this example, the adjustment of the Vorleit #2 over the time and not over the speed is controlled.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP05808123.3A EP1817503B1 (de) | 2004-12-03 | 2005-11-18 | Verfahren zum betrieb eines turboverdichters |
KR1020077015267A KR101197498B1 (ko) | 2004-12-03 | 2005-11-18 | 터보 압축기의 작동 방법 |
US11/806,419 US7758298B2 (en) | 2004-12-03 | 2007-05-31 | Method for operating a turbocompressor |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04106275.3 | 2004-12-03 | ||
EP04106275A EP1666731A1 (de) | 2004-12-03 | 2004-12-03 | Verfahren zum Betrieb eines Turboverdichters |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/806,419 Continuation US7758298B2 (en) | 2004-12-03 | 2007-05-31 | Method for operating a turbocompressor |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2006058848A1 true WO2006058848A1 (de) | 2006-06-08 |
Family
ID=34929990
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2005/056051 WO2006058848A1 (de) | 2004-12-03 | 2005-11-18 | Verfahren zum betrieb eines turboverdichters |
Country Status (4)
Country | Link |
---|---|
US (1) | US7758298B2 (de) |
EP (2) | EP1666731A1 (de) |
KR (1) | KR101197498B1 (de) |
WO (1) | WO2006058848A1 (de) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8291690B1 (en) * | 2012-01-31 | 2012-10-23 | United Technologies Corporation | Gas turbine engine with variable area fan nozzle positioned for starting |
US20130192195A1 (en) | 2012-01-31 | 2013-08-01 | Eric J. Wehmeier | Gas turbine engine with compressor inlet guide vane positioned for starting |
WO2014055100A1 (en) * | 2012-10-01 | 2014-04-10 | United Technologies Corporation | Low compressor having variable vanes |
JP6834845B2 (ja) | 2017-08-15 | 2021-02-24 | 株式会社島津製作所 | ターボ分子ポンプ |
JP6623318B1 (ja) * | 2019-05-13 | 2019-12-18 | 三菱日立パワーシステムズ株式会社 | 燃料ガス供給装置および方法 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2119862A (en) * | 1982-05-06 | 1983-11-23 | Gen Electric | Variable stator vane (VSV) closed loop control system of a compressor |
US5259188A (en) * | 1992-08-24 | 1993-11-09 | General Electric Company | Method and system to increase stall margin |
US20040055310A1 (en) * | 2001-10-10 | 2004-03-25 | Giovanni Mannarino | Control system for positioning compressor inlet guide vanes |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5244976B2 (de) * | 1973-12-12 | 1977-11-11 | ||
US7096657B2 (en) * | 2003-12-30 | 2006-08-29 | Honeywell International, Inc. | Gas turbine engine electromechanical variable inlet guide vane actuation system |
WO2006060000A1 (en) * | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method |
JP4699130B2 (ja) * | 2005-08-03 | 2011-06-08 | 三菱重工業株式会社 | ガスタービンの入口案内翼制御装置 |
-
2004
- 2004-12-03 EP EP04106275A patent/EP1666731A1/de not_active Withdrawn
-
2005
- 2005-11-18 EP EP05808123.3A patent/EP1817503B1/de not_active Not-in-force
- 2005-11-18 KR KR1020077015267A patent/KR101197498B1/ko not_active IP Right Cessation
- 2005-11-18 WO PCT/EP2005/056051 patent/WO2006058848A1/de active Application Filing
-
2007
- 2007-05-31 US US11/806,419 patent/US7758298B2/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2119862A (en) * | 1982-05-06 | 1983-11-23 | Gen Electric | Variable stator vane (VSV) closed loop control system of a compressor |
US5259188A (en) * | 1992-08-24 | 1993-11-09 | General Electric Company | Method and system to increase stall margin |
US20040055310A1 (en) * | 2001-10-10 | 2004-03-25 | Giovanni Mannarino | Control system for positioning compressor inlet guide vanes |
Also Published As
Publication number | Publication date |
---|---|
KR101197498B1 (ko) | 2012-11-09 |
EP1817503A1 (de) | 2007-08-15 |
US20070253805A1 (en) | 2007-11-01 |
EP1666731A1 (de) | 2006-06-07 |
EP1817503B1 (de) | 2014-09-24 |
US7758298B2 (en) | 2010-07-20 |
KR20070089989A (ko) | 2007-09-04 |
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