EP1771663B1 - Procede de modification d'un turbocompresseur - Google Patents

Procede de modification d'un turbocompresseur Download PDF

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Publication number
EP1771663B1
EP1771663B1 EP05776213.0A EP05776213A EP1771663B1 EP 1771663 B1 EP1771663 B1 EP 1771663B1 EP 05776213 A EP05776213 A EP 05776213A EP 1771663 B1 EP1771663 B1 EP 1771663B1
Authority
EP
European Patent Office
Prior art keywords
compressor
blow
line
blades
turbocompressor
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.)
Expired - Lifetime
Application number
EP05776213.0A
Other languages
German (de)
English (en)
Other versions
EP1771663A1 (fr
Inventor
Daniel Glesti
Marco Micheli
Thomas Palkovich
Wilfried Rick
Sasha Savic
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.)
GE Vernova GmbH
Original Assignee
Alstom Technology AG
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
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Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1771663A1 publication Critical patent/EP1771663A1/fr
Application granted granted Critical
Publication of EP1771663B1 publication Critical patent/EP1771663B1/fr
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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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/912—Interchangeable parts to vary pumping capacity or size of pump

Definitions

  • the invention relates to a method for modifying a turbocompressor according to the preamble of claim 1. It further relates to a modified according to this method turbo compressor, and uses of the present invention modified turbo compressor.
  • the characterized in the claims invention has for its object to provide a method of the type mentioned above so that even a modified compressor, which has an increased nominal mass flow, can be approached easily.
  • the capacity for blowing off compressed or partially compressed fluid is increased.
  • the capacity is increased, for example, in the same ratio, as increased by the modification of the compressor blades, the intake volume flow.
  • the increase in the Abblasekapaztician by the critical flow area is increased at least one of the compressor connected to the blow-off line.
  • the narrowest cross-section of the flow line must be increased. This is often in the obturator, which serves to close and release the Abblase horr.
  • the invention can therefore be realized very simply by replacing the obturator, also called blow-off valve, by a shut-off device with an enlarged free cross-section.
  • additional blow-off lines are arranged. This can be done by existing, sealed by flanged lid openings of the compressor housing opened and additional Abblase effeten be connected to the resulting housing openings. Alternatively, additional new housing openings can be incorporated into the compressor housing.
  • the additional blow-off lines can be arranged on the one hand at a pressure stage of the compressor, on which there is already an existing blow-off line. It then increases the Abblasekapaztician at the corresponding pressure level of the compressor. But it is also quite possible to arrange the additional blow-off at a position at which no Abblasetechnisch is connected before the modification. It is then created at a pressure additional Abblaseönkeit.
  • Blow-off lines are or are generally arranged on the compressor in such a way that partially compressed fluid is blown off.
  • the blow-off line branches off between two compressor stages. This ensures that, as mentioned in the introduction, when the blow-off line is open, the mass flow in the front compressor stages is greater than in the rear compressor stages.
  • a blow-off conduit may be disposed downstream of the compressor and upstream of the consumer.
  • a blow-off line of a compressor of a gas turbine group is arranged downstream of the compressor and upstream of a first combustion chamber of the gas turbine group.
  • the invention is suitable for retrofitting and increasing the output of a turbo-compressor, which is for example the compressor of a gas turbine group.
  • the gas turbine group in turn is in one Embodiment of the invention Component of a power plant, for example a combined plant.
  • FIGURE shows a gas turbine group before and after an inventive modification of the compressor.
  • the drawing and the embodiment are to be understood as purely exemplary; Elements not necessary for understanding the invention have been omitted.
  • FIG. 1a shows a gas turbine group, comprising a compressor 1, a combustion chamber 2, and a turbine 3, as the skilled person readily familiar.
  • the compressor 1 sucks in an intake volume flow or a nominal mass flow m 1 .
  • This air mass flow is compressed in the compressor 1.
  • a fuel mass flow is burned in the combustion chamber 2, and the resulting hot flue gas is expanded to perform work in the turbine 3.
  • blow-off lines 11 and 12 are arranged with shut-off elements 21 and 22. As explained in the introduction, these blow-off lines serve to blow off partially compressed air from the compressor during start-up of the compressor at speeds well below the rated speed.
  • the gas turbine group is shown according to an inventive modification of the compressor 1.
  • the intake volume flow of the compressor 1 increases, and accordingly the compressor delivers a nominal mass flow m 2 , which is greater than the nominal mass flow m 1 before the conversion.
  • the increase in the nominal mass flow causes the air mass flow blown off during start-up to be proportionate less than before conversion to new blades. This potentially results in the occurrence of stalling in the front compressor stages and / or clogging of the rear compressor stages despite compressor air blow-off.
  • the blow-off capacities of the compressor have now been increased.
  • the blow-off valve 21 of the blow-off line 11 is replaced by a blow-off valve 21a with an enlarged passage cross-section.
  • a new blow-off line 13 has been rearranged with a blow-off valve 23.
  • the blow-off line 13 can branch off at a pressure stage of the compressor, on which another blow-off line is already arranged, as shown in the figure.
  • the blow-off line 13 may, however, also be arranged at a location of the compressor at which no blow-off line was previously arranged.
  • the blow-off line 13 on the one hand connect to an already existing, but previously closed by a flange cover opening of the housing of the compressor 1; If appropriate, however, a new opening may also have been incorporated into the housing, to which the new discharge line 13 then adjoins.
  • blow-off line 14 connects with a blow-off valve 24.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)

Claims (10)

  1. Procédé de modification d'un turbocompresseur (1), comprenant le démontage de premières pales d'un compresseur et leur remplacement par des deuxièmes pales, de sorte que le débit volumique d'admission du compresseur soit accru pour une même vitesse de rotation et le même rapport de pression, caractérisé par l'augmentation de la capacité de soufflage de fluide comprimé ou partiellement comprimé.
  2. Procédé selon la revendication 1, caractérisé par l'augmentation de la capacité de soufflage dans le même rapport que le débit volumique d'admission.
  3. Procédé selon l'une quelconque des revendications 1 ou 2, caractérisé par l'augmentation de la section transversale d'écoulement d'au moins une conduite de soufflage (11) raccordée au compresseur.
  4. Procédé selon l'une quelconque des revendications précédentes, caractérisé par l'ouverture d'au moins une bride de boîtier existante du boîtier de compresseur et le raccordement d'une conduite de soufflage supplémentaire (13) à l'ouverture de boîtier ainsi formée.
  5. Procédé selon l'une quelconque des revendications précédentes, caractérisé par la réalisation d'au moins une ouverture supplémentaire dans le boîtier de compresseur, et la disposition d'une conduite de soufflage supplémentaire (13) au niveau de cette ouverture.
  6. Procédé selon l'une quelconque des revendications précédentes, dans lequel le compresseur est disposé en amont d'un consommateur (2, 3), caractérisé par la disposition d'une conduite de soufflage (14) en aval du compresseur et en amont du consommateur.
  7. Procédé selon l'une quelconque des revendications précédentes, dans lequel le compresseur est un compresseur d'un groupe générateur à turbine à gaz, caractérisé par la disposition d'une conduite de soufflage (14) en aval du compresseur (1) et en amont d'une première chambre de combustion (2) du groupe générateur à turbine à gaz.
  8. Turbocompresseur modifié par un procédé selon l'une quelconque des revendications précédentes.
  9. Groupe générateur à turbine à gaz comprenant un compresseur selon la revendication 8.
  10. Centrale comprenant un groupe générateur à turbine à gaz selon la revendication 9.
EP05776213.0A 2004-07-26 2005-07-14 Procede de modification d'un turbocompresseur Expired - Lifetime EP1771663B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004036238A DE102004036238A1 (de) 2004-07-26 2004-07-26 Verfahren zur Modifikation eines Turbokompressors
PCT/EP2005/053378 WO2006010712A1 (fr) 2004-07-26 2005-07-14 Procede de modification d'un turbocompresseur

Publications (2)

Publication Number Publication Date
EP1771663A1 EP1771663A1 (fr) 2007-04-11
EP1771663B1 true EP1771663B1 (fr) 2013-11-13

Family

ID=35428126

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05776213.0A Expired - Lifetime EP1771663B1 (fr) 2004-07-26 2005-07-14 Procede de modification d'un turbocompresseur

Country Status (7)

Country Link
US (1) US7628576B2 (fr)
EP (1) EP1771663B1 (fr)
KR (1) KR101243393B1 (fr)
DE (1) DE102004036238A1 (fr)
PE (1) PE20060248A1 (fr)
TW (1) TWI356878B (fr)
WO (1) WO2006010712A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102177347A (zh) * 2008-10-13 2011-09-07 拓博有限公司 用于多级涡轮压缩机的放气系统

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB777955A (en) * 1954-07-06 1957-07-03 Ruston & Hornsby Ltd Improvements in or relating to fluid flow machines such as hydraulic, steam or gas turbines or axial-flow compressors
DE1070880B (de) * 1956-12-19 1959-12-10 Rolls-Royce Limited, Derby (Großbritannien) Gasturbinenaggregat mit Turboverdichter
DE1107887B (de) * 1957-04-16 1961-05-31 Power Jets Res & Dev Ltd Regler zur Pumpverhuetung bei Stroemungsverdichtern
DE3313321A1 (de) * 1983-04-13 1984-10-18 Klöckner-Humboldt-Deutz AG, 5000 Köln Abblasvorrichtung an einem mehrstufigen axialverdichter
GB2158879B (en) * 1984-05-19 1987-09-03 Rolls Royce Preventing surge in an axial flow compressor
JP2619360B2 (ja) * 1986-02-21 1997-06-11 株式会社日立製作所 ターボ圧縮機のサージング防止装置
US5520512A (en) * 1995-03-31 1996-05-28 General Electric Co. Gas turbines having different frequency applications with hardware commonality
DE19541192C2 (de) * 1995-11-04 1999-02-04 Ghh Borsig Turbomaschinen Gmbh Verfahren zum Schutz eines Turbokompressors vor Betrieb im instabilen Arbeitsbereich mittels einer Abblaseeinrichtung
US6379112B1 (en) 2000-11-04 2002-04-30 United Technologies Corporation Quadrant rotor mistuning for decreasing vibration

Also Published As

Publication number Publication date
DE102004036238A1 (de) 2006-02-16
KR20070038527A (ko) 2007-04-10
KR101243393B1 (ko) 2013-03-13
PE20060248A1 (es) 2006-04-12
TWI356878B (en) 2012-01-21
WO2006010712A1 (fr) 2006-02-02
US20070128024A1 (en) 2007-06-07
EP1771663A1 (fr) 2007-04-11
US7628576B2 (en) 2009-12-08
TW200622107A (en) 2006-07-01

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