[go: up one dir, main page]

EP1674734A1 - Méthode d' amélioration de la stabilité de courant d' une turbomachine - Google Patents

Méthode d' amélioration de la stabilité de courant d' une turbomachine Download PDF

Info

Publication number
EP1674734A1
EP1674734A1 EP04106808A EP04106808A EP1674734A1 EP 1674734 A1 EP1674734 A1 EP 1674734A1 EP 04106808 A EP04106808 A EP 04106808A EP 04106808 A EP04106808 A EP 04106808A EP 1674734 A1 EP1674734 A1 EP 1674734A1
Authority
EP
European Patent Office
Prior art keywords
blade
blades
additional
turbocompressor
row
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.)
Withdrawn
Application number
EP04106808A
Other languages
German (de)
English (en)
Inventor
Marco Micheli
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
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP04106808A priority Critical patent/EP1674734A1/fr
Priority to EP05815881.7A priority patent/EP1828616B1/fr
Priority to PCT/EP2005/056294 priority patent/WO2006067025A1/fr
Publication of EP1674734A1 publication Critical patent/EP1674734A1/fr
Priority to US11/812,029 priority patent/US20080003098A1/en
Withdrawn legal-status Critical Current

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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps

Definitions

  • the invention relates to a method for improving the flow stability of a turbocompressor.
  • the method can be used in particular in multi-stage axial turbocompressors.
  • the invention relates to components of a turbo-compressor, which are modified by means of the specified method, and to a turbo-compressor, and to a gas turbine group, which comprises such a turbo-compressor.
  • Compressors of gas turbine groups and in particular air-breathing gas turbine groups must ensure stable operation over a very wide operating range. This is partly due to the wide range of environmental conditions.
  • single-shaft gas turbine groups which serve to generate electricity, to control the operating state of the compressor independently of the rotational speed.
  • machines that are installed in weak networks as they typically occur in third world countries, run with large set by the network frequency and thus speed fluctuations and often with stability-deteriorating underspeed.
  • aging, wear, and contamination of the compressor blades may result in degradation of stability performance.
  • the compressor In the design of gas turbine groups, the compressor must be able to work with very good efficiencies. However, this may result in the compressor under extreme conditions, such as lower stability in itself Compressor inlet temperatures due to the predetermined by the turbine increasing pressure ratio is operated close to the stability limit, or that very high compressor inlet temperatures shift the operating point of the compressor in a conditionally stable range. The stability reserve may then no longer be sufficient to absorb further unfavorable factors mentioned above.
  • a method will now be given which, according to one of many aspects, makes it possible to adapt the operating behavior of a turbocompressor to special boundary conditions and, in particular, to improve the flow stability of the turbocompressor without modifications of the rotor shaft or the housing to have to make. Likewise, according to another exemplary aspect, it should be possible to improve the flow stability of the turbocompressor without having to design and verify new airfoil geometries.
  • the invention makes it possible to change the division ratio of an axial blade grid without changing the geometry of the blades and in particular without changing components such as the rotor shaft or the housing.
  • the pitch ratio of the blade lattice of an axial blade row or a blade ring is defined as the mutual offset of two blade leaves in the circumferential direction, based on the chord length of an airfoil.
  • the proposed method can be realized in a particularly simple manner if the blades arranged in a blade ring are arranged with their blade roots in a circumferential groove of a rotor shaft or of a housing.
  • At least one spacer arranged in the circumferential direction between two blade roots of the blade ring is removed, and in its place at least one additional blade is inserted.
  • at least one spacer arranged between two blade roots of the blade ring is exchanged for a spacer with a smaller circumferential extension, and at least one additional blade is installed.
  • at least one existing spacer is removed and machined so that the circumferential extent of the spacer is reduced; the thus modified spacer is reinstalled, and at least one additional blade is inserted into the blade ring.
  • An alternative or cumulative method variant to be used is characterized in that at least one existing blade is replaced by a blade whose blade root has a smaller circumferential extent, and to insert at least one additional blade into the blade ring.
  • This method may also include expanding an existing blade and machining its blade root so as to reduce the circumferential extent of the blade root. The blade is reinstalled after the modification of the blade root together with an additional blade.
  • blades are used as an additional blade and / or optionally as blades to be installed, whose blade blade has the same chord length and in particular the same blade geometry as the originally installed blades.
  • additional blades with the originally installed blades identical blades.
  • a modification of the blade root is also carried out on these blades, which blades are identical to one another, whereby the peripheral extent of the blade root is reduced compared to the original state.
  • the only grating characteristic that is changed is the division ratio.
  • the effort that is necessary for the modification is kept low because, depending on the specific situation, not all blades of the modified blade ring must be replaced and a new design of the blade geometry is eliminated.
  • the effects on the flow conditions of the downstream blade edge remain minimal.
  • blades are arranged with identical chord length of the blade blade and in particular with identical blade geometry after conversion throughout the blade ring.
  • a major advantage of the method described here is that compressors can be individually and locally modified to specific operating conditions without requiring modifications to large and difficult to handle components such as the rotor shaft and / or the housing.
  • the method can be carried out in such a way that only standard components with, if necessary, easy-to-carry out modifications, such as, for example, easy milling of the blade root, are required.
  • not all blades of the blade ring necessarily be replaced, but it is sufficient, if necessary, to re-supply the additional blades to be built, which greatly simplifies logistics especially in installations such as hard to reach regions.
  • the method described above also makes it possible to optimize turbocompressors for normal use, since it is very easily possible by means of the described method to modify a compressor, which is intended for exceptional and extreme operating conditions, for a more stable operating behavior.
  • the method specified here is particularly suitable for modifying at least one blade row of the rotor and / or the stator of a turbocompressor.
  • the method is suitable for modifying a turbocompressor of a gas turbine group.
  • the invention also includes a rotor of a turbocompressor and a stator of a turbocompressor, with at least one row of tracks, which is modified according to the method described above. It also includes a turbocompressor, which comprises a rotor and / or stator modified by means of the method.
  • Figure 1 is a Gastubond
  • FIG. 2 shows a stage of an axial turbocompressor with compressor blades arranged in a circumferential groove
  • FIG. 3 shows the stage from FIG. 2 in another view
  • Figure 4 is a tabular summary of the modifications of a 17-stage axial turbocompressor.
  • FIG. 1 shows a gas turbine group 1, which comprises a compressor 2, a combustion chamber 3 and a turbine 4.
  • the illustrated gas turbine group is used to drive a generator 5 for power generation.
  • a rotor comprising a rotor shaft with blades and a stator with usually arranged in the housing vanes.
  • any frequency change of the network results directly in a speed change of the gas turbo group.
  • FIG. 2 shows part of a rotor of a compressor with a row of blades.
  • the rotor comprises the rotor shaft 21.
  • a circumferential groove 22 is incorporated, in which the blades 23 of the blade row are arranged.
  • a blade 23 comprises a blade root 231 and an airfoil 232.
  • blade roots 231 and spacers 24 are alternately arranged.
  • the blade ring includes N blades. With U, the circumferential direction of the blade ring is designated.
  • blade roots 231 and spacers 24 in the circumferential groove and the blades 232 is shown in the development shown in Figure 3.
  • the extent of a blade root in the circumferential direction is denoted by I.
  • the extension of a spacer in the circumferential direction is denoted by b.
  • These masses are indicated in each case on the outer circumference of the rotor shaft.
  • the blade pitch that is, the distance between two blades in the circumferential direction, is denoted by t.
  • this measure varies over the blade height;
  • the chord length of an airfoil is not necessarily constant over the entire blade height.
  • the division ratio t / s is, as is familiar to the expert, a decisive grating characteristic. With decreasing division ratio, the wall friction losses of the flow in the blade grid increase. With a very large division ratio, the losses increase due to the increasingly inefficient flow diversion. For compressors, moreover, the tendency for flow separation increases. In between there exists an optimum division ratio, where the losses are minimal, and on which a blade grid is usually designed at least approximately.
  • the optimum division ratio is a function of a grid load characteristic and can be determined by a person skilled in the art without any problem.
  • turbocompressors which are used, for example, as compressors of gas turbine groups, with regard to the losses in such a way that they operate in a frequently occurring operating range with lowest losses, for example in more than 70 percent of all applications.
  • the possibility of improving the operational stability of the turbocompressor without constructive changes makes it possible, inter alia, to carry out this design more uncompromisingly and to have to take less account of extreme operating conditions than hitherto usual.
  • the proposed method makes it possible to individually change individual compressors of a series individually compared to the standard design and adapt to specific operating conditions. For example, problems of stable operation are created by gas turbine group compressors which operate at very high ambient temperatures and which may need to operate at low speed in weak electricity networks. This is further accentuated when the gas turbine group is operated at high ambient temperatures to maintain power with water and / or steam injection into the combustion chamber, thereby also increasing the pressure ratio against which the compressor must operate. According to the method proposed here, the stable operating range of the compressor is widened by increasing the number of blades arranged in the blade ring in at least one row of blades and thus reducing the dividing ratio.
  • An embodiment of the method comprises increasing the number of blades from 41 to 45 in the third row of flights of an axial turbocompressor.
  • One embodiment of the method includes increasing the number of blades from 41 to 45 in the fourth row of an axial turbocompressor.
  • An embodiment of the method comprises increasing the number of blades in the fifth row of flights of an axial turbocompressor from 41 to 45.
  • An embodiment of the method comprises increasing the number of blades in the sixth row of an axial turbocompressor from 51 to 57.
  • An embodiment of the method comprises increasing the number of blades in the 7th row of an axial turbocompressor from 51 to 57.
  • An embodiment of the method comprises increasing the number of blades in the 8th row of an axial turbocompressor from 51 to 57.
  • An embodiment of the method comprises increasing the number of blades in the ninth row of an axial turbocompressor from 65 to 71.
  • An embodiment of the method comprises increasing the number of blades in the 10th row of an axial turbocompressor from 65 to 71.
  • One embodiment of the method comprises increasing the number of blades from 65 to 71 in the 11th row of an axial turbocompressor.
  • One embodiment of the method comprises increasing the number of blades in the 12th row of an axial turbocompressor from 65 to 71.
  • An embodiment of the method comprises, in the 13th row of an axial turbocompressor, increasing the number of blades from 65 to 71.
  • One embodiment of the method comprises increasing the number of blades from 83 to 91 in the 14th row of an axial turbocompressor.
  • One embodiment of the method includes increasing the number of blades from 83 to 91 in the 15th row of an axial turbocompressor.
  • An embodiment of the method comprises increasing the number of blades in the 16th row of an axial turbocompressor from 83 to 91.
  • One embodiment of the method comprises increasing the number of blades in the 17th row of an axial turbocompressor from 83 to 91.
  • One embodiment of the method comprises increasing the number of blades from 34 to 38 in the first guide row of an axial turbocompressor.
  • the first guide row is different from a Vorleit Herbert; the first guide row is understood to mean the row of guide vanes which is arranged immediately downstream of the first row of blades.
  • One embodiment of the method comprises increasing the number of blades from 46 to 50 in the second guide row of an axial turbocompressor.
  • One embodiment of the method comprises increasing the number of blades from 52 to 54 in the third guide row of an axial turbocompressor.
  • One embodiment of the method comprises increasing the number of blades from 52 to 54 in the fourth guide row of an axial turbocompressor.
  • An embodiment of the method comprises increasing the number of blades from 60 to 64 in the fifth guide row of an axial turbocompressor.
  • One embodiment of the method includes increasing the number of blades from 56 to 62 in the sixth row of axial turbocompressors.
  • An embodiment of the method comprises increasing the number of blades in the 7th row of an axial turbocompressor from 52 to 58.
  • One embodiment of the method comprises increasing the number of blades in the eighth guide row of an axial turbocompressor from 66 to 72.
  • An embodiment of the method comprises, in the ninth row of an axial turbocompressor, increasing the number of blades from 66 to 72.
  • An embodiment of the method includes increasing the number of blades from 66 to 72 in the 10th row of an axial turbocompressor.
  • One embodiment of the method includes increasing the number of blades from 66 to 72 in the 11th row of an axial turbocompressor.
  • One embodiment of the method comprises increasing the number of blades from 66 to 72 in the 12th row of an axial turbocompressor.
  • One embodiment of the method includes increasing the number of blades from 84 to 92 in the 13th row of an axial turbocompressor.
  • One embodiment of the method includes increasing the number of blades from 84 to 92 in the 14th row of an axial turbocompressor.
  • One embodiment of the method comprises increasing the number of blades in the 15th row of an axial turbocompressor from 84 to 92.
  • One embodiment of the method includes increasing the number of blades in the 16th order of an axial turbocompressor from 84 to 92.
  • One embodiment of the method includes increasing the number of blades in the 17th order of an axial turbocompressor from 84 to 92.
  • the blade geometry remains preferably unchanged in these modifications.
  • the originally installed blades are reused and additional blades are newly installed.
  • a 17-stage axial turbocompressor is modified according to a method characterized in the claims.
  • the top line indicates the number of the level.
  • LE denotes the guide rows
  • LA denotes the rows of runs.
  • N 0 denotes the number of blades in a blade ring before modification.
  • N 1 denotes the number of blades in a blade ring after the modification. In this way, the modification made can be read from the comparison of the second and third as well as the fourth and fifth line.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP04106808A 2004-12-21 2004-12-21 Méthode d' amélioration de la stabilité de courant d' une turbomachine Withdrawn EP1674734A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP04106808A EP1674734A1 (fr) 2004-12-21 2004-12-21 Méthode d' amélioration de la stabilité de courant d' une turbomachine
EP05815881.7A EP1828616B1 (fr) 2004-12-21 2005-11-29 Méthode d' amélioration de la stabilité de courant d' une turbomachine
PCT/EP2005/056294 WO2006067025A1 (fr) 2004-12-21 2005-11-29 Procede de modification d'un turbocompresseur
US11/812,029 US20080003098A1 (en) 2004-12-21 2007-06-14 Method for modification of a turbocompressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04106808A EP1674734A1 (fr) 2004-12-21 2004-12-21 Méthode d' amélioration de la stabilité de courant d' une turbomachine

Publications (1)

Publication Number Publication Date
EP1674734A1 true EP1674734A1 (fr) 2006-06-28

Family

ID=34930104

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04106808A Withdrawn EP1674734A1 (fr) 2004-12-21 2004-12-21 Méthode d' amélioration de la stabilité de courant d' une turbomachine
EP05815881.7A Not-in-force EP1828616B1 (fr) 2004-12-21 2005-11-29 Méthode d' amélioration de la stabilité de courant d' une turbomachine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05815881.7A Not-in-force EP1828616B1 (fr) 2004-12-21 2005-11-29 Méthode d' amélioration de la stabilité de courant d' une turbomachine

Country Status (3)

Country Link
US (1) US20080003098A1 (fr)
EP (2) EP1674734A1 (fr)
WO (1) WO2006067025A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011054589B4 (de) 2010-10-20 2023-12-14 General Electric Company Rotationsmaschine mit Abstandhaltern zur Steuerung der Fluiddynamik

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008101805A2 (fr) * 2007-02-05 2008-08-28 Az Technologies Sas Machine hydraulique modulaire
CH704212A1 (de) * 2010-12-15 2012-06-15 Alstom Technology Ltd Axialkompressor.

Citations (3)

* 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
EP0707150A2 (fr) * 1994-10-14 1996-04-17 ABB Management AG Compression
US6379112B1 (en) * 2000-11-04 2002-04-30 United Technologies Corporation Quadrant rotor mistuning for decreasing vibration

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1010630A (en) * 1908-05-26 1911-12-05 Colonial Trust Co Blade-holding means for turbines.
US927093A (en) * 1908-12-17 1909-07-06 Westinghouse Machine Co Elastic-fluid turbine.
AT76502B (de) * 1914-02-12 1919-05-26 Erste Bruenner Maschinen Fab Schaufelbefestigung für Dampf- und Gasturbinen.
US1156529A (en) * 1914-06-10 1915-10-12 Gen Electric Turbine bucket-wheel.
US1366605A (en) * 1919-06-27 1921-01-25 Gen Electric Blade-securing means and method of making the same
US1494781A (en) * 1921-05-31 1924-05-20 Westinghouse Electric & Mfg Co Blade fastening
US1590328A (en) * 1923-08-13 1926-06-29 Westinghouse Electric & Mfg Co Fastening means for turbine blading
US2857134A (en) * 1954-03-17 1958-10-21 Parsons C A & Co Ltd Assembly of blades for turbines and the like
US3032864A (en) * 1958-04-29 1962-05-08 Ford Motor Co Wheel manufacture
CH516731A (de) * 1969-12-12 1971-12-15 Bbc Sulzer Turbomaschinen Schaufelkranz für Turbomaschinen
IT1066506B (it) * 1973-12-17 1985-03-12 Seeber Willi Ruota a pale per ventilatori e procedimento per produrla
FR2416341A1 (fr) * 1978-02-02 1979-08-31 Messier Fa Generateur aero-hydraulique reversible et installations de recuperation de chaleur comprenant un tel generateur
US5232346A (en) * 1992-08-11 1993-08-03 General Electric Company Rotor assembly and platform spacer therefor

Patent Citations (3)

* 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
EP0707150A2 (fr) * 1994-10-14 1996-04-17 ABB Management AG Compression
US6379112B1 (en) * 2000-11-04 2002-04-30 United Technologies Corporation Quadrant rotor mistuning for decreasing vibration

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011054589B4 (de) 2010-10-20 2023-12-14 General Electric Company Rotationsmaschine mit Abstandhaltern zur Steuerung der Fluiddynamik

Also Published As

Publication number Publication date
EP1828616B1 (fr) 2014-10-01
WO2006067025A1 (fr) 2006-06-29
US20080003098A1 (en) 2008-01-03
EP1828616A1 (fr) 2007-09-05

Similar Documents

Publication Publication Date Title
DE102011054589B4 (de) Rotationsmaschine mit Abstandhaltern zur Steuerung der Fluiddynamik
EP3611387B1 (fr) Roue à aubes d'une turbomachine
EP1836401B1 (fr) Méthode pour modifier un compresseur multi-étages
EP2304186B1 (fr) Turbomachine axiale à faibles pertes du jeu des extrémités d'aubes
EP2993357B1 (fr) Étage de compresseur radial
DE10233032A1 (de) Strömungsarbeitsmaschine mit integriertem Fluidzirkulationssystem
DE102009043833A1 (de) Relativpositionierung von Turbinenschaufelblättern
EP3428393A1 (fr) Roue aubagée d'une turbomachine
EP2913479A1 (fr) Aubes en tandem d'une turbomachine
EP2846000B1 (fr) Roue statorique d'une turbine à gaz
EP1970542B2 (fr) Décalage d'aube en fonction d'étranglement dans des turbomachines
EP1828616B1 (fr) Méthode d' amélioration de la stabilité de courant d' une turbomachine
EP3388626A1 (fr) Contournage d'une plate-forme de grille d'aube
EP2699793B1 (fr) Ensemble pompe-turbine
DE102007053135A1 (de) Gasturbinenbauteil, insbesondere Flugtriebwerksbauteil bzw. Verdichterbauteil
EP2878773B1 (fr) Turbine à gaz avec anneau fendu de fixation
EP3498972B1 (fr) Module de turbine pour une turbomachine
DE10340827A1 (de) Reparaturverfahren für eine Schaufel einer Strömungsarbeitsmaschine
DE102009043834A1 (de) Relativpositionierung von Turbinenschaufelblättern
DE102004009755A1 (de) Gasturbinenschaufel
WO2010063518A1 (fr) Configuration géométrique des aubes de la roue d'un turbocompresseur
DE102004026367B4 (de) Turbomaschine
EP1143108A1 (fr) Méthode de fabrication d'un segment statorique à ailettes et segment statorique à ailettes
DE102015223210B3 (de) Verdichter, Verfahren und Strömungsmaschine
EP2614222B1 (fr) Dispositif de rupture de tourbillon dans un courant de fuite d'une turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

AKX Designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20061229