EP1199521A1 - Turbine à gaz et procédé pour l'amortissement de vibrations d' une chambre de combustion annulaire de turbine à gaz - Google Patents

Turbine à gaz et procédé pour l'amortissement de vibrations d' une chambre de combustion annulaire de turbine à gaz Download PDF

Info

Publication number
EP1199521A1
EP1199521A1 EP00122554A EP00122554A EP1199521A1 EP 1199521 A1 EP1199521 A1 EP 1199521A1 EP 00122554 A EP00122554 A EP 00122554A EP 00122554 A EP00122554 A EP 00122554A EP 1199521 A1 EP1199521 A1 EP 1199521A1
Authority
EP
European Patent Office
Prior art keywords
clamping ring
gas turbine
combustion chamber
clamping
annular combustion
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Withdrawn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
EP00122554A
Other languages
German (de)
English (en)
Inventor
Roderich Bryk
Otmar Gossmann
Harald Hoell
Burkhard Voss
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP00122554A priority Critical patent/EP1199521A1/fr
Priority to JP2002536469A priority patent/JP2004511752A/ja
Priority to US10/399,264 priority patent/US6988366B2/en
Priority to EP01972093A priority patent/EP1327107A1/fr
Priority to PCT/EP2001/011511 priority patent/WO2002033323A1/fr
Publication of EP1199521A1 publication Critical patent/EP1199521A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement

Definitions

  • the invention relates to a gas turbine with a compressor, an annular combustion chamber and a turbine part.
  • the invention also relates to a method for damping vibrations Annular combustion chamber of a gas turbine.
  • thermoacoustic Vibration is actively damped by the fact that Injecting a fluid is the location of the combustion associated with it Heat release fluctuation is controlled.
  • the object of the invention is to provide a gas turbine with a Annular combustion chamber that is particularly robust against combustion vibrations is.
  • Another object of the invention is Specification of a method for damping the vibration of a Annular combustion chamber of a gas turbine.
  • the task aimed at a gas turbine solved by specifying a gas turbine with a compressor, an annular combustion chamber and a turbine part, the Annular combustion chamber has an outer wall with an outer surface and the annular combustion chamber on its outer surface is surrounded by a clamping ring.
  • the object is directed to a method solved by specifying a method for damping vibrations an annular combustion chamber of a gas turbine, in which Setting a clamping force on one around the outer circumference of the Ring combustion chamber extending clamping ring a dissipation of Vibration energy of the ring combustion chamber due to friction on Clamping ring and thus the damping of the vibration caused becomes.
  • the clamping force is on a predominant one Vibration frequency adjusted adjusted.
  • Figure 1 shows schematically in a longitudinal section a gas turbine 3.
  • the gas turbine 3 is directed along an axis 5 and has a compressor 7, one in series Annular combustion chamber 9 and a turbine part 11. From the compressor 7 air 13 is sucked in and highly compressed. The highly compressed Air 13 is fed to the annular combustion chamber 9. There will they burned with the addition of fuel. The emerging Hot exhaust gas 15 is fed to the turbine part 11.
  • the ring combustion chamber 9 has an outer wall 23 with an outer surface 25 on. On the outer surface 25 runs in the circumferential direction a rib 29 which is radially outward a cylindrical Has contact surface 28. On the cylindrical contact surface 28 is a ring combustion chamber 9 surrounding Clamping ring 27 on.
  • the clamping ring 27 does not require any external support points, d. H. it is not an external compensation of thermal conditional relative movements required. This is special Significant if external bases even temporarily would assume a significantly different temperature level than that of damping structure. In this case there would be compensation the expansion differences not possible with reasonable effort.
  • the friction of the clamping ring 27 on the rib 29 arises in that the neutral fibers on the one hand the rib 29 and on the other hand, the clamping ring 27 on different diameters lie.
  • FIG. 2 shows part of an outer wall 23 of an annular combustion chamber 9.
  • the outer wall 23 is surrounded by a clamping ring 27.
  • the clamping ring 27 is made up of individual clamping ring segments 27a, 27b, 27c, 27, d, 27e.
  • Two of the tension ring segments 27a, 27b are connected by a tensioning device 31.
  • the tensioning device 31 has a bridge-like belt 33 on. Two pairs of lead through this bridge-like belt Tie rods 37.
  • One pair of tie rods 37 is with one pair Drawbar eyes 35 engaged.
  • the tie rods 37 are in the belt 33, respectively via several nuts 41 and disc springs in between 39 pre-tensioned.
  • a Superbold 42 closes one disc spring column each.
  • Each towing eye 35 has an elongated hole 43 with which it is circumferential slidably with one of the clamping ring segments 27a, 27b a hinge pin 36 is connected.
  • the closer structure of the Clamping device 31 is also shown enlarged in FIG. 7.
  • FIG. 3 shows a clamping ring segment 27d.
  • the clamping ring segment 27d has a recess 81 at one end with which it connectable to an adjacent clamping ring segment via bolts 83 is. On the other side of the clamping ring segment also a connection to an adjacent clamping ring segment via a taper 85 of the clamping ring segment thickness and a hole 87 possible. These two types of connections will be explained later.
  • the clamping ring segment 27d has an engagement groove 89 on the assembly of the clamping ring segment 27d is engaged with a guide tab 91.
  • the Guide tab 91 enables positive guidance of the Tension ring segment 27d along the circumference during assembly. In the lower part of the outer wall 23, the guide tabs prevent it 91 swiveling away the clamping ring segment during assembly 27d. This measure will of course also apply to the others Tension ring segments applied in the lower part of the outer wall 23.
  • Figure 4 shows in a cross section how the clamping ring 27 the rib 29 is seated.
  • the clamping ring 27 has on its underside a recess 30.
  • the recess 30 is through two on the underside of the clamping ring 27 in the axial direction outer webs 71 running in the circumferential direction.
  • the webs 71 encompass the rib 29.
  • the rib 29 is two axially spaced circumferential ones Ribs 29a formed between which in radial Direction upward offset in the radial direction open below U-shaped support member 29b is attached.
  • the U-shaped support part 29b has on its radially outer Surface of the contact surface 28.
  • the clamping ring 27 has a width of about 70 mm in the axial direction.
  • the height of the clamping ring 27 in the radial direction including the Rib 29 enclosing lugs 71 is approximately 80 mm, while the radial height H1 of the clamping ring 27 without the approaches 71 is approximately 60
  • FIG. 5 shows a segment connection designed as a coupling element 51 between two clamping ring segments 27d, 27e.
  • the Coupling member 51 has two elongated rectangular side parts 101 on. The side parts 101 are with a central pin 103 connected. Between one end of the side parts 101 is a clamping ring segment 27d with its thick taper 85 inserted between the side parts 101. A coupling pin 105 leads through the side parts 101 and through the bore 87 of the Tension ring segment 27d. In the same way is on the other Side of the coupling member 51, the clamping ring segment 27e attached.
  • the coupling member 51 allows the Tension ring segments 27 d, 27e against each other and also allows an easy releasability of this connection point.
  • the coupling link 51 is in particular over a parting of the outer wall 23 used to open an opening of the annular combustion chamber 9, instead of disassembling the clamping ring 27.
  • Figure 6 shows a further connection between two clamping ring segments 27b, 27d.
  • the clamping ring segments are here in Circumferential direction merged and through continuous connecting bolts 111 secured.
  • FIG. 7 shows the one already described in detail Clamping device 31. Also shown is an elongated hole for the annular combustion chamber 9 spanning bridge 121, the Tension ring segments 27a, 27b connects. Bridge 121 is in Figure 8 shown in detail.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Exposure And Positioning Against Photoresist Photosensitive Materials (AREA)
  • Supercharger (AREA)
EP00122554A 2000-10-16 2000-10-16 Turbine à gaz et procédé pour l'amortissement de vibrations d' une chambre de combustion annulaire de turbine à gaz Withdrawn EP1199521A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP00122554A EP1199521A1 (fr) 2000-10-16 2000-10-16 Turbine à gaz et procédé pour l'amortissement de vibrations d' une chambre de combustion annulaire de turbine à gaz
JP2002536469A JP2004511752A (ja) 2000-10-16 2001-10-05 ガスタービンおよびガスタービンにおける環状燃焼器の振動減衰方法
US10/399,264 US6988366B2 (en) 2000-10-16 2001-10-05 Gas turbine and method for damping oscillations of an annular combustion chamber
EP01972093A EP1327107A1 (fr) 2000-10-16 2001-10-05 Turbine a gaz et procede pour amortir les oscillations d'une chambre de combustion annulaire d'une turbine a gaz
PCT/EP2001/011511 WO2002033323A1 (fr) 2000-10-16 2001-10-05 Turbine a gaz et procede pour amortir les oscillations d'une chambre de combustion annulaire d'une turbine a gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00122554A EP1199521A1 (fr) 2000-10-16 2000-10-16 Turbine à gaz et procédé pour l'amortissement de vibrations d' une chambre de combustion annulaire de turbine à gaz

Publications (1)

Publication Number Publication Date
EP1199521A1 true EP1199521A1 (fr) 2002-04-24

Family

ID=8170107

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00122554A Withdrawn EP1199521A1 (fr) 2000-10-16 2000-10-16 Turbine à gaz et procédé pour l'amortissement de vibrations d' une chambre de combustion annulaire de turbine à gaz
EP01972093A Withdrawn EP1327107A1 (fr) 2000-10-16 2001-10-05 Turbine a gaz et procede pour amortir les oscillations d'une chambre de combustion annulaire d'une turbine a gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP01972093A Withdrawn EP1327107A1 (fr) 2000-10-16 2001-10-05 Turbine a gaz et procede pour amortir les oscillations d'une chambre de combustion annulaire d'une turbine a gaz

Country Status (4)

Country Link
US (1) US6988366B2 (fr)
EP (2) EP1199521A1 (fr)
JP (1) JP2004511752A (fr)
WO (1) WO2002033323A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017034539A1 (fr) * 2015-08-24 2017-03-02 Siemens Aktiengesellschaft Système de chambre de combustion modulaire pour moteur à turbine à combustion
WO2021086320A1 (fr) * 2019-10-29 2021-05-06 Volvo Truck Corporation Pince coulissante

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3814549A (en) * 1972-11-14 1974-06-04 Avco Corp Gas turbine engine with power shaft damper
JPS60200022A (ja) * 1984-03-23 1985-10-09 Hitachi Ltd ガスタ−ビンの燃焼器の共振防止装置
DE3539903A1 (de) * 1985-11-11 1987-05-14 Kloeckner Humboldt Deutz Ag Gasturbine mit einem keramischen laufrad
EP0509801A1 (fr) * 1991-04-16 1992-10-21 General Electric Company Capot amorti pour une chambre de combustion
DE4339094A1 (de) 1993-11-16 1995-05-18 Abb Management Ag Verfahren zur Dämpfung von thermoakustischen Schwingungen sowie Vorrichtung zur Durchführung des Verfahrens
DE19711337A1 (de) * 1997-03-18 1998-09-24 Bmw Rolls Royce Gmbh Verfahren zum Spitzenschleifen von in einem Stator- und Maschinengehäuse eingebauten Statorschaufeln einer Axial-Strömungsmaschine

Family Cites Families (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1635783A (en) * 1926-04-08 1927-07-12 Howard W Goodall Hose clamp
US2653836A (en) * 1948-09-04 1953-09-29 Marman Products Company Inc Reinforced v-band clamp
US2688170A (en) * 1951-03-31 1954-09-07 Hallett Mfg Company Strap clamp
US3029095A (en) * 1955-08-18 1962-04-10 Garrett Corp Flange connecting clamp
US2895748A (en) * 1957-09-12 1959-07-21 Oldham Charles Albert Edward Band type clamp for flanged pipes
US3398527A (en) * 1966-05-31 1968-08-27 Air Force Usa Corrugated wall radiation cooled combustion chamber
GB1249499A (en) * 1969-04-29 1971-10-13 Avica Equip Improvements in and relating to circular clamps
US3601868A (en) * 1969-05-14 1971-08-31 Aeroquip Corp Bolt tension gauge
US3661409A (en) * 1969-08-14 1972-05-09 Gray Tool Co Multi-segment clamp
US3788677A (en) * 1972-03-20 1974-01-29 B Stade Emission-free exhaust pipe joint and clamp therefor
US3797078A (en) * 1972-09-01 1974-03-19 Aeroquip Corp Latch and v band coupler
US3903693A (en) * 1973-03-26 1975-09-09 Anthony Fox Rocket motor housing
FR2404793A1 (fr) * 1977-09-30 1979-04-27 Usinor Dispositif d'assemblage, notamment entre deux troncons d'une descente de vent de haut-fourneau
US4191011A (en) * 1977-12-21 1980-03-04 General Motors Corporation Mount assembly for porous transition panel at annular combustor outlet
US4225160A (en) * 1978-02-27 1980-09-30 Exxon Production Research Company Low friction remotely operable clamp type pipe connector
US5018768A (en) * 1990-07-19 1991-05-28 Quikcoup, Incorporated Pipe coupling hinge
FR2710968B1 (fr) * 1993-10-06 1995-11-03 Snecma Chambre de combustion à double paroi.
US5392596A (en) * 1993-12-21 1995-02-28 Solar Turbines Incorporated Combustor assembly construction
DE69421896T2 (de) * 1993-12-22 2000-05-31 Siemens Westinghouse Power Umleitungsventil für die Brennkammer einer Gasturbine
US5509702A (en) * 1994-08-23 1996-04-23 Eg&G Pressure Science, Inc. Low distortion pipe coupling device
GB2293232B (en) * 1994-09-15 1998-05-20 Rolls Royce Plc A combustion chamber assembly
US5645303A (en) * 1994-10-27 1997-07-08 Eg&G Pressure Science, Inc. Compact pipe coupling device
DE19627841A1 (de) * 1995-08-14 1997-02-20 Heinrich Fend Vorrichtung zum Gegeneinanderpressen von zwei Flanschen einer Rohrverbindung
DE19547172A1 (de) * 1995-12-16 1997-06-19 Mtu Muenchen Gmbh Flanschverbindung mit konischen Spannflächen
US5873611A (en) * 1997-03-10 1999-02-23 Eg&G Pressure Science, Inc. Pipe clamping device
US5868442A (en) * 1997-07-07 1999-02-09 Lin; Yen-Tseng Pipe joint fixing ring
US6098397A (en) * 1998-06-08 2000-08-08 Caterpillar Inc. Combustor for a low-emissions gas turbine engine
NO306917B1 (no) * 1998-07-13 2000-01-10 Abb Offshore Technology As Leddet klammerkopling
DE60135436D1 (de) * 2001-01-09 2008-10-02 Mitsubishi Heavy Ind Ltd Gasturbinenbrennkammer
US6886343B2 (en) * 2003-01-15 2005-05-03 General Electric Company Methods and apparatus for controlling engine clearance closures

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3814549A (en) * 1972-11-14 1974-06-04 Avco Corp Gas turbine engine with power shaft damper
JPS60200022A (ja) * 1984-03-23 1985-10-09 Hitachi Ltd ガスタ−ビンの燃焼器の共振防止装置
DE3539903A1 (de) * 1985-11-11 1987-05-14 Kloeckner Humboldt Deutz Ag Gasturbine mit einem keramischen laufrad
EP0509801A1 (fr) * 1991-04-16 1992-10-21 General Electric Company Capot amorti pour une chambre de combustion
DE4339094A1 (de) 1993-11-16 1995-05-18 Abb Management Ag Verfahren zur Dämpfung von thermoakustischen Schwingungen sowie Vorrichtung zur Durchführung des Verfahrens
DE19711337A1 (de) * 1997-03-18 1998-09-24 Bmw Rolls Royce Gmbh Verfahren zum Spitzenschleifen von in einem Stator- und Maschinengehäuse eingebauten Statorschaufeln einer Axial-Strömungsmaschine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 010, no. 051 (M - 457) 28 February 1986 (1986-02-28) *

Also Published As

Publication number Publication date
EP1327107A1 (fr) 2003-07-16
WO2002033323A1 (fr) 2002-04-25
JP2004511752A (ja) 2004-04-15
US6988366B2 (en) 2006-01-24
US20040025514A1 (en) 2004-02-12

Similar Documents

Publication Publication Date Title
DE3325291C2 (de) Rotorbaugruppe
EP2011965B1 (fr) Dispositif et procédé pour serrer des disques de rotor portant des aubes d'un moteur à réaction
EP1738112B1 (fr) Moteur de fusée avec amortissement de vibrations de la chambre de combustion au moyen de resonateurs
DE2258719A1 (de) Gasturbine
EP2660499A2 (fr) Bride de fixation
EP2042702B1 (fr) Dispositif d'amortissement
EP2395214A1 (fr) Collecteur de gaz d'échappement pour turbomachine et procédé de production dudit collecteur
EP2500648B1 (fr) Chambre de combustion de turbines à gaz
CH703661A2 (de) Flammrohrdeckelbaugruppe mit Stützstäben zum Einstellen der Frequenz von einer freitragenden Kraftstoffdüse.
DE102010037162A1 (de) Dämpfungselement für Entkopplungselemente, insbesondere für Membranbälge
DE102009001913A1 (de) Injektor
EP2363643A1 (fr) Elément de bouclier thermique
EP3063428B1 (fr) Palier
EP1745245A1 (fr) Chambre de combustion pour une turbine a gaz
EP2852735B1 (fr) Turbine à gaz
DE102016201646A1 (de) Metalldichtung
EP2980437A1 (fr) Système de fixation antivibratile
EP3155271A1 (fr) Étrier de couplage comprenant un mat en fil métallique comme élément amortisseur
DE102009003525A1 (de) Brennkammerbrennstoffdüsenaufbau
EP3091188B1 (fr) Turbomachine dotée d'un dispositif d'étanchéité
EP1199521A1 (fr) Turbine à gaz et procédé pour l'amortissement de vibrations d' une chambre de combustion annulaire de turbine à gaz
EP2462379B1 (fr) Stabilisation de la flamme d'un brûleur
DE60224761T2 (de) Balgartiges Überschlagrohr
EP1624251B1 (fr) Dispositif pour atténuer les oscillations acoustiques dans les chambres combustion avec fréquence de résonance ajustable
EP0866933B1 (fr) Ensemble piston-cylindre

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 CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

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: 20021025