EP1865259A2 - Paroi de chambre de combustion de turbine à gaz pour une chambre de turbine à gaz à combustion pauvre - Google Patents

Paroi de chambre de combustion de turbine à gaz pour une chambre de turbine à gaz à combustion pauvre Download PDF

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Publication number
EP1865259A2
EP1865259A2 EP07109395A EP07109395A EP1865259A2 EP 1865259 A2 EP1865259 A2 EP 1865259A2 EP 07109395 A EP07109395 A EP 07109395A EP 07109395 A EP07109395 A EP 07109395A EP 1865259 A2 EP1865259 A2 EP 1865259A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
chamber wall
wall according
turbine 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Withdrawn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
EP07109395A
Other languages
German (de)
English (en)
Other versions
EP1865259A3 (fr
Inventor
Miklós Gerendás
Michael Ebel
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1865259A2 publication Critical patent/EP1865259A2/fr
Publication of EP1865259A3 publication Critical patent/EP1865259A3/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • the invention relates to a gas turbine combustor wall for a lean-burn gas turbine combustor.
  • the UK patent GB 2 309 296 describes a two-layer wall construction of a lean-burning gas turbine combustion chamber with an acoustically damping effect on high-frequency combustion chamber vibrations (indicated is a frequency band of 3 to 9 kHz) with simultaneous cooling of the combustion chamber wall. Both are achieved through the holes perpendicular through the wall.
  • the outer / cold combustion chamber wall generates the impingement cooling jets on the inner / hot wall, the holes through the inner / hot wall discharge the impingement cooling air into the combustion chamber and generate the damping effect.
  • the EP 0 576 435 B1 describes a combustion chamber with a two-layer, subdivided into chambers wall structure, all holes are arranged at a shallow angle to the surface and therefore no damping effect is generated.
  • film cooling with cooling rings and effusion cooling is possible in the single-layer case, as well as shingles mounted in the multi-layered case (with pins on the back or impact-cooled) or soldered or welded sheet metal structures (Transply, Lamilloy).
  • the cooling air is thereby provided by holes or slots in the cooling rings, which generate the cooling film with or without deflection.
  • These openings may be substantially radially mounted to realize delivery of the cooling air based on the static pressure of the cooling air supply, or substantially axially, to realize a supply by means of the total pressure of the air supply, or by both arrangement options simultaneously.
  • a lip on the cooling ring is used, on which the air jets impact and are deflected in the axial direction.
  • the axial and radial openings may be arranged in one or more rows. With several rows of openings in the axial direction, these are radially staggered and the lip is usually omitted.
  • a useful damping effect can only be achieved through openings that are mounted substantially perpendicularly through the combustion chamber wall.
  • the best effect for suppressing combustion vibrations is achieved by dampers connected to the combustion chamber in the area of maximum heat release.
  • the entire combustion chamber wall must contain openings, because areas without cooling openings would be uncooled. Even in the case of impingement cooling, the entire rear side of the area intended for cooling must be accessible, which does not guarantee the installation of dampers in the area of high heat release.
  • the invention has for its object to provide a gas turbine combustor wall of the type mentioned, which has both a good cooling and good damping with simple expansion and simple, cost manufacturability.
  • dampers can be realized single-walled by the arrangement of openings substantially (plus minus 30 degrees to the surface normal) perpendicularly through the combustion chamber wall between the cooling rings, in which case the space between the combustion chamber and the combustion chamber housing acts as a damper volume.
  • the damper can also be designed as a two-walled construction, if the air consumption of the single-walled construction is perceived as too high.
  • a damper volume is separated by another housing on the outside of the combustion chamber, wherein the axial extent of the damper housing is limited by the distance of the cooling rings.
  • the damper housing may be fixedly connected to the combustion chamber wall (e.g., bolted or welded to flanges) on either side, or only on one side (upstream or downstream end), with or without additional sealing on the sliding seat of the movable separation point.
  • the flow of air through the damper is adjusted through holes in the damper housing which restrict compressor discharge air to the desired pressure in the damper.
  • the damper volume communicates with the hot gas flow through substantially vertical damper ports through which the air flows slowly.
  • the two-walled damper conveniently a plurality of openings in the Combustion chamber wall distributed in the region between the cooling rings in the axial and lateral directions. It may be advantageous to use different distances and cross-sectional areas of the openings on the circumference. The change in the distances and cross-sectional areas of the openings can be continuous or erratic. With regular spacing, one can only change the cross-sectional area of the openings or vary the distance with a constant cross-sectional area, or both.
  • the openings in the combustion chamber wall may be cylindrical bores or non-cylindrical openings.
  • the non-cylindrical openings may contain a continuous (linear or non-linear) cross-sectional change or an abrupt, for example, from a small diameter to a larger diameter or vice versa.
  • the cross section of the openings themselves need not be round. It can also be oval, rectangular or star, shamrock or flower-shaped.
  • the throttle bores in the damper housing are usually round and without cross-sectional change, but may also vary in distance and diameter within the bore field.
  • the damper volume can be completely empty in the double-walled structure and form a circumferential space. It may be divided by partitions in the axial and / or lateral direction in chambers with three or more corners or the damper housing is not a circumferential structure, but extends in the circumferential direction only over a certain section.
  • the circulating volume or the individual chambers may be filled all or partly with an air-permeable material.
  • the material may be a felt or web of fibers of a heat-resistant material, such as metal. Glass or ceramic or an open-pored sponge made of metal, ceramic or other heat-resistant material.
  • the kind and the Properties of the filling material may be the same throughout the damper volume or all chambers or vary.
  • the application can be limited to the wall segments located near the maximum heat release zone or centrally between the burner and turbine vane (part between two cooling rings) where the effect is greatest.
  • the dimensions of the damper and thus the frequency band damped by it can differ between the inner and the outer combustion chamber wall, as well between upstream and downstream of cooling rings limited portions of the combustion chamber and also in the circumferential direction within a combustion chamber segment.
  • combustion chamber wall can be made of ceramic or CMC (ceramic matrix composite) instead of metal, as well as the damper housing, these parts need not be made of the same material.
  • effusion cooling holes at a shallow angle to the surface e.g., between the damping holes, which pass through the wall substantially normal (at 90 degrees angle) may still be present. 20-30 degrees, which are fed by the same pressure level as the damper openings.
  • effusion cooling holes at a shallow angle to the surface e.g., between the damping holes, which pass through the wall substantially normal (at 90 degrees angle) may still be present. 20-30 degrees, which are fed by the same pressure level as the damper openings.
  • Outside of the film cooling segments with acoustic dampers can also be improved by the attachment of effusion holes between the cooling rings or at the end of the combustion chamber to the turbine out at a shallow angle to the surface cooling.
  • a ceramic thermal barrier coating between the cooling rings (combustion chamber segments) can be applied.
  • the damping holes no longer have to produce cooling effect (for which they are suitable only to a very limited extent), the cross section of the damping holes can be matched to the combustion chamber wall thickness and the damper volume or the distance of the combustion chamber wall to the combustion chamber housing or the damper housing, which also at frequencies below one kHz results in a significant attenuation effect.
  • the two-layer structure there are further possibilities for tuning through the pressure in the damper housing and thus by controlling the flow velocity in the damper bores.
  • acoustic dampers with acoustically optimized Throughput can be used, which are tuned to the attenuation of frequencies below 1 kHz, for example, the frequency range of 300 to 1000 Hz.
  • a subdivision of the damper gap in the axial and lateral direction serves to prevent compensating flows in the damper housing.
  • the introduction of air-permeable material into the damping volume can increase the damping.
  • FIG. 1 shows, in a schematic representation, a cross-section of a gas turbine combustion chamber according to the prior art.
  • compressor outlet blades 1 and a combustion chamber outer housing 2 and a combustion chamber inner housing 3 are shown schematically.
  • the reference numeral 4 denotes a burner with arm and head (diffusion flame).
  • a combustion chamber head 5 is associated with a combustion chamber wall 6 with cooling rings 6a.
  • Turbine inlet blades are designated by the reference numeral 7.
  • FIG. 2 shows a schematic structure of a damper in detail view according to the prior art, wherein a combustion chamber wall 10 is provided with steaming and cooling holes 11 which each extend perpendicular to the combustion chamber wall 10.
  • the compressor discharge air is indicated at 12, while flame and flue gas from the lean burn burner are indicated by the arrow 13.
  • a steam space 14 is provided between damper wall 9 and combustion chamber wall 10. Cooling air is introduced into these through inflow bores 8.
  • the individual combustion chamber segments which form a single-layer combustion chamber wall, with respect to the longitudinal axis, slightly inclined, so that there is a shingle-like, staggered structure.
  • substantially axial cooling holes 16 By substantially axial cooling holes 16, a laminar inflow of compressor discharge air 12 takes place.
  • essentially radial cooling holes 17 can be provided.
  • the respective upstream combustion chamber segment comprises a lip 18 on the cooling ring.
  • damper volume is formed by the distance 19 b to the housing 2 or 3 .
  • FIG. 4 differs in that no radial cooling holes 17 are provided, but several rows of substantially axial cooling holes are arranged radially staggered.
  • non-cylindrical damping openings are shown, which can have very different cross-sections, both over their axial length and overall.
  • FIGS. 7 to 9 each show a two-layer structure of the combustion chamber wall.
  • a damper housing 20 is additionally provided, which encloses a steamer volume 21.
  • the damper volume 21 may be divided in the circumferential direction and / or be filled with additional material (see above).
  • the embodiments of FIGS. 8 and 9 each show that one end of the damper housing is fixedly connected (22), while the other region has a displaceable or displaceable separation point 23. As a result, thermal length expansions can be compensated.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07109395.9A 2006-06-09 2007-06-01 Paroi de chambre de combustion de turbine à gaz pour une chambre de turbine à gaz à combustion pauvre Withdrawn EP1865259A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006026969A DE102006026969A1 (de) 2006-06-09 2006-06-09 Gasturbinenbrennkammerwand für eine mager-brennende Gasturbinenbrennkammer

Publications (2)

Publication Number Publication Date
EP1865259A2 true EP1865259A2 (fr) 2007-12-12
EP1865259A3 EP1865259A3 (fr) 2014-08-06

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EP07109395.9A Withdrawn EP1865259A3 (fr) 2006-06-09 2007-06-01 Paroi de chambre de combustion de turbine à gaz pour une chambre de turbine à gaz à combustion pauvre

Country Status (3)

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US (1) US7926278B2 (fr)
EP (1) EP1865259A3 (fr)
DE (1) DE102006026969A1 (fr)

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EP2299177A1 (fr) * 2009-09-21 2011-03-23 Alstom Technology Ltd Chambre de combustion de turbine à gaz
EP2559942A1 (fr) * 2011-08-19 2013-02-20 Rolls-Royce Deutschland Ltd & Co KG Tête de chambre de combustion d'une turbine à gaz dotée d'un refroidissement et d'un amortissement
WO2013029981A1 (fr) * 2011-09-01 2013-03-07 Siemens Aktiengesellschaft Chambre de combustion pour une installation de turbine à gaz
CN103807844A (zh) * 2014-01-24 2014-05-21 华东理工大学 一种与高温气体接触的金属壁冷却方法
CN104676649A (zh) * 2015-02-05 2015-06-03 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种阻尼热声振荡声学火焰筒
EP2913589A1 (fr) * 2014-02-28 2015-09-02 Alstom Technology Ltd Dispositif d'amortissement acoustique pour chambres à écoulement rasant
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EP2299177A1 (fr) * 2009-09-21 2011-03-23 Alstom Technology Ltd Chambre de combustion de turbine à gaz
WO2011032959A1 (fr) * 2009-09-21 2011-03-24 Alstom Technology Ltd Chambre de combustion d'une turbine à gaz
US8635874B2 (en) 2009-09-21 2014-01-28 Alstom Technology Ltd Gas turbine combustor including an acoustic damper device
EP2559942A1 (fr) * 2011-08-19 2013-02-20 Rolls-Royce Deutschland Ltd & Co KG Tête de chambre de combustion d'une turbine à gaz dotée d'un refroidissement et d'un amortissement
WO2013029981A1 (fr) * 2011-09-01 2013-03-07 Siemens Aktiengesellschaft Chambre de combustion pour une installation de turbine à gaz
CN103765105A (zh) * 2011-09-01 2014-04-30 西门子公司 用于燃气轮机设备的燃烧室
CN103807844A (zh) * 2014-01-24 2014-05-21 华东理工大学 一种与高温气体接触的金属壁冷却方法
CN103807844B (zh) * 2014-01-24 2016-01-20 华东理工大学 一种与高温气体接触的金属壁冷却方法
EP2913589A1 (fr) * 2014-02-28 2015-09-02 Alstom Technology Ltd Dispositif d'amortissement acoustique pour chambres à écoulement rasant
CN104879781A (zh) * 2014-02-28 2015-09-02 阿尔斯通技术有限公司 用于具有切向流的室的声阻尼装置
US9429042B2 (en) 2014-02-28 2016-08-30 General Electric Technology Gmbh Acoustic damping device for chambers with grazing flow
CN104879781B (zh) * 2014-02-28 2019-08-13 安萨尔多能源瑞士股份公司 用于具有切向流的室的声阻尼装置
CN104676649A (zh) * 2015-02-05 2015-06-03 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种阻尼热声振荡声学火焰筒
EP3133242A1 (fr) * 2015-08-17 2017-02-22 General Electric Company Collecteur avec plaque d'impact pour le réglage thermique d'un composant de turbine
US9995151B2 (en) 2015-08-17 2018-06-12 General Electric Company Article and manifold for thermal adjustment of a turbine component

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US20070283700A1 (en) 2007-12-13
US7926278B2 (en) 2011-04-19
DE102006026969A1 (de) 2007-12-13
EP1865259A3 (fr) 2014-08-06

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