WO2014174012A1 - Ensemble de pré-mélange et mécanisme permettant de modifier la fréquence propre d'une chambre de combustion de turbine à gaz - Google Patents

Ensemble de pré-mélange et mécanisme permettant de modifier la fréquence propre d'une chambre de combustion de turbine à gaz Download PDF

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Publication number
WO2014174012A1
WO2014174012A1 PCT/EP2014/058338 EP2014058338W WO2014174012A1 WO 2014174012 A1 WO2014174012 A1 WO 2014174012A1 EP 2014058338 W EP2014058338 W EP 2014058338W WO 2014174012 A1 WO2014174012 A1 WO 2014174012A1
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WO
WIPO (PCT)
Prior art keywords
assembly
dome plate
struts
pilot
plate
Prior art date
Application number
PCT/EP2014/058338
Other languages
English (en)
Inventor
Jeremy Metternich
Khalid Oumejjoud
Brian Richardson
Original Assignee
Alstom Techonology Ltd
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 Techonology Ltd filed Critical Alstom Techonology Ltd
Priority to JP2016509465A priority Critical patent/JP2017516007A/ja
Publication of WO2014174012A1 publication Critical patent/WO2014174012A1/fr

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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • 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
    • 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
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
    • 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
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49346—Rocket or jet device making

Definitions

  • the present invention generally relates to a gas turbine combustor. More specifically, embodiments of the present invention relate to an apparatus and method for altering the natural frequencies of the dome plate assembly for a gas turbine combustor.
  • a compressor having alternating stages of rotating and stationary airfoils is coupled to a turbine through an axial shaft, with the turbine also having alternating stages of rotating and stationary airfoils.
  • the compressor stages decrease in size in order to compress the air passing therethrough.
  • the compressed air is then supplied to one or more combustors, which mixes the air with fuel.
  • An ignition source proximate the one or more combustors ignite the mixture, forming hot combustion gases.
  • the expansion of the hot combustion gases drives the stages of a turbine, which is coupled to the compressor through an axial shaft.
  • the exhaust gases can then be used as a source of propulsion, to generate steam through a heat recovery steam generator, or in powerplant operations to turn a shaft coupled to a generator for producing electricity.
  • the combustion system of a gas turbine engine can take on a variety of configurations.
  • a combustion system for a gas turbine engine can comprise a single combustion chamber, a plurality of individual combustion chambers spaced about the axis of the engine, a plenum- type combustion system, or a variety of other combustion systems.
  • the exact combustor arrangement will vary depending on the engine geometry, performance requirements, and physical operating location.
  • a typical combustion system generally comprises at least a casing secured to the frame of the engine, a combustion liner secured within at least a part of the casing, and one or more fuel nozzles positioned within or adjacent to the combustion liner for injecting a fuel (gas, liquid, or both) into the combustion chamber.
  • the combustion system is in fluid communication with the engine. More specifically, the casing and liner arrangement provides a way for air from the compressor to enter the combustion system, where it mixes with fuel from the one or more fuel nozzles.
  • the fuel-air mixture is ignited by an ignition source, such as a spark igniter. Hot combustion gases travel through the combustion liner and often through one or more transition pieces and into the turbine.
  • the transition piece is essentially a duct having a geometry that changes from the shape of the combustor to the inlet of the turbine.
  • the combustion liner is at the center of combustor operations.
  • the combustion liner geometry is dictated by the operating parameters of the engine, performance requirements, or available geometry. While combustion liner geometries can vary, the combustion liner typically includes at least a portion for receiving fuel nozzles, for mixing fuel and air together and for containing the reaction when the fuel and air mixture is ignited.
  • Combustion liners of the prior art have met certain performance requirements, but have also exhibited various shortcomings. Combustion liners are subjected to various thermal conditions and as such must be able to withstand the high thermal and mechanical stresses of such operating conditions. By nature, the combustion liner has a series of natural operating frequencies.
  • the gas turbine engine and combustion system also have a natural frequency, and orders of the natural frequency (i.e. IE, 2E, 3E, etc.).
  • IE natural frequency
  • 2E 2E
  • 3E 3E
  • the component can become dynamically excited. If care is not taken to avoid the crossings of these frequencies, operating at these frequencies, or minimizing the time for the crossing, the component may experience excessive wear or failure as a result of the vibratory stress that occurs when operating at or near the natural frequency of the gas turbine engine or combustion system.
  • a novel and improved component for a combustion liner of a gas turbine engine is generally cylindrical in shape and has an inlet end and a discharge end, opposite the inlet end.
  • the combustion liner of the present invention comprises a premixer assembly capable of receiving a plurality of fuel nozzles.
  • the premixer assembly is designed so as to provide a way of altering its natural frequency.
  • a plate assembly for a gas turbine combustor comprising a dome plate, a pilot mixer assembly, a plurality of extension tabs extending from an outer wall of the pilot mixer assembly, and a plurality of radially extending struts secured to both the extension tabs and the dome plate.
  • a system is provided for altering the natural frequency of a premixer assembly.
  • the system comprises a generally circular dome plate, a pilot mixer having an outer wall portion, a plurality of extension tabs fixed at one end to the outer wall and extending through a pilot cone portion, and a plurality of struts extending between the extension tabs and the dome plate.
  • a method of altering the natural frequency of a premixer assembly comprises the steps of providing a dome plate, a pilot mixer assembly, a plurality of extension tabs, and a quantity of radially extending struts.
  • the quantity of radially extending struts are secured to the plurality of extension tabs and dome plate.
  • additional radially extending struts are secured to the plurality of extension tabs and dome plate upon a determination to increase stiffness of the dome plate. Altering the stiffness of the dome plate in turn alters its natural frequency such that its natural frequency is outside of the dynamic frequencies generated by the combustion system.
  • FIG. 1 is a partial cross section view of a gas turbine engine of the prior art in which a combustion system in accordance with an embodiment of the present invention is capable of being used;
  • FIG. 2 is a cross section view of a gas turbine combustor of the prior art capable of operating within the gas turbine engine of FIG. 1;
  • FIG. 3 is a perspective view of a combustion liner incorporating an embodiment of the present invention.
  • FIG. 4 is a cross section view of the combustion liner of FIG. 3 taken through a pilot mixer assembly in accordance with an embodiment of the present invention
  • FIG. 5 is an alternate view of the cross section of FIG. 4, in accordance with an embodiment of the present invention.
  • FIG. 6 is a cross section view of a combustion liner of FIG. 3 taken through the a swirler assembly and pilot mixer assembly in accordance with an embodiment of the present invention
  • FIG. 7 is an alternate view of the cross section of FIG. 6, in accordance with an embodiment of the present invention.
  • FIG. 8 is a detailed cross section view taken through the inlet portion of the combustion liner of FIG. 3 in accordance with an embodiment of the present invention.
  • FIG. 9 is a partial cross section view of the main swirler portion of the combustion liner in accordance with an embodiment of the present invention.
  • FIG. 10 is a perspective view of a pilot mixer assembly in accordance with an embodiment of the present invention.
  • FIG. 11 is cross section view of a portion of the pilot mixer assembly of FIG.
  • FIG. 12 is a perspective view of a plate assembly of a gas turbine combustor in accordance with an embodiment of the present invention
  • FIG. 13 is cross section view of the plate assembly of FIG. 12 in accordance with an embodiment of the present invention.
  • FIG. 14 is an alternate cross section view of the plate assembly of FIG. 12 in accordance with an embodiment of the present invention.
  • FIG. 15 is a flow diagram describing a method of altering the natural frequency of a premixer assembly in accordance with an embodiment of the present invention.
  • the gas turbine engine 100 generally comprises an outer casing 102, enveloping the main portions of the engine.
  • a shaft 104 extends axially along engine axis A- A and couples a compressor 106 to a turbine 108.
  • the compressor 106 receives air through inlet region 110 and directs the air through alternating rows of rotating and stationary airfoils of decreasing size in order to compress the air passing therethrough, thereby increasing air temperature and pressure.
  • the compressed air is then directed through one or more combustion systems 112 where fuel and air are mixed together and ignited to form hot combustion gases.
  • the hot combustion gases are then directed into the turbine 108 to pass through alternating rows of rotating and stationary airfoils of increasing size so as to expand the fluid and harness the energy from the combustion gases into mechanical work to drive the shaft 104.
  • the shaft 104 may also be coupled to a shaft of an electrical generator (not shown) for purposes of generating electricity.
  • FIG. 2 discloses a cross section of a combustor 200 of a gas turbine engine of the prior art.
  • this typical gas turbine combustor 200 comprises a casing 202, a cover 204, one or more fuel injectors 206, and a combustion liner 208.
  • a transition piece 210 connects the combustion liner 208 to an inlet of the turbine 212.
  • FIGS. 3-15 discloses a new and improved system and method for altering the natural frequency of a dome plate in a gas turbine combustor.
  • a combustion liner 300 in which the present invention operates, is disclosed and comprises a plate assembly 430.
  • the plate assembly 430 is part of a larger premixer assembly 330 and is shown in more detail in FIGS. 12-14.
  • the plate assembly 430 generally comprises a dome plate 334 having a central opening 432 contained therein, the central opening 432 passing through the thickness of the dome plate 334.
  • the dome plate 334 also comprises a plurality of openings 370 arranged in an annular array about the central opening 432.
  • the plurality of openings 370 are sized to contain swirler assemblies 332 for the premixer 330. However, for clarity, the swirler assemblies 332 have been removed from FIGS. 12-14.
  • the plurality of swirler assemblies 332 are oriented about the axis of the combustion liner and secured to a dome plate 334.
  • the main swirler assemblies 332, shown in more detail in cross section in FIG. 8, comprise a swirler body 336 comprising a plurality of turning vanes 338 secured to a center ring 340 and an outer sleeve 342.
  • the turning vanes 338 impart a swirl to a passing flow.
  • Secured to the outer sleeve 342 is a forward mounting block 344 and an aft mounting block 346.
  • the forward mounting block 344, aft mounting block 346, and fasteners 350 and 358 are used to secure the swirler assemblies 332 to the combustion liner 300.
  • the dome plate 334 further comprises a plurality of openings, or air holes, 374 extending through the thickness of the dome plate 334.
  • the cooling holes 374 are oriented generally perpendicular to the dome plate 334.
  • the cooling holes 374 could be oriented at a surface angle relative to the dome plate 334 as well as a compound angle.
  • the dome plate 334 includes numerous cooling holes 374 for directing a flow of compressed air into the combustion zone of the combustion liner 300.
  • the exact quantity, size, and shape of the cooling holes 374 can vary depending on the amount of compressed air to be directed through the dome plate 334 as well as to maintain a desired pressure drop into the combustion zone.
  • the cooling holes 374 are approximately 0.165" in diameter and the dome plate 334 includes over 200 cooling holes.
  • the exact size, quantity, and spacing of the cooling holes 374 in the dome plate 334 can vary depending on factors such as the amount of air to pass through the dome plate as well as the desired drop in pressure across the dome plate.
  • the swirler assemblies 332 are positioned so as to be in fluid communication with adjacent tubes 352, or hoovers, which pass the flow of fuel and air from the swirler assembly 332 to the mixing zone of the combustion liner 300. That is, the swirler assemblies 332 are positioned so as to be adjacent to or slightly engaged in the tubes 352.
  • the plate assembly 430 also comprises a pilot mixer assembly 440.
  • the pilot mixer assembly 440 while shown in the plate assembly 430 in FIGS. 12-14, is shown in detail in FIGS. 10 and 11.
  • the pilot mixer assembly 440 extends from the central opening 370 and has an outer wall 442, a center ring 444 located within the outer wall 442. Extending between the center ring 444 and the outer wall 442 are a plurality of s wirier vanes 446.
  • Located around a portion of the outer wall 442 is a pilot cone 448.
  • the pilot cone 448 is positioned radially outward of the outer wall 442, and tapers radially inward towards the central opening 370.
  • the pilot cone 448 then extends through the dome plate 334 and transitions into a divergent portion 448A.
  • the plate assembly 430 also comprises a plurality of extension tabs 450 extending from the outer wall of the pilot mixer assembly 440 and through the pilot cone 448.
  • the plurality of extending tabs 450 are secured to the outer wall 442 of the pilot mixer assembly 440.
  • the plurality of extending tabs can be secured to the outer wall 442 via a weld, braze or other acceptable joining process.
  • the plurality of extending tabs 450 can be integrally formed with the outer wall 442 of the pilot mixer assembly 440, as would be produced via a casting process.
  • the plate assembly 430 also comprises a plurality of radially extending struts
  • the plurality of struts 452, or stiffeners, are used to provide increased rigidity and support to the dome plate 334, thereby increasing the stiffness of the plate assembly 430, resulting in an increase in its natural frequency.
  • the struts 452 are oriented generally perpendicular to the dome plate 334 and are secured at one end to the plurality of extension tabs 450 and at an opposing end to the dome plate 334, as shown in FIGS. 12 and 13. More specifically, the radially extending struts 452 are secured to the extension tabs 450 and the dome plate 334 by a weld, braze or other acceptable securing means. As shown in FIGS.
  • the radially extending struts 452 are positioned between adjacent plurality of openings 370.
  • four struts 394 are used.
  • the number of struts could be increased to equal the number of main swirler assemblies 332, which in an embodiment of the present invention is eight.
  • the radially extending struts 452 are secured to the dome plate 334 at multiple locations, as shown in FIGS. 12 and 13.
  • the radially extending struts 452 are secured at a location radially inward, towards the central opening 370 and radially outward towards an outer edge of the dome plate 334. That is, the radially extending struts 452 have an interrupted surface 452A that is spaced a distance from the dome plate 334 in multiple locations.
  • the radially extending strut and extension tab configuration described herein is merely one such embodiment of a configuration to adjust the natural frequency of the dome plate 334.
  • the design described herein, where the extension tab 450 is secured to the radially extending strut 452, is one such embodiment that lends to ease of manufacturing, lower manufacturing costs, while providing a design that alters the natural frequency of the dome plate. It is conceivable that other configurations for the radially extending strut and extension tabs are possible.
  • the present invention also provides a system for altering the natural frequency of a premixer assembly, where the system comprises a generally circular dome plate 334 having a central opening 432, an upstream face 334A, an opposing downstream face 334B, and a plurality of cooling holes 374.
  • a pilot mixer assembly 440 is located within the central opening 432 where the pilot mixer assembly 440 has an outer wall 442 and a pilot cone 448 that surrounds a portion of the outer wall 442, as shown in FIGS. 10 and 11.
  • the system for stiffening the premixer assembly also comprises a plurality of extension tabs 450 extending from the outer wall 442 of the pilot mixer assembly 440 and through the pilot cone 448.
  • a plurality of struts 452 extend between the plurality of extension tabs 450 and the dome plate 334, as shown in FIGS. 12 and 13. More specifically, for the embodiment of the present invention shown in FIGS. 12 and 13, the struts 452 extend radially outward from some of the plurality of extension tabs 450 and are positioned in a way to provide a desired natural frequency to the generally circular plate assembly 430.
  • the plurality of struts 452 comprise an interrupted or recessed portion 452A located between regions where the struts are in contact and secured to the dome plate 334.
  • This recessed portion 452A provides a way by which cooling air can pass between adjacent swirler assemblies 332 in order to cool that portion of the dome plate 334.
  • the dome plate 334 includes multiple cooling holes 374 positioned under the recessed portion 452A of the struts 452.
  • the system for stiffening the premixer assembly also comprises an outer cone 460 that envelopes a portion of the pilot cone 448, and more specifically, the outer cone 460 envelopes the divergent portion 448 A of the pilot cone 448.
  • the outer cone 460 is spaced a distance from the pilot cone 448 so as to maintain a flow of cooling air between the outer cone 460 and the pilot cone 448 for cooling the pilot cone 448, including the divergent portion 448A.
  • the gap between divergent portion 448A and outer cone 460 can vary depending on operating conditions, but for the embodiment depicted in FIGS. 13 and 14, is approximately 0.055 inches.
  • the gap is maintained by way of dimpled portions in the outer cone 460 causing local contact with regions of the pilot cone 448 when the combustor is operating. In a non-operation, cold state, the dimpled portions in the outer cone 460 do not contact the pilot cone 448.
  • an outer cone similar to that disclosed herein was welded to a pilot cone causing the welded assembly to be overly constrained, resulting in high mechanical stresses and resulting in component cracking and failure.
  • the present invention also comprises a method 500 of altering natural frequency of a premixer assembly.
  • a dome plate and pilot mixer assembly are provided where the pilot mixer assembly has a plurality of extension tabs.
  • a quantity of radially extending struts are secured to a plurality of extension tabs.
  • additional radially extending tabs are secured to the dome plate and to additional extension tabs in order to increase the natural frequency of the dome plate.
  • one or more radially extending struts can be removed from the premixer assembly.

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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)
  • Testing Of Engines (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

L'invention concerne un système et un procédé permettant de modifier la fréquence propre d'une partie de plaque en dôme d'un ensemble de pré-mélange d'une chambre de combustion de turbine à gaz. L'ensemble plaque a une plaque en dôme avec un mélangeur pilote central et une pluralité de pattes d'extension s'étendant dans le sens radial vers l'extérieur en provenance du mélangeur pilote. Une pluralité d'entretoises s'étendant dans le sens radial sont assujetties sur les pattes d'extension afin de modifier la fréquence propre de la plaque en dôme.
PCT/EP2014/058338 2013-04-25 2014-04-24 Ensemble de pré-mélange et mécanisme permettant de modifier la fréquence propre d'une chambre de combustion de turbine à gaz WO2014174012A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2016509465A JP2017516007A (ja) 2013-04-25 2014-04-24 ガスタービン燃焼器の固有振動数を変化させる予混合器アセンブリ及び機構

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US201361815835P 2013-04-25 2013-04-25
US61/815,835 2013-04-25
US14/256,025 2014-04-18
US14/256,025 US20140318140A1 (en) 2013-04-25 2014-04-18 Premixer assembly and mechanism for altering natural frequency of a gas turbine combustor

Publications (1)

Publication Number Publication Date
WO2014174012A1 true WO2014174012A1 (fr) 2014-10-30

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Application Number Title Priority Date Filing Date
PCT/EP2014/058336 WO2014174011A1 (fr) 2013-04-25 2014-04-24 Ensemble de système à prémélange pour une chambre de combustion de turbine à gaz
PCT/EP2014/058338 WO2014174012A1 (fr) 2013-04-25 2014-04-24 Ensemble de pré-mélange et mécanisme permettant de modifier la fréquence propre d'une chambre de combustion de turbine à gaz
PCT/EP2014/058334 WO2014174009A1 (fr) 2013-04-25 2014-04-24 Ensemble coupelle de turbulence amovible pour une chemise de combustion

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PCT/EP2014/058336 WO2014174011A1 (fr) 2013-04-25 2014-04-24 Ensemble de système à prémélange pour une chambre de combustion de turbine à gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
PCT/EP2014/058334 WO2014174009A1 (fr) 2013-04-25 2014-04-24 Ensemble coupelle de turbulence amovible pour une chemise de combustion

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US (3) US20140318140A1 (fr)
JP (2) JP2017516007A (fr)
KR (1) KR20160023657A (fr)
CN (1) CN105121963B (fr)
MX (1) MX2015014400A (fr)
WO (3) WO2014174011A1 (fr)

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MX2015014400A (es) 2016-06-21
WO2014174011A1 (fr) 2014-10-30
JP2016516976A (ja) 2016-06-09
US20140318150A1 (en) 2014-10-30
KR20160023657A (ko) 2016-03-03
CN105121963A (zh) 2015-12-02
CN105121963B (zh) 2017-08-18
US20140318139A1 (en) 2014-10-30
JP2017516007A (ja) 2017-06-15
US20140318140A1 (en) 2014-10-30
WO2014174009A1 (fr) 2014-10-30

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