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, the present invention is directed towards a premixer assembly for a gas turbine combustor, where the premixer assembly is secured together by a plurality of removable fasteners. As a result, the premixer assembly enhances combustor performance and increases component life through improved assembly and disassembly techniques and improved cooling configurations.
• 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.
• One such combustion system comprises 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 a variety of factors including the operating parameters of the engine, performance requirements, and 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.
• prior combustion liners have been primarily or exclusively welded assemblies, thereby making it difficult for operators or repair facilities to easily access all of the features of the combustion liner to be repaired.
• prior combustor designs of similar structure were capable of operating approximately 8,000 hours prior to refurbishment or replacement.
• a novel and improved combustion liner for use in a gas turbine engine.
• the combustion liner 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 further comprises a premixer assembly which is removably fastened to the combustion liner.
• a premixer assembly for a gas turbine combustor comprising an inlet ring basket, a plurality of swirler assemblies each having a premix tube, premix swirler in the premix tube, and a first and second mounting block positioned along the premix tube, a dome plate and a plurality of fasteners, where lugs of the inlet ring basket are positioned between a mounting block of the swirler assembly and the dome plate such that the fasteners pass through the dome plate, openings in the lugs and a hole of the mounting block so as to assemble the premixer.
• a method of assembling a premixer for a gas turbine combustor is disclosed.
• a dome plate is provided having a plurality of dome mounting holes, an inlet ring basket having a plurality of lugs, and a plurality of swirler assemblies, each having at least one mounting block and hole therein.
• the swirler assemblies are then inserted into the inlet ring basket and loosely retained in the radial direction by the first mounting block.
• the dome plate is then placed into contact with the plurality of lugs and the swirler assemblies are then inserted into the dome plate.
• the mounting holes of the dome plate are aligned with corresponding openings in the lugs and holes in the mounting block.
• a removable fastener is then placed through the fastener opening of the dome plate, the opening in the lug, and the hole in the mounting block so as to secure the dome plate, lug (inlet ring basket) and mounting block (swirler assembly) together.
• an interface joint for coupling components of a premixer assembly comprises a lug of an inlet ring basket, a swirler assembly having a mounting block positioned along an outer wall of the premix tube of the swirler assembly, and a dome plate.
• One or more fasteners secure the lug, mounting block, and dome plate together.
• 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 in accordance with an embodiment of the present invention.
• FIG. 4 is a cross section view of a combustion liner taken through a pilot swirler 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 taken through the main swirler 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 perspective view of a main swirler portion of the combustion liner of FIG. 3 in accordance with an embodiment of the present invention.
• FIG. 9 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. 10 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. 11 is a detailed section view of the interface joint for the premixer assembly in accordance with an embodiment of the present invention.
• FIG. 12 is a flow diagram of the steps for assembling a premixer for a gas turbine combustor.
• a gas turbine engine 100 of the prior art is depicted in partial cross section.
• the gas turbine engine 100 generally comprises an outer casing 102, enveloping the main portions of the engine.
• a shaft 104 extends axially along an engine axis A-A and is coupled to a compressor 106 and 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 as it passes therethrough, thereby increasing the temperature and pressure of the air.
• 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.
• 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. 3-12 discloses a new and improved premixer assembly for a combustion liner of a gas turbine engine.
• a combustion liner 300 having a premixer assembly 330 is disclosed.
• the combustion liner 300 comprises a generally cylindrical liner body 302 having an inlet end 304, an outlet, or discharge end 306, and an axis B-B extending through the combustor.
• the combustion liner 300 is generally cylindrical in cross section, but it is understood that the combustion liner 300 can vary in shape, have tapered sections, or sections of varying diameter.
• the combustion liner 300 is generally fabricated from rolled sheet metal that is welded along an axial seam and can be formed or expanded into a modified cylindrical structure depending on the specific combustion geometry.
• the combustion liner 300 is preferably manufactured from a high temperature alloy, such as Haynes 230, capable of withstanding elevated combustor conditions upwards of approximately 1400 degrees Fahrenheit. Alternate materials can be used such as Hastelloy-X or Inconel.
• the combustion liner 300 further comprises an inlet ring basket 308 secured to the generally cylindrical body 302.
• the inlet ring basket 308, as depicted in FIG. 3-7, consists of a series of generally axially- oriented spindles 310 coupled to a forward ring 312 and extends forward from the inlet end 304 of the combustion liner 300.
• the forward ring 312 is positioned a distance from the combustion liner 300 in order to establish a mating location for a set of fuel nozzles (not shown) in order to position the fuel nozzles in the proper axial position within the combustor.
• the inlet ring basket 308 also comprises a plurality of lugs 309 located in an annular array about the inlet ring basket 308, with each of the lugs 309 having an opening 309A extending through the lug 309.
• the lugs 309 extend radially inward from the inlet ring basket 308 and are used in part for securing a premixer assembly 330, as discussed in more detail below.
• the lugs 309 can be fabricated separately and welded to the inlet ring basket 308 or cast as part of the inlet ring basket 308.
• the plurality of lugs 309 can be a fabricated component or a casting and is preferably made from a stainless steel material.
• the premixer assembly 330 also comprises a plurality of swirler assemblies 332, each swirler assembly 332 for receiving a fuel injector.
• the swirler assembly 332 comprises a premix tube 342 having an inlet end 342A and an opposing outlet end 342B, and a longitudinal axis C-C extending therethrough.
• the swirler assembly 332 also comprises a premix swirler 336 positioned within the premix tube 342 where the premix swirler 336 has a plurality of turning vanes 338 for imparting a swirl to a passing flow through the premix tube 342.
• the premix tube 342 is slightly conical, however, alternate shapes for the premix tube 342 are possible.
• the swirler assembly 332 also comprises two mounting blocks for securing the swirler assembly in a gas turbine combustor.
• a first mounting block 344 is positioned along an outer wall of the premix tube 342 proximate the inlet end 342A of the premix tube 342.
• the first mounting block 344 includes a plurality of first holes 348 located in an outer face 347 and oriented generally perpendicular to the longitudinal axis C-C of the premix tube 342, as shown in FIG. 8.
• the swirler assembly 332 also comprises a second mounting block 346 positioned along the outer wall of the premix tube 342 and spaced an axial distance from the first mounting block 344.
• the second mounting block 346 also has one or more second holes 356 extending through the second mounting block 346 in a direction generally perpendicular to the plurality of first holes 348.
• a plurality of fasteners 350 and 358 are used to secure the swirler assemblies
• Fasteners 350 are used to secure the swirler assemblies 332 to the inlet basket 308 via the first mounting block 344 where the fasteners 350 are oriented generally perpendicular to the longitudinal axis C-C of the swirler assemblies 332.
• Fasteners 358 are used to secure the swirler assemblies 332 to the inlet basket 308 via the second mounting block 346 where the fasteners 358 are oriented generally parallel to the longitudinal axis C-C of the swirler assemblies 332.
• the premixer assembly 330 also comprises a dome plate 334 spaced an axial distance from the second mounting block 346 of each of the swirler assemblies 332. As shown in FIGS. 9-11, the dome plate 334 is oriented generally parallel to the second mounting block 346 and the plurality of lugs 309. The dome plate 334 is positioned against a face of the lugs 309.
• the dome plate 334 which can be more clearly seen in FIGS. 10 and 11, is a generally cylindrical plate fabricated from a stainless steel. The exact thickness of the plate can vary, but is approximately 0.350 inches thick.
• the dome plate 334 also comprises a large opening 370 for each swirler assembly 332 to pass therethrough, a series of fastener openings 372 for each axial fastener 358 to pass through, and a plurality of cooling holes 374.
• 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 cooling holes 374 are oriented generally perpendicular to the dome plate 334 (the cooling holes 374 are generally parallel to the longitudinal axis C-C of the swirler assemblies 332).
• the cooling holes 374 could be oriented at a surface angle relative to the dome plate 334 as well as a compound angle in order to impart a swirl to the air passing through the dome plate 334 or to improve the cooling effectiveness through the dome plate 334.
• 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 plurality of lugs 309 of the inlet ring basket 308 are positioned axially between the mounting blocks 346 of the swirler assemblies 332 and the dome plate 334.
• a plurality of fasteners 358 pass through each of the fastener openings 372 in the dome plate 334, through the openings 309A in the lugs 309 and through a second hole 356 in the second mounting block 346.
• the main 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 main swirler assembly 332 to the mixing zone of the combustion liner 300. That is, the main swirler assemblies 332 are positioned so as to be adjacent to or slightly engaged in the tubes 352. In order to ensure that the main swirler assemblies 332 are in the proper radial position in the combustion liner and dome plate 334 and thereby maintain a desired radial clearance with the tubes 352, a plurality of stand offs 354 are located about the outer surface of the premix tubes 342.
• the present invention also provides an interface joint for coupling components of a premixer assembly 330.
• the interface joint 400 comprises a lug 309 of an inlet ring basket 308, where the lug 309 has an opening 309A extending through the thickness of the lug 309.
• the interface joint 400 also includes a swirler assembly 332 having a premix tube 342, a premix swirler 336 and a mounting block 346 having one or more holes 356 extending through the mounting block 346 in a direction parallel to the premix tube 342.
• a dome plate 334 also forms part of the interface joint 400.
• the dome plate 334 has a plurality of cooling holes 374, fastener openings 372, and larger opening 370 for receiving the swirler assemblies 332, as discussed above.
• the interface joint 400 also includes one or more removable fasteners 358 for securing the lug 309, mounting block 346, and dome plate 334 together. The fastener 358 draws the mounting block 346 and dome plate 334 towards the lug 309 of the inlet ring basket 308.
• the present invention also provides a method 1200 of assembling a premixer for the gas turbine combustor.
• the method comprises the step 1202 of providing the components of the premixer including a dome plate having a plurality of fastener openings, an inlet ring basket having a plurality of lugs where each lug has an opening extending therethrough, and a plurality of swirler assemblies having mounting blocks with holes contained therein.
• a step 1204 the swirler assemblies are inserted into the inlet ring basket and loosely affixed to the first mounting block. Then, in a step 1206, the dome plate is placed in contact with the plurality of lugs of the inlet ring basket and in a step 1208, the swirler assemblies are inserted into the cup openings, or large openings, of the dome plate 334. Then, in a step 1210, the fastener opening in the dome plate, the opening in the lug, and the opening in the mounting block of the swirler assembly are all aligned together.
• the swirler assembly has two mounting blocks, and for this embodiment, it is the second, or aft-most mounting block that is used this assembly process.
• a removable fastener is placed through the fastener opening in the dome plate, through the opening in the lug, and through the hole in the mounting block, as shown in FIG. 11.
• the removable fastener engages a series of threads in the hole of the mounting block so as to secure the dome plate, lug, and mounting block of a swirler assembly together.
• This process is repeated for each of the fastener openings in the dome plate, corresponding lugs and swirler assemblies such that the dome plate and swirler assemblies are then bolted to the inlet ring basket.

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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)

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Citations (3)

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• 2014
  • 2014-04-18 US US14/256,023 patent/US20140318139A1/en not_active Abandoned
  • 2014-04-18 US US14/256,022 patent/US20140318150A1/en not_active Abandoned
  • 2014-04-18 US US14/256,025 patent/US20140318140A1/en not_active Abandoned
  • 2014-04-24 CN CN201480023669.0A patent/CN105121963B/zh not_active Expired - Fee Related
  • 2014-04-24 WO PCT/EP2014/058338 patent/WO2014174012A1/en active Application Filing
  • 2014-04-24 JP JP2016509463A patent/JP2016516976A/ja active Pending
  • 2014-04-24 WO PCT/EP2014/058336 patent/WO2014174011A1/en active Application Filing
  • 2014-04-24 JP JP2016509465A patent/JP2017516007A/ja active Pending
  • 2014-04-24 MX MX2015014400A patent/MX2015014400A/es unknown
  • 2014-04-24 KR KR1020157033470A patent/KR20160023657A/ko not_active Application Discontinuation
  • 2014-04-24 WO PCT/EP2014/058334 patent/WO2014174009A1/en active Application Filing

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