CN108278634B - Gas turbine and combustor thereof - Google Patents
Gas turbine and combustor thereofDownload PDFInfo
- Publication number
- CN108278634B CN108278634BCN201711279240.XACN201711279240ACN108278634BCN 108278634 BCN108278634 BCN 108278634BCN 201711279240 ACN201711279240 ACN 201711279240ACN 108278634 BCN108278634 BCN 108278634B
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- gas turbine
- fuel injection
- flame
- air
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- 238000002347injectionMethods0.000claimsabstractdescription175
- 239000007924injectionSubstances0.000claimsabstractdescription175
- 239000000203mixtureSubstances0.000claimsabstractdescription13
- 230000002093peripheral effectEffects0.000claimsdescription17
- NJPPVKZQTLUDBO-UHFFFAOYSA-NnovaluronChemical compoundC1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1FNJPPVKZQTLUDBO-UHFFFAOYSA-N0.000claims1
- 238000005507sprayingMethods0.000abstractdescription6
- 230000000694effectsEffects0.000abstractdescription5
- 239000007789gasSubstances0.000description28
- 238000002485combustion reactionMethods0.000description10
- 238000001816coolingMethods0.000description7
- 230000008602contractionEffects0.000description5
- MWUXSHHQAYIFBG-UHFFFAOYSA-Nnitrogen oxideInorganic materialsO=[N]MWUXSHHQAYIFBG-UHFFFAOYSA-N0.000description3
- 238000007599dischargingMethods0.000description2
- 238000006073displacement reactionMethods0.000description2
- 239000000463materialSubstances0.000description2
- 230000004075alterationEffects0.000description1
- 230000009286beneficial effectEffects0.000description1
- 239000000567combustion gasSubstances0.000description1
- 230000003247decreasing effectEffects0.000description1
- 238000010586diagramMethods0.000description1
- 239000012530fluidSubstances0.000description1
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a combustor of a gas turbine and a gas turbine with the combustor.
Background
In the thermodynamic cycle of a gas turbine, the higher the temperature of the combustion gases in the combustion chamber, the more beneficial the efficiency and power increase. However, excess air readily forms nitrogen oxides NO at high temperaturesXIn order to reduce the thermal NOXThe maximum temperature in the combustion chamber needs to be reduced. Thus, on the one hand, the temperature needs to be increased to meet the power demand, and on the other hand, the maximum temperature needs to be decreased to meet the emission requirements.
In the related art, staged combustion is employed in the combustion chamber of a gas turbine, and one type of staged combustion used in a gas turbine is "late lean injection", in which a late lean injector is located downstream of a main combustion nozzle, and fuel is added at this downstream location, thereby increasing power while avoiding excessive temperatures in the combustion chamber. However, current late lean injectors carry excessive thermal structural loads and also risk leakage; and the fuel inlet is arranged on the annular fuel channel, and the mixing of the fuel and the air is not ideal.
Disclosure of Invention
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art.
To this end, one aspect of the present invention is directed to a combustor for a gas turbine that improves the mixing of fuel and air.
The invention also provides a gas turbine with the combustor.
A combustor of a gas turbine according to an embodiment of the first aspect of the invention includes a liner; the guide bush is sleeved on the flame tube, and an annular channel is formed between the guide bush and the flame tube; the outer end of the rear flame fuel injection pipe is fixed on the guide bush, the inner end of the rear flame fuel injection pipe extends to the flame tube, an air hole plate and an injection plate are sequentially arranged in the rear flame fuel injection pipe along the axial direction of the rear flame fuel injection pipe, a plurality of air holes are formed in the air hole plate, a plurality of spraying holes are formed in the injection plate, and the injection plate is used for mixing fuel and air into a mixture and spraying the mixture into the rear flame fuel injection pipe through the spraying holes.
According to the combustor of the gas turbine provided by the embodiment of the invention, the air hole plate and the injection plate are sequentially arranged in the back flame fuel injection pipe along the axial direction of the back flame fuel injection pipe, so that the mixing effect of fuel and air is improved.
In some embodiments, the air hole plate has an air inlet side surface and an air outlet side surface, and the air outlet side surface is provided with a plurality of distribution grooves correspondingly communicated with the air inlet holes.
In some embodiments, the distribution slot is an arcuate slot extending along a circumference of the air aperture plate.
In some embodiments, the air inlet holes are arranged in a plurality of circles evenly spaced in a radial direction of the air hole plate, and the air inlet holes on each circle are arrayed and evenly spaced in a circumferential direction of the air hole plate.
In some embodiments, the circumferential length of the distribution groove communicating with the air intake holes on the same ring is the same.
In some embodiments, in a radial direction of the air hole plate, a circumferential length of a distribution groove located on an inner side is smaller than a circumferential length of a distribution groove located on an outer side, of two adjacent distribution grooves.
In some embodiments, the air inlet holes are arranged in four circles evenly spaced in the radial direction of the air hole plate, each circle having four air inlet holes evenly spaced in the circumferential direction of the air hole plate, so that all the air inlet holes of the air hole plate are divided into four groups, the air inlet holes in each group are aligned in the radial direction of the air hole plate, and the circumferential length of the distribution groove communicating with the air inlet holes in each group is gradually reduced from the outside to the inside in the radial direction of the air hole plate.
In some embodiments, the injection plate has an inlet side surface with a mixing cavity groove thereon and an outlet side surface with a fuel inlet on a side wall of the mixing cavity groove, and the spouting holes extend from a bottom surface of the mixing cavity groove to the outlet side surface of the injection plate.
In some embodiments, the mixing cavity groove is a plurality of grooves spaced along the circumference of the injection plate, and a plurality of the ejection holes are formed in the bottom surface of each of the mixing cavity grooves.
In some embodiments, the number of the mixing chamber slots is four, the injection plate has a square protrusion at the center of the inlet side surface, adjacent mixing chamber slots are spaced apart by a generally fan-shaped protrusion, the inner end of each fan-shaped protrusion meets a corresponding corner of the square protrusion, an arc-shaped protrusion extending in the circumferential direction of the injection plate is connected to one side of the outer end of each fan-shaped protrusion, and the other end of the arc-shaped protrusion is spaced apart from the adjacent fan-shaped protrusion to form the fuel inlet.
In some embodiments, a rectifying plate is arranged between the air hole plate and the injection plate, and a plurality of rectifying holes are arranged on the rectifying plate.
In some embodiments, the air hole plate and the rectifying plate directly abut against each other in an axial direction of the after-flame fuel injection pipe, and the rectifying plate and the injection plate directly abut against each other in the axial direction of the after-flame fuel injection pipe.
In some embodiments, the combustor of the gas turbine further comprises a floating collar mounted on the flame tube and expandable and contractible generally radially of the floating collar, the inner end of the post-flame fuel injection tube extending through the floating collar to the flame tube.
In some embodiments, the flame tube is provided with a mounting hole in which a support is mounted, and the floating collar is mounted on and movable relative to the support.
In some embodiments, the mount comprises a base and an annular cover plate, the base comprising a barrel, a flange extending radially outwardly of the barrel from an upper end periphery of the barrel, and a weir extending axially outwardly of the barrel from an outer periphery of the flange, a lower end of the barrel being mounted in the mounting hole, the flange being spaced from the liner, the outer periphery of the annular cover plate being connected to the weir such that the annular cover plate, the weir and the flange form an annular groove, a portion of the floating collar being movably fitted in the annular groove.
In some embodiments, the floating collar includes a cylindrical section and a peripheral portion extending radially outward from an inner end of the cylindrical section, the peripheral portion movably fitting within the annular groove, the cylindrical section fitting over and tightly fitting the post-flame fuel injection tube.
In some embodiments, the outer end of the post-flame fuel injection tube has a flange by which the post-flame fuel injection tube is mounted on the flow guide sleeve.
In some embodiments, the flow guide bush is provided with a fixing hole, an outer ring is installed in the fixing hole, the outer ring is provided with an annular outer groove which is opened along the radial direction of the outer ring outwards and an annular inner groove which is opened along the radial direction of the outer ring inwards, and the annular outer side is communicated with the annular outer groove through a communication hole; the outer ring is internally provided with an inner ring, the inner ring is provided with an inner ring annular groove which is radially opened outwards along the inner ring, the inner ring annular groove is butted with the annular inner groove to form an annular fuel channel, the flange is arranged on the outer ring, the rear flame fuel injection pipe penetrates through the inner ring, and the annular fuel channel is communicated with the fuel hole on the rear flame fuel injection pipe through a fuel through hole on the inner ring.
In some embodiments, a swirler is disposed within the post-flame fuel injection tube.
A gas turbine according to an embodiment of the second aspect of the invention comprises the combustor of the above-described embodiment.
Drawings
Fig. 1 is an overall structural schematic diagram of a combustor of a gas turbine according to an embodiment of the present invention.
FIG. 2 is a cross-sectional view at a post-flame fuel injection pipe of a combustor of a gas turbine according to an embodiment of the invention.
FIG. 3 is a cross-sectional view at a post-flame fuel injection tube of a combustor of a gas turbine according to an embodiment of the invention.
FIG. 4 is an inlet side schematic view of an air hole plate of a combustor of a gas turbine according to an embodiment of the present invention.
FIG. 5 is a schematic view of an air outlet side of an air hole plate of a combustor of a gas turbine according to an embodiment of the present invention.
FIG. 6 is a schematic view of an injection plate of a combustor of a gas turbine according to an embodiment of the present invention.
FIG. 7 is a schematic view of a fairing of a combustor of a gas turbine according to an embodiment of the invention.
Reference numerals:
theflame tube 1, theguide bush 2, thefloating collar 3, thetube portion 31, thestraight tube portion 311, theflare portion 312, theperipheral edge portion 32, the after-flamefuel injection tube 4, theair hole plate 5, theinlet side surface 51, theoutlet side surface 52, thesupport 6, thebase 61, thetube body 611, theflange 612, the cofferdam 613, theannular cover plate 62, theinjection plate 7, themixing chamber groove 71, thefuel inlet 72, thesquare protrusion 73, the fan-shaped protrusion 74, the arc-shaped protrusion 75, the cooling hole 8, the flange 9, theouter ring 10, the annularouter groove 101, the annularinner groove 102, thecommunication hole 103, theinner ring 11, the inner ringannular groove 111, theannular fuel passage 12, the fuel throughhole 13, theannular passage 14, theannular groove 15, thefuel passage 16, thefuel cover plate 17, theswirler 18, theair inlet hole 19, thespouting holes 20, thedistribution groove 21.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
As shown in fig. 1 to 7, a combustor of a gas turbine according to an embodiment of the present invention includes acombustor basket 1, aflow guide liner 2, and a rear flamefuel injection pipe 4, and a front end (left end shown in fig. 1) of thecombustor basket 1 is provided with a primary fuel nozzle for injecting fuel into thecombustor basket 1.
Theguide bush 2 is sleeved on theflame tube 1, and anannular channel 14 is formed between theguide bush 2 and theflame tube 1. The high-pressure air compressed by the compressor enters the front end of theflame tube 1 through theannular channel 14, and is mixed and combusted with the fuel sprayed by the primary fuel nozzle in theflame tube 1.
The outer end of the rear flamefuel injection pipe 4 is fixed on theguide sleeve 2, and the inner end of the rear flamefuel injection pipe 4 extends to theflame tube 1. Specifically, the opening of the inner end of the after-flamefuel injection pipe 4 is flush with the inner wall surface of thecombustor basket 1. It can be understood that the after-flamefuel injection pipe 4 has a plurality of fuel holes suitable for fuel to enter, and the plurality of fuel holes are uniformly spaced along the circumferential direction of the after-flamefuel injection pipe 4. Here, "outer end" means an end adjacent to theflow guide sleeve 2, i.e., the upper end shown in fig. 2; "inner end" means the end adjacent to theliner 1, i.e. the lower end as shown in fig. 2.
The post-flamefuel injection tubes 4 are adapted to inject a mixture of fuel and air into the working fluid downstream (to the right as viewed in FIG. 1) of the primary fuel nozzles. The after-flamefuel injection pipe 4 is more specifically used to inject a mixture of fuel and air into the rear end (right end as viewed in fig. 1) of the primary combustion chamber defined by thecombustor basket 1. The post-flamefuel injection pipe 4 realizes mixing and combustion of fuel and air at the downstream of the primary combustion area to improve NOXAnd (5) discharging.
Anair hole plate 5 and aninjection plate 7 are sequentially arranged in the rear flamefuel injection pipe 4 along the axial direction, a plurality ofair inlet holes 19 are formed in theair hole plate 5, air enters a space between theair hole plate 5 and theinjection plate 7 in the rear flamefuel injection pipe 4 from the outer end of theair hole plate 5 through theair inlet holes 19, meanwhile, fuel enters the space between theair hole plate 5 and theinjection plate 7 through fuel holes in the rear flamefuel injection pipe 4 and is mixed with the air in the space between theair hole plate 5 and theinjection plate 7. Theinjection plate 7 is provided with a plurality ofinjection holes 20, and theinjection plate 7 injects a mixture of fuel and air into the post-flamefuel injection pipe 4 through theinjection holes 20.
It can be understood that the external air enters the space between theair hole plate 5 and theinjection plate 7 in the post-flamefuel injection pipe 4 through theair hole plate 5, meanwhile, the fuel enters the space between theair hole plate 5 and theinjection plate 7 through the fuel holes on the post-flamefuel injection pipe 4, the fuel and the air are mixed in the space and then injected into the post-flamefuel injection pipe 4 through theinjection holes 20 on theinjection plate 7, and the injected fuel and air mixture is further mixed in the post-flamefuel injection pipe 4 and injected into theflame tube 1 through the post-flamefuel injection pipe 4.
According to the combustor of the gas turbine of the embodiment of the invention, the air hole plate and the injection plate are sequentially arranged in the axial direction of the back flame fuel injection pipe, so that the fuel and the air are firstly premixed in the space between theair hole plate 5 and theinjection plate 7 in the back flamefuel injection pipe 4, and the mixing effect of the fuel and the air is improved.
In some embodiments, as shown in fig. 2, 4 and 5, theair hole plate 5 has an air inlet side surface 51 (an upper surface shown in fig. 2 and 3) and an air outlet side surface 52 (a lower surface shown in fig. 2 and 3), and the airoutlet side surface 52 is provided with a plurality ofdistribution grooves 21 correspondingly communicating with theair inlet holes 19. In other words, adistribution groove 21 communicating with eachair inlet hole 19 is formed on the airoutlet side surface 52 corresponding to eachair inlet hole 19, and when external air enters the airoutlet side surface 52 from the airinlet side surface 51 through theair inlet holes 19, the air can flow along thedistribution groove 21, thereby improving the fluidity of the air and facilitating the mixing of the air and the fuel.
In some embodiments, thedistribution groove 21 is an arc-shaped groove extending along the circumferential direction of theair orifice plate 5. In other words, an arc-shaped groove extending in the circumferential direction of theair hole plate 5 is provided on the airoutlet side surface 52 corresponding to eachair inlet hole 19.
In some embodiments, the air intake holes 19 are arranged in a plurality of circles evenly spaced in the radial direction of theair orifice plate 5, and the air intake holes 19 on each circle are arrayed and evenly spaced in the circumferential direction of theair orifice plate 5.
In some embodiments, thedistribution grooves 21 communicating with the air intake holes 19 located on the same ring have the same circumferential length. In other words, thedistribution grooves 21 corresponding to the plurality of air intake holes 19 on the same ring have the same circumferential length.
In some embodiments, in the radial direction of theair orifice plate 5, of the adjacent twodistribution grooves 21, the circumferential length of thedistribution groove 21 located on the inner side is smaller than the circumferential length of thedistribution groove 21 located on the outer side. In other words, the circumferential length of thedistribution groove 21 corresponding to the intake holes 19 on the ring having a small radial dimension is smaller than the circumferential length of thedistribution groove 21 corresponding to the intake holes 19 on the ring having a large radial dimension.
In some embodiments, the air inlet holes 19 are arranged in four circles uniformly spaced apart in the radial direction of theair orifice plate 5, each circle having four air inlet holes 19 uniformly spaced apart in the circumferential direction of theair orifice plate 5, so that all the air inlet holes 19 of theair orifice plate 5 are divided into four groups, the air inlet holes 19 in each group are aligned in the radial direction of theair orifice plate 5, and the circumferential length of thedistribution groove 21 communicating with the air inlet holes 19 in each group is gradually reduced from the outside to the inside in the radial direction of theair orifice plate 5.
In some embodiments, as shown in fig. 2 and 6, theinjection plate 7 has an inlet side surface (upper surface shown in fig. 1) having a mixingchamber groove 71 thereon and an outlet side surface (lower surface shown in fig. 1) having afuel inlet 72 on a side wall of the mixingchamber groove 71, and the spouting holes 20 extend from a bottom surface of the mixingchamber groove 71 to the outlet side surface of theinjection plate 7. It can be understood that the fuel is introduced into the mixing chamber groove through thefuel inlet 72, the air introduced from theair hole plate 5 is mixed with the fuel in the mixingchamber groove 71, and the mixed mixture is ejected from the outlet side surface of theinjection plate 7 through the ejection holes 20.
In some embodiments, the mixingchamber groove 71 is plural, the pluralmixing chamber grooves 71 are arranged at intervals along the circumferential direction of theinjection plate 7, and each mixingchamber groove 71 has the plural spouting holes 20 on the bottom surface thereof.
In some embodiments, as shown in fig. 6, the number of mixingchamber slots 71 is four, theinjection plate 7 has asquare protrusion 73 in the center of the inlet side surface, adjacentmixing chamber slots 71 are spaced apart by a generally fan-shapedprotrusion 74, the inner end of each fan-shaped protrusion 74 (i.e., the end radially inward of the injection plate 7) meets a corresponding corner of thesquare protrusion 73, i.e., one fan-shapedprotrusion 74 is connected to each corner of thesquare protrusion 72, an arc-shapedprotrusion 75 is connected to one side of the outer end of each fan-shapedprotrusion 74, the arc-shapedprotrusion 75 extends in the circumferential direction of theinjection plate 7, and the other end of the arc-shapedprotrusion 75 is spaced apart from the adjacent fan-shapedprotrusion 74 to form thefuel inlet 72.
In some embodiments, as shown in fig. 2, 3 and 7, a rectifyingplate 22 is disposed between theair hole plate 5 and theinjection plate 7, and a plurality of rectifyingholes 23 are disposed on the rectifyingplate 22. According to the combustor of the gas turbine of the embodiment of the present invention, the uniformity of the flow of air entering the space between theair hole plate 5 and theinjection plate 7 in the post-flamefuel injection pipe 4 can be further improved by the rectifyingplate 22, thereby facilitating the mixing of air and fuel.
In some embodiments, theair orifice plate 5 and the rectifyingplate 22 are directly attached to each other in the axial direction of the after-flamefuel injection pipe 4, and the rectifyingplate 22 and theinjection plate 7 are directly attached to each other in the axial direction of the after-flamefuel injection pipe 4. In other words, as shown in fig. 2 and 3, theair hole plate 5, the rectifyingplate 22, and theinjection plate 7 are provided in the post-flamefuel injection pipe 4 in this order from top to bottom, and theair hole plate 5, the rectifyingplate 22, and theinjection plate 7 are all circular plates, the axes of the three circular plates are aligned, the upper surface of the rectifyingplate 22 is directly bonded to the lower surface of theair hole plate 5, and the lower surface of the rectifyingplate 22 is directly bonded to the upper surface of the arc-shapedprotrusion 75 of thenozzle plate 7.
In some embodiments, the combustor of the gas turbine of the present embodiment further includes a floatingcollar 3, the floatingcollar 3 being mounted on thecombustor basket 1 and being movable relative to thecombustor basket 1, the inner end of the post-flamefuel injection tube 4 extending through the floatingcollar 3 to thecombustor basket 1. Here, "movable" means that the floatingcollar 3 is provided on theflame tube 1, but theflame tube 1 does not restrict the movement of the floatingcollar 3, which may mainly include the entire displacement of the floatingcollar 3 in the radial direction thereof or the contraction or expansion due to expansion and contraction with heat, and of course, the contraction or expansion due to expansion and contraction with cold in the axial direction of the floatingcollar 3.
It can be understood that the floatingcollar 3 is sleeved on the rear flamefuel injection pipe 4, the rear flamefuel injection pipe 4 and theflame tube 1 generate thermal expansion at high temperature, the floatingcollar 3 can expand or contract (i.e. generate displacement) correspondingly along with the expansion or contraction of the rear flamefuel injection pipe 4, because the thermal expansion difference exists between the rear flamefuel injection pipe 4 and theflame tube 1, and by arranging the floatingcollar 3 between the rear flamefuel injection pipe 4 and theflame tube 1, the thermal expansion difference between the rear flamefuel injection pipe 4 and theflame tube 1 can be compensated, the problem of uneven thermal expansion is avoided, and the generation of thermal stress is reduced.
In some embodiments, theflame tube 1 is provided with a mounting hole in which theseat 6 is mounted, and the floatingcollar 3 is movably provided on theseat 6 with respect to theseat 6. In other words, thesupport 6 is mounted on theflame tube 1, the floatingcollar 3 is mounted on thesupport 6, and the floatingcollar 3 can be expanded or contracted on thesupport 6 in the radial direction of the floatingcollar 3 as a whole, as shown in fig. 2 and 3, and the floatingcollar 3 can be expanded or contracted on thesupport 6 in the left-right direction.
In some embodiments, thesupport 6 comprises abase 61 and anannular cover plate 62, thebase 61 comprising abarrel 611, aflange 612 and a weir 613, wherein theflange 612 extends radially outwardly of thebarrel 611 from the periphery of the outer end (the upper end of thebarrel 611 shown in fig. 3) of thebarrel 611, and the weir 613 extends axially outwardly of thebarrel 611 from the periphery of theflange 612. In other words, weir 613 is connected tobarrel 611 byflange 612 and weir 613 has an inner diameter greater than the inner diameter ofbarrel 611. The inner end of the barrel 611 (the upper end of thebarrel 611 shown in fig. 3) is mounted in a mounting hole on theflame tube 1, and theflange 612 is located outside theflame tube 1 and spaced apart from theflame tube 1. As shown in fig. 3, the lower end of thecylindrical body 611 is fitted in the mounting hole, the lower end surface of thecylindrical body 611 is flush with the inner circumferential surface of thecombustor basket 1, and theflange 612 is provided at the upper end of thecylindrical body 611 and is spaced from thecombustor basket 1 in the up-down direction.
The outer periphery ofannular cover plate 62 is connected to weir 613 so thatannular cover plate 62, weir 613 andflange 612 formannular groove 15. For example, as shown in fig. 3,annular cover plate 62 is attached to the inner wall of weir 613 and is positioned at the upper end offlange 612 with a gap betweenannular cover plate 62 andflange 612 so thatannular cover plate 62, weir 613 andflange 612 formannular trough 15.
A portion of the floatingcollar 3 is movably fitted in thisannular groove 15. In other words, a part of the floatingcollar 3 is fitted in theannular groove 15, and the part of the floatingcollar 3 can be moved wholly outward or wholly inward in the radial direction in theannular groove 15.
In some embodiments, the floatingcollar 3 includes acylindrical portion 31 and aperipheral portion 32, theperipheral portion 32 extending radially outward of thecylindrical portion 31 from an inner end (lower end shown in fig. 2) of thecylindrical portion 31. In other words, as shown in fig. 2, the floatingcollar 3 includes an uppercylindrical portion 31 and a lowerperipheral portion 32, the upper end of theperipheral portion 32 being connected to thecylindrical portion 31, theperipheral portion 32 extending outward in the radial direction of thecylindrical portion 31.
Theperipheral edge portion 32 of the floatingcollar 3 is movably fitted in theannular groove 15. In other words, as shown in fig. 3, theperipheral edge portion 32 expands or contracts within theannular groove 15 and along the upper end face of theflange 612.
Thecylindrical portion 31 is fitted over the rear flamefuel injection pipe 4 and is in close fit with the rear flamefuel injection pipe 4.
In some embodiments, thecylindrical portion 31 includes a straightcylindrical section 311 and a flaredsection 312 connected to an outer end (upper end shown in fig. 3) of the straightcylindrical section 311. In other words, as shown in fig. 2, thecylindrical portion 31 includes a lowerstraight cylinder section 311 and anupper horn section 312, the upper end of thestraight cylinder section 311 is connected to thehorn section 312, and the radial dimension of thehorn section 312 gradually increases from bottom to top.
The rear flamefuel injection pipe 4 passes through thehorn section 312 and thestraight section 311 of thecylindrical part 31 in sequence and extends into thecylinder 611 of thebase 61, and thestraight section 311 of thecylindrical part 31 is tightly fitted with the rear flamefuel injection pipe 4. Specifically, as shown in fig. 2, the lower end surface of thecylindrical body 611, the lower end surface of the after-flamefuel injection pipe 4, and the inner wall surface of thecombustor basket 1 are flush.
In some embodiments, the wall of thebarrel 611 is provided with cooling holes 8 communicating with theannular channel 14, and cooling air can enter the base 61 through the cooling holes 8 to cool and lightly blow the post-flamefuel injection pipe 4.
In some embodiments, the outer end (upper end as shown in FIG. 2) of the post-flamefuel injection tube 4 has a flange 9, and the post-flamefuel injection tube 4 is mounted on theflow guide sleeve 2 by the flange 9. Specifically, the flange 9 is mounted on theflow guide sleeve 2 by a fastener such as a bolt.
In some embodiments, theflow guide bush 2 is provided with a fixing hole in which anouter ring 10 is mounted, and theouter ring 10 has an annularouter groove 101, an annularinner groove 102, and acommunication hole 103.
An annularouter groove 101 opens outward in the radial direction of theouter ring 10, an annularinner groove 102 opens inward in the radial direction of theouter ring 10, and acommunication hole 103 for communicating the annularouter groove 101 with the annularinner groove 102. Specifically, as shown in fig. 3, theouter ring 10 includes an upper cover plate, a connecting plate, and a lower cover plate, and the cross section along the axial direction is substantially i-shaped, the upper cover plate and the lower cover plate are arranged in parallel and at an interval, the connecting plate extends along the axial direction of theouter ring 10, the connecting plate is provided with acommunication hole 103, the upper cover plate is connected to the lower cover plate at a middle position thereof by the connecting plate, the lower cover plate includes an outer side portion and an inner side portion which are arranged in sequence from outside to inside along the radial direction of theouter ring 10, and the radial dimension of the.
Aninner ring 11 is installed in theouter ring 10, and theinner ring 11 has an inner ringannular groove 111, and the inner ringannular groove 111 opens outward in the radial direction of theinner ring 11.
The inner ringannular groove 111 of theinner ring 11 is butted against the annularinner groove 102 of theouter ring 10 to form theannular fuel passage 12.
The flange 9 at the outer end of the post-flamefuel injection pipe 4 is mounted on theouter ring 10, and the post-flamefuel injection pipe 4 passes through theinner ring 11. In other words, as shown in fig. 2 and 3, the flange 9 is fastened to theouter ring 10 by bolts, and theouter ring 10 is fixed to theflow guide sleeve 2, thereby indirectly mounting the flange 9 to theflow guide sleeve 2.
Theannular fuel passage 12 is communicated with the fuel holes on the post-flamefuel injection pipe 4 through the fuel throughholes 13 on theinner ring 11, so that the fuel in theannular fuel passage 12 enters the post-flamefuel injection pipe 4 through the fuel throughholes 13 and the fuel holes in sequence. It can be understood that the fuel in theannular fuel channel 12 passes through the fuel throughholes 13 and the fuel holes in sequence and then enters the post-flamefuel injection pipe 4, and the fuel in the post-flamefuel injection pipe 4 passes through thefuel inlets 72 on theinjection plate 7 and enters the mixingcavity groove 71 on theinjection plate 7, so that the air and the fuel are mixed in the mixingcavity groove 7.
In some embodiments, afuel passage 16 is provided inside theflow guide sleeve 2, and thefuel passage 16 communicates with the annularouter groove 101, that is, theannular fuel passage 12. As shown in fig. 1 and 3, the fuel is received by the left end of thefuel passage 16 inside theflow guide sleeve 2, and is introduced into theannular fuel passage 12 through the right end of thefuel passage 16, so that the fuel is supplied into the mixingchamber groove 71 on theinjection plate 7 in time.
In some alternative embodiments, thefuel passage 16 is formed within the inner wall of theflow sleeve 2. In other embodiments, afuel cover plate 17 is provided inside theflow sleeve 2, and thefuel passage 16 is formed between the inner wall of theflow sleeve 2 and thefuel cover plate 17.
In some embodiments, aswirler 18 is provided within the post-flamefuel injection tube 4. Theswirler 18 may enhance the mixing effect of the fuel and air within the post-flamefuel injection tube 4 to stabilize the flame. Specifically, as shown in fig. 2 and 3, theswirler 18 in the after-flamefuel injection pipe 4 is disposed adjacent to the lower end surface of the after-flamefuel injection pipe 4.
In some embodiments, the after-flamefuel injection pipes 4 are plural, and the plural after-flamefuel injection pipes 4 are arranged at regular intervals in the circumferential direction of theflow guide liner 2. The combustor of the gas turbine of the embodiment of the present invention can further improve NO by providing a plurality of after-flamefuel injection pipes 4 arranged at even intervals in the circumferential direction of theflow guide liner 2 at a position downstream of the primary fuel nozzleXDischarging and improving the performance of the whole machine.
A combustor of a gas turbine according to an embodiment of the present invention is described below with reference to fig. 1 to 7.
As shown in fig. 1 to 7, a combustor of a gas turbine according to an embodiment of the present invention includes aliner 1, aflow guide sleeve 2, a floatingcollar 3, a post-flamefuel injection pipe 4, anair orifice plate 5, asupport 6, aninjection plate 7, anouter ring 10, aninner ring 11, afuel cover plate 17, aswirler 18, and a rectifyingplate 22.
Theguide bush 2 is sleeved on theflame tube 1 to form anannular channel 14 between theguide bush 2 and theflame tube 1, afuel cover plate 17 is arranged in theguide bush 2, and afuel channel 16 is formed between thefuel cover plate 17 and theguide bush 2.
The upper end of the rear flamefuel injection pipe 4 is fixed on theguide sleeve 2, and the lower end of the rear flamefuel injection pipe 4 extends to theflame tube 1. The number of the after-flamefuel injection pipes 4 is plural, and the plural after-flamefuel injection pipes 4 are uniformly arranged along the circumferential direction of theflow guide bush 2 at intervals. Each of the after-flamefuel injection pipes 4 has a plurality of fuel holes thereon, which are arranged at regular intervals in the circumferential direction of the after-flamefuel injection pipe 4.
The rear flamefuel injection pipe 4 is internally provided with anair hole plate 5, a rectifyingplate 22 and aninjection plate 7 which are circular plates in sequence along the axial direction, the axial directions of theair hole plate 5, the rectifyingplate 22 and theinjection plate 7 are consistent, the rectifyingplate 22 is provided with a plurality of rectifyingholes 23, the upper surface of the rectifyingplate 22 is directly attached to theair hole plate 5, and the lower surface of the rectifyingplate 22 is directly attached to the injection plate 7:
theair hole plate 5 is provided with 16 air inlet holes 19, and the air inlet holes 19 are arranged in four circles uniformly spaced apart in the radial direction of theair hole plate 5, each circle having four air inlet holes 19 uniformly spaced apart in the circumferential direction of theair hole plate 5, so that all the air inlet holes 19 of theair hole plate 5 are divided into four groups, the air inlet holes 19 in each group being aligned in the radial direction of theair hole plate 5.
Theair hole plate 5 has an airinlet side surface 51 and an airoutlet side surface 52, the airoutlet side surface 52 is provided with a plurality ofdistribution grooves 21 correspondingly communicated with the air inlet holes 19, and thedistribution grooves 21 are arc-shaped grooves extending along the circumferential direction of theair hole plate 5. The circumferential lengths of thedistribution grooves 21 corresponding to the plurality of air inlet holes 19 on the same ring are the same, and the circumferential lengths of thedistribution grooves 21 communicated with the air inlet holes 19 in each group are gradually reduced from outside to inside along the radial direction of theair hole plate 5.
Theinjection plate 7 has an inlet side surface having 4mixing chamber grooves 71 and an outlet side surface, and each mixingchamber groove 71 has afuel inlet 72 on a side wall thereof communicating with a fuel hole on the after-flamefuel injection pipe 4, and fuel introduced from the fuel hole enters the mixingchamber groove 71 through the fuel inlet.
Theinjection plate 7 has asquare protrusion 73 in the centre of the inlet side surface, adjacentmixing chamber slots 71 are spaced apart by generally fan-shapedprotrusions 74, the inner end of each fan-shaped protrusion 74 (i.e. the end radially inward of the injection plate 7) meets a corresponding corner of thesquare protrusion 73, i.e. one fan-shapedprotrusion 74 is connected to each corner of thesquare protrusion 72, an arc-shapedprotrusion 75 is connected to one side of the outer end of each fan-shapedprotrusion 74, the arc-shapedprotrusion 75 extends in the circumferential direction of theinjection plate 7, and the other end of the arc-shapedprotrusion 75 is spaced apart from the adjacent fan-shapedprotrusion 74 to form thefuel inlet 72.
Theinjection plate 7 is further provided with a plurality of injection holes 20, the injection holes 20 extend from the bottom surface of the mixingchamber groove 71 to the outlet side surface of theinjection plate 7, and theinjection plate 7 injects the mixture of fuel and air into the post-flamefuel injection pipe 4 through the injection holes 20.
Theguide bush 2 is provided with a fixing hole, anouter ring 10 is arranged in the fixing hole, and the outer periphery of theouter ring 10 is welded with theguide bush 2.
Theouter ring 10 has an annularouter groove 101, an annularinner groove 102, and acommunication hole 103. An annularouter groove 101 opens outward in the radial direction of theouter ring 10, an annularinner groove 102 opens inward in the radial direction of theouter ring 10, and acommunication hole 103 for communicating the annularouter groove 101 with the annularinner groove 102.
Aninner ring 11 is installed in theouter ring 10, theinner ring 11 has an inner ringannular groove 111, the inner ringannular groove 111 opens outward in the radial direction of theinner ring 11, and theinner ring 11 also has a fuel throughhole 13.
The inner ringannular groove 111 of theinner ring 11 is butted against the annularinner groove 102 of theouter ring 10 to form anannular fuel passage 12, and theannular fuel passage 12 communicates with thefuel passage 16.
It will be appreciated that fuel in thefuel passage 16 enters the mixingchamber slot 71 from thefuel inlet 72 through the fuel throughholes 13 in theannular fuel passage 12 and theinner ring 11 and the fuel holes of the post-flamefuel injection tubes 4.
The floatingcollar 3 is mounted on theliner 1 by means of amount 6. Thesupport 6 is mounted in a mounting hole on theliner 6, and the floatingcollar 3 is mounted on thesupport 6 and is moved integrally outward or integrally inward in the radial direction of the floatingcollar 3 relative to thesupport 6.
Thesupport 6 includes abase 61 and anannular cover plate 62, thebase 61 includes acylinder 611, aflange 612 and a weir 613, theflange 612 extends from the upper end periphery of thecylinder 611 outward in the radial direction of thecylinder 611, and the weir 613 extends from the outer periphery of theflange 612 outward in the axial direction of thecylinder 611.
The floatingcollar 3 includes an uppercylindrical portion 31 and a lowerperipheral portion 32, the upper end of theperipheral portion 32 being connected to thecylindrical portion 31, theperipheral portion 32 extending radially outward of thecylindrical portion 31. Theperipheral edge portion 32 of the floatingcollar 3 is fitted in theannular groove 15 and moves integrally outward or inwardly in the radial direction of the floatingcollar 3 along the upper end face of theflange 612.
Thecylindrical portion 31 includes astraight cylinder section 311 at a lower portion and ahorn section 312 at an upper portion, the upper end of thestraight cylinder section 311 is connected to thehorn section 312, and the radial dimension of thehorn section 312 is gradually increased from the bottom up.
The upper end of the rear flamefuel injection pipe 4 is provided with a flange 9, the flange 9 is positioned on theouter ring 10, the flange 9 is fastened on theouter ring 10 through bolts, the rear flamefuel injection pipe 4 penetrates through theinner ring 11, the lower end of the rear flamefuel injection pipe 4 sequentially penetrates through thecylindrical part 31 and theperipheral part 32 of the floatinglantern ring 3 and extends into thecylinder 611 of thebase 61, thestraight cylinder section 311 of thecylindrical part 31 of the floatinglantern ring 3 is tightly matched with the rear flamefuel injection pipe 4, and the lower end surface of the rear flamefuel injection pipe 4, the lower end surface of thesupport 6 and the inner wall surface of theflame tube 1 are flush, so that the mixture of fuel and air is injected into theflame tube 1 through the lower end of the rear flamefuel injection pipe 4.
Aswirler 18 is provided in the post-flamefuel injection pipe 4 adjacent to the lower end surface thereof to further enhance the mixing effect of the fuel and air in the post-flamefuel injection pipe 4 and stabilize the flame.
The wall of thecylinder 611 is provided with cooling holes 8 communicating with theannular passage 14, and cooling air can enter the inside of the base 61 through the cooling holes 8 to cool and lightly blow the post-flamefuel injection pipe 4.
A gas turbine according to an embodiment of another aspect of the present invention includes the combustor of the above-described embodiment.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (20)
1. A combustor for a gas turbine, comprising:
a flame tube;
the guide bush is sleeved on the flame tube, and an annular channel is formed between the guide bush and the flame tube;
the outer end part of the rear flame fuel injection pipe is fixed on the guide bush, an air hole plate and a jetting plate are sequentially arranged in the rear flame fuel injection pipe along the axial direction of the rear flame fuel injection pipe, a plurality of air holes are formed in the air hole plate, a plurality of jetting holes are formed in the jetting plate, and the jetting plate is used for mixing fuel and air into a mixture and jetting the mixture into the rear flame fuel injection pipe through the jetting holes;
a floating collar mounted on the flame tube and expandable or contractible relative to the flame tube in a radial direction of the floating collar, an inner end of the post-flame fuel injection tube extending through the floating collar to the flame tube.
2. The gas turbine combustor according to claim 1, wherein the air hole plate has an air inlet side surface and an air outlet side surface, and a plurality of distribution grooves are provided on the air outlet side surface in corresponding communication with the air inlet holes.
3. The gas turbine combustor of claim 2, wherein the distribution groove is an arcuate groove extending in a circumferential direction of the air hole plate.
4. The gas turbine combustor of claim 3, wherein the air inlet holes are arranged in a plurality of circles evenly spaced in a radial direction of the air hole plate, the air inlet holes on each circle being aligned and evenly spaced in a circumferential direction of the air hole plate.
5. The gas turbine combustor according to claim 4, wherein the circumferential length of the distribution groove communicating with the intake port on the same ring is the same.
6. The gas turbine combustor according to claim 5, wherein, of two adjacent distribution grooves in a radial direction of the air hole plate, a circumferential length of a distribution groove on an inner side is smaller than a circumferential length of a distribution groove on an outer side.
7. The gas turbine combustor according to claim 4, wherein said air inlet holes are arranged in four circles uniformly spaced in a radial direction of said air hole plate, each circle having four said air inlet holes uniformly spaced in a circumferential direction of said air hole plate, so that all said air inlet holes of said air hole plate are divided into four groups, said air inlet holes in each group being aligned in the radial direction of said air hole plate, and a circumferential length of said distribution groove communicating with the air inlet holes in each group is gradually reduced from outside to inside in the radial direction of said air hole plate.
8. The gas turbine combustor of claim 1, wherein the injector plate has an inlet side surface with a mixing pocket thereon and an outlet side surface with a fuel inlet on a sidewall of the mixing pocket, the effusion holes extending from a floor of the mixing pocket to the outlet side surface of the injector plate.
9. The gas turbine combustor according to claim 8, wherein the mixing chamber slots are plural and arranged at intervals in a circumferential direction of the injection plate, and a bottom surface of each of the mixing chamber slots has a plurality of the spouting holes.
10. The gas turbine combustor according to claim 9, wherein the number of the mixing cavity slots is four, the injection plate has a square protrusion at a center of the inlet side surface, adjacent mixing cavity slots are spaced apart by a generally fan-shaped protrusion, an inner end of each of the fan-shaped protrusions meets a corresponding corner of the square protrusion, an outer end of each of the fan-shaped protrusions is connected to one side of an outer end thereof with an arc-shaped protrusion extending in a circumferential direction of the injection plate, and the other end of the arc-shaped protrusion is spaced apart from the adjacent fan-shaped protrusion to form the fuel inlet.
11. The gas turbine combustor according to any one of claims 1 to 10, wherein a rectifying plate is provided between the air hole plate and the injection plate, and a plurality of rectifying holes are provided in the rectifying plate.
12. The gas turbine combustor according to claim 11, wherein the air hole plate and the rectifying plate are directly attached to each other in an axial direction of the after-flame fuel injection pipe, and the rectifying plate and the injection plate are directly attached to each other in the axial direction of the after-flame fuel injection pipe.
13. The gas turbine combustor of any one of claims 1 to 10, where the floating collar is further expandable or contractible in an axial direction of the floating collar relative to the liner.
14. The gas turbine combustor of claim 13, wherein the liner has a mounting hole therein, a support is mounted in the mounting hole, and the floating collar is fitted on the support.
15. The gas turbine combustor according to claim 14, wherein the pedestal includes a base and an annular cover plate, the base includes a cylinder, a flange extending radially outward of the cylinder from an upper end periphery of the cylinder, and a weir extending axially outward of the cylinder from an outer periphery of the flange, a lower end of the cylinder is mounted in the mounting hole, the flange is spaced apart from the liner,
the outer periphery of the annular cover plate is connected with the cofferdam so that the annular cover plate, the cofferdam and the flange form an annular groove,
a portion of the floating collar is movably fitted within the annular groove.
16. The gas turbine combustor of claim 15, wherein the floating collar includes a cylindrical section and a peripheral edge portion extending radially outward from an inner end of the cylindrical section, the peripheral edge portion being movably fitted within the annular groove, the cylindrical section fitting over and closely fitting the post-flame fuel injection tubes.
17. The gas turbine combustor of claim 13, wherein the outer end of the aft flame fuel injection pipe has a flange, the aft flame fuel injection pipe being mounted on the flow guide sleeve by the flange.
18. The gas turbine combustor according to claim 17, wherein the flow guide bush is provided with a fixing hole in which an outer ring having an annular outer groove opening radially outward of the outer ring and an annular inner groove opening radially inward of the outer ring is fitted, the annular inner groove communicating with the annular outer groove through a communication hole;
an inner ring is arranged in the outer ring, the inner ring is provided with an inner ring annular groove which is opened outwards along the radial direction of the inner ring, the inner ring annular groove is butted with the annular inner groove to form an annular fuel passage,
the flange is installed on the outer ring, the rear flame fuel injection pipe penetrates through the inner ring, and the annular fuel channel is communicated with the fuel hole in the rear flame fuel injection pipe through the fuel through hole in the inner ring.
19. The gas turbine combustor of any one of claims 1 to 10, where a swirler is disposed within the post-flame fuel injection tube.
20. A gas turbine comprising a combustor according to any one of claims 1 to 19.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711279240.XACN108278634B (en) | 2017-12-06 | 2017-12-06 | Gas turbine and combustor thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711279240.XACN108278634B (en) | 2017-12-06 | 2017-12-06 | Gas turbine and combustor thereof |
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| CN108278634Btrue CN108278634B (en) | 2020-07-14 |
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| CN110979685B (en)* | 2019-12-11 | 2020-07-31 | 贵州理工学院 | An on-demand system for drone seeding |
| CN113738777B (en)* | 2021-09-13 | 2022-11-04 | 中国联合重型燃气轮机技术有限公司 | Shaft coupling |
| CN116357999B (en)* | 2023-04-11 | 2025-06-24 | 哈尔滨工程大学 | Double-layer composite cooling structure for wall surface of flame tube of combustion chamber of gas turbine |
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| US5881756A (en)* | 1995-12-22 | 1999-03-16 | Institute Of Gas Technology | Process and apparatus for homogeneous mixing of gaseous fluids |
| CN101818908A (en)* | 2009-02-02 | 2010-09-01 | 通用电气公司 | Device for fuel injection in a turbine engine |
| CN103189619A (en)* | 2010-10-29 | 2013-07-03 | 索拉透平公司 | Gas turbine combustor with mounting for helmholtz resonators |
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