CN102538009A - Combustor premixer - Google Patents

Combustor premixer Download PDF

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Publication number
CN102538009A
CN102538009A CN2011103858538A CN201110385853A CN102538009A CN 102538009 A CN102538009 A CN 102538009A CN 2011103858538 A CN2011103858538 A CN 2011103858538A CN 201110385853 A CN201110385853 A CN 201110385853A CN 102538009 A CN102538009 A CN 102538009A
Authority
CN
China
Prior art keywords
premixer
combustion chamber
chamber according
swirler blades
opening
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN2011103858538A
Other languages
Chinese (zh)
Inventor
N·G·帕萨尼亚
G·D·迈尔斯
A·P·辛赫
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of CN102538009A publication Critical patent/CN102538009A/en
Pending legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Abstract

A combustor premixer is provided and includes a burner tube having a bell mouth-shaped opening, a plurality of tubular bodies telescopically disposed within the burner tube to deliver combustible materials to a premixing passage defined between the burner tube and an outermost one of the plurality of tubular bodies and a plurality of swirler vanes arrayed circumferentially in the opening, each one of the plurality of swirler vanes including a body extending along a radial dimension from the burner tube to the outermost tubular body and a leading edge protruding upstream from the opening.

Description

The combustion chamber premixer
Technical field
The present invention relates to a kind of premixer that is used for gas turbine combustors.
Background technology
In gas-turbine unit, premixed air and fuel are being arranged at the combustion chamber internal combustion of turbine upstream, and in said combustion chamber, the high-temperature stream cognition that is generated by burning produces mechanical energy.Said mechanical energy can be converted into electric energy subsequently and be transferred in the circuit.The combustion chamber generally includes the fuel nozzle with premixed passage, and in the premixed passage, air and fuel can mix mutually.This premixed can improve the degree that combustible material carries out completing combustion, thereby reduces the amount of the emission of engine producing.Therefore, premixed degree is high more, and the amount of emission is just low more.
The increase of this type of premixed degree is through using large-size rotational flow blade and/or a large amount of swirl vanes to be achieved in cyclone, wherein said cyclone be arranged on the premixed passage upstream extremity or near.Swirl vane can change the flow direction of combustible material, mixes to promote fuel and air.Yet; Large-size rotational flow blade and/or a large amount of swirl vane can increase the gross weight and the cost of fuel nozzle, and, even use said swirl vane; The inlet air that also might get into the premixed passage at least is axially or radially, rather than the hybrid directional of axial flow and Radial Flow.
Summary of the invention
On the one hand, the present invention provides a kind of combustion chamber premixer, and said combustion chamber premixer comprises: the combustion tube with clock mouth shape opening; A plurality of tubular bodies, said tubular body is arranged in the combustion tube with nestable mode, and combustible material is delivered to the premixed passage, wherein said premixed passage is located between the outermost layer tubular body in said combustion tube and the said a plurality of tubular body; And in said opening a plurality of swirler blades of circumferential array, each in said a plurality of swirler blades comprises the main body that size is radially extended to said outermost layer tubular body from said combustion tube, and the leading edge of upstream stretching out from said opening.
Said combustion tube is through forming to define the sleeve pipe side opening that is positioned at said a plurality of swirler blades downstream.Said sleeve pipe side opening is positioned at the position near the trailing edge of said a plurality of swirler blades.Said outermost layer tubular body in said a plurality of tubular body is dispersed in updrift side.Said a plurality of tubular body is carried combustible material through the second place in said clock mouth shape opening and said clock mouth shape opening downstream, and wherein, said premixed passage narrows from said second place downstream.One or more warps in said a plurality of tubular body form to define fuel channel.Said a plurality of tubular body comprises having inner centerbody, and said inside is used to hold the supply that purifies air.In said a plurality of swirler blades each is with the radially size extension of the helical pattern of essence.One or more trailing edges in said swirler blades of each in said a plurality of swirler blades are sentenced certain angle.Pressure essence along said premixed passage is identical.
On the other hand, the present invention provides a kind of combustion chamber premixer, and it comprises: ring sleeve; Annular wall; Said annular wall is arranged in the said sleeve pipe to define premixed passage and fuel channel; Said premixed passage extends from the sleeve pipe upstream extremity downstream; And extend radially inwardly convergent point from the divergence point that is positioned at said sleeve pipe upstream extremity, said fuel channel is through being configured to that fuel is transported to the said premixed passage near said divergence point; And centerbody; Said centerbody has the innermost layer pipe to define the inner passage; And in said wall, can load to define center-aisle, said center-aisle is communicated with said inner passage fluid via first hole, and wherein said first hole is formed in the said innermost layer pipe; Be communicated with said fuel channel fluid via second hole; Wherein said second hole is formed at the position that is positioned at downstream, said first hole in the said wall, and is communicated with said premixed passage fluid via the 3rd hole, and wherein said the 3rd hole is formed at and is positioned at said downstream, second hole in the said wall and near the position of said convergent point.
Said combustion chamber premixer further comprises a plurality of swirler blades that are arranged at said sleeve pipe upstream extremity, cheese of the common formation of the cross section of wherein said sleeve pipe and said a plurality of swirler blades.Said combustion chamber premixer further comprises the mounting flange at the upper reaches that are positioned at said upstream extremity; Wherein said wall is dispersed to said mounting flange from said upstream extremity; And said wall comprises inner wall section and outer wall section; Wherein said outer wall section diverges in the downstream edge place and the said inner wall section of said inner wall section, to define said fuel channel.Said burning gallery is transported to said premixed passage via the teasehole that is located in the said outer wall section with fuel.Said teasehole is around said outer wall section circumferential array.Said second hole at the said downstream edge place of said inner wall section around said inner wall section circumferential array.Said the 3rd hole at the said downstream edge place of said inner wall section around said wall circumferential array.Said first orifice ring is around said innermost layer pipe circumferential array.Said center-aisle narrows from said convergent point downstream.
Again on the one hand; The present invention provides a kind of combustion chamber premixer; Said combustion chamber premixer comprises that annular firing pipe, warp form to define the annular inner wall of fuel channel; And through forming to define inner centerbody, wherein said combustion tube, said inwall and said centerbody have the premixed passage of assembling upstream extremity and downstream part with nestable arrangement so that said combustion tube and said inside are defined one; Said premixed passage is communicated with said fuel channel fluid at upstream extremity; Said inwall and said centerbody define one to have upstream extremity and disperses the center-aisle of downstream part, and said center-aisle is in upstream extremity and fuel channel and said internal fluid communication, and is communicated with said premixed passage fluid at the boundary separately of corresponding upstream extremity and downstream part; And said combustion chamber premixer further is included in a plurality of swirler blades of circumferential array in the said premixed passage; In said a plurality of swirler blades each comprises the main body that size is radially extended to said inwall from said combustion tube, and the leading edge of upstream stretching out from the opening of said premixed passage.
Through following explanation and combine accompanying drawing can be well understood to these and other advantage and characteristic more.
Description of drawings
Claims in the present patent application file are pointed out in detail and have clearly been advocated the present invention.Through following explanation and combine accompanying drawing can be well understood to above-mentioned and other feature and advantage of the present invention, wherein:
Fig. 1 is used for the side cross-sectional, view of the premixer of gas turbine combustors for the present invention;
Fig. 2 is the perspective view of premixer shown in Figure 1;
Fig. 3 is the perspective view of gas turbine combustors shown in Figure 1;
Specific embodiment partial reference accompanying drawing is introduced embodiments of the invention and advantage and characteristic with way of example.
The component symbol tabulation:
Reference number Parts Reference number Parts
10 The combustion chamber premixer 20 Combustion tube
21 Ring sleeve 22 Upstream extremity
23 Tubular portion 25 Clock mouth shape opening
26 The sleeve pipe side opening 30 A plurality of tubular bodies
31 The premixed passage 32 Outer surface
33 The outermost layer tubular body 34 Mounting flange
35 Centerbody 36 Center-aisle
37 The innermost layer pipe 38 The inner passage
40 A plurality of swirler blades 41 Main body
42 Leading edge 43 Trailing edge
44 The cheese configuration 50 Primary importance
51 The second place 60 Wheel hub
61 Annular inner wall 62 Fuel channel
63 Teasehole 70 First hole
71 Second hole 72 The 3rd hole
321 Outer wall section 322 Inner wall section
The specific embodiment
According to Fig. 1 to Fig. 3; The present invention provides combustion chamber premixer 10; The mode that said combustion chamber premixer is not significantly gained in weight through improving mixability makes air inlet keep low pressure drop, thereby lets the combustible material that flows in the premixer have the component that flows to axial and radially.Combustion chamber premixer 10 comprises combustion tube 20, a plurality of tubular body 30 and a plurality of swirler blades 40.
Combustion tube 20 comprises ring sleeve 21, and said ring sleeve passes tubular portion 23 downstream from upstream extremity 22 and extends.Ring sleeve 21 is protrusion at upstream extremity 22 places, has the clock mouth shape opening 25 of dome-shaped design with formation.For example; In running; The compressor air-discharging of from the compressor of gas-turbine unit, discharging flows to the head end of gas-turbine unit in updrift side, and near clock mouth shape opening 25 time, said compressor air-discharging radially inwardly flows to said a plurality of tubular body 30; And, pass said a plurality of swirler blades 40 axial flow further downstream subsequently because of the clock mouth shape opening 25 with dome-shaped design transfers to axially reposefully.A plurality of swirler blades 40 apply angular momentum to the air that gets into clock mouth shape opening 25, so that air is with the turn of predefine angle, the purpose of setting said predefine angle is to let air have enough axially-movables, and promotes air and fuel fully to mix.
Compressor air-discharging also can be flowed through and is formed at the sleeve pipe side opening 26 in the ring sleeve 21.Sleeve pipe side opening 26 can be formed at the downstream of a plurality of swirler blades 40, and in certain embodiments, can be formed at the position of essence near the trailing edge 43 of said swirler blades.For example, sleeve pipe side opening 26 has reduced such as the quantity and the influence of blowing down the low regime that produces because of boundary-layer.
A plurality of tubular bodies 30 are arranged in the ring sleeve 21 of combustion tube 20 with nestable mode, and through forming combustible material is delivered to premixed passage 31.Premixed passage 31 is located between the outer surface 32 of outermost layer tubular body 33 of ring sleeve 21 and a plurality of tubular body 30.The air that gets into the clock mouth shape opening 25 and the swirler blades 40 of flowing through will continue to flow via premixed passage 31, and in said premixed passage, air carries out premixed with the fuel of carrying through a plurality of tubular bodies 30.The premixed distance through prolonging has been considered in the position of the swirler blades 40 at premixed passage 31 upper reaches.In addition, the pressure along premixed passage 31 maintains the consistent level of essence.
A plurality of swirler blades 40 are circumferential array in clock mouth shape opening 25.In a plurality of swirler blades 40 each comprises main body 41, leading edge 42 and trailing edge 43, and wherein said main body is compared relatively thin with weight reduction with the circumference of clock mouth shape opening.The main body 41 of each in a plurality of swirler blades 40 radially size extends to the outer surface 32 of outermost layer tubular body 33 from the internal diameter of leading edge and ring sleeve 21.Leading edge 42 is upstream stretched out from clock mouth shape opening, and trailing edge 43 tilts at a certain angle and flows to promote that air is angled.Stretching out of leading edge 42 makes the tangential momentum at upstream extremity 22 places have less relatively axial/radial momentum, thereby makes air get into relatively reposefully.According to each embodiment, radially size essence is twist for each in a plurality of swirler blades 40.Rely on this structure, the cross section of ring sleeve 21 and a plurality of swirler blades 40 has dome-shaped configuration 44 or some other similar configuration.
As shown in Figure 1; Outermost layer tubular body 33 is dispersed towards mounting flange 34 on updrift side; And ring sleeve 21 form clock mouth shape openings 25 and with the part of outermost layer tubular body 33 axial overlaps of dispersing, premixed passage 31 is dispersed on updrift side, with dispersing of imitation outermost layer tubular body 33.A plurality of tubular bodies 30 are carried combustible material through the primary importance 50 at clock mouth shape opening 25 places and the second place 51 in said clock mouth shape opening 25 downstream; Wherein premixed passage 31 is dispersed at said primary importance place, and premixed passage 31 is assembled to wheel hub 60 at said second place place.Primary importance 50 can be upstream or downstream move, or circumferentially be located between the swirler blades 40, so that fuel is transported to the higher relatively zone of speed.Above-mentioned divergent structure can be gathered fluid, thereby improves the speed of wheel hub and reduce the risk of flame stabilization.
Get into the air and the fuel mix that gets into premixed passage 31 through first and second positions 50,51 of clock mouth shape opening 25, and the said combustible material that is blended in, wheel hub 60 obtains promoting and strengthening when assembling.In addition, as shown in Figure 2, premixed passage 31 radially narrows on downstream direction from the second place 51.Therefore, premixed obtains promoting from upstream extremity 22 when wheel hub 60 is assembled at combustible material, and when the tubular portion that narrows down 23 flows, can avoid occurring pressure drop at combustible material.
A plurality of tubular bodies 30 further comprise centerbody 35.Centerbody 35 can be loaded in the breach of being located in a plurality of tubular bodies 30 defining center-aisle 36, and said centerbody comprises innermost layer pipe 37.Innermost layer pipe 37 is through forming to define inner passage 38, and said inner passage is used for admitting the supply that purifies air.
As the annular inner wall 61 that partly is arranged at nestable mode in the ring sleeve 21, the outer surface 32 of outermost layer tubular body 33 forms wheel hub 60, to define the upstream portion of premixed passage 31.Annular inner wall 61 further comprises outer wall section 321 and inner wall section 322; Wherein said outer wall section and inner wall section are diverged at the separation place of the downstream edge that is positioned at said annular inner wall defining fuel channel 62 each other, and said separation is near upstream extremity 22.As stated; Premixed passage 31 extends from upstream extremity 22 downstream; And radially inwardly assemble to the convergent point near the second place 51 from the divergence point near the primary importance 50 of upstream extremity 22, wherein convergent point is axially set between the tubular portion 23 that upstream extremity 22 and downstream narrow down.
Fuel channel 62 is through being configured to via teasehole 63 fuel to be transported to the premixed passage 31 near the divergence point of upstream extremity 22.Center-aisle 36 is communicated with inner passage 38 fluids via first hole 70 that is formed in the innermost layer pipe 37.In addition, center-aisle 36 is communicated with fuel channel 62 fluids via second hole 71, and wherein said second hole is formed at the axial location that is positioned at 70 downstream, first hole in the annular inner wall 61.Center-aisle 36 also is communicated with premixed passage 31 fluids via the 3rd hole 72, and wherein said the 3rd hole is formed at and is positioned at 71 downstream, second hole in the annular inner wall 61 and near the axial location of the convergent point and the second place 51.Can dispersed and distributed and tilt at a certain angle in first hole 70, second hole 71 and the 3rd hole 72, with the recirculation after reducing power and reducing jet.
Therefore, increase by first hole 70 of can flowing through that purifies air that mixability also is supplied to center-aisle 36 and inner passage 38, and with the fuel mix that flows into the center-aisles 36 from fuel channel 62 via second hole 71.Said fuel and AIR MIXTURES flow in the premixed passages 31 via the 3rd hole 72 subsequently, and therein with premixed passage 31 in already present combustible material mix.The final mixture of said fuel and the air tubular portion 23 that downstream narrow down that continues to flow through, and because premixed passage 31 radially narrows at downstream direction, therefore the pressure of said final mixture will be kept stable.Said radially narrow to disperse from the second place 51 downstream through annular inner wall 61 constitute.
Teasehole 63, first hole 70, second hole 71 and the 3rd hole 72 can be around wall/pipe circumferential array separately, and can separate each other at the even or uneven interval of essence.
Although the present patent application file only combines the embodiment of limited quantity to introduce in detail the present invention, should be appreciated that the present invention is not limited thereto a type disclosed embodiment.On the contrary, the present invention can be through revising variation, change, replacement or the equivalent not introduce before containing all but to be consistent with the spirit and scope of the present invention.In addition,, should be appreciated that various aspects of the present invention can only comprise some embodiment in the previous embodiment although introduced various embodiment of the present invention.Therefore, the present invention should not be regarded as the restriction that receives aforementioned specification, and it only receives the restriction of appended claims scope.

Claims (10)

1. combustion chamber premixer comprises:
Combustion tube with clock mouth shape opening;
A plurality of tubular bodies, said a plurality of tubular bodies are arranged in the said combustion tube with nestable mode, and combustible material is transported to a premixed passage, wherein said premixed passage is located between the outermost layer tubular body in said combustion tube and the said a plurality of tubular body; And
A plurality of in said opening the swirler blades of circumferential array; In said a plurality of swirler blades each comprises a radially size main body of extending to said outermost layer tubular body from said combustion tube, and a leading edge of upstream stretching out from said opening.
2. combustion chamber according to claim 1 premixer is characterized in that, said combustion tube is through forming to define the sleeve pipe side opening that is positioned at said a plurality of swirler blades downstream.
3. combustion chamber according to claim 2 premixer is characterized in that, said sleeve pipe side opening is positioned at the position near the trailing edge of said a plurality of swirler blades.
4. combustion chamber according to claim 1 premixer is characterized in that, the said outermost layer tubular body in said a plurality of tubular bodies is dispersed in updrift side.
5. combustion chamber according to claim 1 premixer; It is characterized in that; Said a plurality of tubular body is carried combustible material through the second place in said clock mouth shape opening and said clock mouth shape opening downstream, and wherein, said premixed passage narrows from said second place downstream.
6. combustion chamber according to claim 1 premixer is characterized in that, the one or more warps in said a plurality of tubular bodies form to define a fuel channel.
7. combustion chamber according to claim 1 premixer is characterized in that, said a plurality of tubular bodies comprise that has an inner centerbody, and said inside is used to hold the supply that purifies air.
8. combustion chamber according to claim 1 premixer is characterized in that, each in said a plurality of swirler blades is with the radially size extension of the helical pattern of essence.
9. combustion chamber according to claim 1 premixer is characterized in that, one or more trailing edges in said swirler blades of each in said a plurality of swirler blades are sentenced certain angle.
10. combustion chamber according to claim 1 premixer is characterized in that, and is identical along the pressure essence of said premixed passage.
CN2011103858538A 2010-11-19 2011-11-18 Combustor premixer Pending CN102538009A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/950,463 US20120125004A1 (en) 2010-11-19 2010-11-19 Combustor premixer
US12/950463 2010-11-19

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CN102538009A true CN102538009A (en) 2012-07-04

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US (1) US20120125004A1 (en)
JP (1) JP2012112642A (en)
CN (1) CN102538009A (en)
DE (1) DE102011055476A1 (en)
FR (1) FR2967754A1 (en)

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CN102840581A (en) * 2012-09-29 2012-12-26 宋涛 Premixing energy-saving cooking range
CN103697499A (en) * 2014-01-15 2014-04-02 大连海事大学 Swirler with variable swirling number
CN104019448A (en) * 2014-06-13 2014-09-03 北京北机机电工业有限责任公司 Double-layer cyclone device of heater combustor
CN104033899A (en) * 2014-06-13 2014-09-10 北京北机机电工业有限责任公司 Single-layer cyclone device for combustion chamber of heater
CN107013942A (en) * 2017-05-17 2017-08-04 大连海事大学 It is pre-mixed the gas-turbine combustion chamber of low swirl nozzle
CN109424978A (en) * 2017-08-21 2019-03-05 通用电气公司 Non-uniform mixing device for kinetics of combustion decaying
CN114738797A (en) * 2022-04-28 2022-07-12 夏语 Combustion chamber of gas turbine

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US9958161B2 (en) 2013-03-12 2018-05-01 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9541292B2 (en) 2013-03-12 2017-01-10 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9366187B2 (en) 2013-03-12 2016-06-14 Pratt & Whitney Canada Corp. Slinger combustor
US9228747B2 (en) 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9127843B2 (en) 2013-03-12 2015-09-08 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
CN104132340A (en) * 2013-05-04 2014-11-05 梁燕龙 Premixing type pressure-adjusting secondary fuel gas nozzle and method
US9416975B2 (en) 2013-09-04 2016-08-16 General Electric Company Dual fuel combustor for a gas turbine engine including a toroidal injection manifold with inner and outer sleeves
CN104515133A (en) * 2013-09-28 2015-04-15 梁燕龙 Premixed adjustable gas burner and method
US9835333B2 (en) * 2014-12-23 2017-12-05 General Electric Company System and method for utilizing cooling air within a combustor
US10228140B2 (en) * 2016-02-18 2019-03-12 General Electric Company Gas-only cartridge for a premix fuel nozzle
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KR102460672B1 (en) * 2021-01-06 2022-10-27 두산에너빌리티 주식회사 Fuel nozzle, fuel nozzle module and combustor having the same
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102840581A (en) * 2012-09-29 2012-12-26 宋涛 Premixing energy-saving cooking range
CN103697499A (en) * 2014-01-15 2014-04-02 大连海事大学 Swirler with variable swirling number
CN103697499B (en) * 2014-01-15 2016-08-17 大连海事大学 A kind of variable swirling number cyclone
CN104019448A (en) * 2014-06-13 2014-09-03 北京北机机电工业有限责任公司 Double-layer cyclone device of heater combustor
CN104033899A (en) * 2014-06-13 2014-09-10 北京北机机电工业有限责任公司 Single-layer cyclone device for combustion chamber of heater
CN107013942A (en) * 2017-05-17 2017-08-04 大连海事大学 It is pre-mixed the gas-turbine combustion chamber of low swirl nozzle
CN109424978A (en) * 2017-08-21 2019-03-05 通用电气公司 Non-uniform mixing device for kinetics of combustion decaying
CN114738797A (en) * 2022-04-28 2022-07-12 夏语 Combustion chamber of gas turbine
CN114738797B (en) * 2022-04-28 2024-04-26 广州发展南沙电力有限公司 Combustion chamber of gas turbine

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DE102011055476A1 (en) 2012-05-24
JP2012112642A (en) 2012-06-14
FR2967754A1 (en) 2012-05-25
US20120125004A1 (en) 2012-05-24

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Application publication date: 20120704