CN101526227A - 具有冠状混合孔的燃烧帽 - Google Patents
具有冠状混合孔的燃烧帽 Download PDFInfo
- Publication number
- CN101526227A CN101526227A CN200910126698A CN200910126698A CN101526227A CN 101526227 A CN101526227 A CN 101526227A CN 200910126698 A CN200910126698 A CN 200910126698A CN 200910126698 A CN200910126698 A CN 200910126698A CN 101526227 A CN101526227 A CN 101526227A
- Authority
- CN
- China
- Prior art keywords
- cap
- fuel nozzle
- combustion liner
- air spray
- nozzle ports
- 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.)
- Granted
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 68
- 238000002485 combustion reaction Methods 0.000 claims abstract description 46
- 239000007921 spray Substances 0.000 claims description 32
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 27
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 7
- 238000009792 diffusion process Methods 0.000 description 7
- 238000007599 discharging Methods 0.000 description 7
- 239000000203 mixture Substances 0.000 description 7
- 239000001301 oxygen Substances 0.000 description 7
- 229910052760 oxygen Inorganic materials 0.000 description 7
- 239000007789 gas Substances 0.000 description 6
- 239000003085 diluting agent Substances 0.000 description 5
- 238000011144 upstream manufacturing Methods 0.000 description 5
- 230000006872 improvement Effects 0.000 description 3
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 241001289717 Hypolimnas Species 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000047 product Substances 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000006227 byproduct Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- UHZZMRAGKVHANO-UHFFFAOYSA-M chlormequat chloride Chemical compound [Cl-].C[N+](C)(C)CCCl UHZZMRAGKVHANO-UHFFFAOYSA-M 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000007634 remodeling Methods 0.000 description 1
Images
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
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/06042—Annular arrangement of burners in a furnace, e.g. in a gas turbine, operated in alternate lean-rich mode
-
- 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
- F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
本发明涉及具有冠状混合孔的燃烧帽，具体而言，本发明提供了一种燃烧器衬套帽(112)，其包括帽中心主体部分(120)和沿该帽中心主体部分外围地限定的燃料喷嘴部分。多个燃料喷口(116)通过该燃料喷嘴部分限定，且多个空气喷孔(114)通过该帽中心主体部分，且各空气喷孔沿该衬套帽的半径方向与相应的燃料喷口对齐。
Description
技术领域
[0001]本发明涉及气态和液态燃料的涡轮机，且更具体地涉及用于发电厂的工业燃气轮机的燃烧器。
背景技术
[0002]燃气轮机通常包括压缩机，一个或多个燃烧器，燃料喷射系统和涡轮。典型地，压缩机对入口气体加压，然后使该入口气体改变方向或者反向而流向燃烧器，在燃烧器中其被用于冷却燃烧器并向燃烧过程提供空气。在多燃烧器的涡轮机中，燃烧器位于燃气轮机的周边附近，并且连接各燃烧器的出口端和涡轮的入口端的过渡导管将燃烧过程的热产物输送到涡轮。
[0003]在降低燃气轮机排气中的氮氧化物(NOx)的量的努力中，发明者Wilkes和Hilt发明了1981年10月6日颁发给本发明受让人的美国专利第4,292,801号中所示的双级、双模式燃烧器。在该前述专利中，公开了如果在燃烧器中形成两个燃烧室，则和常规的单级单燃料喷嘴燃烧器相比，所排放的NOx的量可大幅降低，使得在正常的工作负载条件下，上游即主燃烧室用作预混室，而实际的燃烧发生在下游即辅助燃烧室中。在此正常的工作条件下，主燃烧室内没有火焰(导致NOx的形成减少)，而辅助即中心喷嘴提供用于辅助燃烧器内燃烧的火焰源。该已获专利的发明的具体构造包括各燃烧器内的主喷嘴的环形阵列，其中各喷嘴向燃烧室排入；以及中央辅助喷嘴，该中央辅助喷嘴向辅助燃烧室排入。这些喷嘴都可被描述为扩散喷嘴，因为各喷嘴在其排放端处具有被空气旋流器所包围的轴向燃料供应管，该空气旋流器向燃料喷嘴排放孔供给空气。
[0004]在第4,982,570号美国专利中，公开了一种双级、双模式的燃烧器，其使用了一种组合的扩散/预混嘴作为中心定位的辅助喷嘴。在运行中，相对少量的燃料被用于维持扩散引燃，而喷嘴的预混部分则提供额外的燃料来点燃来自上游主喷嘴的被导入主燃烧室的主要燃料供应。
[0005]在后续的发展中，之前位于辅助燃烧室内扩散和预混喷嘴孔(在辅助火焰区的边界处)下游的辅助喷嘴空气旋流器被重新定位到预混喷嘴孔上游的位置，以便消除在燃烧器内与火焰的任何直接接触。
[0006]美国专利No.5,274,991公开了一种单级(单一燃烧区或燃烧带)双模式(扩散和预混)的燃烧器，其在低涡轮负载下以扩散模式工作，而在高涡轮负载下以预混模式工作。通常各燃烧器包括多个燃料喷嘴，其中各燃烧喷嘴皆类似于扩散/预混喷嘴。换言之，各喷嘴均具有环绕的专用预混部分或管道，以便在预混模式下，燃料在单个燃烧室内燃烧之前先和空气预混。以这样的方式，多个专用的预混部分或管道允许燃料和空气在燃烧之前充分混合，这最终导致低NOx水平。
[0008]更具体来说，在’991专利中，各燃烧器包括具有纵轴线的通常为圆柱形的壳体，燃烧器壳体具有彼此紧固在一起的前后段，并且燃烧壳体整体地紧固到涡轮机壳体上。各燃烧器还包括内部流套管和大致同轴地布置在该流套管内的燃烧衬套。流套管和燃烧衬套均在位于它们的前向即下游端的双层过渡导管和位于它们的后向末端处的套管帽组件(位于燃烧器的后向即上游部分内)之间延伸。流套管直接连接到燃烧器壳体上，而衬套则容纳衬套帽组件，衬套帽组件又固定在燃烧器壳体上。过渡导管的外壁和流套管的至少一部分在它们的相应表面的大部分上具有空气供给孔，从而允许压缩机空气进入燃烧衬套和流套管之间的径向空间，并反向流向燃烧器的后向即上游部分，在此处空气流向再次被反向以流入燃烧器的后向部分并流向燃烧区。
发明内容
[0008]本发明可实施为燃烧器衬套帽，该衬套帽包括帽中心主体部分和限定在帽中心主体部分周边的燃料喷嘴部分；其中通过燃料喷嘴部分限定多个燃料喷口；且其中通过帽中心主体部分限定多个空气喷孔，各所述空气喷孔沿衬套帽的半径方向与相应的燃料喷口对齐。
[0009]本发明还可实施为包含如下部件的燃烧器：燃烧器衬套；和安装到所述燃烧器衬套的一个轴向端上的燃烧器衬套帽，所述燃烧器衬套帽包括帽中心主体部分和限定在帽中心主体部分周边的燃料喷嘴部分；其中通过该燃料喷嘴部分限定多个隔开的燃料喷口；且其中通过帽中心主体部分限定多个空气喷孔，各所述空气喷孔沿衬套帽的半径方向与相应的燃料喷口对齐。
附图说明
[0010]图1图示了常规的MNQC(多喷嘴静音燃烧器)帽和衬套组件；
[0011]图2是从图1的左侧所取的燃烧衬套帽组件的后端视图；
[0012]图3是图2的燃烧器衬套帽组件的前端视图；
[0013]图4是图3的沿线4-4所取的横截面视图；
[0014]图5图示了根据本发明的一个示范实施例的MNQC帽和衬套组件；
[0015]图6是从图5的左侧所取的该燃烧器衬套帽组件的后端视图；
[0016]图7是图6的燃烧器衬套帽组件的前端视图；和
[0017]图8是图7沿线8-8所取的视图。
具体实施方式
[0018]当燃烧器核心或中心区域的氧浓度降低时，发现图1-3中示意性地图示的用于合成气体燃烧的常规MNQC帽和衬套组件会经历CO排放增加。在本发明的一个示范性实施例中，核心区域的氧浓度增加。更具体地说，通过用在中心主体上指向或对准各燃料喷口的大空气混合喷口替代跨越燃料喷嘴的常规小喷口，增高了核心区域中的氧浓度。所得的结构使得能够改善核心中的燃料气体混合，变换CO排放的发生点，增大稀释剂的喷射，加宽工作范围，并降低NOx排放。
[0019]NOx和CO降低受限于燃烧器核心区域内不充分的氧浓度。因此，通常，为了达到稳定运行的目的，同时处理满足前述排放目标所需的高稀释剂流率，燃烧器以差不多整体的方式运行。这样的状况对于达成更具进取心的排放目标是明显的障碍。因此，依据本发明，空气在新的中心主体结构中被重新分配以解决之前遇到的排放和可操作性的限制。由此，本发明提供了一种多喷嘴扩散火焰燃烧器，通过给帽中心主体冠冕增加定向的混合孔，该燃烧器通过模拟燃烧衬套区域内的燃料空气混合而可以获得更低的排放和更大的排放工作窗口。
[0020]本发明致力解决的问题对使用稀释剂来进行NOx控制的多喷嘴扩散火焰燃烧系统相当的孤立。多种其它方法如预混燃烧或使用单个的喷嘴燃烧器来使燃料起反应都是已知的。预混方法具有氧气在燃料中充分分散的优点。
[0021]常规的MNQC(多喷嘴静音燃烧器)帽12和衬套14分别如图2和1所示。图1-4中所示的常规结构使用小空气孔或喷嘴14和跨越的燃料喷嘴16，且由此将进入帽中心主体20的空气的大部分向外喷向外壁18和早已稀薄的区域。由此，常规的混合孔结构促使稀释剂和燃烧产物占据衬套核心区域并阻止通过该核心区域内降低的氧浓度而造成的CO转换。
[0022]依据本发明一个示范实施例的MNQC帽12和衬套114分别如图6和5所示。根据本发明，在帽中心主体120的冠冕上，定位有六个更大的混合孔或喷口114，每个直径大约为0.5到1.5英寸，更优选地为大约1.0英寸，而不是十二个直径为约0.375英寸的小混合孔或喷口14。各混合孔114定向成沿衬套帽的半径与相应的燃料喷口116对齐，但是如前面指出，在现有技术的图2-4的构造中，混合孔14定向成在相邻的燃料喷口16之间对齐。因此在提供了六个燃料喷口116的此实例中，空气喷孔114以60度的间隔布置而与燃料喷口116对齐。与之对比，图2-4帽的空气喷口14则以30度的间隔布置，以便从燃料喷口16的中心偏移约15度。燃料喷嘴的直径从1-8英寸的范围内变化。IGCC MNQC喷嘴典型地在2-4英寸之间。在此示范实施例中，燃料喷口116具有约为2.550英寸的直径且中心对齐，周向地位于衬套帽上的直径D2约为10.500英寸的圆上，如图2-4中所示的典型的用于16英寸衬套的常规帽一样。对于MNQC IGCC单元直径为14英寸的衬套具有在直径约为9.5英寸的圆上对齐的燃料喷口。
[0023]根据本发明，燃料和空气射流的撞击促进了燃烧衬套核心区域中的混合。在图8所示的示范实施例中，通过空气喷孔114的空气流与燃料射流成角度，在所示实施例中从图8中的喷口116的方向看去，燃料射流沿着衬套的轴向方向。具体地说，在图8所示的示范实施例中，通过空气喷孔114的空气流与燃料射流的轴向方向成约35度角。作为备选(图中未示出)，空气喷射孔可以开在与燃料喷口垂直的方向。
[0024]由更大的开口和改善的混合所提供的增加的氧气使得未燃烧的CO能够在燃烧副产物和大的稀释流遇到O2。改善的CO转化使得增加的稀释剂的量能够用于进一步降低NOx。
[0025]根据本发明提供的新颖的混合孔构造向核心区域增加了更多的空气并提供改善的混合。就技术来说，使用16英寸的MNQC衬套构造，喷射已允许达成排放性能的巨大变化。本构造对之前的设计的排放和可操作性也显示出显著改善。
[0026]尽管已经联系当前被认为最可行和优选的实施例对本发明进行了描述，但应懂得，本发明并不限于所公开的实施例，而与之相反，本发明意在覆盖包括在所附权利要求书的精神和范围内的各种改型和等效装置。因此，作为沿衬套帽的半径与各燃料喷口对齐的空气喷孔的替代方案，空气喷孔可以少于燃料喷口。例如，可有三个主空气喷孔和六个燃料喷口，且各主空气喷孔沿衬套帽的半径与燃料喷口中相应的每隔一个燃料喷口对齐，以便只有其中三个喷口与空气喷孔对齐，且这些对齐的喷口与没有对齐的喷口相互间隔。作为另一个示例，可以有四个主空气喷孔和六个燃料喷口，且各主空气喷孔沿衬套帽的半径与相应的燃料喷口对齐，以便只有其中四个喷口与空气喷孔对齐。作为上述实施例的又一备选，如有必要或需要，可在与空气喷孔对齐的主燃料喷口之间插入一个或多个辅助空气喷孔，例如具有小于主空气喷孔直径的直径的辅助空气喷孔。并且，尽管已经详尽描述和示出了具有六个燃料喷口的衬套帽，但应懂得，本发明并不限于具有六个燃料喷口的衬套帽。
Claims (10)
1.一种燃烧器衬套帽(112)，其包括帽中心主体部分(120)和沿所述帽中心主体部分外围地限定的燃料喷嘴部分；
其中，通过所述燃料喷嘴部分限定多个燃料喷口(116)；且
其中，通过所述帽中心主体部分(120)限定多个空气喷孔(114)，各所述空气喷孔沿该衬套帽的半径与相应的燃料喷口对齐。
2.如权利要求1所述的燃烧器衬套帽，其特征在于，有六个沿所述帽中心主体(120)外围地限定的燃料喷口(116)和在所述帽中心主体(120)周围限定的六个空气喷孔(114)，使得所述燃料喷口和所述空气喷孔具有位于该衬套帽的公共半径上的中心，且各个空气喷孔围绕该帽彼此隔开60度布置。
3.如权利要求1所述的燃烧器衬套帽，其特征在于，各所述空气喷孔(114)具有约为0.5-1.5英寸的直径。
4.如权利要求1所述的燃烧器衬套帽，其特征在于，各空气喷孔(114)定向为以便流经其中的空气和来自相应燃料喷口(116)的燃料相撞，藉此燃料和空气射流的撞击促使在安装有帽的燃烧器衬套的核心区域内混合。
5.如权利要求4所述的燃烧器衬套帽，其特征在于，流经所述空气喷孔(114)的空气对于相应的燃料喷口(116)成角度。
6.如权利要求5所述的燃烧器衬套帽，其特征在于，流经所述空气喷孔(114)的空气对于相应的燃料喷口(116)成约35度的角度。
7.如权利要求1所述的燃烧器衬套帽，其特征在于，所述空气喷孔(114)间隔均匀地周向布置在所述帽中心主体(120)上。
8.如权利要求1所述的燃烧器衬套帽，其特征在于，各所述燃料喷口(116)具有约2-4英寸的直径。
9.如权利要求1所述的燃烧器衬套帽，其特征在于，所述燃料喷口(116)围绕所述燃料喷嘴部分布置，使得所述燃料喷口的中心在具有大约10.50英寸直径的假想的圆上对齐。
10.一种燃烧器，包括：
燃烧器衬套；和
如权利要求1所述的安装到所述燃烧器衬套的一个轴向端上的燃烧器衬套帽(112)。
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/073407 | 2008-03-05 | ||
| US12/073,407 | 2008-03-05 | ||
| US12/073,407 US20090223227A1 (en) | 2008-03-05 | 2008-03-05 | Combustion cap with crown mixing holes |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101526227A true CN101526227A (zh) | 2009-09-09 |
| CN101526227B CN101526227B (zh) | 2013-01-16 |
Family
ID=40936474
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009101266980A Active CN101526227B (zh) | 2008-03-05 | 2009-03-05 | 具有冠状混合孔的燃烧帽 |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20090223227A1 (zh) |
| JP (1) | JP5513756B2 (zh) |
| CN (1) | CN101526227B (zh) |
| CH (1) | CH698634B1 (zh) |
| DE (1) | DE102009003572A1 (zh) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102644917A (zh) * | 2011-02-15 | 2012-08-22 | 通用电气公司 | 燃烧器和用于将二次流体导入燃料喷嘴中的方法 |
| CN102679341A (zh) * | 2011-02-21 | 2012-09-19 | 通用电气公司 | 用于将流体喷射到燃烧器的燃烧室中的设备 |
| CN107023834A (zh) * | 2017-04-19 | 2017-08-08 | 中国科学院工程热物理研究所 | 一种多尺度值班火焰的喷嘴及燃烧器 |
| CN113739203A (zh) * | 2021-09-13 | 2021-12-03 | 中国联合重型燃气轮机技术有限公司 | 用于燃烧器的罩帽组件 |
Families Citing this family (85)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2934541C (en) | 2008-03-28 | 2018-11-06 | Exxonmobil Upstream Research Company | Low emission power generation and hydrocarbon recovery systems and methods |
| CN104098070B (zh) | 2008-03-28 | 2016-04-13 | 埃克森美孚上游研究公司 | 低排放发电和烃采收系统及方法 |
| SG195533A1 (en) | 2008-10-14 | 2013-12-30 | Exxonmobil Upstream Res Co | Methods and systems for controlling the products of combustion |
| US8763399B2 (en) * | 2009-04-03 | 2014-07-01 | Hitachi, Ltd. | Combustor having modified spacing of air blowholes in an air blowhole plate |
| WO2011036205A1 (de) * | 2009-09-24 | 2011-03-31 | Siemens Aktiengesellschaft | Brennstoffleitungssystem, verfahren zum betrieb einer gasturbine und ein verfahren zum spülen des brennstoffleitungssystems einer gasturbine |
| MX341477B (es) | 2009-11-12 | 2016-08-22 | Exxonmobil Upstream Res Company * | Sistemas y métodos de generación de potencia de baja emisión y recuperación de hidrocarburos. |
| EP2588729B1 (en) | 2010-07-02 | 2020-07-15 | Exxonmobil Upstream Research Company | Low emission triple-cycle power generation systems and methods |
| MY160832A (en) | 2010-07-02 | 2017-03-31 | Exxonmobil Upstream Res Co | Stoichiometric combustion with exhaust gas recirculation and direct contact cooler |
| EA029523B1 (ru) | 2010-07-02 | 2018-04-30 | Эксонмобил Апстрим Рисерч Компани | Интегрированная система производства энергии и снижения выбросов co |
| CA2801494C (en) | 2010-07-02 | 2018-04-17 | Exxonmobil Upstream Research Company | Stoichiometric combustion of enriched air with exhaust gas recirculation |
| US8322143B2 (en) * | 2011-01-18 | 2012-12-04 | General Electric Company | System and method for injecting fuel |
| US8365534B2 (en) | 2011-03-15 | 2013-02-05 | General Electric Company | Gas turbine combustor having a fuel nozzle for flame anchoring |
| TWI593872B (zh) | 2011-03-22 | 2017-08-01 | 艾克頌美孚上游研究公司 | 整合系統及產生動力之方法 |
| TWI563166B (en) | 2011-03-22 | 2016-12-21 | Exxonmobil Upstream Res Co | Integrated generation systems and methods for generating power |
| TWI564474B (zh) | 2011-03-22 | 2017-01-01 | 艾克頌美孚上游研究公司 | 於渦輪系統中控制化學計量燃燒的整合系統和使用彼之產生動力的方法 |
| TWI563165B (en) | 2011-03-22 | 2016-12-21 | Exxonmobil Upstream Res Co | Power generation system and method for generating power |
| US9103551B2 (en) | 2011-08-01 | 2015-08-11 | General Electric Company | Combustor leaf seal arrangement |
| WO2013095829A2 (en) | 2011-12-20 | 2013-06-27 | Exxonmobil Upstream Research Company | Enhanced coal-bed methane production |
| CA2868732C (en) * | 2012-03-29 | 2017-02-14 | Exxonmobil Upstream Research Company | Turbomachine combustor assembly |
| US9353682B2 (en) | 2012-04-12 | 2016-05-31 | General Electric Company | Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation |
| US20130276450A1 (en) | 2012-04-24 | 2013-10-24 | General Electric Company | Combustor apparatus for stoichiometric combustion |
| US10273880B2 (en) | 2012-04-26 | 2019-04-30 | General Electric Company | System and method of recirculating exhaust gas for use in a plurality of flow paths in a gas turbine engine |
| US9784185B2 (en) | 2012-04-26 | 2017-10-10 | General Electric Company | System and method for cooling a gas turbine with an exhaust gas provided by the gas turbine |
| US20130305725A1 (en) * | 2012-05-18 | 2013-11-21 | General Electric Company | Fuel nozzle cap |
| US20130305739A1 (en) * | 2012-05-18 | 2013-11-21 | General Electric Company | Fuel nozzle cap |
| US9212822B2 (en) | 2012-05-30 | 2015-12-15 | General Electric Company | Fuel injection assembly for use in turbine engines and method of assembling same |
| US9599070B2 (en) | 2012-11-02 | 2017-03-21 | General Electric Company | System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system |
| US10100741B2 (en) | 2012-11-02 | 2018-10-16 | General Electric Company | System and method for diffusion combustion with oxidant-diluent mixing in a stoichiometric exhaust gas recirculation gas turbine system |
| US9631815B2 (en) | 2012-12-28 | 2017-04-25 | General Electric Company | System and method for a turbine combustor |
| US10215412B2 (en) | 2012-11-02 | 2019-02-26 | General Electric Company | System and method for load control with diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system |
| US9869279B2 (en) | 2012-11-02 | 2018-01-16 | General Electric Company | System and method for a multi-wall turbine combustor |
| US10107495B2 (en) | 2012-11-02 | 2018-10-23 | General Electric Company | Gas turbine combustor control system for stoichiometric combustion in the presence of a diluent |
| US9708977B2 (en) | 2012-12-28 | 2017-07-18 | General Electric Company | System and method for reheat in gas turbine with exhaust gas recirculation |
| US9574496B2 (en) | 2012-12-28 | 2017-02-21 | General Electric Company | System and method for a turbine combustor |
| US9611756B2 (en) | 2012-11-02 | 2017-04-04 | General Electric Company | System and method for protecting components in a gas turbine engine with exhaust gas recirculation |
| US9803865B2 (en) | 2012-12-28 | 2017-10-31 | General Electric Company | System and method for a turbine combustor |
| US9599343B2 (en) * | 2012-11-28 | 2017-03-21 | General Electric Company | Fuel nozzle for use in a turbine engine and method of assembly |
| US10208677B2 (en) | 2012-12-31 | 2019-02-19 | General Electric Company | Gas turbine load control system |
| US9581081B2 (en) | 2013-01-13 | 2017-02-28 | General Electric Company | System and method for protecting components in a gas turbine engine with exhaust gas recirculation |
| US9512759B2 (en) | 2013-02-06 | 2016-12-06 | General Electric Company | System and method for catalyst heat utilization for gas turbine with exhaust gas recirculation |
| US9938861B2 (en) | 2013-02-21 | 2018-04-10 | Exxonmobil Upstream Research Company | Fuel combusting method |
| TW201502356A (zh) | 2013-02-21 | 2015-01-16 | Exxonmobil Upstream Res Co | 氣渦輪機排氣中氧之減少 |
| RU2637609C2 (ru) | 2013-02-28 | 2017-12-05 | Эксонмобил Апстрим Рисерч Компани | Система и способ для камеры сгорания турбины |
| US9618261B2 (en) | 2013-03-08 | 2017-04-11 | Exxonmobil Upstream Research Company | Power generation and LNG production |
| US20140250945A1 (en) | 2013-03-08 | 2014-09-11 | Richard A. Huntington | Carbon Dioxide Recovery |
| EP2964735A1 (en) | 2013-03-08 | 2016-01-13 | Exxonmobil Upstream Research Company | Power generation and methane recovery from methane hydrates |
| TW201500635A (zh) | 2013-03-08 | 2015-01-01 | Exxonmobil Upstream Res Co | 處理廢氣以供用於提高油回收 |
| US9617914B2 (en) | 2013-06-28 | 2017-04-11 | General Electric Company | Systems and methods for monitoring gas turbine systems having exhaust gas recirculation |
| US9835089B2 (en) | 2013-06-28 | 2017-12-05 | General Electric Company | System and method for a fuel nozzle |
| TWI654368B (zh) | 2013-06-28 | 2019-03-21 | 美商艾克頌美孚上游研究公司 | 用於控制在廢氣再循環氣渦輪機系統中的廢氣流之系統、方法與媒體 |
| US9631542B2 (en) | 2013-06-28 | 2017-04-25 | General Electric Company | System and method for exhausting combustion gases from gas turbine engines |
| US9587510B2 (en) | 2013-07-30 | 2017-03-07 | General Electric Company | System and method for a gas turbine engine sensor |
| US9903588B2 (en) | 2013-07-30 | 2018-02-27 | General Electric Company | System and method for barrier in passage of combustor of gas turbine engine with exhaust gas recirculation |
| US9951658B2 (en) | 2013-07-31 | 2018-04-24 | General Electric Company | System and method for an oxidant heating system |
| US9273868B2 (en) * | 2013-08-06 | 2016-03-01 | General Electric Company | System for supporting bundled tube segments within a combustor |
| US10030588B2 (en) | 2013-12-04 | 2018-07-24 | General Electric Company | Gas turbine combustor diagnostic system and method |
| US9752458B2 (en) | 2013-12-04 | 2017-09-05 | General Electric Company | System and method for a gas turbine engine |
| US10227920B2 (en) | 2014-01-15 | 2019-03-12 | General Electric Company | Gas turbine oxidant separation system |
| US9915200B2 (en) | 2014-01-21 | 2018-03-13 | General Electric Company | System and method for controlling the combustion process in a gas turbine operating with exhaust gas recirculation |
| US9863267B2 (en) | 2014-01-21 | 2018-01-09 | General Electric Company | System and method of control for a gas turbine engine |
| US10079564B2 (en) | 2014-01-27 | 2018-09-18 | General Electric Company | System and method for a stoichiometric exhaust gas recirculation gas turbine system |
| US10047633B2 (en) | 2014-05-16 | 2018-08-14 | General Electric Company | Bearing housing |
| US10655542B2 (en) | 2014-06-30 | 2020-05-19 | General Electric Company | Method and system for startup of gas turbine system drive trains with exhaust gas recirculation |
| US10060359B2 (en) | 2014-06-30 | 2018-08-28 | General Electric Company | Method and system for combustion control for gas turbine system with exhaust gas recirculation |
| US9885290B2 (en) | 2014-06-30 | 2018-02-06 | General Electric Company | Erosion suppression system and method in an exhaust gas recirculation gas turbine system |
| JP2017530329A (ja) * | 2014-09-11 | 2017-10-12 | シーメンス エナジー インコーポレイテッド | ガスタービンエンジン用の合成ガスバーナシステム |
| US9819292B2 (en) | 2014-12-31 | 2017-11-14 | General Electric Company | Systems and methods to respond to grid overfrequency events for a stoichiometric exhaust recirculation gas turbine |
| US9869247B2 (en) | 2014-12-31 | 2018-01-16 | General Electric Company | Systems and methods of estimating a combustion equivalence ratio in a gas turbine with exhaust gas recirculation |
| US10788212B2 (en) | 2015-01-12 | 2020-09-29 | General Electric Company | System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation |
| US10253690B2 (en) | 2015-02-04 | 2019-04-09 | General Electric Company | Turbine system with exhaust gas recirculation, separation and extraction |
| US10316746B2 (en) | 2015-02-04 | 2019-06-11 | General Electric Company | Turbine system with exhaust gas recirculation, separation and extraction |
| US10094566B2 (en) | 2015-02-04 | 2018-10-09 | General Electric Company | Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation |
| US10267270B2 (en) | 2015-02-06 | 2019-04-23 | General Electric Company | Systems and methods for carbon black production with a gas turbine engine having exhaust gas recirculation |
| US10145269B2 (en) | 2015-03-04 | 2018-12-04 | General Electric Company | System and method for cooling discharge flow |
| US10480792B2 (en) | 2015-03-06 | 2019-11-19 | General Electric Company | Fuel staging in a gas turbine engine |
| US10245600B2 (en) | 2015-04-09 | 2019-04-02 | Nex Flow Air Products Corp. | Blowing nozzle |
| US10690350B2 (en) * | 2016-11-28 | 2020-06-23 | General Electric Company | Combustor with axially staged fuel injection |
| US11156362B2 (en) | 2016-11-28 | 2021-10-26 | General Electric Company | Combustor with axially staged fuel injection |
| US11371702B2 (en) | 2020-08-31 | 2022-06-28 | General Electric Company | Impingement panel for a turbomachine |
| US11994292B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus for turbomachine |
| US11994293B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus support structure and method of manufacture |
| US11614233B2 (en) | 2020-08-31 | 2023-03-28 | General Electric Company | Impingement panel support structure and method of manufacture |
| US11460191B2 (en) | 2020-08-31 | 2022-10-04 | General Electric Company | Cooling insert for a turbomachine |
| US11255545B1 (en) | 2020-10-26 | 2022-02-22 | General Electric Company | Integrated combustion nozzle having a unified head end |
| US11767766B1 (en) | 2022-07-29 | 2023-09-26 | General Electric Company | Turbomachine airfoil having impingement cooling passages |
Family Cites Families (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2676460A (en) * | 1950-03-23 | 1954-04-27 | United Aircraft Corp | Burner construction of the can-an-nular type having means for distributing airflow to each can |
| US4100733A (en) * | 1976-10-04 | 1978-07-18 | United Technologies Corporation | Premix combustor |
| US4292801A (en) * | 1979-07-11 | 1981-10-06 | General Electric Company | Dual stage-dual mode low nox combustor |
| US4344280A (en) * | 1980-01-24 | 1982-08-17 | Hitachi, Ltd. | Combustor of gas turbine |
| US4982570A (en) | 1986-11-25 | 1991-01-08 | General Electric Company | Premixed pilot nozzle for dry low Nox combustor |
| JP2528894B2 (ja) * | 1987-09-04 | 1996-08-28 | 株式会社日立製作所 | ガスタ―ビン燃焼器 |
| US5220795A (en) * | 1991-04-16 | 1993-06-22 | General Electric Company | Method and apparatus for injecting dilution air |
| DE69306025T2 (de) * | 1992-03-30 | 1997-05-28 | Gen Electric | Konstruktion eines Brennkammerdomes |
| US5274991A (en) * | 1992-03-30 | 1994-01-04 | General Electric Company | Dry low NOx multi-nozzle combustion liner cap assembly |
| US5329772A (en) * | 1992-12-09 | 1994-07-19 | General Electric Company | Cast slot-cooled single nozzle combustion liner cap |
| JP3392633B2 (ja) * | 1996-05-15 | 2003-03-31 | 三菱重工業株式会社 | 燃焼器 |
| JP3709671B2 (ja) * | 1997-09-29 | 2005-10-26 | 株式会社日立製作所 | ガスタービン燃焼器 |
| US6272840B1 (en) * | 2000-01-13 | 2001-08-14 | Cfd Research Corporation | Piloted airblast lean direct fuel injector |
| US6530221B1 (en) * | 2000-09-21 | 2003-03-11 | Siemens Westinghouse Power Corporation | Modular resonators for suppressing combustion instabilities in gas turbine power plants |
| US6438959B1 (en) * | 2000-12-28 | 2002-08-27 | General Electric Company | Combustion cap with integral air diffuser and related method |
| DE10217913B4 (de) * | 2002-04-23 | 2004-10-07 | WS Wärmeprozesstechnik GmbH | Gasturbine mit Brennkammer zur flammenlosen Oxidation |
| US6672073B2 (en) * | 2002-05-22 | 2004-01-06 | Siemens Westinghouse Power Corporation | System and method for supporting fuel nozzles in a gas turbine combustor utilizing a support plate |
| US6840048B2 (en) * | 2002-09-26 | 2005-01-11 | General Electric Company | Dynamically uncoupled can combustor |
| US7185494B2 (en) * | 2004-04-12 | 2007-03-06 | General Electric Company | Reduced center burner in multi-burner combustor and method for operating the combustor |
| US20060130486A1 (en) * | 2004-12-17 | 2006-06-22 | Danis Allen M | Method and apparatus for assembling gas turbine engine combustors |
-
2008
- 2008-03-05 US US12/073,407 patent/US20090223227A1/en not_active Abandoned
-
2009
- 2009-03-02 CH CH00309/09A patent/CH698634B1/de not_active IP Right Cessation
- 2009-03-04 JP JP2009050176A patent/JP5513756B2/ja active Active
- 2009-03-05 DE DE102009003572A patent/DE102009003572A1/de not_active Ceased
- 2009-03-05 CN CN2009101266980A patent/CN101526227B/zh active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102644917A (zh) * | 2011-02-15 | 2012-08-22 | 通用电气公司 | 燃烧器和用于将二次流体导入燃料喷嘴中的方法 |
| CN102679341A (zh) * | 2011-02-21 | 2012-09-19 | 通用电气公司 | 用于将流体喷射到燃烧器的燃烧室中的设备 |
| CN107023834A (zh) * | 2017-04-19 | 2017-08-08 | 中国科学院工程热物理研究所 | 一种多尺度值班火焰的喷嘴及燃烧器 |
| CN107023834B (zh) * | 2017-04-19 | 2019-01-08 | 中国科学院工程热物理研究所 | 一种多尺度值班火焰的喷嘴及燃烧器 |
| CN113739203A (zh) * | 2021-09-13 | 2021-12-03 | 中国联合重型燃气轮机技术有限公司 | 用于燃烧器的罩帽组件 |
Also Published As
| Publication number | Publication date |
|---|---|
| DE102009003572A1 (de) | 2009-09-10 |
| CH698634A2 (de) | 2009-09-15 |
| JP2009210260A (ja) | 2009-09-17 |
| CN101526227B (zh) | 2013-01-16 |
| JP5513756B2 (ja) | 2014-06-04 |
| CH698634B1 (de) | 2013-05-15 |
| US20090223227A1 (en) | 2009-09-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101526227B (zh) | 具有冠状混合孔的燃烧帽 | |
| US7546735B2 (en) | Low-cost dual-fuel combustor and related method | |
| CN101713548B (zh) | 用于副燃料喷嘴的管状燃料喷射器 | |
| US7757491B2 (en) | Fuel nozzle for a gas turbine engine and method for fabricating the same | |
| US7908863B2 (en) | Fuel nozzle for a gas turbine engine and method for fabricating the same | |
| CN103080653B (zh) | 燃气涡轮燃烧器及燃气涡轮 | |
| US9562690B2 (en) | Swirler, fuel and air assembly and combustor | |
| JP6557463B2 (ja) | 予混合パイロットノズルを備える燃料噴射器 | |
| US6092363A (en) | Low Nox combustor having dual fuel injection system | |
| US10502426B2 (en) | Dual fuel injectors and methods of use in gas turbine combustor | |
| US20080078183A1 (en) | Liquid fuel enhancement for natural gas swirl stabilized nozzle and method | |
| CN101793408A (zh) | 燃烧器喷嘴 | |
| JP6940393B2 (ja) | ノズル | |
| CN105705863B (zh) | 用于燃料喷嘴的液体燃料筒 | |
| CN101886808A (zh) | 带预混合直接喷射辅助燃料喷嘴的干式低NOx燃烧系统 | |
| JP5925442B2 (ja) | 燃料ノズル及びこれを含む組立体並びにガスタービン | |
| CN102330978A (zh) | 耐火焰副燃料喷嘴 | |
| JPH07305848A (ja) | 燃料ノズル・アセンブリ、ガスタービン装置及び低ＮＯｘガスタービン装置における燃焼不安定性を低減する方法 | |
| JP2011196681A (ja) | 予混合一次燃料ノズルアセンブリを有する燃焼器 | |
| JP6940394B2 (ja) | ノズル | |
| EP3336434B1 (en) | Dual fuel radial flow nozzle for a gas turbine | |
| CN109708148B (zh) | 一种燃气轮机燃烧器双级径向旋流器 | |
| CN103822230A (zh) | 一种低旋流燃烧室喷嘴 | |
| CN111043625A (zh) | 一种微型燃气轮机的燃烧室及微型燃气轮机 | |
| CN110686274A (zh) | 一种分层部分预混燃烧室主燃级空气雾化装置 |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231227 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York, United States Patentee before: General Electric Co. |
|
| TR01 | Transfer of patent right |