CN1144301A - 一种顺序点火的燃气涡轮机组的工作方法 - Google Patents
一种顺序点火的燃气涡轮机组的工作方法 Download PDFInfo
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- CN1144301A CN1144301A CN96108021A CN96108021A CN1144301A CN 1144301 A CN1144301 A CN 1144301A CN 96108021 A CN96108021 A CN 96108021A CN 96108021 A CN96108021 A CN 96108021A CN 1144301 A CN1144301 A CN 1144301A
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 239000007789 gas Substances 0.000 claims description 25
- 238000010304 firing Methods 0.000 claims description 24
- 239000000446 fuel Substances 0.000 claims description 9
- 239000002912 waste gas Substances 0.000 claims description 7
- 238000002485 combustion reaction Methods 0.000 abstract description 6
- 238000005086 pumping Methods 0.000 abstract 1
- 238000006073 displacement reaction Methods 0.000 description 6
- 238000009825 accumulation Methods 0.000 description 3
- 238000007599 discharging Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000000246 remedial effect Effects 0.000 description 2
- DVGKRPYUFRZAQW-UHFFFAOYSA-N 3 prime Natural products CC(=O)NC1OC(CC(O)C1C(O)C(O)CO)(OC2C(O)C(CO)OC(OC3C(O)C(O)C(O)OC3CO)C2O)C(=O)O DVGKRPYUFRZAQW-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000002650 habitual effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000003449 preventive effect Effects 0.000 description 1
- 231100000817 safety factor Toxicity 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/003—Gas-turbine plants with heaters between turbine stages
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Supercharger (AREA)
- Control Of Eletrric Generators (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
一种顺序点火的燃气涡轮机组的工作方法中，在起动时，压缩机(12)中的前级打开增大至接近压缩机的喷振极限。在该燃气涡轮机组空载时的额定转数下，前级开度不变时实现了第一燃烧室(13)的点火(2)，接着前级继续打开直至达到空载额定转数为止。在额定转数下和前级开度不变下运行时，实现第二燃烧室(15)的点火。紧接着，额定转数不变时，前级相应地进一步打开直至达到满载(6)为止。
Description
本发明涉及权利要求1前序部分所述之一种顺序点火的燃气涡轮机组的工作方法。
为了调整整个工作状态，众所周知通过一个主要由一个压缩机、一个高压燃烧室、一个低压燃烧室和一个高压一低压涡轮机构成的顺序点火的燃气涡轮机组，降低在该涡轮机组的不同位置处的特定温度，并且与此相应地改变了工作方式。输送给燃烧室的两种燃料量受如下条件限制，即必须直接控制至少每个燃烧室的热气出口温度。但是上述温度很难控制，温控的可重复性无法保证，所以借助于建立在不可靠测量基础上的燃料调节的可靠工作方式是不可信赖的。虽然实践证明，采用另一个合乎生产条件的参数并且可提供补救措施的工作方式是正确的，但该工作方式仍迫切需要温度调节，所以该工作方式适用于除公认为难以实现的动力学燃料测量外的调整。
在此，本发明将提供补救措施。如权利要求中特别指出的那样，发明任务在于，相对已有技术而采用一套可靠的调整方案，在无论是起动还是停机时，控制燃气涡轮机组的全部工作点。
发明的主要优点在于，实现该燃气涡轮机组的全部工作状态与压缩机中的至少一个前级(Vorleitreihe)结合，该前一级对上述燃气涡轮机组工作方式在两个运行方向上产生综合影响。
根据本发明的任务解决方案的进一步的合适和有利的构造将在从属权利要求中予以特别指出。
以下将根据附图进一步描述本发明的实施例。为了便于直接理解发明而省略不必要的特征。介质流动方向由箭头表示。同一部件在不同图中使用相同的参考标记。
其中，
图1是一种顺序点火的燃气涡轮机组的示意图，以及
图2是负载相对压缩机中前级位移而变化的调整曲线。
以下描述中将交替参考图1和图2。
图2是一条曲线，其中描述了图1中的燃气涡轮机组的起动、负载运行、部分负载运行。横坐标X象征性表示负载百分比，而纵坐标Y定性地表示压缩机12中的前级变化。其基本点在于，图1中的燃气涡轮机组包括一个空气压缩机12，抽进来的空气17在该压缩机中被压缩。然后压缩空气18流入第一燃烧室13，在该燃烧室13中最好通过预混合燃烧部件而准备好热气，这正如EP-B1-0321809文件所述的那样，因此该文件的理论是所述实施中不可缺少的部分。该热气19随后流入第一涡轮14，热气仅产生部分膨胀，即从中排出的废气20仍有较高温度。然后废气20流入第二燃烧室15。在该燃烧室中，因在此喷入燃料而发生点火。这又为后置的第二涡轮16又准备好一定热度的热气21。从第二涡轮16排出的废气22的剩余潜热最好通过汽化以投入后置的蒸气环路中工作或该气体返回燃气涡轮机组(STIG-运转过程)。因而对于已有的单波状蒸汽机，通过仅有的一台发电机11就可实现能量转换。
在图2中起点1处，在前级全封闭情况下起动燃气涡轮机组。在上述预防措施下，明显减少了起动功率所需的质量流量，即抽进的空气量17，并降低了涡轮叶片的交变弯曲负载。因而在开始阶段避免了潜存于压缩机12中的＂转动一腔室一单元＂。(＂Rotating-Stall-Zellen＂)首先投入使用的第一燃烧室13的合适的点火位置2是在达到点火转数时，借助于合适修正的前级位移而测定的，上述点火位置依赖于合适的空气/燃料比例，该测定值表示压缩机12的喘振极限。前级位移使得在第一燃烧室13点火2发生后，不但部分负载运行控制下的压缩量，而且满载运行下的压缩量都可选择。部分负载运行情况在以后将进一步介绍。如图2所示，在第一燃烧室13点火2后，前级位置暂时不变。随后紧接着由于前级进一步打开，空载4转数即O负载时的100％额定转数增大，由此直至较大的部分负载(如满载的50％)阶段都保持不变。然后在此能级下实现了第二燃烧室15的点火5。转数不变时，由于前级位置进一步上移，燃气涡轮机组的负载渐增至满载6，因而前级形成一定的位置移。根据控制的前级位置实现了在合适的时间点处的第二燃烧室15的点火。前级位移使以下情况成为可能，即在点火5发生后确定部分负载运行控制下的从压缩机12排出的压缩空气量18和确定满载运行时的压缩空气量。至于完成部分负载运行，是通过将前级位移与第二燃烧室15中的燃料返回量相应结合而达到的。由于上述结合，在部分负载运行时可以优化温度与效率，即不仅在燃气涡轮机组单独运行时还是在STIG-运行状态或联合运行时，能够保证第二涡轮16产生所希望的废气22的温度。通过已知的空气储备，在由前级可移位性能产生的满载时，可以实现不同保险系数的灵活性。由于前级的位移一升级跨距，可避免＂点火后的停机＂。空载4时，进行快速切断燃料，结果是机器可能由于排气阀打开和前级相对地全封闭而渐渐停转。通过气流量的节流避免了可能导致温度突变和弯曲的机器的快冷。从一个确定的最小转数起至下一个快速切断燃料工序止，前级全部关闭，即金属与金属接触地关闭住，由此可实现机器的进一步的节流和蓄热。通过上述措施，强烈要求重点保护之处在于，即由于大的势能，在这里前级令人称赞之处是它比以前惯用的前级有较短的热力循环周期。接着在停机阶段，由于前级全封闭而机器保温，并且考虑蓄热，这是因为实际情况中的机器在停机阶段没有进气。同时上述蓄热可强烈抑制流动***中的凝汽导致的腐蚀。上述优点仍然进一步明显体现于以下情况中，即现有情况中的机器在短暂停机后必须经常再起动，因而从热力周期方面考虑是很重要的。
1起动 2-第一燃烧室点火
3-前级位置 4-全转数时空载
5-第二燃烧室点火 6-全负载
7-部分负载运行 11-发电机
12-空气压缩机 13-第一燃烧室
14-第一涡轮 15-第二燃烧室
16-第二涡轮 17-抽进的空气
18-压缩空气 19-第一燃烧室产生的热气
20第一涡轮排出的废气 21-第二燃烧室产生的热气
22-第二涡轮排出的废气
X-负载百分比 Y-前级打开定性比
Claims (3)
1、一种顺序点火的燃气涡轮机组的工作方法，该涡轮机组主要由一个压缩机，一个设置在该压缩机后的第一燃烧室，上述燃烧室的热气流入后置的第一涡轮机，一个设置在该第一涡轮机后的第二燃烧室，该燃烧室的热气流入一个后置的第二涡轮机，以及至少一个发电机构成，其特征在于，起动(1)时至少一个压缩机(12)中的前级打开增大接近压缩机的喘振极限，在燃气涡轮机组空载(4)的额定转数下，当前级开度不变时发生第一燃烧室(13)的点火(2)，第一燃烧室(13)点火(2)后前级进一步打开直至达到空载(4)下的额定转数为止，运行中，在额定转数和前级开度不变情况下发生第二燃烧室(15)的点火(5)，紧接着额定转数不变时，前级逐渐打开直至达到燃气涡轮机组的满载(6)为止。
2、如权利要求1所述的方法，其特征在于，由于燃料量返回到第二燃烧室(15)，同时发生部分负载运行(7)和压缩机(12)中的前级闭合。
3、如权利要求2所述方法，其特征在于，联合运行时，由于压缩机(12)中的前级变化，第二涡轮(16)排出的废气(22)温度保持有一定的能级。
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19514991.2 | 1995-04-24 | ||
| DE19514991A DE19514991A1 (de) | 1995-04-24 | 1995-04-24 | Verfahren zum Betrieb einer sequentiell befeuerten Gasturbogruppe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1144301A true CN1144301A (zh) | 1997-03-05 |
| CN1071840C CN1071840C (zh) | 2001-09-26 |
Family
ID=7760212
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN96108021A Expired - Lifetime CN1071840C (zh) | 1995-04-24 | 1996-04-24 | 一种顺序点火的燃气涡轮机组的工作方法 |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US5661967A (zh) |
| EP (1) | EP0740057B1 (zh) |
| JP (1) | JP3828952B2 (zh) |
| KR (1) | KR960038081A (zh) |
| CN (1) | CN1071840C (zh) |
| CA (1) | CA2171271A1 (zh) |
| DE (2) | DE19514991A1 (zh) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10050248A1 (de) * | 2000-10-11 | 2002-04-18 | Alstom Switzerland Ltd | Brenner |
| WO2009118235A2 (de) * | 2008-03-28 | 2009-10-01 | Alstom Technology Ltd | Leitschaufel für eine gasturbine |
| US20110210555A1 (en) * | 2010-02-26 | 2011-09-01 | Xia Jian Y | Gas turbine driven electric power system with constant output through a full range of ambient conditions |
| US9086018B2 (en) * | 2010-04-23 | 2015-07-21 | Hamilton Sundstrand Corporation | Starting a gas turbine engine to maintain a dwelling speed after light-off |
| US9970360B2 (en) * | 2012-03-05 | 2018-05-15 | Siemens Aktiengesellschaft | Gas turbine engine configured to shape power output |
| EP4343131A1 (en) | 2022-09-23 | 2024-03-27 | General Electric Technology GmbH | Method for operating a combustion system, combustion system and gas turbine engine comprising the combustion system |
| US20240175580A1 (en) * | 2022-11-24 | 2024-05-30 | Pratt & Whitney Canada Corp. | Aircraft power plant with interburner |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3470691A (en) * | 1968-06-17 | 1969-10-07 | Avco Corp | Automatic starting and protection system for a gas turbine |
| US3974645A (en) * | 1974-08-08 | 1976-08-17 | Westinghouse Electric Corporation | Control apparatus for matching the exhaust flow of a gas turbine employed in a combined cycle electric power generating plant to the requirements of a steam generator also employed therein |
| FR2392231A1 (fr) * | 1977-05-23 | 1978-12-22 | Inst Francais Du Petrole | Turbine a gaz comportant une chambre de combustion entre les etages de la turbine |
| US4270344A (en) * | 1978-05-19 | 1981-06-02 | General Motors Corporation | Hybrid dual shaft gas turbine with accumulator |
| CH674561A5 (zh) * | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
| US5301500A (en) * | 1990-07-09 | 1994-04-12 | General Electric Company | Gas turbine engine for controlling stall margin |
| US5224337A (en) * | 1991-05-22 | 1993-07-06 | Mitsubishi Jukogyo Kabushiki Kaisha | Operating method for gas turbine with variable inlet vanes |
| JPH06129264A (ja) * | 1992-10-19 | 1994-05-10 | Nissan Motor Co Ltd | ガスタービンエンジンの制御方法 |
-
1995
- 1995-04-24 DE DE19514991A patent/DE19514991A1/de not_active Withdrawn
-
1996
- 1996-03-01 US US08/609,829 patent/US5661967A/en not_active Expired - Lifetime
- 1996-03-07 CA CA002171271A patent/CA2171271A1/en not_active Abandoned
- 1996-04-12 EP EP96810230A patent/EP0740057B1/de not_active Expired - Lifetime
- 1996-04-12 DE DE59607801T patent/DE59607801D1/de not_active Expired - Lifetime
- 1996-04-22 JP JP10041396A patent/JP3828952B2/ja not_active Expired - Lifetime
- 1996-04-23 KR KR1019960012413A patent/KR960038081A/ko not_active Application Discontinuation
- 1996-04-24 CN CN96108021A patent/CN1071840C/zh not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH08291722A (ja) | 1996-11-05 |
| US5661967A (en) | 1997-09-02 |
| DE19514991A1 (de) | 1996-10-31 |
| JP3828952B2 (ja) | 2006-10-04 |
| CN1071840C (zh) | 2001-09-26 |
| EP0740057A3 (de) | 1999-03-03 |
| CA2171271A1 (en) | 1996-10-25 |
| EP0740057B1 (de) | 2001-10-04 |
| KR960038081A (ko) | 1996-11-21 |
| DE59607801D1 (de) | 2001-11-08 |
| EP0740057A2 (de) | 1996-10-30 |
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