CN1071405C - 燃气涡轮机组的控制方法 - Google Patents

燃气涡轮机组的控制方法 Download PDF

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CN1071405C
CN1071405C CN95106367A CN95106367A CN1071405C CN 1071405 C CN1071405 C CN 1071405C CN 95106367 A CN95106367 A CN 95106367A CN 95106367 A CN95106367 A CN 95106367A CN 1071405 C CN1071405 C CN 1071405C
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firing chamber
temperature
fuel
turbo machine
gas turbine
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CN1116274A (zh
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R·阿尔特豪斯
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General Electric Technology GmbH
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Sweden General Electric Brown Boveri AG
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    • 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
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Regulation And Control Of Combustion (AREA)
  • Control Of Turbines (AREA)

Abstract

在一个由最好经两个下游各接有一涡轮机的燃料室(4，9)进行顺序燃烧驱动的燃气涡轮机组中，在紧靠第二燃烧室(9)中自燃点前面处测量第一涡轮机(5)的排气(8)的温度，以便调节第一燃料室(4)的燃料量。利用一体地装于第二燃烧室(9)的燃料喷管(16)中的热电偶(17)测量温度，同时用测得的温度对第二燃烧室(9)的燃料量(10)进行控制。

Description

燃气涡轮机组的控制方法
本发明涉及一种燃气涡轮机组的控制方法以及实施上述方法的燃气涡轮机组。
在顺序燃烧的燃气涡轮机组中，例如带有两个燃烧室的燃气涡轮机组中，将一个燃烧室设置在高压侧，而将另一个燃烧室设置在低压侧，这就牵涉到要根据温度测量来控制两部分燃料的分配量。为了能对上述燃料量适当地进行控制，必须测量从各燃烧室流出的热气流的温度。对新一代的燃气涡轮机组而言，热气流温度相当高，通常大大超过1100℃(有上升的趋势)，因此，随着温度上升，很难对温度进行测量。而且，在整个检测期间，不能确保测量的重复性，因此，根据这种测量结果对燃料进行控制是没有保障的。
本发明将设法解决上述问题。本发明的目的是提供一种控制燃料量的方法和本文开始所提到的那种燃气涡轮机组，为了检测温度必须在现场对供给不同燃烧室的燃料量进行控制，并确保在技术上切实可行而且具有重复性。
本发明的主要优点在于从现有的控制方案出发，只需很容易地检测高压涡轮机下游的温度。至于为了进行控制可能需要的其他参数(如过程压力等)可按现有技术中已描述的公知原理进行测量。
按照本发明的方法，从测出的高压涡轮机下游的温度可直接推断出高压燃烧室中的温度，因而，可根据在低压燃烧室内测得的温度信号直接控制供给高压燃烧室的燃料量。同时，在低温燃烧室内直接测得的高压涡轮机的排气温度可作为对低压燃烧室燃料控制的信息，从而也可以对点火有目的地采取措施。一方面借助于按本发明所测量的温度对高压燃烧室产生作用，另一方面也对低压燃烧室运行所需的燃料量进行控制。
这对于顺序燃烧尤其重要，在此燃烧过程中，低压燃烧室必须按自燃过程工作。在这种结构中，必须保证维持引起自燃所需的最低温度。
本发明技术方案的有利且适宜的改进结构体现在其它从属权利要求中。
下面参照附图对本发明进行详细描述，图中省略了所有对于直接理解本发明并非必需的部件，图中的箭头表示介质的流动方向。
唯一的一幅附图表示顺序燃烧的燃气涡轮机组的一部分。
现在参照附图，该图示出了燃气涡轮机组的一部分，即包括顺序燃烧的那些部分。从压缩机系统(未示出)流出的压缩空气流入用燃料2运行的预混燃烧器3，如欧洲专利EP-A1-0321809中所描述的那样，此文献是本说明书不可缺少的组成部分。接着，在结构为环形燃烧室的高压燃烧室4中形成第一热气流。在高压燃烧室4下游运行的是第一涡轮机，即高压涡轮机5，在高压燃烧室4中形成的热气流6在高压涡轮机5内部分膨胀。从这种连接关系中可看出，在高压涡轮机5的动叶列的上游，导叶列7作用于高压燃烧室4的端部。上述局部膨胀的特点是使高压涡轮机5的排气8仍具有较高的温度。相应地，上述高压涡轮机5包括几级动叶片，最好包括1-3级动叶片。在高压涡轮机5下游运行的是第二燃烧室，即低压燃烧室9，它根据自燃原理工作。低压燃烧室9的形状大体是可使流体流过的环形管道，最好将一股气态燃料10喷入该管道。当高压涡轮机5的排气8的温度达850℃时，喷入的燃料10发生自燃。低压燃料室9基本上被分成预混区11和燃烧区12，其中，预混区11有一排涡旋件(未示出)。这些涡旋件有利于阻止焰锋倒流。大致在低压燃料室9的预混区11的端部沿其四周分布有一些燃料喷管16，它们的作用是喷射燃料10。连接在低压燃料室9下游的是低压涡轮机(未示出)，除了发电机，燃气轮机组的整个结构安装在单根公共的转轴13上，图中示出了轴线14。这种结构的优点是可用一个外壳15盖住。外壳上有一通孔，以便使燃料喷管16穿过。为了避免外壳15上的其它通孔，将用于测量低压燃烧室9中排气8的温度的热电偶17装于燃料喷管16中。燃料喷管16的通孔同时还可用作温度测量线18的入口。然后，在测量/控制系统19中对测量信号进行分析，以便对燃料调节器20发出相应的指令。燃料喷管16同时被用来容纳热电偶17，这既可以不必在外壳15上加工另外的通孔，又便于更换出现故障的热电偶17，尤其是安装和拆卸更加方便。除上述实用的优点外，该测量点同时也是低压燃料室9中的最佳温度取样点。原则上热气流6的温度不会接近热力学极限，相反，该极限由受进气冲击的高压涡轮机5及其机械部件预先确定。此外，预混区11应具有较强的冷却作用，使得在通过测量低压燃烧室9中温度对燃料进行调节的过程中可以考虑到某些无法估计的因素。上面所建议的紧靠低压燃烧室9中自燃点前面的温度测量点可测出该处排气8的实际温度，并可使人们立即得知该温度究竟是否能引起自燃，这一点对于此文所描述的顺序燃烧是十分重要的。借助于对高压燃烧室4的动态燃料控制可对过高或过低排气8的温度进行调整，在这种情况下，高压燃烧室4中所产生的热气6的温度过高同样会对高压涡轮机5的低压燃烧室9的预混区11产生不良影响。采用上述原理还有另一个优点是：通过在每一个燃料喷管16中安装热电偶17，可对由燃料喷管16所构成的每个燃烧器进行独立的温度控制，因此，可对燃料10进行特定的控制。因此，通过对一个中等热负荷点处的单一的温度控制就可对各种燃烧所需要的燃料进行目标控制。

Claims (3)

1．一种燃气涡轮机组的控制方法，上述燃气涡轮机组主要包括一个压缩机部件、一个安装在上述压缩机部件下游的第一燃烧室、一台设置在第一燃烧室下游的第一涡轮机、一个设置在上述第一涡轮机下游、以自燃方式运行的第二燃烧室，该燃烧室的热气流冲击第二涡轮机，还包括至少一台发电机，其特征在于，通过在紧靠第二燃烧室(9)中自燃点前面处测量第一涡轮机(5)的排气(8)的温度至少对第一燃烧室(4)的燃料量的配给进行控制。
2．按照权利要求1所述的方法，其特征在于，通过测量第一涡轮机(5)的排气(8)的温度来控制第二燃烧室(9)的燃料量。
3．实施按照权利要求1所述方法的燃气涡轮机组，该燃气涡轮机组主要包括一个压缩机部件，一个安装在上述压缩机部件下游的第一燃料室、一台设置在上述第一燃烧室下游的第一涡轮机、一个设置在上述第一涡轮机下游的第二燃烧室、一台设置在第二燃烧室下游的涡轮机以及至少一台发电机，其特征在于，第二燃烧室装有沿四周分布的燃料喷管(16)；至少一个燃料喷管(16)与测量该处的优势温度的热电偶(17)成一整体。
CN95106367A 1994-05-26 1995-05-25 燃气涡轮机组的控制方法 Expired - Lifetime CN1071405C (zh)

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CH01630/94A CH688899A5 (de) 1994-05-26 1994-05-26 Verfahren zur Regelung einer Gasturbogruppe.
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DE4422701A1 (de) 1995-11-30
GB2289721A (en) 1995-11-29
CN1116274A (zh) 1996-02-07
GB9507589D0 (en) 1995-05-31
JP3737159B2 (ja) 2006-01-18
JPH07317567A (ja) 1995-12-05
GB2289721B (en) 1998-03-18
US5617718A (en) 1997-04-08
CH688899A5 (de) 1998-05-15
DE4422701B4 (de) 2010-05-12

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