CN1890455A - 燃气轮机的可变喷嘴 - Google Patents

燃气轮机的可变喷嘴 Download PDF

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CN1890455A
CN1890455A CNA2004800359964A CN200480035996A CN1890455A CN 1890455 A CN1890455 A CN 1890455A CN A2004800359964 A CNA2004800359964 A CN A2004800359964A CN 200480035996 A CN200480035996 A CN 200480035996A CN 1890455 A CN1890455 A CN 1890455A
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G·萨萨内利
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Nuovo Pignone Technologie SRL
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/20—Special functions
    • F05D2200/22—Power
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/20—Special functions
    • F05D2200/22—Power
    • F05D2200/221—Square power
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/20—Special functions
    • F05D2200/22—Power
    • F05D2200/222—Cubic power
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/20—Special functions
    • F05D2200/24—Special functions exponential
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/20—Special functions
    • F05D2200/25—Hyperbolic trigonometric, e.g. sinh, cosh, tanh
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/301—Cross-sectional characteristics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/16—Two-dimensional parabolic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/17—Two-dimensional hyperbolic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
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    • F05D2250/712—Shape curved concave
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

一种固定到轴(11)上的燃气轮机的可变喷嘴(10)，所述喷嘴(10)具有上压力面(12)和与上表面(12)相对的下负压面，可变喷嘴包括一系列大致呈“C”形的剖面，每一剖面具有第一修圆端和第二修圆端，所述系列剖面中的每一剖面还具有带有向上正对着底部(90)的凹部，并且每一剖面沿着曲线(60)在轴(11)的轴线方向上彼此连续布置，至少为二次的曲线(60)位于表面(70)上，其中所述表面(70)的轴线与轴(11)的轴线正交，并且所述表面(70)还以一个角度(80)相对于底部(90)倾斜布置。

Description

燃气轮机的可变喷嘴
技术领域
本发明涉及一种燃气轮机的喷嘴，特别是可用于动力涡轮机的第一级中的喷嘴。
本发明涉及一种双轴式燃气轮机，并且特别地是涉及一种低压涡轮机的可变喷嘴。
背景技术
通常在双轴式涡轮机中，由压气机加压的空气与可燃流体混合并被喷射到燃烧室中以产生热的燃烧气体。
燃烧气体流经高压涡轮机的喷嘴，其中所述喷嘴使这些燃烧气体分流并加速。
在高压涡轮机的下游处，气体随后流经低压涡轮机，其中所述低压涡轮机提取剩余的能量以供给用户。
用于机械操作的燃气轮机可具有固定或者可变喷嘴，该喷嘴位于低压涡轮机的第一级内。
当使用可变喷嘴时，可获得高操作性能的涡轮机，同时使污染排放物和涡轮机的效率尽可能地保持恒定。
另外，固定喷嘴的特征在于具有较高的空气动力学效率，然而，却伴随着燃气轮机的低操作性能。
对于可变喷嘴，必须存在允许其旋转的间隙。
可变喷嘴具有被热燃烧气体接触的两个表面，它们彼此相对，其中一个为压力面，而另一个为负压面。
可变喷嘴的一个缺点就是，由于燃烧气体流经间隙所造成的压降而产生的空气动力学效率的损失，同时，在所述间隙上还会产生二次损失，而所述二次损失主要是由于压力面和负压面之间的压差造成的。
发明内容
本发明的目的就在于提供一种燃气轮机的可变喷嘴，这种喷嘴具有与固定喷嘴类似的改进的性能，同时以其流量(flow-rate)的改变保持燃气轮机的高操作性能。
本发明的另一目的在于，提供一种用于燃气轮机的可靠的可变喷嘴。
本发明的这些目的通过提供一种如权利要求1所示例的燃气轮机的可变喷嘴而达到。
本发明的其它特征在从属权利要求中表示。
附图说明
参照附图，本发明的燃气轮机可变喷嘴的特征和优点在以下示意性的、非限制性的说明中更为明显，其中所述附图为：
图1为本发明的可变喷嘴的正视图；
图2为沿着通过可变喷嘴上端的线II-II剖开的图1中的喷嘴的正剖面图；
图3为沿着通过可变喷嘴中部的线III-III剖开的图1中的喷嘴的正剖面图；
图4为沿着通过可变喷嘴轮毂的线IV-IV剖开的图1中的喷嘴的正剖面图；
图5为图1中喷嘴的透视图；
图6为图1中喷嘴的仰视图；
图7为图1中喷嘴的侧视图；
图8为图1中喷嘴的俯视图；
图9为从图1中喷嘴底部看去的后视图。
具体实施方式
参照这些附图，它们示出了固定到轴11上并且能够在致动装置的作用下绕自身轴线旋转的可变喷嘴10，其中所述致动装置在附图中未示出。
成形的可变喷嘴10适用于使压降最小化，并且因此提高燃气轮机的效率。
所述可变喷嘴10包括一系列剖面，这些剖面优选地为可变的大致为“C”形的剖面，它们全部朝着同一个方向，并且优选地是带有向上正对着底部90的凹部。
根据具有平行于轴11轴线的轴线的表面，所述系列剖面的每一剖面代表着可变喷嘴10的剖面。
所述系列剖面的每一剖面具有第一修圆端20和第二修圆端21。
所述系列剖面的每一剖面的第一端20根据至少为二次的曲线(second degree curved line)60沿着轴11的轴线布置。
所述系列剖面沿着轴11的轴线布置并且分别限定了两个表面，即上压力面12和相对的下负压面14，这两个表面都与热的燃烧气体接触。
热气流F的压力作用于上表面12上，而相对的下表面14处于负压状态。
上表面12为鞍形并且其鞍点与可变喷嘴10的中部对应。
因此，上表面12在与轴11的轴线平行的方向上为凸形，而在与所述轴线正交的方向上，为凹形，所有的剖面基本上呈“C”形。
可变喷嘴10具有第一端部17、第二中部18和第三轮毂部19。
第一部分17和第三部分分别包括端部30和轮毂部50，它们具有最小的空气动力学压降，因此提高了可变喷嘴10的空气动力学效率。
此外，总是分别与所述端部30和所述轮毂部50对应的上压力面12和下负压面14之间产生的压差达到最小化并且因此二次空气动力学损失也达到最小。
这样，引导燃烧气体流穿过间隙的作用力也得到减小。
另一方面，第二中部18包括中间部40。
在第二中部18上不会存在边缘效应或者二次损失，并且因此可变喷嘴10该部分内的空气动力学效率将更大。
为此，由于第二中部18的空气动力学效率更大，因此，可变喷嘴10这样成形以提高其上的空气动力学负载(charge)。
这些结果在燃气轮机的运行条件下还可发生变化。
所有这些都通过对可变喷嘴构形而获得，将所述系列剖面中的每一剖面彼此连续放置，并且使所述系列剖面中的每一剖面的第一端在轴11的轴线方向上沿着至少为二次的曲线60布置。
所述曲线60位于表面70上，所述表面70的轴线与轴11的轴线正交并且所述表面70还以不等于0°并且小于90°的角度80相对于底部90倾斜布置。
所述曲线60为至少为二次的曲线，并且包括抛物线或者双曲线或者这些曲线的组合。
在第一优选实施例中，所述曲线60优选地为抛物线。
因此，可变喷嘴10为弓形喷嘴，优选地为抛物线状的弓形。
在第二实施例中，所述曲线60优选地为双曲线。
在第三实施例中，所述曲线60优选地为三次曲线。
此外，所述曲线60优选地具有最大或最小点。
因此，可以看出，本发明的燃气轮机的可变喷嘴达到了上面所指定的发明目的。
可对本发明的燃气轮机的可变喷嘴进行各种改进和变形，其中这些改进和变形都在相同的发明构思内。
此外，在实践中，所采用的材料以及尺寸和部件，都可根据技术要求进行变化。

Claims (8)

1.一种固定到轴(11)上的燃气轮机的可变喷嘴(10)，所述可变喷嘴(10)包括上压力面(12)和与上表面(12)相对的下负压面(14)，其特征在于所述可变喷嘴包括一系列大致呈“C”形的剖面，每一剖面具有第一修圆端(20)和第二修圆端(21)，所述系列剖面中的每一剖面还具有向上正对着底部(90)的凹部，并且每一剖面沿着曲线(60)在轴(11)的轴线方向上彼此连续布置，其特征在于所述至少为二次的曲线(60)位于表面(70)上，其中所述表面(70)的轴线与轴(11)的轴线正交，并且所述表面(70)还以一个角度(80)相对于底部(90)倾斜布置。
2.如权利要求1所述的可变喷嘴(10)，其特征在于所述曲线(60)为抛物线。
3.如权利要求1所述的可变喷嘴(10)，其特征在于所述曲线(60)为双曲线。
4.如权利要求1所述的可变喷嘴(10)，其特征在于所述曲线(60)为抛物线和双曲线的组合。
5.如权利要求1所述的可变喷嘴(10)，其特征在于所述曲线(60)为三次曲线。
6.如前述任一权利要求所述的可变喷嘴(10)，其特征在于所述曲线(60)具有最大点或者最小点。
7.如前述任一权利要求所述的可变喷嘴(10)，其特征在于上表面(12)为鞍形。
8.一种如前所述并且如附图所示和用于上面指定目的的燃气轮机的可变喷嘴。
CNB2004800359964A 2003-12-05 2004-11-30 燃气轮机的可变喷嘴 Active CN100557201C (zh)

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ITMI2003A002388 2003-12-05
IT002388A ITMI20032388A1 (it) 2003-12-05 2003-12-05 Ugello variabile per una turbina a gas.

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CN100557201C CN100557201C (zh) 2009-11-04

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CN101915130A (zh) * 2010-06-25 2010-12-15 北京理工大学 可变几何涡轮增压器喷嘴环三维叶片及其设计方法
CN103711528A (zh) * 2013-10-22 2014-04-09 萍乡市慧成精密机电有限公司 混流涡轮增压器可变喷嘴环

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DE102007020476A1 (de) * 2007-04-27 2008-11-06 Rolls-Royce Deutschland Ltd & Co Kg Vorderkantenverlauf für Turbomaschinenkomponenten
EP2476862B1 (en) * 2011-01-13 2013-11-20 Alstom Technology Ltd Vane for an axial flow turbomachine and corresponding turbomachine
US9879540B2 (en) 2013-03-12 2018-01-30 Pratt & Whitney Canada Corp. Compressor stator with contoured endwall

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Cited By (3)

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Publication number Priority date Publication date Assignee Title
CN101915130A (zh) * 2010-06-25 2010-12-15 北京理工大学 可变几何涡轮增压器喷嘴环三维叶片及其设计方法
CN101915130B (zh) * 2010-06-25 2013-04-03 北京理工大学 可变几何涡轮增压器喷嘴环三维叶片及其设计方法
CN103711528A (zh) * 2013-10-22 2014-04-09 萍乡市慧成精密机电有限公司 混流涡轮增压器可变喷嘴环

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CA2548535A1 (en) 2005-06-16
ITMI20032388A1 (it) 2005-06-06
EP1721065A1 (en) 2006-11-15
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JP2007513283A (ja) 2007-05-24
CA2548535C (en) 2012-10-09

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