CN103061826A - Gas turbine guiding device considering inlet hot spots - Google Patents

Gas turbine guiding device considering inlet hot spots Download PDF

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Publication number
CN103061826A
CN103061826A CN 201110320512 CN201110320512A CN103061826A CN 103061826 A CN103061826 A CN 103061826A CN 201110320512 CN201110320512 CN 201110320512 CN 201110320512 A CN201110320512 A CN 201110320512A CN 103061826 A CN103061826 A CN 103061826A
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guide
gas turbine
guiding device
rotor
inlet
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CN 201110320512
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Chinese (zh)
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安柏涛
刘建军
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中国科学院工程热物理研究所
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Abstract

The invention discloses a gas turbine guiding device considering inlet hot spots, and relates to the gas turbine guiding device technology. The gas turbine guiding device considering the inlet hot spots comprises a guiding device wheel disc. The tubular guiding device wheel disc is arranged on the outer circle of a rotating shaft of a gas turbine in a surrounding and sleeved mode. A gap is formed between the guiding device wheel disc and the rotating shaft of the gas turbine, and a plurality of planetary gears are evenly distributed in the gap. Inner teeth are arranged on the inner wall face of the guiding device wheel disc. Outer teeth are arranged on the positions, opposite to the guiding device wheel disc, of the outer circle wall of the rotating shaft. The planetary gears are simultaneously and movably connected with the inner teeth and the outer teeth respectively. The gas turbine guiding device rotates at a low speed in the same direction as a rotor or in the opposite direction relative to the rotor. The rotating speed of the gas turbine guiding device is 1/50-1/10 of the rotating speed of the rotor. By means of the gas turbine guiding device considering the inlet hot spots, a non-uniform temperature field distributed periodically at an inlet of the gas turbine guiding device in a two-dimensional form is converted into a temperature field in a time average circumferential uniform form; the cooling design of the gas turbine guiding device only needs to be specific to the highest temperature after the hot spots are averaged in the circumferential direction; and the using amount of cold air by vanes of the gas turbine guiding device is reduced. The gas turbine guiding device considering the inlet hot spots is applicable to various stages of guiding devices in multistage turbines.

Description

一种考虑进口热斑的燃气透平导向器 Considering the gas turbine inlet hot spots guide

技术领域 FIELD

[0001] 本发明涉及燃气轮机透平导向器技术领域,是一种考虑进口热斑的燃气透平导向器,可提高燃气透平进口温度或降低透平叶片冷却所需冷气量,适用于燃气轮机中空气冷却的多级轴流透平。 [0001] The present invention relates to a technical field Inflow Turbine guide, considering a gas turbine inlet hot spots guide, gas turbine inlet temperature can increase or decrease the amount of cool air required for cooling the turbine blades for gas turbine air-cooled multi-stage axial flow turbine.

背景技术 Background technique

[0002] 燃气轮机的透平叶片长期工作在极高的温度环境中,通常需要透平冷却技术的帮助来降低合金叶片的工作温度以保证叶片的长寿命要求。 [0002] The turbine blades to work in the gas turbine high temperature environment, the turbine typically require cooling techniques help to reduce the operating temperature of the alloy of the blade to ensure the long life requirements of the blade. 尤其是重型燃机,用于透平冷却的空气量很大,一定程度上降低了燃气轮机的效率。 In particular, heavy-duty gas turbine, a large amount of air for cooling the turbine, reducing the efficiency of the gas turbine to a certain extent. 因此减少冷却空气的使用同时保证叶片的可靠性是透平冷却技术的主要目标。 Thus reducing the use of cooling air while ensuring the reliability of the turbine blade main goal of cooling techniques. 对于多级透平而言,各级中的动静叶片个数一般在几十至上百个,而叶片冷却设计是以叶片排整体的温度以及流动特性为依据进行统一的冷却设计,即全周每个导向器叶片和每个动叶片的冷却设计是完全一致的,冷气量也是完全一致的。 For multi-stage turbine, the blade movement in the number of levels typically in the tens to hundreds, and the blade row is designed blade cooling temperature and the flow characteristics of the whole unified cooling design basis, i.e., the entire circumference of each a guide vane and design of each of the cooling moving blade is exactly the same, the amount of cool air is entirely consistent. 工程上,不可能为叶片排中的每一个叶片单独设计冷却结构和单独提供冷气。 Engineering, it is impossible to individually design each blade cooling structure of the blade row and the cool air provided separately. 对于透平级中的动叶片,采用统一的冷却设计没有问题,因为动叶的旋转使得每一个叶片的时均热负荷是一致的。 For turbine moving blade stage, uniform cooling design is no problem, because the rotation of the buckets of each blade such that the heat load are consistent. 而对于透平级中的导向器叶片,由于进口热斑(燃烧室出口温度场的不均匀)的存在,全周每个导向器叶片的热负荷并不完全一致,有时甚至差别很大,因此导向器叶片按照统一的冷却设计必然会导致各叶片的实际热负荷与设计所用冷气量的不对应。 As for the guide vanes of the turbine stage, due to the presence of hot spots inlet (non-uniform temperature in the combustor outlet), the heat load the entire circumference of each guide vane is not exactly the same, and sometimes very different, so guide vanes in accordance with uniform cooling designs inevitably result in actual heat load and the design of the blades do not correspond with the amount of cold air. 重要的是,为了保证叶片的可靠性,导向器叶片统一的冷却设计必须按照热斑核心的最高温度值进行,而热斑核心的最高温度通常比平均温度高15% -20%,由于全周每个导向器叶片并非均对应热斑最高温度,因此必然导致大部分叶片冷气量的浪费。 Importantly, in order to ensure the reliability of the blade, uniform cooling design guide vanes must be the highest temperature hot spots core, the core and the highest temperature hot spots typically 15% -20% higher than the average temperature, since the entire circumference each guide vane corresponding to the hot spots are not the highest temperature, and therefore the amount of cool air will inevitably lead to waste of the majority of the blade.

[0003] 热斑对透平级叶片传热的影响是非定常的,目前有关热斑非定常流动机理的研究已经比较系统和完善,尤其是热斑与导向器之间周向位置关系(clocking)的研究表明,通过调节热斑的周向位置可以使导向器叶片避开热斑最高温度区的冲击,但对于透平级而言,要么静叶热负荷高,要么动叶热负荷高,二者之间较难平衡。 [0003] Effect of the hot spot on the turbine blade stage heat unsteady current research related hot spots unsteady flow mechanism often been more perfect system and, in particular, the circumferential positional relationship between the hot spot and the guide (clocking) studies show that, by adjusting the hot spots may cause the circumferential position of the guide vanes the maximum temperature to avoid the impact of the hot spot region, but for the turbine stage, the vanes or high heat load, high caloric load or dynamic, two difficult balance between those. 同时,热斑与导向器之间的数比关系决定了热斑与导向器之间能否通过周向位置变动调节动静叶片的热负荷大小。 Meanwhile, the number of hot spots between the guide and determine whether to adjust the position of blade movement variation between the hot spot and the guide through the peripheral heat load than the magnitude relation. 只有在热斑与导向器数比为1:1时,无论如何调整热斑与导向器的周向位置,全周每个导向器叶片的热负荷均完全一致。 Only the number of hot spots with the guide 1 ratio: 1, and in any case to adjust the guide hot spots circumferential position, the entire circumference of each guide vane the heat load they are identical. 但在真实透平中,热斑与导向器个数比并非总是精确的I : I。 But in the real turbine, the number of hot spots and the guide is not always accurate than the I: I. 在不是一一对应的情况下,如何保证全周每个导向器叶片的热负荷一致对于统一冷却设计和减少透平叶片的冷气量有重要意义。 When it is not one to one, how to ensure that the entire circumference of the thermal load of each guide vane coincides uniform cooling designs for turbine blade and to reduce the amount of cool air is important.

[0004] 与动叶类似,如果将透平导向器叶片进行旋转显然能够得到完全一致的时均热负荷。 [0004] Similarly to the bucket, if the rotation of the turbine guide blades can obviously exactly matches the thermal load are obtained. 然而目前燃气透平中的导向器均为静止设计,如果允许其旋转可能带来如下问题••第一,导向器叶片的冷气进气方式和内部冷却结构改变;第二,导向器进口冲角变化,须对气动设计做相应调整;第三,旋转导致叶片热负荷的周期变化,可能导致叶片热疲劳寿命降低;第四,如何实现低速旋转以及结构设计问题。 However, there is the gas turbine stationary guides are designed, if allowed rotation may cause a problem •• a first cool air guide vane and internal cooling Inlet structure changes; second, angle of attack of the inlet guide change of aerodynamic design to be done adjusted; third, rotation causes periodic changes in the heat load blade, the blade may lead to reduced thermal fatigue life; fourth, how low speed rotation and structural design.

[0005] 尽管实现导向器的低速旋转设计存在一系列问题,但允许导向器旋转所带来的优点仍然是不容忽视的。 [0005] Although there are a number of issues to achieve low-speed rotation design director, but the advantage of allowing rotation of the guide brought still can not be ignored. 本发明主要强调了导向器旋转设计所体现的优势以及这一设计概念。 The present invention emphasizes the advantages of this design concept and design director rotation embodied.

发明内容 SUMMARY

[0006] 本发明公开一种考虑进口热斑的燃气透平导向器,可使导向器叶片避开热斑最高温度区,全周每个导向器叶片的热负荷一致,并大量减少透平叶片的冷气量。 [0006] The present invention discloses a consideration of the gas turbine inlet hot spots guide, the guide vanes can avoid the highest hot spot temperature regions, consistent with the heat load the entire circumference of each guide vane, and a significant reduction in the turbine blade the amount of cool air.

[0007] 为达到上述目的,本发明的技术解决方案是: [0007] To achieve the above object, the technical solution of the invention is:

[0008] —种考虑进口热斑的燃气透平导向器,包括导向器轮盘;其导向器的筒状导向器轮盘,环套于燃气透平的转动轴外圆,两者之间有空隙,空隙内均布有多个行星齿轮;在导向器轮盘内壁面设有内齿,转动轴外圆壁上,与导向器轮盘相对处设有外齿,行星齿轮同时分别与内齿、夕卜齿动连接; [0008] - Species considered hot spots gas turbine inlet guide, comprising a guide wheel; Between a cylindrical guide which guide the wheel, in the collar outer rotating shaft of the gas turbine, both voids, the voids are uniformly distributed plurality of planet gears; in the inner wall surface of the guide wheel provided with internal teeth, the cylindrical wall of the rotary shaft, the guide wheel is provided opposite the outer teeth of the planetary gears simultaneously with the internal teeth , Bu Xi movable teeth connected;

[0009] 导向器与转子同方向或反方向做低速旋转; [0009] The guide and the low-speed rotation of the rotor to do the same or reverse direction;

[0010] 导向器转速介于转子转速的1/50-1/10之间。 [0010] guide the rotational speed between the rotational speed of the rotor between 1 / 50-1 / 10.

[0011] 所述的燃气透平导向器,其在多级轴流透平中,各级透平导向器分别与透平转子同向或反向低速旋转。 [0011] guide the gas turbine, in which a multistage axial turbine, the turbine guide levels respectively turbine rotor rotate in the same direction or reverse slow.

[0012] 所述的燃气透平导向器,其所述导向器的转速介于转子转速的1/50-1/10之间,其高低的选择以对导向器进口冲角影响较小为依据,并由导向器进口速度的大小和导向器所处的半径决定。 [0012] The gas turbine guide, which guides the rotational speed of the rotor speed is between 1 / 50-1 / 10, the level of the selected attack angle of the inlet guide little effect based by the inlet guide guides the size and the speed at which the radius determined.

[0013] 所述的燃气透平导向器,其所述导向器与转子同方向或反方向旋转,其转速的变化是通过行星齿轮的结构变化来实现的,即通过调整行星齿轮减速比调整导向器叶片转速。 [0013] The gas turbine guide, which guide the rotation of the rotor with the same or reverse direction, its speed changes by changes in the structure of the planetary gears is achieved, i.e., by adjusting the speed reduction ratio of the planetary gear guide adjustment blade speed.

[0014] 所述的燃气透平导向器,其所述导向器与转子同方向或反方向旋转,其转动方向的变化是以多级行星齿轮来实现的,若导向器转动方向与转子转动方向相反,则导向器输出功;若导向器转动方向与转子转动方向相同,贝1J导向器消耗功。 [0014] The gas turbine guide, which guide the rotation of the rotor with the same or reverse direction, change its rotation direction is multi-stage planetary gear is achieved, if the guide direction of rotation of the rotor rotational direction Instead, the guide output power; if the guide direction of rotation of the rotor is rotated in the same direction, the guide shell 1J power consumption.

[0015] 本发明的燃气透平导向器,优点在于:第一,将导向器进口周期分布的二维形式的不均匀温度场(热斑)转化为时均周向均匀形式(径向温度型),使得全周所有导向器叶片的时均热负荷一致,导向器叶片采用统一的冷却设计不会浪费冷气量;第二,导向器冷却设计不需针对热斑的最高温度,而只需针对热斑周向平均后(径向温度型)的最高温度即可,可以减少透平导向器叶片冷气量的使用,或在冷气量不变条件下提高透平进口温度;第三,导向器的低速旋转对导向器气动性能的影响较小,导向器的气动设计可以不变或仅针对进口冲角变化做微小调整。 [0015] Gas turbine guide according to the present invention, advantages: first, the non-uniform temperature field (hot spot) was converted to two-dimensional form of the inlet guide last cycle distribution were in the form of circumferentially uniform (radial temperature type soaking time), so that all guide vanes entire circumference load uniform, unified guide vane cooling design without wasting the amount of cool air; second, guide cooling designs without the maximum temperature for the hot spots, but only for after the hot spots are circumferential (radial temperature type) of the maximum temperature can be used to reduce the amount of cool air turbine guide vanes, turbine inlet temperature or increasing the amount of cool air at the same conditions; third, the guide less affected by the aerodynamic performance of low-speed rotation of the guide, aerodynamic design guides may be unchanged or only for imports of incidences do minor adjustments.

附图说明 BRIEF DESCRIPTION

[0016] 图1为本发明的考虑进口热斑的燃气透平导向器原理图; [0016] Consider FIG. 1 of the present invention the gas turbine inlet hot spots guide diagram;

[0017] 图2为本发明的考虑进口热斑的燃气透平导向器结构图; [0017] Consider a gas turbine inlet hot spots guide structure of the present invention Figure 2;

[0018] 图3a为本发明的环管燃烧室出口热斑与径向温度型的总温分布示意图中的进口热斑总温等值线图; [0018] FIG loop 3a of the present invention the combustion chamber outlet inlet total temperature of hot spots in the contour diagram schematic total temperature hot spots and radial temperature distribution type;

[0019] 图3b为本发明的环管燃烧室出口热斑与径向温度型的总温分布示意图的进口周向平均的径向总温度分布图; [0019] FIG. 3b loop combustion chamber of the present invention the outlet temperature of hot spots and the total radial temperature profile type inlet schematic overall radial temperature profile of each circumferential;

[0020] 图4为本发明的进口导向器静止时的最大热负荷情况不意图;[0021] 图5为本发明的进口导向器65%叶高绝热壁温度分布对比图;图中T/T#表示当地绝热壁温和进口总温之比,x/C代表相对轴向弦长,x/C为正对应吸力面(SS),x/C为负对应压力面(PS)。 [0020] FIG 4 the maximum heat load case when the stationary inlet guide of the present invention is not intended; [0021] FIG. 5 of the present invention, the inlet guide blade height of 65% heat-insulating wall temperature distribution comparison chart; FIG. T / T # represents the ratio of the total adiabatic wall temperatures of the local mild inlet, x / C represents the relative axial chord length, x / C is positive corresponding to the suction side (SS), x / C corresponding to the negative pressure surface (PS).

[0022] 图6为本发明的进口导向器65%叶高壁面压力分布对比图;图中p/p#表示当地静压与进口总压之比。 Inlet guide [0022] FIG. 6 of the present invention, 65% of the high pressure distribution comparison chart leaf wall; FIG p / p # represents the local static pressure and total pressure ratio of the inlet.

具体实施方式 detailed description

[0023] 如图1所示,为本发明的考虑进口热斑的燃气透平导向器,将多级透平中的导向器设计为低速旋转形式,转速介于转子转速的1/50-1/10之间,转动方向可以与转子同方向或反方向。 [0023] FIG. 1, the present invention contemplates a gas turbine inlet hot spots guide, in the multi-stage turbine is designed as a guide in the form of low-speed rotation, rotation speed of rotor speed range 1 / 50-1 between / 10, the rotational direction may be the same or opposite direction of the rotor. 转速高低的选择以对导向器进口冲角影响较小为依据,还需考虑导向器进口速度的大小和导向器所处的半径。 The high and low speed selected to guide inlet of the angle of attack less affected as the basis, the need to consider the radius of the inlet guide guides the size and the speed at which. 转速越低对导向器气动影响越小,但对导向器热疲劳寿命不利。 Less impact on the low-speed pneumatic guide, but the thermal fatigue life adversely guide. 转速越高对导向器气动影响越大,但对减少导向器热疲劳有利。 The higher the speed the greater the impact on the air guide, but it is advantageous to reduce the thermal fatigue guide. 转速较高时导向器进口冲角变化较大,叶片需针对冲角变化重新设计叶型和径向积叠。 At higher speeds, the inlet guide large angle of attack changes, changes in blade angle of attack against the need to redesign and radial airfoil stacking.

[0024] 图2为实现导向器低速旋转的结构图。 [0024] FIG. 2 is a structural view of the low speed rotation to achieve guide. 图中,导向器1,行星齿轮2,转动轴3。 FIG, the guide 1, the planetary gear 2, the rotary shaft 3. 导向器I的导向器轮盘Ia和转动轴3之间通过行星齿轮2结构实现转速变化,通过调整行星齿轮2减速比调整导向器叶片转速,也可以设计多级行星齿轮结构实现导向器I转动方向变化。 Guide guides I and Ia wheel speed achieved by changing the structure 2 between the planetary gear rotation shaft 3, the planetary gear 2 by adjusting the reduction ratio adjusting guide vanes speed, may also be designed to achieve multi-stage planetary gear mechanism rotatably guide I change direction. 如果导向器I转动方向与转子转动方向相反,贝1J导向器I输出功。 If the guide direction of rotation of the rotor I rotates in the opposite direction, guide shell I 1J output power. 如果导向器I转动方向与转子转动方向相同,贝1J导向器I消耗功。 If the guide direction of rotation of the rotor I rotates in the same direction, the guide shell I 1J power consumption.

[0025] 图3以环管燃烧室为例说明了热斑最高温度与周向平均后的径向最高温度之间的温度差。 [0025] FIG. 3 illustrates an example combustor loop between the radial maximum temperature after hot spot temperatures are the maximum temperature difference with a circumferential. 图3(a)中热斑最高温度为进口平均总温的约1. 2倍,图3(b)中周向平均后的径向最高总温仅为进口平均总温的1. 04左右,二者相差16%的进口平均总温。 In FIG. 3 (a) maximum hot spot temperature is about 1.2 times the average total inlet temperature, left in FIG. 3 (b) radially circumferential highest overall average temperature of the inlet is only 1.04 of the average total temperature, a difference of 16% of the total imports of the average temperature. 假设进口平均总温为1500°C,则二者相差近240°C。 Suppose the average total inlet temperature of 1500 ° C, the difference between the two near 240 ° C.

[0026] 如果进口导向器按照统一的冷却设计,要想保证全周所有导向器叶片的可靠性,则导向器必须将图3(a)所示总温场按照图4所示的情形进行热负荷预估并设计导向器冷却,即以热斑最高温度区正对导向器叶片前缘为设计依据。 [0026] If the inlet guide designed in accordance with uniform cooling, in order to ensure the reliability of the entire circumference of all the guide blades, the guide must FIG. 3 (a) as shown in the total heat temperature field in accordance with the case shown in FIG. 4 load and estimated design-oriented cooling, i.e. the highest temperature at the hot spot area facing the guide vane leading edge as a design basis. 而在导向器旋转条件下,导向器的冷却设计只需按图3(b)中的进口温度分布为依据,且每个导向器叶片的时均热负荷均一致。 In the guide rotation condition, the guide cooling designs simply press inlet temperature in FIG. 3 (b) is based on the distribution, and each guide vane loads are consistent soaking. 由于二者设计所依据的进口温度相差极大,因此导向器旋转条件下所需冷气量将明显减少。 Since both the inlet temperature varies greatly based design, thus requiring lower guide rotation condition will significantly reduce the amount of cool air. 如果冷气量不变,则导向器叶片所能承受的进口平均温度将更高。 If the same amount of cool air, the guide vanes can withstand average inlet temperature will be higher.

[0027] 图5对比了进口导向器叶片65%叶高的绝热壁温度分布。 [0027] Figure 5 compares the high inlet guide vanes 65% leaves the adiabatic wall temperature profile. 图中T/%*表示当地绝热壁温和进口总温之比,x/C代表相对轴向弦长,x/C为正对应吸力面(SS),x/C为负对应压力面(PS)。 FIG T /% * represents the ratio of the total local adiabatic wall temperatures of mild inlet, x / C represents the relative axial chord length, x / C is positive corresponding to the suction side (SS), x / C corresponding to the negative pressure surface (PS) . 点划线表示热斑核心正对导向器叶片前缘情况,即图3所示的情形。 Dashed line represents the core of the hot spot is on the guide vane leading edge situation, i.e. the situation shown in FIG. 实线表示导向器以120rpm转速与转子逆向旋转时的情形。 The solid line represents the case when the guide is rotated at 120rpm speed reverse with the rotor. 显然,进口导向器旋转后时均绝热壁温大大低于导向器对应最大热负荷时的情形。 Obviously, when the rotation of the inlet guide after the adiabatic wall temperature are considerably lower than the case when the guide corresponding to the maximum heat load.

[0028] 图6对比了进口导向器以120rpm转速与转子逆向旋转和静止时的壁面压力分布,仍然选取了65%叶高位置。 [0028] Figure 6 compares the inlet pressure at the wall surface to guide the reverse rotation speed of the rotor and the stationary distribution of 120rpm, still 65% of the blade height selected position. 图中p/p#表示当地静压与进口总压之比。 Figure p / p # represents the ratio of the local static pressure and the total pressure of imports. 结果说明,进口导向器低速旋转对导向器内部流动影响不大,壁面压力变化很小。 The results described, the inlet guide is little influence on a low speed internal flow guides, the wall pressure changed little.

[0029] 除了进口导向器之外,多级透平中的所有各级导向器均可以采用低速旋转设计。 [0029] In addition to inlet guide outside the guides at all levels in a multi-stage turbine can be designed using low-speed rotation. 由于进口热斑的影响贯穿整个多级透平,对于各级导向器而言,其进口总温场仍然是热斑形式的,导向器低速旋转设计对各级导向器均适用。 Due to the impact of imports of hot spots throughout the multi-stage turbine, for a guide at all levels, its total imports of temperature field are still hot spots in the form of a low-speed rotation guide designed to guide all levels are applicable.

Claims (5)

  1. 1. 一种考虑进口热斑的燃气透平导向器,包括导向器轮盘;其特征在于:导向器的筒状导向器轮盘,环套于燃气透平的转动轴外圆,两者之间有空隙,空隙内均布有多个行星齿轮;在导向器轮盘内壁面设有内齿,转动轴外圆壁上,与导向器轮盘相对处设有外齿,行星齿轮同时分别与内齿、夕卜齿动连接; 导向器与转子同方向或反方向做低速旋转; 导向器转速介于转子转速的1/50-1/10之间。 A consideration of the gas turbine inlet hot spots guide, comprising a guide wheel; characterized in that: the guide cylindrical guide wheel, in the gas turbine of the collar outer rotary shaft, both of between voids, a plurality of planetary gears are uniformly distributed within the void; the inner wall surface of the guide wheel provided with internal teeth, the cylindrical wall of the rotary shaft, the guide wheel is provided opposite the outer teeth of the planetary gears simultaneously with inner teeth gear Bu Xi movable connector; guide with the same or reverse direction to make the low speed rotation of the rotor; rotational speed between guide rotor speed of 1 / 50-1 / 10.
  2. 2.如权利要求1所述的燃气透平导向器,其特征在于:在多级轴流透平中,各级透平导向器分别与透平转子同向或反向低速旋转。 Guide the gas turbine as claimed in claim 1, wherein: the multistage axial turbine, the turbine guide levels respectively with the turbine rotor to reverse or low speed.
  3. 3.如权利要求1所述的燃气透平导向器,其特征在于:所述导向器的转速介于转子转速的1/50-1/10之间,其高低的选择以对导向器进口冲角影响较小为依据,并由导向器进口速度的大小和导向器所处的半径决定。 3. The gas turbine guide according to claim 1, wherein: said guide rotor speed between the rotational speed of 1 / 50-1 / 10, the level of the inlet guide selected to overshoot Effects based on small angle, by inlet guide guides the size and speed at which the radius determined.
  4. 4.如权利要求1或2所述的燃气透平导向器,其特征在于:所述导向器与转子同方向或反方向旋转,其转速的变化是通过行星齿轮的结构变化来实现的,即通过调整行星齿轮减速比调整导向器叶片转速。 4. The gas turbine of the guide or claim 12, wherein: said guide rotor rotates with the same or reverse direction, its speed variation is achieved by variation of the configuration of the planetary gear to achieve, i.e., by adjusting the planetary gear speed ratio adjusting guide vanes.
  5. 5.如权利要求1或2所述的燃气透平导向器,其特征在于:所述导向器与转子同方向或反方向旋转,其转动方向的变化是以多级行星齿轮来实现的,若导向器转动方向与转子转动方向相反,则导向器输出功;若导向器转动方向与转子转动方向相同,则导向器消耗功。 5. The gas turbine 1, the guide or claim 2, wherein: said guide rotor rotates with the same or reverse direction, change its rotation direction is multi-stage planetary gear to achieve, if guide direction of rotation of the rotor is rotated in the opposite direction, the guide output power; if the guide direction of rotation of the rotor is rotated in the same direction, the power consumption of the guide.
CN 201110320512 2011-10-20 2011-10-20 Gas turbine guiding device considering inlet hot spots CN103061826A (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB968190A (en) * 1959-10-20 1964-08-26 Bbc Brown Boveri & Cie Regulating device for thermal turbo-machines
GB1505858A (en) * 1976-12-08 1978-03-30 Secr Defence Axial flow rotary machines
US4455121A (en) * 1982-11-01 1984-06-19 Avco Corporation Rotating turbine stator
US20030002975A1 (en) * 2001-06-15 2003-01-02 Honeywell International, Inc. Combustor hot streak alignment for gas turbine engine
CN1847624A (en) * 2005-04-04 2006-10-18 通用电气公司 Method and system for rotating a turbine stator ring
JP2010190057A (en) * 2009-02-16 2010-09-02 Ihi Corp Design method of turbine and turbine
JP2011032966A (en) * 2009-08-04 2011-02-17 Mitsubishi Heavy Ind Ltd Communication structure for combustor with turbine section, and gas turbine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB968190A (en) * 1959-10-20 1964-08-26 Bbc Brown Boveri & Cie Regulating device for thermal turbo-machines
GB1505858A (en) * 1976-12-08 1978-03-30 Secr Defence Axial flow rotary machines
US4455121A (en) * 1982-11-01 1984-06-19 Avco Corporation Rotating turbine stator
US20030002975A1 (en) * 2001-06-15 2003-01-02 Honeywell International, Inc. Combustor hot streak alignment for gas turbine engine
CN1847624A (en) * 2005-04-04 2006-10-18 通用电气公司 Method and system for rotating a turbine stator ring
JP2010190057A (en) * 2009-02-16 2010-09-02 Ihi Corp Design method of turbine and turbine
JP2011032966A (en) * 2009-08-04 2011-02-17 Mitsubishi Heavy Ind Ltd Communication structure for combustor with turbine section, and gas turbine

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