阅读说明：本技术 一种燃气轮机透平闭式蒸汽冷却叶片 (Closed steam cooling blade of gas turbine ) 是由 权立宝 潘春霖 郑伟 李小萌 郭振轩 于 2021-12-02 设计创作，主要内容包括：一种燃气轮机透平闭式蒸汽冷却叶片,属于燃气轮机用叶片技术领域,包括上缘板,上缘板上设置有蒸汽输入管道Ⅰ、蒸汽输入管道Ⅱ、蒸汽输出管道Ⅰ及蒸汽输出管道Ⅱ,下缘板的上尾缘侧设置有导流槽,叶片体内安装有插件,正对叶片体前缘内侧的插件前部沿径向开设多个冲击孔,且插件的内腔与蒸汽输入管道Ⅰ连通,叶片体的冷却腔后部设置若干沿径向等间距设置的隔板,且隔板位于插件的后部,叶片体尾缘实体部分开设有多个径向冷却通道,径向冷却通道由上至下贯穿整个叶片尾部,且多个径向冷却通道通过下缘板设置的导流槽连通。解决从压气机抽取高压空气及冷却介质与主流道燃气混合所产生的负面影响,简化叶片内腔冷却结构,降低叶片制造成本。(The utility model provides a gas turbine closed steam cooling blade, belong to blade technical field for gas turbine, including the upper fringe board, be provided with steam input pipeline I on the upper fringe board, steam input pipeline II, steam output pipeline I and steam output pipeline II, the last trailing edge side of lower fringe board is provided with the guiding gutter, install plug-in components in the blade body, just radially set up a plurality of percussion holes to the plug-in components front portion of blade body leading edge inboard, and the inner chamber and the I intercommunication of steam input pipeline of plug-in components, the cooling chamber rear portion of the blade body sets up a plurality of baffles that set up along radial equidistant, and the baffle is located the rear portion of plug-in components, a plurality of radial cooling channel have been seted up to blade body trailing edge entity part, radial cooling channel runs through whole blade afterbody from top to bottom, and a plurality of radial cooling channel are through the guiding gutter intercommunication that the lower fringe board set up. The negative influence generated by mixing high-pressure air extracted from the air compressor, a cooling medium and main runner gas is solved, the cooling structure of the inner cavity of the blade is simplified, and the manufacturing cost of the blade is reduced.)

1. A closed steam cooling blade of a gas turbine is characterized by comprising a blade body, an upper edge plate, a lower edge plate, a steam input pipeline I, a steam input pipeline II, a steam output pipeline I and a steam output pipeline II, wherein the upper edge plate is provided with the steam input pipeline I, the steam input pipeline II, the steam output pipeline I and the steam output pipeline II, the upper tail edge side of the lower edge plate is provided with a diversion trench, a plug-in is arranged in the blade body, the front part of the plug-in on the inner side of the front edge of the blade body is radially provided with a plurality of impact holes, the inner cavity of the plug-in is communicated with the steam input pipeline I, the rear part of a cooling cavity of the blade body is provided with a plurality of partition plates which are radially arranged at equal intervals, the partition plates are positioned at the rear part of the plug-in, the solid part of the tail edge of the blade body is provided with a plurality of radial cooling channels, and the radial cooling channels penetrate through the tail part of the whole blade from top to bottom, and the plurality of radial cooling channels are communicated through diversion trenches arranged on the lower edge plate.

2. The closed steam cooling blade for a gas turbine according to claim 1, wherein: the width of the insert to the pressure side gap is less than the width of the insert to the suction side gap.

3. The closed steam cooling blade for a gas turbine according to claim 1, wherein: the inner diameter of a plurality of radial cooling channels is gradually reduced from one end close to the partition plate to the solid end of the tail edge of the blade body.

Technical Field

The invention belongs to the technical field of blades for gas turbines, and particularly relates to a closed steam cooling blade for a gas turbine.

Background

An important approach to increasing the thermal efficiency of gas turbines is to increase the turbine inlet temperature, which, however, worsens the operating environment of the turbine components and places ever increasing demands on the performance of the materials. At present, a gas turbine with the grade above 1600 ℃ of the initial temperature of the fuel gas is developed and put into practical use abroad. Because the temperature that the high temperature material that present turbine blade uses can bear does not exceed 1000 ℃, to the high temperature part of gas turbine, especially turbine blade, must take reliable cooling measure to reduce its operating temperature to guarantee the safe operation of gas turbine. The cooling technology using air as cooling medium is developed and applied for decades, and the structural design is increasingly perfect and efficient. Usually, the cooling air is led out from the outlet of the compressor or from some intermediate stage, then enters the high temperature turbine part through various cooling channels to cool it, and finally is discharged into the main gas flow. With the continuous increase of the temperature of the turbine inlet of the gas turbine, the required cooling air quantity is increased increasingly, and the cooling air quantity extracted by the gas turbine on the ground is more than 5 percent, which has a very adverse effect on the overall performance of the engine, and the compressed air cannot participate in combustion and cannot be used as gas to do work on the turbine; the cooling air will eventually be discharged into the main gas stream, causing a reduction in the gas temperature, thereby reducing the power and efficiency of the turbine.

Disclosure of Invention

The invention aims to provide a closed steam cooling blade of a gas turbine, which solves the negative influence generated by the mixing of high-pressure air extracted from a gas compressor and a cooling medium with main channel gas, simplifies the cooling structure of the inner cavity of the blade and reduces the manufacturing cost of the blade.

In order to achieve the purpose, the invention adopts the following technical scheme:

a closed steam cooling blade of a gas turbine comprises a blade body, an upper edge plate, a lower edge plate, a steam input pipeline I, a steam input pipeline II, a steam output pipeline I and a steam output pipeline II, wherein the upper edge plate is provided with the steam input pipeline I, the steam input pipeline II, the steam output pipeline I and the steam output pipeline II, the upper tail edge side of the lower edge plate is provided with a diversion trench, a plug-in unit is arranged in the blade body, the front part of the plug-in unit, which is just opposite to the inner side of the front edge of the blade body, is provided with a plurality of impact holes along the radial direction, the inner cavity of the plug-in unit is communicated with the steam input pipeline I, the front edge of the blade body is subjected to impact cooling through the impact holes, cooled steam flows to the rear part of a cooling cavity along the gaps of the pressure side and the suction side formed by the plug-in and the inner surface of the blade body and is discharged from the steam output pipeline I, and the rear part of the cooling cavity of the blade body is provided with a plurality of partition plates which are arranged along the radial direction at equal intervals, and the baffle is located the rear portion of plug-in components, and a plurality of radial cooling channel have been seted up to blade body trailing edge entity part, and radial cooling channel runs through whole blade afterbody from top to bottom, and a plurality of radial cooling channel pass through the guiding gutter intercommunication that the lower flange plate set up.

The width of the gap between the plug-in and the pressure side is smaller than that of the gap between the plug-in and the suction side, and the steam flow distribution of the pressure side and the suction side is ensured to be uniform, so that the integral temperature distribution of the blade is uniform, and the pressure side and the suction side can be uniformly cooled.

The inner diameter of a plurality of radial cooling channels is gradually reduced from one end close to the partition plate to the solid end of the tail edge of the blade body.

Compared with the prior art, the invention has the following technical effects:

the closed steam is adopted to cool the turbine stator blade, so that the high-pressure air quantity extracted from the air compressor can be reduced, and the part of air can participate in acting, thereby improving the efficiency and the output power of the gas turbine; the closed steam cooling has the advantages that the cooled steam does not need to be discharged into the main gas flow, so that the temperature of the gas is not reduced, the temperature of the gas is increased, and the heat efficiency of the gas turbine is improved; the higher cooling efficiency further simplifies the inner cavity structure of the blade and reduces the manufacturing cost of the blade.

Drawings

FIG. 1 is a schematic overall view of a closed steam-cooled blade of a gas turbine according to the invention;

FIG. 2 is a schematic view of the upper edge plate of a closed steam cooling blade for a gas turbine according to the present invention;

FIG. 3 is a schematic view of the lower edge plate of a closed steam cooling blade for a gas turbine according to the present invention;

FIG. 4 is a schematic illustration of the configuration of the internal cavity of a closed steam cooling blade of a gas turbine according to the present invention;

FIG. 5 is a schematic illustration of an insert for a closed steam cooling blade of a gas turbine according to the present invention;

FIG. 6 is a schematic view of a diaphragm array for a closed steam cooled bucket of a gas turbine according to the present invention;

FIG. 7 is a schematic view of the radial cooling passages of a closed steam cooling blade of a gas turbine according to the present invention;

FIG. 8 is a steam flow diagram of a closed steam cooling blade for a gas turbine according to the present invention;

1-steam input pipeline I; 2-steam input pipeline II; 3-steam output pipeline I; 4-steam output pipeline II; 5-upper edge plate, 6-lower edge plate, 7-diversion groove, 8-impact hole, 9-clapboard, 10-plug-in piece and 11-radial cooling channel.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and examples.

As shown in fig. 1 to 8, a closed steam cooling blade of a gas turbine comprises a blade body, an upper edge plate 5, a lower edge plate 6, a steam input pipeline i 1, a steam input pipeline ii 2, a steam output pipeline i 3 and a steam output pipeline ii 4, wherein the upper edge plate 5 is provided with the steam input pipeline i 1, the steam input pipeline ii 2, the steam output pipeline i 3 and the steam output pipeline ii 4, the upper tail edge side of the lower edge plate 6 is provided with a diversion trench 7, the blade body is separated by an insert 10 installed in the blade body, the front part of the insert 10 facing the inner side of the front edge of the blade body is radially provided with a plurality of impact holes 8, the inner cavity of the insert 10 is communicated with the steam input pipeline i 1, the front edge of the blade body is subjected to impact cooling through the impact holes 8, and cooled steam flows to the rear part of a cooling cavity along a gap between the pressure side and a gap between the suction side formed by the insert 10 and the inner surface of the blade body, the steam is discharged from a steam output pipeline I3, a plurality of partition plates 9 which are arranged at equal intervals along the radial direction are arranged at the rear part of a cooling cavity of the blade body, the partition plates 9 are positioned at the rear part of a plug-in 10, a plurality of radial cooling channels 11 are arranged at the long and narrow solid part of the tail edge of the blade body, the radial cooling channels 11 penetrate through the tail part of the whole blade from top to bottom, and the radial cooling channels 11 are communicated through a diversion trench 7 arranged on a lower edge plate 6.

The width of the plug-in 10 and the width of the pressure side gap are smaller than the width of the plug-in 10 and the width of the suction side gap, and the steam flow distribution of the pressure side and the suction side is ensured to be uniform, so that the integral temperature distribution of the blade is uniform, and the pressure side and the suction side can be uniformly cooled.

The inner diameter of a plurality of radial cooling channels 11 is gradually reduced from one end close to the partition plate 9 to the solid end of the tail edge of the blade body.

The upper edge plate 5 of the turbine closed steam cooling blade is provided with a steam inlet pipeline and a steam outlet pipeline which are used for inputting and discharging steam out of the inner cavity of the blade; secondly, in order to ensure that steam does not flow into the high-temperature main fuel gas, the whole blade adopts a closed structure without structures such as an air film cooling hole, a tail edge cleft and the like; thirdly, in order to ensure uniform temperature of each section of the blade and reduce the thermal stress borne by the blade body, the cooling channel of the inner cavity of the blade is divided into regions according to the temperature distribution condition, a high-temperature region is subjected to large-flow impact cooling, and a relatively low-temperature region is subjected to smaller-flow convection cooling.

The cooling process of the closed steam cooling blade of the gas turbine comprises the following steps:

cooling steam enters an inner cavity of the insert 10 from a steam input pipeline I1, the front edge of the blade is subjected to impact cooling through impact holes 8 of the insert 10, and the cooled steam flows to the rear part of the cooling cavity along gaps of a pressure side and a suction side formed by the insert 10 and the inner surface of the blade and is discharged from a steam output pipeline I3; steam entering from the steam input pipeline II 2 sequentially passes through the radial cooling channel 11 and the diversion trench 7 to enter the blade rear part separation cavity and is discharged from the steam output pipeline II 4, and the primary cooling process is completed.