阅读说明：本技术 一种具有螺旋纽带的燃气轮机涡轮叶片 (Gas turbine blade with spiral band ) 是由 杜长河 高银峰 李洪伟 洪文鹏 杨悦 于 2020-12-17 设计创作，主要内容包括：本发明一种具有螺旋纽带的燃气轮机涡轮叶片,包括：叶片前缘、叶片尾缘,叶片吸力面、叶片压力面、叶片顶部、叶片根部、扰流肋、扰流柱、气膜孔、冷却气体进入通道、旋流腔室、旋流喷嘴和螺旋纽带,通过螺旋纽带进一步加强旋流腔室内冷气的旋转运动,加强冷气对壁面的冲刷,增强对壁面边界层的扰动,提高换热效果,延长冷气在冷却通道内停留的时间,提高冷却气体的利用率,减少所需冷气量从而减少燃气轮机的气动惩罚,提高燃气轮机的效率,解决了现有燃气轮机涡轮叶片前缘部分冷却不均匀的技术问题。(The invention relates to a turbine blade of a gas turbine with helical ligaments, comprising: the blade leading edge, the blade trailing edge, blade suction surface, the blade pressure face, the blade top, the blade root, the vortex rib, the vortex post, the gas film hole, cooling gas access channel, the whirl cavity, whirl nozzle and spiral link, further strengthen the rotary motion of air conditioning in the whirl cavity through the spiral link, strengthen the washing away of air conditioning to the wall, the reinforcing is to the disturbance of wall boundary layer, improve the heat transfer effect, the time that extension air conditioning stayed in cooling channel, improve the utilization ratio of cooling gas, thereby reduce required air conditioning volume and reduce gas turbine's pneumatic punishment, improve gas turbine's efficiency, the inhomogeneous technical problem of current gas turbine blade leading edge part cooling has been solved.)

1. A gas turbine blade having a helical ligament comprising: blade leading edge (1), blade trailing edge (2), blade suction face (3), blade pressure side (4), blade top (5), root of blade (6), vortex rib (7), vortex post (8), film hole (9), cooling gas access channel (10), whirl chamber (11), swirl nozzle (12), characterized by: it still includes: the spiral band (13) is arranged in the cyclone chamber (11), and the upper end and the lower end of the spiral band (13) are fixedly connected with the top and the bottom of the cyclone chamber (11) respectively.

2. A turbine blade for a gas turbine according to claim 1, characterised in that the pitch of the helical ligament (13) is between 2 mm and 5 mm.

Technical Field

The invention relates to the technical field of turbine blades of gas turbines, in particular to a turbine blade of a gas turbine with spiral bands.

Background

The inlet air temperature of the H-grade gas turbine can reach more than 1600 ℃, and the inlet air temperature far exceeds the limit which can be borne by blade materials. The first stages of turbine blades are directly exposed to high-temperature gas and are washed by the high-temperature high-speed gas to bear severe heat load, and particularly, the working conditions of the region where the surface of the front edge of the blade is located are worse. At present, the commonly adopted cooling scheme of the front edge of the gas turbine comprises air film cooling and impingement cooling, and the impingement cooling is seriously influenced by cross flow. Effective impingement cooling needs to be combined with film cooling to avoid the negative effects of cross flow on internal heat transfer and to provide additional protection for surfaces downstream of the film holes. However, the film cooling has the problems of local stress concentration increase, extra pneumatic punishment, blocking of film holes under the long-term work of an industrial environment and the like.

The rotational flow cooling is a new cooling mode for the front edge of the turbine blade of the gas turbine at the present stage, and the rotational flow cooling and the impact air film composite cooling have equivalent cooling effect and are more effective than the single impact cooling. As shown in fig. 1, a cooling gas inlet hole is formed in the blade root 6 and connected with a cooling gas channel 10, a group of swirl nozzles 12 are arranged on the cooling gas channel 10 in the direction corresponding to the swirl chamber 11, cooling gas enters the group of swirl nozzles 12 with a small area from the cooling gas inlet hole of the blade root 6, the flow velocity of the cooling gas is further increased, then the cooling gas tangentially enters the swirl chamber 11, and forms a rotating flow along with the guiding of the surface of the swirl chamber 11, the high-speed jet strongly washes the wall surface, the boundary layer is damaged, and a relatively excellent heat transfer effect is realized.

However, since the rotationally flowing cold air tends to flow more axially than the circumferential rotational movement, the rotational flow movement is sufficient only on the front edge surface corresponding to the nozzle, and the effect of the rotational flow washing is significantly weakened in the region between the two nozzles, resulting in uneven cooling effect and higher thermal stress.

Disclosure of Invention

Aiming at the technical problems in the prior art, the spiral band and the turbine blade of the gas turbine are creatively and organically combined, the turbine blade of the gas turbine with the spiral band is designed, the spiral band is used for further enhancing the rotary motion of cold air in the vortex chamber, enhancing the scouring of the cold air on the wall surface, enhancing the disturbance on the boundary layer of the wall surface, improving the heat exchange effect and solving the technical problem of uneven cooling of the front edge part of the turbine blade of the gas turbine in the prior art.

The technical scheme for realizing the invention is as follows: a gas turbine blade having a helical ligament comprising: blade leading edge 1, blade trailing edge 2, blade suction face 3, blade pressure face 4, blade top 5, blade root 6, vortex rib 7, vortex post 8, gas film hole 9, cooling gas admission passage 10, whirl chamber 11, swirl nozzle 12, characterized by: it still includes: the spiral band 13 is arranged in the cyclone chamber 11, and the upper end and the lower end of the spiral band 13 are fixedly connected with the top and the bottom of the cyclone chamber 11 respectively.

The pitch of the spiral link 13 is 2 mm-5 mm.

The invention discloses a gas turbine blade with spiral bands, which has the beneficial effects that:

1. a gas turbine blade with spiral ties can prolong the retention time of cold air in a cooling channel, improve the utilization rate of cooling gas, reduce the required cold air amount, reduce the pneumatic punishment of a gas turbine and improve the efficiency of the gas turbine by adding the spiral ties;

2. the utility model provides a gas turbine blade with spiral tie, further strengthens the rotary motion of air conditioning in the whirl cavity, strengthens the washing away of air conditioning to the wall, and the reinforcing is to the disturbance of wall boundary layer, improves the heat transfer effect, and the tie can act as the effect of fin, further improves the heat transfer efficiency of blade, has solved the cooling effect uneven, produces the condition of higher thermal stress.

Drawings

FIG. 1 is a three-dimensional schematic view of a prior art gas turbine blade;

FIG. 2 is a three-dimensional schematic view of a gas turbine blade having helical ligaments;

in the figure: 1. the blade comprises a blade front edge, 2 blade tail edges, 3 blade suction surfaces, 4 blade pressure surfaces, 5 blade tops, 6 blade roots, 7 turbulence ribs, 8 turbulence columns, 9 gas film holes, 10 cooling gas inlet channels, 11 swirl chambers, 12 swirl nozzles and 13 spiral ties.

Detailed Description

The present invention will be described in further detail with reference to fig. 2 and the detailed description, which is provided herein for the purpose of illustration only and is not intended to limit the present invention.

As shown in FIG. 2, a gas turbine blade having a helical ligament comprising: blade leading edge 1, blade trailing edge 2, blade suction face 3, blade pressure face 4, blade top 5, blade root 6, vortex rib 7, vortex post 8, gas film hole 9, cooling gas admission passage 10, whirl cavity 11, whirl nozzle 12 and spiral tie 13 whirl cavity 11 in set up spiral tie 13, spiral tie 13 upper and lower both ends link firmly with 11 tops of whirl cavity and bottom respectively, spiral tie 13 the pitch be 3 mm.

The cooling air for cooling the leading edge of the turbine blade of a gas turbine enters the cooling air inlet channel 10 from the cooling air inlet opening of the blade root 6. Between the cooling gas inlet channel 10 and the swirl chamber 11 there is a barrier, on one side of which a set of swirl nozzles 12 are arranged, which are distributed equidistantly. The outer edge surface of the swirl chamber 11 is the same as the outer surface shape of the leading edge 1 of the turbine blade of the gas turbine, and the distance between the outer edge surface of the swirl chamber 11 and the surface of the leading edge 1 of the blade is equal everywhere, so that the arrangement of the swirl chamber is prevented from being limited by the shape of the blade, and the uniformity of cooling is ensured. After entering the air inlet channel 10, the cold air enters the group of swirl nozzles 12 with smaller area, further increase of the cold air flow speed is realized, and then the cold air tangentially enters the swirl chamber 11, impacts the spiral band 13 in the swirl chamber 11, and forms a rotating flow in the swirl chamber 11 under the spiral guide of the spiral band 13. The spiral ties 13 further promote the rotation of the cooling air in the swirl chamber to ensure better cooling of the leading edge surface between the two swirl nozzles 12. And the turbulence intensity of the internal cold air is enhanced, and the disturbance to the boundary layer is stronger. When the rotary motion of the cold air is increased, the retention time of the cold air in the cyclone chamber 11 is prolonged to a certain extent, so that the cold air can be fully utilized, the using amount of the cold air can be reduced, and the efficiency of the gas turbine is further improved. Furthermore, the presence of the helical ligaments 13 may act as fins, which may be beneficial to some extent in improving the heat transfer effect, and finally the cooling gas is discharged from the film holes 13 at the blade tip.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and improvements can be made without departing from the principle of the present invention, and these modifications and improvements should also be considered as the protection scope of the present invention.