阅读说明：本技术 通过调控内部灰尘沉积位置减缓冷却效果退化的涡轮叶片 (Turbine blade for slowing down cooling effect degradation by regulating and controlling internal dust deposition position ) 是由 李广超 王裕东 张魏 赵长宇 曾睿 寇志海 朱建勇 毛晓东 于 2019-12-03 设计创作，主要内容包括：通过调控内部灰尘沉积位置减缓冷却效果退化的涡轮叶片,所属燃气轮机技术领域,涡轮叶片为双层壁结构,在现有双层壁的内壁上连接有遮挡结构。本发明涡轮叶片通过遮挡结构来调控内部灰尘沉积位置,以减缓涡轮叶片的冷却效果退化问题,沉积在双层壁的灰尘可减少10％～13％,从而可减缓20％～23％叶片冷却效果退化时间,并且遮挡结构形状较为简单,易于加工,可实现性强。(The turbine blade is of a double-wall structure, and a shielding structure is connected to the inner wall of the existing double-wall structure. The turbine blade regulates and controls the deposition position of the dust in the turbine blade through the shielding structure so as to slow down the degradation problem of the cooling effect of the turbine blade, the dust deposited on the double-layer wall can be reduced by 10-13%, so that the degradation time of the cooling effect of the blade can be slowed down by 20-23%, and the shielding structure is simple in shape, easy to process and strong in realizability.)

1. Through the turbine blade that slows down cooling effect degradation of regulation and control inside dust deposit position, turbine blade is the double-walled structure, specifically includes inner wall, outer wall and vortex post, the vortex post is located between inner wall and the outer wall, be provided with the air film hole on the outer wall, be provided with the jet orifice on the inner wall, be connected with on the inner wall and shelter from the structure, shelter from the structure and be located the jet orifice upper reaches, shelter from structure and jet orifice central distance for the aperture 1 ~ 1.5 times of jet orifice.

2. The turbine blade for mitigating degradation of cooling effectiveness by modulating the location of internal dust deposition as recited in claim 1, wherein said shielding structure is a right angle baffle, a quarter circle baffle, a baffle that forms an included angle with the inner wall surface, or vertical and horizontal baffles that meet at a rounded corner.

3. The turbine blade for mitigating degradation of cooling effects by modulating internal dust deposition locations as recited in claim 2, wherein said right angle shaped baffles have a length to height ratio of vertical to horizontal baffles of (1.5-2.5): 1 and a length to width ratio of (1.5-2.5): 1.

4. The turbine blade for mitigating cooling degradation by modulating internal dust deposition locations as recited in claim 2, wherein a length to radius ratio of said quarter circle baffle is (1.5-2.5): 1.

5. The turbine blade for slowing the degradation of cooling effect by regulating the position of internal dust deposition as claimed in claim 2, wherein the included angle of the baffle plate forming an included angle with the inner wall surface is in the range of 30 ° to 60 °, and the ratio of the length to the height is (1.2-1.5): 1.

6. The turbine blade for mitigating degradation of cooling effects by modulating internal dust deposition locations as recited in claim 2, wherein said rounded vertical and horizontal baffles have a length to height ratio of (1.5-2.5): 1 and a length to width ratio of (1.5-2.5): 1.

7. The turbine blade for mitigating cooling degradation by modulating internal dust deposition locations as recited in claim 1, wherein a ratio of length to thickness of said shielding structure is (7-9): 1.

Technical Field

The invention belongs to the technical field of gas turbines, and particularly relates to a turbine blade for slowing down cooling effect degradation by regulating and controlling an internal dust deposition position.

Background

As gas turbine technology develops, turbine front temperatures increase further, placing greater demands on cooling of turbine blades. Currently, the cooling method inside the blade in the prior art mainly includes convection cooling and impingement cooling, wherein the impingement cooling is the most effective method for enhancing the local cooling effect. The impingement cooling mainly utilizes high-speed airflow to scour a cooled surface so as to achieve the purpose of cooling, cooling air enters a double-wall structure with turbulence columns through jet holes, the airflow trends to be shown in figure 1, impacts the cooled surface to realize impingement cooling, then flows inside, carries out heat convection with the inner wall surface of a blade, and flows out through air film holes after taking away a part of heat.

Because the engine inevitably inhales dust when the aircraft takes off, lands or passes through the volcanic ash cloud layer, the cooling air with the dust enters the double-wall structure through the jet holes, the dust can form deposition in the double-wall structure, and the heat conductivity of the dust is relatively small, namely, a great thermal resistance is increased in the heat transfer process, and the heat exchange capacity and the cooling effect of the blades are seriously influenced. Especially the deposition on the impact target surface, greatly weakens the impact cooling effect, thereby causing the attenuation of the cooling performance of the blade.

The existing turbine blade has no effective measure for inhibiting the deposition of internal dust, the problem of dust deposition is increasingly prominent, and the problem of dust deposition in the blade is very important for the stable operation of a high-performance gas turbine.

Disclosure of Invention

In order to solve the problems, the invention provides a turbine blade for slowing down the degradation of the cooling effect by regulating and controlling the deposition position of internal dust, and the degradation of the cooling effect of the turbine blade is slowed down by regulating and controlling the deposition position of the internal dust, and the specific technical scheme is as follows:

the turbine blade is of a double-wall structure and specifically comprises an inner wall, an outer wall and a turbulence column, wherein the turbulence column is located between the inner wall and the outer wall, an air film hole is formed in the outer wall, a jet hole is formed in the inner wall, a shielding structure is connected to the inner wall and located at the upstream of the jet hole, and the distance between the shielding structure and the center of the jet hole is 1-1.5 times of the aperture of the jet hole;

the shielding structure is a right-angle baffle, a quarter-ring baffle, a baffle forming a certain included angle with the inner wall surface or a vertical baffle and a horizontal baffle connected by a fillet;

the ratio of the length to the height of the vertical baffle to the height of the horizontal baffle of the right-angle baffle is (1.5-2.5) to 1, and the ratio of the length to the width of the vertical baffle to the width of the horizontal baffle is (1.5-2.5) to 1;

the ratio of the length to the radius of the quarter-circular baffle is (1.5-2.5): 1;

the included angle of the baffle forming a certain included angle with the inner wall surface ranges from 30 degrees to 60 degrees, and the ratio of the length to the height is (1.2-1.5): 1;

the ratio of the length to the height of the vertical baffle and the horizontal baffle which are connected by the fillets is (1.5-2.5) to 1, and the ratio of the length to the width of the vertical baffle and the horizontal baffle is (1.5-2.5) to 1;

the ratio of the length to the thickness of the shielding structure is (7-9): 1.

Compared with the prior art, the turbine blade for retarding the degradation of the cooling effect by regulating and controlling the deposition position of the internal dust has the beneficial effects that:

firstly, the turbine blade is additionally provided with the shielding structure, air with dust flowing in a cross flow mode in the cold air cavity impacts the structure firstly before entering the jet hole, and the dust moves close to the wall surface due to the fact that the density of the dust is larger than that of the air, strikes the shielding structure and forms deposition, the effect of blocking the dust is achieved, the dust in the cold air is deposited in the cold air channel, the movement of the dust is controlled based on a source, and the dust is prevented from entering the double-wall structure. The dust entering the double-layer wall is reduced by 10 to 13 percent compared with the prior dust.

The temperature difference of fluid on two sides of the impact target surface is large and is a main carrier for heat transfer on the gas side of the blade, the temperature difference between fluid in the cold air cavity and fluid in the double-wall inner part is small, the wall surface heat exchange quantity is small, the space of the cold air cavity is large compared with the inner part of the double-wall inner part, therefore, dust is deposited in the cold air cavity through regulation and control, deposition in the double-wall inner part is reduced, and the heat exchange capacity and the cooling effect of the blade can be guaranteed to a great extent. The time for keeping the good cooling effect of the blade is increased by 20-23 percent compared with the prior art.

The problem that the air film holes of the turbine blades are small in aperture and often blocked is solved, the scheme of the invention reduces the deposition of dust in the double-layer wall, the possibility of blocking the air film holes is reduced, the air film holes flow out smoothly, and the air film cooling effect is not influenced. The non-blocking time of the air film hole is increased by 3-5 percent compared with the prior art.

Fourthly, the trend of the airflow is as follows: after the cold air passes through the shielding structure, rotational flow is generated to enter the jet hole, and the reinforced heat exchange in the double-wall structure is facilitated to a certain extent.

Fifthly, the shielding structure is simple in shape, easy to process and strong in realizability. Slowing the degradation of the cooling effect of the blade also means that the effective service time of the blade is increased, and the maintenance and replacement cost is reduced.

Drawings

FIG. 1 is a schematic view of a turbine blade double wall structure and airflow direction of the prior art;

FIG. 2 is a schematic view of the double wall and air flow direction of the turbine blade of example 1;

FIG. 3 is a schematic view of the double-walled structure of the turbine blade with the addition of the right-angled baffle and the air flow direction in accordance with the embodiment 1;

FIG. 4 is a schematic view of the double-walled structure of the turbine blade and the flow direction of the turbine blade with the quarter-circle baffle added in the embodiment 2;

FIG. 5 is a schematic view of a double-walled structure of a turbine blade and the flow direction of the turbine blade in which baffles forming a certain included angle with the inner wall surface are added according to embodiment 3;

FIG. 6 is a schematic view of the double-walled structure of the turbine blade and the flow direction of the turbine blade with the addition of the vertical and horizontal baffle plates connected by the fillets of the embodiment 4;

FIG. 7 is a schematic top view of a double-walled turbine blade of the present invention;

in the figure: 1-inner wall, 2-outer wall, 3-turbulence column, 4-air film hole, 5-jet hole and 6-shielding structure.

Detailed Description

The present invention will be further described with reference to specific examples, but the present invention is not limited to these examples.