Grooving gaseous film cooling hole
A technology of air film cooling and air film hole, which is applied in the direction of supporting elements of blades, engine elements, machines/engines, etc. It can solve the problems of strength reduction, limitation, and the inability of cooling gas to form a more uniform cooling air film, etc., to reduce resistance loss, good cooling effect
Inactive Publication Date: 2007-09-26
XI AN JIAOTONG UNIV
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Problems solved by technology
[0004] Most of the gas film cooling in the existing gas turbine adopts the discrete hole cooling method, but in this cooling method, the cooling gas cannot form a relatively uniform cooling film in the lateral direction, and the area between the holes is the weak area to be cooled
Although two-dimensional slot film cooling can form a uniform cooling film along the lateral direction, its strength is greatly reduced due to its structural discontinuity, which limits its practical application.
Therefore, in the 1960s, some scholars proposed the idea of combining slots and discrete holes (JP patent No.55-114806), which greatly improved the cooling effect, but they were all in the air film A horizontal slot is opened at the outlet of the hole, and the effective combination of the slot and the discrete air film hole is not realized
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[0022] Accompanying drawing is the specific embodiment of the present invention.
[0023] Specific embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.
[0024] Referring to Fig. 1 and Fig. 2, it is an axonometric view of a moving blade part of a gas turbine, the moving blade part includes a blade 25 and a base 5, the blade 25 includes a pressure surface 3 and a suction surface 4, and is located on the base 5 , the interior of the blade 25 is hollow, including two air-cooled cavities 13 , 14 and a trailing edge cavity 15 . There are many exhaust film holes 11 at the blade leading edge 7, some discrete air film holes 10 are arranged at the blade top 26, and the slotted air film cooling holes 12 designed by the present invention are arranged on the blade trailing edge portion, and the blade trailing edge end There are also discrete gas film holes 9 at the top.
[0025] The high-temperature gas 1 washes the blade ...
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Abstract
It relates to a grooving gaseous film cooling hole that comprises the No.1 and No.2 horizontal groove, discrete gas film hole, and sharp corner tongue. The No.1 horizontal groove is conducive to the horizontal diffusion and attachment to the wall of the cooling gas, the No.2 horizontal groove is conducive to the inflow of cooling gas and alleviating flowing loss, and the discrete air film hole is able to ensure the structural strength of the overall vane, the sharp corner tongue is conducive to the horizontal diffusion of cooling gas at the No.1 horizontal groove. Without affecting the structural strength of the vane, it can alleviate flow loss of the cooling gas, with better cooling effect and less cooling gas requirement.
Description
technical field [0001] This invention relates to cooling in turbine power plants, and more particularly to a slotted film cooling hole for reducing the temperature of the combustion chamber walls and turbine blades. Background technique [0002] Increasing the maximum temperature of the thermal cycle is the most basic technical approach to improve the performance of various thermal power machinery. Taking aero-engines as an example, the improvement of aircraft engine thrust largely depends on the increase of the total temperature before the turbine. According to calculations, for every 55°C increase in this temperature, the engine thrust can be increased by about 10°C under the condition that the engine size remains the same. %. The turbine inlet temperature increases at an average annual rate of 20°C, while the metal temperature resistance only increases at an annual rate of about 8°C. Therefore, even if the engine turbine components use high-temperature resistant material...
Claims
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Inventor王秋旺章大海陈秋炀曾敏
OwnerXI AN JIAOTONG UNIV