Swirl and impact combined turbine blade internal cooling structure
A turbine blade and internal cooling technology, applied in the direction of blade support components, stators, engine components, etc., can solve the problems of weak local heat exchange capacity, uneven temperature distribution, and affecting the application of swirl cooling, and achieve low pressure loss , flexible nozzle arrangement, and strong cross-flow resistance
Inactive Publication Date: 2018-06-12
XI AN JIAOTONG UNIV
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Problems solved by technology
However, the local heat transfer capacity of swirl cooling is weaker than that of impingement cooling
The current gas turbine inlet airflow temperature distribution is uneven, and there are local high-temperature areas such as "hot spots"; and swirl cooling cannot effectively deal with the distorted temperature field
This shortcoming affects the application of swirl cooling
Method used
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[0021] The present invention is described in further detail below in conjunction with accompanying drawing:
[0022] see Figure 1-2 , the turbine blade internal cooling structure combined with swirl flow and impact of the present invention includes an inlet chamber 1, a cooling chamber 5, an outlet 4 and several nozzles. The nozzles include impingement nozzles 3 and swirl nozzles 2 , and the air intake chamber 1 and cooling chamber 5 are connected through the swirl nozzles 2 and the impingement nozzles 3 . The swirl nozzles 2 and the impact nozzles 3 can be arranged equidistantly or unequally, or the number of the swirl nozzles and the impact nozzles can be freely combined, depending on the actual situation; the cross section of the swirl nozzle 2 is rectangular, located in the The position where the arc section of the chamber 5 is tangent; the cross section of the impact nozzle 3 is circular, perpendicular to the middle position of the upper surface of the cooling chamber 5...
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The invention discloses a swirl and impact combined turbine blade internal cooling structure which adopts swirl cooling and impact cooling. After cold air enters into an air inlet chamber, the cold air enters into a cooling chamber via swirl nozzles and impact nozzles, and a new composited flowing structure is generated through the mutual effect of a swirl and impact, so that cooling on the wall surface of the cooling chamber is realized. The swirl and impact combined turbine blade internal cooling structure has the characteristics of good heat exchange performance, low pressure loss and hightransverse current resisting ability, and can be used for internal cooling of turbine blades of a gas turbine and an aeroengine. With regards to heat exchange, the swirl and impact combined turbine blade internal cooling structure has the advantages of heat exchange distribution uniformity and high partial heat exchange strength, and is applicable to a gas environment where the temperature is highand a temperature field is not uniform; then, the transverse current resisting ability is high with respect to flowing, the pressure loss is little and the efficiency is high; and finally, the swirland impact combined turbine blade internal cooling structure is simple in structure and reliable in working, the nozzle distribution mode is flexible and the swirl and impact combined turbine blade internal cooling structure is suitable for large-scale industrial application.
Description
technical field [0001] The invention belongs to the field of impeller machinery, and relates to a turbine blade internal cooling structure combined with swirling flow and impact. Background technique [0002] At present, the gas temperature at the inlet of the turbine has reached above 1600K, far exceeding the heat resistance limit of the turbine blade material. Therefore, effective cooling measures must be taken for the blades in order to protect the blades from being damaged by high-temperature gas. Currently, the combination of impingement cooling at the leading edge of the blades, convective cooling of the serpentine channels inside the blades, cooling of the spoiler ribs at the trailing edge of the blades, and air film cooling are mainly used. Composite cooling method. As the inlet temperature of the turbine continues to increase, if the existing cooling structure continues to be used, the flow rate of the cooling gas must be increased, which will lead to a decrease in...
Claims
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IPC IPC(8): F01D5/18F01D9/04F01D25/12
CPCF01D5/18F01D5/187F01D9/041F01D25/12F05D2260/201
Inventor 李亮王杰枫周源远范小军杜长河
Owner XI AN JIAOTONG UNIV