Gradually widened slot staggered rib passage suitable for internal cooling member as turbine blade

A technology of staggered ribs and cooling channels, applied in the directions of blade support elements, engine elements, machines/engines, etc., can solve the problems of large pressure loss and low utilization rate of cold air, and achieve thermal stress reduction and heat transfer uniformity optimization. , the effect of reducing the flow resistance

Inactive Publication Date: 2008-01-09
BEIHANG UNIV
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However, the shortcomings of this structure are also very obvious, such as

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  • Gradually widened slot staggered rib passage suitable for internal cooling member as turbine blade
  • Gradually widened slot staggered rib passage suitable for internal cooling member as turbine blade
  • Gradually widened slot staggered rib passage suitable for internal cooling member as turbine blade

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[0021] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0022] The present invention is a conclusion obtained by studying its heat transfer and flow resistance characteristics through simplified model experiments and three-dimensional numerical simulations. Experimental and numerical researches on the heat transfer and flow resistance characteristics of the straight slot (5) staggered rib channel vary with the groove width w This law is discovered when changing relationships. The research results show that the drag coefficient of the channel keeps decreasing as the groove width w increases. Grooving increases the heat transfer effect of the channel mainly in the first half of the fluid flow, and different groove widths have little effect on the second half of the channel. Therefore, it can be considered that the slot width w corresponding to the best heat transfer effect should be selected in the first half of the cha...

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Abstract

This invention is a turbine blade internal cooling structure. This cooling structure is a notched crossed-rib channel, which groove width increases gradually along from channel inlet to outlet. For the crossed-rib channel that is long along the flow direction, the inner fluid flow resistance will decrease when both sides of channel have micro pass way with the best width. Thus, the heat exchanging ability of inter-fluid will increase. This invention realizes the optimizing design of turbine blade cooling structure.

Description

technical field [0001] The present invention is a cooling structure suitable for internal cooling components such as turbine blades. In the cooling structure, grooves are slotted on both side walls of the staggered rib channel facing the center direction, and the width of the slot gradually increases along the direction from the channel inlet to the outlet. A gradually widening ribless channel is formed. Background technique [0002] In a gas turbine engine, the turbine blades are next to the combustion chamber, where the ambient temperature is locally as high as 2000K. In order to improve the thermal efficiency of the gas turbine engine, it is generally used to increase the temperature before the turbine, which brings about an increase in the heat load of the turbine components. In addition, the turbine blades (working blades) work at high speeds (up to 15,000rpm or more), and are in a very high centrifugal force field. In such a harsh working environment, to ensure the n...

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Application Information

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IPC IPC(8): F01D5/18
Inventor 邓宏武徐国强陶智丁水汀闻洁谭艳
Owner BEIHANG UNIV
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