Abstract
This paper studied the combined influences of the hot streak and swirl on the cooling performances of the NASA C3X guide vane coated with or without thermal barrier coatings (TBCs). The results show that: (1) Even under uniform velocity inlet conditions, the hot streak core can be stretched as it impinges the leading edge which causes higher heat load on the suction side of the forward portion. (2) The swirl significantly affects circumferential and radial migration of the hot streak core in the NGV passage. On the passage inlet plane, positive swirl leads to a hotter tip region on the suction side. In comparison, negative swirl leads to a hotter hub region on the pressure side. (3) Under the influence of swirl, migration of coolant improves the coverage of film cooling close to the midspan, while in the regions close to the hub and tip end-wall, the overall cooling performance decreases simultaneously. (4) In the regions with enough internal cooling, the cooling effectiveness increment is always larger than that in other regions. Besides, the overall cooling effectiveness increment decreases on the region covered by film cooling for the coated vane, especially in the region with negative local heat flux.
Highlights
Gas turbine, as one of the most advanced thermal prime movers, has achieved rapid development in aviation, power generation, shipping, petrochemical and other industries [1]
This paper studies the combined influences of hot streaks and swirls on the cooling performances of the NASA C3X guide vane coated with or without thermal barrier coatings (TBCs)
Even with uniform velocity inlet condition, the hot streak core can be stretched as it impinges on the leading edge which causes a higher heat load on the suction side of forward portion
Summary
As one of the most advanced thermal prime movers, has achieved rapid development in aviation, power generation, shipping, petrochemical and other industries [1]. Because of the continuing demand for improvement of thermal efficiency and power, typical turbine inlet temperatures frequently exceed the highest allowable material temperature of airfoils [2]. Under such harsh running conditions, the turbine vane has to be protected to guarantee safe running conditions [1,2]. Typical advanced cooling techniques include internal cooling, film cooling as well as the use of thermal barrier coatings (TBCs) [3]. Because of the limited opportunities for further improvement of the film cooling performance, typically advanced gas turbine airfoils usually incorporate both TBCs and film cooling techniques [3,4]
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