Research on cooling effect with coolant groove structure parameters in platelet transpiration cooled nosetip

Abstract

A platelet transpiration cooled nosetip is considered as thermal protection system (TPS) to prevent hypersonic vehicle from the serious aerodynamic heating. Based on the one dimensional flow model, a distribution model of coolant is proposed for the temperature calculation. When Si = Sj (i, j=1,…,24), the first cooling effect parameter Pmax is proposed and its relationship with total mass flux and Sc0/Si is investigated. The result shows that Pmax increases while the total mass flux increases, and when the mass flux is fixed, Pmax increases rapidly at the beginning and then turns to a nearly stable value while Sc0/Si increases. Then under the precondition of cooling effect, we fix Sc0/Si to insure there is enough space for the pipe. Numerical investigation shows the design of the nosetip makes the transpiration cooling extremely effective. In order to reduce the temperature difference on the nosetip, the second cooling effect parameter Pdiff is proposed and different Pdiff with different θgi (i=1,…, 23) are analyzed. According to the cases we design, Pdiff decreases while the upstream θgi decreases or the downstream θgi increases. The best result among cases shows Pdiff is reduced by 15.1%.

Film Cooling Effect on the Nosetip in Hypersonic Flow

“…The protection of its body from strong aerodynamic heating is most important and difficult issues in the development of hypersonic transportation system. Many types of cooling system have been investigated for hypersonic vehicles [1][2][3][4][5][6]. Among them, film cooling is taken for a promising thermal protection system because of its high efficiency [6].…”