The development of modern gas turbines for aircraft propulsion and power generation
demands ever-increasing efficiency, which can be achieved by rising the turbine inlet …

In order to explore new cooling methods to further improve the cooling performance for the
gas turbine blade leading edge, a vortex double wall cooling configuration is established …

To compare the behavior of different cooling methods for gas turbine blade leading edge,
configurations of impingement cooling, vortex cooling and double vortex cooling are …

In this paper, 3D viscous steady Reynolds Averaged Navier–Stokes (RANS) equations are
utilized to investigate the influence of jet nozzle geometry on flow and thermal behavior of …

Impingement cooling is applied on the turbine blade leading edge which suffers the highest
heat transfer and needs priority protection. The current work focuses on the rotational effects …

Abstract Based on combined Infrared Thermography and numerical simulations, the heat
transfer and flow performance in a vortex cooling configuration with 5 nozzles were …

This paper presents a comparative experimental and numerical study of heat transfer and
pressure loss characteristics in swirl tubes with one (S1) and five (S5) tangential inlet jets …

In this paper, four swirl and impingement composite cooling structures are established to
deeply study the flow and heat transfer characteristics, where the swirl nozzles and …

Swirl cooling is one of the latest and promising internal cooling strategies, which has been
widely reported in the designs of the turbine blade leading edges. Based on the traditional …

In this paper, we present a detailed experimental and numerical study of the flow
phenomena and the heat transfer in swirl tubes with one and multiple tangential inlet jets …