This paper presents a numerical study of non-isothermal flow and heat transfer in an
enclosed rotor–stator disk cavity. Wall-resolved large-eddy simulation is implemented with …

The appropriate coolant mass flow of turbine blade rim seal has become an important issue
as turbine blades are exposed to increasingly higher thermal load owing to increased …

Turbine blade cooling air is facilitated in part by the pre-swirl system, a crucial part of the
aero-engine secondary air system. This article primarily focuses on the pre-swirl angle and …

In gas turbine and aeroengine, the rim seal is set between the turbine stator and rotor to
prevent ingestion of the high-temperature mainstream into the rotating cavity. This study …

To study the influence of the egress flow on the mainstream flow in a high-pressure turbine,
three-dimensional unsteady Reynolds-averaged Navier–Stokes (URANS) equations were …

为探究涡轮轮缘密封的精细化设计, 在径向轮缘密封结构的基础上引入一种高径位供气孔结构并
将高位孔作为主要的封严气路, 采用经实验验证的非定常雷诺平均(URANS) 数值方法 …

In modern aero-engine, the turbine rim seals whose purpose is to reduce the ingress are
located in a complex flow region between the mainstream and secondary air flows. The …

Rim seal structures and sealing flows are essential in aero engines for preventing hot gas
ingestion from mainstream to turbine disk cavities. A novel design method of rim sealing flow …

Hot gas ingestion refers to the phenomenon of mainstream hot gas flowing into the space
cavity of a turbine wheel. Previous studies have found that mainstream annulus pressure …

A conventional axial turbine drived by a pulse detonation combustor heavily challenges the
turbine cooling and hot gas sealing. In order to fully understand the physical behavior of …