Analysis of the buoyancy-induced heat transferin a rotating cavity

In order to get a better knowledge of the heat transfer in compressor cavities of aero-engines,the simplified rotating cavity with two-plane discs,a shaft and a cylindrical rim has been investigated numerically and compared with the available measurements.The numerical results in agreement with the available experiments show large-scale instabilities.The disk local Nusselt numbers show mainly radial rising distributions for the heated disks with radial rising temperature profiles.In the present work,at the Reynolds number of 20 000,the disk local Nusselt numbers are the correlations of the local Grashof number to the power of 1.89-2.6,and the value of the power is increased as the rotational Reynolds number goes up.At the rotational Reynolds number of 800 000,the local Nusselt numbers are the correlations of the local Grashof number to the power of 0.68-2.6,and the value of the power is decreased as Reynolds number goes up.The area-averaged disk Nusselt number is the correlation of the Reynolds number to the power of 0.479 and the rotational Grashof number to the power of 0.12.

航空发动机旋转盘腔内部流动换热特性研究进展综述

The rotating disk cavity is an important part of the cooling-air system of the aero engine,and it has obviously significance to study the internal flow and heat transfer characteristics of the disc cavity,which will be helpful to improve the efficiency of the aero engine.This paper summarizes the existing research results of domestic and overseas.The present work considers the test methods and calculation methods of the flow and heat transfer characteristics of the rotating disc cavity of the aircraft engine.It points out that,the main factors which affect the heat transfer characteristics are the disc chamber speed,the intake volume,the design of the disc cavity pre-rotation/despin structure,and the type of disc cavity system.The influence of these factors on the characteristics of flow heat transfer is summarized.Based on these factors,the disc cavity structure can be optimized and designed,which provides suggestions for reducing the weight of the turbine,improving the thrust-to-weight ratio of the aero engine,and improving the cooling efficiency.

Experimental and computational investigation on flow characteristics of rotating cavities with high inlet pre-swirl axial throughflow

As an integral part of the internal air system of aero-engines,the axial throughflow of the cooling air can interact with the cavity flow between the rotating compressor disks,forming a threedimensional,unsteady,and unstable flow field.The flow characteristics in an engine-like rotating multi-stage cavity with throughflow were investigated using particle image velocimetry,flow visualization technology and three-dimensional unsteady Reynolds-Averaged Navier-Stokes (RANS)simulations.The focus of current research was to understand the distribution of the mean swirl ratio and its variation with a wide range of non-dimensional parameters in the co-rotating cavity with high inlet pre-swirl axial throughflow.The maximum axial Reynolds number and rotational Reynolds numbers could reach 4.41×10^(4)and 1.24×10^(6),respectively.The velocity measurement results indicate that the mean swirl ratio is greater than 1 and decreases with an increase in the radial position.The flow structure is dominated by the Rossby number,and two different flow patterns (flow penetration and flow stratification) are identified and confirmed by flow visualization images.In the absence of buoyancy,the flow penetration caused by the precession of the throughflow makes it easier for the throughflow to reach a high radius region.Satisfactory consistency of results between measurements and numerical calculations is obtained.This study provides a theoretical basis and data support for toroidal vortex breakdown,which is of practical significance for the design of high-pressure compressor cavities.

Optimal multi-photon entanglement concentration with the photonic Faraday rotation

We put forward an optimal entanglement concentration protocol（ECP） for recovering an arbitrary less-entangled multi-photon Greenberger–Horne–Zeilinger（GHZ） state into the maximally entangled GHZ state based on the photonic Faraday rotation in low-quality（Q） cavity. In the ECP, only one pair of less-entangled multi-photon GHZ state and one auxiliary photon are required, and the concentration task can be realized by local operations. Moreover, our ECP can be used repeatedly to further concentrate the discarded items of conventional ECPs, which can increase its success probability largely. Under the practical imperfect detection condition, our protocol can still work with relatively high success probability. This ECP has application potential in current and future quantum communication.

Theoretical and Experimental Studies for the Transient Response of Cavity

During the transient state of aero-engine,cavity has evidently transient characteristics in the secondary air system.To investigate transient characteristics,theoretical and experimental studies were implemented for both static and rotating cavities.First of all,the typical transient response phenomena in secondary air system were investigated based on the basic concepts of the dynamic process.According to the basic theory of gas dynamics,the causes of transient phenomena were analyzed in two aspects,external disturbance,and system physical properties.Several dimensionless parameters were introduced to analyze the transient response characteristics of air system.Second,the experimental results of the static cavity indicated that the actual response time increased with the increase of the inlet pressure.The experimental results of the rotor-stator cavity showed that the low rotational speed on the response process had little effect,and the response time gradually increased when the speed continued to increase.Third,the test results of multiple components suggested that when the valve was opening the inlet pressure of the static cavity increased quickly and then reached a stable value,but the pressure of the static cavity,stable pressure cavity and rotor-stator chamber rose gradually.It was also obtained the actual response time of them was increased.The closer the measuring points were to the disturbance source,the shorter the delay time was.