Xi'an Jiaotong University

Huawei Device Co., Ltd.

Xi'an Aerospace Propulsion Test Technology Institute

Qiang Gao

Qiuwang Wang

Yining Wu

Min Zeng

Dongjie Zhang

Qiuyang Chen

Yu Liu

Wei Han

Jun Yang

Xu Wang

Tao Li

Wei Du

Xiyu Zhou

Long Jin

Weilai Zhou

Biao He

Chengke Wang

Li Guo

Fa Wang

Chang Xie

Yan Gao

Song Liu

Qing Xia

Binyun Tang

Yu Chen

Ming Han

Hongpeng Xu

Jibin Shen

Di Fang

Zongfeng Li

Ziyue Luo

Zuoyu Wu

Cai Sun

Yuanfeng Hu

Xiangbing Tang

Jinxuan Fang

Qinxu Pan

An application-level memory control group of a first application may be created when the first application is opened. An anonymous page of the first application is added to a least recently used linked list of the application-level memory control group, and a file page of the first application is added to a global least recently used linked list. An application-level memory control group is created in a dimension of an application, and an anonymous page of the application is managed in a refined manner. In addition, a file page of the application-level memory control group may be managed based on a global least recently used linked list.

Application-level memory control group memory reclamation

A cryogenic propellant rocket engine, a flowmeter calibration system and method for the cryogenic propellant rocket engine have been provided. The flowmeter calibration system for the cryogenic propellant rocket engine includes a container filling unit, a container, a supply pipeline, a weighing unit, a quick recovery container, a weighing and filling recovery unit and a recovery unit which are sequentially connected; the container filling unit is configured to connect a tank wagon with the container; and the supply pipeline includes a temperature sensor and a pressure sensor, as well as a first isolation valve, a reference flowmeter, a calibration flow adjusting manual valve, a vertical main pipe and N circumferentially and uniformly distributed horizontal pipes which are sequentially connected by a pipeline.

Flowmeter calibration system and method for cryogenic propellant rocket engine

The present invention provides a single shell-pass shell-and-tube heat exchanger with helical baffles, where within a single pitch, the helical baffles are separated into inner and outer parts along the radial direction of the shell. In the central portion of the inner space of the shell, an inner non-continuous helical form is employed; in other portion outside the central portion, doughnut shaped helical baffles with continuous curved surfaces are arranged to form an outer continuous helical baffle, and the outer helical baffles are arranged to surround the inner helical baffles. Furthermore, the present invention relates to a multiple shell-pass shell-and-tube heat exchanger with helical baffles, in which complete continuous helical baffles are provided in shell-sides other than the inner shell-pass, while non-continuous helical baffles or other flow guide means are employed in the inner shell-pass. The present invention makes flow patterns of fluids on the shell side more desirable, leading to a reduced flow pressure drop, and mitigate fouling, thus the heat transfer rate is improved and the service life of the heat exchanger is increased. The present invention also provides two methods for manufacture of continuous helical baffles, which ensure the concentricity of the tube bundle holes on each continuous helical baffle so as to facilitate installation of heat exchange tube bundles.

Shell-and-tube heat exchanger with helical baffles

Single shell-pass or multiple shell-pass shell-and-tube heat exchanger with helical baffles

Growing community of inventors

Shaanxi, China

Qiang Gao