Results 71 to 80 of about 98,675 (218)

Effect of rotation on film cooling with a single row of shaped holes on blade pressure side

Journal of Thermal Science and Technology, 2017
A numerical investigation is performed to illustrate the mutual interaction between coolant jet issuing from shaped film cooling hole and cascade primary flow as well as the resulting film cooling performance under rotational condition. Four various film-
Xingdan ZHU, Jingzhou ZHANG, Xiaoming TAN, Yong SHAN   +3 more
doaj   +1 more source

Effect of shocks on film cooling of a full scale turbojet exhaust nozzle having an external expansion surface [PDF]

Experimental film cooling data obtained during exploratory testing with an axisymmetric plug nozzle having external expansion and installed on an afterburning turbojet engine in an altitude test facility is presented.
Straight, D. M.
core   +1 more source

Film cooling characteristics of squealer tip of a turbine blade

Xibei Gongye Daxue Xuebao
The high-speed and high-temperature gap leakage flow in the turbine blade tip clearance directly scours the tip of the rotor blade and generates a local high-temperature region, so the active and passive control of the gap leakage flow is very important.
WU Fangfang, XU Weijiang, LIU Cunliang, SHI Jingyin, YU Zeyu   +4 more
doaj   +1 more source

Comparison of heat transfer characteristics of three cooling configurations for air-cooled turbine vanes tested in a turbojet engine [PDF]

A comparison was made of the heat transfer characteristics of three air cooled vanes. The vanes incorporated cooling schemes such as impingement cooling, film cooling, and convection cooling with and without extended surfaces.
Gauntner, J. W., Gladden, H. J., Yeh, F. C.   +2 more
core   +1 more source

Numerical solution for the temperature distribution in a cooled guide vane blade of a radial gas turbine [PDF]

A two dimensional finite difference numerical technique is presented to determine the temperature distribution of an internal cooled blade of radial turbine guide vanes. A simple convection cooling is assumed inside the guide vane blade. Such cooling has
Hosny, W. M., Tabakoff, W.
core   +1 more source

The film cooling performance of spiral-channel holes on turbine guide vane

Case Studies in Thermal Engineering
A spiral-channel hole is implemented to heighten the cooling performance of turbine vanes by inducing swirling flow. Numerical simulations examine and compare the film effectiveness and flow structure at four positions.
Yuhao Jia, Yongbao Liu, Zewei Meng, Xing He, Yang Liu   +4 more
doaj   +1 more source

Computational research on film cooling performance of different shaped holes with backward and forward injection

AIP Advances, 2019
The present work has been performed to evaluate the effect of three shaped holes (cylindrical hole, expansion-shaped hole and fan-shaped hole) with forward injection and backward injection on film cooling effectiveness on the adiabatic wall flat plate ...
Zi-chen Zhao, Li-ming He, Sheng-ji Dai, Shuai Shao   +3 more
doaj   +1 more source

The effectiveness of film cooling

, 1970
Imperial Users ...
Pai, Bhaskar Ramchandra, Pai, Bhaskar Ramchandra   +1 more
openaire   +1 more source

Cooling Performance of Impingement–Effusion Double-Wall Configurations Under Atmospheric and Elevated Pressures

Applied Sciences
The combustor liner of the modern aero-engine operates under extreme thermal loads with limited coolant supply, necessarily making efficient cooling approaches important.
Rongxing Zhang, Wei Li, Jianbai Jiang, Xudong Lang, Jinxin Dai, Tianyou Lian, Xiaoxiang Shi, Wei Li   +7 more
doaj   +1 more source

Research on coupled heat transfer of film cooling in LOX/GH2 thrust chambers

Journal of Thermal Science and Technology, 2018
To better understand the performance of gaseous film cooling near the injector region in the LOX/GH2 thrust chambers, a methodology is employed to simulate the coupled heat transfer of the film cooling in thrust chambers with regenerative cooling.
Jixin XIANG, Bing SUN
doaj   +1 more source