The effect of other parameters on the film cooling is also reported. The numerical results are validated by simple experimental test in this study.X. C. LiG. SubbuswamyJ. Zhou能源与动力工程(英文)Li XC, Subbuswamy G, Zhou J. Performance of gas turbine film cooling with backward injection....
A novel film-cooling scheme for high temperature gas turbine applications was introduced in this paper. Compared with the traditional circular hole, the new scheme combines both the advantages of traditional film cooling with those of impingement cooling. The hole that transports coolant fluid from th...
GAS TURBINE ENGINE SHAPED FILM COOLING HOLE 专利名称：GAS TURBINE ENGINE SHAPED FILM COOLING HOLE 发明人：JinQuan Xu 申请号：US14769983 申请日：20140313 公开号：US20160003056A1 公开日：20160107 专利内容由知识产权出版社提供 专利附图：摘要：A component for a gas turbine engine includes a wall that ...
Coolant passages for gas turbine components Oldfield MLG, Lock GD (1998) Coolant passages for gas turbine components, UK Patent Application No. 9821639.3 (1998) for the new console converging slot hole turbine film cooling hole geometry. University of Oxford, Oxford... Gary D Lock,Martin L G ...
The hot gas temperature in gas turbine engines is far above the permissible metal temperatures. Advanced cooling technologies must be applied to cool the blades, so they can withstand the extreme conditions. Film cooling is widely used in modern high temperature and high pressure blades as an acti...
摘要：A film-cooled gas turbine component for a gas turbine has a surface exposed to a hot gas and a number of film-cooling openings open out, which film-cooling openings combined to form at least one row transverse to a flow direction of the hot gas. Each of the film-cooling openings ...
An experimental investigation was conducted to model the film-cooling performance for a turbine-vane leading edge using the stagnation region of a cylinder in cross flow. Experiments were conducted with a single row of spanwise-angled coolant holes for a range of the coolant blowing ratio with a...
COMPONENT FOR A GAS TURBINE ENGINE WITH A FILM HOLEA component 80 is provided and comprises at least one wall 82 comprising a first and a second surface 84, 86. At least one film cooling hole 90 extends through the wall 82 between the first and second surfaces 84, 86 and has an ...
The present study deals with trailing edge film cooling on the pressure side cutback of gas turbine airfoils. Before being ejected tangentially onto the inclined cut-back surface the coolant air passes a partly converging passage that is equipped with turbulators such as pin fins and ribs. The ...
The paper deals with a small but important part of the overall gas turbine engine combustion system and continues earlier published work on turbulence effects in film cooling to cover the case of film turbulence. Film cooling of the gas turbine combustor liner imposes certain geometric limitations ...