With regard to cooling turbine blades in a gas turbine engine a compromise has to be made between convective cooling within the inner cavity defining a flow path for coolant and the blow rates for developing film cooling on an outer surface of the aerofoil. By providing a chamber between the flow cavity and external apertures reconciliation between the necessary flow rates for convective cooling within the cavity defining the pathway for coolant flow within the aerofoil and the necessary coolant blowing rate for film development can be achieved.
申请公布号
US8322987(B2)
申请公布日期
2012.12.04
申请号
US20090457585
申请日期
2009.06.16
申请人
WEBSTER ADRIAN J.;TOWNES RODERICK M.;TIBBOTT IAN;ROLLS-ROYCE PLC