Abstract
The paper proposes a method of checking calculation of turbine cooled blades of gas turbine engines, which significantly reduces the execution time and complexity of calculation of their thermal state compared to direct numerical calculation in ANSYS CFX. The method is demonstrated by the example of calculation of a turbine nozzle blade with the impingement tube and the spot cooling of the leading edge. The module with a bank of generalized experimental data on heat transfer and resistance in the cooling channels is used for closure of calculation.
Full Text 
Sign-in/Register to access full text options
Sign-in/Register to access full text options 
Published version (
Free)
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
