1

Here

News Discuss 
In transonic high-pressure turbine stages. oblique shocks originating from vane trailing edges impact the suction side of each adjacent vane. High-pressure vanes are cooled to tolerate the combustor exit-temperature levels. then it is highly probable that shock impingement will occur in proximity to a row of cooling holes. https://www.pomyslnaszycie.com/

Comments

    No HTML

    HTML is disabled


Who Upvoted this Story