The film cooling technique is one of the most useful cooling methods. At present, the midchord region of gas turbine blades in an aeroengine often adopt a sparse film cooling technique and impingement cooling technique at the same time. So the interior heat transfer characteristics on the inner side
โฆ LIBER โฆ
Transition modelling for the prediction of the heat transfer coefficient of a gas-turbine blade
โ Scribed by B.A. Jubran; M.A. Hamdan; A.I. Al-Sayeh
- Publisher
- Elsevier Science
- Year
- 1994
- Tongue
- English
- Weight
- 565 KB
- Volume
- 49
- Category
- Article
- ISSN
- 0306-2619
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When a contmuous cylmder IS cooled by passmg lt longltudmally through a qmet flmd (free convecfion IS not consldered) then the followmg relatlon for the local heat transfer coefficlent can be glven The group d(Pรฉ,)/P&. allows for the curvature of the cylmder. the fourth dlmenslonless group accommoda