NDLI: Heat Transfer and Film Cooling of Blade Tips and Endwalls

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Naik, S. Georgakis, C. Hofer, T. Lengani, D.
Copyright Year	2010
Abstract	This paper investigates the flow, heat transfer and film cooling effectiveness of advanced high-pressure turbine blade tips and endwall. Two blade tip configurations have been studied, including a full rim squealer and a partial squealer with a leading edge and trailing edge cut-out. Both blade tip configurations have pressure side film cooling, and cooling air extraction through dust holes which are positioned along the airfoil camber line on the tip cavity floor. The investigated clearance gap and the blade tip geometry are typical of that commonly found in the high pressure turbine blades of heavy-duty gas turbines. Numerical studies and experimental investigations in a linear cascade have been conducted at a blade exit isentropic Mach number of 0.8 and a Reynolds number of 9 × 105. The influence of the coolant flow ejected from the tip dust holes and the tip pressure side film holes has also been investigated. Both the numerical and experimental results showed that there is a complex aero-thermal interaction within the tip cavity and along the endwall. This was evident for both tip configurations. Although, the global heat transfer and film cooling characteristics of both blade tip configurations were similar, there were distinct local differences. The partial squealer exhibited higher local film cooling effectiveness at the trailing edge but also low values at the leading edge. For both tip configurations, the highest heat transfer coefficients were located on the suction side rim within the mid-chord region. However on the endwall, the highest heat transfer rates were located close to the pressure side rim and along most of the blade chord. Additionally, the numerical results also showed that the coolant ejected from the blade tip dust holes partially impinges onto the endwall.
Sponsorship	International Gas Turbine Institute
Starting Page	1763
Ending Page	1775
Page Count	13
File Format	PDF
ISBN	9780791843994
DOI	10.1115/GT2010-23288
e-ISBN	9780791838723
Volume Number	Volume 4: Heat Transfer, Parts A and B
Conference Proceedings	ASME Turbo Expo 2010: Power for Land, Sea, and Air
Language	English
Publisher Date	2010-06-14
Publisher Place	Glasgow, UK
Access Restriction	Subscribed
Subject Keyword	Suction Turbine blades Cooling Blades Cascades (fluid dynamics) Reynolds number Clearances (engineering) Airfoils Pressure Flow (dynamics) Geometry Cavities High pressure (physics) Dust Gas turbines Chords (trusses) Coolants Film cooling Heat transfer coefficients Heat transfer Mach number
Content Type	Text
Resource Type	Article

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