NDLI: Analysis of Cooling Effectiveness and Heat Transfer Variations on the End Wall of a Nozzle Guide Vane Caused by Turbine Leakage Flows

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Dannhauer, Axel
Copyright Year	2008
Abstract	Extensive thermodynamic measurements were carried out on a vane endwall to investigate the interaction with the upstream rotor leakage flow. The experiments were performed at the low speed cascade wind tunnel (NGG) of the German Aerospace Centre (DLR), Go¨ttingen. The investigated cascade consists of three large nozzle guide vanes. The effect of tip leakage flow was simulated by blow-off air. This was ejected through a leakage gap in the side wall closely upstream of the cascade. To investigate the different, possible constructive solutions of tip clearances, at least two different blowing directions were investigated: tangential and perpendicular to the mainstream at three different mass flow ratios. The influence of inlet turbulence was investigated too, applying an active turbulence grid in the intake. To get a realistic temperature gradient the leakage air was cooled down by a heat exchanger to adjust a distinctive temperature difference to the mainstream. The surface temperatures were detected by an infrared camera. Heat flux measurements assisted the interpretation of the resulting distributions of film-cooling effectiveness. It appeared that even for perpendicular injection a large amount of leakage air is distributed to the front area of the end wall although the secondary flow structure is amplified. The leakage air for mass flow ratios until 1.0% is visible between the 3D-separation lines of the horseshow vortices. With tangential ejection an adiabatic effectiveness of ηaw = 0.2 at the cascade outlet was detectable. For both investigated injection directions it was possible to weaken the three dimensional vortex structures. For a further increase in resolution of the adiabatic effectiveness some examinations applying the so-called superposition method were performed.
Sponsorship	International Gas Turbine Institute
Starting Page	543
Ending Page	552
Page Count	10
File Format	PDF
ISBN	9780791843147
DOI	10.1115/GT2008-50555
e-ISBN	0791838242
Volume Number	Volume 4: Heat Transfer, Parts A and B
Conference Proceedings	ASME Turbo Expo 2008: Power for Land, Sea, and Air
Language	English
Publisher Date	2008-06-09
Publisher Place	Berlin, Germany
Access Restriction	Subscribed
Subject Keyword	Tip leakage gap Adiabatic efficiency Shrouded turbine vane Secondary flow field Leakage ejection Heat transfer Leakage Temperature Turbulence Cooling Wind tunnels Cascades (fluid dynamics) Rotors Heat exchangers Separation (technology) Flow (dynamics) Aerospace industry Heat flux Temperature gradient Vortices Nozzle guide vanes Film cooling Resolution (optics) Leakage flows Turbines
Content Type	Text
Resource Type	Article

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