Film cooling from spanwise-oriented holes in two staggered rows

Journal Article · Tue Jul 01 04:00:00 EDT 1997 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2841158· OSTI ID:516726

Ligrani, P M ^[1]; Ramsey, A E ^[2]

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1. Univ. of Utah, Salt Lake City, UT (United States)
2. Naval Postgraduate School, Monterey, CA (United States). Dept. of Mechanical Engineering

Adiabatic effectiveness and iso-energetic heat transfer coefficients are presented from measurements downstream of film-cooling holes inclined at 30 deg. With respect to the test surface in spanwise/normal planes. With this configuration, holes are spaced 3d apart in the spanwise direction and 4d in the streamwise direction in two staggered rows. Results are presented for an injectant to free-stream density ratio near 1.0, and injection blowing ratios from 0.5 to 1.5. Spanwise-averaged adiabatic effectiveness values downstream of the spanwise/normal plane holes are significantly higher than values measured downstream of simple angle holes for x/d < 25--70 (depending on blowing ratio) when compared for the same normalized streamwise location, blowing ratio, and spanwise and streamwise hole spacings. Spanwise-averaged iso-energetic Stanton number ratios range between 1.0 and 1.41, increase with blowing ratio at each streamwise station, and show little variation with streamwise location for each value of blowing ratio tested.

• Sponsoring Organization: USDOE
• OSTI ID: 516726
• Report Number(s): CONF-950629--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 3 Vol. 119; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
CAPACITY
COOLING SYSTEMS
EFFICIENCY
FILM COOLING
GAS TURBINE ENGINES