Heat transfer, adiabatic effectiveness and injectant distributions downstream of single rows and two staggered rows of film-cooling holes with simple and compound angles. PDF
Preview Heat transfer, adiabatic effectiveness and injectant distributions downstream of single rows and two staggered rows of film-cooling holes with simple and compound angles.
DUDLEY KNOX LIBRARY POSTGRADUATE SCHOOI NAVAi MONTEREY CA 93943-5101 NAVAL POSTGRADUATE SCHOOL Monterey, California THESIS HEAT TRANSFER, ADIABATIC EFFECTIVENESS AND INJECTANT DISTRIBUTIONS DOWNSTREAM OF SINGLE ROWS AND TWO STAGGERED ROWS OF FILM-COOLING HOLES WITH SIMPLE AND COMPOUND ANGLES by Stephen Mark Jackson DECEMBER 1991 Thesis Advisor: Phillip Ligrani Approved for public release: Distribution is unlimited Unclassified SECURITYCLASSIFICATION OF THIS PAGE FormApproved REPORT DOCUMENTATION PAGE OMBNo0704-0188 1a. REPORT SECURITYCLASSIFICATION lb. RESTRICTIVE MARKINGS Unclassified 2a SECURITY CLASSIFICATIONAUTHORITY 3. DISTRIBUTION/AVAILABILITYOF REPORT Approved for public release: Distribution is 2b. DECLASSIFICATION/DOWNGRADING SCHEDULE unlimited 4. PERFORMING ORGANIZATION REPORT NUMBER(S) 5. MONITORING ORGANIZATION REPORT NUMBER(S) 6a. NAME OF PERFORMING ORGANIZATION 6b. OFFICE SYMBOL 7a. NAME OF MONrTORING ORGANIZATION (Ifapplicable) Naval Postgraduate School Naval Postgraduate School 6c ADDRESS (City, StateandZIPCode) 7b. ADDRESS (City, State, andZIPCode) CA CA Monterey, 93943-5000 Monterey, 93943-5000 8a. NAME OF FUNDING/SPONSORING 8b. OFFICE SYMBOL 9. PROCUREMENT INSTRUMENT IDENTIFICATION NUMBER ORGANIZATION (Ifapplicable) Naval Sea Systems Command 56X3 RGPLG 8c ADDRESS (City, State,andZIPCode) 10 SOURCE OF FUNDING NUMBER Dr. Dan. Groghan Naval Sea Systems Command EPLREOMGERNATMNO. NPOR.OJECT TNOA.SK WACOCREKSSUINOITN NO. Code 56X3 Washington, DC. 20352 LG2LG 1H1.ETAITTLET(RInAclNuSdeFSEecRu,ntyADClIasAsiBfiAcaTtiIonC) EFFECTIVENESS AND INJECTANT DISTRIBUTIONSDOWNSTREAM OFSINGLEROWSAND TWO STAGGERED ROWS OF FILM-COOLING HOLES WITH SIMPLE AND COMPOUND ANGLES 12 PERSONAL AUTHORS STEPHEN MARK JACKSON M 13a. TYPE OF REPORT 13b TIME COVERED 14. DATE OF REPORT (Year, Month, Day) AGE COUNT FROM TO DECEMBER Master's Thesis 1991 16 SUPPLEMENTARY NOTATION The views expressed are those of the author and do not reflect the official policy or position of the Department of Defense or the U.S. Government 17. COSATI CODES 18. SUBJECTTERMS (Continueonreverseitnecessaryandidentifybyblocknumbers) FIELD GROUP SUB-GROUP compound angle injection,simpleangle injection, film-cooling, turbulent boundary layer 19 ABSTFtACT (Continueonreverseifnecessaryandidentitybyblocknumbers) Experimental results for two compound angle injection systems (configurations 1 and 3), and for a simple injection system (configuration 2) are comparedin this thesis. Theeffects ofblowingratio, spanwiseholespacing, holeangleorientation, andstreamwiseposition (x/d)arediscussedin referencetomeasurementsofspanwise-averaged adiabaticeffectiveness,iso-energeticStantonnumber, andStantonnumber 6approximatelyequal to 1.5obtained downstream of both one row of holesand two staggered rows ofholes. Results indicate thateffectivenessdependsmostly on four parameters: simple or compound angle injection, spanwise hole spacing, one or two rows of holes, and blowing ratio. Results show that for a specifiedblowingratio,forall configurationstested todate, spanwise-averagedadiabaticeffectivenessisgreatestatlowerx/d valuesbutdecreases withstreamwisedevelopmentastheinjectantisconverteddownstream.Therateofspanwise-averagedadiabaticeffectivenessdecreaseisdependent on theblowing ratio, and mostly a result of lift-off of the injectant from thetestsurface at x/d valuesless than about 20. At larger x/d, spanwise- averaged adiabatic effectiveness values generally increase with blowingratiomostlybecauseofgreater amountsofinjectant along thetest surface. Resultsalsoshowthat theiso-energeticStantonnumbeTratioliesbetween 1 and 1.35forallcasesstudiedandgenerallyincreaseswithblowingratio for a given x/d. 20.XDXISUTNRCILBAUSTSIIOFNI/EADVA/IULNALBIIMLIITTEYDOF ABSTSRAAMCETAS RPT DTIC USERS 21.AuBnScTlRaAsCsTifSiECeUdRITY CLASSIFICATION 22a. NAME OF RESPONSIBLE INDIVIDUAL 22b. TELEPHONE (IncludeArea Code) 22c OFFICE SYMBOL Phillip Ligrani (408) 646-3382 ME/Li DD Form 1473, JUN 86 Previous editions are obsolete. SECURITYCLASSIFICATION OFTHIS PAGE S/N 0102-LF-014-6603 Unclassified Approved for public release: Distribution is unlimited Heat Transfer, Adiabatic Effectiveness and Injectant Distributions Downstream of Single Rows and Two Staggered Rows of Film-Cooling Holes with Simple and Compound Angles by Stephen Mark Tackson Lieutenant, United^States Navy B.S., United States Naval Academy, 1983 Submitted in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE IN MECHANICAL ENGINEERING from the NAVAL POSTGRADUATE SCHOOL DECEMBER 1991 ABSTRACT Experimental results for two compound angle injection systems (configurations 1 and 3), and for a simple injection system (configuration 2) are compared in this thesis. The effects of blowing ratio, spanwise hole spacing, hole angle orientation, and streamwise position (x/d) are discussed in reference to measurements of spanwise-averaged adiabaticeffectiveness, iso-energeticStanton number, and Stanton number for approximately equal to 1.5 obtained downstream of both one row of holes and two staggered rows of holes. Results indicate that effectiveness depends mostly on four parameters: simple or compound angle injection, spanwise hole spacing, one or two rows of holes, and blowing ratio. Results show that for a specified blowing ratio, for all configurations tested to date, spanwise-averaged adiabaticeffectiveness is greatest at lower x/d values but decreases with streamwise development as the injectant is convected downstream. The rate of spanwise-averaged adiabatic effectiveness decrease is dependent on the blowing ratio, and mostly a result of lift-off of the injectant from the test surface at x/d values less than about 20. At larger x/d, spanwise-averaged adiabatic effectiveness values generally increase with blowing ratio mostly because of greater amounts of injectant along the test surface. Results also show that the iso-energetic Stanton number ratio lies between 1 and 1.35 for all cases studied and generally increases with blowing ratio for a given x/d. m Ui'5 / tl TABLE OF CONTENTS INTRODUCTION I. 1 BACKGROUND/THEORY A. 1 B. PRESENT STUDY 7 EXPERIMENTAL OUTLINE C. 8 D. THESIS ORGANIZATION 9 EXPERIMENTAL APPARATUS AND PROCEDURES H. 10 A. WIND TUNNEL AND COORDINATE SYSTEM 10 INJECTION SYSTEM AND INJECTION B. CONFIGURATIONS 11 1. Injection System 11 2. Injection Configuration 12 C. STREAMWISE MEAN VELOCITY MEASUREMENTS 13 STANTON NUMBER MEASUREMENTS D. 13 MEAN TEMPERATURE MEASUREMENTS E. 14 BASELINE DATA CHECKS F. 15 HI. EXPERIMENTAL RESULTS 16 A. CONFIGURATION TWO, SIMPLE ANGLE RESULTS 16 1. Heat Transfer Measurements Downstream of Two Rows Of Film-Cooling Holes With m=0.5 16 2. Heat Transfer Measurements Downstream Of Two Rows Of Film-Cooling Holes With m=1.05 17 3. Heat Transfer Measurements Downstream Of Two Rows Of Film-Cooling Holes With m=1.5 18 IV
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