Turbine heat transfer

TURBINE HEAT TRANSFER John E. Rohde National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio 44135 Improved turbine durability and performance and reduced development cost will all result from improved methrids of predicting turbine metal temperatures. As you know, better metal temperature prediction methods require improvements in the method of determining the hot gas flo'''' through the turbine passage and the cooling air flow inside the airfoil and in the methods of predicting the heat transfer rates on the hot gas-side and on the coolant-side of the airfoil. The overall turbine heat transfer effort ~s directed at improving all four of these areas of concern.

Achievement of these improvements requires a rigorous and systematic research effort from both the experimental and analytical sides. The experimental approach being pursued starts with fundamental experiments with simple shapes and flat plates; progresses on to more realistic cold, warm, or hot cascades; contiriues to progress on to more realistic warm turbine, large low-speed turbine, or transient turbine tests; and finally combines all the interactive effects in real-engine environment turbine tests. Analytical approaches being pursued also start with relatively simple mathematical models and progress to more realistic cases that include more interactive effects, and finally combines all the interactive effects of the turbine operating in the real engine environment.

Cutrently, contract and grant activities are being (or will be) conducted to obtain fundamental experimental data and to develop and/or compare analytical methods Ln all four areas of concern. These contract and grant activities will be discussed in detail later in this meeting by the respective principal'investigators.

Major NASA Lewis in-house turbine research efforts are being pursued to obtain more realistic .'lnd real-engine type turbine ~xperiments.' The NASA Lewis Research Center is in the process of activating our High Pressure-High Temperature Facility (HPF) with initial 20 atmosphere and 2500 F experimentation scheduled for the last quarter of 1982. HPF will provide the country with a known real-engine environment in ,~hich to conduct controlled aerothermodynamic and structural research studies. We envision a multiple role for HPF in providing engineering-quality research data for modeling a9d code verification, in defining a real-engine environment, and in evaluating advanced turbine cooling technology in a real-engine environment.

The major turoine research parameters of interest that will be measured or determined to provide a better understanding of the thermal, aerodynamic, and mechanical performance of air-cooled turbine airfoils are the following: 1) local hot gas recovery temperatures along the airfoil surfaces, 2) local airfoil wall temperature, 3) local hot gas-side heat transfer coefficients on the airfoil surfaces, 4) local coolant-side heat transfer coefficients inside the airfoils, 5) local hot gas flow velocities and secondary flows at real-engine conditions, and 6) local delta strain range of the airfoil walls.

Currently, little of this type experimental research information exists with controlled warm or real-engine conditions and known boundary conditions.

These in-house turbine research efforts will be conducted using the best available analyses to help define the test co~figurations, the types of research measurements, and/or the test conditions and for the compariso,n with the measured research'results. Analytical efforts will initially use the best available flow and heat transfer codes such as a two- or three-dimensional inviscid flow code and a two- or three-dimensional boundary layer heat transfer code. These analyses will be applied at the mid-span section and possibly at the hub and tip sections or other local zones of the passage.

More sophisticated three-dimensional V1SCOUS codes and three-dimensional viscous codes with boundary layer resolution will be used as they become available. These analytical efforts will be conducted using the best available source or sources in-house and on contract with industry and universities.

~:~~~~~~~~r~~~~and TURBINE ENGINE HOT SECTION TECHNOLOGV

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Lewis Research Center TURBINE HEAT TRANSFER OBJECTIVES: IMPROVE ACCURACY OF PREDICTING LOCAL BLADE METAL TEMPERATURES USING COMPUTER CODES THAT ARE COMPATIBLE WITH STRUCTURAL ANALYSIS CODES APPROACH: • INVESTIGATE HOT GAS STREAM AND COOLANT PASSAGE FLOW MECHANICS AND HEAT TRANSFER • OBTAIN BENCHMARK-QUALITY AND ENGINEERING~QUALIrY DATA FOR EVALUATION AND IMPROVEMENT OF MODELS PRESENTLY USED IN PREDICTION CODES • UTILIZE IMPROVED MODELS TO IMPROVE ACCURACY OF PREDICTING LOCAL GAS- ......

N N SIDE AND COOLANT-SIDE HEAT TRANSFER COEFFICIENTS • UTILIZE FLOW MODELS TO IMPROVE ACCURACY OF PREDICTING LOCAL HOT GAS STREAM ENVIRONMEN~ THROUGH TURBINE ROWS AND COOLANT FLOW CONDITIONS INSIDE THE AIRFOIL • INTEGRATE IMPROVEMENTS IN PREDICTION OF HOT GAS STREAM ENVIRONMENT AND COOLANT FLOW AND LOCAL HOT GAS-SIDE AND COOLANT-SIDE HEAT TRANSFER COEFFICIENTS INTO IMPROVED METAL TEMPERATURE PREDICTION CODES • PROVIDE ENGINEERING-QUALITY TEST CASES FOR EVALUATION OF ACCURACY OF PREDICTION AN~ INPUT TO STRUCTURAL ANALYSIS CODES National Aeronautics and

Space Adminislralion TURBINE ENGINE HOT SECTION TECHNOLOGV

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Lewis Research Center BUILDING BLOCK AEROTHERMAL TURBINE RESEARCH APPROACH NASA HIGH REAL PRESSURE WORLD TURBINE CODE

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~~;:'and TURBINE ENGINE HOT SECTION TECHNOLOGY

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GAS-SIDE H,AI TRANSFER. NON- --DETERMINE INFLUENCE OF ROTATING. ;l-D VARIABLES ON FLOW TRANSITION AND DURATION AND IMPROVED MODELS GAS-SIDE HEAT TRANSFER. NON- --SAME AS ABOVE WITH FILM

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ROTATING. FILM COOL/N_G GAS FLOW ENVIRONMENT AND ,----------.,------.,-------, --OBTAIN BENc'iiuARK QUALITY AERO- '--- _____ --1. __ - ___ ...J ______ ...I THERMODYNAMIC DATA Al'1D IMPROVED HEAT TRANSFER. NON-ROTATING THREE-DIMENSIONAL VISCOUS FLOW CODES. NO ROTATION ......

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~:aT TRANSFER. ROTAT.ING • MULTIPLE JET ARRAY --IMPROVED HEAT TRANSFER CORRE- l IMPlfroEMENT LATION AND MODEL FOR IMPINGE- MENT COOLING COOLANT SIDE HEAT TRANSFER I _u --HEAT TRANSFER CORRELATIONS.

WITH ~OTATION AND ENTRANCE INCLUDING EFFECTS OF ROTA- GEOMETRY TIONS AND ENTRANCE GEOMETRY ~lETAL TEMPERATURE r - - - - - - - - - - - - -- - -, . --METAL TEMPERATURE PREDICTION PREDICTION CODES L- -- - - - - - - -- - - ----, CODES WITH IMPROVED HEAT TRANSFER MODELS/CORRELATIONS IN-ltoU5E RESEARCH ANn VERI FI CATIONS I~~- --VERIFICATIONS OF FLOW. HEAT TRANSFER METAL TEMPERATURES.

AND STRAIN PREDICTIONS, AT NEAR AND REAL-ENGINE TYPE CONDITIONS • II Nahonal Aeronautics and

Space Administration TURBINE ENGINE HOT SECTION TECHNOLOGY

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Lewis Research Center TURBINE HEAT TRANSFER POSSIBLY CONTRACT AND/OR IN-HOUSE: METAL TEMPERATURE PREDICTION CODES SCOPE: REVIEW AND MODIFY EXISTING AIRFOIL METAL TEMPERATURE CODES FOR EFFICIENT INCORPORATION OF DEVELOPED MODELS AND FOR INTERFACING WITH STRUCTURAL ANALYSIS CODES DURATI ON: THREE YEARS ......

N 1.11 APPROACH: • REVIEW EXISTING CODES • INCORPORATE IMPROVED MODELS DEVELOPED UNDER HOST • ASSURE EFFICIENT INTERFACING WITH STRUCTURAL CODES National Aeronaullcs and

Space Adminislration TURBINE ENGINE HOT SECTION TECHNOLOGY

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Lewis Research Center TURBINE HEAT TRANSFER IN-HOUSE RESEARCH AND VERIFICATIONS SCOPE: EXPERIMENTS AND ANALYSIS TO SUPPLEMENT CONTRACTUAL AND GRANT EFFORTS ON IMPROVING ACCURACY OF FLOW ENVIRONMENT AND HEAT TRANSFER PREDICTIONS AND THE VERIFICATION OF DEVELOPED/IMPROVED PREDICTION METHODS DURATION: SIX YEARS .....

N 0'1 APPROACH: • MEASURE LOCAL HEAT TRANSFER COEFFICIENTS OVER A STATOR VANE AT NEAR-~EAL ENGINE CONDITIO~S AND COMPARE WITH PREDICT~ON • PROCURE LASER ANEMOMETER SYSTEM AND INSTALL AND CHECK-OUT IN NASA WARM TURBINE • OBTAIN MEASUREMENTS IN NASA HIGH PRESSURE TURBINE "(HPT) AT NEAR REAL ENGINE CONDITIONS TO EVALUATE PREDICTION ACCURACIES OF CODES FOR HOT GAS FLOW~ HOT GAS ENVIRONMENT~ HOT GAS-SIDE AND COOLANT-SIDE HEAT TRANSFER COEFFICIENTS~ METAL TEMPERATURES~ AND STRAIN

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National Aeronautics and

Space Administration TURBINE ENGINE HOT SECTION TECHNOLOGY

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Space Administration TURBINE ENGINE HOT SECTION TECHNOLOGV

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National Aeronautics and .

Space Administration TURBINE ENGINE HOT SECTION TECHNOLOGY

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Lewis Research Center BUILT-IN GARDON TYPE LAMINATED TYPE HEAT FLUX SENSOR

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,iI •• Nallonal Aeronautics and Space Administration TURBINE ENGINE HOT SECTION TECHNOLOGY

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,II " ::"'~':1IOd TURBINE ENGINE HOT SECTION TECHNOLOGY

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~~c..- HOST IN-HOUSE HIGH TEMPERATURE TURBINE TESTING ELEMENT FYI 82 EXPECTED RESULTS CONDUCT HEAT TRANSFER ~-REAL ENGINE VALUES OF LOCAL c:=:I STUDIES OVER THE RANGE HOT GAS TEMPlRATURES, LOCAL OF REAL-EI~GINE. CONIlJTlONS HG & HC HOT GAS-SIDE. HEAT TRANSFER WI TH NON-FI UI COOLED COEFFICIENTS, AND LOCAL AIRFOILS COOLANT-SIDE HEAT TRANSFER COEFFICIENTS FOR COMPARISON WITH ANALYTltAL MODELS AND CODES VERIFICATION TEST OF --ASSESSMENT OF AIRFOIL METAL THE NASA BASELINE c=J TEMPERATURE PREDICTION CODES RESEARCH TURBINE WITH WITH THE NASA BASELINE RE- AIRFOIL METAL TEMPER- ,..... SEARCH TUIlBINE ATURE PREDICTION CODES W (J'I MAP THE THREE-DIMENSIONAL --VERIFY THE INVISCID FLOW FLOW FIELD IN A ROTATING c=J c:J REGION OF THE PASSAGE, WHICH PASSAGE WITH NO FILM WILL HAVE BEEN ESTABLISHED IN WARH HPT COOLING WARM TURDINE TESTS AND TURBINE ESTABLISH THE ACTUAL.VELOCI- TIES IN THE SECONDARY FLOW REGIONS OF THE PASSAGE FOR COMPARISON WITH FLOW CODES MEASURE BI-AXIAL STRAIN --ASSESSMENT OF STRUCTURAL CODES DELTAS AT CRITICAL c:::J WITH KNOWN THERMAL AND MECHANI- LOCATIONS ON STATIC AND CAL BOUNDARY tONDITIONS ROTATING AIRFOILS AND THE DISK VERIFICATION TEST OF ~ --ASSESSMENT OF AIRFOIL METAL ADVANCED TECHNOLOGY ~ TEMPERATURE PREDICTION CODES COOLED TURBINE WITH WITH AN ADVANtED TECHNOLOGY AIRFOIL METAL TEMPER- COOLED TURBINE ATURE PREDICTION CODES