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Broad Specificationfuels on High B ,Passturbofan Engine Combustors

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Broad Specificationfuels on High B ,Passturbofan Engine Combustors A/',d_*,,e'/_-/_2 _ Y/ 3 1176 00156 6455 NASA-CR-159641 19790025034 NASA CR-159641 R79AEG504 I,:. Analytical Evaluation of the Impact of " Broad SpecificationFuels on High B_,passTurbofan Engine Combustors FINAL REPORT August 1979 By J. R. Taylor General Electric Company Aircraft Engine Group Cincinnati., OH 45215 Ll_[1_.i[_!_,ll"_l'ti'lit_P7'll_i, ;:t! ,<::iY.ig LANGLEY RE.SEARCH CENTER LIBRARy,NASA HAMPTON,.VIRGINIA . " NATIONAL AERONAUTICS AND SPACEADMINISTRATION LEWISPrepRarEedSEARCHfor: CENTER -: ...... 21000 BROOKPARKROAD CLEVELAND, OHIO 44135 NAS3-20799 1. Report No. I 2. GovernmentA_:cessionNo. 3. Recipient'sCatalogNo. NASA CR-159641 I 4. Title and Subtitle 5. Report Date Analytical Evaluation of the Impact of Broad Specification Fuels August 1979 on High Bypass Turbofan Engine Combustors 6. PerformingOrganizationCode 7. Author{'s) 8. PerformingOrganizationReport No. J.R. Taylor R79AEG504 10. Work Unit No. 9. PerformingOrganizationName andAddress General Electric Company 11. Contractor Grant No. - Aircraft Engine Group Cincinnati, Ohlo 45215 NAS3-20799 13. Type of Report and PeriodCovered 12. SponsoringAgencyName and Address Contractor Report National Aeronautics and Space Administration 14. SponsoringAgency Code Washington, D.C. 20546 15. SupplementaryNotes Project Manager: A.L. Smith, NASA-Lewis Research Center, Cleveland, Ohlo 44135 16.Abstra_ An in-depth analysis of six conceptual combustor designs for the CF6-50 hlgh bypass turbofan engine and slx conceptual combustor designs for the NASA/GE E3 high bypass turbofan engine was performed to provide an assessment of the major problems anticipated in using broad specification fuels in these aircraft engine combustion systems. The conceptual eombustor designs are representative of both state-of-the-art and advanced state-of-the-art combustion systems. Each of the 12 concepts was analyzed to estimate combustor performance, durability, and pollutant emissions when using commercial Jet A aviation fuel and when using Experimental Referee Broad Specification (ERBS) fuel. The results of thls study indicate that lean burning, low emissions, double annular combustor concepts can accommodate a wide range of fuel properties without a serious deterioration of performance or durability. However, rich burning, single annular con- cepts would be less tolerant to a relaxation of fuel properties. Also, as the fuel specifications are relaxed, autolgnitlon delay tlme becomes much smaller which presents a serious design and development problem for premlxing-prevaporlzing combustion system concepts. 17. Key Words(Suggestedby Author(s)) 18. DistributionStatement Combustion Broad Specification Fuels Fuels Double-Annular Combustors Unclassified - Unlimited Gas Turbine Combustors Premlxlng Combustors Gas Turbine Emissions Advanced Combustor Concepts Gas Turbine Fuels 19. Security Classif.(of this report) 20. SecurityClassif.(of this page) 21. No. of Pages 22. Price" Unclassified Unclassified 79 * ForsalebytheNationalTechnicalInformationServiceS,pringfieldVirginia, 22151 NASA-C-168(Rev. 6-71) TABLE OF CONTENTS Sect ton Pa_g_e 1.0 SUMMARY i 2.0 INTRODUCTION 4 3.0 DISCUSSION OF I)ESI(:N STUI)Y CONSTI)EIiATIONS ANI) I_I_SUI,'rs 6 3.1 Fuel Properties and Specifications 6 3.2 Selected Turbofan Engines and Engine Cycle Operating 9 Conditions 3.3 Conceptual Combustor Designs 13 3.3.1 Combustor Design Requirements 13 3.3.2 Conceptual Designs 15 3.3.3 Design Parameters 32 3.3.4 Flow Distribution 37 3.3.5 Fuel Injection Systems 45 3.4 Predicted Performance 52 3.4.1 Pressure Losses 52 3.4.2 Estimated Combustion Performance Characteristics 54 3.4.3 Estimated Pollutant Emissions Characteristics 57 3.5 Comparative Evaluation of the Conceptual Designs 61 3.5.1 Evaluation Criteria 61 3.5.2 Comparative Ratings 62 3.6 Discussion of Possible Relaxation of Fuel Properties 64 3.7 Evaluation of Conceptual Design Complexities and Engine 67 Integration Problems 3.8 Significant Problem Areas and Recommendations for 68 F.t.re _t.(lv 4.0 REFERENCES 69 iil LIST OF ILLUSTRATIONS FiKure Page i. Correlation of Aromatics and Hydrogen Content of 50 Fuels. 8 2. Flash Point Versus Initial Boiling Point - 60 Samples of a i0 Jet A Commercial Aviation Kerosine - 1977 Domestic Production. 3. Production CF6-50 Engine Combustor. 16 4. Short Single Annular CF6-50 Combustor Conceptual Design. 17 5. Annular Slot CF6-50 Combustor Conceptual Design. 18 6. Double Annular CF6-50 Combustor Design. 20 7. Double Annular Combustor. 21 8. Radial/Axial Staged CF6-50 Combustor Design. 22 9. Radial/Axial Staged Combustor. 23 i0. Premixed-Prevaporized CF6-50 Combustor Conceptual Design. 25 ii. Single Annular E3 Combustor Conceptual Design 27 12. Ultra-Short Single Annular E3 Combustor Design. 28 13. Annular Slot E 3 Combustor Conceptual Design. 29 14. Double Annular E3 Combustor Design. 30 15. Radial/Axial Staged E3 Combustor Conceptual Design. 31 16. Premixed-Prevaporized E 3 Combustor Conceptual Design. 33 J7. [mplngement-CooJed Panel with Double Wall Construction and 34 Dilution llole. 18. Typical Combustor Dome Swirlers. 35 19. Typical Dual Orifice Fuel Nozzle Flow Characteristics. 46 20. Typical Fuel Injector Flow Characteristics. 47 21. Preliminary CF6-50 Fuel Flow Schedule with a Two-stage 50 Combustion System. 22. Ignition Delay Times for JP-4, No. 2 Fuel Oil, and No. 6 51 Fuel Oil in Air. IV LIST OF TABLES Table Page i. Preliminary Estimates of Alternative Aviation Turbine Fuel 7_ Specifications. 2. CF6-50C Combustor Operating Conditions. Ii 3. E3 Combustor Operating Conditions. 12 4A. Combustor Performance Requirements. 14 - 4B. CombustorEmissions Requirements. 14 5. Combustor Design Parameters for tile CF6-50 Engine Cycle. 36 6. CF6-50 Single Annular Conceptual Combustor Designs - Air- 38 flow Distribution and Dome Equivalence Ratios with Jet A and Broad Specification (ERBS) Fuels. 7. E3 Single Annular Conceptual Combustor Designs - Airflow 39 Distribution and l)ome Equivalence Ratios with Jet A and Broad Specification (ERBS) Fuels. 8. Double Annular Conceptual Combustor Designs: Airflow 40 Distributions and Dome Equivalence Ratios with Jet A and ERBS Fuel. 9. Radial/Axial Conceptual Combustor Designs: Airflow Distri- 41 butions and Dome Equivalence Ratios with Jet and ERBS Fuel. I0. Premixed-Prevaporized Conceptual Combustor Designs: Airflow 42 Distributions and Dome Equivalence Ratios with Jet A and ERI_S Fuel. Ii. Conceptual Combustor Designs - Fuel Injector Type and Oper- 48 ating Characteristics. 12. Conceptual Coml)._t()r I)(,_klg._; - I'r_,(llct:_,d Pressur(, i.osses. 53 13. Predicted Combustor Performance Characteristics. 55 14. CF6-50 Concepts - Estimated Emissions. 59 15. E3 Concepts - Estimated Emissions. 60 16. Evaluation of Conceptual Combustor Designs. 63 v I. 0 SUMMARY In this effort, an assessment was made of the majo r problems anticipated in using aircraft turbine engine fuels with relaxed fuel specifications in both state-of-the-art and advanced state-of-the-art aircraft turbine engine combustion systems. This study was limited to the design of engine combustion systems and did not encompass assessments of any problems related to airframe fuel systems. Two engine designs were selected for this study - a production turbofan engine, the General Electric CF6-50; and an advanced energy efficient turbofan engine, the NASA/GE E3. For each of these two turbofan engines, combustion system requirements were determined and six different combustion systems were conceptually de- signed. These combustors were designed to use Jet A fuel and a broad specifi- cation fuel (ERBS). Compared to Jet A fuel, ERBS fuel has a higher aromatic content and a higher final boiling point. Each of the 12 concepts was analyzed to estimate combustor perfor- mance, durability, and emissions with Jet A fuel and with ERBS fuel. A comparative evaluation of the conceptual designs was made in terms of the following criteria: i. Fuel flexibility (flexibility to handle current and broad specification fuels). 2. Combustion performance. 3. Exhaust pollutant emissions. 4 Design complexity. 5 Reliability. 6 Maintainability. 7 Durability and operating life. 8 Effect on overall engine weight. 9 Effect on overall engine fuel consumption. Estimates were made as to how far Jet A fuel specifications can be relaxed without degrading CF6-50 or advanced turbofan engine performance or without encountering fuel stability problems. Properties of the ERBS fuel were care- fully examined in order to determine the possibility that any of these prop- erties might limit the use of this fuel for turbofan engine applications. Problems associated with integrating each combustor with the two engine designs were evaluated, and each combustor concept was evaluated in terms of the design complexity required to achieve good performance with the two fuels. Finally, the most significant anticipated problem areas were iden- tified and recommendations made for areas of future study. _1+. r_'s.ltr of thin _t:udy r,,_+,st that, in _en_ral, turbofan engines with lean bur, ing, low emissions double annular combustion systems can accommodate a rather wide range of fuel properties without a serious deterioration of performance or a serious increase in exhaust emissions. A lean burning double annular combustor, designed for the E 3 cycle condition, is predicted to meet all engine performance and emission requirements with a significant relaxa- tion of fuel specifications. Rich burning, single annular combustor design concepts would be some- what less tolerant to a relaxation of fuel specifications.
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