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QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (QCSEE) Preliminary Under the Wing Flight Propulsion System Analysis Report

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QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (QCSEE) Preliminary Under the Wing Flight Propulsion System Analysis Report NASA CR-134868 QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE (QCSEE) Preliminary Under the Wing Flight Propulsion System Analysis Report February 1976 by Advanced Engineering & Technology Programs Department General Electric Company (IASA-CR-134868) QUIET CLEAN SHORT-HAUL NS0-15088 EXPERIMENTAL ENGINE (QCSEE) PRELIMINARY 1UNDER THE WING FLIGHT PROPULSION SYSTEM lANALYSIS REPORT '(General Electric Co.) "nclas '1261 p HC A12/MF A01 CSCL 21E G3/07 33465 Prepared For National Aeronautics and Space Admiistrati Contract NAS3-18021 FOR EARLY DOMESTIC DISSEMNATION-f9, < %,tj64 Because of its significant early commercial potential, th'is information, which has been developed under a U. S. Government program, is being disseminated within the United States in advance of general publication. This information may be dupli­ cated and used by the recipient with the express limitation that it not be published. Release of this information to other domestic parties by the recipient shall be made subject to these limitations. Foreign release may be made only with prior NASA approval and appropriate export licenses. This legend shall be marked on any reproduction of this information in whole or in Datepart. forfa general rel ease,)- 0A16/Zyj/ 1.Rep No. 2. Government Accession No. 3. Recipient's Catalog No: NASA CR-134868 4 Titleand Subtitle 5.Report Date QUIET CLEAN SHORT-HAUL EXPERIMENTAL ENGINE PRELIMINARY February 1976 UNDER-THE-WING FLIGHT PROPULSION SYSTEM ANALYSIS REPORT 6. Performing Organization Code 7. Author(s) D. F. Howard, et al 8.Performing Organization Report No. Advanced Engineering and Technology Programs Dept R75AEG349 Group Engineering Division 10. Work Unit No 9 Performing Organization Name and Address General Electric Company 1 Jimson Road 11. Contractor Grant No. Cincinnati, Ohio 45215 NAS3-18021 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Contractor Report National Aeronautics and Space Administration Washington, D.C. 20546 14 Sponsoring Agency Code 15. Supplementary Notes Topical Report. Project Manager, C. C. Ciepluch, QCSEE Project Office, Technical, Adviser, R. IV. Koenig, NASA Lewis Research Center, Cleveland, Ohio 44135 16. Abstract The Quiet Clean Short-Haul Experimental Engine (QCSEE) Program includes the preliminary design and installation of high bypass, geared turbofan engine with a composite nacelle forming the propulsion system for a short-haul passenger air­ craft. These flight systems contain the technology required for externally blown flap type aircraft with under-the-wing (UTW) propulsion system installations for introduction into passenger service in the mid 1980's. Based on the flight designs the program provides for the design, fabrication and testing of this UTW experimental engine containing the required technology items for low noise, fuel economy, with composite structure for reduced weight and digital engine control. The report deals with the QCSEE UTW Flight Propulsion System installation and nacelle component and systems design features on a short-haul, powered lift air­ craft. A substantial portion of this report was produced at Douglas Aircraft Company and covers their efforts in support of the QCSEE program. 17. Key Words (Suggested by Author(s)) Aircraft Propulsion and Power Integrated Engine/Nacelle Struct.' Composite Materials I Aerodynamics Acoustics Installation 19. Security Classif (ofthisreport)20. Seunty ClasSTrtorsns- ge. .4-- Unclassified Unclassified 247 NASA-C-1SS (R-v &-71) FOREWORD, The Quiet Clean Short-Haul Experimental Engine (QCSEE) Program is' currently being conducted by the General Electric Company, Aircraft Engine Group in accordance with NASA Contract NAS3-18021, under the-direction of Mr. C.C. Ciepluch, NASA Project Manager. The Program includes the design, manufacture aid test of an under-the-wing (UTW) and an over-the-wing (OTW) experimental engine. Both engihes are intended to develop the technology needed for externally blown flaps, short takeoff and landing, commercial, short-haul aircraft. To ensure the selection of appropriate flight system parameters and characteristics, and to provide design guidance, subcontracted study support was obtained from aircraft manufacturers and operators. General Electric selected The Boeing-Company to provide support for the OTW system, Douglas Aircraft Company to provide support for the UTW system, and American Airlines to evaluate both installations and provide an appropriate operational scenario. Specific subcontracted effort con­ sisted of guidance in selection of the engine cycles, installation'design, propulsive-lift interactions, control interfaces, acoustics, performance, and economic analyses. Although earlier studies had indicated a need to operate from a 609.6 m (2000 ft) runway, it was concluded by all contributors that the Flight studies of a commercial short-haul transport should be conducted based on a 914.4 m (3000 ft) runway, typical of existing close-in airports.' The experimental system retained the 609.6 m (2000 ft) runway requirement to assure technology margin for the aircraft ready to enter airline service in the mid 1980's. In either case, the propulsion system would be-designed to meet a noise requirement of 95 EPNdB at 152.4 m (500 ft) sideline during approach and takeoff . Since final system requirements will not be definitized for some time, the experimental engine objectives [including 609.6 m (2000 ft) runway], being the more stringent, were not changed. Thus the technology mar­ gin that is developed in the QCSEE Program will be adequate for any foreseeable system requirement. This report covers the subcontracted analyses of the UTW aircraft system. The propulsion systems used in the study were projected "flight" systems based on the technology being developed in the experimental program. Propulsion system weight, performance, and installation features have been projected- in a rational basis from the experimental propulsion system design. PRECEDING PAME RINj7U{ V)T F Design studies were performed to develop concepts for integrating the flight design version of the QCSEE propulsion system with the UTI, externally blown flap (EFP), powered lift aircraft addressed to the requirements for an airliner designed for short-haul service. The airplane concept was based on technology consistent with providing a reliable vehicle that is both durable and economical to operate and that could be ready to enter airline service in the mid 1980's. The preliminary design studies produced definitions of the airplane configura­ tion, characteristics, performance, and operating economics, in addition to developing the concept of the engine pod/pylon/airframe accessories arrangement., Attention was devoted to identifying the geometry of a suitable engine air inlet including the needed ice protection features. The airplane accessories requirements were identified and the concept of an accessories pack installed remote from the top-mounted engine accessories 'gearboxwas developed. The space envelope, weight, and significant features and characteristics of the various components were identified as were the estimates of the shaft power demands this system placed on the engine power takeoff (PTO) drive. Studies were made to develop the concepts for the cabin environment control and lifting surface ice protection systems needed for the short-haul airplane. The air bleed demands imposed on the engines were estimated and concepts for matching the bleed capacity to the demands were developed. In addition, studies were made to identify the significance of two variants of the QCSEE; one with bottom-mounted accessories and the other with reduced acoustic treatment. These studies indicated the impact of the concepts on airplane characteristics, performance, and economics. The conclusions that could be drawn from the results of the work have been documented. Significant contributions to this report were made by the Douglas Aircraft Engineering Department in the areas of aerodynamics, advanced design, avionics, environmental control, power plant, structures, and weights. American Airlines provided the short-haul aircraft requirements and conducted various installation reviews of the propulsion system. This report deals exclusively with the QCSEE UTW Flight Propulsion System design and analysis based on the aircraft use of a 914.4 m (3000 ft) runaway. With the longer runway the aircraft will attain a higher take­ off velocity permitting reduced aircraft flap angles and reduced engine thrust. On approach, the longer runway permits higher aircraft approach velocity also reducing flap angle and thrust requirements. This results in a reduction in the amount for noise suppression panel treatment required to meet the acoustic program objective. "iV TABLE OF CONTENTS Section Page 1.0 SUMMARY 1 2.0 INTRODUCTION 3 3."0 AIRCRAFT REQUIREMENTS AND CHARACTERISTICS 5 3.1 Aircraft Requirements, Ground Rules, and Sizing Methods 5 3.1.1 Takeoff 5 3.1.2 Landing 7 3.1.3 Sizing Mission 9 3.2 Aerodynamic Characteristics 11 3.3 Aircraft Description 11 3.4 Wing Flap Environment 23 3.5 Aircraft Weights 28 4.0 PROPULSION SYSTEM/AIRPLANE INTEGRATION 31 4.1 Requirements 31 4.1.1 Takeoff Thrust 31 4.1.2 Thrust-to-Weight Ratio 31 4.1.3 Idle Thrust 31 4.1.4 Reverse Thrust 32 4.1.5 Cruise Envelope 32 4.1.6 Inlet Distortion 32 4.1.7 Thrust Response 32 4.1.8 Emissions 32 4.1.9 Durability 32 4.1.10 Mounting 33 4.1.11 Lube Oil System 33 4.1.12 Bleed Air Requirements 33 4.1.13 Airplane Accessories Drive 35 4.1.14 Nacelle Ventilation and Cooling 35 4.1.15 Fire Protection 37 4.1.16 Drains 37 4.1.17 Safety 38 4.1.,18 Inlet Loads 38 4.1.19 Maintainability 39 4.1.20 Engine Control System 41 4.2 Installation Concept 41 4.2.1 Inlet Duct 41 4.2.2 Fan Module 41 4.2.3 Gas Generator 44 4.2.4 Power Turbine 44 4.2.5 Fan Exhaust 45 4.2.6 Engine Accessories 45 v TABLE OF'CONTENTS (Continued) Seiction , Page 4.2.7 Engine Support Concept 46­ 4.2.8 Pylon Beam Auxiliary Functions 49 4.2.9, Fire Protection 49 4.2.10 Fire Detectors 49 4.2.11 Fuel Isolation 50.
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