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A Comparative Propulsion System Analysis for the High-Speed Civil Transport

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A Comparative Propulsion System Analysis for the High-Speed Civil Transport NASA/TM—2005-213414 A Comparative Propulsion System Analysis for the High-Speed Civil Transport Jeffrey J. Berton, William J. Haller, Paul F. Senick, Scott M. Jones, and Jonathan A. Seidel Glenn Research Center, Cleveland, Ohio February 2005 The NASA STI Program Office . in Profile Since its founding, NASA has been dedicated to • CONFERENCE PUBLICATION. Collected the advancement of aeronautics and space papers from scientific and technical science. The NASA Scientific and Technical conferences, symposia, seminars, or other Information (STI) Program Office plays a key part meetings sponsored or cosponsored by in helping NASA maintain this important role. NASA. The NASA STI Program Office is operated by • SPECIAL PUBLICATION. Scientific, Langley Research Center, the Lead Center for technical, or historical information from NASA’s scientific and technical information. The NASA programs, projects, and missions, NASA STI Program Office provides access to the often concerned with subjects having NASA STI Database, the largest collection of substantial public interest. aeronautical and space science STI in the world. The Program Office is also NASA’s institutional • TECHNICAL TRANSLATION. English- mechanism for disseminating the results of its language translations of foreign scientific research and development activities. These results and technical material pertinent to NASA’s are published by NASA in the NASA STI Report mission. Series, which includes the following report types: Specialized services that complement the STI • TECHNICAL PUBLICATION. Reports of Program Office’s diverse offerings include completed research or a major significant creating custom thesauri, building customized phase of research that present the results of databases, organizing and publishing research NASA programs and include extensive data results . even providing videos. or theoretical analysis. Includes compilations of significant scientific and technical data and For more information about the NASA STI information deemed to be of continuing Program Office, see the following: reference value. NASA’s counterpart of peer- reviewed formal professional papers but • Access the NASA STI Program Home Page has less stringent limitations on manuscript at http://www.sti.nasa.gov length and extent of graphic presentations. • E-mail your question via the Internet to • TECHNICAL MEMORANDUM. Scientific [email protected] and technical findings that are preliminary or of specialized interest, e.g., quick release • Fax your question to the NASA Access reports, working papers, and bibliographies Help Desk at 301–621–0134 that contain minimal annotation. Does not contain extensive analysis. • Telephone the NASA Access Help Desk at 301–621–0390 • CONTRACTOR REPORT. Scientific and technical findings by NASA-sponsored • Write to: contractors and grantees. NASA Access Help Desk NASA Center for AeroSpace Information 7121 Standard Drive Hanover, MD 21076 NASA/TM—2005-213414 A Comparative Propulsion System Analysis for the High-Speed Civil Transport Jeffrey J. Berton, William J. Haller, Paul F. Senick, Scott M. Jones, and Jonathan A. Seidel Glenn Research Center, Cleveland, Ohio National Aeronautics and Space Administration Glenn Research Center February 2005 Document History This research was originally published internally as HSR007 in October 1995. This report is a formal draft or working paper, intended to solicit comments and ideas from a technical peer group. This report contains preliminary findings, subject to revision as analysis proceeds. Trade names or manufacturers’ names are used in this report for identification only. This usage does not constitute an official endorsement, either expressed or implied, by the National Aeronautics and Space Administration. Note that at the time of writing, the NASA Lewis Research Center was undergoing a name change to the NASA John H. Glenn Research Center at Lewis Field. Both names may appear in this report. Available from NASA Center for Aerospace Information National Technical Information Service 7121 Standard Drive 5285 Port Royal Road Hanover, MD 21076 Springfield, VA 22100 Available electronically at http://gltrs.grc.nasa.gov A Comparative Propulsion System Analysis for the High-Speed Civil Transport Jeffrey J. Berton, William J. Haller, Paul F. Senick, Scott M. Jones, and Jonathan A. Seidel National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135 Abstract Six of the candidate propulsion systems for the High-Speed Civil Transport are the turbojet, turbine bypass engine, mixed flow turbofan, variable cycle engine, Flade engine, and the inverting flow valve engine. A comparison of these propulsion systems by NASA’s Lewis Research Center, paralleling studies within the aircraft industry, is presented. This report describes the Lewis Aeropropulsion Analysis Office’s contribution to the High-Speed Research Program’s 1993 and 1994 propulsion system selections. A parametric investigation of each propulsion cycle’s primary design variables is analytically performed. Performance, weight, and geometric data are calculated for each engine. The resulting engines are then evaluated on two airframer-derived supersonic commercial aircraft for a 5000 nautical mile, Mach 2.4 cruise design mission. The effects of takeoff noise, cruise emissions, and cycle design rules are examined. (This report was written in 1995 for NASA’s High Speed Research Program.) Introduction savings over long-range subsonic aircraft. Boeing’s market research also suggests that sufficient profitability There is a renewed, worldwide interest in developing is possible with little or no fare premiums. an economically viable and environmentally acceptable The problems that plagued the U.S. Supersonic commercial supersonic transport to begin operations early Transport Program are still present today. In addition to in the twenty-first century. Several attempts have been difficult economic challenges, there are problems posed made over the last quarter century to develop a U.S. by environmental concerns. Namely, the stratospheric supersonic commercial transport. The Supersonic propulsion emissions must be minimized such that the Transport Program, which ran from the mid-1960s to HSCT fleet will have no significant effect on the ozone 1971, focused on establishing an airframe and propulsion layer, and the propulsion noise must be reduced to meet system that could compete in the international supersonic current Federal Aviation Regulation (FAR) Part 36 Stage transport marketplace. The program was canceled when 3 noise rules (ref. 2). Indeed, noise regulations of the near political support waned in the face of increasing technical, future may become even more stringent in the airport environmental, and economic concerns. From 1972 to vicinity, and additional rules may regulate noise levels 1981, NASA conducted the Supersonic Cruise Research many miles from the airport as the aircraft climbs. These Program. This cooperative government/industry effort economic and environmental requirements pose a signifi- investigated areas where advanced technology would cant propulsion engineering challenge. produce significant enhancements in supersonic cruise This study builds upon earlier research performed by performance. New engine concepts and better jet noise the NASA Lewis mission analysis team (refs. 3 and 4). reduction techniques were developed (ref. 1). In 1989, the The candidate propulsion systems evaluated here for the NASA-sponsored High-Speed Research (HSR) Program HSCT are the turbojet, turbine bypass engine, mixed flow was initiated with the objective of providing solutions to turbofan, variable cycle engine, Flade engine, and the the environmental issues associated with a proposed inverting flow valve family of engines (see figs. 1 to 7). future High-Speed Civil Transport (HSCT). NASA-spon- The design variables of each of these cycles are paramet- sored studies involving both airframe and engine rically varied and the performance and weight data are manufacturers have determined that an economically analytically computed. The resulting engines are then viable, environmentally acceptable Mach 2.4 HSCT could evaluated on two airframer-derived HSCTs for 5000 enter the market as early as 2005. The HSCT’s potential nautical mile, Mach 2.4 cruise missions. The effects of economic impact is enormous. The findings of Boeing’s takeoff noise, cruise emissions, and the addition of 1993 Focus Group indicate that due to increased pro- alternate missions are also examined. ductivity, time savings, and passenger preference, the The intent of this study was to provide guidance for HSCT could capture up to seventy percent of the long- the NASA/industry propulsion system downselect team. haul markets in cases where it can offer significant time This team, consisting of representatives from NASA, NASA/TM—2005-213414 1 General Electric, Pratt & Whitney, Boeing, and McDon- Installation Effects nell Douglas, selected two propulsion system concepts, a prime and a backup, in October, 1993. Additional updated A mixed-compression translating centerbody inlet is propulsion system evaluations are also presented for the used for each of the engine cycles in this study. The downselect confirmation of April, 1994. Contained in this performance and aerodynamic characteristics of this inlet paper are the NASA Lewis mission analysis team’s are derived from reference 7 and some of its more recommendations for the selection of these two propulsion dominant performance characteristics
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