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Gas Turbine Characteristics for a Large Civil Tilt-Rotor (LCTR)

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Gas Turbine Characteristics for a Large Civil Tilt-Rotor (LCTR) NASA/TM-2010-216089 Gas Turbine Characteristics for a Large Civil Tilt-Rotor (LCTR) Christopher A. Snyder Glenn Research Center, Cleveland, Ohio Douglas R. Thin-man U.S. Army Research Laboratory, Glenn Research Center; Cleveland, Ohio February 2010 NASA STI Program ... in Profile Since its founding, NASA has been dedicated to the CONFERENCE PUBLICATION. Collected advancement of aeronautics and space science. The papers from scientific and technical NASA Scientific and Technical Information (STI) conferences, symposia, seminars, or other program plays a key part in helping NASA maintain meetings sponsored or cosponsored by NASA. this important role. • SPECIAL PUBLICATION. Scientific, The NASA STI Program operates under the auspices technical, or historical information from of the Agency Chief Information Officer. It collects, NASA programs, projects, and missions, often organizes, provides for archiving, and disseminates concerned with subjects having substantial NASA's STI. The NASA STI program provides access public interest. to the NASA Aeronautics and Space Database and its public interface, the NASA Technical Reports • TECHNICAL TRANSLATION. English- Server, thus providing one of the largest collections language translations of foreign scientific and of aeronautical and space science STI in the world. technical material pertinent to NASA's mission. Results are published in both non-NASA channels and by NASA in the NASA STI Report Series, which Specialized services also include creating custom includes the following report types: thesauri, building customized databases, organizing and publishing research results. • TECHNICAL PUBLICATION. Reports of completed research or a major significant phase For more information about the NASA STI of research that present the results of NASA program, see the following: programs and include extensive data or theoretical analysis. Includes compilations of significant • Access the NASA STI program home page at scientific and technical data and information http://w,",w.sti.nasa.gov deemed to be of continuing reference value. NASA counterpart of peer-reviewed formal • E-mail your question via the Internet to help@ professional papers but has less stringent sti. nasa.gov limitations on manuscript length and extent of graphic presentations. • Fax your question to the NASA STI Help Desk at443-757-5803 • TECHNICAL MEMORANDUM. Scientific and technical findings that are preliminary or • Telephone the NASA STI Help Desk at of specialized interest, e.g., quick release 443-757-5802 reports, working papers, and bibliographies that contain minimal annotation. Does not contain • Write to: extensive analysis. NASA Center for AeroSpace Information (CASI) 7115 Standard Drive • CONTRACTOR REPORT. Scientific and Hanover, MD 21076-1320 technical findings by NASA-sponsored contractors and grantees. NASA/TM-2010-216089 Gas Turbine Characteristics for a Large Civil Tilt-Rotor (LCTR) Christopher A. Snyder Glenn Research Center, Cleveland, Ohio Douglas R. Thin-man U.S. Army Research Laboratory, Glenn Research Center; Cleveland, Ohio Prepared for the 65th Annual Forum and Technology Display (AHS Forum 65) sponsored by the American Helicopter Society Grapevine, Texas, May 27-29, 2009 National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135 February 2010 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 and trademarks are used in this report for identification only. Their usage does not constitute an official endorsement, either expressed or implied, by the National Aeronautics and Space Administration. Level of Review: This material has been technically reviewed by technical management Available from NASA Center for Aerospace Information National Technical Information Service 7115 Standard Drive 5285 Port Royal Road Hanover, MD 21076-1320 Springfield, VA 22161 Available electronically at http://gltrs.grc.nasa.gov Gas Turbine Characteristics for a Large Civil Tilt-Rotor (LCTR) Christopher A. Snyder National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135 Douglas R. Thunman U.S. Army Research Laboratory Glenn Research Center Cleveland, Ohio 44135 Abstract sec second T3 compression system exit temperature, °F In support of the Fundamental Aeronautics Program, Subsonic Rotary Wing Project, an engine system study has T4 combustor exit temperature, °F been undertaken to help define and understand some of the Vtip rotor tip velocity, feet per second major gas turbine engine parameters required to meet W actual mass flow, lbm/sec performance and weight requirements as defined by earlier We corrected mass flow, W * FO/8 , lbm/sec vehicle system studies. These previous vehicle studies will be reviewed to help define gas turbine performance goals. Wturb power turbine actual mass flow, lbm/sec Assumptions and analysis methods used will be described. ratio of actual to standard pressure Performance and wei ght estimates for a few conceptual gas ratio of actual to standard temperature turbine engines meeting these requirements will be given and discussed. Estimated performance for these conceptual engines over a wide speed variation (down to 50 percent Introduction power turbine rpm at high torque) will be presented. Finally, areas needing further effort will be suggested and discussed. The NASA Heavy Lift Rotorcraft System Investigation (Ref. 1) identified a large tilt rotor as the best concept to meet the various airspace and other requirements for the future, Nomenclature short-haul regional market. This evolved into a conceptual vehicle designated as LCTR2 (Large Civil Tilt Rotor— C.G. center of gravity, inches iteration 2) (Ref. 2) as seen in Figure 1 eff efficiency This vehicle iteration was designed to carry 90 passengers fps feet per second at 300 knots with at least a 1,000 n nu range; powered by four turboshaft engines designed for 7,500 hp each. Other design ft feet features included a rotor tip speed of 650 ft/sec in hover and hp horsepower 350 ft/sec during cruise, enabled by a two-speed gearbox. This HPC high-pressure compressor range of rotor tip speeds was needed to achieve the high level of performance and efficiency at two very different flight HPT high-pressure turbine conditions. The rotor tip speed variation could theoretically be lbm pounds mass obtained using a variable diameter rotor or multiple-speed LCTR Large Civil Tilt Rotor gearboxes (orVa combination of these or other approaches); LP low pressure this work is focusing on achieving all speed variation from the engine. Although the exact requirements and characteristics LPC low-pressure compressor for such a vehicle class are still being researched, performing LPT low-pressure turbine analyses on a representative vehicle will help understand the Max maximum sensitivities for such a design, help guide research efforts to reduce risks, and develop a suite of technologies from which N actual speed, rpm this new vehicle class and capability can evolve and be Nc corrected speed, NIJO , rpm developed. The final vehicle design could use one or a PR pressure ratio combination of these variable rotor tip speed concepts, determined from the vehicle's specific design and nussion PSFC power specific fuel consumption, lbm/hr/lip requirements and the state of these various required PT power turbine technologies. NASA/TM-2010-216089 important performance parameters that will help define possible engine configurations. As part of the parametric analysis, compressor pressure ratio (PR) was varied from 5 to 60, assuming a constant polytropic efficiency of 88 percent. Although turbomachinery efficiency would vary dependin g on engine size and configuration, that effect was deferred to later analyses. Combustor exit temperature was varied from 2000 to 3200 °F (in 400° increments). To get turbine cooling bleed estimates for the core turbines, the method of Gauntner (Ref. 3) was used, assuming metal temperatures of 2200 °F for the stator, 2100 °F for the rotor. These turbine metal Figure 1.—Conceptual view of LCTR2. temperatures are higher than present, small gas turbines to include the effects of incorporation of improved turbine This report details gas turbine en gine technology material temperature capabilities and cooling techniques in assumptions and analyses performed to estimate the engine these smaller turbine sizes. The power turbine was assumed to parameters needed to obtain sufficient performance to meet be urncooled. These should be reasonable temperatures and operational goals for the proposed vehicle concept. This efficiencies for engines in the LCTR2-size class with entry-in- vehicle would use the turboshaft version of a gas turbine service in roughly the 2020 timeframe. engine. The core gas turbine engine develops high energy The object-oriented analysis framework, the Numerical (high temperature and pressure) gas to power a separate power Propulsion System Simulator (NPSS) (Ref. 4), was used to turbine and shaft that supplies horsepower and torque to the perform the gas turbine analyses. NPSS contains standard 0/1- main drive system. Initial cycle parametrics were performed to D elements for the gas turbine components. These are suggest gas turbine engine characteristics that would meet configured into a representative steady-state, thermodynamic LCTR2 performance requirements. Based on these overall model. An example block
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