Accession Number : AD0515006
Title : Exploratory Development of Reduced Length Turbo-Propulsion Combustion Systems. Part III. Full Annular Combustion System Demonstration.
Descriptive Note : Technical rept. 1 Jul 67-28 Feb 71,
Corporate Author : GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
Personal Author(s) : Reider,Samuel B. ; Stettler,Richard J.
Report Date : APR 1971
Pagination or Media Count : 105
Abstract : Advanced design turbo-propulsion engines for future aircraft require a compact, high-performance combustion system for high thrust-to-weight ratios and an increased level of reliability. Two concepts are being incorporated to attain this goal. First, an integrated diffuser-combustor designed to achieve minimum length and maximum efficiency with smoke-free operation was demonstrated. Second, improved fuel injection using a high-density premix fuel injection technique to obtain acceptable combustor exit temperature patterns in a high-temperature-rise combustor is feasible. Four diffuser designs were evaluated to establish length reduction techniques. Further, four premix module designs were evaluated for combustor performance values. Additionally, to complete the system design to meet the stated objectives, three liner cooling configurations were tested for system compatibility. A new cooling concept using a convection/film cooling technique was demonstrated which allowed a substantial reduction in cooling air requirements. Test data from the diffusers, premix modules, and liner cooling configurations resulted in a 60-degree sector design which attained program objectives. Development of the fuel injection system is necessary to meet high-altitude ignition and operation requirements. Premix system spray qualities indicate that a pilot nozzle is essential to provide the broad range of operation necessary for the combustion system. Combustors incorporating integrated diffuser-combustor and fuel and air premix techniques have definite feasibility for application to future aircraft turbo-propulsion engines.
Descriptors : (*GAS TURBINES, COMBUSTION CHAMBERS), (*FUEL INJECTION, GAS TURBINES), DIFFUSERS, CONVECTION(HEAT TRANSFER), FILMS, WEIGHT, THREE DIMENSIONAL FLOW, FUEL INJECTORS, COMBUSTION CHAMBER LINERS, EXHAUST GASES, ENTHALPY, QUENCHING, FILM COOLING (U) VERTICAL TAKEOFF AIRCRAFT, SUBSONIC CHARACTERISTICS, BAFFLES, TURBOJET INLETS, SWEAT COOLING, SUPERSONIC CHARACTERISTICS, JET ENGINE FUELS, IGNITION, TURBINE STATORS, SMOKE
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE