Accession Number : AD0515005
Title : Exploratory Development of Reduced Length Turbo-Propulsion Combustion Systems. Part II. Component Design and Development.
Descriptive Note : Technical rept. 1 Jan 68-30 Sep 70,
Corporate Author : GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
Personal Author(s) : Reider,Samuel B. ; Stettler,Richard J.
Report Date : FEB 1971
Pagination or Media Count : 176
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 is being developed. 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 promising. 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. Test data from the diffusers, premix modules, and liner cooling configurations resulted in a 60-degree sector design which attained program objectives. The technology developed on the 60-degree sector testing was used to design a scalable 120-degree sector and a full annular combustor. Combustors incorporating integrated diffuser-combustor and fuel and air premix techniques have definite application in future aircraft turbo-propulsion engines. (Author)
Descriptors : (*GAS TURBINES, COMBUSTION CHAMBERS), (*FUEL INJECTION, GAS TURBINES), DIFFUSERS, TURBOJET ENGINES, COMBUSTION CHAMBER LINERS, GAS FLOW, COMPUTER PROGRAMS, THERMAL INSULATION, QUENCHING, MISSION PROFILES (U) SWEAT COOLING, TURBINE STATORS, FUEL SPRAYS, FILMS, HYDROCARBONS, JET ENGINE FUELS, VERTICAL TAKEOFF AIRCRAFT, SUBSONIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS, EXHAUST GASES, VORTICES, BAFFLES, CONVECTION(HEAT TRANSFER), TURBOJET INLETS
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE