Accession Number : AD0378352

Title :   COMMERCIAL SUPERSONIC TRANSPORT PROGRAM. PHASE II-A. COMPREHENSIVE REPORT. VOLUME VIII-A. AIRCRAFT PROPULSION SYSTEM.

Corporate Author : BOEING CO RENTON WASH AIRPLANE DIV

Report Date : 01 NOV 1964

Pagination or Media Count : 242

Abstract : The studies conducted during Phase II-A have resulted in design improvements for all major propulsion systems. The pods are relocated. The most significant refinement are: The improved General Electric GE4/J5G afterburning turbojet engine has been selected on the basis of economic, performance, and growth advantages. The inlet design has features which improve cruise performance, allow manual control, and reduce engine noise. The propulsion pods are located farther aft on the wing to improve engine-airplane performance. Exhaust flow is directed away from the empennage by afterburner redesign. The thrust reversing system discharges a major portion of the exhaust flow over the wing for increased reversal capability and reduced exhaust gas ingestion. A low-idle engine control feature is provided for economical descent flight operation. The airplane fuel system incorporates recirculation which allows use of lowest quality Jet A or A-1 kerosene. The constant speed drive/generator and the hydraulic pump on an inoperative engine accessory gear box can be starter driven by pressurized air from another engine during flight or from an air cart during ground operations. The four propulsion pods, as well as the major pod components (inlet, engine, and exhaust system), are interchangeable, and can be installed at any of the four positions.

Descriptors :   (*JET ENGINES, JET TRANSPORT PLANES), SUPERSONIC AIRCRAFT, WEIGHT, PERFORMANCE(ENGINEERING), ENGINE NOISE, REDUCTION, THRUST, ACCELERATION, CLIMBING, SCHEDULING, RECOVERY, CONTROL SYSTEMS, SHOCK WAVES, STARTING (U) *TURBOJET ENGINES, *TURBOJET INLETS, TURBOJET EXHAUST NOZZLES, VARIABLE AREA NOZZLES, VORTEX GENERATORS, ENGINE MOUNTS, HEAT SHIELDS, THRUST REVERSAL

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE