Accession Number : ADP006194

Title :   Optimisation of Military Compressors for Weight and Volume,

Corporate Author : ROLLS-ROYCE LTD BRISTOL (UNITED KINGDOM)

Personal Author(s) : Garwood, K. R.

Report Date : SEP 1987

Pagination or Media Count : 7

Abstract : The high pressure compression system for future fighter engines has been projected at two different proven technology standards. For a given cycle of approximately 175 lbs and 25:1 overall pressure ratio, three compressors have been evaluated, ranging from a seven stage unit with medium loading, to a five and a four stage unit with high loading. Test data of the original research parent compressors and two project specific units was commonised to the engine size and conditions. It is shown that apparent benefits between machines are negated and no significant advantage for lower work per stage could be identified at a given blading technology standard. Relative to the seven stage unit a weight advantage of 20% is gained by the adoption of a four stage unit, and is associated with an aerofoil count reduction of 15%. Introduction of higher specific strength already under development will enable a 8% weight reduction to the five stage compressor. Application of these advanced metals to a three stage compressor of higher loading has the potential of a unit weight reduction of 35% relative to the five stage machine.

Descriptors :   *HIGH PRESSURE COMPRESSORS, *GAS TURBINES, AIRCRAFT ENGINES, JET FIGHTERS, AERODYNAMIC LOADING, WEIGHT, VOLUME, AIRFOILS, BENEFITS, COMPRESSION, COMPRESSORS, COUNTING METHODS, ENGINES, EXPERIMENTAL DATA, HIGH PRESSURE, HIGH RATE, JET FIGHTERS, METALS, PRESSURE, RATIOS, REDUCTION, SIZES(DIMENSIONS), STANDARDS, WEIGHT REDUCTION.

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE