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NEW TURBOFAN ENGINES: F101 AND TF34 = NOUVEAUX TURBOREACTEURS SOUFFLANTE CANALISEE: F101 ET TF34WORSHAM JE.1972; IN: SOC. AUTOMOT. ENG. NATL. AEROSP. ENG. MANUF. MEET.; SAN DIEGO, CALIF.; 1972; NEW YORK; SOC. AUTOMOT. ENG.; DA. 1972; VOL. 841; PP. 1-5Conference Paper

F100/F401 AUGMENTED TURBOFAN ENGINES. HIGH THRUST-TO-WEIGHT PROPULSION SYSTEMS = TURBOREACTEURS A SOUFFLANTE CANALISEE F100/F401. SYSTEMES DE PROPULSION A RAPPORT POUSSEE/POIDS ELEVEMCDERMOTT JF.1972; IN: SOC. AUTOMOT. ENG. NATL. AEROSP. ENG. MANUF. MEET.; SAN DIEGO, CALIF.; 1972; NEW YORK; SOC. AUTOMOT. ENG.; DA. 1972; VOL. 842; PP. 1-5Conference Paper

NACHBRENNERSTRAHLTURBINEN. I = TURBOREACTEUR A TUYERE DE POSTCOMBUSTIONKORDIK EJT.1973; MOTORTECH. Z.; DTSCH.; DA. 1973; VOL. 34; NO 5; PP. 151-160Serial Issue

CONCORDE'S OLYMPUS 593. THE BRITISH CENTREPIECE AT THE PEKING EXHIBITION = L'OLYMPUS 593 DE CONCORDE. LA PIECE CENTRALE BRITANNIQUE A L'EXPOSITION DE PEKIN1973; AIRCR. ENGNG; G.B.; DA. 1973; VOL. 45; NO 3; PP. 6-8Serial Issue

CARACTERISTIQUES AERODYNAMIQUES FONDAMENTALES DES STABILISATEURS DE FLAMMESMATTON G; SPIES JP.1973; AERONAUT. ET ASTRONAUT.; FR.; DA. 1973; NO 40; PP. 93-107; ABS. ANGL. ALLEM.; BIBL. 6 REF.Serial Issue

THE CF6 ENGINE. DESIGNED TO IMPROVE OPERATIONAL EFFECTIVENESSHEVENER RW.1971; S.A.E. TRANS.; U.S.A.; DA. 1971; VOL. 80; NO PART 4; PP. 2598-2611Serial Issue

LE TURBOREACTEUR CFM56: UN PROGRES DANS LA REDUCTION DU BRUIT DES MOTEURSBERNARD JP; RAFFY P.1976; AERONAUT. ET ASTRONAUT.; FR.; DA. 1976; NO 56; PP. 20-34; BIBL. 12 REF.Article

DEVELOPPEMENT DU RB.199: LENTEMENT MAIS SUREMENT1975; INTERAVIA; SUISSE; DA. 1975; VOL. 30; NO 4; PP. 339-341Article

THEORETICAL EFFECTS OF POROSITY AND ANGLE OF ATTACK ON JET-STRETCHER PERFORMANCEEPPRIGHT BR JR; WESTKAEMPER JC.sdIN: AIAA 7TH AERODYN. TEST. CONF. PALO ALTO, CALIF., 1972; NEW YORK; AM. INST. AERONAUT. ASTRONAUT.; DA. S.D.; NO 993; PP. 1-4Conference Paper

2.270.450 (A1) (7411300). - 29 MARS 1974. INSTALLATION MOTRICE A TURBINE A GAZ A DEUX OU PLUSIEURS FLUXsdPatent

THE EVOLUTION AND DEVELOPMENT STATUS OF THE ALF 502 TURBOFAN ENGINE = EVOLUTION ET ETAT DU DEVELOPPEMENT DU TURBOREACTEUR A SOUFFLANTE CANALISEE ALF 502DICKEY TA; DOBAK ER.1972; IN: SOC. AUTOMOT. ENG. NATL. AEROSP. ENG. MANUF. MEET.; SAN DIEGO, CALIF.; 1972; NEW YORK; SOC. AUTOMOT. ENG.; DA. 1972; VOL. 840; PP. 1-12; BIBL. 1 REF.Conference Paper

2.277.981 (A1) (75 21408). - 8 JUILLET 1975. PERFECTIONNEMENTS AUX DISPOSITIFS D'EJECTION DES TURBOREACTEURS A DOUBLE FLUXsdPatent

THE NASA QUIET ENGINE PROGRAM = LE PROGRAMME DE MOTEUR SILENCIEUX DE LA NASAKRAMER JJ; MONTEGANI FJ.1971; IN: GAS TURBINE FLUIDS ENG. CONF. PROD. SHOW. SAN FRANCISCO, CALIF., 1972; HEADQUARTERS; A.S.M.E.; DA. 1971; VOL. 96; PP. 1-8; BIBL. 12 REF.Conference Paper

L'INDUSTRIE AEROSPATIALE FRANCAISE EN 19731973; INTERAVIA; SUISSE; DA. 1973; VOL. 28; NO 5; PP. 490-497Serial Issue

APPLICATION DES TECHNIQUES AEROSPATIALES A LA PROPULSION DE L'AEROTRAINCHEZLEPRETRE MB.sdIN: ASSOC. AERONAUT. ASTRONAUT. FRANCE. JOURN. JULES JARRY. 11EME CONGR. INT. AERONAUT.; PARIS; 1973; S.L.; DA. S.D.; PP. 1-34Conference Paper

SYSTEME DE TEST AUTOMATIQUE POUR BANC D'ESSAI DE TURBOREACTEURS.DUPUY C.1975; ELECTRON. MICROELECTRON. INDUSTR.; FR.; DA. 1975; NO 208; PP. 47-49Article

SCALE MODEL PERFORMANCE TEST INVESTIGATION OF EXHAUST SYSTEM MIXERS FOR AN ENERGY EFFICIENT ENGINE (E3) PROPULSION SYSTEMKUCHAR AP; CHAMBERLIN R.1980; AEROSPACE SCIENCES MEETING. 18/1980/PASADENA CA; USA; NEW YORK: AIAA; DA. 1980; 9 P.Conference Paper

PREDICTION OF OFF-DESIGN PERFORMANCE OF TURBOJET AND TURBOFAN ENGINES.WITTENBERG H.1978; A.G.A.R.D. CONF. PROC.; FRA; DA. 1978; NO 242; PP. 4.1-4.31; BIBL. 9 REF.Article

NASA/GE QUIET ENGINE "A" = LE MOTEUR SILENCIEUX "A" DE LA NASA/GEBENZAKEIN MJ; KAZIN SB; MONTEGANI F et al.1973; J. AIRCR.; U.S.A.; DA. 1973; VOL. 10; NO 2; PP. 67-73; BIBL. 5 REF.Serial Issue

THE GENERATION AND SUPPRESSION OF AIRCRAFT NOISEMCPIKE AL.1971; S.A.E. TRANS.; U.S.A.; DA. 1971; VOL. 80; PART 2; PP. 1290-1294; BIBL. 6 REF.Serial Issue

AIRCRAFT NOISE, ITS SOURCE AND REDUCTIONRUSSELL RE; KESTER KD.1971; S.A.E. TRANS.; U.S.A.; DA. 1971; VOL. 80; PART 2; PP. 1295-1314Serial Issue

F15 FLIGHT TEST EXPERIENCE WITH THE F100 ENGINE.HAMER DB; BALLARD GB.1976; J. AIRCR.; U.S.A.; DA. 1976; VOL. 13; NO 4; PP. 292-298; BIBL. 1 REF.Article

REDUCTION OF JT8D POWERED AIRCRAFT NOISE BY ENGINE REFANNING = REDUCTION DU BRUIT DES AVIONS A MOTEUR JT8D PAR MODIFICATION DE LA TURBO-SOUFFLANTESTITT LE; MEDEIROS AA.1974; S.A.E. TRANS.; U.S.A.; DA. 1974; VOL. 83; NO PART. 2; PP. 1859-1870; BIBL. 8 REF.Article

LE MOTEUR PEGASUS: EN PROGRES CONTINUCHOPPING D.1979; INTERAVIA; CHE; DA. 1979; VOL. 34; NO 12; PP. 1159-1160Article

BREVET DISPOSITIF DE COMMANDE DE CARBURANT POUR MOTEURS D'AVION1978; ; FRA; DA. 1978-06-16; FR/A1/2.367.917; DEP.77 21881/1977-07-18; PR. US/733.093/1976-10-18Patent

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