The AL-21 is closely similar in technology to the General Electric J79 first flown in 1955, which was the first engine for supersonic flight, using a variable stator.[1]
It is generally described as being in the "third generation" of Soviet gas turbine engines which are characterized by high thrust-to-weight ratios and the use of turbine air cooling.[2]
^Aircraft Propulsion and Gas Turbine Engines By Ahmed F. El-Sayed p. 16
^Sosounov, V.A. (1990). The Development of Aircraft Power Plant Construction in the USSR and the 60th Anniversary of CIAM. AlAA/ASME/SAE/ASEE 26th Joint Propulsion Conference, July 16–18, 1990. Orlando, Florida. AIAA-90-2761.
External linksEdit
Wikimedia Commons has media related to Lyulka AL-21.
Page of the engine at Russian Aircraft Encyclopedia
October 17, 2023
lyulka, axial, flow, turbojet, engine, created, soviet, design, bureau, named, chief, designer, arkhip, lyulka, 21f3, engine, airforce, museum, bundeswehr, berlin, gatowtype, turbojetnational, origin, soviet, unionmanufacturer, salyut, perm, omkb, umpo, chernm. The Lyulka AL 21 is an axial flow turbojet engine created by the Soviet Design Bureau named for its chief designer Arkhip Lyulka AL 21Lyulka AL 21F3 engine Airforce Museum of the Bundeswehr Berlin GatowType TurbojetNational origin Soviet UnionManufacturer NPO AL Salyut Perm PMZ OMKB UMPO MMP ChernMajor applications Sukhoi Su 17 Sukhoi Su 24 Contents 1 Design and development 2 Specifications AL 21F3 2 1 General characteristics 2 2 Components 2 3 Performance 3 See also 4 References 5 External linksDesign and development EditThe AL 21 is closely similar in technology to the General Electric J79 first flown in 1955 which was the first engine for supersonic flight using a variable stator 1 It is generally described as being in the third generation of Soviet gas turbine engines which are characterized by high thrust to weight ratios and the use of turbine air cooling 2 The AL 21 entered service in the early 1960s Later designed the AL 21F3 it was used in the Sukhoi Su 17 Sukhoi Su 24 Ground attack variant Mikoyan Gurevich MiG 23 and Sukhoi T 10 Sukhoi Su 27 prototype Specifications AL 21F3 EditGeneral characteristics Type Afterburning turbojet Length 5 300 mm 209 in Diameter 1 000 mm 39 in Dry weight 1 700 kg 3 740 lb Components Compressor Two spool 14 stage axial compressor with variable stator vanes Turbine Two stage high pressure single stage low pressurePerformance Maximum thrust 76 4 kN 17 175 lbf dry 109 8 kN 24 675 lbf with afterburner Overall pressure ratio 14 75 1 Turbine inlet temperature 1 100 C 2 000 F Specific fuel consumption 77 5 kg h kN 0 76 lb h lbf at idle 87 7 kg h kN 0 86 lb h lbf at maximum military power 189 7 kg h kN 1 86 lb h lbf with afterburner Thrust to weight ratio 4 6 maximum military power 6 6 with afterburner Life expectancy 1 800 hoursSee also EditGeneral Electric J79Related lists List of aircraft enginesReferences Edit Aircraft Propulsion and Gas Turbine Engines By Ahmed F El Sayed p 16 Sosounov V A 1990 The Development of Aircraft Power Plant Construction in the USSR and the 60th Anniversary of CIAM AlAA ASME SAE ASEE 26th Joint Propulsion Conference July 16 18 1990 Orlando Florida AIAA 90 2761 External links Edit nbsp Wikimedia Commons has media related to Lyulka AL 21 Page of the engine at Russian Aircraft Encyclopedia Retrieved from https en wikipedia org w index php title Lyulka AL 21 amp oldid 1137694895, wikipedia, wiki, book, books, library,
