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38-574: The design of the AL-31 turbofan began in the 1970s under the designation izdeliye 99 by the Lyulka design bureau, also known as Lyulka-Saturn. With an emphasis on greater fuel efficiency over turbojets for longer range, the 12.5 tonnes-force (122.6 kN; 27,560 lbf) class turbofan engine was intended to power the heavy PFI (Russian: ПФИ , short for: перспективного фронтового истребителя , lit.   'Promising Frontline Fighter'), which

76-538: A new full authority digital engine control ( FADEC ) with a hydromechanical backup. Thrust was increased 9% across the envelope, with a maximum thrust of 14.5 tonnes-force (142.2 kN; 31,970 lbf) in afterburner. The engine has an MTBO of 1,000 hours and projected life increased to 3,000 hours. A version of the AL-31FM2 powers initial production batches of the Chengdu J-20 while later batches transitioned to

114-525: A potential powerplant for Sukhoi's T-50 PAK FA design but this was not pursued by Sukhoi, which instead chose Salyut rival NPO Saturn and its AL-41F1. Salyut's developments of the AL-31 would result in serious disputes with Lyulka-Saturn's successor corporation NPO Saturn, which considers them unsanctioned and in violation of intellectual property rights. Due to the decline of the Mikoyan Project 1.42/1.44 MFI fifth-generation fighter program in

152-449: A two-shaft axial-flow afterburning turbofan. The engine has a four-stage low-pressure compressor and a nine-stage high-pressure compressor, both driven by single stage turbines. Overall pressure ratio is 23, and the turbine inlet temperature is 1,392  °C (1,665  K ; 2,538  °F ); the turbine blades incorporate air film cooling. The engine is controlled by the analogue KRD-99 unit, and can tolerate severely distorted air flow from

190-438: Is known as wings level or zero bank angle, equivalent to a level heeling angle on a ship. Yaw is known as "heading". A fixed-wing aircraft increases or decreases the lift generated by the wings when it pitches nose up or down by increasing or decreasing the angle of attack (AOA). The roll angle is also known as bank angle on a fixed-wing aircraft, which usually "banks" to change the horizontal direction of flight. An aircraft

228-526: Is streamlined from nose to tail to reduce drag making it advantageous to keep the sideslip angle near zero, though aircraft are deliberately "side-slipped" when landing in a cross-wind, as explained in slip (aerodynamics) . The forces acting on space vehicles are of three types: propulsive force (usually provided by the vehicle's engine thrust); gravitational force exerted by the Earth and other celestial bodies; and aerodynamic lift and drag (when flying in

266-556: The WS-10 , with early examples directly using the AL-31F control system. According to Saturn's Victor M. Chepkin, chief designer of the 117 and 117S engines, the WS-10 was developed with the aid of the AL-31's maintenance technical documentation; this was recently confirmed by Aviation Industry Corporation of China (AVIC), the parent of Shenyang Aircraft Corporation. The base model AL-31F is

304-420: The angles of rotation with respect to the three aircraft's principal axes about its center of gravity , known as roll , pitch and yaw . Aircraft engineers develop control systems for a vehicle's orientation ( attitude ) about its center of gravity . The control systems include actuators, which exert forces in various directions, and generate rotational forces or moments about the center of gravity of

342-840: The " Kharkiv Aviation Institute " ( Ukrainian SSR ) where Arkhip Mikhailovich Lyulka was working with a team designing the ATsN (Agregat Tsentralnovo Nadduva - Centralised supercharger) installation on the Petlyakov Pe-8 bomber. Lyul'ka was responsible for designing the first Soviet gas turbine engines. Preferring to steer away from copying captured German equipment, it succeeded in producing home grown engines. Engines [ edit ] Summary of engines built/designed by Lyulka Model name Date Type Thrust (kg) / Power (eshp) Fitted to RTD-1 / VDR-2 1938 Two-stage centrifugal compressor Turbojet 500 kg estimated Test-bed only; planned for

380-632: The 1990s, the Russian Defence Ministry initiated the PAK FA program for a more affordable next-generation multirole fighter, with the competition announced in 2001. As the designs would be smaller than the MFI, the original Lyulka-Saturn AL-41F design for the MiG 1.42/1.44 was too large. Instead, a deeply improved AL-31F derivative from Lyulka-Saturn (later NPO Saturn) designated the izdeliye 117

418-526: The AL-31FN before newer variants transitioned to the domestic WS-10A, while the J-20 uses the AL-31FM2 as an interim engine until its intended WS-15 is ready. This reorganization would result in serious disputes between Saturn and Salyut over intellectual property rights and royalties over AL-31 sales to China. The AL-31 was also used to assist Chinese engine designer and manufacturer Shenyang/Liming in developing

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456-599: The AL-37FU, the canting of the vectoring axes allow differential vectoring to produce roll and yaw moments as well. The AL-31FP nozzle has a time before overhaul of 500 hours, while the engine's MTBO is 1,000 hours, and both have a service life of 2,000 hours. AL-31FP is built by UMPO as well as in India by Hindustan Aeronautics Limited (HAL) at the Koraput facility under a deep technology transfer agreement. The AL-31FN variant

494-533: The AL-41F1's thrust was increased by 2.5 tonnes-force (24.5 kN; 5,510 lbf) over the AL-31 while the engine weight growth was reduced by 150 kg (330 lb). The engine produces 9 tonnes-force (88.26 kN; 19,840 lbf) of thrust dry, 14.5 tonnes-force (142.2 kN; 31,970 lbf) in afterburner, and 15 tonnes-force (147.1 kN; 33,070 lbf) in an emergency, with a dry weight of approximately 1,600 kg (3,527 lb). The engine enables

532-2015: The KhAI-2 S-18 / VDR-3 1945 Axial flow compressor Turbojet 1,250 kg Gu-VRD project TR-1 1946 8-stage Axial flow compressor Turbojet 1,300 kg Alekseyev I-211 , Ilyushin Il-22 , Sukhoi Su-10 , Sukhoi Su-11 TR-1A 1947 8-stage Axial flow compressor Turbojet 1,500 kg TR-2 1947 projected growth version of TR-1 TR-3/AL-5 1949 7-stage Axial-flow Turbojet 4,600 kg (at qualification in 1950) Il-30 , Il-46 , La-190 , Aircraft '86' , Yak-1000 , Su-17 , Aircraft '150' TR-7 1950s supersonic compressor prototype Turbojet Prototype for AL-7 AL-7 1954 9-stage supersonic compressor Turbojet 6,500 kg Be-10 , Il-54 , Su-7 , Su-9 , Su-11 , Tu-28/Tu-128 , Tu-98 , Kh-20 AL-21 1961 Axial Turbojet 11,000 kg Su-17 , Su-24 , MiG-23 , T-10 AL-31 1981 Twin-spool Turbofan 0.6 bypass ratio. 13,300 kg Su-27 , Su-30 , Su-33 , Su-34 , Su-35 , Su-37 References [ edit ] Gunston, Bill. “The Osprey Encyclopaedia of Russian Aircraft 1875–1995”. London, Osprey. 1995. ISBN   1-85532-405-9 External links [ edit ] http://www.ctrl-c.liu.se/misc/ram/ v t e Lyulka and Saturn aircraft engines Turbojets AL 5 AL 7 AL 21 TR-1 TR-3 TR-7 Turbofans AL-31 AL-32 AL-41 AL-51 AL-55 Turboprops AL-34 Joint development PowerJet : SaM146 (Turbofan) Retrieved from " https://en.wikipedia.org/w/index.php?title=Lyulka&oldid=1237938872 " Category : Aircraft engine manufacturers of

570-755: The Shenyang/Liming WS-10A in lieu of the AL-31FN. Salyut also developed additional improved variants of the AL-31F with increased thrust and reliability. The first is the AL-31FM1, also designated as the AL-31F series 42, which had a larger KND-924-4 fan, with inlet diameter increasing from 905 mm (35.6 in) on the baseline AL-31 to 924 mm (36.4 in) which increased airflow by 6%. Additional enhancements include an improved core for greater turbine inlet temperature, and improved engine control system. The engine also had improved MTBO of 1,000 hours, projected life of 2,000 hours, and its thrust

608-470: The Soviet Union Flight dynamics Flight dynamics in aviation and spacecraft , is the study of the performance, stability, and control of vehicles flying through the air or in outer space . It is concerned with how forces acting on the vehicle determine its velocity and attitude with respect to time. For a fixed-wing aircraft , its changing orientation with respect to

646-530: The Soviet Union, design bureau and production plant distinctions realigned and gradually faded, and Lyulka-Saturn eventually merged with Rybinsk Motors to become NPO Saturn and was closely aligned with UMPO while Salyut became an independent entity; both Saturn and Salyut would make their own developments for the AL-31 family. Salyut also supplies AL-31 variants to fighters operated by the China . The J-10 uses

684-639: The Su-57 to achieve supersonic speed without afterburner, or supercruise , at Mach 1.3. Following completion of state tests to meet Russian Air Force requirements, serial production of the AL-41F1 began in 2019 for installation in production Su-57 fighters supplied to the Russian Air Force and prospective foreign clients. A non-afterburning version of the AL-41F1 powers the Sukhoi S-70 Okhotnik unmanned combat aerial vehicle (UCAV). While

722-599: The Sukhoi/ Irkut Su-30MKI for India as well as further derivatives including the Su-30MKM for Malaysia and the Su-30SM for the Russian Air Force and Navy. The AL-31FP has the same thrust of 12.5 tonnes-force (122.6 kN; 27,560 lbf) as the baseline AL-31F, but can deflect its nozzle to a maximum of ±15° at a rate of 30°/sec. The vectoring nozzle is used primarily in the pitch plane, but unlike

760-520: The WS-10C; both of these engines are interim powerplants in place of the J-20's intended Xian WS-15 . The last in this line is the proposed AL-31FM3, which would have a new 3-stage fan, designated KND-924-3, with further increased pressure ratio and additional core improvements to increase turbine inlet temperature by 150 °C. Maximum thrust was increased to 15 tonnes-force (147.1 kN; 33,070 lbf) in afterburner. The AL-31FM3 had been proposed as

798-460: The aerodynamic forces and moments applied to the aircraft. Spacecraft flight dynamics involve three main forces: propulsive (rocket engine), gravitational, and atmospheric resistance. Propulsive force and atmospheric resistance have significantly less influence over a given spacecraft compared to gravitational forces. Flight dynamics is the science of air-vehicle orientation and control in three dimensions. The critical flight dynamics parameters are

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836-401: The aircraft, and thus rotate the aircraft in pitch, roll, or yaw. For example, a pitching moment is a vertical force applied at a distance forward or aft from the center of gravity of the aircraft , causing the aircraft to pitch up or down. Roll, pitch and yaw refer, in this context, to rotations about the respective axes starting from a defined equilibrium state. The equilibrium roll angle

874-493: The atmosphere of the Earth or another body, such as Mars or Venus). The vehicle's attitude must be controlled during powered atmospheric flight because of its effect on the aerodynamic and propulsive forces. There are other reasons, unrelated to flight dynamics, for controlling the vehicle's attitude in non-powered flight (e.g., thermal control, solar power generation, communications, or astronomical observation). The flight dynamics of spacecraft differ from those of aircraft in that

912-489: The current Su-57 production tranches are powered by the AL-41F1, the aircraft is meant to be the basis for a family of stealth combat aircraft; future improved variants are planned to be powered by the Saturn izdeliye 30, later designated AL-51F-1 , a new design that fits into the same footprint as the AL-41F1. To spread out development risks and associated costs with the fifth-generation PAK FA program, Sukhoi applied some of

950-509: The engine was deeply improved with up to 80% new parts and application of technology from the AL-41F. It has increased fan diameter of 932 millimetres (36.7 in), new high- and low-pressure turbines, provisions for thrust-vectoring nozzles similar to the AL-31FP, and a digital control system ( FADEC ) integrated into the aircraft's flight control system. Though the specifics remain classified,

988-504: The first prototype of the improved design; the aircraft's aerodynamic refinements from changes in the outer shaping and packaging also resulted in the AL-31 gearbox changing to a top-mounted position. State tests of the AL-31 were completed in 1985, and the T-10 entering Soviet air services as the Su-27 . The engine is manufactured at Ufa-based UMPO and Moscow-based Salyut. After the collapse of

1026-465: The 💕 Lyulka Company type Aero-engine Design Bureau Successor NPO Saturn Headquarters Moscow , USSR Key people Arkhip Mikhailovich Lyulka Products Aircraft engines Lyulka was a USSR aero engine design bureau and manufacturer from 1938 to the 1990s, when manufacturing and design elements were integrated as NPO Saturn based at Rybinsk . The Lyulka design bureau had its roots in

1064-703: The initial customer would be the Russia Defence Ministry. The engine produces 8.8 tonnes-force (86.30 kN; 19,400 lbf) of thrust dry, 14 tonnes-force (137.3 kN; 30,860 lbf) in afterburner, and 14.5 tonnes-force (142.2 kN; 31,970 lbf) in an emergency. The AL-41F1S fan diameter was increased by 3% over the baseline AL-31, from 905 mm (35.6 in) to 932 mm (36.7 in), and also has increased turbine inlet temperature. This engine weighs 1,604 kg (3,536 lb) dry and has an assigned life of 4,000 hours and an MTBO of 1,000 to 1,500 hours. The first flight of this engine

1102-483: The intake. It produces 7.8 tonnes-force (76.49 kN; 17,200 lbf) of thrust dry and 12.5 tonnes-force (122.6 kN; 27,560 lbf) of thrust in afterburner. The AL-31 has a modular design to facilitate maintenance and overhaul. In the twin-engine Su-27, left and right engines are interchangeable. Initially, the Mean Time Between Overhaul (MTBO) of the engine was only 100 hours, short of

1140-422: The local air flow is represented by two critical angles, the angle of attack of the wing ("alpha") and the angle of attack of the vertical tail, known as the sideslip angle ("beta"). A sideslip angle will arise if an aircraft yaws about its centre of gravity and if the aircraft sideslips bodily, i.e. the centre of gravity moves sideways. These angles are important because they are the principal source of changes in

1178-544: The required 300 hours. Later series incrementally improved the MTBO figure to 500 hours while service life was assigned as 1,500 hours. Further improved variants, such as the AL-31F Series 42, increased the MTBO to 1,000 hours with a full-life of 2,000 hours. The AL-37FU and AL-31FP variants have thrust vectoring . The AL-37FU was an experimental thrust vectoring variant for a modified Su-27M, later designated Su-37 , and

Saturn AL-31 - Misplaced Pages Continue

1216-738: The technology, including the propulsion system, into a highly upgraded Su-27 variant, designated T-10BM (popularly called the Su-35BM), before being designated just as the Su-35. The aircraft's powerplant, the NPO Saturn izdeliye 117S, or AL-41F1S, is a slightly simplified derivative of the AL-41F1 from the Su-57, with the key difference being the separate engine control system of the AL-41F1S. The Su-35 and its AL-41F1S engines were originally developed by Sukhoi and Saturn internally for export, although

1254-455: Was being developed by Sukhoi as the T-10. The chief designer was Arkhip M. Lyulka , and after his death, Victor M. Chepkin. As the AL-31 was not yet ready for the first two T-10 prototypes in 1977, they were initially powered by modified AL-21F3 turbojet engines. The third prototype would be the first to install the AL-31. The T-10 design would be heavily revised into the T-10S, with T-10-7 being

1292-547: Was completed in an Su-35BM on 20 February 2008. On 9 August 2010, UMPO started supplying AL-41F1S intended for Su-35S fighters. The engine is also equipped on the Su-30SM2 as part of the upgrade plan to unify its systems with the Su-35S. (Optional) Data from Gordon, Rosoboronexport, United Engine Corporation, UMPO, Saylut Data from Rosoboronexport Comparable engines Related lists Lyulka From Misplaced Pages,

1330-609: Was contracted by Sukhoi for its T-50 design, which would eventually win the competition in 2002 and enter service in 2020 as the Su-57 . First proposed by Saturn in 2001, the izdeliye 117, or AL-41F1, formally began development in April 2004 with contract signing by NPO Saturn. While the AL-41F1 has the same overall architecture as the baseline AL-31, with a 4-stage low-pressure compressor (fan) and 9-stage high-pressure compressor and one-stage low pressure and one-stage high pressure turbines,

1368-554: Was developed by Salyut to power the Chengdu J-10 , with key differences including slightly more thrust of 12.7 tonnes-force (124.54 kN; 27,999 lbf) and gearbox relocated from the top to the bottom of the engine. Later J-10 variants and production lots were equipped with the improved AL-31FN series 3, with thrust increased to 13.7 tonnes-force (134.35 kN; 30,203 lbf) and service life raised by 250 hours. Further production J-10 batches would eventually be equipped with

1406-512: Was increased to 13.5 tonnes-force (132.4 kN; 29,760 lbf); this engine passed Russian state acceptance testing in 2006 and was equipped on the Su-27SM, Su-30M2, and Su-34. The AL-31FM2 is a further development of the AL-31FM1. Fan aerodynamics was further refined to increase its pressure ratio. The engine also incorporated improvements to the combustor and turbine blade aerodynamics and cooling for higher entry temperatures. The AL-31FM2 has

1444-479: Was uprated to 14.5 tonnes-force (142.2 kN; 31,970 lbf) of thrust. The thrust vectoring nozzles could deflect ±15° in the vertical plane together for pitch or differentially for roll. After the engines reached the end of their service lives, the sole Su-37 was equipped with the normal AL-31F until it crashed in December 2002. The research on thrust vectoring would be applied to the production AL-31FP used in

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