Turbofan bypass engine with noise suppression system
The PS-90A engine is one of the significant achievements of the Russian aviation motor industry of the 90s. It is a turbofan bypass two-shaft engine with propulsion unit, core airflows’ mixing, thrust reverser in a fun duct and high level of commonality.
For more than 25 years, the PS-90A remains a single 4Gen engine in the Russian aviation.
In the end of 1982, the contest was announced for a 16 000 kgf - thrust engine with high level of commonality intended for New Gen passenger aircrafts TU-204 and Il-96. Perm design engineers won the contest: the D-90A tests demonstrated the advantages of Perm engine in specific oil consumption and weight and, thus, guaranteed the win in the contest. In 1987, the engine was named after its developer Pavel Soloviev, i.e. PS-90A.
The PS-90A developers were the first to use mounts made of polymer composite materials. Thanks to 2 Gen noise suppression systems, PS-90A aircrafts and its modifications reduced noise level. They can fly to all the airports worldwide without restrictions.
The PS-90А-76 was created in 2003 for cargo aircrafts of the family Il76MD-90 as well as in order to update the Il-76 fleet (increase aircraft efficiency and ensure the conformity of ICAO eco-parameters on emission and noise).
In 2017, special PS-90A-76 modification was installed in the multifunctional aviation complex of radar surveillance and guidance A-100.
The PS-90A1 engine was designed in 2007 for the wide-body transport aircraft Il-960400T. The main feature of the PS-90A1 is an increased takeoff thrust of up to 17 400 kgf. The engine has low-emission combustor, 2 Gen noise absorbing design, and high commonality with the primary engine PS-90A (98 %).
The advanced PS-90A2 was designed in 2009 for a medium-range passenger aircraft Tu204SM (new HP turbine, new control system, new transmission bearings and supports). Compared to the primary engine PS-90A, it has a number of advantages, i.e. reduced maintenance and longer life cycle of main components.
Takeoff Thrust: 16000 kgf
Cruise Thrust: 3500 kgf
Specific Fuel Consumption: 0,595 kg/kgf hr
Bypass Ratio m=4,4
Maximum Gas Temperature Т=1640К
Flight Altitude: up to 13100 m
Altitude by start: 7 000 m
Air Temperature (for start and operation): –47...+45°C
Aerodrome Altitude: up to 3500 m
Motor Maintenance Weight: 2950 kg
Empty Weight: 4300 kg
Length: 4964 mm
Fan Diameter: 1900 mm