Turbofan-50

Initially, the TRDD-50 was intended for the Kh-55 airborne cruise missile (CR) (RKV-500; NATO designation - AS-15 "Kent"), developed by the ICB "Rainbow" . It was developed in the late 1970s by the Omsk Motor Engineering Design Bureau . It is a response to the American KR type BGM-109 "Tomahawk" with the engine F107. According to a number of indicators, the turbofan engine-50 surpasses the F107 engine. Nevertheless, the quality of the engine allows it to be used for a wide range of aircraft - from various types of missiles to UAVs (scouts, targets).

In the second half of the 1970s, the Ministry of Aviation Industry (MAP) commissioned the OMKB (chief designer Pashchenko Viktor Stepanovich) to develop a dual-circuit turbojet engine for cruise missiles developed by the ICB "Rainbow", led by Igor Seleznev. Subsequently, the Novator Design Bureau ( Lev Lyulyev, chief designer) joined this assignment. The decision on development was also facilitated by the firm opinion of CIAM specialists who knew perfectly well the abilities of designers and the potential capabilities of OMKB.

Work on the creation of the turbofan engine-50 began in 1976 and was very successful. The design was based on the best practices of OMKB designers. The engine was delivered on time for flight tests. In 1980, state tests of the layout of the engine with a pylon (“Product 36”, for the MKB “Rainbow”) were successfully carried out, and after a while another - “built-in” layout (“Product 36-01”, for the Design Bureau “Novator”). These tests became a triumph for OMKB, given that at the same time intense work was underway to fine-tune and prepare for state tests of the TVD-10B and AFU-10 engines.

After conducting state tests of the TRDD-50 engine, the technical documentation was transferred to the Rybinsk Motors engine-building plant (which later became part of the Saturn NPO) for mastering serial production.

However, the same task (development of a single-use turbofan turbojet engine) was received by the Soyuz MNPO (the head was Oleg Nikolaevich Favorsky). In parallel with the work on the creation of the engine TRDD-50, the development of a similar engine ( P95-300 , “product 95”) for the same objects begins. After the completion of state tests, all documentation on the “product 95” was transferred to the “Zaporizhzhya Engine Building Plant” for the development of its serial production.

The MAP faced a dilemma - which of these two engines should be given the green road. The issue was put up for discussion at the MAP Scientific and Technical Council. On the one hand, the turbofan engine-50 exceeded its competitor in survivability; on the other hand, several test launches failed due to the fault of this engine ^[1] . As a result, the council decided to launch the “product 95” in large-scale production, thus closing the road to life for many years to the engine TRDD-50.

With the collapse of the USSR, the only manufacturer of the P95-300 engine remained in Ukraine . In this regard, it was decided to resume the production of “Product 36” to replace the exhausted P95-300 and equip new CDs.

NPO Saturn together with OMKB since 2000 conducted work on the restoration of production (to replace the P95-300 engines) and the repair of "product 36". In particular, modifications to the TRDD-50 base model - TRDD-50A and TRDD-50AT engines - were launched into large-scale production. On the very same OMKB developed and launched the release of another modification - the engine TRDD-50B ("Product 37").

At present, both enterprises are actively producing various modifications of the engine TRDD-50. In addition, the active process of modernizing the old and developing new promising cruise missiles, which uses the turbojet engine-50, continues.

• Two tests were attended by two engines at once - TRDD-50 and P95-300 . The first tested P95-300. Before starting the engine, representatives of MNPO Soyuz thoroughly vacuumed the test bench. After it came the turn of the turbojet engine-50. The OMKB representatives were asked whether they would vacuum the booth, which they were very surprised at and said no.
• An interesting proposal was made - to additionally equip passenger airliners with a pair of TRDD-50 engines. The calculation was that if all the engines failed at once, then the turbojet engine-50 would start. The thrust to continue the flight would be too small, but it would be enough to carry out a controlled landing. The offer did not find support.
• The first test flights of the KR X-55 took place with the engine TRDD-50, because at that time it was more complete than the P95-300.
• Motor Engineering Plant named after P.I. Baranova , located on the same territory as the OMKB, rejected the proposal to establish serial production of the engine TRDD-50.

Engine Features:

• Dual-circuit twin-shaft turbojet engine with coaxial shafts of low and high pressure circuits.
• High pressure circuit - axial-diagonal compressor (one axial stage and one diagonal) and a single-stage axial turbine .
• Low pressure circuit - a single-stage fan with wide-chordate blades and a single-stage axial turbine.
• An annular semi - loop combustion chamber with a rotating nozzle.
• Autonomous oil system.
• Electronic-hydraulic regulation system.
• Built-in 4 kW electric generator.
• High fuel efficiency.
• Resistance to small foreign objects (birds, dust, etc.) entering the entrance.
• Resistance to shock and heat waves.
• The ability to spontaneously exit surging after the disappearance of the cause that caused it.
• Reliable start-up in the entire range of external operating conditions (t from −50 ° C to +60 ° C, altitude up to 10,000 m).
• Long operating time - up to 10 hours (according to the project, longer work is possible).
• High reliability - 1 failure per 1000 launches (according to the project).
• Ability to work at maximum speed up to 1-2 hours
• High throttle response.
• The ability to take air for the needs of the aircraft.

Technical data TRDD-50AT:

• Maximum traction - 450 kgf.
• The specific fuel consumption at maximum mode is 0.71 kg / kgf * h.
• Diameter - 330 mm.
• Length - 850 mm.
• Dry weight - 82 kg.
• The oil used is VT-301.
• The fuel used is T-1 (aviation kerosene) , T-6, T-10 ( decylin ), TS-1, RT.

• X-55 (including on modifications: X-65, X-555).
• 3M10
• X-59 .
• X-101 /102.
• X-35 .
• 3M14 .
• 3M54 .

During the Syrian operation , in November 2015, Russian troops first used the X-101 cruise missiles .

On October 7, ships of the Caspian flotilla completed 26 launches of sea-based cruise missiles " Caliber " (which was their first combat use) from the Caspian Sea , destroying 11 targets in Syria. On November 20, ships of the Caspian Flotilla completed 18 launches of cruise missiles , hitting 7 targets in Syria. On December 8, 2015, cruise missile attacks on targets in Syria were carried out by the Rostov-on-Don submarine , which was located in the Mediterranean Sea .

Developments of NPO Saturn:

• TRDD-50A (“Product 36M”, designed for aircraft-based cruise missiles).
• TRDD-50AT ("Product 36MT", designed for tactical missiles X-59ME, X-59MK, X-35E).

Developments of OMKB OJSC:

• TRDD-50B ("Product 37", designed for sea-based cruise missiles of the Club type, developed by the Novator design bureau; promising strike submarines are equipped with these missiles).

• P95-300 (AMNTK Soyuz).
• Williams F107 ("Williams International").

• Website of OMKB OJSC.
• An article by the former director of the MICK Viktor Pashchenko.
• Page about turbofan engine-50 on the website of NPO Saturn.