Lotarev DV-2

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Type	Turbofan
National origin	Soviet Union/Czechoslovakia
Manufacturer	Ivchenko-Progress/PSLM
First run	1987
Major applications	L-39MS Albatros L-59 Super Albatros Hongdu L-15 Ilyushin Il-108
Number built	124^[1]
Developed from	Ivchenko AI-25

The Lotarev DV-2 (or PSLM DV-2) is a two-spool turbofan engine manufactured in Považská Bystrica, Slovakia by Považské Strojárne Letecké Motory (PSLM) (former ZVL) and designed in partnership with Ivchenko Lotarev Design Bureau.^[2]

Design and development

Developed from the Ivchenko AI-25 turbofan engine, ZVL was also responsible for pre-production and serial engine production.^[1]

The DV-2 is a two-spool modular aviation turbofan engine with a single-stage overhung fan, two-stage LP compressor, seven-stage HP compressor, single-stage HP turbine, and two-stage LP turbine, and an annular combustion system. Maximum power at T-O is 4,850 lbf (21.58 kN) with a specific fuel consumption of 0.593lb/hr/lbf, at Maximum Rating, Sea Level Static, ISA.^[3]

One of the most unusual features of this military engine is the single stage fan; most trainer and combat engines have multi-staged fans, single stage fans normally being the preserve of civil and military transport turbofans. Ivchenko Lotarev chose a very low specific thrust (net thrust/airflow) cycle for the DV-2, so a single stage fan is sufficient to develop the desired fan pressure ratio. Even so, the pressure ratio produced is somewhat higher than that normally developed by a single stage fan. Owing to the low specific thrust, the bypass ratio for the engine is higher than normal for a military turbofan.

This engine was required to power new versions of the L-39 trainer, L-39MS and L-59. Other turbofan engine models in the DV-2 family include the DV-2A, DV‑2A.2 and DV-2S.

Applications

Specifications (DV-2S)

Data from PSLM website^[4]

General characteristics

Type: Two-spool low-bypass turbofan engine with a single-stage fan
Length: 1,72 m (67.7 in)
Width: 0.82 m (32.2 in)
Height: 1.04 m (40.9 in)
Diameter: Fan: 0.64 m (25.2 in)
Dry weight: 439 kg (967.8 lb)

Components

Compressor: Two-stage LP, seven-stage HP
Combustors: Annular combustion system with 16 fuel injection nozzles
Turbine: single-stage HP, two-stage LP

Performance

Maximum thrust: 2,498 Kgf; 5,508 pounds-force (24.50 kN)
Overall pressure ratio: 15.5
Bypass ratio: 1.4
Turbine inlet temperature: 1,440°K
Specific fuel consumption: 0.593lb/hr/lbf (60 kg/kN/h)
Thrust-to-weight ratio: 5.69

References

↑ 1.0 1.1 PSLM-DV-2 at janes.com
↑ PSLM Aero-engines manufacturer
↑ Russia, Central/Eastern Europe and China Turbofan and Turbojet Engines
↑ DV-2S by PSLM

External links

PSLM company website

v t e Ivchenko-Progress aircraft engines

Piston engines	AI-4 AI-14 AI-26

Gas turbines	AI-20 AI-22 AI-222 AI-24 AI-25 DV-2 D-18T D-27 D-36 D-436

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