Temperature reduction

Engines PD on the basis of a unified gas generator – a family of domestic twin-turbojet twin-engine engines intended for short- and medium-range aircraft and industrial gas turbines.

Main feature PD engine families – the use of a unified compact gas generator.

Key key technologies: hollow wide chord titanium blades, monowheels (blisks) and a welded section in the rotor of a high-pressure compressor, low-emission intermetallic alloy combustion chamber, single-crystal blades of a high-pressure turbine with a promising cooling system, ceramic coatings on hot parts, hollow blades of a low-pressure turbine, composite nacelle.

The main advantages of PD engines

Operating time for unavoidable in-flight engine shutdown

Reliability of the aircraft departure due to engine readiness

Low fuel consumption

Reduced specific fuel consumption relative to modern engines

Compliance with promising environmental standards

Noise reduction regarding ICAO standard 4 requirements

Reduction of NOx emissions relative to ICAO 2008 norms

Compliance with current certification requirements

AP-33, FAR-33, CS-E, ETOPS

Engine modifications currently under development

The family of promising turbofan engines for BSMS consists of engines PD-14, PD-14A, PD-14M, PD-10;

PD-14 – basic TRDD for aircraft MS-21-300;

PD-14A – throttled version of the turbofan engine for aircraft MS-21-200;

PD-14M – forced version of turbofan engines for aircraft MS-21-400;

PD-10 is a variant with a reduced pressure of up to 10. 11 ts for SSJ ‑ NG aircraft.

Main parameters of engines (all parameters are given without taking into account losses in the air intake and without air bleed and power for aircraft needs)





Thrust on takeoff mode (H = 0; M = 0), tf

Temperature reduction

Specific fuel consumption in cruising mode, kg / kgf · h

-(10-15)% of the level of modern engines of a similar class of thrust and purpose

Fan diameter, mm

Dry engine weight, kg

Also, on the basis of the technologies developed in the framework of the PD-14 Project, it is planned to create industrial gas turbines for the production of gas compressor units and gas turbine power plants in the 8, 16 MW capacity classes.

Competitive advantages in terms of economic efficiency of operation are provided with the following main parametric and design features in comparison with competing analogues:

Lower temperatures at the exit from the combustion chamber are the most important factor in reducing cost, reducing risks in achieving the stated indicators of durability and reliability of aircraft engines with a short flight cycle.

Smaller fan diameter PD-14 allows you to have an objective weight reduction engine and frontal resistance engine nacelle.

The optimal size of the internal circuit (gas generator) facilitate the solution of the problem of relatively large air intake from the compressor for various needs and reduce the installation loss of thrust.

Enough high rated fan compression ratio (due to the use of a slightly lower bypass ratio) eliminates the need to use an adjustable outer contour nozzle with an inevitable increase in mass and resistance of the propulsion system and reduces installation thrust losses.

Field-proven gearless circuit PD-14 engine allows to achieve the required indicators of mass, resource, reliability and cost of maintenance.

The optimal combination of moderately high cycle parameters and a proven engine circuit with a direct drive fan helps to reduce the engine price, maintenance and repair costs, weight and drag of the propulsion system and ensure the advantage of the PD-14 engine in terms of economic efficiency of operation and life cycle cost.

Status of design and development works of the Project PD-14

Completed phase of the technical project. Received positive conclusions.

The work with the Irkut Corporation on the integration of the engine and the aircraft has been expanded.

A large amount of testing of experimental units and engine systems on special installations was performed.

A demonstration engine of the base engine project was designed to confirm the performance of PD-14 units.

The first stage of the gas generator development test has been completed.

Production and testing of the engine-technology demonstrator confirmed the readiness of critical technologies.

Tests of MG assemblies from PKM on the prototype engine were carried out.

Temperature reduction

The working design documentation for the engines PD-14 and engine nacelles of the pilot batch has been released.

Production cooperation has been formed for the production of an experimental batch of engines and engine nacelles; production of an experimental batch of engines and engine nacelles has begun.

The testing program for engines of demonstrators 100-03 and 100-04 has been completed, the need to implement selected design solutions has been confirmed.

An application has been submitted to the IAC AR for obtaining an engine type certificate.

A PD-14 Certification Base was developed covering the requirements of AR IAC, EASA, FAA.

A mock-up commission for the PD-14 engine was conducted and the protocol of the MAC of the IAC AR was approved.

A mock-up commission was conducted on an MS-21 aircraft with a PD-14 propulsion system and the IAC AR protocol of the IAC was approved.

The pre-production was completed and the VI level of technological readiness was ensured in the manufacture of an experimental batch of PD-14 engines.

Flight tests of the PD-14 engine are carried out as part of the IL-76LL flying laboratory at the LII them. Gromov.

ODK-Aviadvigatel received a type certificate for the newest aviation engine PD-14

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