Progress D-27

Open-rotor · Ivchenko-Progress ZMKB
Reaction Turbines
Maximum Takeoff Thrust
119 kN
Diameter
970 mm
Length
4205 mm
Dry Weight
1650 kg

Architecture

Fan Fan Stages — Fan Blades — Fan Technology — Fan Pressure Ratio —
Gearbox Geared Fan Yes Gear — Reduction Ratio —
LP compressor Low-Pressure Compressor Stages — Low-Pressure Compressor Technology — BP Compressor Pressure Ratio —
IP compressor Intermediary-Pressure Compressor Stages — Intermediary-Pressure Compressor Technology — IP Compressor Pressure Ratio —
HP compressor High-Pressure Compressor Stages — High-Pressure Compressor Technology — HP Compressor Pressure Ratio —
Combustor Combustion Chamber Annular combustion chamber
HP turbine High Pressure Compressor Stages — High-Pressure Turbine Technology —
IP turbine Intermediary-Pressure Turbine Stages — Intermediary-Pressure Turbine Technology —
LP turbine Low-Pressure Turbine Stages — Low-Pressure Turbine Technology —
Whole engine Streams 1 Bypass Ratio — Overall Pressure Ratio — Afterburner No

Pictures

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Airplanes

Name Aircraft Engine Number of Engines Length (m) Flat Wing Span (m) Max Seating
Antonov An-180 Progress D-27 2 40.9 35.83
Antonov An-70 Progress D-27 4 40.73 44.06 300
Yakovlev Yak-44 Progress D-27 2 20.39 25.7
Yakovlev Yak-46 Progress D-27 2 41 35.5

Similar reaction turbines

Name Family Aircraft Engine Manufacturer Maximum Takeoff Thrust (kN) Bypass Ratio Overall Pressure Ratio
LEAP-1B25 LEAP-1B CFM International 119.15 8.3584 39.0582 Compare
CFM56-5B4 CFM56-5B CFM International 117.9 5.9 27.1 Compare
CFM56-5A3 CFM56-5A CFM International 117.88 6 27.9 Compare
D-30KP-2 Aviadvigatel 117.6 2.2 19.45 Compare
PW1127G1-JM Pratt & Whitney 120.43 12.28 31.66 Compare
PW1127G-JM Pratt & Whitney 120.43 12.28 31.66 Compare
All data (14 fields)
Name
Progress D-27
Aircraft Engine Manufacturer
Ivchenko-Progress ZMKB
Aircraft Engine Type
Open-rotor
Dry Weight (kg)
1650
Diameter (mm)
970
Length (mm)
4205
Wikipedia Article (URL)
en.wikipedia.org/wiki/Progress_D-27
Geared Fan
Yes
Combustion Chamber
Annular combustion chamber
Afterburner
No
Streams
1
Maximum Takeoff Thrust (kN)
119
Compressor Description
5-stage axial flow low-pressure compressor (LPC); high-pressure compressor (HPC) with 2 axial stages and 1 centrifugal stage
Turbine Description
1-stage high-pressure turbine (HPT), 1-stage low-pressure turbine (LPT), 4-stage free power turbine