SNECMA Turbomeca Larzac

Turbofan · SNECMA

Bypass Ratio

1.04

Diameter

451.866 mm

Length

1186.942 mm

Dry Weight

294.9938 kg

Thrust To Weight

4.567

Specific Fuel Consumption

2067.725 g/(kN·s)

Architecture

Fan	Fan Stages —	Fan Blades —	Fan Technology —	Fan Pressure Ratio —
Gearbox	Geared Fan No	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
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 2	Bypass Ratio 1.04	Overall Pressure Ratio —	Afterburner No

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Name	Aircraft Engine	Number of Engines	Length (m)	Flat Wing Span (m)
Dassault/Dornier Alpha Jet	SNECMA Turbomeca Larzac	2	13.23	9.11
HAL HJT-36 Yashas	SNECMA Turbomeca Larzac	1	11	10

All data (17 fields)

Name: SNECMA Turbomeca Larzac
Aircraft Engine Manufacturer: SNECMA
Aircraft Engine Type: Turbofan
Dry Weight (kg): 294.9938
Diameter (mm): 451.866
Length (mm): 1186.942
Wikipedia Article (URL): en.wikipedia.org/wiki/SNECMA_Turbomeca_Larzac
Fuel: Aviation kerosene Jet A-1 or similar
Geared Fan: No
Combustion Chamber: Annular
Afterburner: No
Streams: 2
Bypass Ratio: 1.04
Thrust To Weight: 4.567
Specific Fuel Consumption (g/(kN·s)): 2067.725
Compressor Description: Low pressure: 2 stage axial, High pressure: 4 stage axial
Turbine Description: Low pressure: 1 stage, High pressure: 1 stage