Snecma-Turbomeca Larzac

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A cut open Larzac 04. The front end (turbofan) can be seen in the picture below.

The Snecma-Turbomeca Larzac is a military turbofan jet engine that was developed by the French consortium GRTS (Groupement Turboméca - SNECMA ) in the late 1960s. It was selected in February 1972 as a drive for the Franco-German light fighter-bomber and training aircraft Alpha Jet and in 1993 as a MiG-ATF drive.

development

The French companies Turboméca and SNECMA founded the GRTS consortium in 1968 to develop the engine . The first test run of the M49 Larzac took place in 1969. This engine, originally intended for civil use, was further developed after the reorientation to the military market to the Larzac 04-C6 , which was selected in 1972 as a drive for the Alpha Jet. From October 1973 to the end of 1975, flight tests were carried out in the Alpha Jet in Istres to obtain certification. Further milestones were the first flights of the first series Alpha jet (November 4, 1977 in Istres) and the first German Alpha jet (April 12, 1978 in Oberpfaffenhofen ).

In 1975 a cooperation with the German companies Klöckner-Humboldt-Deutz (KHD, later Deutz AG ) and MTU was concluded for the series production of the engines . To this was added after the acquisition of the Alpha Jet in Belgium or the Belgian FN Partners (later Techspace Aero ). This ultimately resulted in shares of 29.4% for Turboméca, 23% from SNECMA, 22.6% from MTU, 22% from KHD and 4% from FN / Aerospace Tech in development and production.

The original Alpha Jet engine Larzac 04-C6 was further developed from 1981 to the more powerful Larzac 04-C20 . This version or the parts kits for converting 04-C6 variants were delivered from 1984. A planned civil version Larzac 03 to equip the Aérospatiale Corvette was not ready for the market.

construction

The Larzac is a twin-shaft engine without an afterburner . The low-pressure compressor or fan is two-stage and the high-pressure compressor is four-stage, the high-pressure and low-pressure turbines are each single-stage. All compressor and turbine stages are flowed through axially. The engine has an annular combustion chamber .

use

  • Alpha Jet (two Larzac 04-C6 or 04-C20)
  • HAL HJT-36 Sitara (prototypes for flight tests with a Larzac 04-H20)
  • MiG ATF (export version, with two Larzac 04-R20)

Technical specifications

version Larzac 04-C6 Larzac 04-C20
Series delivery from September 1977 September 1984
length 1,179 mm 1,187 mm
outer diameter 602 mm
Inner diameter fan step 452 mm
Dry matter 302 kg
Air flow 28.09 kg / s 28.57 kg / s
Compressor pressure ratio 10.53: 1 11.13: 1
Bypass ratio 1.13: 1 1.03: 1
Standing thrust 13.19 kN 14.12 kN
Specific consumption 20.44 g / kNs 21.28 g / kNs

literature

  • von Gersdorff, Grasmann: Die deutsche Luftfahrt , Volume 2: Flugmotoren und Strahltriebwerke, Bernard & Graefe Verlag Munich, 3rd supplemented and expanded edition 1995, ISBN 3-7637-6107-1 , p. 338 ff.
  • Mark Lambert (Ed.): Jane's All The World's Aircraft - 1993-94 , Jane's Information Group Ltd., Coulsdon, 1993, pp. 618 f.

Web links