Turbomeca Turmo 1 gas producer

The Turbomeca Turmo I is a turboshaft engine designed and built in France during the 1950s, which was developed into the Turbomeca Turmo III series of turboshaft / turboprop engines.

Turmo I
Type Gas turbine gas producer
National origin France
Manufacturer Turbomeca
Developed from Turbomeca Artouste
Variants Turbomeca Turmo III

Design and development

The Turmo was initially developed with a single-stage centrifugal compressor, annular combustion chamber and single stage turbine. Power output was from a single-stage free power turbine and was initially a very modest 200 kW (270 hp).[1]

During early post-war helicopter development, the use of cold and hot rotor tip-jets was widely investigated. To provide large mass-flow air for efficient operation of the tip-jets, turbomeca developed a gas turbine driven gas producer, powered by the free power-turbine of the Turmo to deliver the required gas flow.[1]

Operational history

A Turmo I was fitted to the Renault Étoile Filante gas-turbine powered car, which set a world speed record for gas-turbine powered cars in 1956.[1]

Variants

Data from:-Jane's all the World's Aircraft 1957–58[1]

Turmo I
The initial version of the Turmo; max continuous gearbox output 200 kW (270 shp) at 3,000 rpm, at 33,750 rpm gas generator speed.
Turmo II
Developed version of the Turmo I; max continuous gearbox output 240 kW (320 shp) at 34,000 rpm gas generator speed.
Turmo III
With 2-stage free power-turbine, pressure ratio 5.7:1 ;Maximum shaft output 560 kW (750 shp), max continuous 450 kW (600 shp) at 33,400 rpm

Specifications (Turmo II)

Data from Aircraft engines of the World 1957[2]

General characteristics

  • Type: Gas turbine power unit with gear box and air producer
  • Length: 1,232 mm (48.5 in)
  • Width:550 mm (22 in)
  • Height:589 mm (23.2 in)
  • Diameter:
  • Dry weight: 170 kg (370 lb)

Components

  • Compressor: 1-stage centrifugal flow
  • Combustors: annular
  • Turbine: 1-stage axial flow
  • Gas producer turbine: 1-stage axial free turbine mounted on output shaft.
  • Fuel type: JP-1 or equivalent
  • Oil system: pressure spray at 300 kPa (43 psi) with return

Performance

  • Maximum power output: 240 kW (320 shp) at 34,000 rpm gas generator speed, gearbox output at 6,000 rpm
  • Overall pressure ratio: 3.9:1
  • Air mass flow: 3.2 kg/s (420 lb/min) at 34,000 rpm
  • Fuel consumption: 170 kg/h (370 lb/h)
  • Oil consumption: 0.25 kg/h (0.55 lb/h)
  • Power-to-weight ratio: 0.55 kg/kW (0.9 lb/shp)

References
  1. Bridgman, Leonard, ed. (1957). Jane's all the World's Aircraft 1957–58. London: Sampson Low, Marston & Company, Ltd.
  2. Wilkinson, Paul H. (1957). Aircraft engines of the World 1957 (13th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 63.
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