Rolls-Royce/Snecma Olympus 593-610

Rolls-Royce/Snecma Olympus 593-610 on display at Aerospace Bristol.

The Concorde 593 Engine Variants

• 593 – Original version designed for Concorde. Thrust : 20,000 lbf (89 kN) dry / 30,610 lbf (136 kN) reheat
• 593-22R – Powerplant fitted to prototypes. Higher performance than original engine. Thrust : 34,650 lbf (154 kN) dry / 37,180 lbf (165 kN) reheat
• 593-610-14-28 – Final version fitted to production Concorde. Thrust : 32,000 lbf (142 kN) dry / 38,050 lbf (169 kN) reheat

Specifications (Olympus 593 Mk 610)

• Type: turbojet
• Length: 4.039 m (159 in)
• Diameter: 1.212 m (47.75 in)
• Dry weight: 3,175 kg (7,000 lb)

Components

• Compressor: Axial-flow, 7-stage low-pressure, 7-stage high-pressure
• Combustors: Nickel alloy construction annular chamber, 16 vapourising burners, each with twin outlets
• Turbine: Two stages: one high-pressure, one low-pressure
• Fuel type: Jet A1

Performance

• Maximum Thrust: wet: 169.2 kN (38,050 lbf) dry: 139.4 kN (31,350 lbf)
• Overall pressure ratio: 15.5:1
• Specific fuel consumption: 1.195 (cruise), 1.39 (SL) lb/(h·lbf)
• Thrust-to-weight ratio: 5.4

Jetpipe

• Straight pipe with pneumatically operated convergent nozzle
• Single ring afterburner
• ‘Eyelids’ nozzles also act as thrust reversers

Concorde engine specification sourced from Heritage Concorde

Side photo of turbojet engine showing logos of Rolls-Royce & Snecma.