Olympus 201 Jet Engine Turbine Blade

The Rolls-Royce / Bristol Olympus 201 jet engine was a turbojet engine developed in the 1950s and used in aircraft like the Avro Vulcan strategic bomber. The Olympus series later evolved into the Olympus 593, which powered the Concorde supersonic aircraft.

Turbine Blade Overview for the Olympus 201 Engine

1. Function & Placement

• The turbine blades in the Olympus 201 engine are located in the high-pressure turbine (HPT) and low-pressure turbine (LPT) stages.

• Their role is to extract energy from the high-temperature exhaust gases, driving the compressor and other engine components.

2. Material Composition

• Likely made from nickel-based superalloys to withstand high temperatures and stress.

• Early directionally solidified (DS) or equiaxed grain casting techniques were used, as single-crystal (SC) technology was not yet widely available at the time.

• Coated with oxidation-resistant and thermal barrier coatings to improve lifespan.

3. Cooling & Heat Resistance

• Some turbine blades in later Olympus models incorporated internal cooling channels.

• Air-cooled designs helped extend operational life by reducing thermal fatigue.

Titanium vs. Nickel Alloy Use in the Olympus 201

• Titanium was primarily used in the compressor blades and fan sections.

• Nickel-based superalloys were used for turbine blades, as titanium cannot withstand the extreme heat of the turbine section.