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Rolls-Royce Olympus variants
The Rolls-Royce Olympus turbojet engine was developed extensively throughout its production run, the many variants can be described as belonging to four main groups.
Initial non-afterburning variants were designed and produced by Bristol Aero Engines and Bristol Siddeley (BSEL) and powered the Avro Vulcan. These engines were further developed by Rolls-Royce Limited.
The first afterburning variant, the Bristol Siddeley Olympus Mk 320, powered the cancelled BAC TSR-2 strike aircraft. A further afterburning variant was the Rolls-Royce/Snecma Olympus 593, jointly developed to power Concorde in the 1960s.
The American Curtiss-Wright company tested a license-developed version known as the J67 and a turboprop designated TJ-38 Zephyr. Neither design was produced.
Further derivatives of the Olympus were produced for ship propulsion and land-based power generation.
Thrust given in foot-pounds (lbf) and kilonewtons (kN).
The performance specification for the BAC TSR-2 was issued in 1962. It was to be powered by two BSEL Olympus Mk 320 (BOl.22R) engines each rated at 19,610 lbf (87.2 kN) dry and 30,610 lbf (136.2 kN) with reheat at take-off. The engine, which was re-stressed for supersonic flight at sea level, and over Mach 2.0 at altitude, and featured much use of high-temperature alloys such as titanium and Nimonic, was a cutting edge derivative of the Olympus Mk 301 with a Solar-type afterburner.
The engine first ran in March 1961, soon achieving 33,000 lbf (150 kN), and was test flown in February 1962 in an underslung nacelle in the belly of Vulcan B1 XA894 and was demonstrated at the Farnborough Air Show in September. In December 1962 during a full power ground run at Filton, the LP shaft failed. The liberated turbine disc ruptured fuel tanks and the subsequent fire completely destroyed the Vulcan.
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Rolls-Royce Olympus variants
The Rolls-Royce Olympus turbojet engine was developed extensively throughout its production run, the many variants can be described as belonging to four main groups.
Initial non-afterburning variants were designed and produced by Bristol Aero Engines and Bristol Siddeley (BSEL) and powered the Avro Vulcan. These engines were further developed by Rolls-Royce Limited.
The first afterburning variant, the Bristol Siddeley Olympus Mk 320, powered the cancelled BAC TSR-2 strike aircraft. A further afterburning variant was the Rolls-Royce/Snecma Olympus 593, jointly developed to power Concorde in the 1960s.
The American Curtiss-Wright company tested a license-developed version known as the J67 and a turboprop designated TJ-38 Zephyr. Neither design was produced.
Further derivatives of the Olympus were produced for ship propulsion and land-based power generation.
Thrust given in foot-pounds (lbf) and kilonewtons (kN).
The performance specification for the BAC TSR-2 was issued in 1962. It was to be powered by two BSEL Olympus Mk 320 (BOl.22R) engines each rated at 19,610 lbf (87.2 kN) dry and 30,610 lbf (136.2 kN) with reheat at take-off. The engine, which was re-stressed for supersonic flight at sea level, and over Mach 2.0 at altitude, and featured much use of high-temperature alloys such as titanium and Nimonic, was a cutting edge derivative of the Olympus Mk 301 with a Solar-type afterburner.
The engine first ran in March 1961, soon achieving 33,000 lbf (150 kN), and was test flown in February 1962 in an underslung nacelle in the belly of Vulcan B1 XA894 and was demonstrated at the Farnborough Air Show in September. In December 1962 during a full power ground run at Filton, the LP shaft failed. The liberated turbine disc ruptured fuel tanks and the subsequent fire completely destroyed the Vulcan.