|Major applications||Boeing 707
Handley Page Victor
The Rolls-Royce RB.80 Conway was the first by-pass engine (or turbofan) in the world to enter service. Development started at Rolls-Royce in the 1940s, but it was used only briefly in the late 1950s and early 1960s before other turbofan designs were introduced that replaced it. The Conway powered versions of the Handley Page Victor, Vickers VC10, Boeing 707-420 and Douglas DC-8-40. The name "Conway" is the English spelling of the River Conwy, in Wales, in keeping with Rolls' use of river names for gas turbine engines.
In early jet engines the exhaust was much faster and hotter than it had to be (contrary to the ideal Froude efficiency) for efficient thrust; capturing some of that energy would improve the fuel economy of the engine. The turboprop is an obvious example, which uses a series of additional turbine stages to capture this energy to power a propeller. However, there is a tradeoff in propeller efficiency compared to forward speed, so while the turboprops are efficient engines, they are only efficient at speeds of up to 500 mph (800 km/h; 430 kn). This meant there was a sweet spot between the high efficiencies of the turboprop at low speeds and the jet at high speeds that was not being directly addressed. This spot, between about 450 mph (720 km/h; 390 kn) and 700 mph (1,100 km/h; 610 kn), was precisely where the vast majority of commercial jet aircraft spent most of their time.
The basic concept of bypass had been studied from the earliest days of jet engine design. Alan Arnold Griffith had proposed a number of different bypass engine designs as early as the 1930s while he and Hayne Constant were trying to get their axial-flow jet engines working at the Royal Aircraft Establishment. Frank Whittle's Power Jets also studied a number of bypass configurations. However, the need to get jet engines into service during the war meant this work had to be put aside in favour of the simpler turbojet designs with shorter introduction times. The ending of the war changed priorities dramatically and, by 1946, Rolls-Royce agreed that existing engines like the Rolls-Royce Avon were advanced enough that it was time to start work on new concepts like bypass.
In a bypass design some of the air from the compressor bypasses the hot core of the engine - the combustion chambers and turbine - and by being channelled around the outside of this section and from then out of the back of the engine where it surrounds the high velocity jet exhaust, is used to provide thrust directly. Due to not being accelerated by combustion in the hot section, the colder air emerges at the back of the engine at a lower velocity than the jet exhaust, one nearer to the aircraft's airspeed in relation to the surrounding atmosphere, thus improving the Froude efficiency. In addition to the reduced fuel consumption over that of a simple turbojet, a beneficial side effect is that the core of hot gas from the jet exhaust is surrounded by a tube of colder, slower moving air, that reduces noise. Rolls-Royce termed the design a Bypass Turbojet.
Griffith suggested building a purely experimental bypass design using parts of the Avon and another experimental jet engine, the AJ.25 Tweed. In April 1947, a 5,000-pound-force (22,000 N) design was proposed but over the next few months it was modified to evolve into a larger 9,250-pound-force (41,100 N) design in response to a need for a new engine to power the Mk.2 low-level version of the Vickers Valiant bomber. The go-ahead to start construction of this larger design was given in October, under the RB.80 name.
During development it was decided to further improve the basic design by adding another feature then becoming common, a "two spool" compressor arrangement. Earlier engines generally consisted of a series of compressor stages connected via a shaft to one or more turbine stages, with the burners between them arranged around the shaft. Although this arrangement is mechanically simple, it has the disadvantage of lowering the efficiency of the compressor. Compressor stages run at their maximum efficiency when spinning at a specific speed for any given input air pressure - in a perfect compressor each stage would run at a separate speed. The multi-spool design, first used on the Bristol Olympus turbojet, is a compromise, the compressor being separated into "spools" designed to operate closer to most efficient speed, driven by separate turbines via concentric shafts. Two- and three-spool designs are common; beyond that the mechanical complexity is too great.
The new version had a four-stage low-pressure compressor driven by a two-stage turbine and an eight stage high-pressure compressor driven by another two-stage turbine. Now known by the Ministry of Supply designation as the RCo.2, design work was completed in January 1950 and the first example ran for the first time in July 1952 at 10,000 pounds-force (44,000 N) thrust. By this time, the low-level Valiant Pathfinder had been abandoned and so the first example was also destined to be the last. Nevertheless, it proved the basic concept sound and "ran perfectly for the whole of its 133 hours life."
The work on the RCo.2 was soon put to good use. In October 1952, the Royal Air Force awarded a contract for the Vickers V-1000, a large jet-powered strategic transport that was intended to allow the V bomber force to be supported in the field through air supply only. Vickers also planned on developing a passenger version of the same basic design as the VC-7. The V-1000 design looked like an enlarged de Havilland Comet but from the Valiant it took the wing layout and added a compound sweep (a passing vogue in UK design). It also featured the Comet's wing-embedded engines, demanding an engine with a small cross-section, which limited the amount of bypass the engine could use. It nevertheless required higher power to support a 230,000 pounds (100,000 kg) gross weight, so Rolls responded with the larger RCo.5.
The new engine was similar to the RCo.2 in most ways, differing in details. The low-pressure compressor now had six stages and the high-pressure nine, driven by two and one stage turbines respectively. The first RCo.5 ran in July 1953 and passed an official type rating in August 1955 at 13,000 pounds-force (58,000 N). Construction of the prototype V-1000 was well underway at Vickers Armstrong's Wisley works in the summer of 1955 when the entire project was cancelled. Having second thoughts about the concept of basing the V-bombers away from the UK, the need for the V-1000 became questionable and it became an easy decision to drop the project.
The Conway was saved once again when it was selected to power the Handley Page Victor B.2 variant, replacing the Armstrong Siddeley Sapphire used by earlier models. For this role, Rolls-Royce designed an even larger model, the RCo.8 of 14,500 pounds-force (64,000 N), which ran for the first time in January 1956. However the RCo.8 was skipped over after receiving a request from Trans-Canada Airlines (TCA) to explore a Conway-powered Boeing 707 or Douglas DC-8, having interested both companies in the idea. Rolls-Royce responded by designing an even larger model of the Conway, the 16,500 pounds-force (73,000 N) RCo.10 and offering the similar military-rated RCo.11 for the Victor. The new engine differed from the RCo.8 in having a new "zeroth stage" at the front of the low-pressure compressor, further increasing cold airflow around the engine. The RCo.10 first flew in the modified prototype Avro Vulcan VX770 on 9 August 1957 only for the aircraft to be lost in a crash the following year. The RCo.11 was flown in the Victor on 20 February 1959.
Boeing had calculated that the Conway, even though it had limited bypass in keeping with its original in-wing mounting, would increase the range of the 707-420 by 8% compared to the otherwise identical 707-320 powered by the non-bypass Pratt & Whitney JT4A (J75). In May 1956, TCA ordered Conway-powered DC-8s, followed by additional orders from Alitalia and Canadian Pacific Air Lines, while the Conway-powered 707 was ordered by BOAC, Lufthansa, Varig, El Al and Air India. RCo.10's development was so smooth that after delivering a small number for testing, further deliveries switched to the 17,150-pound-force (76,300 N) RCo.12, which was designed, built and tested before the airframes had finished their testing. These models also featured a distinctive scalloped silencer and a thrust reverser that could provide up to 50% reverse thrust.
Although successful in this role, only 37 707s and 32 DC-8s were built with the Conway, due largely to the delivery of the first US-built bypass engines, particularly the Pratt & Whitney JT3D. Nevertheless, the Conway was successful on these designs and was the first commercial aero engine to be awarded clearance to operate for periods of up to 10,000 hours between major overhaul.
Rolls-Royce continued working on the Conway, delivering the RCo.15. This was similar to the earlier RCo.12 but had a larger zeroth-stage along with a larger engine housing to fit it. This improved cruise fuel consumption by 3% while at the same time increasing take-off thrust to 18,500 pounds-force (82,000 N). The designs were otherwise similar and RCo.12s could be re-built into RCo.15s during overhauls.
The final development of the Conway series was the RCo.42, designed specifically for the Vickers VC10. As the need for wing-embedded engines was long abandoned by this point, Rolls-Royce dramatically increased the zero-stage diameter to increase the bypass from about 25% to 60% and further increasing thrust to 20,250 pounds-force (90,100 N). First run in March 1961, it would be the most successful of all the Conways, powering all of the VC10 fleet, later models with the RCo.43. It remained in service until the retirement of the RAF's VC10s in 2013.
The RCo.12 Conway was an axial-flow turbofan with a low bypass ratio of about 25%. It had a seven-stage low-pressure compressor, the first six stages made of aluminium and the last of titanium. Behind this was the nine-stage high-pressure compressor, the first seven stages of titanium and the last two of steel. The bypass housing duct was also made of titanium. The bypass duct started after the seventh stage. The combustion area consisted of ten cannular flame cans. The high-pressure compressor was driven by a single-stage turbine using hollow air-cooled blades, which was followed by the two-stage turbine powering the low-pressure compressor. Accessories were arranged around the front of the engine, in order to minimise overall diameter.
The engine produced 17,150 pounds-force (76,300 N) for takeoff, weighed 4,500 pounds (2,000 kg) and had a specific fuel consumption of 0.712 at take-off thrust and 0.87 for cruise.
In November 1966 A French manufacturer of steam turbines and automobile superchargers, Société pour l’exploitation des appareils Rateau of La Courneuve, sued Rolls Royce in London for patent infringement, claiming that their 1939 patent for intake design had been copied in the Avon, Conway and Spey models. After a long and keenly argued hearing the court determined that the claim was "speculative", in that by 1939 no axial-flow aircraft jet engine had been built and that earlier patents from Frank Whittle and others had already considered the design of the intakes.
Engines on display
- A preserved Rolls-Royce Conway engine is on public display at the Royal Air Force Museum Cosford.
- Farnborough Air Sciences Trust museum, Farnborough, UK.
- In the storage wing of the Canada Aviation and Space Museum in Ottawa, Canada.
- On the front lawn of Lockheed Martin Commercial Engines Solutions in St-Laurent, QC, Canada. (Former Air Canada Building No.1)
- A sectioned Conway is displayed as part of a stack of jet engines at the National Museum of Flight at East Fortune in Scotland.
- A sectioned Conway may also be found at the Brooklands Museum, Weybridge, UK.
- Type: Turbofan
- Length: 134.21 in (3,409 mm)
- Diameter: 37.6 in (960 mm)
- Dry weight: 4,500 lb (2,000 kg)
- Compressor: axial flow; 7-stage LP, 9-stage HP
- Combustors: cannular
- Turbine: axial flow; 1-stage HP, 2-stage LP
- Maximum thrust: 17,150 lb (76.3 kN)
- Bypass ratio: 0.25
- Specific fuel consumption: 0.87
- Power-to-weight ratio:
- Related lists
- Kay, pp.113
- Kay, pp.114
- Rolls-Royce, a century of innovation
- "R-R Conway 1". www.enginehistory.org. Retrieved 2017-01-21.
- "Rateau v. Rolls-Royce—The Judgment". Flight International: 684. 4 May 1967.
- Pearson, Harry (1989). Rolls-Royce and the Rateau patents. Derby: Rolls-Royce Heritage Trust. ISBN 0951171089.
- Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. ISBN 0-7509-4479-X.
- Kay, Antony, Turbojet, History and Development 1930–1960, Vol 1, Great Britain and Germany, Crowood Press, 2007. ISBN 978-1-86126-912-6
|Wikimedia Commons has media related to Rolls-Royce Conway.|
- Rolls-Royce Conway By-pass Turbo Jets a 1959 Flight advertisement for the Conway
- Conway - The Evolution of the First Rolls-Royce By-pass Turbojet a 1960 Flight article on the Conway
|This aircraft engine article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them.|