Bristol Aero Engines. Rolls Royce Olympus
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Bristol Aero Engines. Rolls Royce Olympus
Le court chapitre consacré au turboréacteur Olympus de Bristol, puis Rolls Royce, sur Wikipedia de langue anglaise
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The Rolls-Royce Olympus (originally the Bristol B.E.10 Olympus) was one of the world's first two-spool [Vous devez être inscrit et connecté pour voir ce lien] aircraft engines, originally developed and produced by [Vous devez être inscrit et connecté pour voir ce lien].
First running in 1950, its initial use was as the powerplant of the [Vous devez être inscrit et connecté pour voir ce lien].
The design was further developed for [Vous devez être inscrit et connecté pour voir ce lien] performance as part of the [Vous devez être inscrit et connecté pour voir ce lien] programme.
Later it saw production as the [Vous devez être inscrit et connecté pour voir ce lien], the powerplant for [Vous devez être inscrit et connecté pour voir ce lien].
Versions of the engine were licenced to [Vous devez être inscrit et connecté pour voir ce lien] in the USA as the TJ-32 or J67 (military designation) and the TJ-38 'Zephyr'.
The Olympus was also developed with success as a marine and industrial [Vous devez être inscrit et connecté pour voir ce lien].
Bristol Aero Engines (formerly Bristol Engine Company) merged with [Vous devez être inscrit et connecté pour voir ce lien] Motors in 1959 to form [Vous devez être inscrit et connecté pour voir ce lien] Engines Limited (BSEL) which in turn was taken over by [Vous devez être inscrit et connecté pour voir ce lien] in 1966.
As of 2011, the Olympus remains in service as both a marine and industrial gas turbine. It also powers the restored [Vous devez être inscrit et connecté pour voir ce lien].
[Vous devez être inscrit et connecté pour voir ce lien]
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The Rolls-Royce Olympus (originally the Bristol B.E.10 Olympus) was one of the world's first two-spool [Vous devez être inscrit et connecté pour voir ce lien] aircraft engines, originally developed and produced by [Vous devez être inscrit et connecté pour voir ce lien].
First running in 1950, its initial use was as the powerplant of the [Vous devez être inscrit et connecté pour voir ce lien].
The design was further developed for [Vous devez être inscrit et connecté pour voir ce lien] performance as part of the [Vous devez être inscrit et connecté pour voir ce lien] programme.
Later it saw production as the [Vous devez être inscrit et connecté pour voir ce lien], the powerplant for [Vous devez être inscrit et connecté pour voir ce lien].
Versions of the engine were licenced to [Vous devez être inscrit et connecté pour voir ce lien] in the USA as the TJ-32 or J67 (military designation) and the TJ-38 'Zephyr'.
The Olympus was also developed with success as a marine and industrial [Vous devez être inscrit et connecté pour voir ce lien].
Bristol Aero Engines (formerly Bristol Engine Company) merged with [Vous devez être inscrit et connecté pour voir ce lien] Motors in 1959 to form [Vous devez être inscrit et connecté pour voir ce lien] Engines Limited (BSEL) which in turn was taken over by [Vous devez être inscrit et connecté pour voir ce lien] in 1966.
As of 2011, the Olympus remains in service as both a marine and industrial gas turbine. It also powers the restored [Vous devez être inscrit et connecté pour voir ce lien].
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Re: Bristol Aero Engines. Rolls Royce Olympus
Background
At the end of World War II, the Bristol Engine Company’s major effort was the development of the [Vous devez être inscrit et connecté pour voir ce lien] and [Vous devez être inscrit et connecté pour voir ce lien] engines.
By the end of 1946, the company had only 10 hours experience of [Vous devez être inscrit et connecté pour voir ce lien] experience with a small experimental engine called the Phoebus which was the [Vous devez être inscrit et connecté pour voir ce lien] or core of the [Vous devez être inscrit et connecté pour voir ce lien] then in development.
In early 1947, the parent [Vous devez être inscrit et connecté pour voir ce lien] submitted a proposal for a medium-range bomber to the same specification B46/35 which led to the [Vous devez être inscrit et connecté pour voir ce lien] and [Vous devez être inscrit et connecté pour voir ce lien].
The Bristol design was the Type 172 and was to be powered by four or six Bristol engines of 9,000 lbf (40 kN) thrust.
The thrust required of the new engine, then designated B.E.10 (later Olympus), would initially be 9,000 lbf (40 kN) with growth potential to 12,000 lbf (53 kN).
The [Vous devez être inscrit et connecté pour voir ce lien] would be an unheard of 9:1.
To achieve this, the initial design used a low pressure (LP) [Vous devez être inscrit et connecté pour voir ce lien] and a high pressure (HP) [Vous devez être inscrit et connecté pour voir ce lien], each being driven by its own single-stage [Vous devez être inscrit et connecté pour voir ce lien].
This two-spool design made the compression more manageable, enabled faster acceleration, and reduced [Vous devez être inscrit et connecté pour voir ce lien].
The design was progressively modified and the centrifugal HP compressor was replaced by an axial HP compressor.
This reduced the diameter of the new engine to the design specification of 40 in (100 cm).
The Bristol Type 172 was cancelled though development continued for the Avro Vulcan and other projects.
At the end of World War II, the Bristol Engine Company’s major effort was the development of the [Vous devez être inscrit et connecté pour voir ce lien] and [Vous devez être inscrit et connecté pour voir ce lien] engines.
By the end of 1946, the company had only 10 hours experience of [Vous devez être inscrit et connecté pour voir ce lien] experience with a small experimental engine called the Phoebus which was the [Vous devez être inscrit et connecté pour voir ce lien] or core of the [Vous devez être inscrit et connecté pour voir ce lien] then in development.
In early 1947, the parent [Vous devez être inscrit et connecté pour voir ce lien] submitted a proposal for a medium-range bomber to the same specification B46/35 which led to the [Vous devez être inscrit et connecté pour voir ce lien] and [Vous devez être inscrit et connecté pour voir ce lien].
The Bristol design was the Type 172 and was to be powered by four or six Bristol engines of 9,000 lbf (40 kN) thrust.
The thrust required of the new engine, then designated B.E.10 (later Olympus), would initially be 9,000 lbf (40 kN) with growth potential to 12,000 lbf (53 kN).
The [Vous devez être inscrit et connecté pour voir ce lien] would be an unheard of 9:1.
To achieve this, the initial design used a low pressure (LP) [Vous devez être inscrit et connecté pour voir ce lien] and a high pressure (HP) [Vous devez être inscrit et connecté pour voir ce lien], each being driven by its own single-stage [Vous devez être inscrit et connecté pour voir ce lien].
This two-spool design made the compression more manageable, enabled faster acceleration, and reduced [Vous devez être inscrit et connecté pour voir ce lien].
The design was progressively modified and the centrifugal HP compressor was replaced by an axial HP compressor.
This reduced the diameter of the new engine to the design specification of 40 in (100 cm).
The Bristol Type 172 was cancelled though development continued for the Avro Vulcan and other projects.
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Re: Bristol Aero Engines. Rolls Royce Olympus
Initial Development
The first engine, its development designation being BOl.1 (Bristol Olympus 1), had six LP compressor stages and eight HP stages, each driven by a single-stage turbine.
The combustion system was novel in that ten connected flame tubes were housed within a [Vous devez être inscrit et connecté pour voir ce lien] system: a hybrid of separate flame [Vous devez être inscrit et connecté pour voir ce lien] and a true [Vous devez être inscrit et connecté pour voir ce lien] system.
Separate combustion cans would have exceeded the diameter beyond the design limit and a true annular system was considered too advanced.
In 1950, Dr (later Sir) [Vous devez être inscrit et connecté pour voir ce lien] was appointed as Chief Engineer of Bristol Aero Engines.
The BOl.1 first ran in May 1950 and produced 9,140 lbf (40.7 kN) thrust.
The next development was the BOl.1/2 which produced 9,500 lbf (42 kN) thrust in December 1950.
Examples of the similar BOl.1/2A were constructed for US manufacturer Curtiss-Wright which had bought a
licence for developing the engine as the TJ-32 or J67.
The somewhat revised BOl.1/2B, ran in December 1951 producing 9,750 lbf (43.4 kN) thrust.
The engine was by now ready for air testing and the first flight engines, designated Olympus Mk 99, were fitted into a [Vous devez être inscrit et connecté pour voir ce lien] WD952 which first flew with these engines derated to 8,000 lbf (36 kN) thrust in August 1952.
In May 1953, this aircraft reached a [Vous devez être inscrit et connecté pour voir ce lien] of 63,668 ft (19,406 m).
(Fitted with more powerful Mk 102 engines, the Canberra increased the record to 65,876 ft (20,079 m) in August 1955.)
The first engine, its development designation being BOl.1 (Bristol Olympus 1), had six LP compressor stages and eight HP stages, each driven by a single-stage turbine.
The combustion system was novel in that ten connected flame tubes were housed within a [Vous devez être inscrit et connecté pour voir ce lien] system: a hybrid of separate flame [Vous devez être inscrit et connecté pour voir ce lien] and a true [Vous devez être inscrit et connecté pour voir ce lien] system.
Separate combustion cans would have exceeded the diameter beyond the design limit and a true annular system was considered too advanced.
In 1950, Dr (later Sir) [Vous devez être inscrit et connecté pour voir ce lien] was appointed as Chief Engineer of Bristol Aero Engines.
The BOl.1 first ran in May 1950 and produced 9,140 lbf (40.7 kN) thrust.
The next development was the BOl.1/2 which produced 9,500 lbf (42 kN) thrust in December 1950.
Examples of the similar BOl.1/2A were constructed for US manufacturer Curtiss-Wright which had bought a
licence for developing the engine as the TJ-32 or J67.
The somewhat revised BOl.1/2B, ran in December 1951 producing 9,750 lbf (43.4 kN) thrust.
The engine was by now ready for air testing and the first flight engines, designated Olympus Mk 99, were fitted into a [Vous devez être inscrit et connecté pour voir ce lien] WD952 which first flew with these engines derated to 8,000 lbf (36 kN) thrust in August 1952.
In May 1953, this aircraft reached a [Vous devez être inscrit et connecté pour voir ce lien] of 63,668 ft (19,406 m).
(Fitted with more powerful Mk 102 engines, the Canberra increased the record to 65,876 ft (20,079 m) in August 1955.)
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Re: Bristol Aero Engines. Rolls Royce Olympus
First-generation Engines
Olympus 100 series
These are service designations. Development designations are given in brackets.
Avro Vulcan B1 and B1A
Olympus 100 series
These are service designations. Development designations are given in brackets.
Avro Vulcan B1 and B1A
- Olympus Mk 100: (BOl.1/2B) Similar to Olympus Mk 99 rated at 9,250 lbf (41.1 kN) thrust for second Vulcan prototype VX777.First flew September 1953. VX777 was retrofitted with Mk 101 engines.
- Olympus Mk 101: (BOl.1/2C) Larger turbine, 11,000 lbf (49 kN) thrust for initial production Vulcan B1 aircraft. First flew (XA889) February 1955.
- Olympus Mk 102: (BOl.11) Additional zero stage on LP compressor, 12,000 lbf (53 kN) thrust for later production Vulcan B1 aircraft.[Vous devez être inscrit et connecté pour voir ce lien]
- Olympus Mk 104: (BOl.12) Designation for Olympus Mk 102 modified on overhaul with new turbine and burners, 13,000 lbf (58 kN) thrust initially, 13,500 lbf (60 kN) thrust on uprating, standard on Vulcan B1A.
- 'Olympus 106': Used to describe the development engine for the Olympus 200 (BOl.6). Possibly a corruption of BOl.6 (Olympus 6).
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Re: Bristol Aero Engines. Rolls Royce Olympus
Other developments
- Olympus 3: Of all the early initial developments, BOl.2 to BOl.5 (the BOl.5 was never built), perhaps the most significant was the BOl.3. Even before the Vulcan first flew, the Olympus 3 was being suggested as the definitive
powerplant for the aircraft. In the event, the 'original' Olympus was continuously developed for the Vulcan B1. The BOl.3 was described in 1957 as "a high-ended product intermediate between the Olympus 100 and 200 series."
- Olympus Mk 97: This early engine tested an early annular combustion chamber. It was test flown on Bristol's [Vous devez être inscrit et connecté pour voir ce lien] test bed WB493.[Vous devez être inscrit et connecté pour voir ce lien]
- Afterburning: As early as 1952, Bristols had considered the use of [Vous devez être inscrit et connecté pour voir ce lien], to augment the thrust of the Olympus. Initially, a system called Bristol Simplifed Reheat was devised which was tested on a [Vous devez être inscrit et connecté pour voir ce lien] V mounted in an [Vous devez être inscrit et connecté pour voir ce lien]. Later it was tested on an [Vous devez être inscrit et connecté pour voir ce lien] engine in Canada and on an Olympus Mk 100 in the Avro Ashton test bed.[Vous devez être inscrit et connecté pour voir ce lien] Fully variable reheat became possible after an agreement with the [Vous devez être inscrit et connecté pour voir ce lien] of San Diego which manufactured bench units for the Olympus Mks 101 and 102.[Vous devez être inscrit et connecté pour voir ce lien]
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Localisation : France USA
Re: Bristol Aero Engines. Rolls Royce Olympus
Second-generation Engines
The initial design of the second generation 'Olympus 6' began in 1952.
This was a major redesign with five LP and seven HP compressor stages and a canullar combustor with eight interconected flame tubes.
In spite of a much greater mass flow, the size and weight of the BOl.6 was little different to earlier models.
Rival manufacturers Rolls-Royce lobbied very hard to have its [Vous devez être inscrit et connecté pour voir ce lien] engine installed in the Vulcan B2 to achieve commonality with the Victor B2.
As a consequence, Bristols undertook to to complete development using company funds and peg the price to that of its fully government-funded rival.
The initial design of the second generation 'Olympus 6' began in 1952.
This was a major redesign with five LP and seven HP compressor stages and a canullar combustor with eight interconected flame tubes.
In spite of a much greater mass flow, the size and weight of the BOl.6 was little different to earlier models.
Rival manufacturers Rolls-Royce lobbied very hard to have its [Vous devez être inscrit et connecté pour voir ce lien] engine installed in the Vulcan B2 to achieve commonality with the Victor B2.
As a consequence, Bristols undertook to to complete development using company funds and peg the price to that of its fully government-funded rival.
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- Messages : 848
Localisation : France USA
Re: Bristol Aero Engines. Rolls Royce Olympus
Olympus 200 series and Olympus Mk 301
Avro Vulcan B2
Avro Vulcan B2
- Olympus Mk 200: (BOl.6) 16,000 lbf (71 kN) thrust. First B2 (XH533) only.[Vous devez être inscrit et connecté pour voir ce lien]
- Olympus Mk 201: (BOl.7) Uprated Olympus Mk 200. 17,000 lbf (76 kN) thrust. Initial Vulcan B2 aircraft.[Vous devez être inscrit et connecté pour voir ce lien]
- Olympus Mk 202: Disputed. Either Olympus Mk 201 modified with rapid air starter,[Vous devez être inscrit et connecté pour voir ce lien] or Olympus Mk 201 with redesigned oil separator breathing system.[Vous devez être inscrit et connecté pour voir ce lien]
This was the definitive '200 series' engine fitted to Vulcans not fitted with the Mk 301. The restored Vulcan XH558 is fitted with Olympus Mk 202 engines. - 'Olympus Mk 203': Very occasional reference to this elusive mark of engine can be found in some official Air Publications relating to the Vulcan B2. It is also noted in a manufacturer's archived document dated circa 1960.
- Olympus Mk 301: (BOl.21) Additional zero stage on LP compressor. 20,000 lbf (89 kN) thrust.[Vous devez être inscrit et connecté pour voir ce lien] Later Vulcan B2 aircraft plus nine earlier aircraft[Vous devez être inscrit et connecté pour voir ce lien] retrofitted.[Vous devez être inscrit et connecté pour voir ce lien] Later derated to 18,000 lbf (80 kN) thrust.[Vous devez être inscrit et connecté pour voir ce lien] Restored to original rating for [Vous devez être inscrit et connecté pour voir ce lien].[Vous devez être inscrit et connecté pour voir ce lien]
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Localisation : France USA
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