Rolls-Royce/SNECMA M45H
2 participants
aeronewsline :: Accueil :: Histoire :: Moteurs
Page 1 sur 1
Rolls-Royce/SNECMA M45H
L'histoire rapidement expliquée du M-45H du VFW 614 sur Wikipedia.en
[Vous devez être inscrit et connecté pour voir ce lien]
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
The [Vous devez être inscrit et connecté pour voir ce lien]/[Vous devez être inscrit et connecté pour voir ce lien] M45H was a medium [Vous devez être inscrit et connecté pour voir ce lien] turbofan produced specifically for the twin-engined [Vous devez être inscrit et connecté pour voir ce lien] aircraft in the early 1970s.
The design was started as a collaborative effort between Bristol Siddeley and SNECMA.[Vous devez être inscrit et connecté pour voir ce lien]
[Vous devez être inscrit et connecté pour voir ce lien]
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
The [Vous devez être inscrit et connecté pour voir ce lien]/[Vous devez être inscrit et connecté pour voir ce lien] M45H was a medium [Vous devez être inscrit et connecté pour voir ce lien] turbofan produced specifically for the twin-engined [Vous devez être inscrit et connecté pour voir ce lien] aircraft in the early 1970s.
The design was started as a collaborative effort between Bristol Siddeley and SNECMA.[Vous devez être inscrit et connecté pour voir ce lien]
Zitek- CLUB
- Messages : 1759
Re: Rolls-Royce/SNECMA M45H
Design and development
The single-stage fan, together with a five-stage LP compressor, was driven by a three-stage LP turbine, whilst the seven-stage HP compressor was driven by a single-stage, air-cooled, HP turbine.
An annular combustor and an unmixed exhaust, with a plug-type primary nozzle, were other design features.
The engine was developed at the time of the Rolls-Royce bankruptcy which resulted in delays in developing the engine.[Vous devez être inscrit et connecté pour voir ce lien]
The single-stage fan, together with a five-stage LP compressor, was driven by a three-stage LP turbine, whilst the seven-stage HP compressor was driven by a single-stage, air-cooled, HP turbine.
An annular combustor and an unmixed exhaust, with a plug-type primary nozzle, were other design features.
The engine was developed at the time of the Rolls-Royce bankruptcy which resulted in delays in developing the engine.[Vous devez être inscrit et connecté pour voir ce lien]
Zitek- CLUB
- Messages : 1759
Re: Rolls-Royce/SNECMA M45H
Variants
The M45SD-02 or RB.410 was a derivative of the M45H-01 turbofan, designed to demonstrate ultra-quiet engine technologies, needed for [Vous devez être inscrit et connecté pour voir ce lien] aircraft operating from city centre airports.
A geared, variable pitch, fan replaced the first stage of the low pressure (LP) compressor.
A modest fan pressure ratio, consistent with the high [Vous devez être inscrit et connecté pour voir ce lien], meant a low fan tip speed could be employed.
A low hot jet velocity was another major design feature.
In [Vous devez être inscrit et connecté pour voir ce lien], intake air entered the bypass duct, via a gap in the cold nozzle outer wall, and went through the fan, to be expelled through the intake.
A small proportion of the bypass duct air entered the IP compressor, via a special diverter valve, to sustain the gas generator.
Reverse thrust was obtained by the fan going through fine (rather than feather) pitch.
Engine testing took place in the mid 1970's.
The M45SD-02 or RB.410 was a derivative of the M45H-01 turbofan, designed to demonstrate ultra-quiet engine technologies, needed for [Vous devez être inscrit et connecté pour voir ce lien] aircraft operating from city centre airports.
A geared, variable pitch, fan replaced the first stage of the low pressure (LP) compressor.
A modest fan pressure ratio, consistent with the high [Vous devez être inscrit et connecté pour voir ce lien], meant a low fan tip speed could be employed.
A low hot jet velocity was another major design feature.
In [Vous devez être inscrit et connecté pour voir ce lien], intake air entered the bypass duct, via a gap in the cold nozzle outer wall, and went through the fan, to be expelled through the intake.
A small proportion of the bypass duct air entered the IP compressor, via a special diverter valve, to sustain the gas generator.
Reverse thrust was obtained by the fan going through fine (rather than feather) pitch.
Engine testing took place in the mid 1970's.
Zitek- CLUB
- Messages : 1759
Re: Rolls-Royce/SNECMA M45H
Components
- Compressor: 5-stage intermediate pressure and 7-stage high-pressure [Vous devez être inscrit et connecté pour voir ce lien] with a single-stage fan
- Bypass ratio: 3:1
- [Vous devez être inscrit et connecté pour voir ce lien]: Annular
- [Vous devez être inscrit et connecté pour voir ce lien]: 3-stage low pressure and single-stage high pressure turbines
Zitek- CLUB
- Messages : 1759
aeronewsline :: Accueil :: Histoire :: Moteurs
Page 1 sur 1
Permission de ce forum:
Vous ne pouvez pas répondre aux sujets dans ce forum
|
|