Rolls-Royce RB401: Difference between revisions
Start cleanup |
Add infobox |
||
| Line 1: | Line 1: | ||
{{Cleanup|date=January 2007}} |
{{Cleanup|date=January 2007}} |
||
<!-- This article is a part of [[Wikipedia:WikiProject Aircraft]]. Please see [[Wikipedia:WikiProject Aircraft/page content]] for recommended layout. --> |
|||
{{seealso|Rolls-Royce Tay (turbojet)}} |
|||
{|{{Infobox Aircraft Begin |
|||
|name= RB.401 |
|||
|image= |
|||
|caption= |
|||
}}{{Infobox Aircraft Engine |
|||
|type=[[Turbofan]] |
|||
|manufacturer=[[Rolls-Royce plc|Rolls-Royce]] |
|||
|first run={{avyear|1984}} |
|||
|major applications= |
|||
|number built = |
|||
|program cost = |
|||
|unit cost = |
|||
|developed from = |
|||
|developed into = |
|||
|variants with their own articles = |
|||
}} |
|||
| ⚫ | The ''' |
||
|} |
|||
| ⚫ | The '''Rools-Royce RB.401''' was a business jet engine which [[Rolls-Royce plc|Rolls-Royce]] started to develop in the mid-1970s. RB401-06 prototype engines were already being manufactured when a decision to develop the higher thrust RB401-07 was taken. Although ground testing of both the -06 and -07 continued into the early 1980s, a lack of funds caused the project to be cancelled. |
||
==Design and development== |
==Design and development== |
||
Revision as of 23:30, 24 July 2009
 |
| RB.401 | |
|---|---|
| Type | Turbofan |
| Manufacturer | Rolls-Royce |
| First run | Template:Avyear |
The Rools-Royce RB.401 was a business jet engine which Rolls-Royce started to develop in the mid-1970s. RB401-06 prototype engines were already being manufactured when a decision to develop the higher thrust RB401-07 was taken. Although ground testing of both the -06 and -07 continued into the early 1980s, a lack of funds caused the project to be cancelled.
Design and development
Although the basic configurations of both engines were almost identical, the -07 variant had a larger fan diameter. The -06 version HP compressor was based on the 8 stage version of RC34B research compressor, unscaled, whereas the -07 was a scaled-up unit. A single stage fan, driven by 2 stage LP turbine, supercharged the HP compressor which was driven by the single stage transonic HP turbine. The combustor was annular and the co-annular exhaust featured a lightweight target type thrust reverser.
Specifications
Leading particulars for -07 variant were as follows:
Fan Diameter: 32.4 in
Take-off Thrust(Sea Level Static): 5,540 lbf, flat-rated to ISA+15C
Cruise Thrust: 1128lbf (Mach 0.7, 40,000 ft, ISA+10C)
Bypass Ratio: ~4
Overall Pressure Ratio: ~20:1
References
 |
This aircraft article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them. |
| This article about aircraft engines is a stub. You can help Wikipedia by expanding it. |