Phoenix 30.3 & MK4
Specifications
| Diameter: | 111mm |  |
| Length: | 250mm | |
| Thrust: | 25 lbs | |
| Max revs: | 115,000 rpm | |
| Temp: | 580 deg C | |
| Weight: | 4.2 lbs | |
| Lubrication: | Kero / 2cycle oil (2 %). |
Historic information
The 30.3 prototype first ran in
June 1998. It was visualised as a low cost alternative to the AMT
Pegasus (it actually turned out 1 lb lighter). The Mk4 upgrade came
along in November 2000. Basically the same engine but with larger
bearings, better combustor and intake. Designed and developed by
Phillip Heward.
Design
This engine makes an important contribution to the stable of home
built designs. Phil Heward the designer has had considerable success over
the years with his engines and has concentrated on the use of both the
compressor and the turbine from a turbo charger. (The name comes
from the 3rd development of his 30th engine design since 1983 when he
began experimenting with turbine engines). This has the advantage that the 2 parts are a matched pair but the disadvantage
that the turbine is heavier than an axial turbine wheel. As a result the
engine is slightly heavier than the alternative designs of similar thrust. Phil has been able to
demonstrate that his last design was able to run for extended periods of
time and had introduced some welcome reliability into these engines.
Drawings and all parts for the latest version of this design are available
from Phil.
Below is a picture of a recumbent bike that was seen at many shows with the old design Phoenix strapped to it demonstrating the reliability of the engine!
Phil has completely redesigned the engine with the aim of reducing the case size to the now standard 111mm dia. This will make retrofitting the engine into a plane an easier task. This redesign has been a considerable achievement as it has meant a complete redesign of the combustion chamber amongst other things.
The engine produces a lot of thrust at relatively low rpm (20 lbs at 105,000 rpm). When flying the engine will not be highly stressed unless in a really large plane and then only at takeoff. The prototype is running at the design temperature of 550C.
Materials
The engine is made from the usual materials. The compressor is a
75mm GARRETT T04E. The outer case is TIG or Spot-welded 304
Stainless steel. The intake is spun alluminium made from two layers for
extra strength. The front shaft is from EN24T and is screwed onto the
existing turbocharger shaft. The NGV blades are made from Inconel 600 and
welded into 316 Stainless inner and outer rings. The combustion chamber is
made from two spun inner halves and an outer liner, with Inconel 800 "D
stick" burners.
Compressor
Turbine wheel
Bearings
Plans
There is no current information on sources for parts.