You are here: Division TME Research groups Thermotech Thermotechnical Institute Jet Engines

Jet Engines

We have three types of jet engines:

The Whittle W2/700 Jet Engine

History

This engine was acquired by the Thermotechnisch Institute in May, 1947. The engine was given to us by the National Gas Turbine Establishment of England and the company Power Jets Ltd. through direct contacts with their directors Sir Dr. H. Roxbee Cox and M.W.E.P. Johnson, respectively, who both visited the laboratory at that time. Professor Albert Coppens (1885-1910-1957-1966), the director of the Institute at that time, used to work for FN for one year prior to his nomination as a faculty member in Leuven in 1910. He was apparently the first to obtain a jet engine from England in Western Europe, and is kindly remembered by the university for this achievement.

whittle.jpgwhittle_W2700_techdraw.gif

The drawings for this engine stem from Power Jets (Res.&Dev.) Ltd., Whetstone, Leicester, England. Who made the engine is not known for sure. The design dates back to January 1945 and testing of the engine was performed in November 1945. The engine has most probably never flown. Instead it was shipped to Belgium and installed in the laboratories in 1947, when the first lab sessions were given.

When the first lab session was given to the engineering students in the Fall of 1947, the news was all over town: A brand new technology was introduced on Campus. There was a lot of exitement and every one was fascinated by this new and promising technology. Sadly, today, all rotating equipment manufacturers have disappeared from Belgium.

The engine, of which only a few are still in existence today, was used in laboratory engine tests by engineering students untill 1956. That year the engine was put out of service, and the Rolls Royce Derwent engine was installed. The Whittle engine delivered about 700 kg of thrust. Through the internet, I have learned that Cranfield University in England also has a running engine (see figure below) in store. For more information on early jet engines, consult the Jet Genesis web page. For more information on Frank Whittle, consult The Frank Whittle Tribute Page at Cambridge University.

cranfield_whittle.jpg

Specifications

Static thrust700kg
Compressor: double-sided single stage centrifugal
Turbine: single stage axial
Combustion chambers: 10 can-type reverse flow

Table: Technical specifications

The Rolls Royce Derwent 8 Jet Engine

History

This engine was built by the company FN Herstal under licence from Rolls Royce from 1950 until about 1956. The engine was meant to power Gloster Meteor F.8 airplanes for Belgium and Holland. The story goes that 1001 engines were built by FN, and the last one was for us. The director of the Thermotechnisch Instituut at that time, professor A. Coppens, had worked for FN prior to becoming a faculty member at the university. He is kindly remembered for acquiring our two jet engines for the institute.

The engine is still used for teaching laboratory sessions. This is an all time favorite of the students, as the noise produced by the jet engine is tremendous.

rr.jpg

 

You can take a look at the engine's interior on the photograph below, taken at the Duxford Airfield Exhibits.

rr_derwent_cutaway.jpg

 

Specifications

Static thrust1500kg
Maximum rotational speed14500rpm
Power5000 (3680)HP (kW)
Compressor: double-sided single stage centrifugal
Turbine: single stage axial
Combustion chambers: 9 can-type normal flow

Table: Technical specifications

The Orenda 9 Jet Engine

History

This 1954 Canadian built Orenda 9 jet engine was used as a powerplant for the Canadair Sabre and Avro CF-100 Mark 4A 'Canuck'. The engine now exhibited in our collection was saved from a Belgian scrapyard. This is the only engine in our collection that is not in working condition. The engine weighs about 1160 kg and produced a static thrust of 2948 kg.

orenda.jpg

 

Specifications

Static thrust2948kg
Maximum rotational speed15500rpm
Power10000 (7360)HP (kW)
Compressor: 10 stage axial (15000 kW)
Turbine: 2 stage axial (15000 kW)
Combustion chambers: 6 can-annular-type normal flow

Table: Technical specifications