Turbojet Trainer With Reheat

Product Description

Description:

A self-contained, fully instrumented, educational singleshaft gas turbine with reheat. Powered by kerosene, the experimental abilitiesof this high-quality apparatus enable comprehensive practical investigationsinto the principles, and performance of single-shaft gas turbines with reheat.This product helps students to understand the use of this ‘engine’ withadditional exhaust nozzle control, on practical applications such as jetaircraft. A steel frame holds a gas generator, combustion chamber, oil and fueltanks, pumps, ancillaries and guards. Above these is an instrumentation andcontrol panel with schematic diagram. The clearly labelled control panel withmimic diagram includes the instrument displays, controls and warning lights.Air passes into an air box, through a calibrated nozzle into a compressor, theninto the combustion chamber. A pump transfers fuel from the fuel tank to spraythrough a special nozzle into the combustion chamber. A high-energy sparkignites the air and fuel mixture that flows to a radial flow turbine, then tothe reheat section. This increases the temperature and velocity of the gas. Itthen passes through a variable area propelling nozzle. The exhaust gases thendischarge to a suitable exhaust system. The combustion chamber gives excellentcombustion, low pressure loss and good flame stability over a wide range ofconditions. A fuel flow control valve on the instrumentation and control panelregulates the turbine speed. This design reduces the possibility of over speed.A separate control adjusts the fuel flow to the reheat section. A secondhigh-energy spark in the reheat section ignites the reheat fuel. This creates asecondary burn using some of the remaining oxygen in the hot exhaust gasesleaving the turbine.

Specification:

Nett dimensions andweight: 1385 mm (wide) x 1200 mm (depth) x 1721 mm (height) and 260kg

Approximate packeddimensions and weight: 3.8 m3 and 450 kg

Fuel: High-qualityaviation kerosene: ASTM D 1655 Jet A or similar

Gas generatorturbine:

• Maximum continuous speed: Approximately 100000 rev.min–1
  
• Approximate maximum thrust:50 N
  

Instruments:

• Shaft speed
  
• Pressures
  
• Temperatures
  
• Fuel flow
  
• Thrust
  
• Nozzle area
  
• Fuel flow level and pressure
  
• Oil temperature and pressure
  
• Filter condition
  
• Total hours run
  

Automatic shut downconditions:

• Ignition failure
  
• Incorrect turbine speed
  
• Oil pressure failure
  
• Water supply failure
  
• Incorrect temperatures
  

Exhaust emissions(typical):

• Carbon dioxide (CO2): 1.8 – 2.9%
  
• Carbon monoxide, (CO): 240 – 900 ppm
  
• Nitric oxide, (NO): 11 – 26 ppm
  
• Nitrogen dioxide, (NO2): 0 – 1 ppm
  
• Combination of NO and NO2, (NOX): 12 – 26 ppm
  
• Sulphur dioxide, (SO2): 5 – 6 ppm