Patent ID: 7637096

Claim:
A thermo acoustic pressure rise combustor comprising: an air inlet; an air outlet; a combustion chamber; and an associated fuel injector from which in use fuel is injected into the combustor chamber in pulses, the combustor chamber in use exhibiting a cyclical pressure fluctuation having a pressure rising portion and a pressure falling portion induced by deflagration of the fuel, the timing of the start of the pulse of fuel being in a phase relationship with the pressure rising portion, wherein the cyclical pressure fluctuation is sinusoidal, the pressure rising portion starting at the minima of the sinusoidal pressure fluctuation and extending to the maxima of the sinusoidal pressure fluctuation, the pressure falling portion starting at the maxima of the sinusoidal pressure fluctuation and extending to the minima of the sinusoidal pressure fluctuation, wherein the timing of the start of the pulse of fuel is phased from the minima by between 0 degrees and 210 degrees.