Pulse jet engine having pressure sensor means for controlling fuel delivery into a combustion chamber

• US 7,637,096 B2
• Filed: 11/01/2005
• Issued: 12/29/2009
• Est. Priority Date: 11/25/2004
• Status: Expired due to Fees

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Miller, Robert J, Mason, Samuel A, Razzell, Anthony G, Taylor, Mark D
• Primary Examiner(s): Rodriguez; William H
• Application Number:
  US11/262,930
• Publication Number:
  US 20060112672A1
• Time in Patent Office: 1,519 Days
• Field of Search: 602/47, 60/393.8, 60/397.6
• US Class Current: 60/247
• CPC Class Codes: F02C 5/11 using valveless combustion chambers

Abstract

A pressure rise combustor is provided with fuel provided at intermittent periods. The fuel is pulsed at timings such that the phase lag between the addition of the fuel and a resultant pressure rise is minimized. The fuel is pulsed such that the unsteady addition of heat reinforces the amplitude of an unsteady pressure fluctuation.

Claims

1. 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.

2. A thermo acoustic pressure rise combustor according to claim 1, wherein the fuel is pulsed at the same frequency as the pressure fluctuations.

3. A thermo acoustic pressure rise combustor according to claim 1, wherein the timing of the start of the pulse of fuel is phased from the minima by between 90°

degrees and 210°

degrees.

4. A thermo acoustic pressure rise combustor according to claim 1, wherein the timing of the end of the pulse of fuel is phased from the timing of the start of the pulse of fuel by a phase angle of between 30°

degrees and 180°

degrees.

5. A thermo acoustic pressure rise combustor according to claim 1, wherein a phase delay of the timing of the start of fuel injection varies between cycles.

6. A thermo acoustic pressure rise combustor according to claim 1, further comprising pressure sensing means for sensing the pressure within the combustor chamber.

7. A thermo acoustic pressure rise combustor according to claim 6, wherein the pressure sensor is functionally connected to the fuel injector such that fuel is pulsed in response to a sensed pressure value within the combustor casing.