Patent GB-942044-A (GB)
Title: Ramjet engine
Inventor: GARDINER TERENCE EDWARD GOUVEN
IPC: F02K7/10
Filed: 1961-04-28
Abstract: 942,044. Ramjet engines; combustion chambers. BRISTOL SIDDELEY ENGINES Ltd. April 26, 1962 [April 28, 1961], No. 15499/61. Headings F1J and F1L. The invention relates to a ramjet engine comprising an approximately cylindrical outer casing having an intake lip at its forward end, and an inner wall forming the outer perphery of an air flow duct, the inner wall extending rearwardly from the intake lip and departing at a small angle from the outer casing. One embodiment of the invention is shown in Figs. 1A and 1B, the outer casing comprising a forward portion 12, an intermediate portion 11 and a rearward portion 10, the forwardmost part of the portion 12 being formed as an air intake lip 13 and an inner wall 14 being disposed within the forward portion 12 to define the outer wall of an air flow duct. The inner wall is disposed at a small angle to the outer casing up to the transverse plane 25 and then diverges to meet the outer casing portion 10 at 21 so forming an enlargement in the air duct. A centre body 16 is disposed within the air duct, the centre body having pointed upstream and downstream ends, and being supported within the air duct by means of vanes 15. An annular flame tube structure is disposed within the rearward casing portion and defines an annular pilot combustion zone 30 and an annular main combustion zone 63. The pilot combustion zone 30 is formed by outer and inner walls 31 and 32 and by an end wall 34 through which project pilot fuel injectors 35 and which is formed with inlet openings for passage of air from the chamber 36 which itself receives air from the main air duct through inlet 37. A pair of electrically-fired pyrotechnic igniter devices 50, 51 project into the pilot combustion zone. The outer wall of the annular main combustion zone 63 is formed by a series of overlapping ring members 60 forming an extension of the wall 31 while the inner wall thereof is formed by a series of strip members 67 extending from the inner wall 32 to a conical shaped member 68 disposed with its concave surface facing dowstream. A series of V-section flame-holder rings 69 is disposed around the strips 67, the spaces between the strips allowing outward flow of fuel and air mixture from the duct 33 into the annular combustion space 63. Fuel is supplied into the air flowing in the duct 33 by means of a series of injectors 42 connected to ring manifold 41 which is connected to a further manifold 44 by two supply pipes 43. The pilot fuel manifold 48 is connected to the fuel inlet socket 46 by a supply pipe 47. A portion of the air flowing in the duct 33 passes through a passage 38 and flows in the space between the outer wall of the flame tube and the outer casing for cooling purposes, the air passing into the flame tube through openings 62 in the ring members 60. A convergent-divergent nozzle 72 is secured at the downstream end of the casing portion 10 and comprises a wall part 75, which lies close to the outer surface of the nozzle wall 74 so as to define a passage for flow of cooling air which is collected by the flange 76 and flows into the passage through openings 77. In a second embodiment, Fig. 2, the wall 102 of the air flow duct again diverges at 106 but not to the outer wall, the wall 102 being extended as shown at 110 parallel to the outer wall 108. The annular pilot combustion space is shown at 118 and fuel is supplied into the pilot combustion space and into the main air duct 112 by means of injection devices 120, the mixture of fuel and air passing into the annular pilot and main combustion spaces from the duct 112 through the openings 136, 137, 138 and 140 as in the first embodiment. Specification 841,872 is referred to.