Patent GB-817936-A (GB)
Title: Vortex flow reaction chambers
Inventor: PROBERT RHYS PRICE
IPC: F23R3/58
Filed: 1956-08-03
Abstract: <PICT:0817936/III/1> <PICT:0817936/III/2> <PICT:0817936/III/3> A spiral vortex reaction chamber, i.e. a chamber in which chemical or physical reactions are effected between a first fluid and a second fluid or a finely-divided solid material, the first fluid being admitted in a tangential direction at the periphery and being caused to flow inwardly therein in a spiral vortex path to a central outlet on the axis of the chamber, particles of the second fluid being introduced into the first fluid, has a generally tangential peripheral fluid inlet and a central outlet in one of its side walls on the axis of the chamber, and a vane is provided projecting axially from at least one of the side walls into the interior of the chamber and extending wholly or partly along the spiral vortex path of the fluid flow in the chamber so as to reduce secondary flows.  The invention is shown applied to a gas turbine combustion chamber in Figs. 1 and 2 and comprises a peripheral wall 1a of spiral shape and side walls 1b, 1c, a tangential air inlet duct 3 being formed in the peripheral wall.  The side wall 1b is formed with a central axially-directed combustion gas outlet 4, and the side wall 1c is formed with an axially-directed tube 5 extending towards the outlet 4.  An outer casing 6 is disposed around the combustion chamber having a tangential inlet portion 7 disposed around the inlet 3 and an axially-directed outlet 9 disposed around the outlet 4.  Two flame tubes 10 are disposed within the inlet duct 3, each having a central fuel injector 11 surrounded by a set of swirl vanes 12, the two sets of swirl vanes being of opposite hand, as indicated by the arrows A in Fig. 2.  Air is supplied to the inlets 3, 7 from the compressor of the gas turbine plant.  Sets of spiral vanes 14 are secured to each side wall 1b, 1c of the combustion chamber, the vanes each extending continuously from adjacent the inlet 2 to adjacent the outlet 4 of the combustion chamber, and each vane extends axially about one-third of the axial dimension of the chamber.  Alternatively, the vanes 14 may each comprise a series of individual vanes spaced from one another along the spiral paths.  Air supplied to the jacket space between the combustion chamber and the outer casing discharges through the annulus 15 and through the tube 5 to mix with the combustion gases in the outlet 9.  In a second embodiment, in place of the vanes 14 shown in Figs. 1 and 2, a single set of short vanes is disposed within the combustion chamber around the chamber outlet 4, each vane extending along the full axial extent of the chamber and each vane extending partly along the spiral flow paths within the chamber; the vanes may be curved to conform to the shape of the spiral flow paths, or they may possibly be uncurved in view of their short extent in the direction of the spiral flow paths.  The vanes in this embodiment may be hollow to permit flow of cooling air therethrough and they may be airpermeable to allow sweat or effusion cooling.  In a third embodiment, Fig. 5, the combustion chamber is provided with three tangential inlets 24 each having flame tubes 10 as in Figs. 1 and 2 and a spiral vane 25 extends from adjacent each inlet 23 to adjacent the central outlet 26, on each side wall of the combustion chamber.  The side walls of the combustion chamber may be parallel, as shown, or frustoconical, so that the chamber is of greater axial extent at its centre than at its periphery. Specifications 639,468, 639,483, 653,289, [all in Group XII], 676,208, [Group XXVI], 676,263, 719,379, 719,380, and 797,532, [all in Group XII], are referred to.