Patent GB-1329944-A (GB)
Title: Mounting of fuel injection manifolds in combustion chambers
IPC: F02C7/22
Filed: 1972-01-17
Abstract: 1329944 Combustion equipment-mounting fuel injection manifolds SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D' AVIATION 17 Jan 1972 [19 Jan 1971] 2153/72 Heading F1J and F1L The invention relates to a method of mounting a fuel injection ring manifold within a combustion chamber whereby the manifold may move parallel to itself upon thermal expansion, two points on the manifold being maintained in an axial plane of the chamber which contains the point at which the fuel inlet pipe to the manifold passes through the wall of the combustion chamber. The invention is described with reference to a reheat combustion chamber of a gas turbine jet engine which comprises a jet pipe 1 within which is disposed a fuel injection manifold 2, a flame stabilizer ring 4 which is supported from the jet pipe, and a fuel impingement ring member 3. The ring manifold comprises a series of arcuate portions 9 interconnected by members 7 and 8, the portions 9 being formed with fuel injection orifices 2a through which fuel is directed in an upstream direction to impinge on the ring member 3 whereby it is atomized. Fuel is supplied to the manifold through an inlet 6 and an S-shaped duct 5 which terminates in a bi-furcated connection 5a. The duct 5 is connected to the inlet 6 by a connection 5b at the point A at the wall of the jet pipe 1. The fuel manifold member 8 at the point B is supported from the stabilizer ring 4 by a link 10 pivotally connected by a pin 10a to lugs 11 secured to the stabilizer ring and by pin 10b to lugs 8a of the member 8, the pins extending tangentially of the fuel manifold and stabilizer ring. The impingement member 3 is also supported from the member 8 by means of a link pivotally connected by pin 21a to lugs 8b of the member 8 and by pin 21b to angle members 22 secured to the inner surface of the impingement member which is of channel section. The link passes through an opening in the base of the impingement member. The member 7 of the manifold at the point C is connected to the stabilizer ring 4 by means of a link 12 pivotally connected to lugs 11a on the stabilizer ring by means of pin 12a and to lugs 7a of the manifold member 7 by pin 12b, the pins being disposed tangentially of the ring manifold and stabilizer ring. The lugs 11a are spaced so as to permit mounting on the pivot pin 12a of a link 4a by which the stabilizer ring is supported from the jet pipe. The members 8 of the ring manifold at the points D, E, F, G, H, I, J, K are connected to the stabilizer ring by means of links 16. Each link is pivotally connected to the stabilizer ring 4 by a universal coupling comprising a pin 16a which extends through a cylindrical plug 17 rotatably mounted in lugs 19 secured to the stabilizer ring, the plug being formed with an opening 17a to receive the end 16c of the link. The other end of the link is similarly connected to lugs 8a of the manifold member 8 by means of a pin 16b and cylindrical plug 18 formed with an opening 18a to receive the end 16d of the link. The member 8 is also connected at the upstream side to the impingement member 3 by means of link 21 pivotally connected by pin 21a to the lugs 8b on the member 8 and by pin 21b to angle members 22 secured to the inner surface of the impingement member, the link passing through opening 20 in the base of the impingement member.