Patent GB-1058068-A (GB)
Title: Improvements in gas turbine engines
Inventor: MOORE ALAN
IPC: F01D9/02
Filed: 1963-12-16
Abstract: 1,058,068. Gas turbine engines. BRISTOL SIDDELEY ENGINES Ltd. Dec.14, 1964 [Dec. 16, 1963], No. 49610/63. Headings F1G and F1T. A gas turbine engine comprises a compressor section 11, 12, a combustion section 13 which includes a flame tube assembly disposed within an annular chamber defined by inner and outer air casing walls, and a turbine section 14 having a cooling air passage system. An air cooler 21 is disposed around the rearward portion of the combustion section outer casing or around the forward part of the turbine section or around both, air flowing from the annular chamber of the combustion section to the air cooler where it is cooled by a flow of coolant, the cooled air then passing to the cooling passage system of the turbine. As shown in Fig. 3, the combustion section comprises an annular chamber 19 defined between inner and outer air casing walls 17, 18, a series of tubular flame tubes 20 being disposed within the chamber 19. The air cooler 21 is disposed around the outer wall 18 and comprises a series of axially-extending tubes across which the hot air flows circumferentially being cooled by cooler air flowing axially through the tubes. Hot air from within the annular chamber 19 of the combustion section passes radially outwardly through openings 22 in the outer wall 18 then flows circumferentially through the air cooler to the spaces indicated at 23. A portion of this cooled air then flows radially inwardly through groups of tubes 24 extending between adjacent flame tubes 20 to the space 25 within the inner air casing wall 17. From space 25 the cooled air passes to the cooling passage system of the turbine section as shown in Figs. 5 and 6. A further portion of cooled air from the spaces 23 passes rearwardly to a chamber 49 from which it passes to the cooling passage system of the turbine. The air cooler 21 is cooled by means of air taken from adjacent the engine intake and passed through four ducts 30 to an annular header 31 from which it passes through the axial tubes of the air cooler. The cooling air finally passes through duct 32 and outlet 33. The cooling air from space 25 passes into a space between the turbine rotor disc 36 and a disc 35 secured to the upstream side thereof and after flowing through passages 39 in the turbine rotor blades 40 discharges into the working fluid passage 38. Cooling air from the chamber 49 passes through ducts 48 to a manifold 47 then passing radially inwardly through the nozzle guide vanes 45 to a manifold 51 from which the air flows radially outwardly through the vanes 45 and discharges from the trailing edges thereof into the working fluid passage. Air from the chamber 49 also passes into a manifold 57 from which it passes radially inwardly through the hollow stator blades 54 to manifold 55 from which it discharges through openings 58 on to the downstream face of the turbine rotor disc finally discharging into the working fluid passage 38. In the case of combustion equipment having an annular flame tube, the tube assemblies 24 would not be provided, the cooling air being conveyed radially inwardly to the central space 25 through the inlet nozzle guide vanes 45.