| 摘要 |
<p>1,024,957. Air-jacketed combustion chambers. GENERAL ELECTRIC CO. June 17, 1964 [June 19, 1963], No. 25049/64. Headings F1G and F1L. Gas turbine engine combustion apparatus includes an air-jacketed combustion chamber bounded by a wall 17, Fig. 1, comprising joined sections having apertures 19 and being spaced from each other by strips 27 which define air conduits 28, and by an end wall comprising an inner cone 22 provided with radial louvres 24, and an outer frusto-conical member 23 provided with off-radial louvres 26. Air from a compressor flows through the air jacket, 12 and 21, is introduced into the combustion chamber through the louvres 24 and 26 tangentially to the inner cone 22 and the frusto-conical member 23 respectively and is mixed with fuel from injector 25. The off-radial disposition of louvres 26 ensures that the air flowing therethrough has a radially inward component of velocity sufficient to prevent the fuel-air mixture impinging on the combustion chamber walls prior to ignition. The combustion products are diluted with air flowing through the perforations 19 and the conduits 28 and the resultant mixture flows around a hollow cone 30 to the turbine 13. Hollow guide blades 31 support the cone 30 within a cylindrical extension 11 of the wall 17. Air from the air jacket 12 flows through the guide blades into the interior of the cone 30 to pass through an aperture 32 in the cone apex. A domed cap 33 diverts this air back over the outer surface of the cone towards the roots of the turbine blades 29 which are thus cooled. Additional openings 36 and 40 may be provided in the cone 30 and cap 40 respectively and the closed larger end of cone 30 may have an aperture 41 for supplying cooling air to the rotor or for oil sump seal pressurization.</p> |
