| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To further improve engine efficiency by reducing cooling pressurized air extracted from a compressor. <P>SOLUTION: A gas turbine engine 10 comprises a multistage axial compressor 18, an annular combustor 20 generating combustion gas 38 by mixing fuel 36 with the pressurized air 34 from the compressor 18, and a high pressure (HP) turbine 22 including a row of HP turbine blades 44 having dovetails installed in corresponding dovetail slots 52 in the perimeter of a supporting HP rotor disk 46 joined to compressor blades 1 to 7. The HP disk 46 includes a web 60 having a front face 50 and extending inwardly from the perimeter, and a front seal plate 56 extending in the radial direction along the front face 50 and defining an annular manifold 58 in flow communication with the dovetail slot 52, and has an interstage cooling circuit 48 joined in flow communication from intermediate stages 3 and 5 of the compressor 18 to the disk front face 50 and for channeling interstage breed cooling air 34b to the disk front face 50. <P>COPYRIGHT: (C)2008,JPO&INPIT</p> |
