Appeal No. 2002-0538 Application 09/220,468 stator vanes. The engine also comprises a thrust modulator which operates without the necessity of reducing engine speed. In Uehling’s words, [a]s shown schematically in FIG. 3, the turbojet engine 10 is provided with a bypass pipe 24 having a valve 26 interposed therein. One end of the bypass pipe 24 is connected to the compressor 14 near its discharge end, and the valve 26 is actuated by the pilot to bleed off a certain percentage of compressor discharge air thereby reducing the mass flow though the combustion system 16 and the turbine 18. A portion of this bleed air is provided to a turbine cooling flow path 27 from which it is delivered to various components of the turbine 18 to cool the same. . . . . . . [T]he remaining portion of the bleed flow within the pipe 24 is piped from compressor discharge to the turbojet tail pipe 19 forward of the exhaust nozzle 20 and downstream of the turbine 18 . . . through thrust spoiling means, generally designed by the numeral 28, as shown in FIG. 3. As shown in both FIG. 3 and FIG. 4, the thrust spoiling means 28 take the form of a plurality of swirl inducing nozzles 30 positioned within a manifold 32, to which the bleed pipe 24 is connected. By means of the swirl inducing nozzles 30 the bleed flow is introduced into the tail pipe 19 so as to maximize swirl of the gas flowing within the tail pipe 19, thereby significantly increasing the tail pipe pressure and momentum losses and reducing the nozzle thrust coefficient, which, in turn, causes an instantaneous and additional increment of thrust reduction [column 3, line 54, through column 4, line 14]. Figure 3 shows Uehling’s bypass pipe 24, which channels cooling air from the compressor 14 to the turbine 18 via flow path 27, as communicating with the compressor at a position adjacent the tip clearance area of a row of rotating blades. As 4Page: Previous 1 2 3 4 5 6 7 8 9 10 NextLast modified: November 3, 2007