Abstract: A variable flow gas turbine engine of the type having a combustor for generating combustion gases and a turbine rotor for receiving and expanding the hot combustion gases, has an outer wall and an end wall defining a channel for directing the flow of combustion gases from the combustor to the rotor; a plurality of fixed guide vanes mounted in the channel, the space between adjacent vanes forming at least one throat; a winglet fixedly mounted in the throat for separating the gases flowing through the throat into first and second streams; and a passage through at least one of the vanes into the throat, the passage being in fluid communication with source of air under pressure for injecting high pressure into the throat for closing off the flow of combustion gases through the second stream. A method for varying the effective flow area of combustion gases in a gas turbine engine is also disclosed.

Abstract: A combustor for a gas turbine engine including a two-stage burner having first and second combustion and exhaust sections and a burner casing coaxially surrounding the burner to define an annular conduit for reverse flow of inlet air. The burner includes a fuel injector at the upstream end thereof, primary inlet ports introducing 18% of inlet air into the first combustion section, first cooling ports introducing 12% of inlet air into the first combustion section for generating a swirling cooling flow which mixes with primary air after cooling the upstream end of the first combustion section, secondary inlet ports introducing 18% of inlet air into second stage combustion section, second cooling ports introducing 8% of inlet air into the second combustion section to generate a swirling flow which mixes with primary air after cooling the upstream end of the second combustion section, and dilution ports introducing 44% of inlet air into the exhaust section to cool the exhaust gas.

Abstract: A variable flow gas turbine engine of the type having a combustor for generating combustion gases and a turbine rotor for receiving and expanding the hot combustion gases, has an outer wall and an end wall defining a channel for directing the flow of combustion gases from the combustor to the rotor; a plurality of fixed guide vanes mounted in the channel, the space between adjacent vanes forming at least one throat; a winglet fixedly mounted in the throat for separating the gases flowing through the throat into first and second streams; and a passage through at least one of the vanes into the throat, the passage being in fluid communication with source of air under pressure for injecting high pressure into the throat for varying the flow of combustion gases through the second stream. A method for varying the effective flow area of combustion gases in a gas turbine engine is also disclosed.

Abstract: A toroidally shaped double-walled gas-cooled inlet manifold for a radial in-flow turbine has a plurality of can-type combustors mounted on one axially facing side of the torous, arrays of coolant gas inlet holes in the outer wall located midway between the individual combustors, coolant gas inlet slots distributed circumferentially along the torous on the axial face mounting the combustors, and coolant gas inlet impingement orifices proximate the annular manifold exit duct on both axial facing sides of the outer wall. Annular coolant gas exit ports are provided surrounding the circular combustion gas inlet ducts from the individual combustors to induce a blanketing flow of coolant gas over the entire inner wall.

Abstract: Aerodynamically tapered spike is positioned for controlled axial movement in the conical portion of a composite gas turbine engine diffuser controlling engine air mass flow rate by adjusting diffuser area ratio. Also, a straight pipe transition diffuser portion is positioned between the conical portion and a flat plate diffuser portion to flatten the velocity profile.

Abstract: A composite diffuser for a radial compressor has a straight pipe transition portion positioned between a conically diverging upstream portion and a downstream flat plate diffuser portion to flatten the velocity profile prior to entrance into the plate diffuser portion.