초록 ▼

An improved gas turbine engine is disclosed. The engine includes counterrotating first and second turbine rotors without an intervening nozzle. Disclosed also are means for obtaining pitch relative outlet velocity greater than pitch absolute inlet velocity for at least one of the rotors. In one embo

An improved gas turbine engine is disclosed. The engine includes counterrotating first and second turbine rotors without an intervening nozzle. Disclosed also are means for obtaining pitch relative outlet velocity greater than pitch absolute inlet velocity for at least one of the rotors. In one embodiment, the reaction of at least one of the rotors is greater than a reference reaction effecting peak efficiency of the one turbine. Advantages include improved overall engine efficiency and decrease in weight, reduced cooling flow and complexity of the engine.

대표청구항 ▼

A gas turbine engine comprising: first means for compressing air; means for combusting compressed air received from said first compressing means with a fuel and generating combustion gases; a first turbine rotor including a plurality of first blades having hubs mounted to the circumference of a firs

A gas turbine engine comprising: first means for compressing air; means for combusting compressed air received from said first compressing means with a fuel and generating combustion gases; a first turbine rotor including a plurality of first blades having hubs mounted to the circumference of a first disk rotatable in a first direction, said first blades being in flow communication with said combustion means for receiving said combustion gases for rotating said first turbine rotor; means for joining said first compressing means to said first turbine rotor for rotation therewith; a second turbine rotor including a plurality of second blades having hubs mounted to the circumference of a second disk rotatable in a second direction being opposite to said first direction, said second blades being in direct flow communication with said first blades for receiving said combustion gases for rotating said second turbine rotor; and means for obtaining a pitch velocity (W2) of said gases at an outlet of and relative to said blades of at least one of said first and second turbine rotors which is greater than a pitch absolute velocity (C1) of said gases at an inlet of said blades of said one turbine rotor, said blades of said one turbine rotor having pitch chord stagger angles (Y) greater than 30 degrees.