Gas turbine engine
AssigneeGeneral Electric Company
InventorsRollin G. Giffin, III, Dean T. Lenahan
Life of this patent
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Abstract
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.
Claims74
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 (W.sub.2) 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 (C.sub.1) 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.
A gas turbine engine comprising:
- first means for compressing air;
- second means for compressing air disposed upstream of and in flow communication with said first compressing means;
- means for combusting compressed air received from said first compressing means with a fuel and generating combustion gases;
- a first stationary nozzle disposed downstream of and in flow communication with said combusting means;
- a first turbine rotor including a plurality of first blades having hubs mounted to the circumference of a first disk and rotatable in a first direction, said first blades being in flow communication with said first nozzle for receiving said combustion gases for rotating said first turbine, said first nozzle and first turbine rotor defining a first turbine stage;
- 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 and 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;
- means for joining said second compressing means to said second turbine for rotation therewith;
- means for obtaining a pitch velocity (W.sub.2) 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 (C.sub.1) of said gases at an inlet of said blades of said at least one turbine rotor;
- first reaction means for obtaining a first pitch reaction R.sub.1 of said first turbine rotor comprising a predetermined shape of said first turbine blades, and said first reaction R.sub.1 representing the percent static enthalpy drop of said gases flowing through said first turbine stage occurring in said first turbine rotor;
- second reaction means for obtaining a second pitch reaction R.sub.2 of said second turbine rotor comprising a predetermined shape and orientation of said second turbine blades;
- and
- at least one of said first and second reactions R.sub.1 and R.sub.2 being greater than a reference pitch reaction effecting a peak efficiency for said first and second turbine rotors, respectively.
A turbine blade for a gas turbine engine having first and second adjacent counterrotating turbine rotors, the first rotor being rotatably connected to compressing means, at least one of said first and second turbine rotors including a plurality of said blades, each having leading and trailing edges, adjacent ones of said blades being spaced from each other for defining an inlet for receiving combustion gases and an outlet for discharging said gases, said blade further including means for obtaining a pitch velocity (W.sub.2) of said gases at said outlet and relative to said blade which is greater than a pitch absolute velocity (C.sub.1) of said gases at said inlet, said blade having a pitch chord stagger angle (Y) greater than 30 degrees.
A gas turbine engine comprising:
- a first turbine rotor including a plurality of first blades having hubs mounted to the circumference of a first annular member rotatable in a first direction, said first blades being in flow communication with combustion means for receiving combustion gases therefrom for rotating said first turbine rotor;
- a second turbine rotor including a plurality of second blades having hubs mounted to the circumference of a second annular member 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;
- means for obtaining a pitch velocity (W.sub.2) 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 (C.sub.1) of said gases at an inlet of said blades of said one turbine rotor;
- and
- said velocity obtaining means further including means for obtaining a pitch reaction of said one turbine rotor greater than a reference pitch reaction effecting a peak efficiency for a corresponding turbine stage.
A turbine blade for a gas turbine engine having a turbine rotor including a plurality of said blades each having leading and trailing edges, adjacent ones of said blades being spaced from each other for defining an inlet for receiving combustion gases and an outlet for discharging said gases, said blade further including means for obtaining a pitch velocity (W.sub.2) of said gases at said outlet and relative to said blade which is greater than a pitch absolute velocity (C.sub.1) of said gases at said inlet;
- and
- said velocity obtaining means further including means for obtaining a pitch reaction of said turbine rotor greater than a reference pitch reaction effecting a peak efficiency for a corresponding turbine stage.
Dependencies are inferred from the claim text.