Gas turbine engine having improved core system

Gas turbine engine having improved core system

  • CN 1,800,610 B
  • Filed: 09/15/2005
  • Issued: 12/31/2014
  • Est. Priority Date: 09/15/2004
  • Status: Active Grant
First Claim
Patent Images

1. one kind has longitudinal center'"'"'s axis (12) of extending there through and to circulate the gas turbine engine (44) run according to desirable Humphrey, comprising:

  • A () is positioned at the fan section (16) at the front end place of described gas turbine engine (44), it at least comprises the first fan blade be connected with the second live axle (40/62) and arranges;

    B () is located at the booster compressor (20) in the downstream of described fan section (16), it comprises multiple level, each described level comprises stationary compressor rows of blades, and is connected with the second live axle (40) or the first live axle (60) and the rotary blade for compressor interlaced with described stationary compressor rows of blades arranges;

    With,(c) combustion system (46), it is for producing the gas pulses (48) with the pressure and temperature of raising from the fluid stream (52) being supplied to its entrance (54) is middle;

    Wherein, for the entrance (54) of described combustion system provides first source of the gas (64) of pressurized air (52) from described booster compressor (20), and from described booster compressor (20), provide second source of the gas (66) of pressurized air (65) for cooling described combustion system (46), and, wherein, the pressurized air (65) from described second source of the gas (66) has the pressure larger than the pressurized air (52) from described first source of the gas (64).

View all claims
    ×
    ×

    Thank you for your feedback

    ×
    ×