Gas turbine engine having improved core system

Gas turbine engine having improved core system

  • CN 1,800,610 A
  • Filed: 09/15/2005
  • Published: 07/12/2006
  • Est. Priority Date: 09/15/2004
  • Status: Active Grant
First Claim
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1. gas turbine engine (44) with the longitudinal center'"'"'s axis (12) that therefrom passes comprising:

  • (a) be positioned at the fan part (16) at the front end place of described gas turbine engine (44), it comprises that at least first fan blade that links to each other with live axle (40/62) is listed as;

    (b) be located at the partly booster compressor (20) in the downstream of (16) of described fan, it comprises a plurality of levels, each described level all comprises the stationary compressor rows of blades, and link to each other with live axle (40/60) links to each other and is listed as with the interlaced rotary blade for compressor of described stationary compressor rows of blades;

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

    Wherein, first source of the gas (64) of pressurized air (52) is provided for the inlet of described combustion system (54) from described booster compressor (20), and from described booster compressor (20), provides second source of the gas (66) of pressurized air (65) to be used to cool off described combustion system (46).

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