CPC F01D 5/081 (2013.01) [F02C 7/18 (2013.01); F02C 7/05 (2013.01); F02C 7/052 (2013.01); F05D 2260/232 (2013.01); F05D 2260/607 (2013.01); F23R 3/14 (2013.01)] | 5 Claims |
1. A gas turbine engine comprising:
a compressor which pressurizes air taken in from an ambient environment;
a combustor which combusts an air-fuel mixture containing a fuel and the air pressurized by the compressor;
a turbine powered by combustion gas produced by the combustor;
a cooling air supply passage which feeds the air from the compressor, as a cooling medium, to the turbine by swirling the air in a circumferential direction, the cooling air supply passage including:
an entry zone to which the air enters; and
a swirl zone in which the air flowing past the entry zone is circumferentially redirected with respect to an engine rotational axis;
a chamber which branches from the swirl zone and captures foreign particles in the air, the chamber being formed to meet the relation: α≥β where, when viewed in a radial direction with respect to the engine rotational axis, α is an angle defined by the swirl zone relative to an entry direction and β is an angle defined between the chamber and the swirl zone; and
a pre-swirl nozzle member including a ring-shaped block element in which a plurality of cooling air supply bores defining the cooling air supply passage are formed, such that the chamber is defined in the pre-swirl nozzle member.
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