Gas turbine engine
A gas turbine engine includes a cooling air supply passage that feeds air from a compressor, as a cooling medium, to a turbine by swirling the air in a circumferential direction. The cooling air supply passage includes an entry zone to which the air enters, and a swirl zone in which the air flowing past the entry zone is circumferentially redirected. The gas turbine engine also includes a chamber branching from the swirl zone to capture foreign particles in the air. The chamber is formed to meet the relation: α≥β where, when viewed in a radial direction, α is an angle defined by the swirl zone relative to a horizontal direction and β is an angle defined between the chamber and the swirl zone.
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.
2. The gas turbine engine as claimed in claim 1 , wherein the chamber comprises an orifice which is located at a downstream end of the chamber and regulates a flow rate of air exiting the chamber.
3. The gas turbine engine as claimed in claim 1 , wherein the pre-swirl nozzle member has a circular cavity formed therein to define the chamber.
4. 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; and
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,
wherein the chamber comprises a filter which captures the foreign particles flowing into the chamber while allowing air to pass through the filter.
5. The gas turbine engine as claimed in claim 4 , wherein the filter is detachably arranged for the chamber.