Gas Turbine Engine Having A Flow Control Surface With A Cooling Conduit

Abstract: The invention relates to a gas turbine engine [10] comprising a casing [46] having a compressor section [22], combustion section [28] and turbine section [32], axially arranged in a flow direction about a rotational axis [12] of the engine [10]. The engine [10] includes a rotor [51] located within the casing [46] and rotatable about the rotational axis [12], including multiple sets of circumferentially arranged blades [56, 58], with at least one set corresponding to the compressor section [22] and another set corresponding to the turbine section [32]. The engine [10] also includes a set of vanes [60, 62, 63] circumferentially arranged about the rotational axis [12] and at a location upstream of the combustion section [28], with the vanes [60, 62, 63] having a pressure side and a suction side. The engine [10] further includes a cooling conduit [120] extending from upstream of the combustion section [28] to downstream of the combustion section [28], with an inlet [118] located on the suction side of at least one of the vanes [60, 62, 63] which allows cooling air [94] to enter the inlet [118] and is directed through the cooling conduit [120] for cooling. FIG. 1

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