Gas turbine engine with improved cooling between turbine rotor disk elements

摘要

A gas turbine engine is provided comprising a forward rotor disk and blade assembly capable of rotating; an aft rotor disk and blade assembly capable of rotating; and a row of vanes positioned between the forward rotor disk and blade assembly and the aft rotor disk and blade assembly. The vane row and the forward rotor disk and blade assembly may define a forward cavity. The vane row may comprise at least one stator vane comprising: a main body and an inner shroud structure comprising a cover. The cover may include a first inner cavity receiving cooling air. The cover may further include at least one cooling flow passage. Cooling air flowing from the cooling flow passage has a tangential velocity component.

主权项

1. A gas turbine engine comprising:
a forward rotor disk and blade assembly capable of rotating; an aft rotor disk and blade assembly capable of rotating; and a row of vanes positioned between said forward rotor disk and blade assembly and said aft rotor disk and blade assembly; said vane row and said forward rotor disk and blade assembly defining a forward cavity; said vane row comprising at least one vane row segment; the at least one vane row segment comprising: a plurality of stator vanes each comprising a main body having a main body inner passage through which cooling air passes; and an inner shroud structure comprising a cover including a first inner cavity extending circumferentially between said vanes and in fluid communication with said main body inner passage of each of said vanes so as to receive cooling air from said vane main body inner passages, said cover further including a plurality of cooling flow passages extending from said first inner cavity to said forward cavity, wherein said cooling flow passages are configured such that cooling air flowing from said cooling flow passages has a tangential velocity component in a direction of rotation of said forward rotor disk and blade assembly.