FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engine building, in particular to gas turbine engine turbine cooling systems. Cooled gas turbine engine turbine comprises impeller with cooling air supply channels to working blades and swirl guide vanes. Between swirl guide vanes output and impeller disc circular cavity is formed, communicated with vaneless diffuser inlet, which outlet is communicated with cooling air to working blades supply channels. Vaneless diffuser is formed by impeller disc and two elements, movable and fixed. Movable element is located on larger radius relative to engine axis, and fixed element is on smaller. Fixed element lower part is fixed on swirl guide vanes housing, and movable element upper part is fixed on impeller disc. Between each other elements form annular gap equipped with moving seal.
EFFECT: invention enables to provide control over axial load acting on turbine.
1 cl, 1 dwg
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