FIELD: mechanical engineering; engines. SUBSTANCE: proposed gas turbine engine has compressor with impeller provided with rear surface and end part arranged in housing, shaft, section, combustion chambers and space formed inside said engine housing and limited at least partially by rear surface of impeller and arranged in area of end part. Gas flow in end part of impeller has tangential component of velocity relative to axis within the limits of space. Gas turbine engine has also outlet arrangement to control compressed gas flow in combustion chamber, reduce tangential component of velocity of gas flow from end part of impeller in said space, create in this space compression from gas flows from end part of impeller and outlet arrangement and create load on rear part of impeller through shaft onto thrust bearing. Outlet arrangement is located on path of flow between space and section of combustion chamber. EFFECT: improved adjustment of load on thrust bearing. 6 cl, 5 dwg
