GAS TURBINE ENGINE Russian patent published in 2002 - IPC

FIELD: mechanical engineering. SUBSTANCE: invention is designed for devices organizing operation of seals separating dummy spaces from other spaces at non- stationary modes of operation. With engine operating at non-stationary modes, radial clearances between teeth and their mating members increase. Simultaneously, radial clearance between back tooth and additional back member decreases by the same value. It means that increase in passage area determining leaks past teeth is compensated by decrease in passage area and leaks past back tooth. On the other hand, pressure of cooling air in common space by front dummy space and ring air duct is completely determined by gas pressure in turbine blading which provides stability of turbine pressure at specific mode of operation leading, in its turn, to stability of axial load at the mode. Stabilization of axial loads on compressor and turbine leads to stabilization of axial load on radial-thrust bearing. Constant cooling air pressure differential in swirling device is set corresponding to specific mode of engine operation which provides stability of cooling air flow rate. Such design of device makes it possible to stabilize axial loads of turbocompressor at non-stationary modes of operation by stabilizing air pressure in dummy space of compressor and front dummy space of compressor and front dummy space of turbine. EFFECT: preservation and even increase in energy saving at non-stationary modes of operation. 6 cl, 4 dwg