GAS TURBINE ENGINE GAS GENERATOR Russian patent published in 2016 - IPC F01D5/08 F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: high-temperature gas turbine engine gas generator includes centrifugal impeller wheel, diffuser-rectifier, separated from latter by radial annular gap cavity and having annular flange in its lower part, rear power housing, combustion chamber and high pressure turbine. Rear power housing is installed at impeller output with required axial annular gap between impeller rear side and fairing, forming axial annular gap cavity. Axial annular gap cavity between impeller rear side and fairing and rear power housing inner cavity are interconnected with radial annular gap cavity between impeller and diffuser at inlet and combined by common cavity at outlet. Combustion chamber secondary air zone is restricted at bottom by rear power housing and connected with it inner housing, attached to cocurrent swirl device and having annular flange. High-pressure turbine comprises nozzle assembly, resting from below on inner housing annular flange, and impeller with cooled working blades and discs, main and covering, make annular chamber between each other, communicated with working blades inner cavities. Covering disc has no holes and booster blades on its web and attached to main disk rim part with formation of circular cavity between them connected at outlet with working blades internal cavities, and at inlet forming radial annular gap between each other. Inlet to radial annular gap is connected to axial annular gap cavity by annular channel, which inner surface is limited by impeller rear side, and outer is by fairing adjacent to conical shell lower flange, and inner housing lower flange, at joint between which tangential cocurrent swirl device is arranged. Tangential cocurrent swirl device nozzles are arranged in radial plane and communicated with annular channel at outlet, providing input of high-energy air flow from combustion chamber secondary air zone directly into annular channel. Axial clearance between inner housing lower flange and covering disc is sealed.

EFFECT: invention enables to increase impeller service life due to reduction of its rear side temperature and cyclic durability of turbine covering disc due to exclusion of holes and booster blades on its web.

1 cl, 2 dwg